TO 1-1-691sbe85fe43e9b86f2d.jimcontent.com/download/version... · TO 1-1-691 TECHNICAL MANUAL CLEANING AND CORROSION PREVENTION AND CONTROL, AEROSPACE AND NON-AEROSPACE EQUIPMENT

TO 1-1-691TECHNICAL MANUAL

CLEANING AND CORROSION PREVENTIONAND CONTROL,

AEROSPACE AND NON-AEROSPACE EQUIPMENTF42620-00-D-0038FA8501-05-D-0002

DISTRIBUTION STATEMENT A - Approved for public release; distribution is unlimited (WR-ALC/PA Public Affairs Certification NumberPA04-11-96). Other request for this document shall be referred to 584 CBSS/GBHDE, Robins AFB, GA 31098. Questions concerning technicalcontent shall be referred to AFRL/MLS-OLR.

Published Under Authority of the Secretary of the Air Force.

1 JULY 2003 CHANGE 1 - 15 OCTOBER 2006

Dates of issue for original and changed pages are:

Original . . . . . . . .0 . . . . . . . .1 July 2003 Change . . . . . . 1 . . . . . . 15 October 2006

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 350 CONSISTING OF THE FOLLOWING:

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Title . . . . . . . . . . . . . . . . . . . . . 1A . . . . . . . . . . . . . . . . . . . . . . . 1i - vii . . . . . . . . . . . . . . . . . . . . 1viii Blank. . . . . . . . . . . . . . . . . . 0ix . . . . . . . . . . . . . . . . . . . . . . . 1x . . . . . . . . . . . . . . . . . . . . . . . 0xi - xii . . . . . . . . . . . . . . . . . . . 1xiii . . . . . . . . . . . . . . . . . . . . . . 0xiv Blank. . . . . . . . . . . . . . . . . . 01-1 . . . . . . . . . . . . . . . . . . . . . . 11-2 . . . . . . . . . . . . . . . . . . . . . . 02-1 . . . . . . . . . . . . . . . . . . . . . . 12-2 - 2-20 . . . . . . . . . . . . . . . . . 02-21 . . . . . . . . . . . . . . . . . . . . . 12-22 . . . . . . . . . . . . . . . . . . . . . 03-1 - 3-12 . . . . . . . . . . . . . . . . . 13-13 - 3-14 . . . . . . . . . . . . . . . . 03-15 - 3-28 . . . . . . . . . . . . . . . . 13-28.1 Added . . . . . . . . . . . . . . . 13-28.2 Blank. . . . . . . . . . . . . . . . 13-29 - 3-33 . . . . . . . . . . . . . . . . 03-34 - 3-36 . . . . . . . . . . . . . . . . 13-37 . . . . . . . . . . . . . . . . . . . . . 03-38 - 3-41 . . . . . . . . . . . . . . . . 13-42 . . . . . . . . . . . . . . . . . . . . . 03-43 . . . . . . . . . . . . . . . . . . . . . 13-44 - 3-45 . . . . . . . . . . . . . . . . 03-46 - 3-48 . . . . . . . . . . . . . . . . 13-49 . . . . . . . . . . . . . . . . . . . . . 03-50 - 3-51 . . . . . . . . . . . . . . . . 13-52 . . . . . . . . . . . . . . . . . . . . . 03-53 - 3-61 . . . . . . . . . . . . . . . . 13-62 . . . . . . . . . . . . . . . . . . . . . 04-1 - 4-2. . . . . . . . . . . . . . . . . . 14-3 - 4-4. . . . . . . . . . . . . . . . . . 04-5 - 4-6. . . . . . . . . . . . . . . . . . 14-7 - 4-8. . . . . . . . . . . . . . . . . . 04-9 . . . . . . . . . . . . . . . . . . . . . . 14-10 - 4-13 . . . . . . . . . . . . . . . . 04-14 - 4-15 . . . . . . . . . . . . . . . . 14-16 - 4-18 . . . . . . . . . . . . . . . . 05-1 - 5-2. . . . . . . . . . . . . . . . . . 15-3 - 5-11 . . . . . . . . . . . . . . . . . 05-12 - 5-14 . . . . . . . . . . . . . . . . 15-15 - 5-16 . . . . . . . . . . . . . . . . 05-17 - 5-23 . . . . . . . . . . . . . . . . 1

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A-26 - A-46 . . . . . . . . . . . . . . . 0B-1 . . . . . . . . . . . . . . . . . . . . . . 0B-2 - B-3 . . . . . . . . . . . . . . . . . 1B-4 - B-5 . . . . . . . . . . . . . . . . . 0B-6 - B-9 . . . . . . . . . . . . . . . . . 1B-10 - B-15. . . . . . . . . . . . . . . . 0B-16 . . . . . . . . . . . . . . . . . . . . . 1B-17 . . . . . . . . . . . . . . . . . . . . . 0B-18 - B-19. . . . . . . . . . . . . . . . 1B-20 - B-22. . . . . . . . . . . . . . . . 0B-23 . . . . . . . . . . . . . . . . . . . . . 1B-24 - B-33. . . . . . . . . . . . . . . . 0B-34 - B-39. . . . . . . . . . . . . . . . 1B-40 - B-42. . . . . . . . . . . . . . . . 0Glossary 1 . . . . . . . . . . . . . . . . . 1Glossary 2 - Glossary 4. . . . . . . . 0Index 1 . . . . . . . . . . . . . . . . . . . 0Index 2 . . . . . . . . . . . . . . . . . . . 1Index 3 . . . . . . . . . . . . . . . . . . . 0Index 4 - Index 6. . . . . . . . . . . . 1Index 6.1 Added . . . . . . . . . . . . . 1Index 6.2 Blank . . . . . . . . . . . . . 1Index 7 - Index 8. . . . . . . . . . . . 0

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LIST OF EFFECTIVE PAGESINSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

NOTE The portion of the text affected by the changes is indicated by a vertical line in the outer margin ofthe page. Changes to illustrations are indicated by shaded or screened areas, or by miniaturepointing hands.

* Zero in this column indicates an original page.

USAFA Change 1

TABLE OF CONTENTS

Chapter Page Chapter Page

LIST OF ILLUSTRATIONS . . . . . . . . . . . vi

LIST OF TABLES . . . . . . . . . . . . . . . . . . vii

FOREWORD . . . . . . . . . . . . . . . . . . . . . ix

SAFETY SUMMARY . . . . . . . . . . . . . . . xiii

1 INTRODUCTION . . . . . . . . . . . . . . . . . . 1-1

1.1 CORROSION CONTROL PRO-GRAM . . . . . . . . . . . . . . . . . . 1-1

1.1.1 Training . . . . . . . . . . . . . . . . . . . 1-11.1.2 Maintenance . . . . . . . . . . . . . . . . 1-11.1.3 Facilities . . . . . . . . . . . . . . . . . . . 1-11.2 SAFETY . . . . . . . . . . . . . . . . . . 1-11.2.1 Responsibility of Supervisors . . . . . 1-11.2.2 Materials Handling . . . . . . . . . . . . 1-11.3 MATERIALS . . . . . . . . . . . . . . . 1-2

2 CORROSION THEORY . . . . . . . . . . . . . . 2-1

2.1 INTRODUCTION TO CORROSIONTHEORY . . . . . . . . . . . . . . . . 2-1

2.2 DEFINITION OF CORROSION . . 2-12.3 CHEMICAL DEFINITIONS . . . . . 2-12.3.1 Atom . . . . . . . . . . . . . . . . . . . . . 2-12.3.2 Electron . . . . . . . . . . . . . . . . . . . 2-12.3.3 Ions . . . . . . . . . . . . . . . . . . . . . . 2-12.3.4 Electrolyte . . . . . . . . . . . . . . . . . 2-12.4 THEORY OF CORROSION . . . . . 2-12.4.1 Anode . . . . . . . . . . . . . . . . . . . . 2-12.4.2 Cathode . . . . . . . . . . . . . . . . . . . 2-12.4.3 Electrolyte . . . . . . . . . . . . . . . . . 2-12.4.4 Electrical contact . . . . . . . . . . . . . 2-12.5 DEVELOPMENT OF CORRO-

SION . . . . . . . . . . . . . . . . . . . 2-22.5.1 Corrosion Under Painted Surfaces . . 2-22.6 FACTORS INFLUENCE CORRO-

SION . . . . . . . . . . . . . . . . . . . 2-22.6.1 Type of Metal . . . . . . . . . . . . . . . 2-32.6.2 Dissimilar Metal Coupling (Galvanic

Corrosion) . . . . . . . . . . . . . . . . 2-32.6.3 Anode and Cathode Surface Area . . 2-42.6.4 Temperature . . . . . . . . . . . . . . . . 2-42.6.5 Heat Treatment and Grain Direc-

tion . . . . . . . . . . . . . . . . . . . . 2-42.6.6 Electrolytes . . . . . . . . . . . . . . . . . 2-42.6.7 Oxygen . . . . . . . . . . . . . . . . . . . 2-42.6.8 Electrolyte Concentration . . . . . . . 2-52.6.9 Biological Organisms . . . . . . . . . . 2-52.6.10 Mechanical Stress . . . . . . . . . . . . 2-5

2.6.11 Time . . . . . . . . . . . . . . . . . . . . . 2-52.7 TYPES OF CORROSION . . . . . . . 2-52.7.1 Uniform Surface Corrosion . . . . . . 2-52.7.2 Galvanic Corrosion . . . . . . . . . . . . 2-52.7.3 Pitting Corrosion . . . . . . . . . . . . . 2-62.7.4 Intergranular Corrosion . . . . . . . . . 2-62.7.5 Exfoliation Corrosion . . . . . . . . . . 2-62.7.6 Crevice/Concentration Cell Corro-

sion . . . . . . . . . . . . . . . . . . . . 2-72.7.7 Corrosion Fatigue . . . . . . . . . . . . . 2-112.7.8 Filiform Corrosion . . . . . . . . . . . . 2-112.7.9 Fretting Corrosion . . . . . . . . . . . . 2-122.7.10 High Temperature Oxidation (Hot

Corrosion) . . . . . . . . . . . . . . . . 2-122.8 METALS AFFECTED BY CORRO-

SION . . . . . . . . . . . . . . . . . . . 2-122.8.1 Magnesium . . . . . . . . . . . . . . . . . 2-122.8.2 Steel . . . . . . . . . . . . . . . . . . . . . 2-132.8.3 Aluminum . . . . . . . . . . . . . . . . . . 2-132.8.4 Anodized Aluminum . . . . . . . . . . . 2-172.8.5 Titanium . . . . . . . . . . . . . . . . . . . 2-172.8.6 Copper and Copper Alloys . . . . . . . 2-172.8.7 Cadmium . . . . . . . . . . . . . . . . . . 2-172.8.8 CRES/Stainless Steel . . . . . . . . . . 2-172.8.9 Nickel and Chromium . . . . . . . . . . 2-182.8.10 Silver, Platinum, and Gold . . . . . . . 2-182.8.11 Graphite/Carbon Fiber Composites . 2-182.9 CORROSIVE ENVIRONMENTS . . 2-192.9.1 Moisture . . . . . . . . . . . . . . . . . . . 2-192.9.2 Temperature . . . . . . . . . . . . . . . . 2-192.9.3 Salt Atmospheres . . . . . . . . . . . . . 2-192.9.4 Ozone . . . . . . . . . . . . . . . . . . . . 2-192.9.5 Other Industrial Pollutants . . . . . . . 2-192.9.6 Sand, Dust, and Volcanic Ash . . . . 2-192.9.7 Solar Radiation . . . . . . . . . . . . . . 2-202.9.8 Climate . . . . . . . . . . . . . . . . . . . 2-202.9.9 Factors of Influence in Tropical En-

vironments . . . . . . . . . . . . . . . 2-202.9.10 Manufacturing . . . . . . . . . . . . . . . 2-202.9.11 Storage . . . . . . . . . . . . . . . . . . . . 2-212.9.12 Shipment . . . . . . . . . . . . . . . . . . 2-212.9.13 Industrial and Ship Emitted Air Pol-

lutants . . . . . . . . . . . . . . . . . . 2-212.9.14 Animal Damage . . . . . . . . . . . . . . 2-212.9.15 Micro-Organisms . . . . . . . . . . . . . 2-212.10 DEGRADATION OF NON-

METALS . . . . . . . . . . . . . . . . 2-222.11 PREVENTIVE MAINTENANCE . . 2-22

3 PREVENTIVE MAINTENANCE . . . . . . . . 3-1

SECTION I INTRODUCTION . . . . . . . . 3-1

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Change 1 i

3.1 PREVENTIVE MAINTENANCEPROGRAM . . . . . . . . . . . . . . . 3-1

3.1.1 Preventive Maintenance . . . . . . . . 3-1

SECTION II CLEANING . . . . . . . . . . . . 3-7

3.2 INTRODUCTION . . . . . . . . . . . . 3-73.2.1 Reasons for Cleaning . . . . . . . . . . 3-73.2.2 When to Accomplish Work . . . . . . 3-73.2.3 Aircraft Clear Water Rinse Require-

ments . . . . . . . . . . . . . . . . . . . 3-83.2.4 Immediate Cleaning . . . . . . . . . . . 3-83.3 CLEANING COMPOUNDS . . . . . 3-93.3.1 Alkaline Cleaners . . . . . . . . . . . . . 3-93.3.2 Solvent Emulsion and Aqueous

Cleaners for Turbine Engine GasPath and General Area Cleaning . 3-10

3.3.3 Aqueous Parts Washer Cleaning So-lutions . . . . . . . . . . . . . . . . . . 3-10

3.3.4 Solvents . . . . . . . . . . . . . . . . . . . 3-113.3.5 Miscellaneous Cleaning Agents . . . 3-113.3.6 Steam Cleaning . . . . . . . . . . . . . . 3-123.3.7 Dilution . . . . . . . . . . . . . . . . . . . 3-123.4 CLEANING EQUIPMENT . . . . . . 3-293.4.1 High Pressure/Hot Water Wash

Equipment . . . . . . . . . . . . . . . 3-293.4.2 Portable, 15 Gallon, Foam Generat-

ing, Cleaning Unit . . . . . . . . . . 3-293.4.3 Portable, 45 Gallon, Foam Generat-

ing Cleaning Unit . . . . . . . . . . . 3-303.4.4 Turbine Engine Compressor Clean-

ing Equipment . . . . . . . . . . . . . 3-343.4.5 Miscellaneous Large Cleaning

Equipment . . . . . . . . . . . . . . . 3-343.4.6 Spray Cleaning Guns for Solvents . 3-343.4.7 Pneumatic Vacuum Cleaner . . . . . . 3-343.4.8 Universal Wash Unit . . . . . . . . . . . 3-343.4.9 Aqueous Parts Washers . . . . . . . . . 3-343.4.10 Miscellaneous Equipment . . . . . . . 3-363.5 CLEANING PROCEDURES . . . . . 3-373.5.1 Warnings and Cautions . . . . . . . . . 3-373.5.2 Cleaning Methods . . . . . . . . . . . . 3-403.5.3 Clear Water Rinsing of Aircraft . . . 3-473.5.4 Post Cleaning Procedures . . . . . . . 3-473.5.5 Treatment and Disposal of Wash

Rack Waste . . . . . . . . . . . . . . . 3-483.5.6 Fungus Growth Removal . . . . . . . . 3-483.5.7 Soil Barriers . . . . . . . . . . . . . . . . 3-49

SECTION III LUBRICATION . . . . . . . . . 3-50

3.6 INTRODUCTION . . . . . . . . . . . . 3-503.6.1 Conventional Lubricants . . . . . . . . 3-503.6.2 Solid Film Lubricants . . . . . . . . . . 3-503.6.3 Application of Conventional Lubri-

cants . . . . . . . . . . . . . . . . . . . 3-51

SECTION IV PRESERVATION . . . . . . . . 3-53

3.7 INTRODUCTION . . . . . . . . . . . . 3-533.7.1 Operational Preservation . . . . . . . . 3-533.7.2 Non-Operational Preservation . . . . . 3-533.7.3 Types of CPC’s . . . . . . . . . . . . . . 3-533.7.4 Time Limitations of CPC’s . . . . . . 3-533.7.5 Description of CPC’s . . . . . . . . . . 3-563.7.6 Preservation of Speci c Areas . . . . 3-613.7.7 Preservation Application Methods . . 3-613.8 APPLICATION OF POLISH AND

WAX . . . . . . . . . . . . . . . . . . . 3-62

4 INSPECTION AND CORROSION PRONEAREAS . . . . . . . . . . . . . . . . . . . . . . . 4-1

SECTION I INSPECTION . . . . . . . . . . . 4-1

4.1 Purpose . . . . . . . . . . . . . . . . . . . 4-14.1.1 Responsibility . . . . . . . . . . . . . . . 4-14.1.2 Frequency of Inspections . . . . . . . . 4-14.1.3 General Inspections . . . . . . . . . . . 4-14.1.4 Detailed Inspections . . . . . . . . . . . 4-14.2 INSPECTION METHODS . . . . . . 4-14.2.1 Visual inspection . . . . . . . . . . . . . 4-14.2.2 Depth Gauge . . . . . . . . . . . . . . . . 4-24.2.3 Visual Inspection with a Borescope . 4-44.2.4 Optical Depth Micrometers. . . . . . . 4-44.2.5 Fluorescent Penetrant Inspection . . . 4-54.2.6 Eddy Current Inspection . . . . . . . . 4-64.2.7 Ultrasonic Inspection . . . . . . . . . . 4-64.2.8 Radiographic Inspection . . . . . . . . 4-64.3 EVALUATION OF CORROSION

DAMAGE . . . . . . . . . . . . . . . 4-84.4 DEGREES OF CORROSION . . . . 4-94.4.1 Light Corrosion . . . . . . . . . . . . . . 4-94.4.2 Moderate Corrosion . . . . . . . . . . . 4-94.4.3 Severe Corrosion . . . . . . . . . . . . . 4-9

SECTION II CORROSION PRONE AR-EAS . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9

4.5 COMMON AREAS . . . . . . . . . . . 4-94.5.1 Fasteners . . . . . . . . . . . . . . . . . . 4-94.5.2 Faying Surfaces and Crevices . . . . 4-104.5.3 Spot-Welded Assemblies . . . . . . . . 4-104.5.4 Engine Exhaust and Gun Gas Im-

pingement Areas . . . . . . . . . . . 4-114.5.5 Wheel Wells and Landing Gear . . . 4-114.5.6 Flap and Slat Recesses . . . . . . . . . 4-114.5.7 Engine Frontal Areas and Air Inlet

Ducts . . . . . . . . . . . . . . . . . . . 4-124.5.8 Wing/Fin-Fold Joints and Wing and

Control Surface Leading Edges . 4-144.5.9 Hinges . . . . . . . . . . . . . . . . . . . . 4-14

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TABLE OF CONTENTS - CONTINUED


ii Change 1

4.5.10 Control Cables . . . . . . . . . . . . . . . 4-144.5.11 Relief Tube Outlets . . . . . . . . . . . 4-144.5.12 Water Entrapment Areas . . . . . . . . 4-144.5.13 Bilge Areas . . . . . . . . . . . . . . . . . 4-144.5.14 Battery Compartments and Battery

Vent Openings . . . . . . . . . . . . . 4-144.5.15 Magnesium Parts . . . . . . . . . . . . . 4-154.5.16 Electrical Connectors and Other

Components . . . . . . . . . . . . . . 4-15

5 CORROSION REMOVAL AND SURFACETREATMENT . . . . . . . . . . . . . . . . . . . 5-1

SECTION I CORROSION REMOVAL . . 5-1

5.1 PURPOSE . . . . . . . . . . . . . . . . . 5-15.2 RESPONSIBILITY . . . . . . . . . . . 5-15.3 CORRECTIVE ACTIONS . . . . . . . 5-15.4 PAINT REMOVAL . . . . . . . . . . . 5-15.5 CORROSION REMOVAL . . . . . . . 5-15.5.1 Mechanical Methods . . . . . . . . . . . 5-25.5.2 Non-Powered Tools and Materials . 5-25.5.3 Power Tools and Materials . . . . . . 5-45.5.4 Abrasive Blasting . . . . . . . . . . . . . 5-95.6 SURFACE FINISH . . . . . . . . . . . 5-135.7 Pitting on Critical Structure . . . . . . 5-135.8 CORROSION REMOVAL

PROCEDURES-MECHANICAL . . . . . . . . . . . . 5-13

5.8.1 Warnings and Cautions . . . . . . . . . 5-135.8.2 Non-Powered Mechanical Corrosion

Removal . . . . . . . . . . . . . . . . . 5-165.8.3 Powered Mechanical Corrosion Re-

moval . . . . . . . . . . . . . . . . . . . 5-175.8.4 Abrasive Blasting Corrosion Re-

moval . . . . . . . . . . . . . . . . . . . 5-175.9 CORROSION REMOVAL-

CHEMICAL . . . . . . . . . . . . . . 5-185.9.1 Aluminum Alloys . . . . . . . . . . . . . 5-185.9.2 Magnesium Alloys . . . . . . . . . . . . 5-225.9.3 Ferrous Metal (Steel) Alloys Other

Than Stainless Steels (Cres) . . . . 5-235.9.4 Stainless Steel (Cres) And Nickel

Based Alloys . . . . . . . . . . . . . . 5-275.9.5 Copper And Copper Based Alloys . . 5-315.9.6 Titanium and Titanium Based Al-

loys . . . . . . . . . . . . . . . . . . . . 5-335.9.7 Plated And Phosphated Surfaces . . . 5-35

SECTION II SURFACE TREATMENT . . . 5-37

5.10 PURPOSE . . . . . . . . . . . . . . . . . 5-375.10.1 Chemical Prepaint Treatments . . . . 5-375.10.2 Surface Preparation . . . . . . . . . . . 5-395.10.3 Precautions . . . . . . . . . . . . . . . . . 5-405.10.4 Application of Surface Treatments . 5-40

5.10.5 Notes on Conversion Coating/Sur-face Treatment . . . . . . . . . . . . . 5-41

5.10.6 Post Treatment . . . . . . . . . . . . . . . 5-425.10.7 Temporary Preservation . . . . . . . . . 5-42

SECTION III SHOT PEENING/ROTO-PEENING . . . . . . . . . . . . . . . . . . . . . . 5-44

5.11 PEENING OF METAL SUR-FACES . . . . . . . . . . . . . . . . . . 5-44

5.11.1 Types of Peening . . . . . . . . . . . . . 5-445.11.2 Roto-Peening (Rotary Flap Peening)

Procedures . . . . . . . . . . . . . . . 5-45

6 SEALANTS . . . . . . . . . . . . . . . . . . . . . . 6-1

6.1 PURPOSE . . . . . . . . . . . . . . . . . 6-16.2 APPLICATIONS . . . . . . . . . . . . . 6-16.3 SEALING COMPOUNDS . . . . . . . 6-16.3.1 Sealant Packaging . . . . . . . . . . . . 6-16.3.2 Polysul de, Polyurethane, and Poly-

thioether Sealing Compounds . . . 6-16.3.3 Silicone Sealing Compounds . . . . . 6-26.3.4 Adhesion Promoters . . . . . . . . . . . 6-116.3.5 SAE AMS 3255 Oil and Water Re-

sistant, Expanded Polytetra uoro-ethylene Sealing Tape (EPTFE)Sky ex . . . . . . . . . . . . . . . . . . 6-11

6.3.6 Av-Dec® Polyurethane SealantTapes and Two Component Seal-ants . . . . . . . . . . . . . . . . . . . . 6-11

6.4 EQUIPMENT . . . . . . . . . . . . . . . 6-116.4.1 Sealant Gun . . . . . . . . . . . . . . . . 6-116.4.2 Application Nozzles . . . . . . . . . . . 6-116.4.3 Injection Gun . . . . . . . . . . . . . . . 6-116.4.4 Sealant Kits (Semkits®) . . . . . . . . 6-176.4.5 Sealant Removal and Application

Tools . . . . . . . . . . . . . . . . . . . 6-176.5 SEALANT MIXING . . . . . . . . . . 6-186.5.1 Application Life . . . . . . . . . . . . . . 6-196.5.2 Storage Instructions . . . . . . . . . . . 6-22.16.5.3 Mixing MIL-PRF-81733, Type III

Spray-able Sealant Coating . . . . 6-22.16.6 SEALANT APPLICATION PROCE-

DURES . . . . . . . . . . . . . . . . . 6-22.16.6.1 Cleaning . . . . . . . . . . . . . . . . . . . 6-236.6.2 Masking . . . . . . . . . . . . . . . . . . . 6-236.6.3 Adhesion Promoters . . . . . . . . . . . 6-236.6.4 Brush Spatula or Caulking Gun Ap-

plication . . . . . . . . . . . . . . . . . 6-236.6.5 Spray Gun Application . . . . . . . . . 6-246.6.6 Peel and Stick Application; AMS

3255 EPTFE Sky ex® and Av-Dec® HT3935-7 and HT3000Sealing Tapes . . . . . . . . . . . . . 6-24

6.7 SEALING OF SPECIFIC AREAS . 6-25

TO 1-1-691



Change 1 iii

6.7.1 Faying Surface Sealing . . . . . . . . . 6-256.7.2 Fillet Sealing . . . . . . . . . . . . . . . . 6-266.7.3 Injection Sealing . . . . . . . . . . . . . 6-266.7.4 Fastener Sealing . . . . . . . . . . . . . . 6-266.7.5 Integral Fuel Cells/Tanks and Re-

movable Fuel Tanks . . . . . . . . . 6-276.7.6 Form-In-Place (FIP) Gasket Sealant

Repair . . . . . . . . . . . . . . . . . . 6-276.7.7 SAE AMS 3255 EPTFE (Sky ex®)

and Av-Dec® HT3000 andHT3935-7 Sealing Tape GasketRepair . . . . . . . . . . . . . . . . . . 6-27

6.7.8 External Aircraft Structure . . . . . . . 6-296.7.9 Depressions . . . . . . . . . . . . . . . . . 6-296.7.10 Damaged Sealant . . . . . . . . . . . . . 6-296.7.11 Extensive Repair . . . . . . . . . . . . . 6-306.7.12 High Temperature Areas . . . . . . . . 6-306.7.13 Low Temperature Curing . . . . . . . . 6-306.8 STORAGE/SHELF LIFE CON-

TROL OF SEALANTS . . . . . . . 6-30

7 TREATMENT OF SPECIFIC AREAS . . . . . 7-1

7.1 INTRODUCTION . . . . . . . . . . . . 7-17.2 BATTERY COMPARTMENTS,

BOXES, AND ADJACENT AR-EAS . . . . . . . . . . . . . . . . . . . . 7-1

7.2.1 Preparation of Solutions for Clean-ing and Neutralizing BatteryElectrolytes . . . . . . . . . . . . . . . 7-1

7.2.2 Cleaning and Neutralizing Proce-dures . . . . . . . . . . . . . . . . . . . 7-2

7.2.3 Paint Systems . . . . . . . . . . . . . . . 7-27.3 RELIEF TUBE AREAS . . . . . . . . 7-27.4 CORROSION TREATMENT FOR

STEEL CABLES . . . . . . . . . . . 7-37.5 PIANO TYPE HINGES . . . . . . . . 7-37.6 INTEGRAL AND EXTERNAL

FUEL TANKS AND DROPTANKS . . . . . . . . . . . . . . . . . 7-3

7.6.1 Corrosion Removal and Rework ofPitted Areas of Integral FuelTanks . . . . . . . . . . . . . . . . . . . 7-3

7.6.2 Removal of Corrosion and Reworkof Aluminum External FuelTanks/Drop Tanks . . . . . . . . . . 7-4

7.7 FAYING SURFACES AND AT-TACHMENT POINTS . . . . . . . 7-5

7.7.1 Faying Surfaces, Joints, and Seams . 7-57.7.2 Attaching Parts and Hardware . . . . 7-57.7.3 Severely Corroded (Rusted) Hard-

ware . . . . . . . . . . . . . . . . . . . . 7-67.8 NATURAL AND SYNTHETIC

RUBBER PARTS . . . . . . . . . . . 7-77.9 POTABLE WATER TANKS . . . . . 7-7

7.10 SURFACES AND COMPONENTSEXPOSED TO EXHAUSTGASES, GUN GASES ANDROCKET BLAST . . . . . . . . . . 7-7

7.11 ELECTRICAL AND ELECTRONICEQUIPMENT . . . . . . . . . . . . . 7-7

7.11.1 Grounding and Bonding Connec-tions . . . . . . . . . . . . . . . . . . . . 7-7

7.11.2 Conduit and Junction Boxes . . . . . 7-77.11.3 Wires and Cables . . . . . . . . . . . . . 7-77.11.4 Corrosion Protection for Electrical

Connectors, Lead-ins, etc . . . . . 7-77.11.5 Moisture and Fungus Proo ng of

Electrical and Electronic Equip-ment . . . . . . . . . . . . . . . . . . . 7-7

7.11.6 Antennas . . . . . . . . . . . . . . . . . . 7-77.12 STRUCTURAL TUBING MEM-

BERS AND ASSEMBLIES . . . . 7-77.12.1 Structural Aluminum Alloy Tubing . 7-77.12.2 Structural Magnesium Alloy Tub-

ing . . . . . . . . . . . . . . . . . . . . . 7-87.12.3 Structural Copper Alloys, Stainless

Steel (CRES) Alloys, and HeatResistant Alloy Tubing . . . . . . . 7-8

7.12.4 Structural Carbon Steel Tubing . . . . 7-87.13 NON-STRUCTURAL TUBING

MEMBERS AND ASSEM-BLIES . . . . . . . . . . . . . . . . . . 7-8

7.13.1 Aluminum Alloy Tubing . . . . . . . . 7-87.13.2 Stainless Steel (CRES) Tubing . . . . 7-97.13.3 Cadmium Plated Steel Tubing . . . . 7-97.13.4 Special Instructions for Tubing Fit-

tings and Sleeves . . . . . . . . . . . 7-107.13.5 Removable Installations . . . . . . . . 7-107.14 CORROSION REMOVAL FROM

THIN METAL (0.0625 INCHTHICKNESS AND LESS) . . . . . 7-10

7.15 AIR INTAKE DUCTS FOR JETAIRCRAFT . . . . . . . . . . . . . . . 7-11

7.16 CLOSELY COILED SPRINGS . . . 7-117.17 CORROSION PREVENTION ON

ASSEMBLIES AND PARTS RE-MOVED FROM AIRCRAFTDURING MAINTENANCE, 30DAY SHORT TERM STORAGE,AND OVER 30 DAY LONGTERM STORAGE REQUIRE-MENTS . . . . . . . . . . . . . . . . . 7-11

7.17.1 Short Term Storage . . . . . . . . . . . 7-117.17.2 Long Term Storage . . . . . . . . . . . . 7-117.18 DEPLETED URANIUM

COUNTER-WEIGHTS . . . . . . . 7-127.18.1 Corrosion and Finish Damage Treat-

ment Procedures . . . . . . . . . . . 7-127.19 MONEL RIVETS . . . . . . . . . . . . . 7-13

TO 1-1-691



iv Change 1

7.20 BERYLLIUM-COPPER ALLOYS,BERYLLIUM-ALUMINUM AL-LOYS, AND BERYLLIUM OX-IDE . . . . . . . . . . . . . . . . . . . . 7-13

7.20.1 Corrosion Removal and Treatment . 7-137.20.2 Depot Maintenance . . . . . . . . . . . . 7-147.21 EMI SEALS AND GASKETS . . . . 7-147.21.1 Treatment of EMI Seals and Gas-

kets . . . . . . . . . . . . . . . . . . . . 7-14

8 EMERGENCY PROCEDURES . . . . . . . . . 8-1

8.1 PURPOSE . . . . . . . . . . . . . . . . . 8-18.2 RESPONSIBILITY . . . . . . . . . . . 8-18.3 EMERGENCY PREPARATIONS . . 8-18.3.1 Priority Removal List of Equipment

and/or Components . . . . . . . . . . 8-18.3.2 Emergency Reclamation Team . . . . 8-28.3.3 Emergency Reclamation Equip-

ment . . . . . . . . . . . . . . . . . . . 8-28.3.4 Production Planning . . . . . . . . . . . 8-28.4 GENERAL PROCEDURES . . . . . . 8-28.4.1 Removal of Contaminated Installed

Equipment . . . . . . . . . . . . . . . 8-58.4.2 Disassembly/Removal of Compo-

nents . . . . . . . . . . . . . . . . . . . 8-58.4.3 Clean . . . . . . . . . . . . . . . . . . . . . 8-58.4.4 Tagging . . . . . . . . . . . . . . . . . . . 8-58.5 GENERAL CLEANING PROCE-

DURES . . . . . . . . . . . . . . . . . 8-58.5.1 Primary Method . . . . . . . . . . . . . . 8-58.5.2 Alternate Methods . . . . . . . . . . . . 8-68.5.3 Removing O-D-1407 Potassium Bi-

carbonate (Purple K Powder/PKPor Other Dry Chemical Fire Ex-tinguishing Agents . . . . . . . . . . 8-6

8.5.4 Removing MIL-F-24385 AqueousFilm Forming Foam (AFFF) FireExtinguishing Agent . . . . . . . . . 8-7

8.5.5 Removal of Carbon Dioxide (CO2),HFC-125, or Halon Fire Extin-guishing Agents . . . . . . . . . . . . 8-7

8.5.6 Removal of Protein Type Foam andSoda-Acid Fire ExtinguishingAgents . . . . . . . . . . . . . . . . . . 8-7

8.5.7 Treatment After Landing on aFoamed Runway . . . . . . . . . . . 8-8

8.5.8 Treatment After Exposure to Volca-nic Ash . . . . . . . . . . . . . . . . . . 8-8

8.6 SPECIFIC INTERNAL AREAS . . . 8-88.6.1 Aircraft Cockpit Area . . . . . . . . . . 8-88.6.2 Aircraft Ejection Seats . . . . . . . . . 8-88.6.3 Avionic, Electronic and Electrical

Equipment . . . . . . . . . . . . . . . 8-9

8.6.4 Photographic Equipment . . . . . . . . 8-98.6.5 Graphite or Carbon Fiber/Epoxy,

Boron Fiber/Epoxy, and TungstenFiber/Epoxy Composite Materi-als . . . . . . . . . . . . . . . . . . . . . 8-9

8.7 SPECIFIC EXTERNAL AREAS OFAIRCRAFT . . . . . . . . . . . . . . . 8-10

8.7.1 Airframes . . . . . . . . . . . . . . . . . . 8-108.7.2 Antennas . . . . . . . . . . . . . . . . . . 8-108.7.3 Reciprocating Engines . . . . . . . . . 8-108.7.4 Turbine Engines . . . . . . . . . . . . . . 8-118.7.5 Treatment for Engines Which Have

Ingested Fire Extinguishing Pow-der (Purple K/PKP, Aqueous FilmForming Foam (AFFF), and/orSodium Bicarbonate) . . . . . . . . 8-11

8.7.6 Helicopter Transmission, RotorHead, and Rotor Hub . . . . . . . . 8-11

8.7.7 Helicopter Main and Tail RotorBlades . . . . . . . . . . . . . . . . . . 8-12

8.7.8 Armament . . . . . . . . . . . . . . . . . . 8-128.7.9 Aircraft Fuel Systems . . . . . . . . . . 8-13

9 SOUTHWEST ASIA ENVIRONMENTS . . . 9-1

9.1 INTRODUCTION . . . . . . . . . . . . 9-19.1.1 Climatic Conditions . . . . . . . . . . . 9-19.1.2 Aircraft Wash . . . . . . . . . . . . . . . 9-29.1.3 Aircraft Clear Water Rinse (CWR) . 9-29.1.4 Effects of Desert Environment . . . . 9-29.2 PRE-DEPLOYMENT RECOM-

MENDATIONS . . . . . . . . . . . . 9-29.3 RECOMMENDED ACTIONS

WHILE DEPLOYED . . . . . . . . 9-29.3.1 High Efficiency Particulate Air

(HEPA) Filtration . . . . . . . . . . . 9-29.3.2 Areas to be Checked and Cleaned . . 9-39.4 POST DEPLOYMENT . . . . . . . . . 9-39.5 CORROSION PREVENTIVE COM-

POUNDS (CPC’s) . . . . . . . . . . 9-39.5.1 Recommended CPC’s . . . . . . . . . . 9-3

APPENDIX A CONSUMABLE MATERI-ALS . . . . . . . . . . . . . . . . . . . . . . . . . . A-1

APPENDIX B EQUIPMENT FORCLEANING AND CORROSION PRE-VENTION AND CONTROL . . . . . . . . . B-1

GLOSSARY . . . . . . . . . . . . . . . . . . . . . .Glossary-1

INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . Index-1

TO 1-1-691



Change 1 v

LIST OF ILLUSTRATIONS

Figure Title Page Figure Title Page

2-1 Simpli ed Corrosion Cell . . . . . . . . . . 2-12-2 Elimination of Corrosion by Application

of an Organic Film to a MetalSurface . . . . . . . . . . . . . . . . . . . . 2-2

2-3 Effect of Sea Water on GalvanicCorrosion . . . . . . . . . . . . . . . . . . . 2-3

2-4 Galvanic Corrosion in a FlashlightBattery . . . . . . . . . . . . . . . . . . . . 2-4

2-5 Effect of Area Relationship in DissimilarMetal Contacts . . . . . . . . . . . . . . . 2-4

2-6 Galvanic Corrosion of MagnesiumAdjacent to a Steel Fastener . . . . . . 2-5

2-7 Pitting of an Aluminum WingAssembly . . . . . . . . . . . . . . . . . . . 2-6

2-8 Cross-section of Corrosion Pits . . . . . . 2-62-9 Cross-section of 7075-T6 Aluminum

Alloy . . . . . . . . . . . . . . . . . . . . . 2-72-10 Grain Structure of a Corroding

Aluminum Surface . . . . . . . . . . . . 2-72-11 Intergranular Corrosion of 7075-T6

Aluminum Adjacent to SteelFastener . . . . . . . . . . . . . . . . . . . . 2-7

2-12 Example of Exfoliation . . . . . . . . . . . 2-72-13 Another Example of Exfoliation . . . . . 2-82-14 Concentration Cell Corrosion . . . . . . . 2-92-15 Stress Corrosion Cracking . . . . . . . . . 2-92-16 Galvanic Series of Metals and Alloys in

Sea Water . . . . . . . . . . . . . . . . . . 2-102-17 Filiform Corrosion Found Under Paint

Coating on a Magnesium Panel . . . . 2-112-18 Schematic of the Development of

Filiform Corrosion on an AluminumAlloy . . . . . . . . . . . . . . . . . . . . . 2-12

2-19 Magnesium Corrosion Products . . . . . . 2-132-20 Steel Corrosion Products (Rust) . . . . . . 2-142-21 Aluminum Surface Corrosion Products . 2-152-22 Cadmium Plated Surface Conditions . . 2-162-23 Failed Chromium Plating . . . . . . . . . . 2-183-1 Foam Generating Cleaning Unit (15

Gallons) . . . . . . . . . . . . . . . . . . . . 3-303-2 Foam Generating Cleaning Unit (45

Gallons) . . . . . . . . . . . . . . . . . . . . 3-313-3 Universal Wash Unit . . . . . . . . . . . . . 3-333-4 Top Loading Type . . . . . . . . . . . . . . . 3-363-5 Front Loading Type . . . . . . . . . . . . . . 3-373-6 Use of Aircraft Washing Applicator . . . 3-413-7 Aircraft Cleaning Procedure . . . . . . . . 3-423-8 Automatic Water Spray Nozzle . . . . . . 3-454-1 Depth Dimension of Corrosion Pits . . . 4-34-2 Fiber Optic Borescope . . . . . . . . . . . . 4-44-3 Optical Depth Micrometer (Analog

Mechanical Read Out Type) . . . . . . 4-74-4 Optical Depth Micrometer (Digital Read

Out Type) . . . . . . . . . . . . . . . . . . 4-8

4-5 Typical Use of a Straight Edge toDetermine if Suspect Areas HaveBeen Previously Reworked . . . . . . . 4-9

4-6 Corrosion Around Fasteners . . . . . . . . 4-104-7 Galvanic Corrosion of Aluminum

Adjacent to Steel Fasteners . . . . . . . 4-104-8 Spot Weld Corrosion . . . . . . . . . . . . . 4-114-9 Spot Welded Skin Corrosion

Mechanism . . . . . . . . . . . . . . . . . 4-124-10 Gun Blast Area Corrosion Points . . . . . 4-124-11 Exhaust Trail Area Corrosion Points . . . 4-124-12 F-15 Nose Landing Gear Wheel Well . . 4-134-13 Flaps Lowered to Expose Recess

Areas . . . . . . . . . . . . . . . . . . . . . 4-134-14 Reciprocating Engine Frontal Area

Corrosion Points . . . . . . . . . . . . . . 4-134-15 Jet Engine Frontal Area Corrosion

Points . . . . . . . . . . . . . . . . . . . . . 4-134-16 Corrosion Prone Point of Air Inlet . . . . 4-134-17 Corrosion in Air Intake Duct . . . . . . . . 4-144-18 Wing Fold Joint . . . . . . . . . . . . . . . . 4-154-19 Hinge Corrosion Points . . . . . . . . . . . 4-164-20 Piano Hinge Lugs . . . . . . . . . . . . . . . 4-164-21 Control Cables . . . . . . . . . . . . . . . . . 4-164-22 Personnel Relief Tube Vent . . . . . . . . . 4-164-23 Common Water Entrapment Areas . . . . 4-174-24 Bilge Areas . . . . . . . . . . . . . . . . . . . 4-174-25 Battery Compartment . . . . . . . . . . . . . 4-185-1 3M Co. Scotch-BriteTM Flap Brush and

Mandrel . . . . . . . . . . . . . . . . . . . . 5-55-2 Abrasive Flap Wheels with Spindle

Mount . . . . . . . . . . . . . . . . . . . . . 5-55-3 3M Co. Radial Bristle Disc . . . . . . . . . 5-65-4 3M Co. Roloc Discs . . . . . . . . . . . . . 5-65-5 3M Co. Inline Bristle Disc . . . . . . . . . 5-85-6 Abrasive Blasting Equipment . . . . . . . 5-105-7 Shaping Reworked Areas . . . . . . . . . . 5-155-8 Acceptable Clean-up of Pitting

Corrosion on Critical Structure . . . . 5-155-9 Limited Clearance . . . . . . . . . . . . . . . 5-165-10 A Water-Break Free Surface Compared

with One with Breaks . . . . . . . . . . 5-415-11 Peening Intensity Conversion Graph (Isp

to Irp) . . . . . . . . . . . . . . . . . . . . . 5-485-12 Saturation Coverage Curves for

MIL-W-81840, Type I Wheels . . . . . 5-495-13 Saturation Coverage Curves for

MIL-W-81840, Type II Wheels(Flaps) . . . . . . . . . . . . . . . . . . . . . 5-50

5-14 Flap De ection Ranges . . . . . . . . . . . 5-516-1 Pneumatic Sealant Gun . . . . . . . . . . . 6-126-2 Sealant Application Nozzles . . . . . . . . 6-136-3 Countersink Application Nozzles . . . . . 6-14

TO 1-1-691

vi Change 1

6-4 Rivet Application Nozzles . . . . . . . . . 6-156-5 Sealant and Adhesive Smoothing Tools . 6-166-6 Sealant Injection Guns . . . . . . . . . . . . 6-176-7 Injection Style Semkit® . . . . . . . . . . . 6-186-8 Non-metallic Spatula . . . . . . . . . . . . . 6-246-9 Faying Surface Sealing . . . . . . . . . . . 6-266-10 Typical Fillet Seal . . . . . . . . . . . . . . . 6-276-11 Typical Injection Seal . . . . . . . . . . . . 6-286-12 Typical Methods of Sealing Fasteners . . 6-286-13 Typical Lap Skin Sealing . . . . . . . . . . 6-306-14 Sealing Procedures for Typical Aircraft

Fitting . . . . . . . . . . . . . . . . . . . . . 6-326-15 Typical Spar Cap Sealing . . . . . . . . . . 6-336-16 Sealing of Access Doors . . . . . . . . . . 6-347-1 Beryllium-Copper Spiral Contact With

Environmental Fluorosilicone Seal . . 7-15

7-2 Dorsal Longeron EMI Seal . . . . . . . . . 7-167-3 Stainless Steel (CRES) EMI Screen . . . 7-177-4 Bonding Cable From Airframe To

Graphite/Epoxy Avionics Bay Door . 7-187-5 EMI Bonding Washers in an Avionics

Bay . . . . . . . . . . . . . . . . . . . . . . . 7-199-1 Soil Makeup in the SWA Area . . . . . . 9-19-2 Global Dust Producing Regions . . . . . . 9-29-3 Open Circuit Board . . . . . . . . . . . . . . 9-3B-1 Back Mounted Full Facepiece

Respirator . . . . . . . . . . . . . . . . . . B-41B-2 Front Mounted Full Facepiece

Respirator . . . . . . . . . . . . . . . . . . B-42B-3 Hooded Air Respirator System . . . . . . B-43

LIST OF TABLES

Table Title Page Table Title Page

2-1 Corrosion of Metals - Type of Attack andAppearance of Corrosion Products . . . 2-16

3-1 Aircraft Wash Intervals . . . . . . . . . . . . . 3-23-2 Cleaning of Specific Areas and

Components . . . . . . . . . . . . . . . . . . 3-123-3 Recommended Dilution of Low

Temperature Cleaner . . . . . . . . . . . . . 3-463-4 Common Military Greases the Their

Uses . . . . . . . . . . . . . . . . . . . . . . . . 3-523-5 Time Limitations for CPC’s . . . . . . . . . . 3-543-6 Corrosion Preventive Compounds . . . . . . 3-543-7 Preservation of Specific Areas and

Components . . . . . . . . . . . . . . . . . . 3-574-1 NDI Inspection Tools for Various Types of

Corrosion . . . . . . . . . . . . . . . . . . . . 4-25-1 Grades of Abrasive Mats . . . . . . . . . . . . 5-25-2 Grades of Steel Wool . . . . . . . . . . . . . . 5-25-3 Recommended Powered Abrasives for

Corrosion Removal . . . . . . . . . . . . . . 5-115-4 Recommended Non-Powered Abrasives for

Corrosion Removal . . . . . . . . . . . . . . 5-125-5 Typical Chemical Corrosion Removal

Procedures For Aluminum Alloy Partsand Assemblies . . . . . . . . . . . . . . . . 5-20

5-6 Typical Chemical Corrosion RemovalProcedures for Magnesium Alloys . . . . 5-23

5-7 Typical Chemical Corrosion RemovalProcedures for Ferrous Metals OtherThan Stainless Steel (CRES) . . . . . . . 5-27

5-8 Typical Chemical Corrosion RemovalProcedures for Stainless Steel (CRES)and Nickel Based Alloys . . . . . . . . . . 5-29

5-9 Control of Corrosion Removal/ PicklingAction of Nitric-Hydrofluoric AcidSolutions . . . . . . . . . . . . . . . . . . . . 5-31

5-10 Typical Chemical Corrosion RemovalProcedures for Copper and CopperAlloys . . . . . . . . . . . . . . . . . . . . . . 5-33

5-11 Typical Chemical Corrosion Removal ofTitanium and Titanium Base Alloys . . 5-34

5-12 Typical Chemical Corrosion RemovalProcedures for Plated and PhosphatedSurfaces . . . . . . . . . . . . . . . . . . . . . 5-37

5-13 Prepaint Treatments for Metal Surfaces . . 5-425-14 Tool Operation Speed Requirements . . . . 5-465-15 Standard Peening Intensity (Isp) for

Complete Coverage Arc-Height inInches . . . . . . . . . . . . . . . . . . . . . . 5-46

6-1 Sealing Compounds . . . . . . . . . . . . . . . 6-36-2 Time Requirements for Sealants When

Used At 75 Degree F (24 Degree C)and 50 Precent RH . . . . . . . . . . . . . . 6-19

8-1 Priority Guide for Emergency Treatmentof Aircraft, Missiles, & Equipment . . . 8-2

8-2 Suggested List of Emergency ReclamationItems . . . . . . . . . . . . . . . . . . . . . . . 8-3

A-1 Units of Issue Codes . . . . . . . . . . . . . . A-1A-2 Consumable Materials . . . . . . . . . . . . . . A-2B-1 Unit Of Issue Codes . . . . . . . . . . . . . . . B-1B-2 Equipment For Cleaning and Corrosion

Prevention and Control . . . . . . . . . . . B-2

TO 1-1-691

LIST OF ILLUSTRATIONS - CONTINUED

Figure Title Page Figure Title Page

Change 1 vii/(viii blank)

FOREWORD

1 PURPOSE.

The purpose of this manual is to provide information onmaterials and procedures for the prevention and repair ofcorrosion damage to aircraft and missile weapon systems andrelated equipment. Supervisory and maintenance personnelshall use this manual as a guide for all corrosion control andmaintenance efforts. Contractors who maintain and repaircorrosion of aircraft, missiles, and related equipment shallalso use this manual.

1.1 Usage. Use this manual in conjunction with and insupport of the appropriate systems specific aircraft, missile,or equipment technical orders (TO’s). In the case of a conflictbetween this manual and a systems specific aircraft, missile,or equipment manual, the system specific manual shall takeprecedence over this manual. Paragraph 5 lists related tech-nical publications used by personnel involved in cleaning andcorrosion control.

2 SCOPE.

The material in this manual provides basic cleaning, corro-sion prevention and control, and corrective maintenanceinformation to be used at organizational, intermediate, anddepot levels. This manual is divided into a foreword, safetysummary, eight chapters, two appendices, a glossary, and analphabetical index.

2.1 Foreword. This Foreword explains the purpose,responsibility for changing this manual, and presents thescope and outlay of the manual.

2.2 Safety Summary. This Safety Summary providesgeneral safety precautions personnel shall use during allphases of operations and maintenance.

2.3 Chapter 1, Introduction. This chapter explains theappropriate usage of this manual.

2.4 Chapter 2, Corrosion Theory. This chapter ex-plains what corrosion is, why it occurs, the various forms itcan take, and how to recognize it.

2.5 Chapter 3, Preventive Maintenance. This chapteroutlines accepted procedures, methods, and materials to be

used in maintenance cleaning in Section I, lubrication inSection II, and preservation in Section III of aircraft, missiles,and related equipment.

2.6 Chapter 4, Inspection and Corrosion Prone Ar-eas. This chapter describes inspection techniques fordetecting corrosion in Section I and discusses corrosion proneareas in Section II.

2.7 Chapter 5, Corrosion Removal and Surface Treat-ment. This chapter outlines the approved methods for theremoval of corrosion damage in Section I and the applicationof surface treatments in Section II.

2.8 Chapter 6, Sealants. This chapter covers recom-mended materials and procedures for the application ofsealing compounds to aircraft, missile, and related equipmentstructures.

2.9 Chapter 7, Treatment of Specific Areas. Thischapter describes the recommended procedures for treatingand protecting against corrosion in specific areas.

2.10 Chapter 8, Emergency Procedures. This chapteroutlines emergency procedures to be followed after exposureof aircraft to salt water, fire extinguishing chemicals, etc.

2.11 Appendix A, Consumable Materials. This appen-dix lists the recommended materials for cleaning, corrosionprevention, surface treatment, and preservation of aircraft,missiles, and related equipment.

2.12 Appendix B, Equipment for Cleaning and Corro-sion Prevention and Control. This appendix lists equip-ment used for cleaning, corrosion removal, conversion coat-ing, and sealing of aircraft, as well as associated safetyequipment including personal protective equipment (PPE) forthese operations.

2.13 Glossary. The glossary defines terms commonlyused by personnel performing aircraft, missile, and equip-ment cleaning and corrosion prevention and control.

2.14 Alphabetical Index. This index locates specificsubjects in the manual.

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Change 1 ix

3 ABBREVIATIONS AND ACRONYMS.

This manual contains standard and non-standard abbrevia-tions. The standard abbreviations are in accordance withASME Y14.38.

AFCPCO Air Force Corrosion Prevention andControl Office

AFFF Aqueous Film Forming FoamAISI American Iron and Steel InstituteBOD Biological Oxygen DemandCaCO3 Calcium CarbonateCBR Chemical, Biological, RadiologicalCFM Cubic Feet per MinuteCPC Corrosion Preventive CompoundsCRES Corrosion Resistant SteelsCWR Clear Water Rinse°C Degrees Celsius°F Degrees FahrenheitDI DeionizedDTIC Defense Technical Information

CenterEA EachEPA Environmental Protection AgencyEPTFE Expanded Polytetrafluoroethyleneft Foot/FeetFIP Form-In-PlaceHAP Hazardous Air PollutantsIAW In Accordance WithID Inside Diameterin InchKSI Kilograms per Square InchLG Landing GearLOX Liquid OxygenMEK Methyl Ethyl Ketonemg/L Milligrams per Litermm Hg Millimeters of MercuryMOS Maximum Operating SpeedMSDS Material Safety Data SheetNDI Non-Destructive InspectionNRA Nuclear Regulatory AgencyNSN National Stock NumberOD Outside DiameterODC Ozone Depleting CompoundsODS Ozone Depleting Substances% PercentpH Potential of Hydrogen

PMF Pre-Mixed and FrozenPPE Personal Protective Equipmentppm Parts Per MillionQPL Qualified Products ListRH Relative HumidityRTU Ready To UseSE Support EquipmentSPD System Program DirectorSPM System Program ManagerTDS Total Dissolved SolidsTNP Touch-N-PrepTM

TPH Total Petroleum HydrocarbonTSS Total Suspended Solids

4 RESPONSIBILITY FOR CHANGES TO THISMANUAL.

This manual is maintained for technical content by the AirForce Corrosion Prevention and Control Office (AFCPCO),AFRL/MLS-OLR, 325 Richard Ray Blvd., Robins AFB GA31098-1639, Tel: (478) 926-3284 (DSN 468-3284), Fax:(478) 926-6619 (DSN 468-6619), email: afcorr@ robin-s.af.mil; and for TO administration by WR-ALC/LESGI, 460Richard Ray Blvd., Robins AFB GA 31098-1640, Tel:(478)926-7046 x122 (DSN 468-7046 x122), email: wralc.lesgi.in-dustrialbackhop@ robins.af.mil.

4.1 Recommended Changes, Corrections, or Dele-tions. All activities using this manual are invited to submitrecommended modifications, additions, or deletions. Use thecurrent reporting system in TO 00-5-1 to submit thesechanges to WR-ALC/LESGI.

5 RELATED PUBLICATIONS.

List of Related Publications

Number TitleDOD 6050.5LR Hazardous Material Control

and Management(HMC&M)

AFI 32-1067 Water SystemsAFI 32-7080 Pollution Prevention Pro-

gramAFI 40-201 Managing Radioactive Ma-

terials in the U.S. AirForce

AFM 23-110, Vol.7,Pt.3 Inspection and Control ofUSAF Shelf Life Equip-ment

TO 1-1-691

x

List of Related Publications - Continued

Number TitleAFM 88-11 Sanitary and Industrial

Waste Water CollectionAFM 91-11 Solid Waste ManagementAFOSH STD 91-66 General Industrial Opera-

tionsAFP 85-14 Commanders Facility Im-

provement GuideMIL-HDBK-729 Corrosion and Corrosion

Prevention-MetalsTO 00-5-1 AF Technical Order SystemTO 00-20-1 Aerospace Equipment

Maintenance, GeneralPolicies and Procedures

TO 00-20-2 Maintenance Data Docu-mentation

TO 00-25-107 Maintenance AssistanceTO 00-25-172 Ground Servicing of Air-

craft and Static Ground-ing/Bonding

TO 00-25-234 General Shop Practice Re-quirements for the Re-pair, Maintenance, andTest of Electronic Equip-ment

TO 00-25-235 Safety Procedures andEquipment For ConfinedSpace Entry (IncludingMissile Propellant Tanks)

TO 00-35D-54 USAF Material DeficiencyReporting and Investigat-ing System

TO 00-85-3 Corrosion Control for Pack-aging

TO 00-85A-03-1 Preservation, Packaging andPacking - External Air-craft Fuel Tanks, FuelCells

TO 00-110A-1 Guidelines for Identificationand Handling of Aircraftand Material Contami-nated with RadioactiveDebris (Fallout)

TO 1-1-3 Preparation, Inspection, andRepair of Aircraft Fuel,Oil, and Water-AlcoholCells and Integral Tanks

TO 1-1-8 Application and Removalof Organic Coatings,Aerospace and Non-Aerospace Equipment


Number TitleTO 1-1-17 Storage of Aircraft and

Missiles SystemsTO 1-1-24 Maintenance Repair and

Electrical Requirementsfor Fiberglass AirborneRadomes

1-1-689-1 Cleaning and CorrosionControl, Volume I, Corro-sion Program and Corro-sion Theory

1-1-689-3 Cleaning and CorrosionControl, Volume III, Avi-onics and Electronics

1-1-689-5 Cleaning and CorrosionControl, Volume IV, Con-sumable Materials andEquipment for Avionics

TO 1-1-690 General Advanced Compos-ite Repair Processes

TO 1-1A-1 Engineering H/B Series forAircraft Repair - GeneralManual for StructuralRepair

TO 1-1A-8 Engineering Manual Seriesfor Aircraft and MissilesRepair Structural Hard-ware

TO 1-1A-9 Engineering Series for Air-craft Repair AerospaceMetal General Data andUsage Factors

TO 1-1A-12 Fabrication, Maintenanceand Repair of Transpar-ent Plastic

TO 1-1A-14 Installation Practices forAircraft Electric andElectronic Wiring

TO 1-1A-15 General Maintenance In-structions for SupportEquipment (SE)

TO 2-1-11 Corrosion Control of En-gine Parts During Over-haul and Field LevelMaintenance, Reciprocat-ing, Turbojet, and GasTurbine Aircraft Engines

TO 2-1-111 Standard Maintenance Prac-tices, Navy, USAF andArmy, P&W Aircraft En-gines

TO 1-1-691

Change 1 xi


Number TitleTO 2J-1-13 Cleaning of Gas Turbine

Aircraft Engines andParts

TO 2J-1-18 Preparation for Shipmentand Storage of Gas Tur-bine Engines

TO 2J-1-32 Standard Maintenance Prac-tice Instructions - GEAircraft Engines, ModelTF-34-GE-100, A, -400,A, B, TF58-GE-3, -5,-8B, -10, -16, -100(USCG), -4OOB, -402,T64-GE-6B, -7, A, 100,-413, -415, -416, -416A,F404-GE-400, YF404-GE-400, F110-GE-400,YT700-GE-401, T700-GE-401,4

TO 2R-1-11 Corrosion Control - Recip-rocating Aircraft Engines

TO 2R-1-84 Cleaning of ReciprocatingEngines and Parts

TO 4B-1-32 Maintenance and O/H In-structions - All Type Air-craft Brakes

TO 4S-1-182 General O/H & Mainte-nance Instr. All FSC1620 Landing Gear &Components

TO 4W-1-61 Operation, Service, andMaintenance Instructions— All Aircraft Wheels

TO 10-1-179 Corrosion Control Manualfor Photographic Equip-ment

TO 13A1-1-1 Repair, Cleaning, Inspec-tion and Testing AircraftSafety Belts, ShoulderHarness, and Miscella-neous Personnel RestraintEquipment.

TO 31-1-221 Field Instructions for Paint-ing and Preserving Elec-tronics Command Equip-ment


Number TitleTO 33B-1-1 Nondestructive Inspection

MethodsTO 34-1-3 Inspection and Maintenance

of Machinery and ShopEquipment

TO 35-1-3 Corrosion Prevention,Painting, and Marking ofUSAF Support Equip-ment (SE)

TO 35-1-4 Processing and Inspectionof Support Equipment forStorage and Shipment

TO 35-1-12 Compounds and Proceduresfor Cleaning AerospaceGround Equipment

TO 36-1-191 Technical and ManagerialReference for Motor Ve-hicle Maintenance

TO 42A1-1-1 Evaluation and ServiceTesting of Materials -Cleaning, Painting, Seal-ing, Protective Treating,Anti-Corrosion, Inspec-tion Materials, and Re-lated Items

TO 42A3-1-2 General Use of Cements,Sealants, and Coatings

TO 42B-1-6 Corrosion Preventive Lubri-cants and Anti-SeizeCompounds

TO 42C-1-2 Anti-Icing, Deicing, andDefrosting of Parked Air-craft

TO 42C-1-12 Quality Control of Chemi-cals

TO 42C2-1-7 Electro deposition of Met-als and Metal SurfaceTreatments to meet AirForce MaintenanceRequirements.

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SAFETY SUMMARY

1 GENERAL SAFETY INSTRUCTIONS.

This manual describes physical and chemical processeswhich may cause injury or death to personnel, or damage toequipment if not properly followed. This safety summaryincludes general safety precautions and instructions that mustbe understood and applied during operation and maintenanceto ensure personnel safety and protection of equipment. Priorto performing any task, the WARNINGs, CAUTIONs andNOTEs included in that task shall be reviewed and under-stood.

2 WARNINGS, CAUTIONS, AND NOTES.

WARNINGs and CAUTIONs are used in this manual tohighlight operating or maintenance procedures, practices,conditions or statements which are considered essential toprotection of personnel (WARNING) or equipment (CAU-TION). NOTEs are used in this manual to highlight operatingor maintenance procedures, practices, conditions or state-ments which are not essential to protection of personnel orequipment. The headings used and their definitions are asfollows:

Highlights an essential operating or maintenanceprocedure, practice, condition, statement, etc.,which if not strictly observed, could result ininjury to, or death of, personnel or long termhealth hazards.

Highlights an essential operating or maintenanceprocedure, practice, condition, statement, etc.,which if not strictly observed, could result indamage to, or destruction of, equipment or loss ofmission effectiveness.

NOTE

Highlights an essential operating or maintenanceprocedure, condition or statement.

3 SAFETY PRECAUTIONS.

The following safety precautions shall be observed whileperforming procedures in this manual.

• Some cleaning materials specified herein are flam-mable and/or toxic. Keep away from open flame orother ignition sources. Do not use synthetic wipingcloths with flammable solvents. Open all circuitbreakers associated with battery power prior to ap-plication of any flammable solvent. Provide adequateventilation and avoid skin/eye contact. Wear PersonalProtective Equipment (PPE). Consult the MaterialSafety Data Sheets (MSDS) for specific informationon hazards, effects and protective equipment require-ments.

• Some cleaning processes described herein use mate-rials and generate effluent that may be hazardous topersonnel and the environment. Contact the localbioenvironmental engineer and safety office for guid-ance on PPE and other health and safety precautions,and waste disposal.

• Some cleaning operations described herein utilizepower tool operations and abrasive blasting opera-tions which often generate toxic/hazardous airborneparticles. Always wear proper PPE.

• Ensure that all electrical power is disconnected andall systems in aircraft, missiles, or equipment aredeactivated before starting cleaning operations onavionics, electronics, or electrical equipment to pre-vent electrical shock.

• Remove jewelry and remove/cover loose fittingclothing before operating power equipment to pre-vent entanglement and injury.

• Cleaning with compressed air can create airborneparticles that may enter eyes or penetrate skin.Pressure shall not exceed 30 PSIG. Wear goggles. Donot direct compressed air against skin.

• Depleted uranium is extremely toxic and shall beworked only under a license from the Nuclear Regu-latory Agency (NRA). Machining or other work,such as surface sanding, may be done only by thelicensee. No drilling, sanding, abrasive blasting, orother mechanical work is permitted on depleteduranium by any field level (organizational or inter-mediate) maintenance activity. If the protective finish(plating) which covers the depleted uranium ischipped, peeled, or otherwise removed so the darkgray or black uranium oxide is visible, the part mustbe returned to the licensee for rework or disposal.Packaging and shipping procedures shall conform toAFI 40-201 and any other related current regulationsfor handling radioactive materials.

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CHAPTER 1INTRODUCTION

1.1 CORROSION CONTROL PROGRAM.

All activities responsible for maintenance of aircraft, mis-siles, and related equipment shall establish corrosion preven-tion and control programs as required by AFI 21-105. Thetype of program depends upon the environment to which theaircraft, missile, or equipment may be exposed. Aircraft,missiles, and equipment may be exposed to industrial gases,salts, rain, mud, and mists containing sea salts if located nearsalt water. A comprehensive corrosion prevention and controlprogram shall provide a Structural Maintenance Work Centerwith personnel trained in the prevention, early detection,reporting, and repair of corrosion damage. In addition, such aprogram requires a dedicated effort by all maintenancepersonnel to prevent corrosion from occurring and/or todetect it in its initial stages so it can be treated early thusminimizing costly repairs and improving the operationalreadiness of aircraft, missiles, and equipment.

1.1.1 Training. All personnel performing maintenanceon aircraft, missiles, and related equipment shall be trained inbasic corrosion prevention and control skills and must befully aware of the reasons for the corrosion prevention andcontrol program. Without such training and understanding,more severe damage and additional problems will result.

1.1.2 Maintenance. An effective corrosion preventionand control program shall include thorough cleaning, inspec-tion, preservation, and lubrication, at specified intervals, inaccordance with Chapters 3 and 4. Check for corrosiondamage and integrity of protective finishes during all sched-uled and unscheduled maintenance. Early detection andrepair of corrosion will limit further damage. When corrosionis discovered, treat corrosion as prescribed in Chapters 5 and7 as soon as possible using only approved materials, equip-ment, and techniques. Only affected areas shall be repaired.Seal in accordance with Chapter 6, and paint as required inaccordance with TO 1-1-8 and the systems specific TO Allmaintenance personnel shall report corrosion promptly inaccordance with established Air Force directives.

1.1.3 Facilities. In accordance with Paragraph 7.10.5 ofAFH 32-1084 titled “FACILITY REQUIREMENTS”, baseswith a large number of aircraft (40 or more large or mediumassigned aircraft) or located in a severe environment areauthorized, with proper justification, a Corrosion ControlHangar and aircraft wash hangar.

1.2 SAFETY.

Safety is everyone’s business and concern.

1.2.1 Responsibility of Supervisors. Work center su-pervisors shall receive the following training in accordancewith established Air Force directives:

• The recognition and elimination of hazards.

• Occupational safety and health.

• The safety of the individual.

• Accident investigation and reporting.

• The inspection and maintenance of personal protec-tive equipment (PPE).

1.2.1.1 Supervisors shall ensure that all corrosion controlpersonnel are informed of: Current safety procedures;

• Current safety procedures.

• Characteristics of materials to which they will beexposed.

• Required protective clothing and personal protectiveequipment (PPE) to ensure safety of personnel.

1.2.1.2 In addition, supervisors shall ensure that an ad-equate supply of safety equipment is in a ready-for-issuecondition, and that personnel under their control are given,and use, appropriate protective equipment to prevent acci-dents, injuries, and occupational illness. Maintenance person-nel shall use the appropriate equipment while exposed tohazardous conditions, and shall report any protective equip-ment that is broken, damaged, defective, or inadequate to thesupervisor. No one shall use protective equipment that is notin a satisfactory and serviceable condition. Personnel shallcomply with occupational safety and health requirements,including medical examinations, respirator training and fittesting, and protection for eyes, ears, head, skin, and feet.

1.2.2 Materials Handling. Many of the materials andprocedures outlined in this manual are potentially hazardousto personnel and potentially damaging to aircraft, missiles,and equipment, especially when improperly used. Whenusing any chemicals, such as paint removers, detergents,conversion coatings, and solvents, follow the correct proce-dures and use appropriate protective gear to prevent person-nel injury and structural damage. Read the appropriatewarnings and cautions in this manual prior to use of anyhazardous materials. Misuse of certain materials can damageparts or cause corrosion which may lead to catastrophicfailure. Refer to DOD 6050.5-LR, Hazardous MaterialsInformation System, and the appropriate Air Force directivesfor the handling, storage, and disposal of hazardous materials.Refer to local directives and policies pertaining to hazardous

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waste management. When in doubt, contact the base safetyoffice, and/or bioenvironmental engineer for assistance.

1.3 MATERIALS.

Consumable materials listed in Appendix A and accessorieslisted in Appendix B shall be used for corrosion preventionand control. The materials and equipment listed have beenapproved only after extensive testing to prove their ability toperform properly and effectively without damage to any ofthe metallic or nonmetallic materials used in aircraft, mis-siles, and related equipment. Only those materials listed inthis manual shall be used for cleaning and corrosion preven-

tion and control of aircraft, missile, and equipment compo-nents. Materials listed in other manuals shall be used onlywhen required procedures are not covered by this manual.Materials or processes considered to be an improvement overexisting ones shall be forwarded to the Aircraft SystemProgram Director (SPD) or the Missile or Equipment SystemProgram Manager (SPM) and the Air Force Corrosion Pre-vention and Control Office (AFCPCO), AFRL/MLS-OLR,for further evaluation. When approved materials are notavailable, substitutions shall only be made after approval bythe appropriate SPD/SPM in conjunction with the AFCPCO.When several methods or materials are listed, the preferredone is listed first, with alternates following.

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CHAPTER 2CORROSION THEORY

2.1 INTRODUCTION TO CORROSION THEORY.

This chapter is an introduction to corrosion theory, the causesof corrosion, and the factors which influence its development.The various forms of corrosion and the effect of corrosiveenvironments on aircraft and metals are described. Thepurpose of this discussion is to provide maintenance person-nel with the background knowledge necessary to understandthe causes of corrosion and to minimize corrosion damage.

2.2 DEFINITION OF CORROSION.

Corrosion is the electrochemical deterioration of a metalbecause of its chemical reaction with the surrounding envi-ronment. This reaction occurs due to the tendency of metalsto return to their naturally occurring states, usually oxide orsulfide ores. For example, iron in the presence of moistureand air will return to its natural state, iron oxide or rust.Aluminum and magnesium form corrosion products that arewhite oxides or hydroxides. When a water solution containingsoluble salts is present, corrosion of many alloys can occureasily at ambient temperatures. This type of corrosion can beeffectively treated by maintenance personnel as discussed inthis manual. Corrosion can also occur in the absence of water,but only at high temperatures such as those found in gasturbine engines. However, the most common type of corro-sion (and the one that can be most effectively treated bymaintenance personnel) is electrochemical corrosion.

2.3 CHEMICAL DEFINITIONS.

2.3.1 Atom. The smallest unit of an element. There areover 100 elements, including metals such as aluminum,magnesium, gold, platinum, iron, nickel, titanium, cadmium,chromium, copper, silver, lead, uranium, beryllium, zinc andcarbon and non-metals such as hydrogen, oxygen, nitrogen,sulfur, chlorine, helium and boron.

2.3.2 Electron. A negatively charged particle muchsmaller than an atom. An electric current occurs whenelectrons are forced to move through metal conductors.Electrons flow through water solutions only in the presence ofions.

2.3.3 Ions. Atoms or groups of atoms bound togetherwhich are either positively or negatively charged. An electriccurrent occurs when ions are forced to move through watersolutions. Ions cannot move through metal conductors.

2.3.4 Electrolyte. A liquid (usually water) solution con-taining ions. Salt water is an electrolyte: an aqueous (mean-ing, water) solution of sodium ions and chloride ions.Electrochemistry is the branch of chemistry concerned withchemical reactions at surfaces in contact with electrolytes.

2.4 THEORY OF CORROSION.

All structural metals will corrode to some extent in a naturalenvironment. When a metal corrodes, the metal atoms loseelectrons and become positively charged metal ions in theelectrolyte. In solution, the positively charged metal ions cancombine with negatively charged ions to form corrosionproducts, such as metallic chlorides, oxides, hydroxides,sulfides, etc. Four conditions must exist before this type ofcorrosion can occur.

2.4.1 Anode. A metal which has a tendency to corrodemust be present (the corroding metal is known as the anode).

2.4.2 Cathode. A dissimilar conductive material (thecathode) which has less tendency to corrode than the anodemust be present (such as a different metal, a protected part ofthe same metal, or conductive plastics).

2.4.3 Electrolyte. A conductive liquid (electrolyte) mustconnect the anode and cathode (so that ions can carry electriccurrent between them).

2.4.4 Electrical contact. Electrical contact between theanode and cathode (usually in the form of metal-to-metalcontact) must exist (so that electrons can move from theanode, where they are released, to the cathode).

2.4.4.1 The elimination of any one of the four conditions,illustrated in Figure 2-1, will stop corrosion. For example, apaint film on a metal surface will prevent the conducting

Figure 2-1. Simplified Corrosion Cell

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liquid (electrolyte) from connecting the anode and cathode,thereby, stopping the electric current (refer to Figure 2-2).Another example: two connected dissimilar metal partsplaced in distilled water corrode very slowly due to a lack ofions in solution to conduct the electric current; in sea waterthe corrosion reaction is accelerated by a factor of 1000 ormore (refer to Figure 2-3).

2.5 DEVELOPMENT OF CORROSION.

All corrosive attack begins on the surface of metals. Ifallowed to progress, corrosion can penetrate in the metal. Ifcorrosion begins on an inside surface of a component (forexample, the inner wall of metal tube), it may go undetecteduntil perforation occurs. When corrosion products form, theyoften deposit on the corroding surface as a powdery deposit.This film of corrosion products may reduce the rate ofcorrosion, if the film acts as a barrier to electrolytes. Somemetals (such as stainless steel and titanium), under the rightconditions, produce corrosion products that are so tightlybound to the corroding metal that they form an invisible oxidefilm (called a passive film), which prevents further corrosion.However, when the film of corrosion products is loose andporous (such as those of carbon steel, aluminum and magne-sium), an electrolyte can easily penetrate and continue thecorrosion process, producing more extensive damage thansurface appearance shows.

2.5.1 Corrosion Under Painted Surfaces. Paint coat-ings can mask the initial stages of corrosion. Since corrosion

products occupy more volume than the original metal, paintsurfaces should be inspected often for irregularities such asblisters, flakes, chips, lumps and worm like tracks.

2.6 FACTORS INFLUENCE CORROSION.

Some factors which influence metal corrosion and the rate ofcorrosion are:

• Type of metal

• Presence of a dissimilar, less corrodible metal (gal-vanic corrosion)

• Anode and cathode surface areas (in galvanic corro-sion)

• Temperature

• Heat treatment and grain direction

• Presence of electrolytes (hard water, salt water,battery fluids, etc.)

• Availability of oxygen

• Presence of different concentrations of the sameelectrolytes

• Presence of biological organisms

• Mechanical stress on the corroding metal

• Time of exposure to a corrosive environment

Figure 2-2. Elimination of Corrosion by Application of an Organic Film to a Metal Surface

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2.6.1 Type of Metal. Most pure metals are not suitablefor aircraft construction and are used only in combinationwith other metals, and sometimes non-metals, to form alloys.Most alloys are made up entirely of small crystalline regions,called grains. Corrosion can occur on surfaces of thoseregions, which are less resistant, and also at boundariesbetween regions, resulting in the formation of pits andintergranular corrosion. The metals most commonly used inaircraft construction are aluminum, steel, titanium and mag-nesium. Cadmium, zinc, nickel, chromium and silver aresometimes used as protective platings. Metals have a widerange of corrosion resistance. The most active metals (thosewhich tend to lose electrons easily), such as magnesium andaluminum, corrode easily and are listed at the top or anodicend of Figure 2-16. The most noble metals (those which donot lose electrons easily), such as gold and silver, do notcorrode easily and are listed at the bottom or cathodic end ofFigure 2-16.

2.6.2 Dissimilar Metal Coupling (Galvanic Corro-sion). When two dissimilar metals make electrical contactin the presence of an electrolyte, the rate at which corrosionoccurs depends on the difference in their activities, that is,their positions in Figure 2-16. The greater the difference inactivity, the faster corrosion occurs. For example, magnesiumwould corrode very quickly when coupled with gold in ahumid atmosphere. But aluminum would corrode veryslowly, if at all, in contact with cadmium. A flashlight battery(or dry cell) is an example of galvanic corrosion put topractical use. In Figure 2-4, the zinc battery casing steadilycorrodes supplying a steady flow of electrons, but only whenthe switch is closed. When the switch is open, there is nocorrosion because electrons are not able to leave the zincanode.

Figure 2-3. Effect of Sea Water on Galvanic Corrosion

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2.6.3 Anode and Cathode Surface Area. The rate ofgalvanic corrosion also depends on the size of the parts incontact. If the surface area of the corroding metal (the anode)is smaller than the surface area of the less active metal (thecathode), corrosion will be rapid and severe. But, when thecorroding metal is larger than the less active metal, corrosionwill be slow and superficial. For example, an aluminumfastener in contact with a relatively inert Monel structure maycorrode severely, while a Monel bracket secured to a largealuminum member would result in a relatively superficialattack on the aluminum sheet (refer to Figure 2-5).

2.6.4 Temperature. Higher temperature environmentstend to produce more rapid corrosion due to acceleratedchemical reactions and, in humid environments, higher con-centration of water vapor in the air. In addition, nightly dropsin temperature can cause greater amounts of condensation,leading to increased corrosion rates.

2.6.5 Heat Treatment and Grain Direction. Whenheat-treated, heavy sections of metals do not cool uniformlyand, as a result, tend to vary in chemical composition fromone part of the metal to another. This can cause galvanic

corrosion if one area is more active than another. Alloys,which are fabricated by rolling, extruding, forging, or press-ing, have properties which depend highly on direction (grainlength vs. cross grain). For example, exposed end grainscorrode much more easily than flattened elongated surfaces insheet stock. This explains why exfoliation occurs at the edgeof aircraft skin sections or next to countersunk fasteners.

2.6.6 Electrolytes. Electrically conducting solutions areeasily formed on metallic surfaces when condensation, saltspray, rain, or rinse water accumulate. Dirt, salt, acidic stackgases and engine exhaust gases can dissolve on wet surfaces,increasing the electrical conductivity of the electrolyte,thereby increasing the rate of corrosion.

2.6.7 Oxygen. When some of the electrolyte on a metalsurface is partially confined (such as between faying surfacesor in a deep crevice) metal in this confined area corrodesmore rapidly than other metal surfaces of the same partoutside this area. This type of corrosion is called an oxygenconcentration cell or differential aeration cell. Corrosionoccurs more rapidly than would be expected, because thereduced oxygen content of the confined. electrolyte causes

Figure 2-4. Galvanic Corrosion in a Flashlight Bat-tery

Figure 2-5. Effect of Area Relationship in DissimilarMetal Contacts

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the adjacent metal to become anodic to other metal surfaceareas on the same part immersed in electrolyte exposed to theair.

2.6.8 Electrolyte Concentration. In the same way thatmetals can corrode when exposed to different concentrationsof oxygen in an electrolyte, corrosion will also occur if theconcentration of the electrolyte on the surface varies from onelocation to another. This corrosive situation is known as aconcentration cell.

2.6.9 Biological Organisms. Slimes, molds, fungi andother living organisms (some microscopic) can grow on dampsurfaces. Once they are well established, the area tends toremain damp, increasing the possibility of corrosion. Theirpresence can cause the areas they occupy to have differentoxygen and electrolyte concentrations. In addition, corrosivewastes are secreted, which cause corrosion.

2.6.10 Mechanical Stress. Almost all alloys used inaircraft construction are sensitive to a form of corrosionknown as stress corrosion cracking. Manufacturing processessuch as machining, forming, welding, or heat treatment canleave stresses in aircraft parts. This residual stress and/orstress applied to a part causes corrosion to proceed morerapidly in structurally important regions of the part untilfailure occurs.

2.6.11 Time. As time goes on, metals naturally tend tocorrode. In some cases, the corrosion process occurs at thesame rate, no matter how long the metal has been exposed tothe environment. In other cases, corrosion can decrease withtime, due to the barrier formed by corrosion products, orincrease with time if a barrier to corrosion is being brokendown.

2.7 TYPES OF CORROSION.

Corrosion is catalogued and typed in many ways. Occasion-ally, different names are used for the same type of corrosion.The common types of corrosion are described below.

2.7.1 Uniform Surface Corrosion. Uniform surfacecorrosion or etching results from a direct chemical attack ona metal surface and involves only the metal surface. On apolished surface, this type of corrosion is first seen as ageneral dulling or etching of the surface and, if the attack isallowed to continue, the surface becomes rough and possiblyfrosted in appearance. This type of corrosion appears uniformbecause the anodes and cathodes are very small and con-stantly shift from one area of the surface to another. Anexample is the etching of metals by acids. The discolorationor general dulling of metal created by exposure to elevatedtemperatures is not considered to be uniform surface corro-sion.

2.7.2 Galvanic Corrosion. Galvanic corrosion occurswhen different metals are in contact with each other and anelectrolyte, such as salt water. It is usually recognizable bythe presence of a buildup of corrosion at the joint between themetals. For example, aluminum skin panels and stainless steeldoublers, riveted together in an aircraft wing, form a galvaniccouple if moisture and contamination are present. Figure 2-6shows galvanic corrosion of magnesium adjacent to steelfasteners. When metals which are known to be in electricalcontact are well separated from each other in Figure 2-16,galvanic corrosion is probably occurring.

Figure 2-6. Galvanic Corrosion of Magnesium Adjacent to a Steel Fastener

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2.7.3 Pitting Corrosion. The most common corrosionon aluminum and magnesium alloys is called pitting (Figure2-7). It is first noticeable as a white or gray powdery deposit,similar to dust, which blotches the surface. When the depositis cleaned away, tiny pits or holes can be seen in the surface(Figure 2-8). Pitting corrosion can also occur in other types ofalloys. The combination of small active anodes to largepassive cathodes cause severe pitting.

2.7.4 Intergranular Corrosion. Intergranular corrosionis an attack on the grain boundaries of the metal. A highlymagnified cross section of any commercial alloy (refer toFigure 2-9 and Figure 2-10) shows the granular structure ofthe metal. It consists of quantities of individual grains, eachhaving a clearly defined boundary, which chemically differsfrom the metal within the grain. Frequently the grain bound-aries are anodic (tend to corrode more easily) to the metalwithin the grain. When in contact with an electrolyte, rapidcorrosion occurs at the grain boundaries. Figure 2-11 showsintergranular corrosion of 7075-T6 aluminum alloy adjacentto steel fasteners. In this example, the grain boundaries areanodic to both the metal grain and the steel fastener.

2.7.5 Exfoliation Corrosion. Exfoliation (refer to Fig-ure 2-12 and Figure 2-13) is an advanced form of intergranu-

lar corrosion where the surface grains of a metal are lifted upby the force of expanding corrosion products occurring at the

Figure 2-7. Pitting of an Aluminum Wing Assembly

Figure 2-8. Cross-section of Corrosion Pits

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grain boundaries. The lifting up or swelling is visible evi-dence of exfoliation corrosion. Exfoliation occurs on ex-truded, rolled, wrought and forged high strength aluminumand magnesium parts.

2.7.6 Crevice/Concentration Cell Corrosion. Crevicecorrosion occurs when the electrolyte has a different concen-tration from one area to another. Electrolyte inside the crevice

Figure 2-9. Cross-section of 7075-T6 Aluminum Al-loy

Figure 2-10. Grain Structure of a Corroding Alumi-num Surface

Figure 2-11. Intergranular Corrosion of 7075-T6Aluminum Adjacent to Steel Fastener

Figure 2-12. Example of Exfoliation

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contains less oxygen and more metal ions than electrolyte justoutside the crevice. As a result, the metal surfaces, eventhough they may be part of the same metal, have differentactivities and corrosion occurs inside the crevice. This kind ofcorrosion also occurs when a surface is covered by a foreignmaterial. There are three general types of crevice/concentra-tion cell corrosion (1) metal ion concentration cells (2)oxygen concentration cells; and (3) active-passive cells (Fig-ure 2-14).

2.7.6.1 Metal Ion Concentration Cells. Stagnant elec-trolytes under faying surfaces will normally have a highconcentration of metal ions, while a low concentration ofmetal ions will exist adjacent to the crevice created by thefaying surface. The area of the metal in contact with thehigher concentration of metal ions will be cathodic and notshow signs of corrosion, but the area in contact with the lowermetal ion concentration will be anodic and suffer corrosion.Figure 2-14, view A, illustrates metal ion concentration cellcorrosion.

2.7.6.2 Oxygen Concentration Cells. Electrolyte incontact with metal surfaces will normally contain dissolved

oxygen. An oxygen cell can develop at any point where theoxygen in the air is not allowed to diffuse into the solution,thereby creating a difference in oxygen concentration be-tween two points. Typical locations of oxygen concentrationcells are under either metallic or non-metallic deposits (dirt)on the metal surface and under faying surfaces such as rivetedlap joints. Oxygen cells can also develop under gaskets,wood, rubber, plastic tape and other materials in contact withthe metal surface. Corrosion will occur in the area of lowoxygen concentration (anode) as illustrated in Figure 2-14,view B. Alloys such as stainless steel, which owe theircorrosion resistance to surface passivity, are particularlysusceptible to this type of crevice/concentration cell corro-sion.

2.7.6.3 Active/Passive Cells. Metals which depend ona tightly adhering passive film, such as the oxide film oncorrosion resistant steel, are prone to rapid corrosive attackby active-passive cells. The corrosive action usually startswith a deposit of dirt or salt, which creates an oxygenconcentration cell. The passive film is then broken in the areaof the salt deposit and the more active metal beneath thepassive film will be prone to corrosive attack. This smallanodic area will corrode rapidly due to the much larger areaof the surrounding cathode (passive film). The result is rapidpitting of the surface, as illustrated in Figure 2-14, view C.

2.7.6.4 Stress Corrosion Cracking. Stress corrosioncracking (Figure 2-14) is the intergranular or transgranularcracking of a metal caused by the combined effects ofconstant tensile stress (internal or applied) and corrosion.Internal or residual stresses are produced by cold working,forming and heat treatment operations during manufacture ofa part and remain concealed in the part unless stress reliefoperations are used. Other hidden stresses are induced inparts when press or shrink fits are used and when slightlymismatched parts are clamped together with rivets and bolts.All these stresses add to those caused by applying normalloads to parts in operation. Metals have threshold stressesbelow which stress corrosion cracking will not occur. Thisthreshold stress varies from metal to metal, is different fordifferent tempers of the same metal and is different for eachof the three grain directions in which stress can be applied.

Figure 2-13. Another Example of Exfoliation

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Figure 2-14. Concentration Cell Corrosion

Figure 2-15. Stress Corrosion Cracking

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2.7.6.5 Associated Hazards. Stress corrosion crackingis an extremely dangerous type of failure because it can occurat stress levels far below the rated strength of a metal, startingfrom what is thought to be a very minor corrosion pit. Partscan completely sever in a split second or they can crackslowly, and the rate of cracking is very unpredictable inoperating service. As an example, 7075-T6 aluminum alloycan fail by stress corrosion cracking when a stress which is

only 10% of its rated strength is present across the thicknessof its metal grains or the short transverse grain direction.

2.7.6.6 Causes. Specific environments have been iden-tified which cause stress corrosion cracking of certain alloys.Salt solutions, seawater, and moist salt laden air may causestress corrosion cracking of heat treatable aluminum alloys,

Figure 2-16. Galvanic Series of Metals and Alloys in Sea Water

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high strength steels, stainless steels, and some titaniumalloys. Magnesium alloys may stress corrode in moist air.Stress corrosion can be prevented by placing an insulatingbarrier between the metal and the corrosive environment suchas protective coatings and water displacing corrosion preven-tive compounds. Stress relief operations during fabrication ofparts will help, because it lowers the residual stress level inthe parts. Shot peening a metal increases resistance to stresscorrosion cracking by creating compressive stresses on thesurface, which must be overcome by an applied tensile stressbefore the surface sees any tension load.

2.7.7 Corrosion Fatigue. Corrosion fatigue is thecracking of metals caused by the combined effects of cyclicstress and corrosion, and is very similar to stress corrosioncracking. No metal is immune to a reduction of its resistanceto cyclic stressing if it is in a corrosive environment. Damagefrom corrosion fatigue is greater than the sum of the damagefrom both cyclic stresses and corrosion. Corrosion fatiguefailure occurs in two stages: During the first stage, thecombined action of corrosion and cyclic stress damages themetal by pitting and crack formation in the pitted area. Thesecond stage is the continuation of crack propagation by astraight fatigue mode, in which the rate of cracking iscontrolled by: the stress concentration in the main crosssection; and the physical properties of the metal. Fracture ofa metal part due to corrosion fatigue occurs at a stress farbelow the fatigue limit even though the amount of corrosionmay be very small. For this reason, protection of all parts

subject to alternating stress is particularly important, even inenvironments that are only mildly corrosive. Preventivemeasures are the same as those given above for stresscorrosion cracking.

2.7.8 Filiform Corrosion. Filiform corrosion (refer toFigure 2-17) is a special form of oxygen concentration cellcorrosion or crevice corrosion, which occurs on metal sur-faces having an organic coating system. It is recognized by itscharacteristic wormlike trace of corrosion products beneaththe paint film. Filiform occurs when the relative humidity ofthe air is between 78 and 90%, and when the surface isslightly acidic. It starts at breaks in the coating system, suchas scratches and cracks around fasteners and seams, andproceeds underneath the coating, due to the diffusion of watervapor and oxygen from the air through the coating (refer toFigure 2-18). Filiform corrosion can attack steel, magnesium,and aluminum surfaces, and may lead to more seriouscorrosion in some locations. Filiform corrosion can beprevented by storing equipment and aircraft in an environ-ment with a relative humidity below 70%, by using coatingsystems having a low rate of diffusion for oxygen and watervapors, by maintaining coatings in good condition, and bywashing equipment and aircraft to remove acidic contami-nants from the surface (such as those created by pollutants inthe air). Maintain coatings in good condition (prompttouch-up around fasteners) and apply corrosion preventivecompounds (CPC’s) when paint is damaged.

Figure 2-17. Filiform Corrosion Found Under Paint Coating on a Magnesium Panel

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2.7.9 Fretting Corrosion. This is a special form ofconcentration cell corrosion, which occurs in combinationwith surface wear. The corrosion products increase the wearof the surface and the wear exposes more bare metal surfaceto be corroded. The overall effect is greater than the singleeffects of corrosion and wear added together. It has thegeneral appearance of galling, in which chunks of metal aretorn from the surface with corrosion at the torn areas orragged pits. This type of corrosion occurs on faying surfacesof close tolerance and on parts under high pressure in acorrosive environment when there is slight relative movementof the parts such as that caused by vibration. Frettingcorrosion is normally encountered in heavily loaded staticjoints which are subject to vibration and are not and/or cannotbe sealed to prevent moisture entry, such as landing gearcomponent attachment areas having lug holes with slightpress fits or slip fit bushings with very close tolerance boltspassing through the bushings. Another area is wing rootaccess panels or wing-to-body fairings, which are generallynot tightly secured and cannot be sealed in faying surfaces.

2.7.10 High Temperature Oxidation (Hot Corro-sion). Corrosion in the absence of water can occur at hightemperatures, such as those found in turbine engine compres-sors and hot sections. When hot enough, metals can reactdirectly with the surrounding gases producing oxide scale(by-products of oxidation). Contaminants, such as chloridesand sulfates (by-products of sulfidation), can accelerate thehot corrosion reaction by reducing the melting point of themetallic oxide and promoting its vaporization. High tempera-ture ceramic coatings can reduce this type of corrosion, butare usually applied only by the manufacturer due to highlyspecialized equipment required for application.

2.8 METALS AFFECTED BY CORROSION.

Characteristics of corrosion on metals are summarized inTable 2-1. The following is a discussion of corrosion char-acteristics of metals commonly used on aircraft, missiles, andrelated equipment.

2.8.1 Magnesium. Magnesium alloys are the lighteststructural metals used for aircraft and missile airframes.These alloys are highly susceptible to corrosion, whichappears as white, powdery mounds or spots when the metalsurface is exposed to the environment without a protectivefinish (refer to Figure 2-19). The normal oxide-carbonate filmformed on magnesium alloys does not provide sufficientcorrosion protection even in the mildest environment. Thecorrosion rate of a magnesium alloy increases when the alloyis immersed in water, periodically subjected to moisture,coupled to a dissimilar metal, or exposed to water in whichconductive contaminants are dissolved. Corrosion of magne-sium alloys can be greatly diminished by the use of the properprotective finish. Some magnesium parts in current aircraftand missiles have been originally protected by anodizingprocesses, such as the ASTM D1732, Class II, Type III(MIL-M-45202, Type I, Class A) HAE and the ASTM D1732,Class II, Type II (MIL-M-45202, Type I, Class C) DOW 17coatings. The HAE process can be identified by the brown tomottled gray appearance of the unpainted surface. DOW 17coatings have a green to grayish-green color. Coatings of thistype are thicker than those applied by immersion or brushing.Anodized finishes cannot be restored in the field. Care shouldbe taken to minimize removal of these coatings.

Figure 2-18. Schematic of the Development of Filiform Corrosion on an Aluminum Alloy

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2.8.2 Steel. Ferrous (iron) alloys are used to manufac-ture many aircraft and missile components, and massivestructural assemblies in aircraft and missile ground supportequipment, such as missile gantries, silo crib structures,frames and bodies of trailers and vans, and lesser structuralparts such as brackets, racks, and panels. If unprotected,ferrous alloy surfaces (with the exception of CorrosionResistant Steels (CRES) or stainless steels) easily corrode orrust in the presence of moisture. Ferrous alloy surfaces ofstructures or assemblies are normally painted or plated andpainted to prevent corrosion. Corrosion of steel is easilyrecognized because the corrosion product is red rust (Figure2-20). When ferrous alloys corrode, a dark corrosion product

usually forms first, and when moisture is present, it convertsto red rust. Further attack is promoted by the rust absorbingmoisture from the air.

2.8.3 Aluminum. Aluminum and its alloys are the mostwidely used materials for aircraft and missile construction.Aluminum is highly anodic as evidenced by its position in thegalvanic series (Figure 2-16). However, the formation of atightly adhering oxide film offers increased resistance undermild corrosive conditions. The corrosion products of alumi-num (refer to Figure 2-21) are white to gray powderymaterials (aluminum oxide or hydroxide), which can beremoved by mechanical polishing or brushing with abrasive.It is anodic to most other metals and, when in contact withthem, galvanic corrosion of the aluminum will occur. Alumi-num alloys are subject to pitting, intergranular corrosion,intergranular stress corrosion cracking, and corrosion fatiguecracking. In some cases, the corrosion products of the metalin contact with aluminum are corrosive to aluminum. There-fore, it is necessary to clean and protect aluminum and itsalloys to prevent corrosion. Since pure aluminum is morecorrosion resistant as well as being more anodic than mostalloys, aluminum alloy sheet stock is often covered with athin layer of nearly pure aluminum called alclad. While fullyintact, the alclad layer is very resistant to corrosion because avery adherent oxide film rapidly forms on its surface toprotect it. Alclad is easily removed by harsh treatment withabrasives and tooling, exposing the more corrosion suscep-tible aluminum alloy base metal surface. If the break in thealclad layer is small, the alclad will sacrificially corrode andprotect the exposed base metal alloy because it is more anodicthan the alloy. In such areas, chemical conversion coatings,paints, and corrosion preventive compounds are especiallyimportant. In a marine environment, all aluminum surfacesrequire protection.

Figure 2-19. Magnesium Corrosion Products

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Figure 2-20. Steel Corrosion Products (Rust)

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Figure 2-21. Aluminum Surface Corrosion Products

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Table 2-1. Corrosion of Metals - Type of Attack and Appearance of Corrosion Products

Alloys Type of Attack to Which Alloy Is Susceptible Appearance of Corrosion Product

Magnesium Alloy Highly susceptible to pitting White, powdery, snow-like mounds, andwhite spots on the surface.

Low Alloy Steel(4000-8000 series)

Surface oxidation and pitting; surface andintergranular corrosion

Reddish-brown oxide (rust).

Aluminum Alloy Surface pitting, intergranular, exfoliation,stress corrosion and corrosion fatiguecracking, and fretting

White to gray powder.

Titanium Alloy Highly corrosion resistant; extended or re-peated contact with chlorinated solventsmay result in degradation of the metal’sstructural properties

No visible corrosion products at low tem-perature. Various colored surface oxidesdevelop above 700° F (360° C). Colordependant on temperature.

Cadmium (used as aprotective platingfor steel)

Uniform surface corrosion; used as sacrificialplating to protect steel

From white powdery deposit to brown orblack mottling of the surface.

Stainless Steels (300-400 series)

Crevice/concentration cell corrosion; somepitting in marine environments; corrosioncracking; intergranular corrosion (300 se-ries); surface corrosion (400 series)

Rough surface; sometimes a red, brown, orblack stain.

Nickel-base Alloy(Inconel, Monel)

Generally has excellent corrosion resistancequalities; susceptible to pitting in sea water

Green powdery deposit.

Copper-base Alloy,Brass, Bronze

Surface and intergranular corrosion Blue or blue-green powdery deposit (pa-tina).

Figure 2-22. Cadmium Plated Surface Conditions

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Table 2-1. Corrosion of Metals - Type of Attack and Appearance of Corrosion Products - Continued

Alloys Type of Attack to Which Alloy Is Susceptible Appearance of Corrosion Product

Chromium (plate) Pitting (promotes rusting of steel where pitsoccur in plate)

No visible corrosion products; blistering ofplating due to rusting of the base metaland lifting of plating.

2.8.4 Anodized Aluminum. Some aluminum parts areprotected with an electrochemically applied oxide coating(i.e., anodize). An aluminum oxide film on aluminum is anaturally occurring protective film, and anodizing merelyincreases the thickness and density of the oxide film. Whenthis coating is damaged in service, it can be only partiallyrestored by chemical conversion coating treatment of thedamaged area (Chapter 5, Section II). Avoid damage (e.g.,nicks and scratches) to the anodized surface during process-ing of anodized aluminum alloy parts.

2.8.5 Titanium. Titanium and titanium alloys have manyuses in aircraft and missiles at temperatures up to 1,000° F(540° C). Above 1000° F, titanium readily absorbs gases fromthe surrounding air becoming very brittle. Titanium and itsalloys are highly corrosion resistant because an extremelyadherent oxide film forms on their surfaces almost immedi-ately upon contact with air and thus provides a protectivebarrier. This is identical to the way aluminum forms aprotective oxide film on its surface. Even at temperaturesapproaching 1,000o F, titanium retains its strength andcorrosion resistance. When titanium is heated, different ox-ides having different colors form on the surface. A blue oxidecoating will form at 700° to 800° F (370° to 425° C), a purpleoxide will form at 800° to 950° F (425° to 510° C), and a grayor black oxide will form at 1,000° F (540° C) or higher. Theseare protective discolorations and should not be removed.Titanium is the less active member (cathodic) of mostdissimilar metal couples, and could possibly greatly acceler-ate corrosion of a dissimilar metal coupled to it. However,electrical insulation between titanium and other metals isprovided by the rapidly formed, very adherent, non-conductive oxide film, which prevents galvanic corrosion ofthe other metal. Frequent inspection of such areas is requiredto ensure that the oxide film has not failed and allowedcorrosion to begin. Under certain conditions, chlorides andsome chlorinated solvents may induce stress corrosion crack-ing of certain titanium alloys.

2.8.6 Copper and Copper Alloys. Copper and copperalloys are quite corrosion resistant and corrosion is usuallylimited to staining and tarnish. Generally, such changes insurface conditions are not dangerous and should ordinarilyhave no effect on the part. Copper corrosion is evidenced bythe accumulation of blue or blue-green corrosion products onthe corroded part. Protective paint coatings are seldomrequired because of the inherent resistance of the metal.However, paint finishes may be applied for decorative pur-poses or if the normal tarnish or green patina on the copper isobjectionable. The green patina is merely a thin coating

consisting mainly of basic copper sulfate and perhaps hy-drated copper carbonate. The patina in the thin, firmlyadhering state actually offers increased corrosion protectionto the base metal, but the patina in a rough or frosted stateshould be removed. When coupled with most metals used inaircraft construction, copper is the less active metal andgreatly accelerates corrosion of the other metals. This isespecially true in copper/aluminum couples. Examples areusually found in electrical components and in areas wherecopper bonding strips or wires are fastened to an aluminumchassis or structural components.

2.8.7 Cadmium. Metal parts are plated either to increasethe corrosion resistance of the parts or to develop certainphysical properties on the surface of the parts, such asabrasion (wear) resistance and high temperature oxidationresistance. Parts may also be plated to create a compatibledissimilar metal contact, to provide a satisfactory surface forsoldering, or to provide a sacrificial metal layer. Cadmium isused as a coating to protect metal parts and to provide acompatible surface when a part is in contact with othermaterials. Attack on cadmium is evidenced by brown to blackmottling of the surface or as white powdery corrosionproducts. When cadmium shows mottling and isolated voidsor cracks in the coating, the plating is still performing itsprotective function. The cadmium plate on iron or steelcontinues to protect until such time as actual iron rust appears(refer to Figure 2-22). Even then, any mechanical removal ofcorrosion products should be limited to metal surfaces fromwhich the cadmium has been depleted.

2.8.8 CRES/Stainless Steel. Basically, stainless steels,or corrosion resistant steels (CRES), as they are moreproperly described, are alloys of iron with chromium andnickel. Many other elements, such as sulfur, molybdenum,vanadium, cobalt, columbium, titanium, and aluminum areadded in various amounts and combinations to developspecial characteristics. Stainless/CRES steels are much moreresistant to common rusting, chemical action, and hightemperature oxidation than ordinary steels, due to the forma-tion of an invisible oxide film or passive layer on the surfaceof these alloys. Corrosion and heat resistance are the majorfactors in selecting stainless/CRES steels for a specificapplication. However, it should be well understood thatstainless/CRES steels are not the cure-all for all corrosionproblems, due to service conditions, which can destroy theoxide film on their surfaces. Stainless/CRES steels are highlysusceptible to crevice/concentration cell corrosion and stresscorrosion cracking in moist, salt laden environments and cancause galvanic corrosion of almost any other metal with

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which they are in contact if proper techniques of sealing andprotective coating are ignored. Stainless/CRES steels may bemagnetic or non-magnetic. The magnetic steels are identifiedby numbers in the American Iron and Steel Institute (AISI)400-series, such as 410, 430, etc. These steels are not ascorrosion resistant as the non-magnetic steels which areidentified by numbers in the AISI 300-series, such as 304,316, etc. The AISI 300-series steels have nickel contentsranging from 6% to 22%, while the 400-series steels havenickel contents of only 2%.

2.8.9 Nickel and Chromium. Nickel and chromium areused as protective platings. Chromium plating is also used toprovide a smooth, wear-resistant surface and to reclaim wornparts. Where corrosion resistance in a marine environment isrequired, a nickel under-coat is used. The degree of protectionis dependent upon plating thickness. Both of these metalsform continuous oxide coatings that can be polished to a highluster and still protect not only themselves but also anyunderlying metal. Chromium platings contain micro-cracks,and corrosion/rust originates on the base metal below theseseparations and spalls the plating from the surface. Figure2-22 shows the results of a failed chromium plate.

2.8.10 Silver, Platinum, and Gold. These metals do notcorrode in the ordinary sense, although silver tarnishes in thepresence of sulfur. The tarnish is a brown-to-black film. Goldtarnish is not really corrosion but is a very thin layer of soilsor contaminants that shows up as a darkening of the reflectingsurfaces. All these metals are highly cathodic to almost allother metals and can cause severe galvanic corrosion ofalmost any metal with which they are in contact in thepresence of moisture if joint areas are not sealed or otherwiseinsulated.

2.8.11 Graphite/Carbon Fiber Composites. Graphiteor carbon fiber composites are materials, which consist ofreinforcing fibers in a matrix, made of organic resin, usuallyepoxy. They are an important class of aviation materialsbecause of their high strength-to-weight ratios and highstiffness. Since carbon is the least active metal in the galvanicseries, it will accelerate the corrosion of any aircraft metal towhich it is coupled. Insulation between graphite or carbonepoxy composites and other metals is necessary to preventdissimilar metal attack on the attached part.

Figure 2-23. Failed Chromium Plating

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2.9 CORROSIVE ENVIRONMENTS.

Corrosion of aircraft, missiles, and equipment is caused byboth natural and man-made environments. Natural condi-tions, which affect the corrosion process, are moisture,temperature, salt atmospheres, ozone, sand, dust, solar radia-tion, insects and birds, and microorganisms. Man-madeconditions, which also affect the corrosion process, areindustrial pollution, manufacturing operations, storage con-ditions, and shipment. By understanding these conditions,maintenance personnel will be better able to prevent aircraftdamage.

2.9.1 Moisture. Moisture is present in air as a gas (watervapor) or as finely divided droplets of liquid (mist or fog) andoften contains contaminants such as chlorides, sulfates, andnitrates, which increase its corrosive effects. Moisture entersall areas of an aircraft or missile that air can enter. Allenclosed areas, which are not sealed, allow air to enter andleave as the difference in pressure between inside and outsidechanges. These pressure differences occur when the aircraftchanges altitude, when atmospheric pressure changes, andwhen the temperature of air inside an enclosed area changes.Moisture will condense out of air when the air becomes toocool to hold all of the moisture in it. The dew found onaircraft and missile exteriors and many times on their interiorsurfaces after a cool night is the result of condensation.

2.9.1.1 Condensed Moisture. Condensed moisturewill usually evaporate as surrounding air warms, but willleave its contaminants (residues), including salts, behind.This can result in the build-up of soils and salt contamination.Condensed moisture and its contaminants can also be trappedin close fitting wetable joints, such as faying surfaces. Somegasket and packing materials will absorb several times theirweight in water and, when heated, can transmit this retainedmoisture into the sealed area. Moisture can accumulate insuch areas through successive cycles of warming and coolingleaving pools of moisture and a relative humidity approach-ing 100%. This is known as the desert still effect. In addition,moisture can be drawn into poor bond lines by capillaryaction (wicking). Conditions of temperature and humidity canvary widely in separate sections of aircraft depending on thesuccess of environmental sealing condensation, and locationnear heat-generating equipment.

2.9.1.2 Effect of Moisture. Electrolyte formation resultsfrom condensation and/or collection of moisture. All non-metals absorb some moisture, which may cause changes indimensional stability, dielectric strengths, ignition voltages,and volume insulation resistances. In general, organic matrixcomposites are adversely affected by moisture and may suffera loss of strength and stiffness from exposure. Hermeticsealing (liquid and vapor proof at normal temperatures andpressures) is recommended for moisture-critical items such ascapacitors and quartz crystals. Refer to TO 1-1-689 foradditional information related to electronics equipment.

2.9.2 Temperature. Temperatures at the high end of therange for which equipment is designed may result in either

improvement or degradation of equipment, depending onconditions. Some electronic equipment may not functionproperly at high temperatures. Generally, corrosion and otherharmful processes (such as the degradation of non-metallicmaterials) increase as temperatures rise, but in some in-stances, moderate increases in temperature may serve toreduce corrosion by preventing condensation. Growth ofmolds and bacteria is also inhibited by temperatures above104° F (40° C). Temperatures at the low end of the designrange generally reduce the rate of corrosion.

2.9.3 Salt Atmospheres. When dissolved in water, saltparticles form strong electrolytes. The ocean, which carriesfrom 3.5 to 3.9% salt, is the world’s primary source of salt.Normal sea winds carry from 10 to 100 pounds of sea salt percubic mile of air. Since dissolved salts are strong electrolytes,it is easy to understand why shipboard and coastal environ-ments are highly corrosive.

2.9.4 Ozone. Ozone is a particularly active form ofoxygen, which is formed naturally during thunderstorms, byarcing in electrical devices, and by photochemical reactionsin smog. When ozone is absorbed by electrolyte solutions incontact with metals, it increases the rate of corrosion. It alsooxidizes many nonmetallic materials, being particularlyharmful to natural and certain types of synthetic rubber.Rubber seals stored near welding equipment have experi-enced complete degradation.

2.9.5 Other Industrial Pollutants. Carbon (from inter-nal combustion engine exhaust), nitrates (from agriculturalfertilizers), ozone (from electrical motors and welding opera-tions), sulfur dioxide (from engine exhaust and industrial andship smoke stacks), and sulfates (from automobile exhaust)are important airborne pollutants. The combination of thesepollutants contributes to the deterioration of non-metallicmaterials and severe corrosion of metals.

2.9.6 Sand, Dust, and Volcanic Ash. Sand, dust, andvolcanic ash are present in many areas. In industrial areas,they often contain a number of tar products, ashes, and soot.Dust is also found in the tropic zones during times of little orno rainfall. Sand and dust are extreme problems in thedeserts, since dry, powdery sand and dust are carried by wind.During sandstorms, they can penetrate sealed equipment aswell as many internal areas of airframes, and small sandparticles are often blown as high as 10,000 feet by thesiroccos hot, dust laden winds). Sand, dust and volcanic ashare hygroscopic and, when present on internal or externalsurfaces of aircraft or electronic parts, can absorb and holdmoisture. The presence of sand, dust, and volcanic ash mayalso effect the operation of electrical contacts, prevent properaction of rotating motor-drive devices, and cause malfunc-tions of indicating instruments. Dust from volcanic areascontains chlorides and sulfates, which are extremely corro-sive in the presence of moisture. Although small amounts ofsand or dust may be unnoticed by operating personnel, theymay be sufficient to promote corrosion and wear.

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2.9.7 Solar Radiation. The two ranges of solar radiationmost damaging to materials are ultraviolet, the range thatcauses sunburn, and infrared, the range that makes sunlightfeel warm. On earth, maximum solar radiation occurs in thetropics and equatorial regions, but considerable damageoccurs in the temperate zones as a result of solar heating,photochemical effects, and combinations of these two phe-nomena. Non-metals, especially organic and synthetic mate-rials, are strongly affected by sunlight. Both natural andsynthetic rubber deteriorates rapidly in sunlight. After ex-tended exposure, plastics darken, paints lose their protectivecharacteristics, polymers undergo marked decreases instrength and toughness, and colors fade. This can lead toremoval of essential color-coding on tubing and electroniccomponents. Most electronic equipment is housed in en-closed structures and is protected from solar radiation. Extracare must be taken in the selection and surface treatment ofparts, such as cables and harnesses that are to be exposed toexterior environments.

2.9.8 Climate. Warm, moist air, normally found intropical climates, tends to accelerate corrosion while cold, dryair, normally found in arctic climates, tends to reducecorrosion rates. Corrosion does not occur in very dry condi-tions. For this reason, desiccants are used in shipping con-tainers to produce very dry local environments. The opera-tional climate extremes have always been considered inaircraft design. However, certain areas within an aircraft,such as the cockpit and air-conditioned equipment bays, maybe subjected to climatic conditions very different fromexternal areas of the aircraft. Relatively warm, dry air that hasbeen cooled by air conditioners, thus increasing its relativehumidity, and ducted into interior areas of the aircraft withoutdrying or passing it through an expansion valve can releasesufficient moisture to accelerate corrosion. It is imperative toconsider not only the exterior operational environment butalso the environments in which the equipment will befabricated, transported, reworked, repaired, and mountedinside the aircraft or missile.

2.9.8.1 Desert. Hot, wind-swept deserts create a severemaintenance problem because powdery dust can penetrateeven supposedly sealed components. High daytime tempera-tures, high humidities (in areas such as the Persian Gulf),ultraviolet radiation, and fine dust are the four most serious,destructive elements of the desert climate. Non-metallicmaterials suffer the most damage from the hot desert climateswhere air temperature during the day may reach 124° F (51°C). Temperatures inside closed containers may be 100° F (38°C) higher than external air temperatures.

2.9.8.2 Temperate Zones. The temperate or interme-diate climate zone encompasses most of the North Americanand European continents. These areas at various times of theyear may approximate the extremes of polar, desert, ortropical temperatures and humidity. The temperate zonetemperatures range from -25° to +59° F (-32° to +15° C) in

the winter and from +59° to +125° F (+15° to +52° C) in thesummer. The relative humidity (RH) also fluctuates between5 and 100. The most critical areas are coastal locations,during the warm periods of the year in which the RHapproaches 100at night and the air has high concentrations ofsalt. Moisture from this salt-laden air can condense onequipment during early evening and morning hours, therebycausing serious corrosion. Because of its relatively mildtemperatures, the temperate zone is also the most heavilypopulated. Consequently the smoke, smog, ozone, and cor-rosive fumes associated with heavy industry are also foundthere.

2.9.8.3 Tropics. The greatest challenge to the aircraftand missile industries is to the design equipment that isprotected from corrosion and deterioration in the heat andhumidity of tropical climates. Even though they encompassonly a small portion of the earth’s land area, the tropicsdemand the greatest amount of consideration from the stand-point of corrosion treatment and control. Relative humiditiesof up to 100at ambient air temperatures of 85° F (29° C) andabove create a formidable threat of corrosion. When highhumidity and temperature conditions are combined withsalt-laden air, the corrosive environment becomes extremelysevere. The critical combination of high temperatures, con-densation, high relative humidity, and contaminants such assalt and sand may cause catastrophic failure of equipment.Deterioration of the materials used in electronic equipmentmay also be accelerated.

2.9.9 Factors of Influence in Tropical Environ-ments. Tropical environments are noted for long periodsof heavy rainfall, during which 100 inches or more of rainmay fall. Extended periods of high heat and humiditycontribute to rapid corrosion of metals, cracking and flakingof rubber and plastic materials, and deterioration of seals.Equipment, whether stored or in use, requires special protec-tive containers/measures and frequent preventive mainte-nance. Microorganisms multiply excessively in tropical en-vironments and attack many non-metallic materials. Manyitems become covered with fungi in a matter of hours.Electronic equipment requires special efforts for effectiveoperation in the tropics. Intensive preventive maintenanceand the best possible protective techniques are necessary foraircraft, missiles, and their components in tropical environ-ments.

2.9.10 Manufacturing. During the manufacture, assem-bly, or repair of aircraft, missiles, and their subsystems, manyfactors that might lead to corrosion may be introduced. Theuse of unsuitable materials and improper materials processingcan cause corrosion. The shearing or hole-punching opera-tions on some metal alloys, especially high strength alumi-num, may introduce stresses that eventually lead to stresscorrosion cracking. Assembly of parts in areas contaminatedby fumes or vapors from adjacent operations may result inentrapment of the fumes or vapors in the equipment which

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may cause future corrosion. Spaces that are air conditionedwithout humidity control may be sources of condensedmoisture.

2.9.11 Storage. Even traces of corrosive vapors inpackages containing aircraft or missile parts may result inserious corrosion. Moreover, the natural breathing of pack-ages may introduce moisture into the parts and equipment.Some packing materials have been known to decompose andemit corrosive vapors during periods of prolonged storage.Refer to TO 1-1-17 and the system specific (-17) manual foradditional storage information.

2.9.12 Shipment. During shipment, materials such asplastics and lubricants are often exposed to environments thatwere not considered during the design stage. Materialsshipped by air are subjected to changes in atmosphericpressure and can lose volatile components by out-gassing.The vibration and mechanical shocks associated with ship-ment by truck can damage protective coatings or platings.Shipment by ocean vessel may expose the equipment tocorrosive marine environments, vibrations and shock fromengines or sea conditions, and residual corrosive vapors fromprevious shipments. Although packaging equipment in accor-dance with MIL-STD-2073-1 will protect the equipment fromcorrosive environments, packaging may be damaged duringhandling and thus become ineffective.

2.9.13 Industrial and Ship Emitted Air Pollutants.Smog, smoke, soot, and other airborne contaminants areextremely corrosive to exposed aircraft, missiles, and equip-ment. Many of the fumes and vapors emitted by ships andfrom factories can greatly accelerate metal corrosion. Indus-trial atmospheres may exist over large areas, since wind maycarry these corrodents many miles from their source. Gener-ally, air pollutants, when combined with water, create elec-trolytic solutions and accelerate corrosion.

2.9.14 Animal Damage. Damage to aircraft, missiles,and their subsystems may be caused by insects, birds, andvarious small animals, especially in tropical environments.Equipment in storage is most susceptible to this type ofattack, since animals may enter through vent holes or tears inpackaging and sometimes build nests. Moisture absorbed bynests plus excretions from animals may cause corrosion anddeterioration that goes unnoticed until equipment is put intouse and fails. Another type of damage may occur whenorganic materials, such as upholstery, are shredded for nestsor consumed as food.

2.9.15 Micro-Organisms. Microbial attack includes theaction of bacteria, fungi, or molds. Micro-organisms arenearly everywhere and outnumber all other types of livingorganisms. Organisms that cause the greatest corrosion prob-lems are bacteria and fungi. Damage resulting from microbialgrowth can result from: (1) the tendency of the growth to hold

moisture which then causes corrosion; (2) digestion of thesubstrate as food for the microorganism; or (3) corrosion ofthe surface beneath the growth by secreted corrosive fluids

2.9.15.1 Bacteria. Bacteria may be either aerobic oranaerobic. Aerobic bacteria require oxygen to live. They canaccelerate corrosion by oxidizing sulfur to produce sulfuricacid or ammonia to produce nitric acid. Bacteria living on oradjacent to metals may promote corrosion either by depletingthe oxygen supply or by releasing metabolic products.Anaerobic bacteria, on the other hand, can survive only whenfree oxygen is not present. The metabolism of these bacteriarequires them to obtain food sources by oxidizing inorganiccompounds such as iron, sulfur, hydrogen, and carbon mon-oxide. The resultant chemical reactions cause corrosion.

2.9.15.2 Microbial Growth Requirements. Fungimake up one class of microorganisms that feed on organicmatter. Low humidity levels inhibit the growth of mostspecies of fungi and bacteria. Ideal growth conditions formost fungi and bacteria are temperatures of +68° to +104° F(+20° to +40° C) and relative humidities of 85 to 100%. Itwas formerly believed that microbial attack could be pre-vented by applying moisture-proof coatings to nutrient ma-terials or by drying the interiors of compartments withdesiccants. However, some moisure-proof coatings are at-tacked by microorganisms, especially if the surface to whichthey are applied is contaminated. Some microorganisms cansurvive in spore form for long periods while dry, and canbecome active when moisture is available. When desiccantsbecome saturated, they form what is known as a “desiccantpump” which pumps their absorbed moisture into the affectedarea by evaporation and allows microorganisms to begin togrow. Dirt, dust, and other airborne contaminants are the leastrecognized contributors to microbial attack. Unnoticed, smallamounts of airborne debris may be sufficient to promotefungal growth by absorbing moisture.

2.9.15.3 Microbial Nutrients. Since fungi, bacteria, andother microorganisms are classified as living, it was previ-ously thought that only materials derived from living organ-isms could provide them with food. Thus wool, cotton,feathers, leather, etc., were known to be microbial nutrients.To a large extent this rule of thumb is still valid, but theincreasing complexity of synthetic materials makes it diffi-cult, if not impossible, to determine from the name alonewhether a material will support growth of microorganisms.Many otherwise resistant synthetic materials are renderedsusceptible to microbial attack by the addition of chemicals,which change the properties of the material. In addition,different species of microorganisms have different growthrequirements. The service life, size, shape, surface smooth-ness, cleanliness, environment, and species of microorganisminvolved all determine the degree of microbial attack on theaffected item.

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2.10 DEGRADATION OF NON-METALS.

Non-metallic materials (plastics, elastomers, paints, and ad-hesives) are not subject to electrochemical corrosion, sinceions are not easily formed from non-metallic materials andtheir electrical conductivity is extremely low. The degrada-tion of non-metals depends on the chemical makeup of thematerial and the nature of the environment. In 2-10. general,non-metallic materials on aircraft, missiles, and related equip-ment are selected for their obvious performance properties(flexibility, transparency, strength, electrical resistance, etc.)as well as their resistance to heat, impact, abrasion, ultravioletradiation, moisture, ozone and other detrimental gases, andoperational fluids such as hydraulic fluid, lube oil, cleaners,deicing fluids, etc. However, the use of unauthorized main-tenance chemicals and procedures can accelerate degradationand ultimately lead to material failure resulting in leakage,corrosion, electrical shorts, crazing, and/or mechanical fail-ure.

2.11 PREVENTIVE MAINTENANCE.

The two most important factors in preventing corrosion, andthe only ones which can be controlled by field personnel, arethe removal of the electrolyte and the application of protec-tive coatings. Since the extent of corrosion depends on thelength of time electrolytes are in contact with metals, corro-sion can be minimized by frequent washing. If non-corrosivecleaners are used, the more frequently a surface is cleaned ina corrosive environment the less the possibility of corrosiveattack. In addition, by maintaining chemical treatments, paintfinishes, lubricants, and corrosion preventive compounds(CPC’s) in good condition, corrosion can be minimized. Thedegradation of non-metallic materials can be minimized byavoiding the use of unauthorized maintenance chemicals andprocedures. In addition, when repair or replacement ofnon-metallic materials is required, use only approved mate-rials. Dedication to proper preventive maintenance practicesmaximizes equipment reliability.

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CHAPTER 3PREVENTIVE MAINTENANCE

SECTION I INTRODUCTION

3.1 PREVENTIVE MAINTENANCE PROGRAM.

As directed by AFI 21-105, the prevention and control ofcorrosion on aircraft missiles and related equipment is acommand responsibility. Each command must place specialemphasis on the importance of the corrosion control programand lend its full support to ensure that corrosion preventionand control receives sufficient priority to be accomplishedalong with other required maintenance.

3.1.1 Preventive Maintenance. Aluminum and magne-sium alloys found in aviation equipment will corrode if saltdeposits, other corrosive soils, or electrolytes are allowed toremain on their surfaces. To prevent corrosion, a constantcycle of cleaning, inspection, operational preservation, andlubrication must be followed. Prompt detection and removalof corrosion will limit the extent of damage to aircraftcomponents. An effective preventive maintenance programrequires all of the procedures specified in this chapter, butalso includes corrosion removal, paint removal, surfacetreatment, sealing, and painting. A disciplined preventivemaintenance program includes:

a. Regularly scheduled aircraft washing as specified inTable 3-1.

b. Regularly scheduled cleaning or wipe down of allexposed unpainted surfaces, such as landing gear strutsand actuating rods of hydraulic cylinders with a com-patible fluid or lubricant as specified by system specifictechnical orders.

c. Keeping low-point drains open.

d. Inspection, removal, and reapplication of corrosionpreventive compounds (CPC’s) on a scheduled basis.

e. Earliest detection and repair of damaged protectivecoatings.

f. Using only clean/fresh tap water with low chloridecontent for all aircraft, missile, and equipment washingand rinsing operations. Fresh water used for these washand rinse operations shall meet the following require-ments:

To prevent corrosive salt buildup in the water,water from recycling systems shall also meetthese same quality standards. Recycled watershall be tested every 30 days to ensurecompliance.

(1) Chloride content shall be 400 mg/L maximum(somewhat higher than EPA potable drinking waterstandard of 250 mg/L).

(2) pH shall be between 6.5 and 8.5.

(3) Total dissolved solids (TDS) content shall be 500mg/L maximum.

(4) Total suspended solids (TSS) content shall be 5 mg/Lmaximum.

(5) The Langlier Saturation Index shall be slightly above0.

(6) The biological oxygen demand (BOD) concentrationshall be 5 mg/L maximum.

(7) Adequate disinfection of the water shall be providedto control the growth of microorganisms in the water.

(8) The water hardness shall be between 75 and 150mg/L as CaCO3.

(9) The total petroleum hydrocarbon (TPH) content shallbe 10 mg/L maximum.

g. Using padded panel racks to store panels/parts foraircraft and equipment during maintenance; using pro-tective measures to prevent abrasions/scratches resultingfrom placement of parts, tools, tool boxes, etc. on wings,fuselage or other aircraft surfaces.

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Table 3-1. Aircraft Wash Intervals

Wash Interval By SeverityAir Base Name and Location Severe (30

Days)Moderate (90

Days)Mild (120 Day)

Aj Taif, SA XAl Dhafra UAE XAl Jouf, SA XAl Udeid AB QATAR XAli Al Salem Kuwait XAllen C. Thompson Fld.; Jackson, MS XAltus AFB, OK XAs Sulayyil, SA XAnderson AFB, GU XAnchorage IAP, AK XAndrews AFB, MD (Wash. DC) XAtlantic City, NJ XAviano AB, IT XBagram AB, Afganistan XBahrain XBalad XBangor IAP, ME XBarksdale AFB; Shreveport, LA XBarnes M. Apt.; Westfield, MA XBattle Creek, MI XBeale AFB; Marysville, CA XBirmingham Apt., AL XBoise Air Term., ID (ANG) XBradley IAP; Windsor Locks, CT XBrindisi/Casale AB, IT XBuckley ANGB; Denver, CO XBurlligton IAP, VT XByrd Fld.; Richmond,VA XCannon AFB; Clovis, NM XCapital Mun. Apt.; Springfield, IL XChannel Island; Port Hueneme NAS, CA XCheyenne Apt. WY XCharleston AFB, SC XCharleston Apt. , WV XColumbus AFB, MS XCuracao Netherlands Antilles XCyprus International Airport XDanelly Fld.; Montgomery, AL XDavis-Monthan AFB; Tucson, AZ XDes Moines IAP, IA XDhahran, SA XDiego Garcia XDobbins AFRB; Marietta, GA XDouglas IAP; Charlotte, NC XDover AFB, DE XDuluth IAP, MN X

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Table 3-1. Aircraft Wash Intervals - Continued


Days)Moderate (90

Days)Mild (120 Day)

Dyess AFB; Abilene, TX XEareckson (Shemya) AFB, Aleutian Is., AK XEast. WV Reg. Apt; Martinsburg, WV XEdwards AFB; Rosamond, CA XEglin AFB; Valparaiso, FL XEglin AFB (Aux Fld. #3), FL XEielson AFB, AK XEllington Fld.; Houston, TX XEllsworth AFB; Rapid City, SD XElmendorf AFB; Anchorage, AK XFairchild AFB; Spokane, WA XFairford, UK XFalcon AFB, CO XForbes Fld., KS XFort Smith Mun. Apt., AR XFort Wayne Apt., IN XFrancis E. Warren AFB; Cheyenne, WY XFresno Air Term., CA XGeilenkhirchen, GE XGen. Mitchell IAP; Milwaukee, WI XGrand Forks AFB; Emarado, ND XGreat Falls IAP, MT XGreater Peoria Apt.; IL XGriffiss AFB; Rome, NY XGrissom ARB; Peru, IN XHancock IAP; Syracuse, NY XHanscomb AFB; Bedford, MA XHarrisburg IAP, PA XHector IAP; Fargo, ND XHickam AFB; Honolulu, HI XHill AFB; Ogden, UT XHolloman AFB; Alamogordo, NM XHomestead ARB, FL XHoward AB; Panama XHulman Reg. Apt., IN XHurlburt Fld.; Fort Walton Beach, FL XIncirlick AB, Turkey XIstres AB, France XJacksonville IAP, FL XJeddah, SA XJoe Foss Fld.; Sioux Falls, SD XKadena AB, Japan XKeesler AFB; Biloxi, MS XKey Fld.; Meridian, MS XKhamis Mushay, SA XKhandahar Afghanistan X

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Days)Moderate (90

Days)Mild (120 Day)

Kikuk Iraq XKing Khalid, SA XKingsley Fld.; Klamoth Falls IAP, OR XKirtland AFB, NM; Albuquerque, NM XKunsan AB; S. Korea XLackland AFB, TX XLajes Fld.; Azores, Portugal XLambert Fld., St. Louis IAP, MO XLangley AFB; Hampton, VA XLarnaka International Apt. , Cyprus XLaughlin AFB; Del Rio, TX XLincoln Mun. Apt., NE XLittle Rock AFB, AR XLuke AFB; Glendale, AZ XMacDill AFB; Tampa, FL XMalmstrom AFB; Great Falls, MT XManas Kyrgystan XMansfield Lahm Apt., OH XMantas Ecuador XMarch ARB; Riverside, CA XMartin St. Apt.; Baltimore, MD XMaxwell AFB; Montgomery, AL XMcChord AFB; Tacoma, WA XMcConnell AFB, Wichita, KS XMcEntire ANGB; Columbia, SC XMcGhee Tyson Apt.; Alcoa, TN XMcGuire AFB; Wrightstown, NJ XMcMurdo Station Antarctica XMemphis IAP, TN XMinot AFB, ND XMinn.-St. Paul IAP, MN XMisawa AB, Japan XMoffett Fld., CA XMoody AFB; Valdosta, GA XMountain Home AFB; Boise, ID XNAS Fort Worth, TX XNAS Keflavic, Iceland XNAS New Orleans, LA XNAS Sigonella; Sicily, Italy XNAS Souda Bay (Chania Apt.), Crete XNashville Met. Apt., TN XNellis AFB; Las Vegas, NV XNewburgh Apt. NY XNew Castle Co. Apt.; Wilmington, DE XNiagra Falls IAP, NY XOffutt AFB; Omaha, NE X

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Days)Moderate (90

Days)Mild (120 Day)

O’Hare IAP; Chicago, IL XOsan AB; S. Korea XOtis ANGB; Falmouth, MA XPatrick AFB; Cocoa Beach, Fl, XPease ANGB; Portsmouth, NH XPeterson AFB; Colorado Springs, CO XPittsburgh IAP, PA XPope AFB; Fayetteville, NC XPortland IAP, OR XPrince Sultan AB, Al Kharj, SA XPuerto Rico IAP/Muniz ANGB; San Juan, PR XQuonset St. Apt; Providence, RI XRAF Akrotiri, Cyprus XRAF Lakenheath, UK XRAF Mildenhall, UK XRamstein AB, GE X XRandolph AFB; San Antonio, TX XReno/ Tahoe IAP, NV XRhein-Main, GE XRickenbacker IAP; Columbus, OH XRiyadh, SA XRobins AFB; Warner Robins, GA XRosecrans Mem. Apt.; St. Joseph, MO XSalt Lake City IAP, UT XSchenectady Co. Apt. NY XScott AFB; Belleville, IL XSelfridge ANGB; Mount Clemens, MI XSeymour Johnson AFB; Goldsboro, NC XShaw AFB; Sumter, SC XSheppard AFB; Wichita Falls, TX XSioux Gateway Apt.; Sioux City, IA XSouda Bay, Crete XSky Harbor Apt.; Pheonix, AZ XSpangdalhem AB, GE XSpringfield-Bleckley Mun. Apt., OH XStandiford Fld./Lvle. IAP; Louisville, KY XSuffolk Co. Apt., NY XTabuk, SA XTaegu, S. Korea XTalil Iraq XTinker AFB; Oklahoma City, OK XThumrait Oman XToledo Exp. Apt.; Swanton, OH XTravis AFB; Fairfield, CA XTravis Fld.; Savannah, GA XTruax Fld./Dane City Reg. Apt; Madison, WI X

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Days)Moderate (90

Days)Mild (120 Day)

Tucson IAP, AZ XTulsa IAP, OK XTyndall AFB; Panama City, FL XVance AFB; Enid, OK XVandenburg AFB; Lompoc, CA XWestover AFB; Chicopee, MA XWhiteman AFB; Knobnoster, MO XWillow Grove ARS; Philadelphia, PA XWill Rogers IAP; Oklahoma City, OK XWright-Patterson AFB; Dayton, OH XYeager Apt.; Charleston, WV XYokota AB, Japan XYoungstown-Warren Reg. Apt. ARS, OH X

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SECTION II CLEANING

3.2 INTRODUCTION.

• Authorized cleaning agents and equipment arelisted in this Chapter and Appendixes A and B.Order materials and equipment by NSN fromthe lists in these appendixes through regularsupply channels, or local purchase from vend-ers listed on the most current QPL of aspecification or by vender part number listedin these appendixes for an authorized non-specification material.

• Specification QPL’s are the responsibility ofthe authority for the specification. For infor-mation access, many cleaning and corrosionprevention and control process related speci-fications having a QPL are available, withtheir most current revision, from theAFCPCO, AFRL/MLS-OLR, web site: https://afcpco.robins.af.mil or the Defense TechnicalInformation Center (DTIC) Scientific andTechnical Information Network web site:http://stinet.dtic.mil.

• Do not use unauthorized cleaners. Althoughother commercial cleaners may appear to per-form as well as, or better than, approvedproducts, these materials may be corrosive tometal alloys used in aircraft, missiles, andrelated equipment. They can also acceleratedegradation of non-metallic materials causingmaterial failures, which may result in fluidleakage, corrosion of surrounding metals,electrical shorts, crazing, and/or mechanicalfailure.

NOTE

Ozone depleting substances (ODS) are solventssuch as, but not limited to, 1,1,1 trichloroethane(MIL-T-81533) and trichlorotrifluoroethane(MIL-C-81302). These solvents, as well as prod-ucts containing them, are still used in someaircraft maintenance processes, including oxygensystems cleaning and some avionics cleaning.Alternate materials continue to be identified.Wherever possible, specifications are beingchanged to eliminate their use automatically.Some products that have been reformulated arenow flammable. Pay close attention to all CAU-TION/WARNING labels on solvents and solvent-based products.

3.2.1 Reasons for Cleaning. Aircraft cleaning is thefirst step in preventing aircraft corrosion. Cleaning requires aknowledge of the materials and methods needed to removecorrosive contaminants and fluids, which tend to retaincontaminants. Clean aircraft, missiles, and related equipmentregularly in order to:

a. Prevent corrosion by removing salt deposits, othercorrosive soils, and electrolytes.

b. Maintain visibility through canopies and windows.

c. Allow a thorough inspection for corrosion damage;aircraft washing before Isochronal (ISO)/ Phase inspec-tions is strongly recommended to facilitate corrosioninspections.

d. Maintain turbine engine efficiency.

e. Reduce fire hazards by the removal of accumulations ofleaking fluids.

f. Improve overall appearance.

g. Ensure aerodynamic efficiency of the aircraft.

h. Maintain paint scheme characteristics.

3.2.2 When to Accomplish Work. Accomplish clean-ing and related treatments at the frequency prescribed in thisSection, or more frequently if inspection indicates the need.Inspect areas of missiles not protected from the elements (e.g.rain, dust, snow, etc.) daily. The Aircraft System ProgramDirector (SPD) in conjunction with the Using Command andthe Air Force Corrosion Prevention and Control Office(AFCPCO) shall establish aircraft wash cycle requirements.The Unit Commander shall establish a definite schedule forinspection, cleaning, and corrosion treatment of the unit’sassigned aircraft, missiles, and equipment, and may at his/herdiscretion direct a wash cycle that is more frequent (not lessfrequent) than the established aircraft wash cycle to promotethe professional appearance of assigned aircraft, missiles, andequipment.

3.2.2.1 Cleaning Frequency. The frequency of inspec-tion, cleaning, and related corrosion treatment depends on thetype of systems assigned as well as the existing localenvironmental and other conditions. Table 3-1 specifies therequired aircraft/weapon system wash interval by base orlocation as dictated by existing, recorded environmental andpollution data at each base and/or location unless a differentinterval is specified in a system specific technical order.Under certain local conditions, depending on aircraft type andusage, the established wash cycle may be insufficient. Sometypes of aircraft, missiles, and related equipment may requiremore frequent cleaning of affected areas when:

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NOTE

When unique operational requirements, contin-gencies, droughts, or facility limitations severelyimpact a unit’s ability to wash as prescribed inTable 3-1, the requirement may be temporarilywaived by the MAJCOM Corrosion ProgramManager in conjunction with the Aircraft SystemProgram Director (SPD), who has the final ap-proval authority. The MAJCOM Corrosion Pro-gram Manager must forward a copy of the waiverto the AFCPCO. Each waiver is valid for a periodnot to exceed one year, unless requirementschange.

a. Excessive exhaust or gun blast soil and exhaust gasesaccumulate within impingement areas.

b. Paint is peeling, flaking, or softening.

c. Fluid leakage (coolant, hydraulic fluid, oil, etc.) occurs.

d. Exposure to salt spray, salt water, or other corrosivematerials occurs.

3.2.3 Aircraft Clear Water Rinse Requirements. Air-craft exposed to a salt-water environment require clear waterrinse (CWR). Specific rinse requirements are as follows:

3.2.3.1 All aircraft stationed at bases located within 1.25mi (2 km) of salt water shall be CWR’d at least once every 15days unless washed first. Aircraft flown at low level (under3000 ft) or making two or more take-offs and/or landings,including touch-and-go landings, over salt water require aCWR after the last flight of the day.

3.2.3.2 All aircraft deployed to a location within 1.25 mi(2 km) of salt water for 10 days or more have the same CWRrequirements as if stationed there. When mission require-ments and/or facility limitations prevent accomplishment ofclear water rinsing at the deployed location, make an entry inthe aircraft forms to require a clear water rinse be performedwithin 3 days after return to home station. If an aircraft isdeployed for 30 days or more at a location where it cannot beclear water rinsed, it shall be washed within 5 days afterreturning to home station.

NOTE

When extremely unique operational requirementsor facility limitations severely impact a unit’sability to CWR daily, this requirement may betemporarily waived by the MAJCOM CorrosionProgram Manager in conjunction with the Air-craft System Program Director (SPD) who hasthe final approval authority. The MAJCOM Cor-rosion Program Manager must forward a copy ofthe waiver to the Air Force Corrosion Preventionand Control Office (AFCPCO). Each waiver isvalid for a period not to exceed one year.

3.2.3.3 Any aircraft (primarily transient aircraft) per-forming only a single take-off and/or landing requiringlow-level flight over salt water in a single day are excludedfrom clear water rinsing unless this occurs ten or more timeswithin a 30 day period. After the tenth occurrence, an entryshall be made in the aircraft forms to require a clear waterrinse within five days after returning to home station.

3.2.3.4 Bases that must routinely CWR their assignedaircraft due to low-level flights over salt water may adopt, attheir option, a 15 day CWR program for all their assignedaircraft in lieu of the routine daily rinsing of flyers. Thisoption shall not be granted for aircraft on bases located within1.25 mi (2 km) of salt water or those involved in search,rescue, and recovery missions or any other special operationsover salt water. Approval of a 15 day CWR program must berequested from the Air Force Corrosion Prevention andControl Office (AFCPCO) through the MAJCOM CorrosionProgram Manager. Bases approved for a 15 day CWRprogram shall ensure their Plans and Scheduling Office entersa special inspection requirement into their maintenance datacollection system so that the CWR program is tracked asscheduled maintenance and not just entered into the aircraftAFTO 781K Forms as unscheduled maintenance.

NOTE

Optimum use of taxi-through rinse facilities isrecommended for removal of salt contaminationand light deposits when operating near salt water.CWR does not satisfy aircraft washing require-ments as it only removes readily water-solublematter from aircraft exterior surfaces.

3.2.4 Immediate Cleaning. These affected areas andsoils must be cleaned immediately:

a. Spilled electrolyte and corrosive deposits found aroundbattery terminals and battery area shall be cleaned,neutralized, and treated. Close attention and regularcleaning is required for battery areas of aircraft, mis-siles, and equipment.

b. Areas of aircraft, missiles, and equipment exposed tocorrosive fire extinguishing materials shall be cleanedwithin 4 hours after application if at all possible. If anaircraft, missile, or piece of equipment is impounded byan Accident Investigation Board, the board shall con-sider the corrosive effect of fire fighting materials anddirect their removal as soon as possible consistent withthe accident investigation. Prompt removal of thesematerials saves considerable labor hours and materialswhen salvaging and restoring equipment to a serviceablestatus (Refer to Chapter 8 for instructions).

c. Salt deposits, relief tube waste, or other contaminants.

d. Aircraft, missiles, or equipment exposed to significantamounts of salt water. If shipped or transported via ship

TO 1-1-691

3-8 Change 1

over salt water, they shall be cleaned and given anynecessary treatment after receipt, particularly if thepreservation and/or packaging are damaged.

e. Fungus growth.

f. Chemical, biological, or radiological (CBR) contami-nants. Procedures for CBR decontamination of aircraft,missiles, and equipment are contained in the 00-110-Series technical orders.

g. Spills of corrosive chemicals. An entry in the aircraftAFTO 781A Form shall be made for all corrosivechemical spills, and the chemicals shall be neutralized inaccordance with procedures in AFM 71-4.

3.3 CLEANING COMPOUNDS.

Cleaning compounds work by dissolving soluble soils, emul-sifying oily soils, and suspending solid soils. There areseveral types of cleaning compounds, each of which cleans asurface using one or more of these mechanisms.

3.3.1 Alkaline Cleaners.

When high strength steels (typically 180 KSI andabove), some high strength aluminum, and somestainless steels are exposed to acid paint remov-ers, plating solutions, other acidic materials(cleaners, etc.), and even some alkaline materials,a cathodic reaction on the metal surface produceshydrogen. The hydrogen diffuses into the bulkmetal, accumulating at grain boundaries andweakens the structure. If the part is under load orcontains residual manufacturing stresses, suddencatastrophic failure known as hydrogen em-brittlement occurs when the part can no longersustain the internal and/or applied stresses. Hy-drogen embrittlement has been known to occur inparts stressed to only 15% of the nominal tensilestrength of the metal.

Many alkaline cleaners are not authorized for cleaning of AirForce aircraft, missiles, and related equipment because theyare incompatible with the polyimide insulation on the elec-trical wiring used on many aircraft, missiles, and relatedequipment. Cleaning compounds conforming to MIL-PRF-87937 and MIL-PRF-85570 and that are listed on the QPL foreach specification have been tested and proven compatiblewith polyimide insulation. Types I and IV of MIL-PRF-87937and Types I and II of MIL-PRF-85570 all contain detergentsand foaming agents and work the same way as any detergentsolution. Type I cleaners of both specifications containsolvents and are more effective for removal of heavy oils andgreases such as wire rope lubricant, but they cannot be usedin poorly ventilated areas due to their solvent content. Types

II and IV of MIL-PRF-87937 and Type II of MIL-PRF-85570are all good general cleaners for removal of dirt, grime, lightoils, and hydraulic fluid; and they are usable in confined areassuch as cockpits, cabins, bilges, and equipment bays as theycontain no solvents.

3.3.1.1 MIL-PRF-87937, Type I (terpene solvent based)and MIL-PRF-85570, Type I (aromatic solvent based) clean-ers are water dilutable and biodegradable materials, and arevery good general cleaners for washing aircraft, missiles,components, and support equipment. However, since theycontain solvents, environmental and waste disposal factorsneed to be considered prior to use. Since MIL-PRF-87937,Type I materials contain terpenes which are potentiallycorrosive if entrapped and not completely removed, their usemay be restricted on some weapon systems in specificapplications. Always consult weapon system specific -23TO’s for precautions and/or restrictions on use of this class ofmaterials. These cleaners may be used as alternates forMIL-PRF-87937, Types II and IV, and MIL-PRF-85570,Type II materials. MIL-PRF-87937, Type I cleaners areapproved for use on support equipment (SE) per TO 35-1-3,and aircraft wheels per TO 4W-1-61.

3.3.1.2 MIL-PRF-87937, Types II and IV, and MIL-PRF-85570, Type II cleaners are water dilutable and biodegradablematerials, and are the primary cleaners for washing theexterior of aircraft, missiles, engines, and support equipment(SE). They are excellent materials for removing light tomedium soils (greases, oils, grime, etc.) from almost allsurfaces. Since they contain no solvents, their use is notlimited; except that approval by the aircraft SPD is requiredprior to use on transparent plastic aircraft canopies, windows,and windshields/windscreens. Depending on the type of soilsinvolved, these cleaners may be used in various dilutions assubstitutes for solvents in hand wipe cleaning of greasy andoily areas. Apply them from a pump spray bottle followed bydrying with a clean, lint free cloth. When applied from apump spray bottle at the most dilute mixture recommended,these are excellent cleaners for lightly soiled surfaces inaircraft cabins and cockpits such as non-transparent plasticparts and instrument glass covers.

3.3.1.3 MIL-PRF-87937, Type III and MIL-PRF-85570,Type V are gel type cleaners intended for full strengthapplication with no dilution in areas requiring special clean-ing, such as aircraft wheel wells, control surface wells, andwing butts. They contain small amounts of solvents, deter-gents, and thickening agents, which make them cling verywell to vertical and overhead surfaces. These cleaners arevery effective in emulsifying and/or cleaning heavy depositsof hydraulic fluids, oils, greases, and carbon. In areas wherecomplete rinsing with water can be tolerated, they may beused as direct replacements for solvent cleaners such asMIL-C-43616, MIL-PRF-680, and A-A-59601. To be mosteffective, these materials are applied full strength with nopre-rinsing of the surface, allowed to dwell 5 to 15 minutes,agitated with a non-metallic bristle brush, and then rinsed

TO 1-1-691

Change 1 3-9

thoroughly with tap water. These cleaners are not intended forand shall not be used on transparent plastic aircraft canopies,windows, and windshields/windscreens.

3.3.1.4 MIL-PRF-87937, Type IV is also an excellentheavy duty, water dilutable, solventless cleaner intended forremoval of light to heavy deposits of greases, oils, hydraulicfluids, and carbon from aircraft, missile, and other equipmentsurfaces. It is not intended for and shall not be used ontransparent plastic aircraft canopies and windows.

3.3.1.5 MIL-PRF-85570, Type IV is a cleaner that con-tains solvents, detergents, and suspended rubber particles andis intended for removal of exhaust gas and gun gas residues,smudges, boot marks, and other embedded soils from aircraft,missiles, and other equipment with flat (low gloss)/camou-flage coating systems. When rubbed across a soiled surface,the rubber particles in the cleaner mechanically entrap thesoils like tiny erasers without polishing the surface of thecoating system and increasing its gloss.

NOTE

Solvents used in MIL-PRF-85570, Type IVcleaners may be hazardous air pollutants(HAP’s). Consult with bioenvironmental engi-neering before using this cleaner. MIL-PRF-87937, Types III and IV or MIL-PRF-85570,Type V may be used as alternates.

3.3.1.6 MIL-PRF-85570, Type III is a cleaner that con-tains detergents and fine abrasive particles and is intended forremoval of exhaust gas and gun blast residues from aircraftwith a high gloss coating system. When rubbed across asoiled surface, the abrasive particles mechanically remove thesoils which are then suspended in the detergent whileproducing only a very minimal dulling of the high glosscoating system.

3.3.2 Solvent Emulsion and Aqueous Cleaners forTurbine Engine Gas Path and General Area Clean-ing. MIL-PRF-85704, Types I, II, and III materials aresolvent emulsion (Types I and II) and aqueous (Type III)cleaners intended for cleaning the internal areas or gas path ofaircraft turbine engines. MIL-C-43616, Classes 1 and 1Amaterials are solvent emulsion cleaners intended for generalcleaning of heavily soiled exterior areas of aircraft, missiles,and other equipment. Use only those materials listed on theQPL’s for MIL-PRF-85704 and MIL-C-43616.

3.3.2.1 MIL-PRF-85704, Type I (solvent emulsion witharomatic hydrocarbons) and Type II (aqueous with somenon-aromatic hydrocarbons) are materials intended for clean-ing the interior of an aircraft engine by spraying the cleanerinto the intake while the starter is motoring the engine. Thereis a Type II, RTU (ready-to-use) material that requires nodilution before use, but the bulk form of Type II and Type Imust be diluted with water having a maximum conductivityof 10 micro-mho/centimeter and a pH in the 5.0 to 8.0 rangebefore use. Type III (bulk, same water dilution requirements)

and Type III RTU (ready-to-use with no dilution) are aqueousmaterials with no hydrocarbon solvents intended for cleaningthe interior of an aircraft engine by spraying the cleaner intothe intake while the engine is on line or running per specificengine maintenance instructions. These cleaners work verywell for removal of accumulated salts, dirt, and oily soilsfrom the compressor section and other areas of the gas path ofaircraft engines, and their use is followed by spraying freshtap water through the engine to rinse away the contaminants.

3.3.2.2 MIL-C-43616, Class 1 (bulk- requires dilutionwith tap water) and Class 1A (aerosol- ready-to-use with nodilution) are solvent emulsion cleaners and are very effectivefor removal of oily and greasy soils from general exteriorpainted (polyurethane only) and unpainted areas of aircraft,missiles, and other equipment. The Class 1A aerosol materi-als are excellent spot cleaners for removal of oily and greasysoils.

NOTE

• MIL-PRF-85704 materials are specially for-mulated to minimize corrosion of aircraftturbine engines. Other types of cleaners shallnot be used to clean engine interior areaswithout specific approval by the engine SPMand/or as required by the system specificengine maintenance TO. The system specificengine maintenance TO shall be consulted forinterior cleaning procedures and the require-ment/authorization to use MIL-PRF-85704cleaners.

• MIL-C-43616 solvent emulsion cleaners shallnot be used on non-polyurethane paint systemsand markings as their high solvent content cancause them to fade and/or streak. These clean-ers also leave a very thin oil and/or solventfilm on the surface, so they are not suitable foruse as a final cleaner prior to painting, sealing,or adhesive bonding.

• Large scale use of bulk solvent emulsioncleaners may cause problems for waste watertreatment facilities. Local air pollution regula-tions may restrict the amount and applicationmethods of solvent emulsion cleaners. If so,use MIL-PRF-85704, Type II, RTU in lieu ofthe Type I and the appropriate type of MIL-PRF-87937 or MIL-PRF-85570 in lieu ofMIL-C-43616, Class 1 or 1A.

3.3.3 Aqueous Parts Washer Cleaning Solutions.Materials conforming to and listed on the QPL for MIL-PRF-29602, Type I (liquid concentrate) and Type II (powder)Cleaning Compounds for Parts Washers and Spray Cabinets,either diluted with water (Type I) or dissolved in water (TypeII) in accordance with manufacturer’s instructions are thecleaning agents to be used in high pressure cabinet style partswashers for removing oils and greases from disassembledcomponents. They are not to be used for bearings unless

TO 1-1-691

3-10 Change 1

authorized by system specific technical data. Due to theirmaximum allowable pH of 13.5, MIL-PRF-29602 cleaningsolutions can attack/corrode aluminum alloys. Aircraft SPDand/or equipment SPM engineering authority approval isrequired before cleaning aluminum alloy parts. In addition,many heated MIL-PRF-29602 solutions can attack the IVDAluminum coating used on many high strength steel compo-nents and generate hydrogen, which can enter into the steeland cause a catastrophic failure by hydrogen embrittlement.This is of particular concern for IVD Aluminum coated highstrength steel aircraft landing gear (LG) components. TheseLG components shall be cleaned in aqueous parts washersusing only those materials listed on the most current revisionof AF Drawing No. 9825019 by the Landing Gear SPM,OO-ALC/LGHLE.

3.3.4 Solvents. Cleaning solvents dissolve oily andgreasy soils so that they can be easily wiped away orabsorbed on a cloth. However, solvents differ significantly intheir cleaning ability, toxicity, evaporation rate, effect onpaint, and flammability. A-A-59601, Type II and/or MIL-PRF-680, Type II are the most common cleaning solventsused on aircraft, due to their low toxicity, minimal effect onpaint, and relative safety. Other solvents such as alcohols,ketones, chlorinated solvents, and naphtha, are specializedmaterials restricted for use, as recommended in Table 3-2.

NOTE

• Solvent cleaning operations are becomingmore and more limited due to environmentalregulations. Determine local requirements re-garding limitations on type and volume usedand disposal from your work center supervi-sor, safety officer, and/or bioenvironmentalengineer.

• A-A-59601 Dry Cleaning and Degreasing Sol-vent PD680 and MIL-PRF-680 DegreasingSolvent, replace P-D-680 Dry Cleaning andDegreasing Solvent. MIL-PRF-680 has beenreformulated to reduce Hazardous Air Pollut-ants by reducing the aromatic content of thesolvent, while A-A-59601 is identical toP-D-680.

3.3.4.1 MIL-PRF-680 Degreasing Solvent, and A-A-59601 Dry Cleaning and Degreasing Solvent,PD680. These solvents are used as cleaners and degreasersfor painted and unpainted metal parts and to remove corro-sion preventive compounds. The solvents are available inseveral types. Although the degreasing effectiveness is ap-proximately the same, the flash points differ as follows: TypeI, both specifications, 100° F (38° C) minimum; Type II, bothspecifications, 140° F (60° C) minimum; Type III, bothspecifications, 200° F (93° C) minimum, Type IV (d-limonene additive), MIL-PRF-680 only, 140° F (60° C)minimum. Though the flash points differ, all types will burnintensely once ignited. Type I, both specifications, is notauthorized as a general cleaner due to its flammability, butmay be used in parts washers designed for such solvents.

Type II, both specifications, is the most common cleaningsolvent used on aircraft, missiles, and equipment because ofits higher flash point. If necessary, ASTM D 235, Type II,Class C, Mineral Spirits may be used as a substitute forMIL-PRF-680 or A-A-59601, Type II. Type III, both speci-fications, is intended for use in confined spaces and inlocations with environmental constraints where a solvent witha very low vapor pressure (evaporation rate) and a very highflash point is required. MIL-PRF-680, Type IV (d-limoneneadditive) may be used where a higher flash point and strongsolvency is desired if approved by the aircraft SPD or themissile or equipment SPM. The dwell time for all typesshould be held to a minimum (less than 15 minutes) to avoiddamage to paint.

3.3.4.2 TT-I-735 Isopropyl Alcohol. Isopropyl alcoholis a flammable solvent used primarily as a disinfectant forcleaning fungus and mold. It is a poor degreaser.

3.3.4.3 ASTM D 740 Methyl Ethyl Ketone (MEK).This is a highly flammable solvent used primarily forcleaning prior to painting and bonding. It may also be usedfor cleaning if surfaces become contaminated with leakingoils and/or hydraulic fluids after surface treatment. Mostlocations cannot use MEK due to environmental restrictionson use of solvents with vapor pressures greater than 44millimeters of mercury (mm Hg). MIL-PRF-87937, Type IIor MIL-PRF-85570, Type II (either-diluted 1 part cleaner to 9parts water), may be used as an alternate followed by rinsingthoroughly with fresh water and air drying; or surfaces maybe cleaned by solvent wiping with AMS 3166, Solvents,Cleaning, Cleaning Prior to Application of Sealing Com-pounds.

3.3.4.4 Aliphatic Naphtha. Aliphatic naphtha is ahighly flammable solvent used primarily for cleaning oily orgreasy deposits from acrylic canopy materials. Other solventscause crazing of acrylics. It can also be used to removemasking or preservation tape residue.

3.3.4.5 MIL-T-81772, Type I (Polyurethane), andType II (Epoxy) Thinner. Both of these thinners are highlyflammable solvents that can be used for prepaint solventcleaning when necessary at locations requiring a solventvapor pressure less than 45 mm Hg.

3.3.5 Miscellaneous Cleaning Agents. Some othercleaning materials used on aircraft, missiles, and equipmentare listed here. P-P-560 plastic polish containing a mildabrasive is used to polish out scratches in acrylic canopy andwindow materials. Some alkaline chemicals used to neutral-ize specific acidic soils are: A-A-59370 ammonium hydrox-ide for urine, and ASTM D 928 sodium bicarbonate forelectrolyte spills from sulfuric acid batteries. Some acidicchemicals used to neutralize specific alkaline soils are:ANSI/AWWA B 504 monobasic sodium phosphate andA-A-59282 boric acid for electrolyte spills from nickel-cadmium batteries. MIL-F-24385 AFFF fire extinguishingagent containing wetting and foaming agents can be used towash out residues from fire extinguishing solutions made

TO 1-1-691

Change 1 3-11

with salt water. A-A-59199 optical glass lens cleaner is usedfor cleaning optical lenses on aircraft, missiles, and equip-ment. Solutions of O-D-1435 and A-A-1439 disinfectants areused to sanitize and deoderize relief tube areas; latrine areasincluding toilet bowls, urinals, and latrine buckets; garbagereceptacles; sinks; galley areas; and other interior areas ofaircraft and equipment requiring disinfection. SAE AMS1453 disinfectant is a ready-to-use material that can be usedas a general disinfectant cleaner for aircraft and equipmentinterior surfaces requiring disinfection.

3.3.6 Steam Cleaning. Steam cleaning shall not beused on aircraft and missiles at all levels (Organizational/Unit, Intermediate, or Depot) of maintenance. In addition,steam cleaning shall not be used on the following items on

equipment and components removed from aircraft and mis-siles: honeycomb bonded structure, sealant, fiberglass com-posites, acrylic windows and canopies, or electrical wiring.Steam cleaning erodes paint, crazes plastics, disbonds adhe-sives, damages electrical insulation, and drives lubricationout of bearings.

3.3.7 Dilution. More concentrated solutions than thoserecommended do not clean any better and are wasteful;MORE IS NOT ALWAYS BETTER. In fact, if too muchcleaner is used, the solution merely becomes slippery film,preventing the washing pad from loosening the soil andmaking rinsing more difficult. Do not exceed the cleanerdilution ratios recommended in Table 3-2.

Table 3-2. Cleaning of Specific Areas and Components

Area or Compo-nent

Type of Soil Cleaning Agent orCompound

Mixing Directionsand Nomenclature

Cleaning Procedures

NOTE

• Cleaning procedures are listed in this table. Ordering information for approved materials can be foundin Appendix A. Ordering information for approved equipment can be found in Appendix B.

• Use of hot water (120° to 140° F/49° to 60° C) for rinsing during aircraft washing operations isstrongly recommended as it provides much more efficient rinsing and is known to reduce man-hours foraircraft washing operations by approximately 20%.

• A-A-59601 Dry Cleaning and Degreasing Solvent, PD680 and MIL-PRF-680 De-greasing Solvent are combustible. Keep away from open flames. Use in a well-ventilated area. Wear rubber gloves and chemical or splash proof goggles. Avoid skincontact. Consult the local safety office regarding respiratory protection.

• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots dur-ing cleaning operations using MIL-PRF-87937 and MIL-PRF-85570 cleaning com-pounds. If cleaner is splashed in eyes, rinse thoroughly with fresh water for 15 min-utes and report to medical facility. Remove clothing saturated with cleaning solutionimmediately and flush exposed skin areas with fresh water.

EXTERIORSURFACES,PAINTED

Light Soils (dirt,dust, mud, salt,loose soot)

MIL-PRF-87937,Type II or IVor MIL-PRF-85570, Type IIor

1 part cleaner in 9parts water

Apply cleaner solution with foamgenerator, spray, sponge, softbrush, or cloth. Scrub and thenrinse with fresh water and dry.MIL-PRF-87937, Type I materi-als contain terpenes. Aircraft SPDand/or missile or equipment SPMrestrictions may apply. Consultsystem specific maintenancemanuals.

MIL-PRF-87937or MIL-PRF-85570, Type I


TO 1-1-691

3-12 Change 1

Table 3-2. Cleaning of Specific Areas and Components - Continued

Area or Compo-nent



Cleaning Procedures

Moderate Soils(hydraulic fluids,lube soils, lightpreservatives)

MIL-PRF-87937Type II or IV,or MIL-PRF-

85570, Type IIor


Apply cleaner solution with foam gen-erator spray, sponge, soft brush, orcloth. Rub gently with a circularmotion for up to one minute. Rinsewith fresh water and dry. Use ofMIL-PRF-87937, Type I is subject torestrictions noted above.

MIL-PRF-87937or MIL-PRF-85570, Type I


Heavy Soils (car-bonized oil,aged preserva-tives, grease,gun blast andexhaust depos-its)

MIL-PRF-87937,Type III orMIL-PRF-85570, Type Vor

Undiluted Spray or brush on cleaner. After 5 to15 minutes, brush and rinse thor-oughly.

EXTERIORSURFACES,PAINTED -Cont.

A-A-59601 orMIL-PRF-680,Type II and

Degreasing SolventUndiluted

Pre-clean by wiping or brushing withA-A-59601 or MIL-PRF-680, TypeII solvent, then apply cleaner solu-tion with foam generator, spray,sponge, or cloth. Allow the cleanerto dwell for up to one minute with-out scrubbing then scrub for up to aminute. Rinse thoroughly, then dry.Do not allow cleaning solution todry on surfaces or streaking will oc-cur. Use of MIL-PRF-87937, Type Iis subject to restrictions noted abovein Exterior Painted Surfaces.

CCC-C-440, TypeII or III, Class1 or A-A-2522,Grade A orAMS 3819,Class 1, GradeA and

Cotton Cheesecloth(Unbleached)White CottonCloth WhiteCleaningCloth

MIL-PRF-87937or MIL-PRF-85570, Type Ior


MIL-PRF-87937,Type IV orMIL-PRF-85570, Type II


Stubborn Soil onGloss PaintedAircraft (scuffmarks, exhaust,etc.)

MIL-PRF-87937,Type IV


Apply cleaner with a damp cloth. Rubwith a circular motion. Rinse thor-oughly, then dry. Do not allow thecleaner to dry on surfaces or rinsingmay be difficult.

MIL-PRF-85570,Type III, IV orV

Undiluted

Stubborn Soil onLow Gloss/Flatand/or Camou-flage PaintScheme Aircraft(scuff marks,exhaust, etc.)

MIL-PRF-85570,Type IV

Undiluted Apply cleaner with a non-abrasivecleaning pad. Allow 1-3 minutesdwell time. Rub with a circular mo-tion. Rinse thoroughly, then dry. Donot allow the cleaner to dry on sur-faces or rinsing may be difficult.

TO 1-1-691

3-13


Area or Compo-nent



Cleaning Procedures

Wear rubber gloves, chemical or splash proof goggles, and water resistant boots duringcleaning operations using MIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. Ifcleaner is splashed in eyes, rinse thoroughly with fresh water for 15 minutes and report tomedical facility. Remove clothing saturated with cleaning solution immediately and flushexposed skin with fresh water.

Do not allow MIL-PRF-87937 or MIL-PRF-85570, Type I cleaning solutions to contactcanopy, window, or windshield/windscreen transparent plastic panels as they may causecrazing.

EXTERIORSURFACES,UNPAINTED

Gunblast residues,carbonized ex-haust residues



Wet surface with fresh water. Applycleaning solution and scrub brisklywith A-A-58054 Type I, Grade A orB abrasive mat. Rinse with freshwater and dry. Use of MIL-PRF-87937, Type I is subject to restric-tions noted above in Exterior PaintedSurfaces.

MIL-PRF-87937,Type III orMIL-PRF-85570, Type IVor V

Undiluted

• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots duringcleaning operations using MIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. Ifcleaner is splashed in eyes, rinse thoroughly with fresh water for 15 minutes and reportto medical facility. Remove clothing saturated with cleaning solution immediately andflush exposed skin with fresh water.

• When using Ammonium Hydroxide (Ammonia), do not breathe vapors and avoid skincontact. Wash immediately if spilled on skin.

• When using Ammonium Hydroxide (Ammonia), do not allow any solutions to contactaircraft wiring. Flush immediately with fresh water if spillage occurs.

• Avoid use of compressed air to clean electronic equipment. Do not use abrasives in ra-dome compartments.

TO 1-1-691

3-14


Area or Compo-nent



Cleaning Procedures

INTERIOR AR-EAS

Lavatories Urine residue A-A-59370 Ammonium Hydrox-ide (Ammonia) 1part in 20 partswater

Sponge with a solution of ammo-nium hydroxide (Ammonia).Flush with fresh water or wetsurface with sodium bicarbonatesolution, allow to dry, and rinsewith fresh water. Dry with aclean cloth.

ASTM D 928 Sodium Bicarbonate,6 oz to 1 gallonof fresh water

USDA Reg 100-12-1

Germicidal Tablets Use germicidal tables as toilet andurinal deodorants.

All types of soilson lavatory sur-faces

O-D-1435; A-A-1439; or SAEAMS 1453

Mix per manf. in-structions

Pour solution into toilets, urinals,and latrine buckets. Scrub with abrush, and rinse with fresh water.Sponge all other surfaces withthe solution, sponge area withfresh water; and wipe dry.

Floor and Deck Dirt, debris MIL-PRF-87937,Type II or IVor MIL-PRF-85570, Type II(Preferred) or


Remove loose dirt with vacuumcleaner. Wipe with cleaning com-pound, and rinse with fresh wa-ter. Use of MIL-PRF-87937, TypeI is subject to restrictions notedabove in Exterior Painted Sur-faces.

MIL-PRF-87937,or MIL-PRF-85570, Type I(Alternate)


Radome andEquipmentCompartment(interior)

Dust, dirt, oil, anddebris

MIL-PRF-87937,Type II or IVor MIL-PRF-85570 Type IIand


Remove loose dirt with a vacuumcleaner. Wipe fiberglass and othersurfaces with a cloth wet withcleaning solution and rinse withcloth wet with fresh water. Drywith a clean cloth.CCC-C-440, Type

I or II, Class 1or A-A-59323,Type II or AMS3819, Class 1,Grade A or B

Cotton Cheesecloth(Unbleached)CleaningCloth, Low lintWhite CleaningCloth

Cockpit Interior Dust, dirt, mud,and light debris

MIL-PRF-87937,Type II or IVor MIL-PRF-85570, Type IIand


Loosen any accumulations of mudon control pedals, floors, or othercockpit equipment with brush andremove with vacuum cleaner.Wipe with cloth wet with clean-ing solution and follow with acloth wet with fresh water. Drywith a clean cloth.

A-A-50129 Cloth, Flannel

EnvironmentalControl Duct-ing

Light debris, dust,and grime

MIL-PRF-87937,Type II or IVor MIL-PRF-85570, Type II


Refer to applicable maintenancemanuals.

TO 1-1-691

Change 1 3-15


Area or Compo-nent



Cleaning Procedures

NOTE

Refer to aircraft system specific manual to determine acrylic plastic parts.

ACRYLICPLASTICPARTS (EX-CEPT CANO-PIES andWINDOWS)

Light soil andsmudges

MIL-PRF-87937,Type II or IVor MIL-PRF-85570, Type IIand


Wipe with cloth wet with cleaningsolution and follow with a clothwet with fresh water. Dry with aclean cloth.

A-A-50129 Cloth, FlannelINTERIOR

PLASTICAND GLASSPANELS

A-A-50129 Cloth, Flannel Vacuum and then dust with soft,clean, damp cloth. Keep clothfree of grit by rinsing frequentlyin water and wringing out.

ELASTOMERICSEALS

Dust, dirt, oil, andgrime



Wipe with cloth wet with cleaningsolution and rinse with a clothwet with fresh water. Dry with aclean cloth.

CCC-C-440, TypeI or II, Class 1or

Cotton Cheesecloth(Unbleached)

Cleaning Cloth(Low lint) White

A-A-59323, TypeII or AMS3819, Class 1,Grade A or B

Cleaning Cloth

Wear rubber gloves, chemical or splash proof goggles, and water resistant boots duringcleaning operations using MIL-PRF-87937 and MIL-PRF-85570 cleaning compounds. Ifcleaner is splashed in eyes, rinse thoroughly with fresh water for 15 minutes and reportto medical facility. Remove clothing saturated with cleaning solution immediately andflush exposed skin with fresh water.

FABRICPARTS,SOUND-PROOFINGAND UP-HOLSTERY

Light soil and oilspots



Remove loose dirt with vacuumcleaner. Apply soap solution withsponge and scrub briskly. Rinsewith clean, dampened rag orsponge using clean, fresh water.Allow area to dry. Raise nap bybrushing.

TO 1-1-691

3-16 Change 1


Area or Compo-nent



Cleaning Procedures

Do not use synthetic wiping cloths with flammable solvents, such as TT-N-95 aliphaticnaphtha.

Refer to aircraft system specific manual to determine cleaning procedures for aircraftcanopies. In addition, refer to TO 1-1A-12. Remove rings, watches, or other hard ob-jects from hands and wrists before washing transparent plastics. Personnel must alsotake precautions to prevent buttons, badges, or other hard objects from scratching sur-faces. Do not use hard, dirty, or gritty cloths in cleaning and polishing transparent plas-tics. Wiping with such cloths can mar and scratch plastic surfaces. Do not use anychemical compounds unless specifically authorized for cleaning plastics. Do not rub dryplastic panels with dry cloth, which might scratch surface or create electrostatic chargethat attracts dust.

CANOPY EX-TERIOR,PLASTICAND GLASSWINDOWAND WIND-SHIELD/WIND-SCREENPANELS

Dust, dirt grime,salt spray,

P-P-560 and Plastic Polish Com-pound

Rub gently with bare hands orclean cloth while flushing withfresh water to remove loose dirt.Apply polishing compound witha soft, clean cloth and rub usinga circular motion until clean. Pol-ish with another soft, clean cloth.

A-A-50129 Cloth, FlannelOil, grease TT-N-95 and Aliphatic Naphtha Apply naphtha with soft, clean

cloth. Blot gently; solvent willevaporate and not leave a film.

P-P-560 and Plastic Polish Com-pound

Apply polishing compound. Rubusing a circular motion untilclean and polish with anothersoft, clean cloth.

A-A-50129 Cloth, Flannel

TO 1-1-691

Change 1 3-17


Area or Compo-nent



Cleaning Procedures

• Open all circuit breakers associated with battery power (refer to applicable systemspecific maintenance manuals) prior to application of MIL-PRF-680 Degreasing Sol-vent or A-A-59601 Dry Cleaning and Degreasing Solvent, PD680.

• Both of these solvents are combustible. Keep away from open flames. Use in a well-ventilated area. Wear rubber gloves and chemical or splash proof goggles. Avoid skincontact. Consult the local safety office regarding respiratory protection.

Do not use excessive cleaning solvent on control cables. Solvent will remove internallubricant.

CONTROLCABLES

Dust, dirt oil,grease


Degreasing Solvent Wipe with clean cloth dampenedwith solvent. Apply MIL-PRF-81309, Type II water displacingCPC to cables, and recoat cableswith MIL-PRF-16173, Grade 4CPC.

MIL-PRF-81309,Type II and

Water Displacing,CPC

MIL-PRF-16173,Grade 4

CPC

Wipe away from seal areas to preclude collection of soil at seal junction areas. Makesure piston surface is clean and completely lubricated but not dripping. If piston is dry,telescoping action of strut will force gritty particles into cylinder causing leaks andeventual failure. Do not use aerosol type cleaning fluids on hydraulic systems.

LANDINGGEAR EX-POSED PIS-TON SUR-FACES

Sand, dirt, saltdeposits, andother foreignparticles

MIL-PRF-83282 Hydraulic Fluid, Clean exposed surfaces with cleancloth dampened with hydraulicfluid. Take care not to scratch thesurface. Wipe away from seals,not toward them.

CCC-C-440, TypeI or II, Class 1or A-A-59323,Type II or AMS3819, Class 1,Grade A or B

Cotton Cheesecloth(Unbleached)Cleaning Cloth(Low lint) Clean-ing Cloth

TO 1-1-691

3-18 Change 1


Area or Compo-nent



Cleaning Procedures

• Open all circuit breakers associated with battery power (refer to applicable systemspecific maintenance manuals) prior to application of MIL-PRF-680 Degreasing Sol-vent or A-A-59601 Dry Cleaning and Degreasing Solvent, P-D-680.


Do not use MIL-PRF-16173, Grade 4 or MIL-DTL-85054 on micro-switches or exposedpiston rod surfaces.

DOORS, LINK-AGES, CYL-INDERS

Dust, dirt, oil,grease

A-A-59601 orMIL-PRF-680,Type II

Degreasing Solvent Brush surfaces as necessary withsolvent. Cover rod ends andsprings with MIL-PRF-16173,Grade 4 CPC. Where lubricationis not required, MIL-DTL-85054CPC may be applied.

MIL-PRF-16173,Grade 4 or

CPC

MIL-DTL-85054 CPCWHEELS AND

BRAKESOil, grease, dirt,

sand, and otherforeign matter

For cleaning wheels and brakesreference TO 4W-1-61 and 4B-1-32.

AF Drawing #9825019 speci-fied materials

Dilute and/or mixper manufacturer’sinstructions

Use only those cleaners listed inthe most current revision of AFDrawing No. 9825019. Place offaircraft parts in the AqueousParts Washer and run through thecomplete wash, rinse, and drycycle.

TO 1-1-691

Change 1 3-19


Area or Compo-nent



Cleaning Procedures


• Both of these solvents are combustible. Use in a well-ventilated area. Keep it awayfrom open flames. Avoid contact with skin.

• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots dur-ing cleaning operations using MIL-PRF-87937, MIL-PRF-85570, or MIL-C-43616cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly with fresh waterfor 15 minutes and report to medical facility. Remove clothing saturated with clean-ing solution immediately and flush exposed skin with fresh water.

Protect tires from contact with degreasing solvents or cleaning solutions.

LANDINGGEAR(OTHERTHAN EX-POSED PIS-TON AREA)AND WHEELWELLS

Dirt, grease, hy-draulic fluid, etc.

MIL-PRF-87937,Type III orMIL-PRF-85570, Type Vor

Undiluted Apply thixotropic gel Type III orType V cleaner with spray orbrush and allow a 5-15 minutedwell. Brush, if necessary, andrinse thoroughly with fresh water.Repeat rinsing with brushing toremove cleaner residues.

A-A-59601 orMIL-PRF-680,Type II or III

Undiluted De-greasing Solvent

Alternate procedure: Brush on sol-vent to loosen stubborn soil.

MIL-C-43616,Class 1 or MIL-PRF-85570,Type I


Apply MIL-C-43616, Class 1, MIL-PRF-85570, Type I or MIL-PRF-87937, Type I cleaning solution,brush, and rinse. Omit solventpre-soak if desired. Use of MIL-PRF-87937, Type I may be re-stricted as noted above in Exte-rior Painted Surfaces.

TO 1-1-691

3-20 Change 1


Area or Compo-nent



Cleaning Procedures

Before cleaning electrical and avionic equipment, make sure electrical power is discon-nected. Injury and death may otherwise result.

Avoid use of compressed air in electronic compartments because air can force dust, dirt,and other foreign materials into components or equipment and cause damage.

ELECTRICALCONNEC-TORS ANDAVIONICCOMPO-NENTS

Dust, dirt, lint, andother loose for-eign matter,grease, oilsmudges, lighttarnish, corro-sion, or fungi

Refer to TO 1-1-689-1, TO 1-1-689-3, and TO 1-1-689-5.

• Open all circuit breakers associated with battery power (refer to applicable systemspecific maintenance manuals) prior to application of TT-I-735 isopropyl alcohol.

• Do not use synthetic wiping cloths with flammable solvents such as TT-I-735 isopro-pyl alcohol.

ORGANIC MA-TERIALS;MILDEW,MOLD, FUN-GUS, ETC

Fungi, mold, mil-dew, etc.

TT-I-735 Isopropyl Alcohol Wipe with clean cloth wet withisopropyl alcohol. To preventrecurring fungus growth, keeparea dry and clean. For treatmentof fungus in fuel systems, contactthe appropriate aircraft SPDand/or missile or equipmentSPM.

CCC-C-440, TypeI or II, Class 1or A-A-59323,Type II or AMS3819, Class 1,Grade A or B

Cotton CheeseclothCleaning ClothLow lint CleaningCloth

OXYGENLINES (EX-TERIORSURFACES)

Oil, grease Refer to system specific maintenance manuals.

TO 1-1-691

Change 1 3-21


Area or Compo-nent



Cleaning Procedures

Wear rubber gloves, chemical or splash proof goggles, and water resistant boots duringcleaning operations using MIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. Ifcleaner is splashed in eyes, rinse thoroughly with fresh water for 15 minutes and reportto medical facility. Remove clothing saturated with cleaning solution immediately andflush exposed skin with fresh water.

RELIEF TUBES(EXTERIOR)

Human waste(urine)



Wash thoroughly with solution us-ing a soft, bristle brush, thenrinse thoroughly with fresh waterand wipe dry.


Do not use strong alkaline cleaners or highly abrasive compounds when cleaning rotortip cap areas. Refer to systems specific technical orders for specific cleaninginstructions.

HELICOPTERAND PRO-PELLERBLADES

Grime, oil, grease,exhaust stains

MIL-PRF-87937,Type IV orMIL-PRF-85570, Type II


Apply cleaning solution with acleaning pad or brush and agitate.Rinse with fresh water and wipedry.

A-A-3100 Cleaning PadHELICOPTER

CARGO ANDRESCUEHOISTCABLE, ANDEND FIT-TINGS

Salt, and salt water MIL-PRF-16173,Grade 3 orMIL-PRF-81309, Type IIor MIL-L-87177, Type I,Grade B

Water DisplacingCorrosion Preven-tive Compound

Flush thoroughly with fresh water.Blow dry with clean, compressedair or thoroughly dry with a cot-ton cloth. Spray with MIL-PRF-16173, Grade 3; MIL-PRF-81309, Type II; or MIL-L-87177,Type I, Grade B compound as itis being rewound. Remove excesswith clean dry cloth.A-A-50129 Cloth, Flannel

TO 1-1-691

3-22 Change 1


Area or Compo-nent



Cleaning Procedures

Wear rubber gloves, chemical or splash proof goggles, and water resistant boots duringcleaning operations using MIL-C-43616, MIL-PRF-87937, or MIL-PRF-85570 cleaningcompounds. If cleaner is splashed in eyes, rinse thoroughly with fresh water for 15 min-utes and report to medical facility. Remove clothing saturated with cleaning solutionimmediately and flush exposed skin with fresh water.

HELICOPTERCARGO ANDRESCUEHOISTDRUM

Salt, and salt water MIL-PRF-87937or MIL-PRF-85570, Type Ior MIL-C-43616, Class 1


Rinse with fresh water. Applycleaning solution and scrub witha clean cloth or sponge. Rinsewith clean water. Blow dry withclean, compressed air or dry witha clean, dry cloth. Use of MIL-PRF-87937, Type I may be re-stricted as noted above in Exte-rior Painted Surfaces.


HELICOPTERRESCUESLING

Salt, and salt water MIL-PRF-87937,Type IV orMIL-PRF-85570, Type II


Rinse with fresh water. Applycleaning solution with sponge orclean cloth. Rinse thoroughlywith fresh water. Blow dry withclean compressed air or suspendand allow to dry. If suspended todry, ensure water will drain awayfrom the buckle.

TO 1-1-691

Change 1 3-23


Area or Compo-nent



Cleaning Procedures



ENGINES, RE-CIPROCAT-ING

Oxidized oil, dust,carbon, salt de-posits


Degreasing Solvent Apply solvent with cleaning clothor brush. Repeat application anddry. Collect solvent runoff anddispose in accordance with localregulations.

CCC-C-440, TypeI or II, Class 1or

Cotton Cheesecloth(Unbleached)

A-A-59323, TypeII or AMS3819, Class 1,Grade A or B

Cleaning Cloth LowLint CleaningCloth

TO 1-1-691

3-24 Change 1


Area or Compo-nent



Cleaning Procedures

Wear rubber gloves, chemical or splash proof goggles, protective wet weather clothingwhere necessary, and water resistant boots during cleaning operations using cleaningcompound MIL-PRF-85704, Types II or II RTU. If cleaner is splashed in eyes, rinsethoroughly with fresh water for 15 minutes and report to medical facility. Removeclothing saturated with cleaning solution immediately and flush exposed areas with freshwater.

• Use only MIL-PRF-85704 cleaning compound for cleaning turbine engine gas paths.Prepare aircraft in accordance with applicable system specific maintenance manualsand/or maintenance work cards. In case of conflict, the manuals and/or work cardstake precedence over the following instructions.

• MIL-PRF-85704, Type I gas path cleaners typically contain 30 to 60 percent solvent.When diluted (1 part cleaner to 4 parts water), some products are above the 10%solvent limit; and most contain enough naphthalene to cause wash rack runoff to ex-ceed the discharge permit limits. The current substitute is MIL-PRF-85704, Type II, awater-base product that contains less than 10 percent solvent in the concentrate. Thismaterial shall be used at the same dilution ratio while using the same starter crankedengine wash procedures, which are currently approved in aircraft engine manuals.MIL-PRF-85704, Type II RTU is ready to use (does not require dilution, but required5 times the storage space since it is already diluted with water).

GAS TURBINEENGINEINTER-IOR(GAS PATH)


MIL-PRF-85704,Type II or


Use in accordance with applicableengine maintenance manual in-structions. Dispose of wastecleaner in accordance with localregulations.

MIL-PRF-85704,Type II RTU

Do not dilute, this isa ready mix form

TO 1-1-691

Change 1 3-25


Area or Compo-nent



Cleaning Procedures

Wear rubber gloves, chemical or splash proof goggles, and water resistant boots duringcleaning operations using MIL-PRF-87937, MIL-PRF-85570, MIL-C-43616, or MIL-PRF-85704, Types I or II cleaning compounds. If cleaner is splashed in eyes, rinse thor-oughly with fresh water for 15 minutes and report to medical facility. Remove clothingsaturated with cleaning solution immediately and flush exposed skin with fresh water.

Prepare aircraft in accordance with applicable system specific maintenance manualsand/or maintenance work cards. In case of conflict, the manuals and/or work cards takeprecedence over the following instructions.

GAS TURBINEENGINE EX-TERIOR, EN-GINE BAYAND EN-GINE BAYDOORS


MIL-C-43616,Class 1 or MIL-PRF-85704,Type I or II or


Apply mixed cleaning solutions(MIL-C-43616, Class 1; MIL-PRF-85704, Type I or II; MIL-PRF-87937, Type IV; or MIL-PRF-85570, Type II) or the pre-mixed cleaners (MIL-C-43616,Class 1A or MIL-PRF-85704,Type II RTU) with a brush,scrub, then rinse with fresh water.When using the MIL-PRF-87937,Type III or MIL-PRF-85570,Type V, apply the undiluted con-centrate with a brush, allowcleaner to remain on surface for5 minutes, then brush and rinsethoroughly. Dispose of wastecleaners in accordance with localdirectives.

MIL-C-43616,Class 1A or

Aerosol Can

MIL-PRF-85704,Type II RTU or

Do not dilute, this isa ready mix form

MIL-PRF-87937,Type IV orMIL-PRF-85570, Type IIor


MIL-PRF-87937,Type III orMIL-PRF-85704, Type V

Undiluted concen-trate

TO 1-1-691

3-26 Change 1


Area or Compo-nent



Cleaning Procedures

Never use a wire brush to clean a battery or a battery area. Wear rubber gloves, a rub-ber apron, and protective goggle when handling batteries.

• Nickel-cadmium batteries must not be exposed to acid or acid vapors. Battery elec-trolytes are extremely corrosive. Spilled electrolyte shall be removed immediately.Refer to applicable system specific aircraft, missile, or equipment manuals for batterytype.

• Fumes from overheated electrolyte will spread to adjacent areas, causing rapid corro-sion on unprotected surfaces.

NOTE

Refer to chapter 7 for additional instructions.

Battery Com-partments

Nickel-cadmiumbattery electro-lyte deposits(potassium hy-droxide solution)

A-A-59282 or Boric Acid Remove spilled electrolyte immedi-ately by flushing with fresh wa-ter. Spray the contaminated areawith Bromothymol Blue solution(Refer to Chapter 7). Neutralizethe area by sponging or sprayinggenerously with boric acid orsodium phosphate solution. Brushwith a fiber bristle brush andflush with fresh water. Reapplythe Bromothymol Blue solutionto determine if all the electrolytehas been neutralized. Retreat areaas required and rinse. Dry withclean wiping cloths. Keep thecell vents open, but do not allowany solutions to enter the cells.Preserve compartment with MIL-PRF-81309, Type II, Class 1 or 2or MIL-L-87177, Type I or II ,Grade B CPC. Do not paint orpreserve batteries.

ANSI/AWWA B504

Monobasic sodiumphosphate

Mix either material6 oz in 1 gallonwater

MIL-PRF-81309,Type II, Class 1or 2, or MIL-L-87177, Type Ior II, Grade B

Water DisplacingCPC

TO 1-1-691

Change 1 3-27


Area or Compo-nent



Cleaning Procedures

Lead-acid batteryelectrolyte de-posits (sulfuricacid solution)

ASTM D 928 Sodium bicarbonate,6 oz in 1 gallonwater

Remove spilled electrolyte immedi-ately by flushing with fresh wa-ter. Spray the contaminated areawith Litmus solution (Refer toChapter 7). Neutralize the area bysponging or spraying with so-dium bicarbonate solution. Applygenerously until bubbling stopsand the Litmus solution turnsblue. Let it stay on the surfacefor 5 minutes, but do not allowto dry. Brush with a fiber bristlebrush, then flush with fresh wa-ter. Reapply the Litmus solutionto determine if all the electrolytehas been neutralized. Retreat thearea as required and rinse. Drywith clean wiping cloths. Keepthe cell vents open but do notallow any solutions to enter thecells. Preserve compartment withMIL-PRF-81309, Type II, Class 1or 2, or MIL-L-87177, Type I orII, Grade B CPC. Do not paint orpreserve batteries.

MIL-PRF-81309,Type II, Class 1or 2, or MIL-L-87177, Type Ior II, Grade B

Water DisplacingCPC

• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots dur-ing cleaning operations using MIL-PRF-87937 or MIL-PRF-85570 cleaning com-pounds. If cleaner is splashed in eyes, rinse thoroughly with fresh water for 15 min-utes and report to medical facility. Remove clothing saturated with cleaning solutionimmediately and flush exposed skin with fresh water.

• A-A-59601, Type III Dry Cleaning and Degreasing Solvent, PD680 and MIL-PRF-680, Type III Degreasing Solvent are non-combustible, but can still burn if exposedto flames. Use in a confined area is allowed, but this area should still be well-ventilated. Keep away from open flames. Avoid contact with skin.

BILGE AREAS Hydraulic fluid,water, dirt, me-tallic debris

MIL-PRF-87937,Type II or IV,or MIL-PRF-85570, Type IIor


Vacuum clean liquids and debris.Wipe area with a sponge damp-ened in cleaning solution. Rinseby sponging with fresh water.Wipe dry with a clean cloth.



Use of MIL-PRF-87937, Type Imay be restricted as noted abovein Exterior Painted Surfaces.

TO 1-1-691

3-28 Change 1


Area or Compo-nent



Cleaning Procedures

A-A-59601 orMIL-PRF-680,Type III

Degreasing Solvent Wipe with cloth dampened withsolvent. Wipe dry with a cleancloth.

Algae contamina-tion

MIL-PRF-87937,Type IV, orMIL-PRF-85570, Type IIor


Mix cleaner and water in a pumpspray bottle. Spray mixture oncontaminated area and allow it todwell at least 2 minutes. Wipe offwith a sponge and dry with aclean cloth. Use of MIL-PRF-87937, Type I may be restrictedas noted above in ExteriorPainted Surfaces.



MIL-PRF-87937,Type III orMIL-PRF-85570, Type V

Undiluted concen-trate

OPTICALGLASS

Dust, grease, oil A-A-59199 and Optical cleaner Spray cleaner onto flannel and care-fully wipe the lens or other opti-cal surface. Wipe dry with cleanflannel cloth.A-A-50129 Cloth, Flannel

EJECTIONSEATS

• Application of corrosion preventive compounds (CPC’s) or paints to certain areas ofejection seats could prevent or restrict seat operation. Specific ejection seat instruc-tions must be followed carefully.

• See system specific ejection seat maintenance manuals and SPM instructions for cor-rosion prevention and control and lubrication of ejection seats.

REMOVABLEMETALFUEL TANKS

Fuel residues,grease, and ex-haust deposits

MIL-PRF-85570 Use MIL-PRF-85570 detergent inaccordance with procedures insystems specific fuel tank manu-als.

TO 1-1-691

Change 1 3-28.1/(3-28.2 blank)

3.4 CLEANING EQUIPMENT.

• High pressure wash equipment which devel-ops more than 175 PSI nozzle pressure shallnot be used to apply cleaning compoundsunless specifically authorized by the aircraftSPD and/or the missile or equipment SPM.

• High pressure wash equipment shall never beused on aircraft landing gear and components,wheels, and brakes as they can force lubricantsout of bearings and attach points, and causecorrosion and wear problems.

NOTE

• Use only cleaning materials and equipmentauthorized and described in this manual. Ex-perimentation with unauthorized cleaners maydamage aircraft, missiles, and equipment thusreducing reliability and increasing mainte-nance costs.

• Cleaning equipment specific to one type ofaircraft, missile, or piece of equipment is notcovered by this manual. Approved equipmentfor general cleaning is discussed in thismanual, and ordering information is presentedin Appendix B of this manual. General oper-ating instructions are in Paragraph 3.4.1through 3.4.9. See specific equipment operat-ing manuals for detailed equipment operatinginstructions.

3.4.1 High Pressure/Hot Water Wash Equipment. Ifapproved by the aircraft SPD and/or the equipment SPM,high pressure/hot water wash equipment can be used forgeneral purpose cleaning of aircraft, support equipment, andvehicles. These machines can deliver four gallons per minuteof water and/or cleaning solution at a temperature of 210° Fand a pressure of 3000 PSI at the attach points on the machinefor each output hose. These machines shall be operated perthese instructions and the directions in the specific equipmentoperating manual.

a. Fill the cleaner reservoir with only approved cleaningcompounds.

b. Set the water cleaning compound mixture ratio to 50parts water to 1 part cleaner.

c. Use only 40° flat fan spray nozzles.

d. Ensure that the nozzle stand-off distance to the surface isalways at least 12 inches and never less.

NOTE

• Pressure and temperature at the nozzles will beless than at the hose attach points on themachine due to losses in the hoses.

• This equipment may remove any loose sealantand/or paint.

3.4.2 Portable, 15 Gallon, Foam Generating, Clean-ing Unit. This cleaning unit is compact, portable, light, andideal for cleaning hard to reach areas. It consists of a 54 inchapplicator wand, 50 feet of hose, and a 15 gallon tankmounted on a frame with rubber tire wheels (refer to Figure3-1). The control system allows the operator to adjust thefoam wetness to fit any job. The cleaning unit provides afoam capable of clinging to vertical surfaces to soften anddislodge soils. These machines shall be operated per theseinstructions and the directions in the specific equipmentoperating manual:

Do not service the portable 15 gallon foamgenerating cleaning unit without releasing thetank pressure.

When the cleaning task is completed, drain andflush the tank with fresh water to prevent formingan extremely concentrated solution by pouringadditional cleaner into the solution remaining inthe tank which could damage the equipmentbeing cleaned.

a. Release the tank pressure prior to servicing, and removethe tank fill cap. Fill the tank with an authorized,pre-diluted cleaning solution, while leaving an adequateair space at the top of the tank. Replace the tank fill cap.

b. Connect the air supply hose to the air inlet valve on theair regulator.

NOTE

Table 3-2 for the proper cleaner to water mixratio.

c. Open the cleaning compound metering valve and the airinlet valve to the full open position and set the airregulator to a pressure within the range of 30 to 70 PSI.

d. Open the foam discharge valve while directing thenozzle at the surface to be cleaned.

TO 1-1-691

3-29

e. If the foam is too wet, close the cleaning compoundmetering valve slightly. If the foam is too dry, open thecleaning compound metering valve slightly and/or lowerthe air pressure slightly by adjusting the air regulator.Dry foams have a longer dwell time and prolong thecleaning operation, but wet foams clean better.

f. Apply the foam to the surface and allow it to dwell fora minimum of one minute, but not long enough to dry onthe surface, and then scrub with a cleaning kit, brush, orcloth and rinse. Refer to Table 3-2 for additionalinstructions.

3.4.3 Portable, 45 Gallon, Foam Generating Clean-ing Unit. This cleaning unit is a simplified, portablepressure operated, foam-dispensing system (refer to Table3-2). It uses available air supply for its power source withoutusing pumps. Air is metered directly into the pressurizedsolution chamber which forces cleaning solution into the hoseto create foam. These machines shall be operated per theseinstructions and the directions in the specific equipmentoperating manual:

Do not service the portable 45 gallon foamgenerating cleaning unit without releasing thetank pressure.

When the cleaning task is completed, drain thetank and flush with fresh water to prevent form-ing an extremely concentrated solution by pour-ing additional cleaner into the solution remainingin the tank which could damage the equipmentbeing cleaned.

a. Release the tank pressure prior to servicing. Close thecleaning compound metering valve and the air valve,and open the air dump valve to bleed off retained airpressure.

TO 1-1-691

3-30

Figure 3-1. Foam Generating Cleaning Unit (15 Gallons)

TO 1-1-691

3-31

Figure 3-2. Foam Generating Cleaning Unit (45 Gallons)

TO 1-1-691

3-32

b. Open the tank by removing the cover retaining bolts andlifting off the cover. Fill the tank with an authorized,pre-diluted cleaning solution, while leaving an adequateair space at the top of the tank. Replace the cover andbolt it firmly in place.

NOTE

Refer to Table 3-2 for the proper cleaner to watermix ratio.

Figure 3-3. Universal Wash Unit

TO 1-1-691

3-33

c. Make sure the cleaning compound metering valve andthe air valve are closed. Attach an air line to the airinlet/dump valve on the side of the unit, and fill the voidin the tank with air until the pressure is within the rangeof 30 to 70 PSI as indicated at the air regulator.

d. Open the air valve, and then open the cleaning com-pound metering valve slowly while pointing the nozzleat the surface to be cleaned. Adjust the cleaner com-pound metering valve until the desired foam consistencyis reached.

e. If the foam is too wet, close the cleaning compoundmetering valve slightly and/or open the air valveslightly. If the foam is too dry, open the cleaningcompound metering valve slightly and/or close the airvalve slightly.

f. Apply the foam to the surface and allow it to dwell fora minimum of one minute, but not long enough to dry onthe surface, and then scrub with a cleaning kit, brush, orcloth and rinse. Refer to Table 3-2 for additionalinstructions.

3.4.4 Turbine Engine Compressor Cleaning Equip-ment. Equipment used for cleaning aircraft turbine enginesis contained in specific system specific engine TO’s.

3.4.5 Miscellaneous Large Cleaning Equipment.Other equipment such as truck, trailer, or wash rack/hangermounted spray or foam equipment may be available at manylocations.

3.4.6 Spray Cleaning Guns for Solvents. These sol-vent spray guns have an extended nozzle/tube and requireapproximately 14 CFM of air at 50 PSI to siphon solvent orcleaner from container and deliver it to a surface in anon-atomized spray.

3.4.7 Pneumatic Vacuum Cleaner. This unit is asmall, portable, wet/dry, air-operated vacuum cleaner forremoving debris and water from aircraft (Refer to AppendixB).

3.4.8 Universal Wash Unit. Universal wash units areused for general purpose cleaning (refer to Figure 3-3). Theyapply cleaning solutions to aircraft and/or equipment surfacesin a non-foam state at the approximate rate of 2.5 gal/min. ata pressure of 30 PSI. These machines shall be operated perthese instructions and the directions in the specific equipmentoperating manual:

Use the universal wash unit in the horizontalposition only.

a. Connect the strainer unit to the intake hose and insert itinto the container of water or cleaning compoundsolution.

b. Connect the wand and the spray nozzle assembly to theoutput/discharge hose, or connect the discharge quickdisconnect to the aircraft wash manifold quick discon-nect.

c. Press the start switch on the unit or the remote startswitch and observe the pressure gauge on the unit. Itshould indicate an increase of pressure immediately.When the pressure reaches approximately 10 PSI, re-lease the start switch and the unit will continue to run.

d. Point the nozzle at the aircraft or equipment surface tobe cleaned and spray the surface with the cleaningsolution.

e. Press the stop switch on the unit or the remote stopswitch to stop the unit.

f. Allow the cleaning compound solution to dwell forseveral minutes, but not long enough to dry on thesurface, and then scrub with a cleaning kit, brush, orcloth and rinse. Refer to Table 3-2 for additionalinstructions.

3.4.9 Aqueous Parts Washers. These units are auto-matic industrial power washers comprised of an enclosedcabinet equipped with a system of spray impingementnozzles; a cycle timer; a cleaning solution reservoir with aheater unit; a fluid pump; and an effluent reservoir with askimmer unit for removal of oil, grease, and residues (Referto Figure 3-4 and Figure 3-5). These automatic washers caneffectively clean aircraft, missile, and equipment componentsby using aqueous cleaning solutions applied at varyingcombinations of high temperatures and pressures for theremoval of soils, oils/greases, corrosion preventive com-pounds, and other contaminants when authorized by theaircraft SPD and/or the missile or equipment SPM. Thesemachines shall be operated per these instructions and thedirections in the specific equipment operating manual:

TO 1-1-691

3-34 Change 1

Materials used in and effluent generated by thiscleaning process may be hazardous to personneland the environment. Contact the local bioenvi-ronmental engineer and safety office for guidanceon personal protective equipment (PPE) andother health and safety precautions and wastedisposal. Parts may be very hot and retain hotwater and/or cleaning solution in part cavities atthe end of the cleaning cycle. Handle parts withwater proof and heat resistant protective gloves,and drain entrapped fluids back into the partswasher.

• Aqueous parts washers shall not be used toclean bearings unless authorized by systemspecific technical data.

• Due to the maximum allowable pH of 13.5 forthe MIL-PRF-29602 cleaning compoundsused in these parts washers, they can attackaluminum alloy and IVD aluminum coatedparts. Aircraft SPD and/or missile or equip-ment SPM approval is required prior to clean-ing these types of parts in aqueous partswashers.

• Due to the possibility for hydrogen embrittle-ment and other damage, only those cleanerswhich have been tested, approved, and listedin the most current revision of AF DrawingNo. 9825019 by the Landing Gear (LG) SPM,OO-ALC/LGHLE shall be used in aqueousparts washers for cleaning LG componentsincluding wheels and brakes.

• Depending on the type of equipment used,water/cleaning solution spray pressures inaqueous parts washers can range from 40 to100 PSI. Suitable fixtures and/or baskets mustbe used to secure components during thecleaning cycle to prevent damage caused byimpingement of the high pressure spray.

3.4.9.1 The effectiveness of cleaning in aqueous partswashers is influenced by several factors that should beconsidered when using this cleaning method.

3.4.9.1.1 Spray Nozzles. There are two basic nozzledesigns, fan and cone spray. The distance of the parts in thecabinet from the spray nozzles determines how effective theforce of the spray from the nozzles will be and the area ofcoverage. Placing parts too close to the spray nozzles reducesthe surface coverage of the nozzles and too far from the spraynozzles reduces the force of the spray. Understanding this andracking parts properly in aqueous parts washers will improvethe cleaning effectiveness of the machine.

3.4.9.1.2 Bath Quality. Maintaining the condition of thecleaning bath affects its ability to remove soils. There are twotypes of detergents used in aqueous cleaning, emulsifying andnon-emulsifying. Emulsifying cleaners break down the oilsand greases and hold them in suspension in the bath. Withthese cleaning materials, their cleaning ability becomesdegraded by excessive amounts of oil and greases being heldin the bath. It is important to monitor and change the bathsolution routinely to maintain effective cleaning. The non-emulsifying cleaners break down the oils and greases but donot hold the materials in the bath solution, they rise to the topof the bath. It is important to have an effective skimmer onmachines using non-emulsifying cleaners to remove the oiland greases. The proper concentration of cleaner in the bathalso affects the bath performance. The heated cleaningsolutions cause evaporation and proper make up of both waterand cleaner should be added. This should be monitoredregularly and adjustments made per the manufacturer’s in-structions.

3.4.9.1.3 Skimmers and Filtration. Several types ofboth skimmers and filtration systems are available for usewith aqueous parts washers. These have a major impact onmaintaining bath quality. It is recommended that both thefilters and skimmers be used and that they be maintainedproperly per manufacturer’s instructions to ensure bath qual-ity and the cleaning effectiveness of the machine.

3.4.9.2 Determine the capacity of the aqueous partswasher cleaning compound reservoir, and fill it with MIL-PRF-29602 or AF Drawing No. 9825019 approved cleaningcompound solution mixed/diluted per the manufacturer’sdirections.

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NOTE

Agitation prior to reaching the required operatingtemperature may cause the cleaning solution tofoam excessively. Do not use the washer until thecleaning solution has stabilized at the propertemperature.

a. Allow the cleaning solution to stabilize at the tempera-ture recommended by the manufacturer within the rangeof 140° to 180° F.

• When cleaning components which can entrapfluids, load the components in the basket sothat as many cavities as possible that canentrap fluids are face down to prevent corro-sion caused by fluid retention.

• Due to evaporation of the heated cleaningbaths, the bath level must be monitored. Thisis necessary to ensure levels do not go downand expose the heating elements of the ma-chine as this will cause them to burn out.

b. Place components to be cleaned in the aqueous partswasher, and either secure them to the turntable or securethe basket in which they are placed on the turntable.

Do not leave parts unattended in the washercabinet as the very hot and humid environmentinside the unit can cause the parts to corroderapidly. Remove the cleaned components fromthe washer as soon as possible after the cycle iscomplete

c. Set the wash cycle timer for 3 to 30 minutes dependingon the type of soil to be removed, the quantity of soilson the parts, and the number of parts involved and basedon the manufacturer’s recommendations in the equip-ment operating manual. Light degreasing may requireonly 3 minutes, while heavy soils and baked on greasemay require a full 30 minute cycle. Always run theaqueous parts washer for the entire programmed timecycle, and then allow the cleaned components to cool fora short time before removing and handling them.

d. If the cleaned components are to be subjected to animmediate in line process such as fluorescent penetrantinspection, surface treatment and/or painting, or

follow-on precision cleaning, rinse the part with freshtap water and dry them thoroughly.

e. Apply a film of MIL-PRF-81309, Type II, MIL-L-87177, Type I, Grade B, or MIL-PRF-16173, Grade 3,followed by a film of MIL-PRF-16173, Grade 4 on baresteel parts that have been cleaned and rinsed and will beleft unprotected from the environment without furtherprocessing for a period of time.

3.4.10 Miscellaneous Equipment. Accessories andconsumable materials for manual cleaning operations arelisted in Appendixes A and B, and include the followingimportant items:

3.4.10.1 The 3M Co. PN 251 Aircraft Washing Kit (referto Figure 3-6) is a conformable plastic device/head with asurface for attaching non-abrasive cleaning pads and sponges.It attaches to a mop handle for cleaning aircraft surface areas.

3.4.10.2 A-A-3100 Non-Metallic Cleaning and ScouringPads are crimped polyester fiber pads for use with detergentsand solvents for cleaning aircraft, missile, and equipmentsurfaces. These pads can also be attached to a 3M Co. PN 251Aircraft Washing Kit.

3.4.10.3 MIL-B-23958, Non-Metallic Bristle Brushes areused to agitate MIL-PRF-87937 and MIL-PRF-85570 deter-gent cleaners on aircraft, missile, and equipment surfacesduring cleaning operations.

Figure 3-4. Top Loading Type

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3.4.10.4 CCC-C-440, Type I or II, Class 1 or 2 Cheese-cloth, CCC-C-46, Type I, Class 7 Non-Woven Wiping Cloths,A-A-59323, Type I or II Low Lint Cleaning Cloths, and AMS3819A, Class 1 or 2, Grade A or B Cleaning Cloths are usedfor cleaning critical areas where an exceptionally clean clothis required, such as solvent cleaning prior to painting,adhesive bonding, or sealing.

3.4.10.5 A-A-2806, or equal, Plastic Pump-Spray Bottlesare used for applying diluted MIL-PRF-87937, Type I or IV,and MIL-PRF-85570, Type I or II, or concentrated MIL-PRF-87937, Type III and MIL-PRF-85570, Type V cleaningsolutions to small, localized areas being cleaned.

3.5 CLEANING PROCEDURES.

Where high outdoor temperatures are encountered (80° F /27°C and above) and an indoor wash rack is not available,

cleaning operations should be scheduled for early morning,late afternoon, or night. Wet aircraft exteriors with fresh waterbefore applying cleaners to cool surfaces and help preventfast evaporation and drying of cleaners during hot weather.For cold weather procedures, refer to Paragraph 3.5.2.6.

NOTE

Only water meeting the requirements in Para-graph 3.1.1, steps f (1) through (9) shall be usedin cleaning operations (washing and rinsing) onaircraft, missiles, and equipment.

3.5.1 Warnings and Cautions. The following warningsand cautions shall be observed during aircraft cleaningoperations:

3.5.1.1 Electrical.

• Aircraft and/or other equipment shall not bewashed, cleaned, or inspected on an outdoorwashrack when an electrical storm is in theimmediate area.

• Open all circuit breakers associated with bat-tery power (refer to applicable aircraft manu-als) prior to application of flammable solventcleaners.

• In order to guard against the danger of staticelectricity, aircraft shall be electricallygrounded during all cleaning operations andwhen moored and parked.

• Before cleaning electrical and avionic equip-ment, make sure electrical power is discon-nected. Injury or death may otherwise result.

Figure 3-5. Front Loading Type

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3-37

3.5.1.2 Personal Protection.

• Wear rubber gloves, chemical or splash proofgoggles, and water resistant boots duringcleaning operations using MIL-PRF-87937,MIL-PRF-85570, MIL-C-43616, or MIL-PRF-85704 cleaning compounds. If cleaner issplashed in eyes, rinse thoroughly with freshwater for 15 minutes and report to medicalfacility. Remove clothing saturated with clean-ing solution immediately and flush exposedskin areas with fresh water.

• Cleaning solutions are slippery. Use mainte-nance stands where practical. A safety harnessand safety lines shall be used when standingon upper surfaces of aircraft during cleaningoperations.

Consult the local safety office and bioenvironmental engineerfor personal protective equipment (PPE) requirements.

3.5.1.3 Use of Solvents.

• Do not use synthetic wiping cloths with flam-mable solvents, such as TT-N-95 aliphaticnaphtha.

• Solvents shall not be applied with atomizingspray equipment. This is not only hazardous,but violates environmental regulations in mostareas.

• Keep all solvents away from open flames andany live electrical circuit or sources of electri-cal arcing. Ensure that residual solvent isremoved from aircraft, engine bays, andequipment.

• Use solvents only in well-ventilated areas.Wear chemical resistant rubber gloves andchemical or splash proof goggles when usingsolvents. Avoid skin contact. Consult the localsafety office and bioenvironmental engineerregarding respiratory protection.

• Do not mix cleaning compounds with anysolvent such as A-A-59601 and MIL-PRF-680. The added solvents create a fire hazard, aserious disposal problem, and can damagenonmetallic materials.

3.5.1.4 Use of Cleaners.

• Steam shall not be used for cleaning aircraft,missiles, or their components. Steam can dam-age and/or deteriorate sealants, paint coatings,and elastomers.

• Do not apply MIL-PRF-87937 (except TypeIV) or MIL-PRF-85570 (except Type II),MIL-C-43616, or MIL-PRF-85704, Type Icleaning solutions or any unauthorized sol-vents to electrical wiring or plastic aircraftcanopies, as they may cause damage to insu-lation or crazing of transparent surfaces.

• Do not use cleaning compounds at higherconcentrations than those recommended. Donot allow cleaning solutions to dry on aircraftsurfaces. Such practices cause streaking andcan damage aircraft finishes and components.

3.5.1.5 Water Intrusion.

• To prevent entrapment of water, solvents, andother cleaning solutions inside of aircraft,missile, and equipment parts and structuralareas, all drain holes, flapper valves, etc., shallbe opened before washing to ensure thatproper drainage occurs.

• Do not wash or rinse aircraft, missiles, orequipment with a solid stream of water. Use asoft spray pattern to avoid damaging fragilesections or causing water intrusion.

• Do not direct water streams at pitot tubes,static ports, vents, etc. These areas shall beadequately protected by masking prior to start-ing a cleaning operation.

• Relubricate all fittings and other lube points inareas where cleaning compounds have beenapplied, such as wheel wells, flap wells, flightcontrol wells, etc. Ensure that these areas areadequately drained and check the system spe-cific aircraft manual to determine lubricationrequirements.

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3.5.1.6 Oxygen Systems.

Observe warnings and cautions in system specificoxygen system manuals.

3.5.1.7 Special Precautions.

Use extreme care when cleaning around radomes,access doors to integral fuel tank cells, lightfixtures, electrical components, antennas, etc.These areas may be damaged by cleaning solu-tions and equipment.

3.5.1.8 Preparation for Cleaning.

Open all circuit breakers associated with batterypower (refer to applicable system specific aircraftmanuals) prior to application of any flammablesolvent.

Cover acrylic or polycarbonate canopies andwindows on aircraft during washing operations toprevent accidental scratching or crazing by clean-ing compounds and equipment. Cover canopiesand/or windows with A-A-50129 flannel cloth.Cover the flannel cloth on the canopies and/or thewindows with MIL-PRF-131, Class 1 barriermaterial (plastic side toward aircraft) and tape itto the canopy and/or window frames, or thepainted surface near them using AMS-T-21595,Type III masking tape or AMS-T-22085, Type IIpreservation tape. Do not apply the tape directlyto the transparent surfaces.

3.5.1.9 Pre-Wash Lubrication Point Protection. Toprotect against cleaning solution entrapment, inspect alllubrication points having exposed lubrication fittings. Prior tomasking any components or parts, remove all foreign matterfrom joints, fittings, and bearing surfaces, using a CCC-C-46,non-woven cleaning cloth or an AMS 3819, Class 1, Grade Bcleaning cloth. Wipe up all spilled or excess oil and grease.Mask all fittings which will be exposed to wash solutionswith MIL-PRF-131, Class 1, barrier material and AMS-T-21595, Type III masking tape as needed. See the applicablesystem specific maintenance manuals and cards, and Para-graph 3.6 for location of lubrication points.

NOTE

Consult the system specific aircraft (-23) corro-sion manual for cleaning operation masking re-quirements for specific aircraft in addition tothose in this manual.

3.5.1.10 Water/Cleaning Compound Intrusion. Takethe following steps to prevent water/cleaning compoundintrusion during cleaning operations:

a. Close all doors, removable panels, and emergencyopenings, and seal and/or mask their edges if required toprevent leakage into interior areas. Mask all areas wherecleaning solutions and water can become entrapped andcause corrosion and other damage to aircraft and missilecomponents and structure, such as pod doors, areasaround thrust rings, radomes, optical glass, nirdomes,etc. Use prefabricated covers and/or MIL-PRF-131,Class 1 barrier material and AMS-T-21595, Type IIImasking tape or AMS-T-22085, Type II preservationtape for masking.

b. Check drain holes. Make sure that all drain holes areclean by inserting a probe, such as a pipe cleaner, intothem except for pressurized flapper valves. Refer tosystem specific aircraft maintenance manuals or (-23)corrosion manuals for location of drain holes.

Make sure that pitot static tubes and static vents/openings/ports are not fouled by tape adhesivetransfer. Cover them as directed in step c. below.

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Change 1 3-39

c. Cover all static vents, openings, and ports with circularcut pieces of MIL-PRF-131, Class 1 barrier material(plastic side toward the aircraft surface) and hold inplace with AMS-T-21595, Type III masking tape orAMS-T-22085, Type II preservation tape. Refer tosystem specific aircraft and missile maintenance manu-als and (-23) corrosion manuals for locations of staticvents, openings, and ports to be masked. Place covers onpitot static tubes. If covers are not available, a piece ofMIL-PRF-131, Class 1 barrier material may be cut andtaped in place on the pitot static tube with AMS-T-21595, Type III masking tape or AMS-T-22085, Type IIpreservation tape. Covers and masking must be removedprior to release of aircraft for flight. Particular care shallbe taken to ensure that static vents, openings, and portsand pitot static tubes are not fouled by tape adhesivetransfer. In the event of significant adhesive transfer,clean with TT-N-95 aliphatic naphtha.

Do not use a direct spray of water or cleaningcompound on carbon brakes, wheels or wheelhubs. If wheel bearings are suspected of contami-nation, corrosion, or loss of lubricant, removewheel bearings and relubricate in accordancewith applicable system specific maintenance in-structions and TO 4W-1-61. If carbon brakes aresuspected of contamination, decontaminate perapplicable system specific maintenance instruc-tions and TO 4B-1-32.

d. Cover wheels with covers designed and manufacturedfor the specific aircraft or locally fabricated covers toprevent water/cleaning compound contamination ofwheel bearings and carbon brakes. Carbon brakes havetemporarily reduced performance when subjected towater, deicers, degreasers, and oil. Protect brakes fromdirect impingement of fluids as much as practical duringmaintenance and aircraft cleaning operations. Weak orspongy brakes (and in some cases, smoke) may resultuntil the contaminants are burned off (normally oneflight/take off and landing).

3.5.2 Cleaning Methods.

• Wear rubber gloves, chemical or splash proofgoggles, and water resistant boots duringcleaning operations using MIL-PRF-87937,MIL-PRF-85570, or MIL-PRF-85704 clean-ing compounds. If cleaner is splashed in eyes,rinse thoroughly with fresh water for 15 min-utes and report to medical facility. Removeclothing saturated with cleaning solution im-mediately and flush exposed skin areas withfresh water.

• Open all circuit breakers associated with bat-tery power (refer to applicable system specificaircraft manuals) prior to application of flam-mable solvents.

• There are potential health risks associated withcleaning compounds if proper handling, mix-ing, and usage instructions are not followed.Consult the specific cleaning compoundMSDS and the local safety office and bioen-vironmental engineer for specific information.

The methods for cleaning aircraft, missiles, and equipmentmay vary depending upon the type of aircraft, missile, orequipment involved. Use the following methods for cleaningaircraft, missile, and equipment exterior surfaces. Refer toTable 3-2 for instructions on specific areas and components.

3.5.2.1 Alkaline Detergent and/or Solvent EmulsionCleaning, Painted and Unpainted Surfaces; Fresh Wa-ter Readily Available. Use procedures in Paragraph3.5.2.1.1, steps a through g.

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Do not use A-A-58054 abrasive mats for cleaningoperations on painted or unpainted surfaces.

3.5.2.1.1 Accomplish cleaning operations in planned stepsstarting with the lowest and most inboard surfaces to becleaned and work upward and outward. Dilute and/or mixcleaning compounds as recommended in Table 3-2.

a. Flush aircraft, missile, or equipment surfaces with freshwater when necessary to reduce skin temperature.Streaking will occur if cleaning solutions run down onand/or dry on hot painted or unpainted surfaces.

• MIL-C-43616 solvent emulsion cleaner andA-A-59601 and/or MIL-PRF-680 solventsshall not be used on non-polyurethane paintsystems and markings as the solvent materialswill cause them to fade.

• Consult the base bioenvironmental engineerbefore using these solvent materials as theycan create waste disposal problems.

b. Apply properly mixed/diluted MIL-PRF-87937, Type I,II, or IV, MIL-PRF-85570, Type I or II, or MIL-C-43616cleaning compound solution from a bucket, sprayingequipment (including the high pressure type if approvedby the aircraft SPD and/or the missile or equipmentSPM), or foaming equipment. Scrub surfaces with a 3MCo. PN 251 Aircraft Washing Kit (Appendix B; Item 1)fitted with a cleaning pad (Appendix A; Item 38; refer toFigure 3-6), one of the 3M Co. Improved Wash Padsfitted to its appropriate holder and handle (Appendix A;Item 39), or with a cleaning brush. Allow the solution todwell on the surface for 5 to 10 minutes. Start at thelower and inboard edges of the surfaces being cleanedworking upward and outward (refer to Figure 3-7).

NOTE

MIL-PRF-87937, Type I materials contain terpe-nes. Aircraft SPD and/or missile or equipmentSPM restrictions may apply. Consult system spe-cific maintenance manuals.

c. Rinse away the loosened soil and cleaner with fresh,heated, tap water at a temperature of 120° F/49° Cminimum to 140° F/60° C maximum. Use a rubberpadded shut-off spray nozzle (refer to Figure 3-8) torinse the cleaner and loosened soil from aircraft, missile,or equipment surface. Adjust the nozzle to provide alight to coarse fan spray directed at an angle between15° and 30° from the surface. Start at the outboard andupper edges of the area being rinsed working inward anddownward. Continue rinsing until all evidence ofcleaner and soils have been removed from aircraft,missile, or equipment. Small areas may be rinsed withwater applied with cloths or sponges which are rinsedout frequently, and then dried with a clean cloth orsponge, or allowed to air dry.

Figure 3-6. Use of Aircraft Washing Applicator

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Figure 3-7. Aircraft Cleaning Procedure

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NOTE

If hot water is unavailable, regular tap water maybe used for rinsing; but it takes a great deallonger, requires much more water, and is not asefficient in removal of residue from the surface.Hot water rinsing is known to reduce man-hoursrequired for rinsing by approximately 20 percent.

d. For aircraft, or equipment painted with a low gloss/flatand/or camouflage paint scheme, ground-in soils (bootmarks, smudges, etc.) can be cleaned with MIL-PRF-85570, Type IV spot cleaner. Apply with a cleaning pador sponge; and after several minutes dwell time, scrubthese areas with the pad or sponge, and rinse thoroughly.When the rubber particles in this cleaner are rubbed withthe pad, removable soils are erased from the low areas ordepressions in the surface of the paint

e. Clean wheel, flap, aileron, elevator, rudder wells andother heavily soiled areas which can tolerate waterrinsing with MIL-PRF-87937, Type III, or MIL-PRF-85570, Type V gel cleaner. These cleaning compoundsmay be sprayed on using a hand operated pump spray.Allow to dwell for 5 to 15 minutes, and then rinsethoroughly with a rubber padded shut-off fan spraynozzle adjusted to provide a light to coarse fan spray(refer to Figure 3-8).

f. Clean painted and unpainted surfaces on aircraft, mis-siles, and/or equipment that are protected/treated withCPC’s with MIL-C-43616, Class 2 (aerosol type) sol-vent emulsion cleaner applied by spray or A-A-59601,Type II or III, or MIL-PRF-680, Type II or III degreas-ing solvents applied with a brush, cloth, sponge, ornon-atomizing spray. Rinse the area thoroughly withfresh tap water (preferably hot water), and then wash byalkaline detergent cleaning per steps b and c above.

NOTE

MIL-PRF-87937, Type III or MIL-PRF-85570,Type V gel cleaning compounds may be used asalternates to clean CPC coated areas per proce-dure in step e above.

g. If surfaces are not clean at this point, repeat the cleaningprocess.

3.5.2.2 Waterless Wipe Down. Waterless wipe downprocedures for spot cleaning will be used only when water isnot available for rinsing, or when cold weather prevents theuse of water. The waterless wipe down method for removal ofsoils and corrosive salt residues is as follows:

a. Using a plastic spray bottle, apply MIL-PRF-87937,Type I or IV, or MIL-PRF-85570, Type I or II, (mixedone part cleaner to nine parts water) to the exteriorsurfaces of the aircraft (several square feet at a time).

NOTE


b. After 30 seconds, scrub, then wipe cleaner and soil fromthe surface with the clean CCC-C-46, Type I, Class 7 orAMS 3819, Class 1, Grade B cloth.

c. Rinse the cleaned surface with fresh water when itbecomes available and/or weather permits.

3.5.2.3 Alkaline Detergent Cleaning with Only Lim-ited Fresh Water Available. Use the following procedure,only when sufficient rinse water is not available:

a. Mix either of the following in a bucket depending on thetype of soil to be removed:

(1) One part MIL-PRF-87937, Type I, II, or IV, orMIL-PRF-85570, Type I or II cleaning compoundand 16 parts water for removal of light to moderatesoils; or

(2) One part MIL-PRF-87937, Type I, II, or IV, orMIL-PRF-85570, Type I or II cleaning compoundand 4 parts water for removal of heavy soils.

NOTE


b. Apply the cleaner with a cleaning pad, sponge, cloth, orcleaning brush one small area at a time (10 to 20 SQFT).

c. Scrub the area with the applicator from step b, and thenwipe clean with a CCC-C-46, Type I, Class 7, or AMS3819, Class 1, Grade B cloth.

d. For very stubborn soils, clean with A-A-59601, Type Ior II, or MIL-PRF-680, Type I or II degreasing solvent,and then scrub with one of the above solutions (1).

3.5.2.4 Solvent Cleaning. The use of MIL-PRF-87937,Type III, or MIL-PRF-85570, Type V cleaning compoundsfor cleaning very stubborn or exceptionally oily areas onexhaust tracks, landing gears, wheel wells, control surfacewells, and engine nacelles will normally be sufficient. Whenthese materials do not completely clean these areas, A-A-59601, Type II or III, or MIL-PRF-680, Type II or III can beused in small quantities. The quantity used shall be limited tothe minimum necessary to accomplish the required cleaning.Remember that solvents will burn intensely once ignited, solimit the amount of solvent available at the aircraft, missile,or piece of equipment to a maximum of three gallons underthe use and/or control of each authorized person involved in

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the solvent cleaning operation. Each authorized person shallbe thoroughly familiar with applicable safety precautions anddisposal requirements/information. The solvent dwell time onpainted surfaces shall be held to a minimum of 10 to amaximum of 15 minutes to prevent softening of the paint.Any dirty solvent draining off the surface during the cleaningoperation shall be controlled to prevent unauthorized entryinto the sewer. All solvent spillage shall be cleaned up perlocal regulations/directions. In no instance shall solvents beallowed to drain into or enter a public sewer or otherwise beallowed to contaminate streams or lakes. These guidelinesshall be followed when using A-A-59601, Type II or III, orMIL-PRF-680, Type II or III solvents:

a. Use only in areas approved by the local safety office.

b. Ensure that the area within 50 feet of the solventcleaning operation is clean and remains clear of allpotential ignition sources.

c. Use only explosion-proof electrical devices and powerequipment. Power units used in servicing shall be placedupwind and beyond the 50 feet clearance. Ensure thatthe aircraft, missile, or equipment is properly grounded.

d. No smoking shall be allowed in the solvent cleaningarea.

e. Mixing of solvents with other chemicals, cleaningcompounds, water, etc., is strictly prohibited except asspecified by this manual.

f. Suitable fire extinguishing equipment shall be availableto the solvent cleaning area.

g. Wear ANSI Z87.1, Type II goggles, protective wetweather clothing, solvent resistant gloves, boots, andhead covering. Use a respirator fitted with organic vaporcartridges when working in an enclosed area. Ensurethat good ventilation is maintained. Consult the localsafety office and bio-environmental engineer for PPErequirements.

h. Apply A-A-59601, Type II or III, or MIL-PRF-680,Type II or III solvents using a pad, cloth, or brush. Cleanup solvent spills as they occur.

i. Ensure that no solvent is trapped or has entered theequipment interior. Remove by wiping with clean cottonwiping cloths or by blowing dry, using clean, lowpressure air (10-15 PSI).

j. Collect waste solvents and solvent wetted wiping ragsand dispose of them per local regulations/directions.

k. After cleaning with A-A-59601 or MIL-PRF-680 sol-vents, re-clean the area using procedures in Paragraph3.5.2.1 to remove residue left by the solvents.

3.5.2.5 Interior Cleaning (Vacuum). Remove dirt,dust, small loose objects, paper, etc., from an area with anindustrial or domestic type vacuum cleaner. A soft bristlebrush on the end of the inlet tube/hose of the vacuum cleanerwill aid in removal of soils.

a. Inspect aircraft floor boards and bilge area underneaththe floor boards during depot level maintenance and asmay otherwise be required during field level mainte-nance for conditions that would necessitate cleaning orcorrosion removal and treatment. Particular attentionshall be given to urinal and latrine areas.

Accidental spills shall be investigated immedi-ately after occurrence to determine if the spilledmaterials are corrosive. Spills determined to becorrosive shall be neutralized as soon as possibleper directions in AFM 71-4 followed by cleaningper procedures in Table 3-2. Failure to complycan result in extensive corrosion damage andpossible unsafe conditions for operation of theaircraft, missile, or equipment.

b. When it is determined that harmful contamination, (i.e.,dirt spillage, foreign material, etc.) is present in anaircraft bilge area, remove the floor boards as necessaryto allow proper cleaning of the bilge area.

c. Clean the aircraft bilge area by vacuuming up all looseforeign material, dirt, etc., The vacuum removal of dirtor soil may be aided by agitating with the brush. Becareful not to sweep or wipe the dirt, etc., into oily orwet areas.

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Ensure there is adequate ventilation when usingA-A-59601, Type II or III, or MIL-PRF-680,Type II or III solvents and be sure the bilge and/orother areas are properly ventilated (blown out)before floor boards are reinstalled or closed.Warning signs shall be conspicuously placed atall aircraft entrances to indicate that combustiblematerials are being used. The guidelines cited inParagraph 3.5.2.4 for solvent cleaning proceduresapply.

d. Clean oily areas and/or spots by wiping them with aclean cloth dampened with A-A-59601, Type II or III, orMIL-PRF-680, Type II or III solvent followed immedi-ately by drying with a clean dry cloth. Do not over-saturate the cloth used for applying the solvent becausethis may result in the solvent puddling or enteringrecessed areas and creating a fire hazard. Precautionsshall be taken when using these solvents around electri-cal equipment to prevent entry.

Figure 3-8. Automatic Water Spray Nozzle

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Before starting the following cleaning operation,be sure that the spray or other method of appli-cation will not result in moisture damaging anycomponents, especially electrical components.Before using a spray method, ensure all drainholes are open, that the fluid materials will drain,and that the cleaning solution will not be forcedinto inaccessible areas. Do not apply the solutionto any moisture absorbing material such as insu-lation, sponge rubber (open cell), felt, etc.

e. If further cleaning is required, use a solution of 1 partMIL-PRF-87937, Type II or IV, or MIL-PRF-85570,Type II mixed with 9 parts fresh water applied by spray,mop, sponge, or brush. Use this solution only if it can beadequately rinsed and/or removed from the surface.

f. After applying the cleaning solution, allow dwell timeof approximately 10 minutes, agitate the solution on thesurface with a non-metallic bristle brush, and flush orrinse with clean water. Check drain holes to ensure thatthey are open and that the cleaning solution and waterare draining properly. Remove any remaining waterusing clean cloths. The surface shall then be thoroughlydried by blowing warm air over the surface or wipingwith clean, dry cloths.

g. In those areas where the above procedures cannot beused due to lack of drainage, possible damage tocomponents, etc., hand cleaning procedures will have tobe used. Apply a solution of 1 part MIL-PRF-87937,Type II or IV, or MIL-PRF-85570, Type II mixed with 9parts water to the surface with a rag or sponge wettedwith the solution and then agitate it with the applicator.Immediately following agitation of the solution, rinsethe area by wiping it with a rag wetted with clean waterand then wipe it dry with a clean, dry rag. Thisprocedure may have to be repeated several times onextremely soiled areas.

h. If corrosion is encountered and/or paint is removed, treatthe corrosion per this manual and the applicable systemspecific maintenance manual, and touch-up the paintsystem per TO1-1-8 and the applicable system specificmaintenance manual before the floor boards are replacedor area is closed.

3.5.2.6 Low Temperature Cleaning. Do not performroutine scheduled cleaning when the ambient temperature is40° F (4° C) and below. Instead, aircraft, missiles, orequipment shall be cleaned in an indoor, heated wash rack.However, if the ambient temperature is between 40° F (4° C)and 32° F (0° C) and such a facility is not available, exteriorareas/surfaces on aircraft, missiles, or equipment contami-nated with corrosive materials, such as runway deicing agentsand salt water shall have these areas/surfaces cleaned out-

doors using the waterless wipe down method in Paragraph3.5.2.2. Normal cleaning solutions cannot be used in freezingweather of 32° F (0° C) and below; so under these conditions,the following procedures shall be used for cleaning:

Table 3-3. Recommended Dilution of Low Tempera-ture Cleaner

AMBIENT TEMPERA-TURE

DILUTION RATIO (Partsmixture: parts water)

+30° F and above 1:4+10° F to +30° F 1:2+10° F and below 1:1

SAE AMS 1424, Type I aircraft deicing/anti-icing fluid is mildly toxic. Contact with skin andeyes shall be avoided. Do not inhale deicing fluidmist. Spray equipment operators and personnelusing brush applicators should stay on the wind-ward side of the aircraft and/or equipment to becleaned during cleaning solution application.Chemical, splash-proof goggles and wet weathergear, including boots and gloves, shall be wornby all maintenance personnel involved in lowtemperature cleaning operations.

TT-I-735 isopropyl alcohol or any other alcoholshall not be used for deicing acrylic plasticcanopies. Use Type AMS 1424, SAE Type Iaircraft deicing/anti-icing fluid for theseapplications.

a. If necessary, deice the aircraft, missile, or equipment perprocedures in TO 42C-1-2 and/or the applicable systemspecific maintenance manual.

b. Solvent clean heavily soiled areas of aircraft by wipingor brushing with A-A-59601, Type II or III, or MIL-PRF-680, Type II or III degreasing solvent using proce-dures in Paragraph 3.5.2.2.

c. To make a low temperature cleaner, mix ½ pint ofconcentrated/undiluted MIL-PRF-87937, Type IV orMIL-PRF-85570, Type II cleaning compound into onegallon of the ready-to-use (RTU) SAE AMS 1424, TypeI Aircraft Deicing/Anti-Icing Fluid or into one gallon ofa solution of the concentrated form of the SAE AMS1424, Type I Aircraft Deicing/Anti-Icing Fluid diluted 1

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to 1 with water. If necessary, warm either of thesecleaning compound materials until they can be easilypoured into the deicing/anti-icing fluid. Mix thoroughly.

d. Dilute this mixture as required by the ambient tempera-ture involved per Table 3-3 and mix thoroughly.

e. Scrub the aircraft, missile, or equipment using a brush,cloth, or aircraft washing kit.

f. Rinse by deicing as in step a. Heated deicing/anti-icingfluid mixtures will speed up the rinsing process.

3.5.3 Clear Water Rinsing of Aircraft.

• Do not rinse aircraft with a solid stream ofwater. Use a soft, spray pattern to avoiddamaging fragile sections or causing waterintrusion. Water must not be directed at pitottubes, static ports, vents, etc. Critical areasshall be adequately protected with groundplugs, covers, etc.

• Application of water in wheel wells, flapwells, flight control wells, etc., may necessi-tate the relubrication of some components/areas. Ensure that these areas are adequatelydrained and check the system specific aircraftmaintenance manuals to determine lubricationrequirements.

NOTE

• Clear water rinsing does not satisfy aircraftwashing requirements.

• Only water meeting the requirements in Para-graph 3.1.1, steps f (1) through (9) shall beused for clear water rinse operations.

3.5.3.1 Requirements. As directed by the requirementsin Paragraph 3.2.3, aircraft shall be clear water rinsed toremove salt contamination from aircraft surfaces caused byoperations near salt water. Most salt deposits are readilydissolved and/or dislodged and flushed away by rinsing.Rinsing can be done in a taxi-through facility or by directmanual spraying.

3.5.3.2 Taxi-Through Rinsing. Deluge rinse facilities(bird baths) are automatic installations located in a taxiwayarea for use by aircraft after flight through salt air. Theseinstallations provide multiple jet sprays of fresh water tocover the entire aircraft exterior surface to rinse off salt andwater soluble contaminants. Such facilities should be used asfrequently as possible per the requirements in Paragraph3.2.3.

3.5.3.3 Manual Application. Fresh water can be appliedfrom a hand held hose or piece of spraying equipment. Theforce or pressure used to apply the water is not as critical asthe amount of water. Satisfactory results are achieved with anamount of water that will create a full flowing action over thesurface. This requires a minimum of eight gallons per minute(GPM) of water at a nozzle pressure of 25 PSI minimum to175 PSI maximum.

3.5.3.4 Rinsing Procedures. Clear water rinsing shallbe accomplished as follows:

a. Direct water at an angle of 15° to 30° from the surface.Ensure that sufficient water flow is achieved on allsurfaces.

b. Begin rinsing on lower surfaces and work upwardstarting with the lower wing surfaces, then the lowerfuselage, and the lower horizontal stabilizer surfaces.Then rinse from the top down, starting with the upperand lower surfaces of the horizontal stabilizer on T-tailaircraft, the vertical stabilizer surfaces, then the upperfuselage, upper wing surfaces, and upper horizontalstabilizer surfaces. (Refer to Figure 3-7).

3.5.4 Post Cleaning Procedures.

Do not use synthetic wiping cloths with flam-mable solvents as these solvents can dissolvethem.

3.5.4.1 Post Cleaning Task Sequence. Strict compli-ance with the following post cleaning procedures is essential,and they shall be done in the following order:

a. Remove covers and masking from all static vents, pitotstatic tubes, air ducts, heater ducts, etc.

b. Remove tape from all other openings sealed withmasking tape.

c. Remove all tape adhesive residues with TT-N-95 ali-phatic naphtha or TT-I-735 isopropyl alcohol.

d. Ensure all drain holes are open by inserting a probe,such as a pipe cleaner.

e. Ensure that all areas that accumulate water have beendrained and/or otherwise dried. Whenever this is arecurring problem, specialized procedures shall be de-veloped and implemented to remove entrapped waterand other fluids to prevent their accumulation.

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An effective corrosion prevention and controlprogram requires that prescribed preservation andlubrication procedures be accomplished as soonas possible after a cleaning operation to prevent/minimize the occurrence of corrosion.

f. Upon completion of all cleaning operations, lubricate allexposed static joints and inject lubricant into all lubefittings in the areas cleaned in accordance with Para-graph 3.6 and applicable system specific maintenancemanuals to displace any entrapped water or cleaningmaterials that could cause corrosion and failure oflubricated parts if they remained.

g. Apply preservatives/corrosion preventive compounds(CPC’s) to components in the area cleaned in accor-dance with Paragraph 3.7 and applicable system specificmaintenance manuals as necessary. Cleaning com-pounds tend to remove preservatives, making previouslyprotected surfaces vulnerable to corrosion.

3.5.5 Treatment and Disposal of Wash RackWaste.

NOTE

Cleaning solutions which remove greases, oils,and surface contamination from aircraft, missiles,equipment, and components may exceed dis-charge concentration limits for oil and grease(especially where oil/water separators are notinstalled or not operating properly), naphthalene(from cleaners containing aromatic hydrocar-bons), chromium, cadmium, nickel, or otherheavy metals (from cleaning operations involvingengines or plated parts). If your wash rack is asource of hazardous waste, consult the basesafety office and/or bioenvironmental engineer todetermine corrective action. Take precautionarymeasures to prevent wash rack waste from con-taminating lakes, streams, or other natural envi-ronments. Some chemicals used for cleaningrequire treatment or other special controls prior todisposal.

3.5.5.1 The disposal of materials shall be accomplished inaccordance with applicable directives and in a manner thatwill not result in the violation of local, state, or federalpollution directives.

3.5.5.2 To reduce the problems associated with disposaland the actual cleaning process, all work shall be accom-plished on an approved wash rack. The only exception to this

requirement shall be for those facilities which are temporarilyestablished to support combat operations or special missions.

3.5.5.3 Aircraft wash rack cleaning waste shall receive theequivalent of secondary sewage treatment. When MIL-PRF-85704, Type I or MIL-C-43616, Class 1 solvent emulsioncleaning solutions are used, waste shall be released so that thetotal effluent entering the waste treatment plant does notcontain more than the amount limited by local environmentalregulations or 100 parts per million (ppm) of cleaningcompound.

3.5.6 Fungus Growth Removal.

A 50-50 by volume mixture of isopropyl alcoholand water is flammable with a flash point of 60°F. Use only with adequate ventilation, and com-ply with guidelines for solvent cleaning in thischapter.

Do not use isopropyl alcohol on transparentacrylic or polycarbonate plastics used for aircraftcanopies and windows or meththacrylate plastic(plexiglas) components as it can cause them tocraze.

Fungus growth (mildew and mold) occurs on the surface oforganic materials (plastics, paper, organic coatings/paints,etc.) and inorganic materials (metals, concrete, etc.) particu-larly in warm, damp/humid climates. Fungus growths must beremoved to prevent corrosion of metals and deterioration ofother materials caused by the fungus by-products.

3.5.6.1 Fungus Removal from Plastics. Since theterm plastics includes a wide variety of different chemicalcompounds with a wide variety of chemical and physicalproperties, one type can be cleaned by a method which candeteriorate another type. In general, organic solvents, mineralspirits, and paint thinners should not be used to clean plasticsor be allowed to come in contact with them. Except as notedabove, remove fungus from plastics by scrubbing the con-taminated area with a lint-free cloth or a sponge wet with a50-50 by volume solution of TT-I-735, Grade A or B, andfresh tap water with two (2) fluid ounces of P-D-410, Type IIdetergent per gallon of solution mixed in. Wipe off the residuewith a lint-free cloth wet with fresh tap water and wipe drywith a clean dry cloth. Clean fungus from transparent plasticsand plastic electrical insulation as follows:

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TT-N-95 aliphatic naphtha is flammable and toxicto the skin, eyes, and respira-tory tract. Keepaway from all sources of ignition. Avoid skin andeye contact. Good general ventilation is adequate.

TT-N-97 aromatic naphtha shall not be used toclean transparent plastics as it can attack anddamage them.

a. Remove fungus from acrylic, polycarbonate, and meth-acrylate (plexiglas) transparent plastic com-ponentswith a lint-free cloth or sponge wet with TT-N-95aliphatic naphtha, and then wipe dry with a clean, drycloth. If polishing is required, rub the area with SS-P-821, Grade F or finer pumice ground abrasive. ConsultTO 1-1A-12 for details on polishing transparent plastics.

b. Remove fungus from plastic electrical insulation bywiping with a lint-free cloth or sponge wet with a 50-50by volume solution of TT-I-735, Grade A or B isopropylalcohol and fresh tap water, and then wipe dry with aclean, dry cloth. Consult TO 1-1-689 for additionalinformation on cleaning electrical insulation.

3.5.6.2 Fungus Removal from Metal Surfaces. Re-move fungus from all metal surfaces other than electricalconnectors by first wiping the contaminated area with alint-free cloth or sponge wet with TT-I-735, Grade A or Bisopropyl alcohol followed by cleaning per the standardmethods in Table 3-2 for the type of area involved. Removefungus from electrical connectors as follows:

a. Remove fungus from exterior surfaces of electricalconnectors by wiping with a lint-free cloth or brushingwith a non-metallic bristle brush (tooth brush) wet withTT-I 735, Grade A or B isopropyl alcohol followed byrinsing with a stream of the alcohol from a plastic washbottle and then drying with clean, dry, oil free com-pressed air (15 PSI max).

b. Remove fungus from male pins/contacts using the samemethods as for the exterior surfaces of the electricalconnector.

NOTE

Consult TO 1-1-689 for additional information oncleaning of electrical connectors.

c. Remove fungus from female pins/contacts by scrubbingwith a pipe cleaner or a toothpick saturated withTT-I-735, Grade A or B isopropyl alcohol followed byrinsing with a stream of the alcohol from a plastic washbottle and drying with clean, dry, oil free compressed air(15 PSI max).

3.5.7 Soil Barriers.

Do not apply soil barrier materials to any areaother than engine exhaust and gun gas residueareas on aircraft having a camouflage or a flatpaint scheme. These materials increase the specu-lar gloss and IR reflectance of paint systemsthereby compromising the effectiveness of thecamouflage and flat paint schemes.

Soil barriers are transparent materials that are very effectivein preventing damage to both painted and unpainted engineexhaust track areas and areas exposed to gun gas residue onaircraft and/or other equipment. Soil barrier materials shall beapplied to these areas on aircraft immediately after curing ofa new or overcoat paint system prior to engine run andexisting paint systems after each aircraft wash as a part of theaircraft wash. Soil, soot, and/or gun gas residue graduallyaccumulate on or in the soil barrier film instead of the paintsystem protected by the film. when the protected area doesn’tmeet acceptable aircraft or equipment appearance standards,or an aircraft undergoes a routine wash, remove the soilbarrier film per Paragraph 3.5.7.3 and reapply per Paragraph3.5.7.2 using materials specified in Paragraph 3.5.7.1.

3.5.7.1 Materials. McGean-Rocho, Inc. PN Cee-BeeA-6 and Eldorado Chemical Co., Inc. PN PC-1020 are thesoil barrier materials approved for use on Air Force aircraftand equipment.

NOTE

• Rain or water do not deteriorate soil barriermaterials; but solvents, alkaline cleaners, andsolvent emulsion cleaners tend to degradeand/or remove them.

• If the temperature of the surfaces to be treatedwith soil barriers reaches or exceeds 100° F(38° C), cool the surfaces with a light spray offresh water before applying soil barrier mate-rials.

• No prior cleaning and/or rinsing of an area isrequired if soil barriers are being applied on anew or overcoat paint system.

3.5.7.2 Application. If an old soil barrier film is presenton the surface, remove it per Paragraph 3.5.7.3.

a. Thoroughly clean surface with MIL-PRF-87937, Type IIor MIL-PRF-85570, Type II cleaning compound perTable 3-2 and Paragraph 3.5.2.1.

b. Rinse surface thoroughly with fresh water to remove allgrease, oil, dirt, and cleaning compound residue andallow the water to drain off.

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c. When most of the rinse water has drained off, apply auniform film of either soil barrier material listed inParagraph 3.5.7.1 with a non-atomizing type sprayer(garden sprayer), brush, or roller, and allow the film todry for one hour before releasing the aircraft or equip-ment.

d. Flush the sprayer and/or rinse the brush or roller withfresh water immediately after completing the applica-tion operation. If soil barrier materials dry on/in appli-cation equipment, remove it with A-A-59601, Type II orIII, or MIL-PRF-680, Type II or III degreasing solventor soak the equipment in a solution of one part MIL-PRF-87937, Type II or MIL-PRF-85570, Type II clean-ing compound and four parts water for a minimum offour hours.

3.5.7.3 Removal.

a. Apply McGean-Roncho, Inc. PN Cee-Bee A-276 orEldorado Chemical Co., Inc. PN Astromat A soil barrierremover or A-A-59601, Type II or III, or MIL-PRF-680,Type II or III degreasing solvent to the surface from

which the soil barrier film is to be removed with anon-atomizing sprayer, mop, brush, or cloth.

NOTE

• Soil barrier removers may be used as receivedor diluted 1 to 1 with water, but undilutedworks best.

• Soil barrier removers are to be used only forremoval of soil barrier films. They shall not beused for any other type of aircraft or equip-ment cleaning

b. Allow the soil barrier remover or solvent to dwell on thesurface until it penetrates the soil barrier film (usuallyabout 20 to 60 minutes).

c. Scrub the area thoroughly with a brush or 3M Co. PN251 aircraft washing kit fitted with a non-abrasivecleaning pad or sponge, and then flush the area withfresh water.

d. Reapply soil barrier material per Paragraph 3.5.7.2.

SECTION III LUBRICATION

3.6 INTRODUCTION.

Lubrication performs a dual purpose: to prevent wear be-tween moving parts; and also to fill air spaces, displace water,and provide a barrier against corrosive elements. The lubri-cation requirements contained in system specific maintenancemanuals and/or cards are usually adequate to prevent corro-sion of most lubricated surfaces under normal operatingconditions. Aircraft lubrication shall be accomplished only bypersonnel qualified in lubrication procedures. In the eventthat the specified lubricant is not available, request substitu-tions from the aircraft SPD and/or the missile or equipmentSPM.

NOTE

Comply with relubrication time frame require-ments outlined in the system specific mainte-nance manual.

3.6.1 Conventional Lubricants. Table 3-4 contains thetitle, specification, intended use, and temperature range of themost frequently used conventional lubricating materials.

3.6.2 Solid Film Lubricants.

• Not all lubricating materials are compatiblewith each other and/or metals used in AirForce aircraft, missiles, or equipment. Someare known to promote galvanic corrosion orcause paint or acrylic plastics to deteriorate.Using the correct lubricating material is criti-cal. Do not use greases or oils with solid filmlubricants. Use only lubricants specified byappropriate system specific manuals and/orcards.

• Do not lubricate Teflon bearings or bushings.Clean Teflon bearings and bushings with A-A-59601, Type II or III, or MIL-PRF-680, TypeII or III degreasing solvent.

• Lubricants containing graphite, either alone orin mixture with any other lubricants, shall notbe used since graphite is cathodic to mostmetals and will cause galvanic corrosion in thepresence of electrolytes.

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Solid film lubricants are used where conventional lubricantsare difficult to apply or retain, or where other lubricants maybe contaminated with dust, wear products, or moisture and toreduce fretting corrosion on close tolerance fittings that seeprimarily static loads with only very small relative movementcaused by vibration. Typical applications of solid film lubri-cants are sliding motion components such as flap tracks,hinges, turnbuckles and cargo latches.

• Do not use solid film lubricants in areassubject to rotational speeds above 100 RPMunder heavy loads or on roller bearing ele-ments because they will not provide adequatelubrication in these situations.

• Do not use solid film lubricants in conjunctionwith oils or greases as they are not compatible.

3.6.2.1 As with paints, surface preparation prior to appli-cation is extremely important to the service wear life of solidfilm lubricants. In reality, solid film lubricants are nothingmore than paints with solid (powder) type lubricants used asthe pigment. They are usually applied over surfaces pre-coated with other films, such as anodize (aluminum andmagnesium base material), phosphate (steel base material),and sometimes over organic coatings such as epoxy primers.

3.6.2.2 SAE AS5272 (MIL-PRF-46010), Lubricant, SolidFilm, Heat Cured, Corrosion Inhibiting is a heat cured,corrosion-inhibiting, solid film lubricant that provides ex-tended wear life. It can be used on aluminum, copper, steel,stainless steel, and titanium in areas of infrequent operationand in areas requiring long term protection under staticconditions to prevent galling, corrosion, and metal seizure.Because SAE AS5272 (MIL-PRF-46010), Type I must becured at 400° F (205° C) for one hour and Type II must becured at 300° F (149° C) for two hours, they are not suitablefor all applications as metallurgical damage may occur atthese temperatures.

3.6.2.3 MIL-PRF-46147 and/or MIL-L-23398, Lubricant,Solid Film, Air Cured, Corrosion Inhibiting are air-cured,corrosion-inhibiting, solid film lubricants that can be used onaluminum, steel and titanium in areas of infrequent operationand areas requiring long term protection under static condi-tions to prevent galling, corrosion, and metal seizure. Theyprovide moderate wear life and corrosion protection in theseareas when it is not feasible to use a solid film lubricant thatrequires curing at elevated temperatures, and can be used torepair damaged SAE AS5272 (MIL-PRF-46010) heat-cured,solid film lubricants. MIL-L-23398, Type I (bulk) and Type II

(aerosol) both require a 6 hour cure at a temperature of 77°±3° F(25° ±2° C). MIL-PRF-46147, Form 1 (bulk) and Form2 (aerosol); Type I (standard solvents) require a 18 hour cureand Type II (low VOC content), both forms, require a 24 hourcure at these same temperatures. Curing of both MIL-L-23398 and MIL-PRF-46147 solid film lubricants may beaccelerated by allowing air drying at room temperature for 30minutes to flash off solvents and then heating to 125° ±5° F(52° ±3° C) for 1 to 1½ hours.

3.6.3 Application of Conventional Lubricants.

When lubricating hinges and pinned joints, applya generous quantity of either MIL-PRF-63460(preferably); MIL-PRF-81309, Type II; or MIL-PRF-32033 water displacing, Corrosion Preven-tive Compound (CPC) before applying the speci-fied lubricant. Actuate hinges several times tomake sure that the CPC’s and lubricants penetrateall crevices thoroughly, and then wipe off excessfrom exterior surfaces.

3.6.3.1 Apply lubricants as sparingly as possible toprevent accumulation of dust, dirt, and other foreign matter,but always apply enough to provide adequate lubrication.Wipe away any excess lubricant. Using the proper method ofapplication as specified in the appropriate system specificmaintenance manual is important. Apply lubricants by one ofthe following methods:

• Grease guns: lever or pressure type

• Oil, squirt, and aerosol spray cans

• Hand or brush

3.6.3.2 Grease Gun Application. When applyinggrease type lubricants in pressure type grease fittings (Zerkfittings) with a grease gun, clean grease fitting with A-A-59601, Type II or III, or MIL-PRF-680, Type II or IIIdegreasing solvent and clean cloth before applying lubricant.Make sure the lubricant has emerged around the bushing. Ifno grease appears, check the fitting and grease gun for properoperation. Be certain the grease gun is properly attached tothe fitting prior to applying pressure. When applying grease toa flush type (high pressure) fitting, make sure that the greasegun is fitted with a flush type adapter and held perpendicularto the surface of the fitting before applying pressure. If thefitting does not accept lubrication, replace the fitting andlubricate. Wipe excess grease from the fitting and the sur-rounding surfaces with a clean, dry cloth.

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Change 1 3-51

Table 3-4. Common Military Greases the Their Uses

Specification and Nomencla-ture

Intended Use Recommend Temperature Range

AMS-G-4343 Grease, Pneu-matic System (NATO CodeG-392)

Lubrication between rubber and metal partsof pneumatic systems; pressurized cabinbulkhead grommets and other mechanismsrequiring rubber to metal lubrication.

-65° to 200° F (-54° to 93° C)

AMS-G-6032 Grease, Plug,Valve, Gasoline and Oil Re-sistant (NATO Code G-363)

Tapered plug valves; gasket lubricant or seal;general plug valve and fitting use wheregasoline, oil, alcohol, or water resistance isrequired.

-32° to 200° F (0° to 93° C)

MIL-G-21164 Grease, Molyb-denum Disulfide, for Lowand High Temperatures(NATO Code G-353)

Heavily loaded steel sliding surfaces, acces-sory splines, or anti-friction bearings car-rying high loads and operating throughwide temperature ranges where molybde-num disulfide will prevent or delay seizurein the event of inadequate lubrication. Thisgrease is not intended for use in wheelbearings.

-100° to 250° F (-73° to 121° C)

MIL-PRF-23827 Grease, Air-craft and Instrument, Gearand Actuator Screw (NATOCode G-354)

Lubrication of ball, roller, and needle bear-ings, gears, and sliding and rolling sur-faces of equipment such as instruments,cameras, electronic gear and aircraft con-trol systems that are subject to extrememarine and low temperature conditions;rolling and sliding surfaces of equipmentwith low motivating power (low torqueequipment); general use on aircraft gears,actuator screws, and other equipment withhigh load carrying capacity. Its extremelylow volatility makes it useful on aircraftoptical equipment since it will not produceoil fogging

-100° to 250° F (-73° to 121° C)

MIL-G-25013 Grease, Aircraft,Ball and Roller Bearing(NATO Code G-372)

Lubrication of ball and roller anti-frictionbearings that operate at extreme high orlow temperatures, especially in applica-tions where soap-type petroleum or syn-thetic oil greases and oils cannot be used.Can be used on aircraft actuators, gear-boxes, and similar equipment.

-100° to 450° F (-73° to 232° C)

MIL-G-25537 Grease, Aircraft,Helicopter, Oscillating Bear-ing (NATO Code G-366)

Lubrication of aircraft bearings having oscil-lating motion of small amplitude.

-65° to 160° F (-54° to 71° C)

MIL-PRF-27617 Grease, Air-craft and Instrument, Fueland Oxidizer Resistant

Lubrication of taper plug valves, gaskets,and bearings in aircraft and ground supportequipment fuel systems; lubrication ofvalves, threads, and bearings of liquid oxy-gen (LOX) systems of aircraft, aerospacevehicles, and support equipment. Do notuse on aluminum or magnesium dynamicbearings due to possible ignition hazard.

Type I (NATO Code G-397) -65° to +300° F (-54° to +149° C)Type II (NATO Code G-398) -40° to +400° F (-40° to +204° C)

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Table 3-4. Common Military Greases the Their Uses - Continued

Specification and Nomencla-ture

Intended Use Recommend Temperature Range

Type III (NATO Code G-399) -30° to +400° F (-34° to +204° C)Type IV (NATO Code G-1350) -100° to +400° F (-73° to +204°C)Type V -100° to +450° F (-73° to +232° C)MIL- PRF-81322 Grease, Air-

craft, General Purpose, WideTemperature Range (NATOCode G-395)

NLGI Grade 1: arresting gear sheave spacersand other equipment that operates underhigh contact loads and high sliding speeds.

-65° to +350° F (-54° to +177° C)

NLGI Grade 2: aircraft wheel bearings andinternal brake wheel assemblies, anti-friction bearings, gearboxes, and plainbearings. Both will withstand high speedoperations and operations on equipmentsubject to extreme marine environments.

SECTION IV PRESERVATION

3.7 INTRODUCTION.

Corrosion preventive compounds (CPC’s), or preservatives,are used to protect metal aircraft, missile, and equipmentparts and components by preventing corrosive materials fromcontacting and corroding bare metal surfaces. Many of thesecompounds are also able to displace water, including seawater, and other contaminants from these surfaces; and someprovide lubrication, as well as corrosion protection. Gener-ally, CPC’s are mixtures of special additives in petroleumderivative bases (special oils or greases). CPC’s range inappearance and consistency from the thick, black types, suchas MIL-C-16173, Grade 1, to light oils, such as MIL-PRF-32033. The thicker CPC’s provide the best corrosion protec-tion, are longer lasting, and are more difficult to remove. Thethinner materials provide some lubrication and do not crack,chip, or peel; but they must be removed and replacedregularly to provide continuing protection.

3.7.1 Operational Preservation. The day to day appli-cation of CPC’s to prevent corrosion on operational aircraft isknown as operational preservation. Areas which are corrosionprone or where paint has been damaged should be routinelyprotected by CPC’s until more permanent treatment, such aspaint touch-up or sealant, can be applied.

3.7.2 Non-Operational Preservation. Preservation ofaircraft or components during periods of prolonged inactivity,storage, or shipment is known as non-operational preserva-tion.

3.7.3 Types of CPC’s. CPC’s can be separated into twomajor categories: water displacing and non-water displacingcompounds.

3.7.3.1 Water Displacing Compounds. Water displac-ing CPC’s can be used to remove water, in-cluding sea water,or other electrolytes from metal surfaces. MIL-PRF-81309,MIL-PRF-63460, MIL-PRF-16173, Grade 3, and MIL-PRF-32033 are water displacing CPC’s that are able to penetrateinto cracks, crevices, voids at faying surface edges, aroundfastener heads, and into hinges. They usually provide verythin coatings, one mil (0.001 inch) or less in thickness, thatare clear or translucent and remain soft and oily afterapplication, so they cannot provide long term protectionoutdoors or in areas which are frequently handled. Anothertype, MIL-DTL-85054, differs from the other water displac-ing compounds as it doesn’t penetrate into joints very well,but forms a relatively hard, dry film on exterior surfaces, andtherefore, it can be used for protection outdoors and in areasof frequent handling.

3.7.3.2 Non-Water Displacing Compounds. Non-water displacing CPC’s may be used on dried surfaces or onsurfaces which have been first treated with a water displacingCPC. MIL-PRF-16173, Grades 1, 2 and 4 are non-waterdisplacing CPC’s. They are heavier bodied, waxy typegreases which provide long term corrosion protection byforming a barrier film on metal surfaces. These CPC’sprovide thicker coatings and are light brown to very darkbrown in color, with a waxy greasy appearance. They providegood corrosion protection in areas where large amounts ofwater collect on or run off of structures.

3.7.4 Time Limitations of CPC’s. Because of theirtemporary nature, CPC’s must be regularly removed andreplaced to provide continuing corrosion protection. Table3-5 provides the recommended time intervals for indoor andoutdoor CPC use.

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Table 3-5. Time Limitations for CPC’s

CPC Outdoor1 Indoor2 3Indoor Covered

Soft Thin FilmsMIL-PRF-81309, Type II 14 Days 30 Days 180 DaysMIL-PRF-81309, Type III 5 Days 14 Days 90 DaysMIL-L-87177, Grade B 5 Days 14 Days 90 DaysMIL-PRF-16173, Grade 3 14 Days 30 Days 180 Days

Lubrication and ProtectionMIL-PRF-32033 5 Days 30 Days 180 DaysMIL-PRF-63460 5 Days 30 Days 180 Days

Hard Thick FilmsMIL-DTL-85054 90 Days 210 Days 365 DaysMIL-PRF-16173 Grade 4 90 Days 210 Days 365 DaysMIL-PRF-16173 Grade 2 90 Days 210 Days 365 DaysMIL-PRF-16173 Grade 1 210 Days 365 Days 365 Days

1 Outdoor: Without cover; exposed to elements in a mild climate; absence of Outdoor: Without cover; exposed to elementsin a mild climate; absence of Outdoor: Without cover; exposed to elements in a mild climate; absence of rain and otherwashing forces; free from air and water borne pollutants.

2 Indoor: Hangars, shop areas, storage or parts accumulation areas, warehouses3 Indoor covered: Items are wrapped or sealed in a water-resistant material and stored indoors in a hangar, warehouse, or

shop area. Soft thin film CPCs were designed for indoor use and ease of removal.

Table 3-6. Corrosion Preventive Compounds

Specification and Nomenclature Intended Use Type of Coating

WATER-DISPLACING CPC’sMIL-PRF-32033 Lubricating Oil,

General Purpose, Preservative,(Water Displacing, Low Tempera-ture); Military Symbol PL-S;NATO Code O-190

Lubrication and corrosion protectionof hinges, other moving parts, smallarms and automatic weapons, andwherever a low temperature, waterdisplacing lubricant is required; re-quires frequent reapplications.

Soft, oily coating and lubricant

MIL-PRF-63460 Lubricant, Cleaner,and Preservative for Weapons andWeapons Systems; Military Sym-bol CLP; NATO Code S-758

Lubrication and short term preserva-tion of hinges, and small and largecaliber weapons in all climatic con-ditions within a temperature rangeof -65° to +150° F (-54° to +66° C);facilitates the effective removal offiring residues, gums, and other con-taminants from weapons componentswhile providing adequate lubricationand short term preservation. Of allwater displacing CPC’s, this mate-rial is the best lubricant. Excellentwater displacing characteristics andpenetration into tight joints.

Thin corrosion preventive lubricantfilm

TO 1-1-691

3-54 Change 1

Table 3-6. Corrosion Preventive Compounds - Continued


MIL-PRF-16173 Corrosion Preven-tive Compound, Solvent Cutback,Cold Application, Grade 3

Displacement of water; short term cor-rosion protection of metal surfacesduring shipment, storage, and in-service use; can be used on movingparts where minor lubrication is re-quired, such as on hinges, bombracks, and sliding parts.

Soft, oily, thin film (1.0 mil), lightamber color

MIL-PRF-81309 Corrosion Preven-tive Compounds, Water Displacing,Ultra-thin Film

Type II Displacement of water; short term cor-rosion protection of metal surfacesduring shipment, storage, and in-service use; corrosion protection ofmoving parts where very minor lu-brication is required, such as hingeareas, bomb racks, and sliding parts.Cannot be used on interior of elec-trical or electronic equipment andconnectors.

Soft, oily, very thin film (0.5 mil)translucent, light amber color

Type III Displacement of water; corrosion pro-tection of electrical, avionics, andother electronic equipment, electricalconnector plugs and contact pins.This material and MIL-L-87177,Grade B are the only CPC’s that canbe used on the interior of electricalor electronic equipment and connec-tors

Soft, oily, ultra thin film (0.2 mil),translucent, light amber color.

MIL-L-87177 Lubricants, CorrosionPreventive, Water Displacing, Syn-thetic Grade B

Displacement of water, corrosion pro-tection, and some lubrication on in-service lightly loaded moving parts.Can be used on interior of electrical,avionics and other electronics equip-ment and connectors

Soft, oily, thin film (0.5 mil), translu-cent, light amber color

MIL-DTL-85054 Corrosion Preven-tive Compound, Water Displacing,Clear (AMLGUARD)

Corrosion protection and water dis-placement for non-moving parts,such as skin seams, installed fas-tener heads where paint has cracked,access panel edges, and areas withdamaged paint. Cannot be used oninterior areas of electrical or elec-tronics equipment and connectors orin joint areas of moving parts as itdries to a hard film.

Dry, thin film (1.0 mil), transparent,colorless to slight blue tint

NON-WATER DISPLACING CPC’sMIL-PRF-16173 Corrosion Preven-

tive Compound, Solvent Cutback,Cold Application

TO 1-1-691

Change 1 3-55

Table 3-6. Corrosion Preventive Compounds - Continued


Grade 1 Protection of metal surfaces againstcorrosion when exposed with orwithout covering indoors or out-doors. Cannot be used if tempera-tures will fall below 0° F (-18° C)as the film will crack and can spallfrom the surface leaving it unpro-tected.

Hard, tack-free, thick film (4.0 mils),dark brown or black color

Grade 2 Protection of metal surfaces againstcorrosion during rework or storage;film remains tacky.

Soft, non-drying, thick (2.0 mils),light brown color

Grade 4 Protection of metal surfaces againstcorrosion during indoor storagewhen a transparent coating is re-quired; coating of aircraft and equip-ment interior, metal wire controlcables.

Soft, tack-free, thick (2.0 mils), lightbrown color

3.7.5 Description of CPC’s. A list of CPC’s and theirintended uses is summarized in Table 3-6.

3.7.5.1 MIL-PRF-81309, Corrosion Preventive Com-pound, Water Displacing, Ultra Thin Film and MIL-L-87177, Lubricants, Corrosion Preventive, Water Dis-placing, Synthetic.

MIL-DTL-85054, MIL-PRF-63460, and MIL-PRF-81309 have been revised to eliminateODC’s. Some reformulated products now containflammable solvents and/or propellants. Pay closeattention to all CAUTION/WARNING labels onthe product containers.

MIL-PRF-81309 and MIL-L-87177 materials are generalpurpose corrosion preventive compounds for use when a thin,water displacing CPC is needed. MIL-PRF-81309 and MIL-L-87177 are for indoor protection and short term protectionwhere surfaces can be recoated when required. These mate-rials are excellent water displacing compounds which providean ultra thin, soft film (0.5 mil or less). The MIL-PRF-81309specification covers two types of materials and the MIL-L-87177 specification covers one grade of material that areuseful for Air Force purposes to provide temporary protectionfrom corrosion while still being easily removable with a

solvent. They should not be used around LOX fittings. All ofthese CPC’s may be applied by either dipping, brushing, orspraying with a pump or aerosol sprayer.

3.7.5.1.1 MIL-PRF-81309, Type II and MIL-L-87177,Grade B. These CPC’s form a soft, thin film for generaluse on moving or sliding parts where some lubrication isneeded, such as on hinges or bomb rack components. Thesematerials can be easily washed away by rain or washprocedures, so frequent reapplication may be required. Theyare useful in the protection of areas which cannot be properlydrained or contain recesses that are particularly difficult toreach due to their excellent water displacing abilities.

3.7.5.1.2 MIL-PRF-81309, Type III and MIL-L-87177,Grade B. These CPC’s form an ultra thin, soft film thatprovides excellent water displacement and corrosion protec-tion for the interior of electrical, avionics and other electronicequipment and connectors. Although these CPC coatings arenon-conductive, they will allow electrical contact becausetheir very soft, thin film is easily moved aside by mechanicalaction or contact. These materials are the only CPC’s allowedfor interior use on electrical and electronics equipment.

3.7.5.2 MIL-DTL-85054, Corrosion Preventive Com-pound, Clear (AMLGUARD). AMLGUARD is a waterdisplacing CPC which forms a clear, hard/dry, semi-flexiblefilm. It is intended for use as a protective coating on baremetal areas where the paint system has been damaged or

TO 1-1-691

3-56 Change 1

failed until touch-up and/or repainting is practical. Because ofits paint-like characteristics, it provides no lubrication andblocks electrical conductivity.

Ensure that all areas where MIL-DTL-85054 isapplied are fully dried before sealing an area.Although MIL-DTL-85054 is a corrosion preven-tive compound, its solvent vapors may causecorrosion if not allowed to dissipate.

3.7.5.2.1 AMLGUARD can be applied by either dipping,brushing, or spraying with a paint spray gun or an aerosolcan, but it is primarily applied by spraying from aerosol cans.Invert the aerosol can after each use and spray to clear thespray tip (nozzle) of entrapped material. If an aerosol candoes not spray, invert and depress the spray tip several timesto clear the delivery tube and spray tip (nozzle). If the can stilldoes not spray, remove and clean the plastic spray tip(nozzle), and then reinstall the spray tip (nozzle), and sprayagain to clear the delivery tube. Dip application provides onlya very thin coating and therefore much less corrosion protec-tion.

3.7.5.2.2 Remove AMLGUARD if it is damaged due toabrasion, there are cracks in the coating, or if there is

evidence of corrosion under the coating. Since excessiveAMLGUARD buildup is difficult to remove, especially afterprolonged exposure to direct sunlight, remove previouslyapplied coatings before reapplication. If the solvents recom-mended in Table 3-7 do not remove old films of AML-GUARD, spraying on fresh AMLGUARD to soften the filmand wiping or rubbing while wet is often effective.

3.7.5.3 MIL-PRF-16173, Corrosion Preventive Com-pound, Solvent Cutback, Cold Application. MIL-PRF-16173 covers five different grades of CPC’s which can beapplied by brushing or dipping. Grades 1, 2, and 4 do notdisplace water and must be applied to dried surfaces or tosurfaces which have been treated with MIL-PRF-81309, TypeII or III, MIL-L-87117, Grade B, or MIL-PRF-16173, Grade3.

3.7.5.3.1 Grade 1. A thick, hard, black CPC which canbe removed with difficulty using mineral spirits or degreasingsolvents. It offers the most corrosion protection of all theCPC’s indoors and outdoors, and may be used at tempera-tures down to 0° F(-18° C). If used at temperatures below 0°F (-18° C), the CPC film can crack and spall off leaving thesurface unprotected.

Table 3-7. Preservation of Specific Areas and Components

Area or Component CPC Application Instructions Removal Instructions

NOTE

Prior to the application of preservatives (CPC’s), ensure removal of old preservative CPC coatings.

EXTERIOR SURFACESNOT REQUIRING LU-BRICATION

Unpainted areas and areaswith damaged paint whichdo not require lubrication(fastener heads; fayingsurface, access panel,door, and frame edges;attachment points; non-moving attachment hard-ware; wheel well areas;ram air ducts; and flap/slat cavities)

MIL-DTL-85054 or Wipe off dirt and excessmoisture. Apply thin coat-ing of AMLGUARD. Al-low to dry ½ hour. Applya second coat.

Use a non-synthetic wipingcloth wet with A-A-59601,Type II or III, or MIL-PRF-680, Type II or IIIdegreasing solvent. Forstubborn AMLGUARD,refer to Paragraph3.7.5.2.2.

MIL-PRF-81309, Type IIor

Wipe off dirt and excessmoisture. Apply a coatingof MIL-PRF-81309, TypeII or MIL-L-87177, GradeB followed by a coating ofMIL-PRF-16173, Grade 4.

MIL-L-87177 Grade Band

MIL-PRF-16173, Grade 4

EXTERIOR SURFACESNOT REQUIRING HIGHPERFORMANCE LU-BRICANT OR HY-DRAULIC FLUID

TO 1-1-691

Change 1 3-57

Table 3-7. Preservation of Specific Areas and Components - Continued


Sliding or moving parts re-quiring only minor lubri-cation (bomb rack compo-nents, hinges, door locks)

MIL-PRF-63460 or Apply a continuous wet coatof MIL-L-63460.

Use a non-synthetic wipingcloth wet with A-A-59601,Type II or III, or MIL-PRF-680, Type II or IIIdegreasing solvent.


Apply a coating of MIL-PRF-81309, Type II orMIL-L-87177, Grade Bfollowed by a coating ofMIL-PRF-32033. Ifhandled, reapply as neces-sary.

MIL-L-87177, Grade Band MIL-PRF-32033

THREADED SURFACES MIL-PRF-63460 or Dip screws or fasteners inCPC and install. Whendisassembly is frequent,use MIL-PRF-63460, pre-ferably, or use MIL-PRF-81309, Type II or MIL-L-87177, Grade B asalternates. When disassem-bly is infrequent, use MIL-C-16173, Grade 4 for longterm protection.

Immerse screws or fastenersin A-A-59601, Type II orIII, or MIL-PRF-680, TypeII or III degreasing solventand blot or blow dry.

Screws, various fasteners MIL-PRF-81309, Type IIor

MIL-L-87177, Grade B or

MIL-C-16173, Grade 4

HYDRAULIC PISTONSURFACES

System hydraulic fluid Wipe exposed surface with acloth dampened with thehydraulic fluid used in thesystem. Always wipe awayfrom seals. Take care notto scratch surfaces.

Do not remove.

Reapply as necessary.

ELECTRICAL CONNEC-TOR SHELLS (EXTE-RIOR SURFACES)

NOTE

For additional information refer to TO 1-1-689.

Connector shells located incontrol surface wells,wheel wells, bilge areas,and other interior areas ofaircraft and missiles, andall areas of other equip-ment

MIL-DTL-85054 or Wipe off dirt and excessmoisture. Apply thin coat-ing of MIL-DTL-85054(AMLGUARD). Do notallow CPC to contact in-ternal surfaces. Allow todry ½ hour, and then ap-ply a second coat.


For stubborn AMLGUARD,refer to Paragraph3.7.5.2.2.

MIL-C-8130,9 Type II orIII or

Wipe off dirt and excessmoisture. Apply coating ofMIL-PRF-81309, Type IIor III, or MIL-L-87177,Grade B followed by acoating of MIL-PRF-16173, Grade 4.

MIL-L-87177, Grade BAnd


ELECTRICAL CONNEC-TOR SHELLS (INTE-RIOR SURFACES)

NOTE

For additional information refer to TO 1-1-689.

TO 1-1-691

3-58 Change 1



Do not use any other type of CPC than thoselisted here on the interior of electrical connectorshells as all other types will interfere with electri-cal conductivity.

Connector shells located inall the same areas notedfor exterior surfaces ofconnectors

MIL-PRF-81309, Type IIIor

Wipe off dirt and excessmoisture. Apply a thin,uniform coating of CPC.

Use a non-synthetic wipingcloth wet with TT-I-735isopropyl alcohol.

MIL-L-87177, Grade B

ELECTRICAL CONNEC-TOR PINS (ALL)

Do not use anyother type of CPCthan those listedhere on electricalconnector pins andsockets as theywill interfere withelectricalconductivity.

Connector pins and sockets MIL-PRF-81309, Type IIIor

Apply a continuous thin, wetcoat of CPC. If handled orexposed to water, reapply.

Use an acid brush with non-synthetic bristles to applyTT-I-735 isopropyl alcoholto pins and sockets.Lightly dab all pins andsockets, and then blot dry.

MIL-L-87177, Grade BELECTRICAL AND ELEC-

TRONIC EQUIPMENTRefer to TO 1-1-689.

CONTROL CABLES (ALL)(INTERIOR AND EXTE-RIOR)


Apply a continuous film ofMIL-PRF-81309, Type II;MIL-L-87177, Grade B; orMIL-PRF-16173, Grade 3water displacing CPC byaerosol can or by wipingwith cloth wet with theCPC.



MIL-PRF-16173, Grade 3and

Follow with a coating ofMIL-PRF-16173, Grade 4applied with a non-synthetic cloth or a non-metallic bristle brush.


TO 1-1-691

Change 1 3-59



HELICOPTER CARGOHOIST DRUM


Apply a continuous film ofMIL-PRF-81309, Type II;MIL-L-87177, Grade B; orMIL-PRF-16173, Grade 3water displacing CPC tothe drum surfaces by aero-sol can or by wiping witha non-synthetic cloth wetwith the CPC. Wipe with aclean cloth to remove ex-cess.



MIL-PRF-16173, Grade 3or

MIL-DTL-85054 Spray a continuous film ofMIL-DTL-85054 (AML-GUARD) on the drumsurfaces by aerosol can.Allow to dry one-halfhour, and then apply asecond coat.

For stubborn AMLGUARD,refer to 3.7.5.2.2.

ARMAMENTS Refer to the system specific equipment maintenance and/or instruction manual.EJECTION SEATS Refer to the system specific ejection seat maintenance manuals and SPM instructions.

3.7.5.3.2 Grade 2. A thick, soft, grease-like, brownCPC that remains tacky and can be removed with mineralspirits or degreasing solvents. It protects under relativelysevere conditions and given adequate maintenance touch-upas necessary, can be used for most maximum protectionrequirements. It may be used at temperatures down to -40° F(-40° C). It is not a good choice for parts that are handledfrequently since it remains tacky.

3.7.5.3.3 Grade 3. A thin, soft, oily film, water displac-ing CPC. This CPC doesn’t penetrate into tight joints as wellas MIL-PRF-81309, Type II or MIL-L-87177, Grade B, soone of them should be used as a substitute for this type ofapplication.

NOTE

Remove the MIL-C-16173, Grade 3 film withA-A-59601, Type II or III, or MIL-PRF-680,Type II or III degreasing solvent prior to inspect-ing an area when the coating is dark and preventsvisual inspection of the underlying surface forcracks and hydraulic leaks.

3.7.5.3.4 Grade 4. A thick, soft, waxy type CPC thatdrys to a tack free, semi-transparent film through whichidentification can be read. It provides good protection underrelatively severe conditions when touched-up as necessary. Itis excellent for use on in-service equipment over MIL-PRF-81309, Type II; MIL-L-87177, Grade B; or MIL-PRF-16173,Grade 3 water displacing CPC since it drys to a tack free film.It can be used at temperatures down to -40° F (-40° C).

3.7.5.4 MIL-PRF-63460, Lubricant, Cleaner, and Pre-servative for Weapons and Weapon Systems.

• If MIL-PRF-63460 is used in an area whichwill later be sealed or totally enclosed with noventilation, allow at least 4 hours for thesolvent to evaporate prior to sealing or closingoff the area. Although MIL-PRF-63460 is acorrosion preventive compound, its solventvapors may cause corrosion if not allowed todissipate.

• Do not use MIL-PRF-63460 on rubber orother elastomeric parts. MIL-PRF-63460 con-tains solvents which attack rubber O rings andother elastomeric parts. Do not use as a directsubstitute for VV-L-800.

MIL-PRF-63460 is a thin, water displacing, protective, pen-etrating lubricant used for cleaning, lubrication, and preser-vation of aircraft, missile, and equipment hinges and fittingjoints that experience only minor and infrequent relativemotion, and on parts and areas of small or large caliberweapons. This material has good lubricating properties be-tween -65° and +150° F (-54° and +65° C), and it is the bestlubricant of all water displacing CPC’s. It may be applied bybrushing, dipping, or spraying by aerosol can or a pumpsprayer.

TO 1-1-691

3-60 Change 1

3.7.5.5 MIL-PRF-32033, Lubricating Oil, GeneralPurpose, Preservative, Water Displacing.

MIL-PRF-32033 material suffers a loss of viscos-ity or starts to gel at very low temperatures,therefore, it shall not be used when temperaturescan drop below -40° F (-40° C).

MIL-PRF-32033 is a general purpose, water displacing,lubricating oil with preservative properties intended for thelubrication and preservation of aircraft, missile, and equip-ment components. It may be applied by brushing, dipping, orspraying by aerosol can or a pump sprayer.

3.7.6 Preservation of Specific Areas.

• Do not use corrosion preventive compoundson the interior of fuel tanks or fuel cells,engines, or engine fuel systems as fouling offuel systems may occur.

• Do not use corrosion preventive compoundson engine parts or accessories which exceed800° F (427° C). Corrosive reactions mayoccur with CPC’s at high temperatures.

• CPC’s are not compatible with LOX andshould not be used on oxygen equipment,lines, fittings or storage bottles. Fire mayresult.

NOTE

Use only corrosion preventive compounds(CPC’s) authorized by and described in thismanual and/or a system specific equipmentmanual.

Table 3-7 provides procedures for the preservation of specificareas and components where the use of a CPC on exposedmetal surfaces is generally recommended for reducing corro-sion. This list does not constitute authority to use CPC’s onspecific equipment. The use of some or all types of CPC’s incertain areas or on equipment may be detrimental. Therefore,consult the appropriate system specific aircraft, missile, orequipment corrosion and/or maintenance manuals beforeapplying a CPC in a new area to determine which, if any,compounds should be used in that area.

3.7.7 Preservation Application Methods.

• CPC’s and solvents can produce toxic vapors.Use only in well ventilated areas. Avoid con-tact with skin. Consult the local safety officeand bioenvironmental engineer for PersonalProtective Equipment (PPE) requirements.

• Do not use synthetic wiping rags or clothswith these materials as they will dissolve thesynthetic cloth/rag.

• Keep CPC’s and solvents away from openflames, heat, or sparks as they are flammable.

CPC’s can be applied by brushing, dipping, or spraying. Thearea of application, viscosity of the material, and conditionsunder which they need to be applied are factors that influencethe decision of which application method should be used.Low viscosity materials are best applied by spraying, whereashigh viscosity materials are more suited for brushing ordipping. Dipping can be used for all types of materials, butthe thickness of the coating obtained with low viscositymaterials may be too thin to provide adequate corrosionprotection. Prior to application of preservatives, remove oldpreservative coatings, and then apply a fresh coating usingone of the following methods:

3.7.7.1 Brushing. Brushing may be accomplished usingan ordinary paint brush. This method is most appropriate forapplying thick materials on small areas or in areas where it isnecessary to prevent material from getting on surroundingareas or nearby equipment.

3.7.7.2 Dipping. Dipping may be accomplished usingany suitable container for the CPC. It is most suitable forsmaller, disassembled parts. It cannot be used for assemblieswhich contain any part or area adversely affected by the CPC.

3.7.7.3 Spraying.

For spray application, do not thin or dilute bulkpreservative CPC unless absolutely necessary. Donot use synthetic wiping cloths. Mask off adja-cent areas to prevent overspray.

TO 1-1-691

Change 1 3-61

Spraying may be accomplished using paint spraying equip-ment, various types of pump sprayers, or aerosol cans. Thismethod is very effective for application to large areas whereconfined areas are not involved. The viscosity of the materialwill determine which type of spraying apparatus to use.

3.8 APPLICATION OF POLISH AND WAX.

Polishing and waxing of aircraft exterior surfaces is prohib-ited.

TO 1-1-691

3-62

CHAPTER 4INSPECTION AND CORROSION PRONE AREAS

SECTION I INSPECTION

4.1 PURPOSE.

Frequent corrosion inspections are essential for an effectiveoverall corrosion control program. Early detection, identifi-cation, and treatment, minimizes the costs resulting fromcorrosion damage. Without regular systematic inspections,corrosion will seriously damage aircraft, missiles, and equip-ment. This chapter describes the basic visual and Non-Destructive (NDI) inspection procedures for detecting corro-sion as well as some of the signs of corrosion damage.

4.1.1 Responsibility. Corrosion detection is everyone’sresponsibility. Since corrosion can occur almost anywhere onaircraft, missiles, and equipment, all maintenance personnelmust be able to identify and report corrosion problems.Personnel performing any scheduled inspections shall bequalified in corrosion detection and shall have attendedappropriate corrosion prevention and control courses estab-lished by AETC and the MAJCOM, and required by AFI21-105.

4.1.2 Frequency of Inspections. The frequency andextent of inspections are established by the aircraft SystemProgram Director (SPD) and/or the missile or equipmentSystem Program Manager (SPM). However, during sched-uled or unscheduled maintenance actions on aircraft, missiles,or equipment and their components, the area involved as wellas those within 36 inches (18 inches on each side) of therepair or treatment area shall be visually inspected forcorrosion. Additional inspections of areas particularly proneto corrode, such as magnesium gear boxes, wheel and controlsurface wells, bilge areas, etc. may be necessary. Corrosionprone areas are discussed in Paragraph 4.5.

4.1.3 General Inspections. A general inspection ofaircraft, missiles, and equipment is performed as follows:

a. Clean area thoroughly per instructions in Paragraph 3.5.

Prior to removing any access covers or panelscoated with TT-P-2760 flexible polyurethaneprimer either with or without a MIL-PRF-85285polyurethane topcoat, score the coating system atthe edges of the cover/panel with a sharp plastictool to prevent fraying or peeling of the paintfinish system when the panel is removed for thefirst time after the finish system is applied.

b. If corrosion is suspected, examine the area with a 10Xmagnifying glass and flashlight. Pay particular attentionto edges of skin panels, rivet heads, and other corrosionprone areas. If blisters, bubbles, or other coating irregu-larities are present, attempt to dislodge the paint byscraping with a sharp plastic tool. If paint does notdislodge easily, the irregularity is probably a sag or runwhich is confined to the paint film itself and no furtheraction is necessary. When corrosion is suspected but noirregularities are present, clean and dry the area perParagraph 3.5; and apply a strip of 3M Co. PN 250(preferred) or A-A-883, Type II, flat-back masking tapeover the area leaving a two inch length free at one end.Hand rub the tape for several strokes in order to assuregood adhesion. Grip the free end of the tape, and removethe tape with an abrupt lifting motion. Where paint isremoved, inspect and determine the extent/degree ofcorrosion as described by Paragraph 4.4.

c. Remove corrosion, clean, and treat the surface perprocedures in Chapter 5, and touch-up the paint per TO1-1-8.

4.1.4 Detailed Inspections. A detailed inspection ofaircraft, missiles, and equipment shall be performed if thecorrosion damage found during a general inspection issuspected to be extensive or severe, and/or as specified inappropriate system specific aircraft, missile, or equipmentmaintenance manuals. Aircraft, missiles, and equipment shallbe carefully inspected for corrosion using the NDI tools andprocedures listed in Table 4-1. Refer to Paragraph 4.5 forinformation on common corrosion prone areas.

4.2 INSPECTION METHODS.

4.2.1 Visual inspection. Visual inspection is the mostwidely used method for the detection and evaluation ofcorrosion. It is very effective for detecting most types ofcorrosion if done carefully with a knowledge of where and forwhat to look. Read Chapter 2 (Corrosion Theory) beforeperforming corrosion inspection, paying particular attentionto Table 2-1 (Appearance of Corrosion Products). The fol-lowing tools can be used to find and evaluate the extent ofcorrosion damage:

• Flashlight

• 10X Magnifying Glass

• Plastic Scraper

• Depth Gauge, pin micrometer type

TO 1-1-691

Change 1 4-1

• Borescope

• Optical Micrometer

4.2.1.1 Evidence of Corrosion. Aluminum corrosionproducts are either white, gray, or black and may appear as apaste when wet or as either a hard, adherent film or easilycrumbled deposits when dry. Magnesium corrosion productsare white and powdery, and form in large amounts withsignificant losses to the base metal. Steel corrosion products(rust) are red, brown, or black deposits either in the form ofa powder or when severe, as flakes that spall off easily.Copper corrosion products (patina) are blue or blue-greendeposits that adhere tightly to the surface. Titanium andstainless steels do not produce significant amounts of visiblecorrosion products on their surfaces, but they can exhibitcracking due to stress corrosion cracking. When corrosionoccurs beneath a paint system, the surface of the paintappears blistered, bubbled, or distorted.

4.2.2 Depth Gauge. Depth gauges are tools used tomeasure the depth of corrosion pits and areas reworked forpitting, exfoliation, and other types of corrosion to determinethe extent of corrosion damage and the amount of metalremoved during rework. If the pit and/or rework area depthare within allowable tolerances specified in a system specificaircraft, missile, or equipment manual as directed by Para-graph 5.6, the pits can be acceptably reworked, and areasreworked for corrosion damage of any type are acceptable.Reapplication of a protective coating system to reworkedareas per TO 1-1-8 and the applicable system specific aircraft,missile, or equipment manual is required. If the depth of pitsor a reworked area are not within allowable tolerances, the

part must be replaced or repaired, if allowed, or a request forengineering assistance must be submitted to the aircraft SPDand/or the missile or equipment SPM.

NOTE

On thin sheet material, waviness in the materialmay result in false depth readings. Several read-ings may be necessary, or it may be necessary toimprovise another method for determining thedepth of the corrosion damage. The depth gaugeis not suitable for determining the depth of astress corrosion or corrosion fatigue crack due tothe relatively large size of the indicator pin.

4.2.2.1 Use of Depth Gauges. Take several depthreadings in the affected area, and select the deepest reading asthe corrosion damage depth. Where there are several dam-aged areas in the same skin panel or component part, plot orsketch a diagram of the depth and location of each damagedarea for comparison with damage limits specified in theapplicable system specific aircraft, missile, or equipmentmanuals or for forwarding to the aircraft SPD and/or themissile or equipment SPM engineer when requesting engi-neering assistance. Place the depth gauge base flat against theundamaged surface on each side of the corrosion damagearea. When taking measurements on concave or convexsurfaces, place the base perpendicular to the surface (refer toFigure 4-1). Also, on the interior or exterior of an aircraftfuselage or a missile body, it is best to align the length of thedepth gauge base with the fuselage or body length.

Table 4-1. NDI Inspection Tools for Various Types of Corrosion

EquipmentType of Corrosion Detected orEvaluated (See Type Below)

Borescope 1, 2, 3, 4, 5, 10, 11, 12Depth Gauge 4, 5Optical Micrometer 1, 2, 4, 5, 6, 7, 8, 10,11Fluorescent Penetrant 3, 4, 8, 9Eddy Current 1, 3, 4, 6, 8, 9Ultrasonic 3, 4, 6, 8, 9,Radiography 6, 8, 9,Type 1 Uniform surface corrosion

2 Galvanic or dissimilar metal corrosion3 Intergranular attack (general)4 Intergranular attack (exfoliation)5 Pitting6 Crevice/concentration cell corrosion7 Fretting corrosion8 Stress corrosion cracking9 Corrosion fatigue10 Filiform corrosion11 Microbiologically induced corrosion

TO 1-1-691

4-2 Change 1

Table 4-1. NDI Inspection Tools for Various Types of Corrosion - Continued

EquipmentType of Corrosion Detected orEvaluated (See Type Below)

12 High temperature oxidation

Figure 4-1. Depth Dimension of Corrosion Pits

TO 1-1-691

4-3

4.2.3 Visual Inspection with a Borescope. The bore-scope has a small, high intensity light that can be used to aidin the inspection of interior surfaces which are not accessibleby any other method. Insert the head assembly into any cavityhaving a large enough opening. With the cavity illuminated,visually inspect it’s interior for defects, such as damage to thepaint system and corrosion (refer to Figure 4-2).

NOTE

Wearing eyeglasses makes it difficult to place theeye at the ideal distance from the eyepiece, andthe view is distorted by external glare and reflec-tion. Rubber eye shields on optical instruments(e.g. borescope, optical micrometer) are designedto shut out external light, but are not as effectivewhen glasses are worn. For these reasons, it isdesirable that the inspector be able to adjust theinstrument without wearing glasses to compen-sate for variations in visual acuity.

4.2.4 Optical Depth Micrometers..

4.2.4.1 Analog Mechanical Read-Out Type. This in-spection tool is an alternate for the digital read-out opticaldepth micrometer and is used to measure the depth ofscratches, cracks, pits, and reworked areas and/or the height

of spurs and other protrusions (refer to Figure 4-3). Theoptical depth micrometer is first focused on the highestsurface in the area of interest and a reading is taken. A secondreading is taken when the lowest surface is in focus. Thedifference between the readings is the distance between thetwo surfaces. Optical micrometers are available with 100 and200 power magnification, reticle eyepieces, and accessorylighting. Use the procedures outlined below to determine thedepth of corrosion pits and/or areas reworked due to corro-sion damage on any surface with the optical depth microme-ter:

a. Select the appropriate base surface (e.g., flat, curved,round, or inside/outside angle surfaces) in the areawhere the measurement is to be made that will providea stable location for the micrometer feet.

b. Position the micrometer solidly over the base surface Aof Figure 4-3 (undamaged surface close to surface B ofFigure 4-3) to make an initial measurement. While themicrometer is set over the surface, a pin point of lightwill cover the area being measured.

c. Look through the eyepiece of the micrometer and rotatethe micrometer thimble clockwise or counterclockwisestarting with the hundred thousandth scale, then the tenthousandth scale, and finally the thousandth scale until

Figure 4-2. Fiber Optic Borescope

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surface A of Figure 4-3 comes into sharp focus usingextreme care when focusing to reduce inaccuracy in themeasured values.

d. Obtain and record the reading for surface A of Figure4-3 located on the vernier scale. Since the vernier scaleis not one that can be simply read, an experiencedtechnician with the proper training is required to readthe scale accurately.

e. Position the micrometer over surface B of Figure 4-3(corrosion pit or area reworked due to corrosion dam-age) to measure the pit or rework depression depth.When measuring the depth of corrosion pits or reworkedareas, ensure that the surface being measured has a largeenough area to focus on for an accurate reading.

f. Repeat procedures in steps c. and d. on surface B ofFigure 4-3. Take several readings from the corrosiongrind-out area and/or the corrosion pit, and use thedeepest reading for the depth calculation.

g. Subtract the surface A of Figure 4-3 reading from thesurface B of Figure 4-3 reading to obtain the depth of acorrosion grind-out or a corrosion pit or: Pit/DamageDepth = B Reading - A Reading.

4.2.4.2 Digital Read-Out Type. This digital read-outoptical depth micrometer is the preferred inspection tool formeasuring the depth of scratches, cracks, pits, and reworkedareas and/or the height of spurs and other protrusions (refer toFigure 4-4). The optical depth micrometer is first focused onthe highest surface in the area of interest (usually an undam-aged surface next to a scratch, pit, or grind out area), and thedigital display is set to zero (0). The micrometer is thenfocused on the lowest surface of the area being inspected (thebottom of the scratch, pit, or grind out area). The readingshown in the digital display when the lowest surface isbrought into focus is the actual depth of the area or thedifference between the undamaged surface and the bottom ofthe damaged area. This type of optical micrometer comeswith extra lenses capable of 40, 80, 100, and 200 powermagnification. The depth of narrow features such as stresscorrosion and corrosion fatigue cracks can be observed andmeasured with the higher power lenses while using the reticleeyepiece to measure the width of such features. The digitalmicrometer kit also includes interchangeable bases, accessorylighting, and a sample scratch plate for demonstration andpractice. Use the procedures outlined below to determine thedepth of corrosion pits and/or areas reworked due to corro-sion damage on any surface with the optical depth microme-ter:

a. Select the appropriate base to use on the type of surface(e.g. flat, curved, round, or inside/outside angle) onwhich the measurement will be made.

b. Turn on the digital display, and check to see if it readsin inches and not millimeters. Change it to inches withthe in/mm button if necessary.

NOTE

The “origin” button is not needed or use in thisapplication.

c. Shine a flashlight down through the eyepiece to spot thetarget and position the micrometer. Look through theeyepiece, and focus up and down to assure that both thehigh and low surfaces are within the field of view.Rotating the focus thimble counterclockwise moves thelens up and clockwise moves the lens down. The 10Xobjective lens will focus when it is approximately ¼ inabove the surface.

d. Focus on surface A, and carefully press the “zero”button on the display without moving the micrometer.

e. Focus on surface B, and read the depth on the digitaldisplay while observing the following points:

(1) Do not move the micrometer base when refocusingbetween surface A at the 0.000 inch digital read-outand surface B.

(2) To get accurate readings, take extreme care infocusing. Be sure to focus well past the surface B(clockwise rotation) you picked in case even lowerareas might be found.

(3) If both surfaces A and B are not within the field ofview, use the 4X lens to get a wider field of view.

f. Take several readings from the corrosion damaged/grindout area, and select the deepest reading as the actualdepth.

4.2.5 Fluorescent Penetrant Inspection.

The apparent simplicity of the penetrant inspec-tion is deceptive. Very slight variations in theinspection process can invalidate the inspectionby failing to indicate serious flaws. It is essentialthat personnel performing penetrant inspection betrained and experienced in the penetrant process.

NOTE

The following inspection methods shall be ac-complished only by qualified and certified NDItechnicians. Refer to TO 33B-1-1 and the specificsystem specific NDI manual for more detailedinspection procedures.

Fluorescent penetrant inspections require components to becleaned and then treated with a fluorescent penetrating liquidwhich is capable of entering surface cracks and/or flaws.After removing the penetrant from the surface, a developer

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(powder or liquid suspension of powder) is applied to absorbpenetrant trapped in the cracks or flaws. Under ultravioletlight, the absorbed penetrant is visible directly above thecracks or flaws from which it was drawn out. The penetrantinspection method is used to detect stress corrosion cracking,corrosion fatigue and plain fatigue cracks, intergranularcorrosion, and residual corrosion following corrosion re-moval by grinding or sanding. Intergranular corrosion attackat metallic grain boundaries and the network of very finecracks it forms are visible in the early stages only under a10X or greater magnification, and developer is not used whenevaluating a penetrant indication with a magnifying glass. Inaddition, if penetrant inspection is used to monitor a surfacefor adequacy of corrosion removal by grinding or sanding,caution must be exercised because mechanical removal meth-ods can cause smearing which may obscure indications ofremaining corrosion. When monitoring corrosion grind-outareas with penetrant, a developer is not used followingremoval of excess surface penetrant; because the area mustalso be examined with a 10X magnifying glass after aminimum five minute dwell time. When corrosion is nolonger detected in a corrosion grind-out area, the inspectionprocess shall be repeated using non-aqueous developer todetermine if any cracks are present.

4.2.5.1 Limitations of Penetrant Inspection.

4.2.5.1.1 Flaw Location. Penetrant inspection is appli-cable to all solid, non-porous materials provided the flawbeing inspected for is open to the surface of the part. To detectsubsurface flaws, another inspection method must be used.

4.2.5.1.2 Restricted Flaw Openings. The penetrantinspection process depends upon the ability of the penetrantto enter and exit the flaw opening. Any factor that interfereswith the entry or exit reduces its effectiveness. Organiccoatings, such as paint, oil, grease, or resin, are examples ofthis interference. Any coating that covers or bridges the flawopening prevents penetrant entry, and even if it does not coverthe opening, material at the edge of the opening affects themechanism of penetrant entry and exit, and greatly reducesthe reliability of the inspection. Coatings at the edge of theflaw may also retain penetrant causing background fluores-cence. An inspection method other than penetrant must beused if the organic coating cannot be stripped or removedfrom the surface in the area to be inspected.

4.2.5.1.3 Smeared Metal. Mechanical operations, suchas shot peening, machine honing, abrasive blasting, buffing,wire brushing, grinding, or sanding, can smear or peen thesurface of metals. This mechanical working closes or reducesthe surface opening of any existing discontinuities or flaws.Mechanical working (smearing or peening) also occurs dur-ing service when parts contact or rub against each other.Penetrant inspection will not reliably indicate discontinuitiesor flaws when it is performed after a mechanical operation orservice that smears or peens the surface. Chemical etching

per procedures in TO 33B-1-1 and/or the system specificaircraft, missile, or equipment NDI manual is recommendedprior to penetrant operations to improve test sensitivity whensmeared metal is present.

4.2.5.1.4 Porous Surfaces. Penetrant inspection is im-practical on porous materials with interconnected subsurfaceporosity. The penetrant rapidly enters the pores and migratesthrough the network. This results in an overall fluorescence orcolor that masks any potential discontinuity or flaw indica-tions. In addition, removal of the penetrant after the inspec-tion may be impossible.

4.2.6 Eddy Current Inspection. The eddy current in-spection method may be used to detect or evaluate accessibleand inaccessible surfaces for corrosion. This method candetect and evaluate pitting, intergranular, exfoliation, stresscorrosion cracking, and corrosion fatigue cracking. Detectionof corrosion with eddy current techniques is used on aircraft,missile, and equipment skins where corrosion may occur oninaccessible interior surfaces. Corrosion usually occurs inareas where moisture is entrapped in faying surface areas. Ifrelatively uniform thinning is expected, corrosion detectionmay be simply a matter of thickness measurement. In mostinstances, corrosion is confined to smaller localized areas ofrelatively small diameter. As skin thicknesses increase, sen-sitivity to small areas and shallow depths of corrosion isreduced. Corrosion on either member of faying surfaces maybe detected. Refer to TO 33B-1-1 and/or the system specificNDI manuals for more detailed inspection procedures. Eddycurrent can also be used for corrosion removal inspections,but is less sensitive than penetrant.

4.2.7 Ultrasonic Inspection. The ultrasonic inspectionmethod may be used to detect exfoliation, intergranular,pitting corrosion; and stress corrosion and corrosion fatiguecracking. Ultrasonic thickness gauging is included in thismethod. Ultrasonic inspection for far-side pitting and internalexfoliation corrosion may be accomplished using shear (“S”)wave and longitudinal (“L”) wave techniques. The use of adelay line transducer is recommended for “L” wave inspec-tion to improve resolution of both near and far surfacecorrosion. Technique development is required for each spe-cific application. Refer to TO 33B-1-1 and/or system specificNDI manuals for more detailed inspection procedures.

4.2.8 Radiographic Inspection. Although the radio-graphic inspection method is available for detection andevaluation of corrosion, it is generally used only when noother method can accomplish the inspection. The labor hourrequirements are high for on-aircraft/missile/equipment radi-ography as well as requiring restricted access for othermaintenance personnel during the inspection. Radiographicinspection is used in combination with ultrasonics to deter-mine the condition of aluminum honeycomb. Refer to TO33B-1-1 and/or system specific NDI manuals for moredetailed inspection procedures.

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Figure 4-3. Optical Depth Micrometer (Analog Mechanical Read Out Type)

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4.3 EVALUATION OF CORROSION DAMAGE.

Visually determine if the corrosion is present in an area whichhas previously been reworked. If the corrosion damage is ina previously reworked area, measure the damage to includethe material which has previously been removed. A straightedge and a 10X magnifying glass may be used to assist indetermining if an area has previously been reworked. Place

the straight edge across the area being examined at variousangles and check for irregularities, low spots, or depressions(refer to Figure 4-5). If any irregularities, low spots, ordepressions are found, and a visual determination cannotverify previous rework, closely examine the suspected areaand the surrounding area using the 10X magnifying glass.After determining that the area has been previously reworked,evaluate the depth of the previous rework (grind-out) to

Figure 4-4. Optical Depth Micrometer (Digital Read Out Type)

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determine if further metal removal will exceed grind-outlimits specified in the applicable aircraft, missile, or equip-ment system specific manuals or as specified in Paragraph5.6. Depth measurements can also be made using the depthgauges as described in Paragraph 4.2.2 and Paragraph 4.2.4.

4.4 DEGREES OF CORROSION.

Corrosion must be evaluated after the initial inspection andcleaning to determine the nature and extent of repair orrework needed. It is difficult to draw a distinct and specificdividing line among the degrees of corrosion, so reliableevaluation requires sound maintenance judgment. Use thefollowing categories in reporting degrees of corrosion:

4.4.1 Light Corrosion. This degree of corrosion isindicated by the protective coating being scraped, gouged, orchipped to bare metal, or showing the tracks of filliformcorrosion in the film and the bare metal showing is charac-terized by discoloration of surface corrosion and/or pitting to

a depth of approximately one mil (0.001 inch) maximum.This type of damage can normally be removed by light handsanding.

4.4.2 Moderate Corrosion. This degree of corrosionlooks somewhat like light corrosion except some blisters orevidence of scaling and flaking of the coating or paint systemis present, and the pitting depths may be as deep as 10 mils(0.010 inch). This type of damage is normally removed byextensive hand sanding or light mechanical sanding.

4.4.3 Severe Corrosion. The general appearance of thisdegree of corrosion is similar to moderate corrosion in theappearance of the coating system but with severe intergranu-lar corrosion cracks and blistering exfoliation with scaling orflaking of the metal surface. The pitting depths are deeperthan 10 mils (0.010 inch). This damage must be removed byextensive mechanical sanding or grinding and may require apatch type repair or component replacement.

SECTION II CORROSION PRONE AREAS

4.5 COMMON AREAS.

There are certain corrosion prone areas common to allaircraft, missiles, and equipment. (refer to Figure 4-6 throughFigure 4-25). Corrosion prone areas should be cleaned,inspected, and treated more frequently than less corrosionprone areas. The following paragraphs describe the areas andcontain illustrations to aid in inspections. However, the list isnot complete and should be expanded by referring to the

system specific maintenance manuals and cards for eachspecific aircraft, missile, or piece of equipment which showother possible trouble spots.

4.5.1 Fasteners. There are hundreds to thousands offasteners on aircraft, missile and equipment exterior surfaces,and areas around these fasteners are trouble spots (refer toFigure 4-6 and Figure 4-7). These areas are subject to highoperational loads and/or moisture intrusion which makes the

Figure 4-5. Typical Use of a Straight Edge to Determine if Suspect Areas Have Been Previously Reworked

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skin material highly susceptible to corrosion at fastenerlocations. High strains cause paint to crack around thefasteners which provides a path for corrosive materials toenter the joint between fastener heads and skin panels. Anypaint that is not highly flexible will crack to some degreearound fasteners.

4.5.2 Faying Surfaces and Crevices. Similar to cor-rosion around fasteners, corrosion in faying surfaces, seams,and joints is caused by the intrusion of salt water and/or othercorrosive fluids or agents. Entry of fluids by capillary actioncauses corrosive liquids to flow into the tightest of joints. Theeffect of corrosion resulting from fluid intrusion into jointareas is usually detectable as bulging of the skin surface.

4.5.3 Spot-Welded Assemblies. Spot-welded assem-blies are particularly corrosion prone due to entrapment ofcorrosive agents between the parts of the assemblies (refer toFigure 4-8 and Figure 4-9). Corrosive attack causes skinbuckling or spot-weld bulging (refer to Figure 4-9) andeventual spotweld fracture. Skin and spot-weld bulging maybe detected in their early stages by sighting or feeling alongspot-welded seams. This condition is prevented by keepingpotential moisture entry points such as gaps, seams, and holescreated by broken spot-welds, filled with a sealant or asuitable preservative or CPC.

Figure 4-6. Corrosion Around Fasteners

Figure 4-7. Galvanic Corrosion of Aluminum Adjacent to Steel Fasteners

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4.5.4 Engine Exhaust and Gun Gas ImpingementAreas. Exhaust and gun gas impingement areas includeareas on an aircraft, missile, or piece of equipment exposed toengine, rocket, missile, and equipment exhaust, gun blast orany other surface exposed to them on installed equipment.These gases cover the organic finish on the surface withdeposits (i.e. corrosive ash and residual solids) that damagethe finish. Surfaces located in the path of rocket and gunblasts, including gun compartment systems and spent ammu-nition collection chutes, are particularly susceptible to dete-rioration and corrosion (refer to Figure 4-10). In addition tothe corrosive effect of the gases and exhaust deposits, theprotective finish is often blistered by the heat, blasted awayby the high velocity gases, or abraded by spent shell casingsor solid particles from engine, gun, and rocket exhausts/gases(refer to Figure 4-11). These areas require more attentionduring inspections.

4.5.5 Wheel Wells and Landing Gear. Wheel wellareas probably receive more abuse than any other area on anaircraft. They are exposed to water spray, mud, salt and otherrunway deicing agents, gravel, and other flying debris fromrunways during taxiing, takeoff, and landing. They are alsoexposed to salt air and spray when aircraft are parked atlocations near salt water. Because of the many complicated

shapes, assemblies, and fittings in the area, complete cover-age with protective coatings is difficult to maintain (refer toFigure 4-12).

4.5.6 Flap and Slat Recesses. Flap and slat recesses/wells (refer to Figure 4-13) and equipment installed in themare normally hidden from view since flaps and slats areusually maintained in the retracted/closed position when an

Figure 4-8. Spot Weld Corrosion

Figure 4-9. Spot Welded Skin Corrosion Mechanism

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aircraft is on the ground, and they may experience corrosionthat goes unnoticed unless special inspections are performed.

4.5.7 Engine Frontal Areas and Air Inlet Ducts. Sincethese areas are constantly abraded by dirt, dust, and gravel,and eroded by rain, special attention shall be given to:

a. Engine frontal areas (refer to Figure 4-14 and Figure4-15) for general surface corrosion, pitting, intergranu-lar corrosion, and erosion.

b. Leading edges of air inlet ducts, including hardwareinside ducts (refer to Figure 4-17 and Figure 4-16) fordamaged/deteriorated protective coating/paint system,galvanic corrosion at fastener locations, general surfacecorrosion, exfoliation corrosion, and erosion .

c. Due to heat dissipation requirements, oil cooler coresand reciprocating engine cylinder fins are not usuallypainted. Engine accessory mounting bases may havesmall, unpainted areas on the machined mounting sur-faces. With moist, salt-laden air flowing over thesesurfaces, they are vulnerable to general surface corro-sion/rusting and pitting.

Figure 4-10. Gun Blast Area Corrosion Points

Figure 4-11. Exhaust Trail Area Corrosion Points

Figure 4-12. F-15 Nose Landing Gear Wheel Well

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Figure 4-13. Flaps Lowered to Expose Recess Areas

Figure 4-14. Reciprocating Engine Frontal AreaCorrosion Points

Figure 4-15. Jet Engine Frontal Area CorrosionPoints

Figure 4-16. Corrosion Prone Point of Air Inlet

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4.5.8 Wing/Fin-Fold Joints and Wing and ControlSurface Leading Edges.

a. Wing and fin-fold areas are vulnerable to corrosiveattack when the wings or fins are folded, so they requirespecial attention (refer to Figure 4-18).

b. Both wing and control surface leading edges on aircraftare constantly exposed to salt laden air and wind erosionwhich make them vulnerable to corrosion, so they bothrequire special attention.

4.5.9 Hinges. Hinges (refer to Figure 4-19 and Figure4-20) are highly susceptible to corrosion because of dissimi-lar metal contact that results from wear and damage toprotective metallic coatings. They are natural traps for dirt,salt, and moisture. Piano type hinges which are used exten-sively on aircraft hatches and control surfaces are especiallyvulnerable to attack.

4.5.10 Control Cables. Control cables present a corro-sion problem whether they are made of carbon steel orstainless steel. As shown in Figure 4-21, the presence of barespots in the plastic cladding on clad cables or missing or gapsin the protective CPC coating are the main contributingfactors to the corrosion of cables. Dirt, grime, and rust thatcollect between cable strands lead to more severe corrosionand wear that eventually cause cable failure.

4.5.11 Relief Tube Outlets. Urine products are verycorrosive (refer to Figure 4-22). Relief tube areas should becleaned frequently and the paint finish kept in good condition.The relief tubes are usually made of plastic and do not presenta corrosion problem, but the surrounding metallic aircraftfuselage structure can be severely corroded by urine products.

4.5.12 Water Entrapment Areas. Figure 4-23 showscommon water entrapment areas. Design specifications re-

quire that aircraft have drains installed in all areas wherewater may collect, but in many cases these drains areineffective either because of improper location or becausethey are plugged by sealants, fasteners, dirt, grease, and/orother debris. The plugging of a single drain hole or thealtering of the attitude of the aircraft can cause seriousstructural defect if salt water or other corrosives remain forany appreciable amount of time in one of these entrapmentareas. Daily inspection and cleaning, if necessary, of lowpoint drains is a standard requirement. These areas mayaccumulate water following washing or rinsing of aircraft.Where this is a recurring problem, field units shall request theaircraft SPD to develop procedures to prevent water accumu-lation. Drain holes shall not be drilled by field units unlessspecifically authorized by the aircraft SPD.

4.5.13 Bilge Areas. Aircraft bilge areas are naturalcollection points (i.e., low points/areas in an aircraft fuselage)for water, salt water, dirt, loose fasteners, drill shavings, andother debris (refer to Figure 4-24). Keeping bilge areas free ofdebris and fluids, maintaining the protective finish system ingood condition, and application of CPC’s as required inaircraft system specific maintenance manuals are the bestprotection against corrosion in bilge areas.

4.5.14 Battery Compartments and Battery VentOpenings. In spite of protective paint systems, corrosionpreventive compounds, and venting provisions, battery com-partments are high corrosion problem areas (refer to Figure4-25). Fumes from overheated battery electrolyte will spreadto adjacent internal cavities causing rapid corrosion of un-protected surfaces. If the battery installation has an externalvent opening on the aircraft, missile, or equipment skin,include this area in battery compartment inspection andmaintenance procedures. Frequent cleaning and neutraliza-tion of deposits will minimize corrosion. Leakage of electro-lytes of either sulfuric acid from lead-acid batteries or

Figure 4-17. Corrosion in Air Intake Duct

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potassium hydroxide from nickel-cadmium batteries willcause corrosion. Consult the applicable system specific main-tenance manuals of the particular aircraft, missile, or piece ofequipment to determine which type of battery is used. Referto Chapters 3, 8 and system specific maintenance manuals forinstructions on neutralizing battery electrolytes.

4.5.15 Magnesium Parts. Magnesium parts are ex-tremely corrosion prone. Special attention must be given toproper corrosion preventive surface pretreatment of theirsurfaces, insulation from contact with other metal surfaces,and maintenance of protective paint coatings.

4.5.16 Electrical Connectors and Other Compo-nents. Some electrical connectors are potted with a sealantcompound to prevent the entrance of water into the backside

areas of connectors where wires are attached to pins. RubberO-rings are also used to seal moisture out of the front side orpin mating areas of connectors when two connector halvesare mated together. If moisture gets into electrical plugs, itwill cause corrosion and electrical failure. Electrical plugsmust be disconnected periodically for inspection and corro-sion treatment. The use of improper and unauthorized seal-ants, potting compounds, and corrosion preventive com-pounds can cause severe corrosion damage and/or electricalfailure of electrical connectors or components. Refer to TO1-1-689 for authorized materials and procedures for use onavionics and other electronic and electrical equipment.

Figure 4-18. Wing Fold Joint

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Figure 4-19. Hinge Corrosion Points

Figure 4-20. Piano Hinge Lugs

Figure 4-21. Control Cables

Figure 4-22. Personnel Relief Tube Vent

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Figure 4-23. Common Water Entrapment Areas

Figure 4-24. Bilge Areas

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Figure 4-25. Battery Compartment

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CHAPTER 5CORROSION REMOVAL AND SURFACE TREATMENT

SECTION I CORROSION REMOVAL

5.1 PURPOSE.

This chapter covers procedures for corrosion removal andsurface treatment. When corrosion is detected, a specific andimmediate corrective action is required. Each type of corro-sion has its own specifics and requires special treatment.Complete treatment involves a thorough inspection of allcorroded areas, evaluation of the corrosion damage (refer toChapter 4), paint removal per TO 1-1-8, corrosion removalper this chapter, application of chemical surface treatmentsper this chapter, sealing (refer to Chapter 6), and application/touch-up of protective paint finishes per TO 1-1-8.

5.2 RESPONSIBILITY.

Propellers and helicopter blades have criticalbalance requirements. Refer to the appropriatesystem specific propeller or blade manual forevaluation and repair limits for corrosion, ero-sion, and abrasion damage.

Personnel assigned to perform corrosion removal correctivemaintenance tasks shall be specially trained in the use ofchemical paint removers, abrasive materials, powered andhand tools, depth and area measurement of metal removed,and determination of damage limits from the applicablesystem specific maintenance manuals. Inadequate trainingwill lead to further damage of equipment and poses a safetyhazard to the individual.

5.3 CORRECTIVE ACTIONS.

Corrective maintenance depends on: the type of surfaceinvolved (metallic or composite); the area of the damagedsurface (small corrosion spot or large heavily corroded area);and the degree of corrosion, as determined in Chapter 4.Composite materials, such as fiberglass or graphite-reinforcedstructures, shall not be exposed to chemical paint remover,but shall only be scuff sanded to the primer coat. Sincecomposite materials do not corrode, corrosion removal tech-niques are not applicable and shall not be used. Corrosionshall always be removed by the mildest effective technique.

For mechanical procedures specific to the various metalalloys, refer to Table 5-3 and Table 5-4.

5.4 PAINT REMOVAL.

Refer to TO 1-1-8 for proper paint removal procedures.Choose the most effective method that produces the leastamount of hazardous waste and danger to personnel for thejob to be accomplished.

5.5 CORROSION REMOVAL.

Corrosion can be removed by either mechanical or chemicalmethods. Certain factors must be considered prior to startingany corrosion removal operation. The most important factoris that corrosion products must be removed completelywithout causing additional damage to the structure during theprocess. This can be accomplished by first removing allcorrosion visible through a 10X magnifying glass, thenremoving an additional two mils (0.0020 inch) to ensure thatall deposits have been eliminated. Failure to remove allcorrosion allows the corrosion to continue even after affectedsurfaces are refinished. Additional factors to consider are asfollows:

a. Before attempting to remove corrosion products, stripthe paint and clean contaminants from the surface.Surface contaminants and paint interfere with corrosionremoval procedures and make the operation more diffi-cult.

b. Protect adjacent components and parts from corrosionresidue and possible damage that could be caused by theremoval operation. Corrosion residue can cause addi-tional corrosion and damage the surface finish of thesurrounding area. An accidental slip of a corrosionremoval tool can quickly result in additional damage.

c. Prior to corrosion removal, determine the allowablelimits from the system specific aircraft, missile, and/orequipment manuals and/or technical orders. When re-moving corrosion from critical aircraft, missile, orequipment structure, take the following steps:

(1) If allowable metal removal or damage limits will notbe exceeded, remove corrosion completely. Metalloss due to corrosion damage is cumulative. Metal

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loss from prior corrosion removal operations andcorrosion removal from areas on the opposite side ofa part must be considered when assessing the degreeof corrosion damage.

(2) If allowable damage limits will be exceeded, repairthe damaged area or replace parts per procedures insystem specific aircraft, missile, or equipment repairmanuals/technical orders. Coordinate any repair orpart replacement not covered in these manuals/technical orders with the aircraft SPD or the missileor equipment SPM.

5.5.1 Mechanical Methods. There are various me-chanical methods for removing corrosion from metal sur-faces. The method used and the types of tools and equipmentselected for the removal operation depend on the type ofmetal involved, the location and accessibility of the corrodedarea, the degree of damage, and the type of corrosioninvolved. It is important that the removal method, tools, andequipment selected be compatible with the metal surface.Compatibility involves two considerations: the mechanicaleffect of the equipment and tools on the surface and thecompatibility of metallic particles worn off the removalequipment and tools which might become embedded in themetal surface.

5.5.1.1 Mechanical Compatibility.

Corrosion removal accessories/tools, such as flapbrushes or rotary files, shall be used on one typeof metal only. For example, a flap brush used toremove corrosion from aluminum alloys shall notbe used to remove corrosion from magnesiumalloys or steel also.

Mechanical compatibility refers to the selection of the righttools and equipment to prevent additional damage caused by

the removal process. Often it is necessary to select a series ofremoval techniques involving the use of different grades orclasses of equipment and material to effectively remove thecorrosion products. The initial use of a rapid and coarseremoval method followed by a slower and finer removalmethod produces a smooth metal surface finish (e.g. using avacuum blaster first followed by using a fine abrasive cloth orpaper to finish the job).

5.5.1.2 Material Compatibility. Material compatibilityrefers to using a medium for brushing, abrading, blasting,etc., that will not cause additional corrosion. Material com-patibilities are assured by using like metals during corrosionremoval operations (e.g. regular carbon steel wool shall neverbe used to remove corrosion from aluminum alloys as it willembed in the aluminum alloy surface and cause galvaniccorrosion).

5.5.2 Non-Powered Tools and Materials.

5.5.2.1 Abrasive Mats. Abrasive mats are made from anylon mesh material impregnated with various grades ofaluminum oxide. Abrasive mats are available in 9 x 11 inchsheets under A-A-58054, Type I, Class 1, Grade A - Very Fine(280-400 grit), Grade B - Fine (180 grit), and Grade C -Medium (100-150 grit). These mats are used by hand toremove small areas of corrosion and/or paint where the use ofpowered tools would be impractical or prevented by the shapeor accessibility of the area. Table 5-1 is a guide for relatingabrasive mat materials to coated abrasive paper and/or clothgrit particle sizes.

5.5.2.2 Abrasive Cloth. Abrasive cloths with bondedaluminum oxide grit per A-A-1048 and silicon carbide gritper A-A-1200 are used for dry sanding of light to moderatecorrosion products. They are available in 9 x 11 inch sheetsand 2 or 3 inch wide x 150 foot long rolls in 240 grit (fine)and 320 grit (very fine) grades.

Table 5-1. Grades of Abrasive Mats

Grade Coated Abrasive (CA) Equivalent

Medium (C) 100- 150Fine (B) 180 - 240

Very Fine (A) 240- 320Super Fine (AA) 500 & finerUltra Fine (AAA) 10 microns & finer

Table 5-2. Grades of Steel Wool

Type Grade Use

Very Fine Final smoothing

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Table 5-2. Grades of Steel Wool - Continued

Type Grade Use

II Fine Most commonly usedIII Medium General purposeIV Coarse Rough workV Extra coarse Restoration work

5.5.2.3 Abrasive Paper. Heavy paper with silicon car-bide grit bonded to it per A-A-1047 is used for either wet ordry sanding to remove light to moderate corrosion. It isavailable in 9 x 11 inch sheets in 240 grit (Fine) and 320 grit(Very Fine) grades. Silicon carbide is usually more effectivethan aluminum oxide on harder metals such as low carbonand corrosion resistant steel alloys. Other abrasive paper andcloth with bonded emery or flint are available, but they sufferfrom poor efficiency and short working life.

5.5.2.4 Metallic Wools. Metallic wools are abrasivematerials used for removing corrosion that is not tightlybonded to a metal surface. The four major types of metallicwools are: aluminum, copper, stainless (CRES) steel, andcarbon steel. Metallic wools are available in five grades,ranging from very fine to extra coarse. Table 5-2 is a guide tohelp select the correct grade of metallic wool.

5.5.2.4.1 The type of corroded metal must be knownbefore using metallic wool. Carbon steel wool is used on lowcarbon steel alloys; aluminum wool is used on aluminum andmagnesium alloys; copper wool is used on copper, bronze,and brass alloys; and stainless steel wool is used on stainless(CRES) steel alloys. The use of metallic wools which are notgalvanically compatible with the metal surface being treatedis not authorized. These metallic wool materials are verygood for removing corrosion from tubing or extruded parts.Remove all metallic wool residue from the metal surfacebeing treated and the surrounding area with a vacuum cleaner.Metallic wool particles can create galvanic cells if left on themetal surface.

5.5.2.5 Wire Brushes. Wire brushes are available withcarbon steel, stainless (CRES) steel, aluminum, and brassbristles and are used to remove heavy corrosion deposits andflaking paint that are not tightly bonded to the metal surface.Densely set, short, stiff bristles are most effective for rapidcorrosion removal. The metallic bristles must be compatible

with the metal surface being treated to prevent galvaniccorrosion with stainless (CRES) steel being considered neu-tral and usable on all metals. Do not use brushes with a bristlewire gauge or diameter above 0.010 inch, as severe gougingof the surface leading to stress risers and fatigue crackingmay occur. Remove the corrosion with a linear motion; do notcross-hatch as this will unnecessarily damage the surroundingsurface area. After wire brushing, the surface areas must bepolished with fine abrasive paper to remove and/or smoothout gouges and scratches.

5.5.2.6 Pumice Powder. Pumice powder is a very fineand soft abrasive used to remove stains or to remove surfacecorrosion on thin metal surfaces where minimum metalremoval is allowed. It is mixed with water and then rubbedover the area with a soft cloth to polish the surface. After thecorrosion is removed, the powder is wiped off the surfacewith a clean cloth wet with fresh water.

5.5.2.7 Scrapers. Scrapers are used primarily for theinitial removal of heavy corrosion deposits such as flakingrust and exfoliation blisters, and are particularly effective incorners and crevices that cannot be reached with otherequipment. Scrapers may be locally manufactured fromphenolic plastic, fiberglass, aluminum alloys, plain carbonsteel or carbide-tipped carbon steel, or stainless (CRES) steel.Plastic and fiberglass scrapers may be used on any type ofmetal surface but are of limited value due to their softnessrelative to a metal surface; stainless (CRES) steel andcarbide-tipped carbon steel scrapers may be used on any typeof metal surface; aluminum alloy scrapers may be used onlyon aluminum or magnesium alloy surfaces; and plain carbonsteel scrapers may be used only on carbon steel surfaces.Scrapers made from copper or brass alloys shall never beused on any structural metal surface as galvanic corrosionwill result. Failure to use the correct metal scraper can alsolead to galvanic corrosion after the part is returned to service.

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Surface areas must receive further finishing after corrosionremoval with scrapers due to the gouging action of scrapersand the difficulty in determining complete corrosion removalafter their use.

5.5.3 Power Tools and Materials.

• Power tool operations can often generate toxicairborne particles containing heavy metals,such as chromium (in the form of chromates),titanium, nickel, and beryllium, depending onthe surface being treated. Eye protection, ven-tilation, and an adequate respirator for dustcontrol are required.

• Do not use hands to probe for air leaks inpower tools and their hoses as injury mayresult.

• Before using any powered equipment, removeany clothing such as ties and shirts with longloose sleeves as well as all rings and otherjewelry which might become entangled in theequipment. Always wear proper personalsafety equipment (PPE), such as goggles,face-shields, respirators, etc. Ensure that allelectrical equipment is grounded.

• Corrosion removal with power tools is a veryaggressive method which shall only be usedwhen and where the extent of corrosion makesnon-powered corrosion removal impractical.The indiscriminate use of power tools forcorrosion removal can result in damage toprotective surface finishes.

Power tools are used to remove heavy corrosion fromlocalized areas on metal surfaces or mild to severe corrosionover large surface areas. Their use results in saving time andmoney, but care must be exercised when using power tools.

Application of excessive pressure can easily damage metalsurfaces and cause internal metallurgical changes in the metaldue to excessive heat buildup.

5.5.3.1 Pneumatic Drill Motors. Pneumatic drill motorsare the preferred power tools for removing heavy corrosion orreworking large surface areas. The drill motor is normallyused with wire brush wheels, rotary files, flap brushes,sanding pads, abrasive wheels, or buffing wheels. These drillsare available in many shapes and sizes to satisfy almost anyrequirement. Check all pneumatic equipment air hoses forbreaks or bulges in the coverings.

5.5.3.1.1 Maximum chuck capacity of portable powereddrills is usually ¼ inch. Insert the tool shank into the drill andtighten chuck securely with the chuck key prior to use. Whenit is difficult or impossible to reach the work area with astraight drill, use a flexible shaft or angle adapter. The flexibleshaft permits working around obstructions with a minimumof effort.

5.5.3.1.2 To prevent the rotary file, abrasive wheel, flapbrush, or sanding disc from digging into the metal, keep thetool off the metal when initially starting the drill motor. Whenthe abrading stroke is finished, lift the tool from the metalbefore releasing the power to the motor.

5.5.3.1.3 Holding the drill motor with both hands, applymoderate pressure while holding the rotary file, sanding disc,flap brush, or abrasive wheel against the work surface. Whenusing the pneumatic tool as a sander, be sure to check the sizeand type of the abrasive disc. Ensure that the type of disc iscompatible with the metal. Keep the sanding disc tilted toapproximately a 10 degree angle so that only one side of thedisc is in contact with the metal surface. If the entire discsurface is in contact with the surface, a “bucking” effect willoccur. Excessive pressure will cause a“chattering” effect.Move the tool over the surface with slightly overlappingstrokes. Do not grind, sand, or file in one area for anyextended length of time without stopping and allowing themetal to cool. Excessive heating of the metal will alter itsmetallurgical structure.

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Figure 5-1. 3M Co. Scotch-BriteTM Flap Brush and Mandrel

Figure 5-2. Abrasive Flap Wheels with Spindle Mount

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Figure 5-3. 3M Co. Radial Bristle Disc

Figure 5-4. 3M Co. Roloc Discs

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5.5.3.2 Pneumatic Sanders. The proper technique forusing pneumatic sanders with oscillating heads shall includethe following:

5.5.3.2.1 To prevent the sander from digging into themetal, start the sander before it touches the metal. When thesanding stroke is finished, lift the sander from the metalbefore pressing the stop switch. Do not lay the unit down withthe motor running.

5.5.3.2.2 For best results, apply moderate pressure whileholding the sander against the work. Move the sander overthe surface with parallel and slightly overlapping strokes.Move it as slowly as possible without causing overheating ofthe metal. Generally, the coverage rate should be about twosquare feet per minute.

5.5.3.3 3M Co. Scotch-BriteTM Finishing FlapBrushes.

Do not use flap brushes (refer to Figure 5-1)down to within 2 inches of core. Continued usebeyond this limit may cause gouging due to lossof flexibility of fiber. When using flap brushes,apply minimal pressure to remove a minimumamount of metal. Excessive pressure on flapbrushes will cause paint at the edge of the areabeing worked to melt, gum up, and streak ontothe work area. Do not use on non-metallicsurfaces.

Flap brushes are made of non-woven, nylon webbing impreg-nated with aluminum oxide grit. The brushes are veryeffective for removing mild surface corrosion and preppingsurfaces. It can also be used for mechanical removal andfeathering of paint systems. The brushes are comprised of a

series of flaps bonded to a cardboard core and attached to amandrel. Each flap impacts the surface as the brush spins.When used correctly, the brushes will lead to minimal metalremoval. The flap brush and mandrel (refer to Figure 5-1)shall be assembled so that the arrow, painted on the brush, isfacing the operator and points in the direction of rotation(clockwise). To achieve maximum effectiveness, use at thespecified RPM, and do not exceed the maximum RPM ratingspecified on the brush to prevent disintegration during useand either damage to equipment or injury to personnel.

5.5.3.4 Abrasive Flap Wheels. Abrasive flap wheelscome in various types. One type is made of paper flapsimpregnated with aluminum oxide abrasive and mounted ona spindle (refer to Figure 5-2). Another type is made from aresin reinforced nylon mesh impregnated with aluminumoxide abrasive in a convoluted flap form per A-A-59292,Class 1 or a unitized, rigid, laminated form per A-A-59292,Class 2, both of which are mounted on arbors. Depending ongrit size, these wheels can be used to remove medium tosevere corrosion from thick materials, but caution must beused to minimize the amount of metal removal. For the mosteffective use of this equipment, use at the specified RPM andnever exceed the maximum RPM rating specified on thewheel to prevent disintegration of the wheel during use andeither damage to equipment or injury to personnel.

5.5.3.5 Abrasive Cloth and Paper. Aluminum oxideand silicon carbide cloth and paper can be used with sandersand drill motors by cutting suitable pieces from stock or usingprecut discs mounted on pad type holders.

5.5.3.6 Powered Wire Brushes. Powered wire brushesare available with various types of wire (straight, twisted, orcrimped), various lengths of wire (short, medium, or long),and various wire densities (light, medium, or heavy). Differ-ent actions can be obtained by varying wire type, trim length,and density.

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5.5.3.7 Rotary Files.

Unless authorized and directed by the cognizantaircraft SPD or missile or equipment SPM, rotarywire brushes are not authorized for corrosionremoval on any metals except low strength car-bon steels. They can severely damage softermetal alloys such as aluminum and magnesiumby leaving deep gouges in them and cause fatigueproblems in high strength steel and aluminumalloys due to the stress risers created by the deepscratches/gouges they leave on the surface.

Since they provide one of the fastest ways to removecorrosion and underlying metal, rotary files should only behandled by an experienced structural repair technician. Thistool is a tungsten carbide cylinder or cone into which cuttingedges have been machined. When installed in the chuck of apneumatic drill, rapid metal removal can be achieved.

5.5.3.8 3M Co. RolocTM Disc and Radial Disc Abra-sives.

Improper use of rotary files can rapidly damagealuminum structures by creating thin spots thatexceed established damage limits. Their use isauthorized only for removal of severe intergranu-lar or exfoliation corrosion by qualified structuralrepair technicians. Do not use rotary files toremove corrosion from installed fasteners.

These tools are available in various grits and diameters tocover all corrosion removal requirements from initial grindout to final finishing/smoothing of the grind-out area. TheRolocTM discs consist of a spindle that screws into a disc padthat receives a screw on type paper coated abrasive disc, aScotch-BriteTM nylon mesh abrasive disc, or a plastic BristleDiscTM abrasive. These disc assemblies are mounted to eithera straight or right angle type pneumatic drill to remove

Figure 5-5. 3M Co. Inline Bristle Disc

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corrosion from all types of readily accessible metal surfaces.The radial type plastic Bristle DiscTM is similar to a flapwheel and is mounted to an arbor either by itself or inmultiples with the assembly being installed in a straight typepnuematic drill to remove corrosion from all types of metalsurfaces, particularly in bores and recessed areas. To achievemaximum effectiveness with these discs, use at the specifiedRPM, and never exceed the maximum RPM rating specifiedon the disc to prevent disintegration of the disc during use andeither damage to equipment or injury to personnel.

5.5.4 Abrasive Blasting.

Abrasive blasting operations create airborne par-ticles which may be hazardous to the skin andeyes. A hood, gloves with gauntlets, and adequateventilation are required.

In abrasive blasting, abrasive media is propelled toward thework piece either with air pressure (conventional or vacuumblasting) or with water (wet blasting).

5.5.4.1 Conventional Equipment. Two types of equip-ment are used to propel dry abrasives: direct pressure feed

and suction/venturi feed. In direct pressure equipment, theabrasive holding tank is a pressure vessel from whichabrasive media is forced, through a metering device, into thepressurized blast line to the blast nozzle. In suction/venturifeed equipment, the abrasive holding tank is unpressurizedand provides media, through a metering device, into a passingair stream which then propels it through the blast hose to theblast nozzle. Small blast cabinets known as glove boxes (referto Figure 5-6, A) are built to accommodate small parts andhave a recycle system which removes dust and light particlecontaminants such as paint chips or corrosion products.Blasting rooms, designed for large components, use a recy-cling and ventilating system. The operator works within theroom, using a blast gun.

NOTE

Suction/venturi feed equipment requires highernozzle pressure than direct pressure equipment toobtain the required abrasive action. Pressuresgiven in Table 5-3 are for direct pressure equip-ment. As a general rule, increase the nozzlepressure by 50 percent when using suction/ven-turi feed equipment.

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Figure 5-6. Abrasive Blasting Equipment

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Table 5-3. Recommended Powered Abrasives for Corrosion Removal

Abrasive Blasting Parameters

AlloyFlap Brush, Abra-

sive Wheels (1)Abrasive Cloth/

Paper (2) Media (3) Pressure (PSI) Other Tools

Aluminum alloys(Clad)

Aluminum oxideor silicon car-bide


Glass beads (Sizes 10-13) or (AGB-15, 12, 9,or 6)

30-40 (4) None

Aluminum alloys(Non-clad)




40-45 (4) Rotary files (finefluted)

Magnesium alloys Aluminum oxideor silicon car-bide



10-35 (4) Rotary files (finefluted)

Ferrous metals(other thanstainless steel)



Aluminum oxide (Type I,Grade A or B); Glassbeads (sizes 10-13) or(AGB-15, 12, 9, or 6)

40-50 (4) 40-50(4)

Rotary files,Wire wheels(steel or stain-less steel)

Stainless steel andNickel alloys



(5)Glass beads (Sizes10-13) or (AGB-15,12, 9, or 6)

40-50 (4) Wire wheels(stainlesssteel) Rotaryfiles (finefluted)

Copper alloys DO NOT USE POWERED ABRASIVE METHODS DUE TO TOXICITY OF RESIDUE/PAR-TICLES GIVEN OFF - IN PARTICULAR FROM BERYLLIUM-COPPER ALLOYS.

Powered abrasive operations on titanium alloys can generate severe sparking. Keep areaclear of all ignitable substances when performing powered abrasive operations on titaniumalloys.

Titanium alloys Aluminum oxideor silicon car-bide


Glass beads (Sizes 10-13) or (AGB-15, 12, 9,or 6); Aluminum oxide(Type I, Grade A or B)

40-50 (4) 40-50(4)

None

Plated and phos-phated surfaces

DO NOT USE POWERED ABRASIVE METHODS DUE TO TOXICITY OF RESIDUE/PAR-TICLES GIVEN OFF FROM MANY TYPES OF PLATING AND PROBABLE SEVEREDAMAGE TO VERY THIN PLATING FILMS.

(1) This includes RolocTM type discs and inline and radial type Bristle DiscsTM.(2) This includes RolocTM type discs.(3) Media specifications: Glass beads - AMS 2431/6 Aluminum oxide - A-A-59316(4) Indicated pressure is for direct pressure equipment. For suction/venturi equipment, use 50% higher pressure.(5) Use only on heavily corroded parts prior to acid pickling and/or passivation.

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Table 5-4. Recommended Non-Powered Abrasives for Corrosion Removal

Alloy Non-woven Abrasive Abrasive Cloth/Paper Metallic Wool Brushes Others

Aluminumalloys

Abrasive Mat Aluminum oxide,Silicon carbide

Aluminum wool Stainless steel,Aluminum

Pumice paste,Carbide-tippedscrapers

Magnesiumalloys


None Stainless steel,Aluminum


Ferrous met-als (otherthan stain-less steel)


Steel wool Carbon steel,Stainless steel

Carbide-tippedscrapers

Stainless steeland Nickelalloys

None Aluminum oxide,Silicon carbide

Stainless steel wool Stainless steel,Aluminum

None

Copper alloys None Aluminum oxide(400 grit), Siliconcarbide (400 grit)

Copper wool Brass None

Titanium al-loys


Stainless steel wool Stainless steel,Aluminum


Cadmium orZinc platedsurfaces


None None None

Chromium,Nickel, Tin,or copperplated sur-faces


None Stainless steel,Aluminum

None

Phosphatedsurfaces

USE METHOD RECOMMENDED FOR BASE METAL

5.5.4.1.1 Blast Media. A wide variety of materials invarious sizes (measured by mesh or grit size) are available forblasting applications. Only aluminum oxide per A-A-59316,Type I, Grades A or B and glass beads per AMS 2431/6,Designation Nos. 15, 12, 9, and 6 (sizes 10-13) abrasives areapproved for use on aircraft, missiles, and their components.Other media may be used on steel components of supportequipment as designated in TO 35-1-3 and/or the equipmentsystem specific maintenance manual.

5.5.4.1.2 Air Hoses. The nozzle pressure of a blaststream is affected by the length and inside diameter (ID) ofthe air hoses. It is best to use the shortest hose possible toprevent excessive pressure drop due to friction. If it isnecessary to couple lengths of hose, use quick disconnectexternal couplers.

5.5.4.1.3 Blast Nozzles. In general, larger nozzle sizesare preferable to smaller ones, because more area can becleaned per hour with the same amount of labor. Highefficiency, wear resistant nozzles (e.g. tungsten carbide)should be used, since they have a longer service life anddirect the blasting particles more efficiently. Inspect nozzles

periodically for wear and discard them when the orifice isworn to a diameter which is 50 percent greater than thediameter when new. A worn nozzle, just as a larger nozzle,will require a larger volume of air flow from the compressorto sustain the needed pressure at the nozzle.

5.5.4.1.4 Air Supply. Frictional losses in the hosesreduce the pressure at the nozzle, and nozzle wear increasesthe volume of air needed to maintain the desired nozzlepressure. To allow for nozzle wear, it is generally goodpractice to use a compressor with the capability of deliveringat least 1½ times the cubic feet per minute (CFM) of airrequired for a new nozzle to permit adjustments as the nozzlewears. Moisture and oil in the air stream gradually accumu-lates in the abrasive during blasting operations and willeventually cause the abrasive to clog the blaster. A water andoil separator must be used in the compressed air supply lineto prevent this problem.

5.5.4.2 Portable Vacuum Abrasive Blast Equip-ment. Also known as vacu-blasters or dry honing ma-chines, these devices are portable machines designed torecover the abrasive as it rebounds from the work piece.

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Vacu-blasters have an abrasive hopper, a reclaimer, a dustcollector, a vacuum pump, and a blast gun which containsboth a blast nozzle and a vacuum duct surrounding the nozzlefor recovery of the media (refer to Figure 5-6 B). Thisequipment is useful only on flat or slightly curved surfaces sothat the rebounding media can be collected by the vacuumduct surrounding the blast nozzle. Refer to TO 35-1-3, theequipment operators manual, and systems specific mainte-nance manuals for the aircraft, missile, or equipment beingrepaired for further information on the authorization and useof these machines.

5.5.4.3 Wet Abrasive Blasting Equipment. Wet abra-sive blasters use high pressure water as the medium for thedelivery of abrasives. This method is not as harmful to thebase metal as dry abrasive blasting due to the cushioningeffect of the water medium. Unfortunately, this effect inhibitsthe speed with which corrosion products are removed, and thewater can be driven into joint areas and cause corrosion itself.For these reasons, this method should not be used on aircraftor missiles. Wet abrasive blasters are useful for removing rustfrom steel surfaces of support equipment. The abrasivematerial is normally not recoverable in wet blasting opera-tions, and only sand per A-A-59316, Types II or VI, GradesB or C; aluminum oxide per A-A-59316, Type I, Grades A orB; or glass beads per AMS 2431/6, Designation No. AGB-6(size 13) shall be used. A corrosion inhibitor must be added tothe water or a temporary protective film such as a CorrosionPreventive Compound (CPC) must be applied to the blastedsurface immediately after blasting to prevent rusting of thesteel surface until the part can be painted.

5.6 SURFACE FINISH.

All depressions resulting from corrosion removal shall beblended smoothly and evenly with the surrounding originalsurfaces. In critical and highly stressed areas, all pits remain-ing after removal of corrosion products, by any method, shallbe blended out to prevent stress risers which may becomestarting points for stress corrosion cracking and/or metalfatigue. On non-critical structures, it is not necessary to blendout pits remaining after removal of corrosion products sincethis can result in unnecessary metal removal. Always checkthe system specific aircraft, missile, or equipment mainte-nance/repair manuals for maximum allowable depth of de-pressions due to pitting or corrosion removal. The generalguidelines for shaping and blending corrosion grind-outs areshown in Figure 5-7 through Figure 5-9. For additionalinformation on blend out procedures, refer to the systemspecific aircraft, missile, or equipment maintenance manualsand/or contact the aircraft SPD or the missile or equipmentSPM.

5.7 PITTING ON CRITICAL STRUCTURE.

On critical structures having a large number of closely spacedpits, intervening material may be removed to minimizesurface irregularity or waviness. The resulting depressionshall have no sharp corners and shall be saucer-shaped,wherever clearance permits, with its major axis running

spanwise on wings and horizontal stabilizers, longitudinallyon fuselages, and vertically on vertical stabilizers (refer toFigure 5-7). In areas where a true saucer shaped depressioncannot be formed due to inadequate clearance, blend out adepression as nearly as possible to that shape so that there areno abrupt or sharp edges.

5.8 CORROSION REMOVAL PROCEDURES-MECHANICAL.

5.8.1 Warnings and Cautions. The following warningsand cautions shall be observed during corrosion removaloperations.

5.8.1.1 Personal Protection.

• Many materials such as copper alloys (espe-cially beryllium-copper, refer to Paragraph7.20), cadmium plate, chromate conversioncoatings, paints containing chromates, lead,barium, and strontium, and chemicals used forcorrosion removal are toxic. Use approvedrespirators, eye protection, and skin protec-tion. Take proper safety precautions to avoidinhalation or ingestion of chemical fumes orliquids and dust from corrosion products dur-ing corrosion removal. Wash hands thoroughlybefore eating or smoking.

• All powered mechanical corrosion removalprocedures create airborne particles. Respira-tors and eye protection and adequate ventila-tion are required.

• It is essential that all blasting media and otherresidue be completely removed after abrasiveblasting operations. The blasting media can bevery slippery and can cause dangerous falls.

• Operators shall be adequately protected withcomplete face and head covering equipment,and provided with pure breathing air perrequirements of AFOSH Standards 91-31 and161-1 for all abrasive blasting operations .

• Wear leather gloves when using metallicwools to prevent hand injuries.

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• Do not use abrasive flap brushes, wheels, discsor wire brushes above their authorized RPMrating. These tools can fly apart, causingserious injury.

• Abrasive blasting operations create extensiveairborne particles which may be hazardous tothe eyes, lungs, skin, etc. A hood, gloves withgauntlets, and respirator are required.

• Exercise caution when using sharp or pointedtools to prevent injury.

• Depleted uranium is extremely toxic and shallbe worked only under a license from theNuclear Regulatory Agency (NRA). Machin-ing or other work, such as surface sanding,may be done only by the licensee. No drilling,sanding, abrasive blasting, or other mechani-cal work is permitted on depleted uranium byany field level (organizational or intermediate)maintenance activity. If the protective finish(plating) which covers the depleted uranium ischipped, peeled, or otherwise removed so thedark gray or black uranium oxide is visible,the part must be returned to the licensee forrework or disposal. Packaging and shippingprocedures shall conform to AFI 40-201 andother any other related current regulations forhandling radioactive materials.

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Figure 5-7. Shaping Reworked Areas

Figure 5-8. Acceptable Clean-up of Pitting Corrosion on Critical Structure

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5.8.1.2 Mechanical Damage.

• Use extreme care to ensure that blast mediadoes not contaminate hydraulic, fuel, oil, cool-ant, or oxygen systems. Blockages in flightcritical components caused by abrasive mediaparticles can result in loss of life and aircraft.

• Finely divided dried particles of many mate-rials (metallic, organic, and inorganic) canform explosive mixtures with air resulting indust explosion hazards. Use extreme carewhen dry abrasive blasting magnesium andtitanium alloys, and provide adequate ventila-tion to prevent formation of explosive dustmixtures during all abrasive blasting opera-tions.

• Abrasive blasting operations of these surfacesshall not be subjected to severe abrasive ac-tion. Do not use rotary files to remove corro-sion from installed fasteners.

• Use only non-powered abrasive paper, cloth,or mat, powered flap brushes or wheels, orabrasive blasting to remove corrosion fromhigh steels. Other power tools can cause localoverheating and/or formation of notcheswhich can generate fatigue or stress corrosioncracking failures. Refer to TO 4S-1-182 foradditional procedures/restrictions to be usedon aircraft landing gear components.

• Dry abrasive blasting of titanium alloys andhigh strength steel crates sparking. Ensure thatthe abrasive blasting area is free of all flam-mable vapors and liquids.

• Do not use flap brushes down to within twoinches from the center of the hub. Continueduse beyond this limit may cause gouging dueto loss of flexibility of the fiber. Followdirection of rotation, as indicated by arrowimprinted on side surface of the core.

• Excessive pressure on flap brushes will causepolyurethane paint to melt, gum up, and streakaround the area being worked

• Protect areas adjacent to corrosion removaloperations from chips, dust, and other debriswhich could produce dissimilar metal corro-sion on previously uncorroded surfaces.

• Use only those materials recommended inTable 5-3 and Table 5-4 to prevent dissimilarmetal particles from becoming embedded insurfaces and generating rapid galvanic corro-sion.

• Be careful when removing corrosion from softplated surfaces (zinc, cadmium, etc.). Softplating is easily damaged or removed bymechanical methods.

5.8.2 Non-Powered Mechanical Corrosion Re-moval. This method is accomplished by abrading thecorroded surface with hand held tools or abrasives to removethe corrosion. It is normally used to remove surface corrosionand other forms of mild to moderate corrosion by scraping orwearing away the corrosion products along with a minoramount of base metal. The basic steps in this procedure are.

5.8.2.1 Determine whether all the corrosion can be re-moved without exceeding the allowable damage limits before

Figure 5-9. Limited Clearance

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starting the removal operation. If damage limits will beexceeded, repair or replace the part per directions in theapplicable system specific aircraft, missile, or equipmentmaintenance manual or request disposition from the aircraftSPD or the missile or equipment SPM if repair or replace-ment is not covered in the manuals.

5.8.2.2 Protect adjacent components and/or areas fromscale, chips, corrosion products, and chemical agents. Masklap joints, hinges, faying surfaces, access doors, air scoops,and other openings which would allow chips, dust, or otherdebris to enter interior areas. Use barrier material/paper andmasking tape.

a. Clean the affected area to remove grease, oil, and soils(refer to Chapter 3).

b. Using materials in Table 5-4, remove all corrosion usingthe mildest effective method. Determine whether corro-sion has been completely removed by inspecting with a10X magnifier (refer to Appendix B). If necessary, amore sensitive evaluation can be made by using fluo-rescent penetrant in conjunction with the magnifier.

c. When complete removal has been attained, blend or fairout the edges of the damaged areas using fine abrasivepaper or cloth. After all corrosion has been removed,recheck to ensure that allowable damage limits have notbeen exceeded.

d. Treat the surface in accordance with Section II of thisChapter and apply protective coatings in accordancewith TO 1-1-8 and the applicable system specificmaintenance manual.

5.8.3 Powered Mechanical Corrosion Removal.Powered corrosion removal is generally done using pneu-matic drills with flap brush, rotary file, sanding pad orabrasive wheel attachments. This method is normally used toremove heavy corrosion by wearing away the corrosionproducts. Part of the base metal is abraded away with thecorrosion products using this procedure. The basic steps incorrosion removal are:

5.8.3.1 Determine whether all the corrosion can be re-moved without exceeding the allowable damage limits beforestarting the removal operation. If damage limits will beexceeded, repair or replace the part per directions in theapplicable system specific aircraft, missile, or equipmentmaintenance manual or request disposition from the aircraftSPD or the missile or equipment SPM if repair or replace-ment is not covered in the manuals.

5.8.3.2 Protect adjacent components and/or areas fromscale, chips, corrosion products, and chemical agents. Masklap joints, hinges, faying surfaces, access doors, air scoops,and other openings which would allow chips, dust, or otherdebris to enter interior areas. Use barrier material/paper andmasking tape.

a. Clean the affected area to remove grease, oil, and soils(refer to Chapter 3).

b. Using materials in Table 5-3, remove all corrosion usingthe mildest effective method. Determine whether corro-sion has been completely removed by inspecting with a10X magnifier (refer to Appendix B). If necessary, amore sensitive evaluation can be made by using fluo-rescent penetrant in conjunction with the magnifier.

c. When complete removal has been attained, blend or fairout the edges of the damaged areas using fine abrasivepaper or cloth.

d. After all corrosion has been removed, recheck to ensureallowable damage limits have not been exceeded.

e. Treat the surface in accordance with Section II of thisChapter and apply protective coatings in accordancewith TO 1-1-8 and the applicable system specificmaintenance manual.

5.8.4 Abrasive Blasting Corrosion Removal. Beforebeginning abrasive blasting operations, ensure that all safetyprecautions listed in the warnings and cautions in Paragraph3.5.1.2 and Paragraph 5.8.1.2 are fully observed. Failure tocomply with these precautions may result in harm to person-nel and equipment.

5.8.4.1 Abrasive Blasting Procedures. The blastingoperation should be accomplished in the following steps:

a. Inspect corroded areas and surfaces and decide whichones can be abrasively blasted and what techniques willbe used. Clean any oil, grease, or other soils fromsurfaces with MIL-PRF-87937, Type IV; MIL-PRF-85570, Type II; or an approved cleaning solvent such asA-A-59601 and/or MIL-PRF-680, Types II or III perinstructions in Chapter 3 of this manual.

(1) Blasting shall not be used in areas or under condi-tions that would allow any escaped abrasive particlesto contaminate any system, engine, or other compo-nent.

(2) Examine all corroded areas for corrosion blisters. Ifintergranular and/or exfoliation corrosion is present,use other recommended mechanical removal meth-ods. Abrasive blasting will not remove these types ofcorrosion effectively.

(3) Blasting shall not be performed on surfaces wherethere is a danger of warping or distorting the basematerial. Sheet metal, 0.0625 inch (16 gauge, U.S.Standard) or thinner shall not be blasted. Consult theapplicable system specific aircraft, missile, or equip-ment manuals to determine metal type, thickness,and allowable metal removal limits for the particularpart.

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b. Determine what areas need protection from the mediablast stream and entrapment of the media, and mask orseal these areas. Composite surfaces and those requiringa very smooth surface finish (63 RMS or better) must beeffectively protected from the media blast stream. Useform fitting metal or wood shields as required and animpact resistant tape such as 3M Co. PN 510 or YR-500.

c. Statically ground the abrasive blast equipment and theaircraft, missile, or equipment to be blasted.

d. Blast corroded areas using the pressures and materialsgiven in Table 5-3. Do not attempt to use pressureshigher than those specified, since higher air pressurestend to cause significant damage to components byrapidly removing too much surrounding metal alongwith the corrosion products. When cleaning non-ferrousmetal alloys (i.e. aluminum, magnesium, etc.), never usemedia which has been used for cleaning ferrous metals.Abrasives used for cleaning ferrous metals will retainmany ferrous metal particles which will contaminateany non-ferrous metal being blasted. Refer to theapplicable abrasive blasting equipment operator’smanual for specific operating instructions.

(1) Direct the blast stream at the surface from whichcorrosion is being removed to sweep across thesurface at an angle of 30° to 40° from the blastnozzle to the surface. Several short passes over thecorroded area with the blast nozzle are much moreeffective and less damaging to the surrounding metalthan dwelling on an area for an extended period oftime. Passes should start a few inches before and enda few inches beyond the corroded area being worked.

(2) Maintain the nozzle distance from the surface beingclean wherever the best cleaning is obtained withinthe range of 2 inches minimum to 6 inches maxi-mum.

(3) Continue blasting with short passes over the cor-roded area until a near-white metal surface is ob-tained. A near-white metal surface is a surface fromwhich all mill scale, rust, oxides, any other types ofcorrosion products, paint, and/or any other foreignmatter have been removed.

(4) On critical high strength aluminum and steel parts, itis necessary to fair out and smooth edges of pits toreduce stress concentrations that generate metal fa-tigue and/or stress corrosion cracking problems. Themost effective manner is to rotate the blast nozzlearound the outer edge of the pit, keeping the nozzleat a constant rate using several short passes over thecorroded area.

e. Upon completion of blasting, inspect for the presence ofcorrosion in the blasted area. It may be necessary to usefluorescent penetrant inspection in conjunction with a10X magnifier. Pay particular attention to areas where itis suspected that pitting has progressed into intergranu-

lar attack, because abrasive blasting has a tendency toclose up streaks of intergranular corrosion rather thanremove them if e. the operator uses an improperimpingement angle. If corrosion has not been removedin a total blasting time of 60 seconds on any one specificarea, other mechanical methods of removal should beutilized.

NOTE

• Refer to the individual system specific aircraft,missile, or equipment maintenance manualsfor limits on metal removal. Do not exceedthese limits without engineering approvalfrom the aircraft SPD or the missile or equip-ment SPM.

• Abrasive blasting will not remove intergranu-lar and/or exfoliation corrosion from alumi-num alloys.

• Abrasive blasting shall be used on stainlesssteel (CRES) and nickel alloy parts only toremove severe/heavy corrosion and prior toacid pickling and/or passivation.

f. Completely clean all residue from the surface andexposed areas using either a pneumatic or an electricwet/dry vacuum cleaner. The vacuum cleaner nozzleshall be plastic or covered with masking tape to protectsurfaces from mechanical damage. Clean the surfaceusing materials and procedures in Chapter 3. Treat andprotect all blasted areas as soon as possible after blastingin accordance with the procedures in Section II of thisChapter.

5.9 CORROSION REMOVAL-CHEMICAL.

The following paragraphs discuss chemical removal proce-dures for use on aircraft, missile, and other equipmentparts/components and assemblies. Each type of metal alloyrequires specific chemicals for removal of the different typesof corrosion that are encountered on the metal alloy. Theauthorized chemical corrosion removal materials and proce-dures for their usage for each of the various metal alloys usedon Air Force aircraft, missiles, and equipment is discussedseparately for each metal alloy.

5.9.1 Aluminum Alloys. These paragraphs outlinechemical corrosion removal procedures for aluminum alloyparts and assemblies of aircraft, missiles, and other equip-ment. Table 5-5 provides procedures for removal of specifictypes of corrosion.

5.9.1.1 Preparation. Before starting chemical removalof corrosion products, perform the following procedures:

a. Clean all dirt, grease, oil, and other contamination fromsurfaces to be worked in accordance with Chapter 3.

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b. Inspect the equipment to determine which area(s) areand should be treated with a chemical corrosion removalcompound. If an aircraft is being prepared for completepainting or repainting, all cleaned bare aluminum sur-faces shall be treated.

• Protect all magnesium surfaces from contactwith SAE AMS-1640 (MIL-C-38334) corro-sion removal compound and treat later, asprescribed in this manual. Steel and cadmiumplated parts should also be protected from thiscompound, but protection of all steel andcadmium plated steel fastener heads in largestructures is impractical and need not be done.

• Do not allow these chemical corrosion remov-ers to contact high strength steel. Hydrogenembrittlement may occur and cause a cata-strophic failure.

c. Mask all lap joints, hinges, faying surfaces, accessdoors, air scoops, and other openings that would allowthe corrosion removal compound to enter interior areasor crevices, or contact unprotected magnesium, steel,and cadmium plated parts. Mask with MIL-PRF-131,Class 1 water and vapor proof barrier material (plasticside toward the surface) and SAE AMS-T-23397, TypeII (MIL-T-23397, Type II) masking tape. 3M Co. PN425 tape is the most effective tape for extensive opera-tions, such as chemical corrosion removal and surfacepreparation on large structures such as aircraft exteriorsduring depot repaint operations.

5.9.1.2 Chemical Corrosion Removal Materials forAluminum Alloys. SAE AMS-1640 (MIL-C-38334, TypeI) Corrosion Removal Compound for Aircraft Surfaces is theauthorized general chemical remover for removing corrosionproducts from aluminum alloys, in particular on larger areas.Limited area corrosion removal can also be accomplished byusing MIL-DTL-81706, Class 1A chemical conversion coat-ing solution or Semco® PN Pasa-Jell 102 gel type aluminumcorrosion remover in conjunction with A-A-58054, Type I,Grade B or C abrasive mats.

5.9.1.2.1 SAE AMS-1640 (MIL-C-38334, Type I) Cor-rosion Removing Compound for Aircraft Surfaces.

SAE AMS-1640 (MIL-C-38334, Type I) andSemco® PN Pasa-Jell 102 are moderately toxicand MIL-DTL-81706, Class 1A is highly toxic toskin, eyes, and respiratory tract. Chemical orsplash proof goggles and/or face shields, andchemical resistant rubber gloves, and aprons arerequired. Good general ventilation is normallyadequate.

This material is a liquid concentrate material which shall bemixed with an equal volume of tap water before use; furtherdilution renders it ineffective. This material has a shelf life ofone year from the date of manufacture; discard any of thematerial which has reached or exceeded its shelf life. SAEAMS-1640 (MIL-C-38334, Type I) is used as a generalchemical corrosion remover to remove surface and pittingcorrosion products from aluminum alloy surfaces. It is notLiquid Oxygen (LOX) compatible.

5.9.1.2.1.1 Application and Use. The procedure forapplication and use of SAE AMS-1640 (MIL-C-38334, TypeI) materials is as follows:

a. After mixing properly, apply the solution by eitherflowing, mopping, sponging, brushing, wiping, or spray-ing with a non-atomizing sprayer onto the surface beingworked. For large areas, begin the application at thelowest point and work upward while using a circularmotion to apply the solution to ensure proper coverageand to disturb the oxide film on the surface.

b. Allow the solution to dwell on the surface for 11 to 12minutes while vigorously agitating it on the surface atleast every 2 minutes with a non-metallic, acid resistant,bristle brush or an A-A-58054, Type I, Grade B or Cabrasive mat. Then rinse the surface thoroughly withfresh water heated to a temperature of +120° to +140° F(+49° to +60° C). The solution is much more effective ifit is also heated to a temperature of +120° to +140° F(+49° to +60° C) and applied while warm. For severepitting, removal may be aided by lightly agitating thepits by hand with a stainless steel (CRES) wire bristlebrush with wire bristles having a maximum diameterbetween 0.005 and 0.006 inch (5-6 mils). Areas with

TO 1-1-691

Change 1 5-19

moderate to heavy surface or pitting corrosion mayrequire additional applications.

c. After each solution application and rinse, examine thearea being worked, aided with a 10X magnifier forpitting, to determine if all corrosion products have beenremoved. If not, repeat this process a maximum of threemore times. If corrosion products remain after the fourthapplication of this chemical remover, use an appropriatemechanical method described in this Chapter to removethe remaining corrosion products.

NOTE

(MIL-DTL-81706)/MIL-DTL-5541, Class 1Achemical chromate conversion coating shall beapplied immediately after the final rinse whencorrosion removal is the last process of a reworkoperation, or when the item or area will bepainted.

Table 5-5. Typical Chemical Corrosion Removal Procedures For Aluminum Alloy Parts and Assemblies

Type of CorrosionStep 1

Corrosion Removal

Step 2Surface Treatment (When ap-

plicable)

Step 3Final Protective Paint

Finish (When applicable)

Light or heavy pitting oretching of aluminum al-loys (clad)

Remove corrosion withSAE AMS-1640 (MIL-C-38334, Type I) per Para-graph 5.9.1.2.1.

MIL-DTL-81706/MIL-DTL-5541, Class 1A per SectionII of this chapter.

See TO 1-1-8 and air-craft, missile, or equip-ment system specificmaintenance manualsfor paint system

Light or heavy pitting oretching of aluminum al-loys (non-clad)

Remove corrosion withSAE AMS-1640 (MIL-C-38334, Type I) perParagraph 5.9.1.2.1 fol-lowed by appropriate me-chanical methods in thischapter if necessary.

As above As above

Intergranular or exfoliationcorrosion of aluminumalloys

Not applicable. Removecorrosion by appropriatemechanical methods inthis chapter.

As above As above

Light or heavy pitting oretching on small alumi-num alloy parts whichcan be removed for treat-ment

Remove corrosion and/oroxide film by immersionin a SAE AMS-1640(MIL-C-38334, Type I)prepared per Paragraph5.9.1.2.1.

Immersion in MIL-DTL-81706, Class 1A solutionper Section II of this chap-ter.

As above

Stress corrosion cracking ofaluminum

Not applicable; replace/re-pair as required in thestructural handbook

See step 1 See step 1

5.9.1.2.2 Semco® PN Pasa-Jell 102. This material isa gel type chemical corrosion remover for use on aluminumalloys in limited areas, in particular where LOX compatibilityis required, to remove pitting and surface corrosion oretching/oxidation. Pasa-Jell 102 is a relatively strong acidmixture that can be detrimental to equipment or componentsif improperly used. Therefore, it shall be used only in small

areas, and primarily where LOX compatibility is an essentialrequirement. Personnel must be properly trained and qualifiedto use this material for corrosion removal.

5.9.1.2.2.1 Application and Use.

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Do not use aluminum or any type of steel wool toapply or agitate Semco® PN Pasa-Jell 102 or firewill result.

Excessive use of abrasive materials and Semco®PN Pasa-Jell 102 can cause removal of protectivecladding (Alclad) and/or excessive metalremoval.

The procedure for application and use of Semco® PNPasa-Jell 102 material is as follows:

a. Apply Pasa-Jell 102 with an acid brush. Agitate areas ofdeep pitting with an acid brush that has the bristlesshortened by cutting off half their length or an A-A-58054, Type I, Grade A or B abrasive mat until corrosionproducts are removed. A thin, evenly dispersed filmgives the best results. Keep the dwell time to theminimum necessary to effectively remove the corrosionproducts (5 to 12 minutes). Usually, dwell time can becontrolled by closely observing the reaction of thePasa-Jell 102 mixture with the aluminum surface towhich it is applied to determine when all corrosionproducts have been lifted from the surface.

b. After all the corrosion products have been freed fromthe surface or the maximum 12 minutes dwell time isreached, whichever is first, wipe off the Pasa-Jell 102and other residue with a clean, moist cloth followed byrinsing with a stream of fresh tap water applied with awash bottle or continue to wipe with a clean, moistcloth, frequently rinsed in fresh tap water.

c. Inspect the area being worked to determine if allcorrosion has been removed giving particular attentionto pitted areas. Use a 10X magnifier to aid in examina-tion of questionable areas. Remaining corrosion willappear as a powdery crust, slightly different in colorthan the uncorroded base metal. One application ofPasa-Jell 102 is usually sufficient in most cases. How-ever, in severe cases, the preceding steps may have to berepeated.

5.9.1.2.3 MIL-DTL-81706, Class 1A Chemical Chro-mate Conversion Coating Solutions. Limited area cor-rosion removal from aluminum alloy surfaces while simulta-neously applying a chemical chromate conversion coatingcan be accomplished by using a MIL-DTL-81706, Class 1Asolution in conjunction with an A-A-58054, Type I, Grade Cabrasive mat. This material helps to clean an area byoxidizing all organic soils on the aluminum alloy surface,while the abrasive mat acts to remove the corrosion products,and then the solution forms a chemical chromate conversioncoating film on the aluminum alloy surface. If organic soilsare present, they will turn green upon application of the

solution. The green residue and the solution contaminatedwith the residue should be wiped from the surface anddiscarded. Mix the MIL-DTL-81706, Class 1A solution inaccordance with the manufacturer’s instructions and SectionII of this chapter. It is recommended that the technicianpractice on some condemned components or parts prior tousing this material on serviceable aircraft, missile, or equip-ment aluminum alloy parts.

5.9.1.2.3.1 Application of MIL-DTL-81706, Class 1ASolutions for Corrosion Removal.

MIL-DTL-81706, Class 1A chemical chromateconversion coating solutions are moderately toxicto the skin, eyes, and respiratory tract. Chemicalor splash proof goggles and chemical resistantrubber gloves are required. Good general venti-lation is normally adequate.

MIL-DTL-81706, Class 1A solutions shall not beused on high strength steels (180 KSI or higher),due to the potential of hydrogen embrittlement.Also, they shall not be used on magnesium,titanium, or cadmium or zinc plated parts/sur-faces as they will damage and/or corrode thesemetals.

The procedures for application of these materials for corro-sion removal are the same as those cited in Section II of thischapter for the standard chemical chromate conversion coat-ing solutions, except as follows:

a. The small area requiring corrosion removal and surfacetreatment can be cleaned with the chemical chromateconversion coating solution instead of cleaning, rinsing,and drying per Chapter 3 before application of thesolution.

b. Thoroughly wet or flood the area being worked with thesolution and keep it wet with solution until all phases ofthe process are completed and the final film is formed toprevent streaking and/or powdering on the surface.

c. Lightly abrade the surface while wet with the solutionusing a A-A-58054, Type I, Grade C abrasive mat.

d. If the solution turns green, continue to abrade the entirearea until it is completely cleaned, and then wipe alldirty solution from the surface with a sponge, whichshould leave a bright, shiny surface. If dark spots orlines are seen in the area which indicates the presence ofresidual spots of moderate to severe corrosion, reapplythe solution and vigorously agitate the wetted area withan abrasive mat as before. If the corrosion is notcompletely removed after this second application of

TO 1-1-691

Change 1 5-21

solution, remove the remaining corrosion using anappropriate mechanical method in this chapter. Aftercorrosion removal is complete and the dirty solution isremoved, reapply MIL-DTL-81706, Class 1A to form aMIL-DTL-5541, Class 1A film on the surface and allowthe film to form in accordance with procedures inSection II of this chapter for application of chemicalchromate conversion coatings to aluminum alloy sur-faces.

5.9.1.3 Application of Organic Coatings. Reapply theorganic coating system specified in the appropriate systemspecific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3 forSupport Equipment (SE) using TO 1-1-8 for applicationprocedures. Apply a MIL-DTL-5541, Class 1A chemicalchromate conversion coating using materials conforming toMIL-DTL-81706, Class 1A, if not already done, per SectionII of this chapter; and paint within 48 hours after applicationof the conversion coating. Reapply the conversion coating inaccordance with Section II of this chapter if more than 48hours have elapsed since application of a conversion coating.

5.9.2 Magnesium Alloys. These paragraphs outlinechemical corrosion removal procedures for the removal ofcorrosion from magnesium alloy parts and assemblies ofaircraft, missiles, or other equipment. Table 5-6 providesprocedures for the removal of specific types of corrosion.Removable parts can be treated more effectively by applyingone of the electrodeposition conversion coatings, such asType IV or VII, of SAE AMS-M-3171 (MIL-M-3171) aftercorrosion removal instead of the brush on Type VI coatingspecified for coating repair after corrosion removal fromsmall areas discussed here.

5.9.2.1 Preparation. Before starting chemical removalof corrosion products, remove paint from the area per TO1-1-8 and clean all grease, oil, and other contamination fromsurfaces to be worked in accordance with Chapter 3 ifimmersion, spray, or vapor blast cleaning is not practical. Ifpractical, use one of the procedures for cleaning magnesiumalloys by immersion, spray, or vapor blast included in SAEMS-M-3171 (MIL-M-3171).

5.9.2.2 Chemical Corrosion Removal Materials forMagnesium Alloys. Chromic acid pickle solution which isa mixture of A-A-55827 chromic acid in water may be usedto remove surface oxidation and light corrosion from mag-nesium alloy surfaces. It is not adequate for removal of deeppitting, heavy corrosion, sand or other blast media residue, orthe effects of blasting which will require use of one of themechanical methods described in this chapter. If properlyused, this chemical method removes much less metal causingmuch less reduction of sectional thickness than mechanicalmethods, but it shall not be used on parts containing copperor steel inserts unless they are completely masked off. Do notallow excessive amounts of anions such as chlorides, sulfates,

or fluorides to build up in the solution; they tend to coat oretch the metal surface rather than removing corrosion prod-ucts. Do not reuse old solutions; prepare fresh solutions foreach separate removal operation.

5.9.2.2.1 Application and Use.

• Do not allow rags, brushes, abrasive mats, orany other item soaked with A-A-55827 chro-mic acid or the chromic acid pickle solutionprepared with it to come in contact with anyorganic solvent (MEK, acetone, paint thinner,A-A-59601/MIL-PRF-680 dry cleaning sol-vent, etc.) or fire will result.

• A-A-55827 chromic acid and the chromic acidpickle solution prepared with it are highlytoxic to the skin, eyes, and respiratory tract.Chemical splash proof goggles and/or faceshield, chemical resistant rubber gloves andapron are required. Good general ventilation isusually adequate. In case of eye or skincontact, flush with water immediately andreport to the base medical facility.

The procedure for application and use of chrome picklesolution, a mixture of A-A-55827 chromic acid in water, is asfollows:

a. Mix 24 ounces of A-A-55827 chromium trioxide inenough water to make one gallon for each gallon ofsolution being prepared in a container fabricated fromlead lined steel (any alloy), stainless steel (any CRESalloy), or 1100 aluminum alloy. For depot level opera-tions only, a removable part that is being treated can becompletely immersed in the solution with an immersiontime ranging from one to 15 minutes at an operatingtemperature ranging from 190° to 202° F (88° to 94° C).For hand application with the solution at room tempera-ture, the dwell time for the solution on the surface is 15minutes minimum to 30 minutes maximum. Steps bthrough d are for hand application. Steps e through gapply to both the immersion and hand applicationmethods.

b. Mask off the surrounding areas, in particular to includeall nearby operating mechanisms, joints, crevices, cop-per and/or steel inserts, and plated steel to keep thesolution from attacking them.

c. Apply the chromic acid pickle solution carefully to thecorroded area with an A-A-289 acid brush.

d. Allow the solution to remain on the surface for approxi-mately 15 minutes for a solution at room temperature.

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Agitate the area with an A-A-289 acid brush having halfthe bristle length cut off or an A-A-58054, Type I, GradeB or C abrasive mat.

e. Thoroughly rinse the solution from the surface withplenty of fresh tap water.

f. Repeat the preceding sequence as necessary until allcorrosion products have been removed and the metal isa bright metallic color.

g. Apply a SAE AMS-M-3171 (MIL-M-3171), Type VIchromic acid brush-on pretreatment coating to the areafrom which corrosion was removed in accordance withprocedures in Section II of this chapter for application ofa brush-on chromic acid pretreatment coating to mag-

nesium alloy surfaces. If desired, parts that were treatedby complete immersion may receive one of the othercoatings listed in SAE AMS-M-3171 (MIL-M-3171) fordepot level operations.

5.9.2.3 Application of Organic Coatings. Reapply theorganic coating system specified in the appropriate systemspecific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3 forsupport equipment (SE) using TO 1-1-8 for applicationprocedures. Apply the paint within 48 hours after applicationof the pretreatment coating. Reapply the pretreatment coatingin accordance with Section II of this chapter if more than 48hours have elapsed since application of the pretreatmentcoating.

Table 5-6. Typical Chemical Corrosion Removal Procedures for Magnesium Alloys

Type of Corrosion Step 1Corrosion Removal

Step 2Surface Treatment

Step 3Protective Finish

Light pitting or sur-face oxidation/etch-ing

Remove corrosion with chro-mic acid pickle solutionper Paragraph 5.9.2.2

SAE AMS-M-3171 (MIL-M-3171),Type VI per Section II of this chapter

Approved paint sys-tem per Paragraph5.9.2.3

Heavy pitting or etch-ing

Not applicable. Remove cor-rosion by an appropriatemechanical method in thischapter.

As above As above

Intergranular or exfo-liation

Not applicable. Remove cor-rosion by an appropriatemechanical method in thischapter.

As above As above

Light or heavy corro-sion on small partswhich can be re-moved for treatment

Remove corrosion in accor-dance with SAE AMS-M-3171 (MIL-M-3171)

As above As above

Stress corrosioncracking

Not applicable. Replace orrepair as required in thesystem specific structuralhandbook.

Not applicable Not applicable

5.9.3 Ferrous Metal (Steel) Alloys Other Than Stain-less Steels (Cres). These paragraphs outline chemicalcorrosion removal procedures for treating ferrous metal alloyparts and assemblies of aircraft, missiles, and other equip-ment. Use of chemical corrosion removers on steels isrecommended only for areas where there is no danger ofentrapping the chemicals in crevices and/or recesses. Table5-7 provides procedures for the removal of specific types ofcorrosion.

5.9.3.1 Preparation. Before starting chemical removalof corrosion products, remove paint from the area per TO1-1-8 and clean all heavy deposits of grease, oil, and othercontaminants from the surfaces to be worked in accordancewith Chapter 3.

5.9.3.2 Chemical Corrosion Removing Materials forFerrous Metal Alloys Other Than Stainless Steels(CRES). Chemical corrosion/rust removers for steels areof two types; the MIL-C-10578 acid type and the A-A-59260(MIL-C-14460) alkaline type.

5.9.3.2.1 MIL-C-10578 Corrosion Removing andMetal Conditioning Compound (Phosphoric AcidBase). MIL-C-10578 covers six separate types of phos-phoric acid based corrosion/rust removing compounds usedto remove corrosion/rust from ferrous metal surfaces. Thefollowing types are available:

TO 1-1-691

Change 1 5-23

5.9.3.2.1.1 Type I (Wash-Off) and II (Wipe-Off). TypeI and II materials are suitable as rust removers for ferrousalloy metal parts. They may also be used as metal condition-ers for ferrous and nonferrous (zinc galvanized, cadmium,brass, and relatively pure aluminum or alclad) metals prior tothe primer and paint application and/or as a corrosionpreventive to provide minor corrosion protection to thesemetals in an unpainted condition. Remove very heavy rustincrustations using an appropriate mechanical method listedin this chapter and heavy grease, oil, and other contaminationper Chapter 3 as directed by Paragraph 5.9.3.1 beforeapplication of these materials. Type I is a little more efficientin removing rust and grease than Type II. Type I materials areapplied by either spray, dip, flow-on, brush, rag, or spongeand are always rinsed off with water, preferably hot. Type IImaterials are applied by either brush, rag, or sponge and donot have to be rinsed off with water, but are wiped off withclean, damp rags followed by wiping with clean, dry ragsprior to painting. Type II materials leave a light, gray-whitecoating/film on the surface that acts as a pretreatment forpainting.

5.9.3.2.1.2 Type III (Inhibited). Type III materials areintended for corrosion/rust removal from chromium platedferrous alloy surfaces and those bare ferrous alloy surfacesrequiring very close dimensional tolerances. Remove veryheavy rust incrustations by an appropriate mechanical methodin this chapter, and heavy grease, oil, and contamination perChapter 3 as directed by Paragraph 5.9.3.1 or by vapordegreasing before application of these materials. Type IIImaterials are applied by either spray, dip, flow-on, brush or byfull immersion in a tank containing the material. Parts are leftin the solution tank or the solution is left on the surface of thepart until the rust is dissolved or loosened sufficiently topermit easy removal, and then the residue is rinsed off thesurface with fresh, tap water, preferably hot, and the part isdried. It is then ready for application of the required corrosionpreventive treatment or paint system application.

5.9.3.2.1.3 Type IV (Nonfoaming). Type IV materialsare very similar to Type I, except that nonfoaming detergentsare included in the mixture. It is intended for use inpressurized spray systems at temperatures up to 150° F (66°C) maximum, after which it is rinsed off with fresh, tap water.

5.9.3.2.1.4 Type V (Immersion Tank). Type V materi-als are also very similar to Type I, except no grease removingsolvents are used in these materials, so they are only suitablefor use on surfaces from which all grease, oil, and contami-nation have been completely removed by cleaning per Chap-ter 3 as directed by Paragraph 5.9.3.1. It is intended for use inimmersion tanks either at ambient temperatures or at tem-peratures up to 140° F (60° C) maximum.

5.9.3.2.1.5 Type VI (Brush, Spray, or Dip). Type VImaterials are surface pretreatments and/or rust converters forapplication on either newly sand blasted or corroded/rusty

steel surfaces by spray, brush, or dipping. All old grease, oil,and dirt must be removed as well as all loose and scaly rustbefore applying these materials. After application, they areallowed to dwell on the surface for a minimum of six hoursto form a pretreatment coating on uncorroded ferrous alloysor to convert the rust on a corroded ferrous surface to aprotective, pretreatment film. After a dwell time of six hours,the excess materials are rinsed off, the surface is allowed toair dry, and then the surface can be primed and painted ortreated with a CPC.

5.9.3.2.2 Application and Use of MIL-C-10578 Corro-sion Removing Compounds.

• Phosphoric acid corrosion removal com-pounds are toxic to the skin, eyes, and respi-ratory tract. Chemical splash proof gogglesand rubber gloves and aprons are required.Use only in a well ventilated area. In case ofeye or skin contact, flush immediately withwater and report to the Base Medical Facility.

• When mixing, always add the phosphoric acidcorrosion remover to the water. Do not add thewater to the acid, since this causes excessiveheat to be generated.

• High strength steel parts, those heat-treatedabove Rockwell C40 (180,000 PSI) tensilestrength, are subject to hydrogen embrittle-ment when exposed to acids, therefore, use ofacid rust/corrosion removers on these parts isprohibited.

• Do not use acidic rust/corrosion removers ifthere is a danger of entrapping the materials increvices or recesses, as they can cause corro-sion in these areas.

5.9.3.2.2.1 Application and Use of Type I (Wash-Off). The directions for application and use of thesematerials are as follows:

a. Add one part of the concentrated material as received tothree parts of water by volume. Use either a stainlesssteel, aluminum, vinyl, polyethylene, or rubber mixingcontainer.

b. Remove heavy grease, oil, and contamination per Chap-ter 3 and heavy rust using an appropriate mechanicalmethod in this chapter before applying the chemicalremoval compound.

TO 1-1-691

5-24

c. Protect adjacent components by masking to preventdamage by scale, chips, corrosion products, or chemi-cals.

d. Apply the solution to the surfaces to be treated by eithernon-atomized spray, dip, flow-on, or brush. Allow thematerial to remain only long enough to wet the surfaceand cause etching. On rusted surfaces, allow the solutionto dwell on the surface long enough to loosen the rust (2to 10 minutes, depending on the degree of rusting) whileagitating the surface with an A-A-58054, Type I, GradeC abrasive mat or a hand held stainless steel (CRES)brush.

e. Rinse the surface with fresh, tap water, preferably hot(120° - 140° F/ 49° - 60° C). Allow the surface to drythoroughly prior to application of a rust/CPC or arequired paint system.

5.9.3.2.2.2 Application and Use of Type II (Wipe-Off). The directions for application and use of thesematerials are as follows:

a. Add one part of the concentrated material as received tothree parts of water by volume. Use the same type ofmixing containers specified in Paragraph 5.9.2.2.1 , stepa.

b. Remove heavy grease, oil, and contamination per Chap-ter 3 and heavy rust using an appropriate mechanicalmethod in this chapter before applying the chemicalremoval compound.


d. Apply the solution to the surfaces to be treated by eitherbrush, rag, or sponge. Allow the compound to dwell onthe surface for about 30 seconds.

e. Wipe off residue first with damp rags followed with dryrags leaving no more than a light gray-white coatingfilm on the surface. Allow the surface to dry thoroughlyprior to applying the required paint system.

5.9.3.2.2.3 Application and Use of Type III (Inhib-ited). The directions for application and use of thesematerials are as follows:

5.9.3.2.2.3.1 Follow these procedures for non-atomizedspray, flow-on, and brush applied operations with Type IIImaterials:

a. Add one part of the concentrated material as received toone part of water by volume. Use the same type ofmixing containers specified in Paragraph 5.9.2.2.1, stepa.

b. Remove grease, oil, and contamination per Chapter 3and heavy rust using an appropriate mechanical methodin this chapter prior to applying the chemical removalcompound.


d. Apply the solution to the surfaces to be treated bynon-atomized spray, flow-on, or brush. Allow the con-ditioner to dwell on the surfaces long enough to loosenand/or dissolve the rust, and then rinse off all residuewith fresh, hot, tap water (120° - 140° F/ 49° -60° C).

e. Allow the surface to thoroughly dry, and then eitherapply a CPC or a required paint system, or place the partdirectly into service, whichever is directed by the systemspecific maintenance technical data for the equipmentinvolved.

Heated dip tanks shall be properly ventilated, andventilation shall be evaluated by the Bioenviron-mental Engineer prior to initial use.

5.9.3.2.2.3.2 Follow these procedures for dip tank opera-tions with Type III materials:

a. Stainless steel (CRES) tanks are preferred for use withthis method. Mix the material as specified for non-atomized spray, flow-on, and brush applications, but mixit in the stainless steel (CRES) dip tank.

b. Immerse the part in the solution only long enough toloosen the rust. For heavy rust removal, the solution canbe heated to 140° F (60° C) maximum.

c. Agitate the part in the solution to increase the rustremoval rate. Rinse in a continuously over-flowingfresh, cold, tap water rinse tank, if available, or spraywith fresh, hot, tap water (120° - 140° F/49° - 60° C).Thoroughly dry the parts and immediately apply therequired paint system or CPC or place the part directlyinto service, whichever is directed by the system specificmaintenance technical data for the equipment involved.

5.9.3.2.2.4 Application and Use of Type IV (Non-Foaming). The directions for application and use of thesematerials are as follows:

a. Add one part of the concentrated material as received tothree parts of water by volume. Use the same type ofmixing containers as specified in Paragraph 5.9.3.2.2.1,step a.

b. Remove all heavy grease, oil, and contamination perChapter 3 and heavy rust using an appropriate mechani-cal method in this chapter prior to applying the chemicalremoval compound.

c. Apply the solution to the surface being treated bynon-atomized, pressurized spray. To increase the rust

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Change 1 5-25

removal rate, the solution may be heated up to atemperature of 150° F (66° C).

d. Rinse with fresh, tap water, preferably hot (120° - 140°F/ 49° - 60° C).

e. Allow the part to thoroughly dry prior to application ofa rust/CPC or a required paint system.

5.9.3.2.2.5 Application and Use of Type V (Immer-sion Tank). The directions for application and use of thesematerials are as follows:

a. Add one part of the concentrated material as received tothree parts of water by volume. Use the same type ofmixing containers as specified in Paragraph 5.9.3.2.2.1,step a, and pour the solution into a stainless steel(CRES) immersion tank, or mix the solution directly inthe immersion tank.

b. This material contains no solvents to assist in cleaning,so all heavy grease, oil, and contamination must bethoroughly removed per Chapter 3 or immersion in analkali bath prior to immersing a part in the corrosionremoval solution. Remove heavy rust with an appropri-ate mechanical method in this chapter also prior toimmersion of the part in the chemical removal com-pound.

c. Submerge the part being treated in the chemical removalcompound just long enough to loosen the rust. Forheavy rust removal, the solution can be heated to atemperature of 140° F (60° C).

d. After immersion, rinse all metal surfaces thoroughlywith fresh, tap water, or immerse the part in an alkalisolution followed by rinsing with fresh, tap water.

e. Allow the part to thoroughly dry prior to applying aCPC or a required paint system.

5.9.3.2.2.6 Application and Use of Type VI (Brush,Spray, or Dip). The directions for application and use ofthese materials are as follows:

a. Add one part of the concentrated material as received tothree parts of water by volume. Use the same type ofmixing containers specified in Paragraph 5.9.2.2.1, stepa. This material is also available mixed in a pen typeapplicator for direct application to the surface.

b. Remove all heavy grease, oil, and contamination perChapter 3 and heavy rust using an appropriate mechani-cal method in this chapter prior to applying the chemicalremoval compound.

c. Apply the solution to the surface being treated by brush,any sprayer that will accommodate acid solutions,dipping the part in the solution, or with the penapplicator.

d. Allow the material to dwell on the surface and react withthe metal and convert the rust to a protective film for

6-24 hours for brush and spray applications. For dipapplications, allow the part to remain in the solution for1-5 hours, and then remove it from the solution, andallow the material to dwell on the part surfaces for anadditional 6-24 hours.

e. After the dwell time is completed, rinse all excess/unreacted material off all part surfaces with fresh,running, tap water for at least 30 seconds.

f. Allow the part to thoroughly dry prior to applying aCPC or a required paint system.

5.9.3.2.3 A-A-59260 (MIL-C-14460, Type I) CorrosionRemoving Compound, Sodium Hydroxide Base; forElectrolytic or Immersion Application. This is a highlyalkaline chemical corrosion/rust removing compound suitablefor rust removal by immersion of the parts in the solution. Itdoesn’t cause dimensional change of critical or machinedsurfaces, and it is safe to use on high strength steels as it willnot cause hydrogen embrittlement. It can be used on smallparts with or without paint, grease, or other surface coatings.

5.9.3.2.4 Application and Use of A-A-59260 (MIL-C-14460, Type I) Corrosion Removing Compounds. Thedirections for application and use of these materials are asfollows:

• A-A-59260 (MIL-C-14460, Type 1) corrosion/rust removing compound is a sodium hydrox-ide solution and therefore, highly alkaline. It istoxic to the skin, eyes, and respiratory tract.Chemical splash proof goggles and/or faceshields and chemical resistant rubber glovesand aprons are required. Heated dip tanks shallbe properly ventilated, and ventilation shall beevaluated by the Bioenvironmental Engineerprior to their initial use.

• When preparing/mixing this highly alkalinesolution, never pour water onto the sodiumhydroxide granules or flakes; this will generatean excessive amount of heat. Always pour thesodium hydroxide granules/flakes into thewater.

a. Prepare/mix this alkaline corrosion/rust remover solu-tion per the manufacturer’s instructions printed on thecontainer to obtain a solution concentration of fivepounds of sodium hydroxide granules or flakes pergallon of water. Use either carbon steel or stainless steel(CRES) tanks to contain the solution.

b. Immerse the parts in the corrosion/rust remover solu-tion. Rust removal time varies with the extent of therust. At room temperature, rust removal is very slow,and a long soak time is required. This solution is mosteffective if the temperatures of the solution is brought up

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to the point of a rolling boil which increases the rate ofthe corrosion/rust removal significantly.

c. Rinse the parts thoroughly in fresh, tap water (preferablyhot- 120°-140° F/ 49°-60° C).

d. Dry the parts thoroughly, and immediately apply a CPCor a required paint system.

5.9.3.3 Application of Organic Coatings. Reapply theorganic coating system specified in the appropriate system

specific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3 forsupport equipment (SE) using TO 1-1-8 for applicationprocedures. Apply the paint system, when required within 4hours after completion of the corrosion removal procedure toprevent surface rusting from occurring. As a minimum, aprimer should be applied within this time frame.

Table 5-7. Typical Chemical Corrosion Removal Procedures for Ferrous Metals Other Than Stainless Steel(CRES)

Type of Corrosion Corrosion Removal

Light or heavy rust on installed parts where chemicalrust removal is practical

Remove very heavy corrosion by wire brushing, sanding,or other appropriate mechanical method in this chapterfollowed by phosphoric acid etch with MIL-C-10578,Type I, II, IV, or VI materials (refer to Paragraph5.9.3.2.2.1, Paragraph 5.9.3.2.2.2, Paragraph 5.9.3.2.2.4,and Paragraph 5.9.3.2.2.6). Do not use phosphoric acidetch on high strength steel.

Light or heavy rust on small parts where vat treatmentis practical

a. Acid Method: Remove corrosion by immersing parts inMIL-C-10578, Type III, V, or VI phosphoric acid solu-tion (refer to Paragraph 5.9.3.2.2.3, Paragraph5.9.3.2.2.5, and Paragraph 5.9.3.2.2.6). Do not usephosphoric acid on high strength steel.

Alkaline Method (recommended for critical or mechanicalsurfaces): Remove corrosion by immersing parts inA-A-59260 (MIL-C-14460, Type I) alkaline solution(refer to Paragraph 5.9.3.2.4)

5.9.4 Stainless Steel (Cres) And Nickel Based Al-loys. These paragraphs outline chemical corrosion removalprocedures for stainless steel (CRES) and nickel based alloyparts and assemblies. Table 5-8 provides procedures forremoving specific types of corrosion. Chemical corrosionremoval is recommended for severely corroded areas onlywhen there is no danger of entrapping chemicals in recesses,cavities, or joint areas or damaging surrounding metals andplating. Use these chemical procedures on installed compo-nents which are not readily removable. When internal corro-

sion is evident, affected components shall be removed andprocessed through an overhaul facility in accordance withsystem specific maintenance manuals for the specific aircraft,missile, or piece of equipment.

5.9.4.1 Preparation. If the corroded area is contami-nated with grease, oil, dirt, or any other foreign material,clean the area per Chapter 3.

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Change 1 5-27

a. Protect adjacent unaffected areas not being treated bymasking to prevent damaging them with the chemicalsused.

• A-A-59601 and MIL-PRF-680, Types II andIII dry cleaning and degreasing solvents aretoxic to the skin, eyes, and respiratory tract.Skin and eye protection are required. Avoidrepeated or prolonged skin contact or inhala-tion. Good general ventilation is normallyadequate.

• When using metallic wools, wear leathergloves and exercise care to prevent injury tohands and fingers.

• Take care to prevent solvents from splashingor running because they can damage paintsand elastomers (e.g., rubbers, plastics).

• Take care to protect surrounding unaffectedareas next to the area being treated by prevent-ing leakage of chemicals into recesses orinaccessible areas in the structure which cancause additional damage from corrosionattack.

b. Remove all loose corrosion by abrading the surface witheither A-A-1043, Type IV, Class 1 stainless steel wool,240 grit ANSI B74.18 (A-A-1047) silicon carbide abra-sive paper or ANSI B74.18 (A-A-1200) silicon carbideabrasive cloth, 240 grit ANSI B74.18 (A-A-1048) alu-minum oxide abrasive paper or cloth, or A-A-58054,Type I, Grade C abrasive mat. Remove all looseparticles by wiping the surface with a clean clothdampened with A-A-59601 or MIL-PRF-680, Type II orIII dry cleaning and degreasing solvent.

5.9.4.2 Chemical Corrosion Removing Materials forStainless Steel (CRES) and Nickel Based Alloys.There are three types of chemicals used for corrosion removalfrom stainless steels (CRES) and nickel based alloys:Semco® PN Pasa-Jell 101 mineral acid, gel type material;MIL-C-10578, Type III -inhibited phosphoric acid basedsolution; and acid pickling solutions consisting of a mixtureof A-A-59105 (O-N-350) nitric acid, MIL-A-24641 hydrof-luoric acid, and water.

5.9.4.2.1 Semco® PN Pasa-Jell 101. This is a min-eral acid, gel type material used for chemical corrosionremoval from assembled aircraft, missile, and equipmentstructures in areas involving LOX storage and gaseousoxygen transfer systems and other areas where a gel typematerial is necessary and/or preferred.

5.9.4.2.1.1 Application and Use of Semco® PNPasa-Jell 101.

• Do not use aluminum or steel wool to agitateSemco® PN Pasa-Jell 101, as a combustiblereaction will occur.

• Semco® PN Pasa-Jell 101 contains strongacids and is toxic to the skin, eyes, andrespiratory tract. Chemical splash proofgoggles and/or face shield and chemical resis-tant rubber gloves and aprons are required.Avoid inhaling fumes, and use only in a wellventilated area.

The directions for the application and use of this material areas follows:

a. Prepare the area per the procedures outlined in Para-graph 5.9.4.1.

b. Apply the Semco® PN Pasa-Jell 101 material to the areabeing worked with an acid brush and in accordance withthe manufacturer’s instructions.

c. To remove light to medium corrosion, agitate the areawith an acid brush having half the bristle length cut off,if necessary. To remove heavy corrosion where pitting ispresent, agitate the area with an A-A-58054, Type I,Grade C abrasive mat until all corrosion embedded inpits and on the surface is removed. Allow the material todwell on the surface only long enough to loosen and/ordislodge all the corrosion products.

d. Remove the Semco® PN Pasa-Jell 101 material andcorrosion products from the surface with a clean,lint-free cloth frequently rinsed in fresh, tap water.

e. For a final wipe, use a clean, lint-free dry cloth. Afterdrying, either apply a CPC or a required paint system, orplace the part directly into service, whatever is directedby the system specific maintenance technical data forthe equipment involved. Usually, stainless steel (CRES)and nickel based alloy parts do not require painting.

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5-28 Change 1

5.9.4.2.2 MIL-C-10578, Type III Corrosion Removingand Metal Conditioning Compound (Phosphoric AcidBase)/Inhibited. This is a phosphoric acid based materialthat can be used to remove corrosion from assembled aircraft,missile, and equipment structures in areas that do not containoxygen systems and where a liquid material is acceptable.

5.9.4.2.2.1 Application and Use of MIL-C-10578,Type III. The directions for the application and use of thismaterial are as follows:


b. Protect adjacent components by masking to preventdamage by scale, chips, corrosion products, or chemi-cals.

c. Add one part of the concentrated material as received toone part of water by volume. Use either a stainless steel,aluminum, vinyl, polyethylene, or rubber mixing con-tainer.

d. Apply the solution to the surfaces to be treated bynon-atomized spray, flow-on, or brush. Allow the con-ditioner to dwell on the surfaces long enough to loosenand/or dissolve the corrosion/rust, and then rinse off allresidue with fresh, hot, tap water (120° - 140° F/ 49°-60° C).

e. Allow the surface to thoroughly dry, and then eitherapply a CPC or a required paint system, or place the partdirectly into service, whatever is directed by the systemspecific maintenance technical data for the equipmentinvolved. Usually, stainless steel (CRES) and nickelbased alloy parts do not require painting.

Table 5-8. Typical Chemical Corrosion Removal Procedures for Stainless Steel (CRES) and Nickel Based Alloys

Type of CorrosionStep 1

Corrosion RemovalStep 2

Surface TreatmentStep 3

Protective Finish

Light to heavy corrosion/rustto include pitting on in-stalled parts where liquidchemical corrosion/rust re-moval is impractical becauseof location involving LOXstorage or gaseous oxygentransfer equipment, complex-ity of the structure, or rins-ing difficulties.

Remove very heavy corrosion/rust first with stainless steelwool or wire brush, rotary file,or other mechanical means inthis chapter followed by appli-cation of Semco® PN Pasa-Jell 101 (refer to Paragraph5.9.4.2.1.1).

None Normally not required (referto Paragraph 5.9.4.3) fordiscussion of paint systems)

As above, when liquid chemi-cal corrosion/rust removal ispractical.

Remove very heavy corrosion/rust as above first, followed byapplication of MIL-C-10578,Type III solution (refer toParagraph 5.9.4.2.2.1).

None As Above

Light to heavy corrosion toinclude pitting on partswhich can be removed forprocessing

Remove very heavy corrosion/rust as above first followed byimmersion in the nitric-hydrofluoric acid pickling so-lution (refer to Paragraph5.9.4.2.3.1).

Passivate in accor-dance with SAEAMS-QQ-P-35,Type II, VI,VII, or VIII asapplicable tothe type ofstainless steel(CRES) alloybeing treated

As Above

5.9.4.2.3 Acid Pickling for Corrosion Removal (FORDEPOT AND OTHER AUTHORIZED FACILITY USEONLY). Acid pickling solutions consisting of a mixture ofA-A-59105 (O-N-350) nitric acid, MIL-A-24641 hydrofluo-

ric acid, and water are used to remove corrosion/rust fromremoved stainless steel (CRES) and nickel based alloy partsthat can be immersed in the solution.

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Change 1 5-29

Scale loosening, pickling, and passivating solu-tions are all strong acids which are toxic to theskin, eyes, and respiratory tract. Chemical splashproof goggles and/or face shield and chemicalresistant rubber gloves and aprons are required.In case of eye or skin contact, flush immediatelywith water and report to the Base Medical Facil-ity. Avoid inhaling fumes, and provide adequateventilation. Solution tanks shall be properly ven-tilated with a lateral exhaust type ventilationsystem. The ventilation system and procedureshall be properly evaluated by the Bioenviron-mental Engineer prior to initial use.

• Heat-treatable stainless steel alloys, such asAISI types 403, 410, 420, and others, aresusceptible to cracking when placed in pick-ling solutions. Use only mechanical methodsto remove corrosion from these alloys.

• When preparing pickling solutions, never pourwater into the acids as excessive heat will begenerated. Always pour the acids into thewater.

• Rubber lined or Koroseal tanks shall be usedto hold these solutions because they are sohighly acidic.

a. Pickling Solution Concentration. Pickling solutions areprepared by mixing various amounts of A-A-59105(O-N-350) nitric acid and MIL-A-24641 hydrofluoricacid in water with the correct content of the two acidsfor a given corrosion removal job being determined bythe testing procedure outlined below. The nitric acidcontent may vary from 5 to 50% by volume, while thehydrofluoric acid content may vary from 0.5 to 5% byvolume. A solution of 12 to 15% nitric acid by volumeand 1% hydrofluoric acid by volume in water is nor-mally used to remove light scale and/or corrosion/rust.Increase the percentage of hydrofluoric acid within therange specified above to remove heavier scale and/orcorrosion/rust. As the amount of nitric acid increaseswith respect to the amount of hydrofluoric acid in thesolution, the rate of corrosion/rust and/or scale removaldecreases, because nitric acid inhibits the action ofhydrofluoric acid.

b. Pickling Solution Temperature. The temperature of thepickling solution may be adjusted from ambient/roomtemperature up to a maximum of 140o F (60o C). Highertemperatures shall be avoided to reduce evaporation lossof hydrofluoric acid. Use temperatures below 120o F

(49o C) if intergranular attack is experienced in local-ized areas, such as weld zones.

NOTE

AISI 300 series stainless steel (CRES) alloytubing may be used to manufacture steam coils toheat the solution. The heating coils should beinstalled so that they are easily replaced, sincethey will be corroded by the solution over time.

c. Testing for Optimum Pickling Conditions. Optimumpickling conditions (temperature, time, and acid concen-tration) shall be determined by exposing test panels tovarious combinations of these parameters and process-ing them through the entire cleaning and corrosionremoval/pickling cycle. Excessive etching and/or inter-granular attack of the base metal indicates conditions aretoo aggressive, and slow removal rates indicate condi-tions are not aggressive enough.

(1) Make four inch square test panels from the samematerial from which the parts that will be treated aremade. Process these test panels through the completecleaning and corrosion removal/pickling cycle.

(2) If etching or intergranular attack is excessive (i.e.,would cause the component to be condemned), or ifcorrosion removal is not complete, adjust the acidconcentration, immersion time, and/or solution tem-perature until the desired result is obtained. Table 5-9shows the effect that varying the parameters of acidconcentration, immersion time, and/or solution tem-perature has on the corrosion removal/pickling ac-tion of the solution.

5.9.4.2.3.1 Application and Use of Acid Pickling Solu-

tions for Corrosion Removal. The directions for theapplication and use of nitric acid-hydrofluoric acid solutionsfor corrosion removal are as follows:

a. Clean parts to be treated per procedures in Chapter 3.

b. If severe scale is present, remove it by one of thefollowing methods:

(1) Remove scale using an appropriate mechanicalmethod in this chapter, or

(2) Remove scale using this chemical method:

(a) Immerse parts in a solution of 8 to 10% byweight A-A-55828 (O-S-809) sulfuric acid andwater at a temperature of 150° to 160° F (66° to71° C) for about 5 minutes. If required, scrub thesurface of the parts with a stainless steel (CRES)wire brush to remove any sludge formed in thearea having severe scale.

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(b) Repeat the above process if required, and thenquickly rinse the parts thoroughly in fresh, hot,tap water at a temperature of 120° to 130° F (49°to 54° C).

c. c. Prepare the pickling solution by mixing the properproportions of A-A-59105 (O-N-350) nitric acid andMIL-A-24641 hydrofluoric acid in fresh, tap water. As astarting point, a typical pickling solution consists of15% nitric acid by volume and 2 to 3% hydrofluoric acidby volume in water. Make adjustments as determined byresults of the testing in Paragraph 5.9.4.2.3, step c.

d. Immerse parts in the typical pickling solution at atemperature of 60° to 140° F (16° to 60° C) for a periodof 5 to 15 minutes. Make adjustments to the solutiontemperature and immersion time as determined by theresults of the testing in Paragraph 5.9.4.2.3, step c. Ifrequired, scrub the surface of the parts with a stainlesssteel (CRES) wire brush to loosen and remove allcorrosion products.

NOTE

• Ensure that the parts are completely immersedin these solutions to prevent corrosive attackof the part at the liquid level line.

• New welds should be mechanically vibrated oragitated during the pickling operation.

e. Immediately after removing the parts from the picklingsolution, thoroughly rinse the parts with fresh, hot, tapwater at a temperature of 120° to 130° F (49° to 54° C).

5.9.4.3 Passivation of Stainless Steel (CRES) AlloyParts. After corrosion removal is completed on removedstainless steel (CRES) parts, passivate the surfaces of theseparts as follows:

a. Prepare a passivating solution in accordance with SAEAMS-QQ-P-35 either Type II, VI, VII, or VIII asapplicable to the stainless steel (CRES) alloy of the partto be passivated.

b. Immerse the part in the passivating solution held withinthe temperature range and for the time interval specifiedin SAE AMS-QQ-P-35.

c. Remove the parts from the passivating solution, andthoroughly rinse with fresh, hot, tap water at a tempera-ture of 120° to 130° F (49° to 54° C). As required bySAE AMS-QQ-P-35, immerse all ferritic and/or marten-sitic stainless steel (CRES) alloy parts in a 4 to 6% byweight solution of A-A-59123 (O-S-595) sodiumdichromate in water at a temperature of 140° to 160° F(60° to 71° C) for 30 minutes.

d. Remove the parts from the sodium dichromate solution.Rinse thoroughly with fresh tap water and dry. Place theparts directly in service or in the supply system unlesspainting is required by system specific technical data.

5.9.4.4 Application of Organic Coatings. Stainlesssteels (CRES) and nickel based alloys are normally notpainted. However, where extreme corrosive conditions areencountered, where organic finishes are required for decora-tive purposes, or where the stainless steel (CRES) or nickelbased alloy is in contact with a dissimilar anodic metal,painting may be required. Reapply the organic coating systemspecified in the appropriate system specific maintenancemanual and/or engineering drawing for the aircraft, missile,or piece of equipment and TO 35-1-3 for support equipment(SE) using TO 1-1-8 for application procedures.

5.9.5 Copper And Copper Based Alloys. These para-graphs outline chemical corrosion removal procedures forcopper and copper based alloy parts and assemblies ofaircraft, missiles, and equipment. Table 5-10 provides proce-dures for removing specific types of corrosion.

5.9.5.1 Preparation. If the corroded area is contami-nated with grease, oil, dirt, or other foreign materials, cleanthe area per Chapter 3. Protect adjacent components and areasnot being treated by masking to prevent damaging them withthe chemicals used.

5.9.5.2 Chemical Corrosion Removing Materials forCopper and Copper Based Alloys. There are two typesof chemical solutions used for corrosion removal from copperand copper based alloys provided there is no danger ofchemical entrapment in crevices and/or recesses: MIL-C-10578, Type III Corrosion Removing and Metal ConditioningCompound (Phosphoric Acid Base)/Inhibited solution andA-A-55828 (O-S-809) Sulfuric Acid solution.

Table 5-9. Control of Corrosion Removal/ Pickling Action of Nitric-Hydrofluoric Acid Solutions

Action Is More Aggressive Action Is Less Aggressive

1. When the nitric acid content is decreased and/or thehydrofluoric acid content is increased.

1. When the nitric acid content is increased and/or thehydrofluoric acid content is decreased.

2. When the temperature is increased. 2. When the temperature is decreased.3. When immersion time is increased. 3. When immersion time is decreased.

5.9.5.2.1 MIL-C-10578, Type III Corrosion Removingand Metal Conditioning Compound (Phosphoric Acid

Base)/Inhibited. This is a phosphoric acid based materialused to remove corrosion from assembled copper and/or

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Change 1 5-31

copper alloy aircraft, missile, and equipment structures inareas that do not contain oxygen systems and where a liquidmaterial is acceptable.

5.9.5.2.1.1 Application and Use of MIL-C-10578,Type III Solutions. The directions for the application anduse of this material are as follows:


b. Add one part of the concentrated material as received toone part of water by volume. Use either a stainless steel,aluminum, vinyl, polyethylene, or rubber mixing con-tainer.

c. Apply the solution to the surfaces to be treated bynon-atomized spray, flow-on, or brush. Allow the con-ditioner to dwell on the surfaces long enough to loosenand/or dissolve the corrosion and then rinse off allresidue with fresh, hot, tap water (120° - 140° F/ 49°-60° C).

d. Allow the surface to thoroughly dry, and then eitherapply a CPC or a required paint system, or place the partdirectly into service, whatever is directed by the systemspecific maintenance technical data for the equipmentinvolved.

5.9.5.2.2 A-A-55828 (O-S-809) Sulfuric Acid Solu-tions. Sulfuric acid solutions may be used to removecorrosion from copper and/or copper alloy components whichcan be disassembled and treated in immersion tanks. Thetanks must be either manufactured from or lined with eitherstainless steel (CRES), lead, ceramic, glass, or acid resistantrubber; and they must be provided with an adequate lateralexhaust ventilation system. Part holding racks must bemanufactured from either stainless steel (CRES) or Monel.The proper conditions (i.e., time, temperature, and acidconcentration) for the process shall be determined by thesame test procedure outlined in Paragraph 5.9.4.2.3, step c.using test panels made from the same material being treated.

5.9.5.2.2.1 Application and Use of A-A-55828 (O-S-809) Sulfuric Acid Solutions.

Sulfuric acid solutions are toxic to the skin, eyes,and respiratory tract. Chemical, splash proofgoggles and/or face shields and chemical resis-tant rubber gloves and aprons are required. Incase of eye or skin contact, flush immediatelywith fresh water and report to the Base MedicalFacility.

The directions for the application and use of this material areas follows:

a. Disassemble the components from which corrosion willbe removed to the piece part level as necessary.

b. Prepare parts per the procedures outlined in Paragraph5.9.5.1.

When preparing sulfuric acid solutions, neverpour water into the acid, as excessive heat will begenerated. Always pour the acid into the water.

c. Prepare a 5 to 10% by volume solution of A-A-55828(O-S-809) sulfuric acid in water and maintain thesolution temperature within a range of 60° to 120° F(16° to 49° C). As required by Paragraph 5.9.5.2.2,determine the actual operating solution concentrationand temperature within the ranges listed above andestablish the required part immersion time by testing perParagraph 5.9.4.2.3, step c.

Do not process components having assembleddissimilar metal parts or separate parts madefrom different metals in a sulfuric acid solution,as corrosion problems can result.

d. Immerse parts in the sulfuric acid solution prepared andmaintained at the solution concentration and tempera-ture per step c, for the immersion time established instep c.

e. Remove the parts from the acid solution, and immedi-ately rinse them thoroughly with fresh tap water.

NOTE

Thorough rinsing is important, since any residualacid will cause staining of the metal surface.

f. If a red stain appears on the parts following the abovetreatment, remove the stain by immersion of the parts ina solution of 4 to 10% by volume A-A-55828 (O-S-809)sulfuric acid and 4 to 8 ounces per gallon of solution ofA-A-59123 (O-S-595) sodium dichromate in watermaintained within a temperature range of 60° to 120° F(16° to 49° C).

TO 1-1-691

5-32 Change 1

Compressed air used for drying purposes cancause airborne particles that may enter the eyes.Eye protection is required. Air pressure shall notexceed 30 PSI.

g. Dry rapidly, preferably with hot air, to prevent waterstains on the surface, and then either apply a CPC or arequired paint system, or place the part directly intoservice, whatever is directed by the system specificmaintenance technical data for the equipment involved.

5.9.5.3 Application of Organic Coatings. Normallycopper and copper based alloys are not painted. If required,reapply the organic coating system specified in the systemspecific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3 forsupport equipment (SE) using TO 1-1-8 for applicationprocedures.

Table 5-10. Typical Chemical Corrosion Removal Procedures for Copper and Copper Alloys

Type of Corrosion Step 1Corrosion Removal

Step 2Surface Treatment

Step 3Protective Finish

Tarnish or colored corrosionproducts (patina) on in-stalled components when-ever chemical corrosion re-moval is practical

Remove corrosion withMIL-C-10578, Type IIIcorrosion removingcompound (phosphoricacid base)/inhibited(refer to Paragraph5.9.5.2.1.1.)

Not required Refer to Paragraph 5.9.5.2.1.1for specific instructions

Corrosion on parts which canbe disassembled for immer-sion treatment

Remove corrosion byimmersion in A-A-55828 (O-S-809) sulfu-ric acid solution (referto Paragraph5.9.5.2.1.1, steps a.through e.)

If required, removestain by immersionin A-A-55828 (O-S-809) sulfuric acidsolution and A-A-59123 (O-S-595)sodium dichromatesolution (refer toParagraph5.9.5.2.1.1, steps f.through h.)

As above

5.9.6 Titanium and Titanium Based Alloys. Theseparagraphs outline chemical corrosion removal proceduresfor titanium and titanium alloy parts and assemblies. Table5-11 provides procedures for removing specific types ofcorrosion.

5.9.6.1 Preparation. If the corroded area is contami-nated with grease, oil, dirt, or other foreign materials, cleanthe area per Chapter 3.

a. Protect adjacent unaffected areas not being treated bymasking to prevent damage from scale, chips, corrosionproducts, or chemicals.

b. If present, remove gray or black oxides by an appropri-ate mechanical method in this chapter.

5.9.6.2 Chemical Corrosion Removal Materials forTitanium and Titanium Based Alloys. There are twotypes of chemical solutions used for corrosion removal fromtitanium and titanium based alloys: an acid pickling solutionof A-A-59105(O-N-350), nitric acid and MIL-A-24641, hy-drofluoric acid in water; and an SAE AMS-1640 (MIL-C-38334) corrosion removing compound solution.

5.9.6.2.1 Acid Pickling Solutions.

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Change 1 5-33

• Nitric-acid-hydrofluoric acid pickling solu-tions are toxic to the skin, eyes, and respira-tory tract. Chemical, splash proof gogglesand/or face shields and chemical resistantrubber gloves and aprons are required. In caseof eye or skin contact, flush immediately withwater and report to the Base Medical Facility.Use only in a well ventilated area.

• When preparing sulfuric acid solutions, neverpour water into the acid, as excessive heat willbe generated. Always pour the acid into thewater.

Titanium is susceptible to hydrogen embrittle-ment in acid solutions. Therefore, acid picklingshall be used only when other corrosion methodsare not adequate. Competent operators must beassigned to monitor the process.

An acid pickling solution for removing corrosion fromremoved titanium and titanium alloy parts consists of amixture of 20% by volume, A-A-59105 (O-N-350), nitricacid and 3% by volume, MIL-A-24641, hydrofluoric acid inwater. This solution will remove most oxide coatings fromtitanium, provided the scale was formed at temperaturesbelow 1000° F (538° C) by immersing them in the solution.As noted in Paragraph 5.9.6.1, step b, gray or black oxideswhich form at temperatures above 1000° F (538° C) shouldbe removed by an appropriate mechanical method in thischapter, such as abrasive blasting, prior to the acid pickling toprevent pitting of the titanium.

5.9.6.2.1.1 Application and Use of Acid Pickling Solu-tions. The directions for the application and use of thesematerials are as follows:

a. Remove the components to be treated, and disassemblethem to the piece part level.

b. Prepare the parts per Paragraph 5.9.6.1.

c. Immerse the parts in the nitric acid - hydrofluoric acidpickling solution specified in Paragraph 5.9.6.2.1, whilemaintaining the solution at room temperature. Allow the

parts to remain in the solution only long enough toloosen and remove the oxide film from the surface.Intermittent scrubbing of the part surfaces with an acidbrush or wiping them with a cloth during this operationwill facilitate oxide film removal and minimize anypitting of the part surfaces.

NOTE

This process may be optimized by adjusting theacid concentration and immersion time as deter-mined by testing per Paragraph 5.9.4.2.3, step c.prior to starting the pickling operation

d. Remove the parts from the solution, and immediatelyrinse them thoroughly in fresh, running, tap water.Either air dry them at room temperature, or dry them ina circulating air oven at a temperature of 180° to 240° F(82° to 116° C).

e. If required by system specific technical data, apply anorganic coating system per Paragraph 5.9.6.3.

5.9.6.2.2 SAE AMS-1640 (MIL-C-38334) CorrosionRemoval Compound for Aircraft Surfaces. This is thesame material used to remove corrosion from aluminum alloysurfaces, and it may also be used to remove corrosion fromtitanium and titanium alloy assemblies and/or on equipmentsurfaces (refer to Paragraph 5.9.1.2.1).

5.9.6.2.2.1 Application and Use of SAE AMS-1640(MIL-C-38334). The procedure for application and use ofthis corrosion removal compound to remove corrosion prod-ucts/oxides from titanium and titanium alloy surfaces is thesame as it is for aluminum alloy surfaces (refer to Paragraph5.9.1.2.1.1).

5.9.6.3 Application of Organic Coatings. Titaniumand titanium alloys do not normally require a paint system forcorrosion protection. Where organic finishes are required fordecorative purposes, for continuity with the finish system onsurrounding surfaces, or to provide a barrier to preventcontact with a dissimilar anodic material, prepare the titaniumor titanium alloy surface for painting by applying a thixotro-pic MIL-DTL-81706/MIL-DTL-5541, Class 1A chemicalchromate conversion coating solution per Section II of thisChapter. Apply the organic finish system specified in theapplicable system specific aircraft, missile, or equipmentmaintenance manual and/or engineering drawing and TO35-1-3 for support equipment using TO 1-1-8 for applicationprocedures.

Table 5-11. Typical Chemical Corrosion Removal of Titanium and Titanium Base Alloys

Type of Corrosion Corrosion Removal Protective Finish

Light to heavy oxide on partswhere acid pickling is prac-tical on removed parts

(1) Remove gray or black oxide by an ap-propriate mechanical method in this chap-ter.

When required, refer to Paragraph5.9.6.3.

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5-34 Change 1

Table 5-11. Typical Chemical Corrosion Removal of Titanium and Titanium Base Alloys - Continued

Type of Corrosion Corrosion Removal Protective Finish

(2) Remove remaining oxide by immersionin nitric/hydrofluoric acid solution (referto Paragraph 5.9.6.2.1.1.

Light to heavy oxide on as-sembled parts and/or onequipment surfaces

(1) As in (1) above As above

(2) Remove remaining oxide by treatingwith SAE AMS-1640 (MIL-C-38334) so-lution (refer to Paragraph 5.9.6.2.2.1 andParagraph 5.9.1.2.1.1).

5.9.7 Plated And Phosphated Surfaces. These para-graphs outline chemical corrosion removal procedures forremoving corrosion from plated and phosphated surfaces.Table 5-12 provides guidelines for touch-up of corrodedareas, but where an organic finish on the plated part isspecified and/or required for engineering or other reasons, thetable can be used as a guide for treating the entire surface ofthe plated or phosphated parts. Chemical corrosion removalusing acid type chemical corrosion/rust removers is recom-mended for use where there is no danger of the chemicalsbecoming entrapped in crevices or recesses. They are in-tended for brush application following removal of heavycorrosion by an appropriate mechanical means in this chapterto remove the remaining red rust and other types of corrosionfrom the base metal and to condition the metal surface forbetter paint adhesion.

5.9.7.1 Preparation.

Many platings and their corrosion products, suchas copper, cadmium, and chromium are toxic.Take proper safety precautions to avoid inhala-tion or ingestion of residue created during corro-sion removal operations. Wash hands thoroughlybefore eating, drinking or smoking after remov-ing corrosion from plated surfaces.

If the corroded area is contaminated by grease, oil, dirt, orother foreign materials, clean the area per Chapter 3. Protectadjacent components and areas by masking to prevent dam-age from scale, chips, corrosion products, and the chemicalsused.

5.9.7.2 Treatment of Corroded Areas on Cadmium orZinc Plated Surfaces. Cadmium and zinc platings pro-vide anodic protection to underlying steel/ferrous (sometimes

copper) base metal. If the plating surface is broken duringnormal usage, the cadmium or zinc plate being anodic to thebase metal will corrode preferentially and sacrificially protectthe base metal. The removal of corrosion from cadmium orzinc plated surfaces shall be limited to the removal of theplating and the base metal corrosion products from thelocalized area of the underlying base metal.

5.9.7.2.1 Application and Use of Chemical CorrosionRemovers on Cadmium and Zinc Plated Surfaces.The directions for the application and use of chemicalremovers on these plated surfaces are as follows:

a. Prepare the area per Paragraph 5.9.7.1.

b. As stated in Paragraph 5.9.7, remove heavy cadmium orzinc and base metal corrosion products from part sur-faces using an appropriate hand type mechanical methodin this chapter such as ANSI B74.18 (GGG-C-520, TypeII, Class 1) 240 grit abrasive paper; ANSI B74.18(A-A-1047) 240 grit abrasive cloth; or A-A-58054, TypeI, Grade B abrasive mat. Avoid removing undamagedcadmium or zinc plating adjacent to the corroded area,and limit corrosion removal to the immediate area of thecorrosion on the base metal and the plating surroundingit.

c. Remove any remaining corrosion and condition thesurface of the plating and base metal with MIL-C-10578, Type I, wash-off, phosphoric acid base, corrosionremoving and conditioning compound. Refer to Para-graph 5.9.3.2.2.1 for additional instructions for applica-tion and use of this material. Allow the acid to contactthe surface only long enough to remove the corrosion,and then rinse the area thoroughly with fresh tap water.

d. Allow the area to dry, and immediately apply an organiccoating system or CPC as directed by system specifictechnical data (refer to Paragraph 5.9.7.5).

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Change 1 5-35

NOTE

These procedures are intended only for field leveltreatment of localized corroded areas on cad-mium or zinc plated surfaces and reapplication ofa protective coating after corrosion removal.When the use of organic finishes or the thicknessof the organic finish will impair the normaloperation of a part, severely corroded parts mustbe removed and replaced. Where facilities areavailable, parts with severely corroded cadmiumor zinc plating may be stripped and replated inaccordance with procedures in TO 42C2-1-7.When high strength steels are being replated, useonly those specialized procedures authorized forhigh strength steels as many plating solutions cancause hydrogen embrittlement of these materials.

5.9.7.3 Treatment of Corroded Areas on Plated Sur-faces Except Cadmium or Zinc Plating. When a breakoccurs in the surface of either chromium, nickel, tin, orcopper platings, corrosion of the steel/ferrous base metal andundercutting of the plating will rapidly follow. The corrosionwill occur at a highly accelerated rate due to the galvanicaction of these platings which are highly cathodic to thesteel/ferrous base metals.

5.9.7.3.1 Application and Use of Chemical CorrosionRemovers on Plated Surfaces Except Cadmium orZinc Plating. Directions for the application and use ofchemical removers on plated surfaces except cadmium andzinc platings are as follows:

a. Prepare the area per Paragraph 5.9.7.1.

b. Remove heavy corrosion by an appropriate hand typemechanical method in this chapter, such as a wire brushor abrasive paper, cloth, or mat.

c. Remove any remaining corrosion and condition thesurface of the plating and base metal with MIL-C-10578, Type I, wash-off, phosphoric acid base, corrosionremoving and conditioning compound. Refer to Para-graph 5.9.3.2.2.1 for additional instructions for applica-tion and use of this material. Allow the acid to contactthe surface only long enough to remove the corrosion,and then rinse the area thoroughly with fresh tap water.

d. Allow the area to dry, and immediately apply an organiccoating system or CPC or place the part directly into

service, whichever is directed by system specific tech-nical data (refer to Paragraph 5.9.7.5).

NOTE

These procedures are intended only for field leveltreatment of localized corroded areas on chro-mium, nickel, tin, and copper plated surfaces.Where service temperatures preclude the use oforganic finishes and/or the film thickness of theorganic finish will impair normal operation of thepart, severely corroded parts must be removedand replaced. Where facilities are available, se-verely corroded parts with chromium, nickel, tin,or copper plating may be stripped and replated inaccordance with procedures in TO 42C2-1-7.When high strength steels are being replated, useonly those specialized procedures authorized forhigh strength steels as many plating solutions cancause hydrogen embrittlement of these materials.

5.9.7.4 Treatment of Corroded Areas on PhosphatedSurfaces. Cadmium and zinc plated surfaces as well asmany bare steel surfaces are treated with a phosphate coatingat the time of manufacture to improve paint adhesion andcorrosion resistance of the surfaces or as a base for theapplication of grease, oil, or CPC’s. When phosphatedsurfaces corrode, corrosion should be removed by the methodrecommended for the base material.

5.9.7.5 Application of Organic Coatings. Organiccoatings may be applied to phosphated surfaces and someplated surfaces to provide corrosion protection to the platingand/or to increase the corrosion protection the plating orphosphate coating provides to the base metal. They shouldnot be used when the part operates at temperatures whichpreclude their use or when the finish will prevent the partfrom performing its intended function. Organic coatings shallnot be used on bearing or wearing surfaces of gears, cams,slides, etc., and on surfaces requiring electrical conductivity.Apply the organic finish system specified in the applicablesystem specific aircraft, missile, or equipment maintenancemanual and/or engineering drawing and TO 35-1-3 forsupport equipment using TO 1-1-8 for application proce-dures.

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5-36 Change 1

Table 5-12. Typical Chemical Corrosion Removal Procedures for Plated and Phosphated Surfaces

Type of Corrosion Corrosion Removal Protective Finish*

Light corrosion of plating andbase metal under and at breaksin cadmium or zinc platings

Remove corrosion from plating andbase metal with an abrasive pa-per, cloth, or mat. Complete cor-rosion removal and conditionmetal with MIL-C-10578, Type I,wash-off, phosphoric acid basecorrosion removing and condi-tioning compound (refer to Para-graph 5.9.7.2.1 and Paragraph5.9.3.2.2.1).

Refer to Paragraph 5.9.7.5 for discussionof organic coating systems.

Light corrosion of base metalunder and at breaks in tin,chromium, nickel, or copperplatings

Remove corrosion from the basemetal using an appropriate handmechanical method in this chap-ter, followed by metal condition-ing with MIL-C-10578, Type I,wash-off, phosphoric acid basecorrosion removing and condi-tioning compound (refer to Para-graph 5.9.7.3.1 and Paragraph5.9.3.2.2.1).

As above

Heavy corrosion of base metalunder and at breaks in cad-mium, zinc, chromium, nickel,or copper platings

As above As above

Light to heavy corrosion of basemetal under and at breaks inphosphate coatings

Remove corrosion by method usedfor corrosion removal on the basemetal

As above

* Protective finish should be applied only when the service temperature of the part does not preclude use of an organiccoating and/or where the film thickness of the coating will not impair the operation of the part.

SECTION II SURFACE TREATMENT

5.10 PURPOSE.

Surface treatment of the metal with a prescribed chemical toform a protective film is an important step in the corrosionprevention process. Properly applied chemical treatmentsimpart considerable corrosion resistance to the metal andgreatly improve the adhesion of subsequently applied paints.Epoxy primers, for example, which do not adhere well to barealuminum alloy surfaces, adhere very well to them when theyare treated with chemical conversion coatings.

5.10.1 Chemical Prepaint Treatments. Also known aschemical conversion coatings, chromate conversion coatings,chemical films, or surface pretreatments, these treatments areaqueous acid solutions of active inorganic compounds whichcombine with aluminum or magnesium surfaces to form acorrosion resistant film. In addition, these films improve theadhesion of paint coatings.

5.10.1.1 MIL-DTL-81706 Chemical Conversion Mate-rials for Coating Aluminum and Aluminum Alloys.MIL-DTL-81706 covers six different forms (I, II, III, IV, V,and VI) of two different classes (1A and 3) of chromateprepaint treatment materials (with various fluoride activators)with four separate application methods (A-spray, B-brush,C-immersion, and D-pen application) for treating bare andclad aluminum surfaces, including touch-up of damagedanodized aluminum, and titanium alloys. Application of thesematerials and the performance of the coatings developed bythem are covered by MIL-DTL-5541. MIL-DTL-81706,Class 1A coatings provide maximum protection againstcorrosion when left unpainted and superior adhesion whenpaint systems are applied. Class 3 coatings are intended foruse as a corrosion preventative film for electrical and elec-tronic applications where low contact resistance is required.Class 1A is available in the following forms:

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Change 1 5-37

5.10.1.1.1 Form I (concentrated liquid).

• Form II (powder) and Form V (premeasuredthixotropic powder) contain chromic acid dustand the other forms contain liquid chromicacid all of which can cause burns of the skin,eyes, and mucous membranes, including irri-tation and ulcers of the nasal septum. Usechemical resistant, rubber gloves and aprons;chemical, splash proof goggles and/or faceshield; and a dust filter mask when mixing thepowder and handling the solutions.

• Chromic acid is a strong oxidizer and mayignite on contact with organic materials andreducing agents.

NOTE

Mix the Form I concentrated liquid, the Form IIpowder, and the Form V premeasured thixotropicpowder in accordance with the manufacturer’sinstructions.

When the concentrated liquid is mixed with water, preferablydeionized (DI) water, per the manufacturer’s instructions, itforms a solution equivalent to a Form III solution and is readyfor use in touch-up by brush, spray, and immersion (MethodsA, B, and C) applications. The unused portions of the mixedsolution may be stored in a container and used as required.The shelf-life of the concentrated liquid and the mixedsolution is around six months if they are not contaminated.

5.10.1.1.2 Form II (powder). When the powder ismixed with water, DI water, per the manufacturer’s instruc-tions a solution equivalent to a Form III solution is formedthat can be used for brush, spray, and immersion (Methods A,B, and C) applications. The powder has an indefinite shelf-life until mixed with water. The unused portions of the mixedsolution may be stored in a closed container and used asrequired. Once mixed, the shelf-life of the solution is aroundsix months if the solution is not contaminated.

5.10.1.1.3 Form III (premixed liquid). This material isready for use as received for brush, spray, and immersion(Methods A, B, and C) applications. The Form III premixedliquid is the most convenient form of MIL-DTL-81706 foruse at field level since it requires no mixing, but is moreexpensive than the Form II powder. The shelf-life of thisliquid is about six months from the date of manufacture.

5.10.1.1.4 Form IV (premixed, thixotropic liquid).This material is a thickened, premixed liquid which is readyto use as received for brush (Method B) application. It is idealfor use on small areas, particularly vertical surfaces, since itwill remain in place without running. It is also intended foruse as a surface pre-treatment on titanium alloys prior topainting. The shelf-life of this liquid is about six months fromthe date of manufacture.

5.10.1.1.5 Form V (premeasured, thixotropic pow-der). This material is a premeasured powder that will forma thixotropic solution equivalent to Form IV when mixedwith water, preferably DI water, per the manufacturer’sinstructions. Its use and application are the same as Form IV.The powder has an indefinite shelf-life until mixed withwater. The unused portions of the mixed solution may bestored in a closed container and used as required. Oncemixed, the shelf-life of the solution is about six months if thesolution is not contaminated.

5.10.1.1.6 Form VI (premixed liquid in a self-contained applicator device). This material is a pre-mixed, ready-to-use liquid contained in its own applicatordevice/pen for application by (pen application) (Method D).It is intended to touch-up small damaged areas of MIL-DTL-5541 chemical chromate conversion coatings and anodizedcoatings, and to apply a pre-treatment coating on corrosiongrind out areas on aluminum alloys. The shelf-life of thesolutions in the applicators is about six months from the dateof manufacture.

5.10.1.2 AMS-M-3171 (MIL-M-3171), Type VI Mag-nesium Alloy, Processes for Pretreatment and Preven-tion of Corrosion On; Chromic Acid Brush-On Treat-ment.

The newly formed conversion coating is soft andcan be easily removed. Do not disturb the coatedsurface until coating is completely dry. Maintainthe drying temperature below 140° F (60° C) toavoid compromising integrity of the film. Theminimum drying time is two hours.

Also known as the Henkel Process, this is a corrosionpreventive and prepaint surface treatment/conversion coatingfor application on all magnesium alloys after corrosionremoval by either brush-on or immersion methods. Eitherobtain the premixed AMS-M-3171 (MIL-M-3171), Type VIsolution through supply channels or mix the solution perthese instructions:

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5-38 Change 1

• AMS-M-3171 (MIL-M-3171), Type VI, con-tains chromic acid which can cause burns ofthe skin, eyes, and mucous membranes, in-cluding irritation and ulcers of the nasal sep-tum. Use chemical resistant rubber gloves andaprons, chemical, splash proof goggles and/orface shield, and dust filter mask when mixingor handling these chemicals and/or solutions.

• Chromic acid is a strong oxidizer and mayignite on contact with organic materials suchas solvents, thinners, and reducing agents.

• MIL-DTL-81706/MIL-DTL-5541 aluminumconversion coating is not authorized for treat-ing magnesium alloy surfaces as it can causecorrosion of these surfaces as well as poorpaint adhesion to magnesium alloys.

a. Obtain a one gallon stainless steel, aluminum, vinyl,polyethylene or rubber container.

b. Add ½ gallon of water, preferably DI water, to thecontainer.

c. Add 1-1/3 ounces (37.8 grams) of A-A-55827 (O-C-303) Chromic Acid (CrO3) and 1 ounce (28.3 grams) ofO-D-210 Anhydrous Calcium Sulfate (CaSO4.2H2O) tothe water (refer to Appendix A for ordering informationof chemicals).

d. Top off with enough water to make one gallon ofsolution and mix thoroughly until Calcium Sulfate hascompletely dissolved into the solution.

5.10.2 Surface Preparation. After completing corro-sion removal, proceed as follows:

a. Feather the edges of the paint around areas that havebeen chemically or mechanically stripped for removaland treatment of corrosion prior to pretreatment/conver-sion coating and repainting to ensure a smooth, over-lapping transition between the old and new paint sur-faces. Feathering shall be accomplished using 240 or320 grit ANSI B74.18 (A-A-1048) aluminum oxideabrasive cloth or paper; A-A-58054, Type I, Grade B or

C (fine or medium) aluminum oxide abrasive mat; or afine or very fine aluminum oxide finishing flap brush.

b. Clean the surface of the parts and/or areas being treatedper procedures in Chapter 3 to remove all grease, oil,and dirt, and then rinse with fresh water. For watersensitive areas, use an approved cleaning solvent perprocedures in Chapter 3.

c. Abrade the area from which corrosion was removedwith an A-A-58054, Type I, Grade A or B (very fine orfine) aluminum oxide abrasive mat to remove the oxidelayer/coating. This is the most effective means forcleaning the surface so that it will accept a prepainttreatment/chemical conversion coating.

NOTE

For aluminum alloy surfaces, the oxide layer maybe removed from the area being treated withAMS-1640 (MIL-C-38334) corrosion removingcompound per procedures in TO 1-1-8 and/orParagraph 5.9.1.2.1. of this manual followed byrinsing with fresh water.

d. After abrading and/or deoxidizing the area, rinse thesurface thoroughly by flushing with fresh water, payingparticular attention to fasteners and other areas whereresidues may become entrapped. At this stage of thecleaning process, the surface should be water break-free(refer to Figure 5-10). A surface showing water breaks(water beading or incomplete wetting) is indicative ofcontamination, which will later interfere with conver-sion coating, sealing, and painting.

e. If the surface is not free of water breaks, repeat steps b,c, and d.

NOTE

Areas of aircraft, missiles, or equipment that havebeen waxed, particularly with a silicone material,or that have been treated with a silicone grease oroil require special cleaning to obtain a surfacefree of water breaks. When silicone wax, grease,or oil are suspected, solvent clean using anapproved cleaning solvent per procedures inChapter 3, and then perform steps b, c, and d.

TO 1-1-691

Change 1 5-39

5.10.3 Precautions. Observe the following precautionswhen applying chemical prepaint treatments on aluminum,titanium, or magnesium:

5.10.4 Application of Surface Treatments.

• Chemical prepaint treatments are toxic to theskin, eyes, and respiratory tract. Use chemicalresistant rubber gloves and aprons, and chemi-cal, splash proof goggles and/or face shieldduring mixing or application. If the material(which is an acid) accidentally contacts theskin or eyes, flush immediately with plenty offresh water, and report to the Base MedicalFacility if eyes are affected or the skin isburned.

• Mixing and application should be done in anadequately ventilated area. Avoid prolongedbreathing of vapors.

• Chemical conversion coating/prepaint treat-ment materials are strong oxidizers and are afire hazard in contact with flammable, com-bustible, and readily oxidizable materials.They must be stored separately from flam-mable, combustible, and oxidizable materialsand never mixed in containers previouslycontaining flammable, combustible, and oxi-dizable products. Rags contaminated withchemical conversion coating materials shouldbe thoroughly rinsed and disposed of as soonas it is practicable.

• Do not use chemical prepaint treatments onhigh strength steel parts. Catastrophic failuremay occur due to hydrogen embrittlement.

• Do not use steel, lead, copper, or glass con-tainers for holding/storing chemical prepainttreatments. Use only plastic, rubber, or stain-less steel. Brushes with tin plated steel handlesor ferrules may be used, but contact with thetreatment solution should be minimized.

NOTE

Acrylic tip of TNP pen can be modified or alteredto form any shape to allow touching up hard toreach areas.

Refer to Table 5-13 for recommended materials and proce-dures for specific alloys. Immediately after cleaning to awater break-free surface and rinsing thoroughly, apply chemi-cal conversion coating material by brush, sponge stickmoistener, immersion, or non-atomizing spray. The type ofapplication method used depends on the type of conversionmaterial being applied, the area to be covered, and whetherapplication is on a removed part or on an assembly or onequipment area. The sponge stick moisteners and the Touch-N-PrepTM (TNP) pens are particularly useful for small areas.The sponge stick moisteners may be used to apply all types ofconversion coatings for aluminum, magnesium, and titaniumalloys; and when used, they should be rinsed with fresh waterand discarded at the end of each work shift. The TNP pens areused to apply MIL-DTL-81706, Class 1A, Form VI, MethodD (Alodine 1132) conversion coatings on aluminum alloys.

5.10.4.1 Conversion Coating Using TNP Pens. Therepair of damaged chemical conversion coatings on alumi-num alloys can be accomplished by applying Alodine 1132using the TNP pens conforming to MIL-DTL-81706, Class1A, Form VI, Method D. The TNP pen applicators are idealfor touching-up small surface areas such as nicked, scratched,and chipped areas in a protective coating system. The solutionapplied with TNP pens doesn’t require rinsing or wiping offfollowing application, thus minimizing hazardous waste gen-eration. Empty pens can be returned to manufacturer fordisposal. To use the TNP pen, remove the cap and charge thetip by pressing the tip against a flat surface for 10 to 15seconds. The conversion coating solution will saturate the tip.Do not over-saturate the tip. Refresh solution often during usein a similar fashion. Use of TNP pens is restricted to 1 sq ft.

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5-40 Change 1

a. Prepare and clean the damaged area to be repaired inaccordance with Paragraph 5.10.2 prior to using theTNP pen.

b. Immediately following cleaning, use the TNP pen toapply a chemical conversion coating solution in over-lapping parallel strokes. Do not overapply the solutionwhich would allow puddles, drips, or runs to form.

c. Apply one coat of solution and allow coating to dry for5-10 minutes before next application.

d. Apply a second coat perpendicular to the first coat andallow it to dry. The treated surface does not requirerinsing or wiping off, and it can be air dried at ambienttemperature or force air dried with hot air. Oncecompletely dried, the coating is ready for priming and/orpainting.

e. After processing, if bare surface areas still exist, repeatsteps b through d. Also, if the treated surface does notturn to an iridescent yellow color shortly followingapplication, reclean the surface and reapply per steps athrough d.

5.10.5 Notes on Conversion Coating/Surface Treat-ment. Prepaint treatments shall be applied immediatelyafter corrosion removal procedures. Failure to obtain a goodconversion coating may be attributed to the following:

5.10.5.1 Allowing too long a period of contact prior torinsing can result in a powdery coated surface. Chemicalconversion coating/prepaint treatments for aluminum alloysshall be rinsed immediately when the surface has an irides-cent yellow to gold appearance. This usually occurs in 1 to 5

minutes. A brownish color indicates too long a dwell time andproduces a powdery coating. This will not provide a goodsurface to which the paint/coating system can adhere. If apowdery coating is formed, remove it with an A-A-58054,Type I, Grade B abrasive mat and reapply the material. Thenormal dwell time for magnesium conversion coating/paintpretreatments is 1 to 3 minutes to form a brown-green film,but longer contact times for magnesium pretreatments do notusually cause problems. Titanium alloys require a dwell timeof 45 minutes using a thixotropic MIL-DTL-81706, Form IVor V solution. Consult Chapter 3 of TO 1-1-8 and the materialmanufacturer’s instructions for additional instructions formixing and application of conversion coating solutions.

5.10.5.2 Allowing pretreatment solutions to contact lead,steel, copper, glass, or other incompatible materials canreduce the effectiveness of the solutions and may preventadequate pretreatment.

5.10.5.3 Insufficiently cleaned metal surfaces will preventthe conversion coating from forming on the metal surface.Cleaning must provide a water break-free surface. Refer toParagraph 5.10.2, step d.

5.10.5.4 Insufficient dwell time doesn’t allow the conver-sion coating to form on the metal surface. As the solutionapproaches its shelf-life, or at temperatures below 50° F (10°C), more time may be required to form good films.

5.10.5.5 Test a solution or material that is beyond its shelflife date using a small sample of scrap of the aluminum ormagnesium alloy metal that is to be treated. If a iridescentyellow to gold coating is produced within five minutes on an

Figure 5-10. A Water-Break Free Surface Compared with One with Breaks

TO 1-1-691

5-41

aluminum alloy or a brown-green coating is formed withinthree minutes on a magnesium alloy at 77° F (25° C), thematerial may be used.

5.10.6 Post Treatment. Allow the chemical conversioncoated surface to dry for a minimum of two hours beforepainting or applying any other temporary treatment. Moretime may be required at low temperatures or high humidity.The coating is soft until completely dried. Do not wipe thearea with a cloth or brush when coating is still wet, since thiswill remove the coating. To avoid contamination of thetreated surface and to provide a surface that is receptive toorganic coatings, prime the treated area per procedures in TO1-1-8 with the primer specified in the system specific main-

tenance manual for the aircraft, missile, or equipment in-volved within 48 hours after application of the conversioncoating/prepaint treatment. If this is not possible, performtemporary preservation procedures (refer to Paragraph5.10.7) as soon as possible. If the surface is allowed tobecome dirty, scratched or more than 48 hours have elapsedsince its application, it must be cleaned with a wet A-A-58054, Type I, grade A or B abrasive mat and retreated beforeany organic coatings/paint systems or sealants are applied.

5.10.7 Temporary Preservation. Under adverse condi-tions or when the pressure of operations will not permit theapplication and curing of an organic coating/paint system,apply an appropriate CPC in accordance with Chapter 3.

Table 5-13. Prepaint Treatments for Metal Surfaces

Alloy Surface Treatment Procedure

Aluminum alloys MIL-DTL-81706, Class 1A, Form I(Conc. Liquid), Form II (Powder),Form III (Pre-mixed Liquid),Method A, B, or C

Prepare a proper solution with either Form I or II mate-rials per the manufacturer’s instructions and TO 1-1-8or use a Form III solution as received. Spray the solu-tion with a non-atomizing sprayer (Method A) orbrush the solution with a sponge stick applicator orbrush (Method B) on the part or area being treated orimmerse a removed part in solution (Method C). Keepthe part/area wet with or the part immersed in thesolution for one to five minutes, until an iridescentyellow/gold color is obtained. Immediately rinse partthoroughly. Allow to dry (usually two hours, but notto exceed 48 hours) before painting. (1)

MIL-DTL-81706, Class 1A, FormVI, Method D; TNP Pen

Brush the surface using the acrylic tip of the pen to ap-ply a MIL-DTL-81706, Form VI conversion coatingper Method D (refer to Paragraph 5.9.4.1). The treatedsurface does not require rinsing.

Magnesium alloys AMS-M-3171 (MIL-M-3171), TypeVI (chromic acid brush-on treat-ment)

Obtain a premixed solution or mix a solution per in-structions in Paragraph 5.10.1.2. Apply the solution tothe area being treated with a sponge stick applicatoror brush and keep the area wet with solution for oneto three minutes until a brown-green, brassy, orbrown-yellow color is obtained. Immediately rinsepart thoroughly. Allow part to dry (usually eighthours) before painting. (1)

Ferrous metal(other thanstainless steel)

None Treatment prior to painting is limited to corrosion re-moval, cleaning and application of MIL-PRF-26915organic zinc rich primer or MIL-C-8514 or DOD-P-15328 wash primer per instructions in TO 1-1-8.Some of the MIL-C-10578 treatments will leave afilm adequate to paint over (refer to Paragraph5.9.3.2.2)

Stainless steel andnickel alloys

None Under engineering guidance, surfaces may be pickled(refer to Paragraph 5.9.4.2.3)

Cooper alloys None (2)

TO 1-1-691

5-42 Change 1

Table 5-13. Prepaint Treatments for Metal Surfaces - Continued

Alloy Surface Treatment Procedure

Titanium alloys MIL-DTL-81706, Class 1A, Form IV(premixed thixotropic liquid) orForm V (premixed thixotropicpowder)

Obtain the Form IV premixed thixotropic liquid or mixthe Form V premixed thixotropic powder with waterper the manufacturer’s instructions and apply the solu-tion to the surface being treated with a sponge stickapplicator or a brush. Allow the solution to dwell onthe surface for 45 minutes and then rinse thoroughlywith fresh water. Allow to dry (usually two hours, butnot to exceed 48 hours) before painting (1)

Plated and phos-phated cadmium

None (2)

(1) Drying time may be accelerated by blowing with filtered warm air (140° F/60° C maximum). If the air contains oil(from a compressor) or other impurities, the paint system which is applied over the conversion coating will notpass wet tape adhesion tests and will probably peel leading to additional corrosion. Drying air temperatures higherthan 140° F (60° C) will degrade the conversion coating and cause it to lose its effectiveness.

(2) Treatment is limited to corrosion removal and cleaning. These surfaces are not normally painted, but may requirepainting for decorative purposes, or in instances where the surface will be in contact with a dissimilar anodicmetal. (CPCs) may be applied as recommended in Chapter 3.

TO 1-1-691

5-43

SECTION III SHOT PEENING/ROTO-PEENING

5.11 PEENING OF METAL SURFACES.

Peening is a special form of abrasive blasting which slightlydeforms the metal surface by dimpling it and produces acompressive stress on the metal surface. It acts as a preloadstress which must be exceeded by tensile loads applied to apart before the metal surface experiences any tensile stressfrom an applied tensile load. The deformation on the surfacetends to close off exposed metal end grains and grainboundaries on the metal surface. The compressive stress onthe surface increases the resistance of the metal to fatigue andstress corrosion cracking, because both begin on the surfaceof the metal when it is subjected to tensile stresses. Theclosure of exposed end grains and grain boundaries increasesthe resistance of the metal to intergranular corrosion; inparticular, it increases the resistance of high strength alumi-num alloys to exfoliation corrosion. Because it increasesresistance to corrosion and fatigue, peening is specified forprotection of numerous new, high strength steel and alumi-num alloy parts as well as being required as a final procedureduring rework/grindout of corrosion damaged areas at bothfield and depot levels of maintenance on many aircraft,missile, and other equipment components fabricated fromthese metals. Peening will not restore the strength lost in ametal structure caused by metal removal due to corrosiondamage, but it increases corrosion and fatigue resistance ofthe remaining metal. Peening requires the use of larger sizedabrasive particles than used in abrasive blasting operations,specialized blasting procedures for accomplishment, andspecial techniques and equipment for measuring the intensityand saturation or surface coverage of a peening operation.Peening intensity is measured with an Almen gauge and teststrips, while saturation or surface coverage is determined byobservation of the surface with a 10X magnifying glass.

5.11.1 Types of Peening.

Peening operations can cause injury to personnel,as high speed airborne abrasive particles canstrike unprotected areas of the body, enter into therespiratory tract, and cause slippage due to abra-sive residue buildup on the floor. Personal pro-tective equipment (PPE): protective gogglesand/or a face-shield, dust filter mask, gloves, andcoveralls are required for personnel engauged inpeening operations. The work areas shall be keptclean of abrasive residue buildup, and adequateventilation shall be provided.

• Peening is a specialized process requiringspecialized training in peening techniquesused. Personnel who have not been specifi-cally trained for peening operations and/orwho are not thoroughly familiar with thespecifications which cover these operationsAMS-S-13165 (MIL-S-13165) AMS-2431and its subordinate slash numbers (/1 through/8), MIL-R-81841, and MIL-W-81840, shallnot be allowed to perform peening operations.Damage to structure, injury to personnel, in-effective peening, and a false sense of securityabout the condition of peened aircraft, missile,or piece of equipment structure will result ifuntrained and inexperienced personnel areallowed to perform peening operations.

• Damage to equipment can also result fromabrasive particles which enter working mecha-nisms. Masking and shielding materials shallbe used to prevent penetration of abrasiveparticles in areas adjacent to the area beingpeened and to contain abrasive over-spray toprevent damage to the structure.

There are two basic types of peening used on Air Forceequipment: shot peening and glass or ceramic bead peeningper AMS-S-13165 (MIL-S-13165), and roto-peening perMIL-R-81841.

5.11.1.1 Shot Peening and Glass or Ceramic BeadPeening.

Do not use peening media (i.e. steel shot, glassbeads, etc.) previously used for peening one typeof metal to peen a different type of metal, ascontamination of the metal surface and subse-quent galvanic corrosion will result. Do not useany steel wire or shot for peening aluminum alloysurfaces, as steel particles will become embeddedand cause galvanic corrosion. Use only AMS2431/6 glass bead shot or AMS 2431/7 ceramicbead shot per parameters outlined in AMS-S-13165 for peening aluminum alloys.

TO 1-1-691

5-44

Shot and glass or ceramic bead peening, per AMS-S-13165(MIL-S-13165), is the peening of a metal surface by directingan air driven stream of abrasive particles onto the metalsurface, using the same type of equipment employed forabrasive blasting to remove corrosion. The materials used are:stainless steel (CRES) cut wire shot per AMS 243¼; cast steelshot per AMS 2431/1 and /2; conditioned carbon steel cutwire shot per AMS 2431/3 and /8; ceramic bead shot perAMS 2431/7; and glass bead shot per AMS 2431/6. ConsultAMS-S-13165 (MIL-S-13165) for all parameters that con-cern peening, such as intensity, saturation points, angle ofblasting, nozzle distance, dwell times, pressures, and castshot, cut wire shot, and glass or ceramic bead shot sizes. Shotpeening by blasting will not be discussed further in thismanual as this is normally a depot level operation requiring aspecific step by step work procedure for each job and is notused very often in every day corrosion removal work.

5.11.1.2 Roto-Peening (Rotary Flap Peening).

MIL-W-81840, Type I flaps shall not be used topeen aluminum alloy surfaces, since they containcast steel shot which can become imbedded in thesurface and cause galvanic corrosion. Use onlyType II flaps on aluminum alloy surfaces.

Roto-peening or rotary flap peening per MIL-R-81841 is aprocess that uses fiber type flaps with metal shot bonded tothem and mounted in a mandrel which is rotated in apneumatic drill motor to peen a metal surface. The flaps areheld close to the metal surface while the drill motor is movedlinearly along the surface so that the bonded shot strike thesurface causing a peening action to occur over the entire areabeing worked. Rotary flap peening wheels used for roto-peening conform to MIL-W-81840 and are of two types: TypeI - rigid core with semi-rigid bonded flaps to which cast steelshot conforming to AMS 243½ or SAE J827 are bonded; andType II (Class 1, 2, or 3; defines flap size) - a flexible flapassembly mounted in a slotted mandrel with tungsten carbideshot bonded to the flap. Consult the specification coveringrotary flap peening of metal parts, MIL-R-81841, for allparameters that concern roto-peening, such as intensity,saturation points, flap distance from surface, linear movementrate of flap, dwell times, drill motor speed (in RPM), and sizeof flap. This method of peening is convenient for peeningsmall areas where corrosion rework has been accomplished inplace on an aircraft, missile, or piece of equipment since itdoes not produce the contamination and abrasive residueassociated with the airblast methods and doesn’t requireremoval/disassembly of a part for placement in a blast booth.Roto-peening (rotary flap peening) is the primary peeningprocess used on aircraft, missile, and equipment componentsafter corrosion removal, so it is the only peening processdiscussed in detail in this manual. These procedures arelimited in scope for use only for peening or repeening metal

surfaces after corrosion removal and no other purpose.Peening that may be accomplished is limited as follows:

a. The area peened shall not be larger than 3 x 4 inches.

b. When more than one area on a component requirespeening, the cumulative size of these areas shall notexceed 3 x 4 inches.

c. This procedure is not authorized for peening to accom-plish fatigue or stress relief on previously unpeenedareas where corrosion removal is not involved.

d. Any roto-peening operation which exceeds these param-eters shall be accomplished in accordance with allrequirements in MIL-R-81841 in addition to theseprocedures.

e. Roto-peening shall be used on a weapon system com-ponent only when required in a specific system specifictechnical order or the component is identified as havingbeen previously peened.

5.11.2 Roto-Peening (Rotary Flap Peening) Proce-dures.

Roto-peening (rotary flap peening) operationscreate airborne particles. Eye protection in theform of safety goggles/glasses and/or face shieldis required.

5.11.2.1 Equipment. The tools required for rotary peen-ing are: a pneumatic drill or high speed grinder; a flap wheel,conforming to MIL-W-81840; an air regulator for the drill orgrinder; and a tachometer. The pneumatic drill or high speedgrinder must be capable of achieving the RPM required forthe type and class of peening wheel or flap being used (within±10 RPM under load; refer to Table 5-14). The tachometer isused to check the speed (RPM) of the drill/grinder. The airregulator is used to adjust the air pressure for the control ofthe RPM. An Almen gauge designed specifically for theroto-peen process along with appropriate Almen test strips isused to determine peening intensity. MIL-W-81840 flapwheels are of two types: Type I wheels are for use on ferrousmetal alloys (steels); and Type II, Class 1, 2, or 3 wheels (flapassemblies mounted in mandrels) are for use on aluminumand steel alloys.

5.11.2.2 Surface Preparation Procedure. Prepare thesurface to be peened as follows:

5.11.2.2.1 Dimensions and Part Conditions. Areas ofparts to be roto-peened shall be within required dimensionaland surface finish requirements before peening. Unless oth-erwise directed, all heat treatments required to developspecified mechanical properties, and all machining, grinding,

TO 1-1-691

Change 1 5-45

and required polishing operations shall be completed beforepeening. Prior to roto-peening, all fillets shall be properlyformed, all burrs shall be removed, and all sharp edges andcorners to be peened shall be machined or sanded to providethem with a sufficient radius to result in complete coveragewithout any distortion.

5.11.2.2.2 Cleaning and Coating/Paint Removal.Unless otherwise specified, all areas to be roto-peened shallbe cleaned in accordance with Chapter 3 of this manual, andcoatings/paints shall be removed from the areas per proce-dures in TO 1-1-8.

Table 5-14. Tool Operation Speed Requirements

Operational Speed (RPM)

Tool (MIL-W-81840) Tool Description Normal RangeMaximum Al-

lowed

Type I Rigid Core with Bonded Semi-Rigid Flaps and CastSteel Shot Bonded to Flaps

1500 to 4000 4500

Type II, Class 1 Mandrel with 2 in L x 1 in W Flaps 1500 to 5000 6000Type II, Class 2 Mandrel with 1¼ in L x 9/16 in W Flaps 2750 to 7000 14000Type II, Class 3 Mandrel with 1 in L x 9/16 in W Flaps 2750 to 7000 14000

5.11.2.2.3 Masking. Any areas of the part which havecritical surface finishes that must be free from peening shallbe suitably masked or otherwise handled to protect them fromdamage caused by the rotary flap action. Masking of areas notrequiring peening and whose surface finishes are not criticalis optional.

5.11.2.3 Peening Intensity Determination. The peen-ing intensity is a measure of the amount of compressive stressdeveloped on the surface of the metal component by peening.This is measured as an arc-height value, based on the fact thata sheet of metal which is cold worked on one side only willdeform due to the compressive stresses set up on the coldworked side and form a bow or arc. The arc height is

determined by measuring in inches the bow created in anAlmen test strip at its center by roto-peening it using the sameparameters as will be used to peen the area of the componentbeing worked. The peening intensity required after corrosionremoval is that which is specified in a system specificmaintenance technical order for the specific weapon systemor it may be determined from Table 5-15. The peeningintensities given in this table are for standard shot peeningand were determined with an Almen test strip in accordancewith AMS-S 13165 (MIL-S-13165). These intensities must beconverted to roto-peen (rotary flap peening) intensities inaccordance with MIL-W-81840, using the graph in Figure 5-8which is reprinted here from MIL-W-81840.

Table 5-15. Standard Peening Intensity (Isp) for Complete Coverage Arc-Height in Inches

Material Thick-ness (In.)

Steel: Under 20000PSI

Steel: Over 20000 PSI Titanium and TitaniumAlloys

Aluminum and AluminumAlloys

0.090 or less 0.003-0.0006A 0.003-0.006A 0.00.-0.006A0.0090 0.375 0.006-0.012A 0.006-0.010A 0.006-00.010A 0.0060-0.010A0.375 or more 0.012-0.016A 0.006-0.010A 0.006-0.010A 0.010-0.014A

NOTE

• Base on test strip holder is specified in AMS-S-13165 (MIL-S-13165).

• The suffix letter A indicates that the values have been determined by using an A type Almen test strip. AnA type Almen test strip is used for arc heights up to 0.024A. For greater intensities, Almen test strip Cshould be used. Almen test strip N is used if the intensity is less than 0.004A.

5.11.2.4 RPM and Peening Time Determination. Therequired peening intensity determined from Table 5-15 isconverted in Figure 5-8 and then used in Figure 5-9 and/or

Figure 5-10, as applicable, to establish peening time andRPM requirements. Figure 5-9 converts peening intensity tothe RPM and peening time required to achieve this intensity

TO 1-1-691

5-46 Change 1

when using MIL-W-81840, Type I roto-peening wheels.Figure 5-10 accomplishes the conversion for MIL-W-81840,Type II, Class 1, 2, and 3 peening wheels (flaps). The peeningtimes have been determined by saturating the 2.25 squareinch Almen test strip at the RPM and times given in Figure5-9 and/or Figure 5-10 to obtain the corresponding peeningintensity. For areas smaller or larger than 2.25 square inches,use the following equation to determine peening time:

T = TsA/As

T = Total peening time, in minutes.

Ts = Saturation peening time, as determinedfrom Figure 5-9 and/or Figure 5-10, inminutes.

A = Area of part to be peened in squareinches.

As = The 2.25 in2 area of the test strip whena flap with a width of ¾ inch or less isused; if the flap width is greater than ¾inch, multiply effective width of the flapby 3 inches to obtain As.

Isp = Standard peening intensity measuredwith an AMS-S-13165 (MIL-S-13165)Almen strip holder. The intensity rangerequired for saturation peening forvarious metal alloys at variousthicknesses is specified in Table 5-15.

Irp = Roto-peening intensity required forsaturation peening as measured with aMIL-W-81840 Almen strip holder anddetermined by conversion of Isp to Irpusing the graph in Figure 5-8.

Example: Determine the peening timeand the tool speed (RPM) required toroto-peen (rotary flap peen) a 3 x 4 inarea on an aluminum alloy componenthaving a thickness within the range of0.090 to 0.375 in using aMIL-W-81840, Type II, Class 1 flap andmandrel.

A = 3 x 4 in = 12 in2

As= 1 x 3 in = 3 in2. This is the case since aType II, Class 1 flap is 1 in (wider than¾ in).

Isp = 0.010A (10 mils). This is the maximumallowed intensity for aluminum alloyswith a thickness within the 0.090 to0.375 in range as determined with aAMS-S-13165 (MIL-S-13165) Almenstrip holder and specified in Table 5-15.

Irp = 13.2 mils (0.013A). This is the requiredroto-peening intensity measured with aMIL-W-81940 Almen strip holder. It isdetermined by entering Figure 5- 8 onthe horizontal (X) axis with the Isp of 10mils, moving up to the line in the graph,and reading across to the vertical (Y)axis to find an Irp of 13.2 mils.

T =s3.25 minutes. This is determined byentering Figure 5-10, the saturationcurve graph for Type II wheels (flaps) ofMIL-W-81840, on the vertical (Y) axiswith the Irp of 13.2 mils from above,moving across to the “C” curve, whichis the only curve that works in this casefor Class 1 flaps, and reading down tothe horizontal (X) axis to find a Ts of3.25 minutes at a flap speed of 2500RPM.

T = (3.25) 12/3 = 13.00 min = 13 min and 0sec at a flap speed of 2500 RPM.

5.11.2.5 Peening Process.

MIL-W-81840, Type I flaps shall not be used topeen aluminum alloy surfaces, since they containcast steel shot which can become imbedded in thesurface and cause galvanic corrosion. Use onlyType II flaps on aluminum surfaces.

To achieve the required peening intensity, it is essential thatthe flap wheel be operated at the required speed under loadand that the proper flap deflection be maintained throughoutthe peening process. Move the flap wheel over the surfacebeing peened with longitudinal sweeps and transverse oscil-lation to provide uniform surface coverage, while applyingsufficient hand pressure to the tool to deflect the flaps asshown in Figure 5-11. Perform this procedure over the entiresurface area being peened for the time determined by themethods stated in Paragraph 5.11.2.4.

NOTE

The flaps used for this procedure are expensiveand tear apart easily when they drop over theedge of a part during the peening operation. Theuse of a hard rubber material clamped in place atthe edges of the part being peened will preventthe flaps from dropping over the edge of the partduring the peening operation, thus increasing theuseful life of each flap.

TO 1-1-691

5-47

5.11.2.6 Peened Coverage. Visually inspect peenedareas with a 10X power magnifier to determine if completecoverage and saturation have been accomplished. Everyportion of the critical surface shall show visible evidence ofplastic flow to demonstrate complete coverage and saturationwhich is indicated by the complete obliteration of the originalsurface finish and overlapping peening impressions.

5.11.2.7 Surface Finish. Conversion coat or passivatethe peened area in accordance with Section II or otherapplicable paragraph of this chapter. Apply protective coat-ings as specified in the system specific maintenance manualfor the aircraft, missile, or equipment involved using appli-cation procedures in TO 1-1-8

Figure 5-11. Peening Intensity Conversion Graph (Isp to Irp)

TO 1-1-691

5-48 Change 1

Figure 5-12. Saturation Coverage Curves for MIL-W-81840, Type I Wheels

TO 1-1-691

5-49

Figure 5-13. Saturation Coverage Curves for MIL-W-81840, Type II Wheels (Flaps)

TO 1-1-691

5-50

Figure 5-14. Flap Deflection Ranges

TO 1-1-691

5-51/(5-52 blank)

CHAPTER 6SEALANTS

6.1 PURPOSE.

This chapter covers sealing compounds and procedures fortheir application to aircraft, missile, and equipment struc-tures. When properly applied, sealants prevent the intrusionof moisture from condensation, rain, and salt water as well asdust, dirt, and aircraft fluids into joint areas where they cancause extensive corrosion. Sealants are one of the mostimportant tools for corrosion prevention and control. To beeffective, it is critical that the correct sealant be chosen for aspecific area/situation and that it be applied correctly. Onlyqualified personnel thoroughly familiar with sealants andtheir application shall be permitted to handle and apply them.

6.2 APPLICATIONS.

Sealants are used for the following reasons:

a. Fuel sealing (fuel tanks and delivery components).

b. Pressure area sealing (aircraft cabin areas).

c. Weather and fluid sealing (aircraft, missile, and equip-ment exterior and interior skin and structural joints andsurfaces).

d. Firewall sealing (engine and ordnance areas).

e. Electrical sealing (bulkhead wiring, electrical connec-tors, and components).

f. Acid-resistant sealing (aircraft, missile, and equipmentbattery compartments, and aircraft relief tubes andwaste collection tanks).

g. Window sealing (aircraft and equipment windows).

h. High temperature sealing (engine areas, anti-icing ducts,and some electronics).

i. Aerodynamic sealing/smoothing (aircraft and missileexterior skin surfaces).

6.3 SEALING COMPOUNDS.

Table 6-1 lists approved sealing compounds, and their avail-able types, properties, and intended use. Refer to the appli-cable aircraft, missile, or equipment system specific mainte-nance manual and Paragraph 6.7 for specific informationconcerning selection of the proper sealing compound and its

application. Observe the warnings and cautions in Paragraph6.6 when using any sealing compound.

6.3.1 Sealant Packaging. Sealants are generally pack-aged and available as three different types of packaging orunits of issue (U/I):

6.3.1.1 Two-Part Kit (KT). The package consists of twoseparate containers, usually metal cans. One contains thecatalyst (part A) and the other contains the base compound(part B), each in pre-measured amounts for mixing together.

6.3.1.2 Cartridge (CA). Cartridges come in two differ-ent types. One for single component sealants and one for twocomponent sealants.

6.3.1.2.1 Single component sealants are contained in aplastic cartridge or tube in a ready to use condition requiringno mixing. If some of a single component sealant remainsafter a job, it can be stored and used at a future time as longas the cartridge/tube is tightly capped at the nozzle opening toprevent contact with air.

6.3.1.2.2 Two component sealants are packaged in Sem-kits® which are complete plastic cartridge assemblies thatstore both sealant components (each in separate chambers).Mixing of sealant materials is accomplished within theassembly, which is then used for application. Semkits® areconvenient because they eliminate the need to measure andhandle the materials for mixing, and generate less waste asthey contain small quantities for small area applications.

6.3.1.3 Premixed and Frozen (PMF). Two componentsealants can be premeasured, mixed, and frozen at tempera-tures of -40° F (-40° C) and stored at temperatures of -20° F(-29° C) or lower with the unit of issue being in ounces. ThePMF material in plastic tubes is a convenient packageconfiguration for low and intermittent usage applications,particularly in depot level operations. Simply thaw thematerial and use.

6.3.2 Polysulfide, Polyurethane, and PolythioetherSealing Compounds. All these materials are two com-ponent with the Part B base containing the prepolymer andthe Part A catalyst containing the curing agent packaged inseparate containers supplied together as a kit. When thor-oughly mixed, the catalyst cures the prepolymer to a rubberysolid. Rates of cure depend on the type of prepolymer andcatalyst, as well as the temperature and humidity. Full cure of

TO 1-1-691

Change 1 6-1

these materials may require as long as 7 days. Refer to Table6-1 for a general description of these materials.

6.3.3 Silicone Sealing Compounds.

Room Temperature Vulcanizing (RTV) siliconesconforming to MIL-A-46106 produce acetic acid(vinegar smell) which is corrosive. Therefore, asa rule of thumb, if the RTV silicone materialsmells like vinegar, don’t use it.

These materials are generally one component materials whichcure by reacting with moisture in the air. If silicones areapplied too thick or in such a way that moisture is preventedfrom entering the material, they may not cure at all. Inaddition, many unauthorized silicone sealing compoundsproduce acetic acid, indicated by a vinegar smell, whilecuring which can lead to severe corrosion problems. Thereare two silicone sealant specifications, MIL-A-46146 andMIL-A-46106. Only MIL-A-46146 materials are non-corrosive. MIL-A-46106 materials give off acetic acid whilecuring and shall not be used on Air Force equipment.

TO 1-1-691

6-2

Tabl

e6-

1.Se

alin

gC

ompo

unds

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

MIL

-PR

F-81

733

(sup

erse

des

MIL

-S-

8173

3),

Seal

ing

and

Coa

ting

Type

I(t

hin)

-fo

rbr

ush

ordi

pap

-pl

icat

ion

Two

com

pone

nts

Seal

ing

fayi

ngsu

rfac

esan

dfo

rw

etin

-st

alla

tion

offa

sten

ers

onpe

rman

ent

stru

ctur

ere

pair

s.C

lass

1,G

rade

Am

ater

ials

are

the

pref

erre

dse

alan

tsfo

rth

ese

appl

icat

ions

asth

eypr

ovid

eth

ebe

stco

rros

ion

prot

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n.

Com

poun

d,C

orro

sion

Inhi

bitiv

eTy

peII

(thi

ck)

-fo

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alan

tgu

nor

spat

ula

appl

icat

ion

Roo

mte

mp

cure

Cla

ss1

-Po

lysu

lfide

Type

III

(spr

ayab

le)

-fo

rsp

ray

gun

appl

icat

ion

Serv

ice

tem

p:-6

5°to

+25

0°F

(-54

°to

+12

1°C

)C

lass

2-

Poly

thio

ethe

rTy

peIV

(spr

eada

ble)

-fo

rfa

ying

surf

ace

seal

ing

requ

irin

gex

tend

edas

sem

bly

times

Peel

stre

ngth

:15

inlb

wid

th(m

in)

Gra

deA

-C

hrom

ate

Inhi

bito

rsC

orro

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inhi

bitin

gG

rade

B-

Non

-Chr

omat

eIn

hibi

tors

Res

ists

fuel

,oi

l,an

dhy

drau

licflu

id.

SAE

AM

S-S-

8802

(sup

erse

des

MIL

-S-

8802

),Se

alin

gC

ompo

und,

Tem

pera

-tu

reR

esis

tant

,In

tegr

alFu

elTa

nks

and

Fuel

Cel

lC

aviti

es,

Hig

hA

dhe-

sion

(Pol

ysul

fide)

Cla

ssA

(thi

n)-

for

brus

hap

plic

a-tio

nTw

oco

mpo

nent

sU

sed

for

fille

tan

dbr

ush

seal

ing

inte

gral

fuel

tank

san

dfu

elce

llca

vitie

s.N

otto

beex

pose

dto

fuel

orov

erco

ated

until

tack

-fre

e.C

lass

B(t

hick

)-

for

seal

ant

gun

orsp

atul

aR

oom

tem

pcu

re

Cla

ssC

(spr

eada

ble)

-fo

rus

ew

here

exte

nded

asse

mbl

ytim

esar

ere

-qu

ired

Serv

ice

tem

p:-6

5°to

+25

0°F

(-54

°to

+12

1°C

)

Peel

stre

ngth

:20

inlb

wid

th(m

in)

No

corr

osio

nin

hibi

tors

Res

ists

fuel

,oi

l,an

dhy

drau

licflu

id.

TO 1-1-691

6-3

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

SAE

AM

S32

76(s

uper

sede

sM

IL-S

-83

430)

,Se

alin

gC

ompo

und,

Inte

gral

Fuel

Tank

san

dG

ener

alPu

rpos

e(P

olys

ulfid

e).

Cla

ssA

(thi

n)-

for

brus

hap

plic

a-tio

nTw

oco

mpo

nent

s

Cla

ssB

(thi

ck)

-fo

rse

alan

tgu

nor

spat

ula

appl

icat

ion

Roo

mte

mp

cure

Cla

ssC

(thi

ck)

-fo

rus

ew

here

ex-

tend

edas

sem

bly

times

are

re-

quir

ed

Serv

ice

tem

p-6

5°to

+25

0°F

(-54

°to

+12

1°C

)su

stai

ned,

inte

rmitt

ent

(abo

ut6

hour

sm

ax.)

expo

sure

to36

0°F

(182

°C

)

For

high

erte

mpe

ratu

reap

plic

atio

ns.

Use

dfo

rfu

elta

nkse

alin

g,ca

bin

pres

-su

rese

alin

g,ho

lean

dvo

idfil

ling,

and

aero

dyna

mic

smoo

thin

g;fo

rfa

ying

surf

ace

seal

ing,

wet

-ins

talla

tion

offa

sten

ers,

over

coat

ing

fast

ener

s,an

dse

alin

gjo

ints

and

seam

sin

fuel

wet

area

s;an

dfo

rno

n-st

ruct

ural

adhe

sive

bond

ing.

Tre

atbo

ndsu

rfac

esw

ithSA

EA

MS

3100

adhe

sion

prom

oter

toen

hanc

ese

alan

tad

hesi

on.

Cla

ssD

(thi

ck)

-fo

rho

lean

dvo

idfil

ling

Peel

stre

ngth

:20

inlb

wid

th(m

in)

Cla

ssE

(thi

ck)

-fo

rau

tom

atic

rive

t-in

geq

uipm

ent

appl

icat

ion

No

corr

osio

nin

hibi

tors

Res

ists

fuel

,oi

l,an

dhy

drau

licflu

id;

PR-1

773

(sup

erse

des

PR-1

403G

),Se

alin

gC

ompo

und,

Non

-Chr

omat

eC

orro

sion

Inhi

bitiv

ePo

lysu

lfide

Rub

ber

Cag

eC

ode

#835

74

Cla

ssB

(thi

ck)

-fo

rse

alan

tgu

nor

spat

ula

appl

icat

ion

Two

com

pone

nts

Pref

erre

dse

alan

tfo

rge

nera

lpu

rpos

e,lo

wad

hesi

onse

alin

gof

acce

ssdo

ors,

floor

pane

lsan

dpl

ates

,re

mov

able

pane

ls,

and

form

edin

plac

e(F

IP)

gas-

kets

inno

n-fu

elar

eas.

Can

beus

edto

repa

irde

fect

sin

FIP

Gas

kets

.

Roo

mte

mp

cure

Serv

ice

tem

p:-6

5°to

250°

F(-

54°

to+

121°

C)

Peel

stre

ngth

:2

inlb

wid

th(m

ax)

Cor

rosi

onin

hibi

tors

Res

ists

fuel

,oi

l,an

dhy

drau

licflu

id.

SAE

AM

S32

67/1

,/2

,/3

,an

d/4

(su-

pers

edes

MIL

-S-8

784)

,Se

alin

gC

ompo

und,

Low

Adh

esio

n,C

orro

-si

onIn

hibi

ting,

For

Rem

ovab

lePa

n-el

san

dFu

elTa

nkIn

spec

tion

Plat

es

Cla

ssA

(thi

n)-

for

brus

hap

plic

a-tio

nTw

oco

mpo

nent

sPo

lysu

lfide

rubb

erse

alin

gco

mpo

und

for

fille

tan

dfa

ysu

rfac

ese

alin

gof

re-

mov

able

stru

ctur

essu

chas

acce

ssdo

ors,

floor

pane

lsan

dpl

ates

,re

mov

-ab

lepa

nels

,an

dfu

elta

nkin

spec

tion

plat

es.

Not

for

high

tem

par

eas

orpe

rman

ent

stru

ctur

es.

Cla

ssB

(thi

ck)

-fo

rse

alan

tgu

nor

spat

ula

appl

icat

ion

Roo

mte

mp

cure

Serv

ice

tem

p:-6

5°to

250°

F(-

54°

to+

121°

C)

/1=

Cla

ssA

-½Pe

elst

reng

th:

4in

lbw

idth

(max

)/2

=C

lass

B-½

Cor

rosi

onIn

hibi

tors

/3=

Cla

ssA

-2R

esis

tsfu

el,

oil,

and

hydr

aulic

fluid

./4

=C

lass

B-2

TO 1-1-691

6-4

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

SAE

AM

S33

74/1

,/2

,/3

,an

d/4

(su-

pers

edes

MIL

-S-3

8249

),Se

alin

gC

ompo

und,

Air

craf

tFi

rew

all

Type

1(o

ne-p

art

high

tem

p.si

li-co

ne)(

cond

ensa

tion

cure

dO

neco

mpo

nent

,Ty

pe1;

Two

com

pone

nts,

Type

s2,

3,an

d4

Seal

ing

firew

all

stru

ctur

esex

pose

dto

very

high

tem

pera

ture

sag

ains

tth

epa

ssag

eof

air

and

vapo

rs.

Cur

eson

expo

sure

toai

r./1

=Ty

pe1

Type

2(t

wo-

part

high

tem

p.si

li-co

ne)

-ad

ditio

ncu

red

Roo

mte

mp

cure

/2=

Type

2Ty

pe3

(tw

o-pa

rthi

ghte

mp.

sili-

cone

)-

cond

ensa

tion

cure

dSe

rvic

ete

mp;

-65°

to+

400°

F(-

54°

to+

204°

C)

with

stan

dsfla

shte

mpe

ratu

reof

2000

°F

(109

3°C

)/3

=Ty

pe3

Type

4(t

wo-

part

poly

sulfi

de)

Peel

stre

ngth

:10

inlb

wid

th(m

in)

/4=

Type

4N

oco

rros

ion

inhi

bito

rsR

esis

tsfu

el,

oil,

and

hydr

aulic

fluid

MIL

-S-8

5420

,Se

alin

gC

ompo

unds

,Q

uick

Rep

air,

Low

Tem

pera

ture

Cur

ing

Poly

sul-

fide,

for

Air

craf

tSt

ruct

ures

Cla

ssA

(thi

n)-

for

brus

hap

plic

a-tio

nTw

oco

mpo

nent

sQ

uick

repa

irse

alin

gof

airc

raft

stru

c-tu

res

atlo

wte

mpe

ratu

res.

Use

only

with

the

reco

mm

ende

dad

hesi

onpr

o-m

oter

/pri

mer

for

optim

umre

sults

.W

hen

cure

dat

ate

mpe

ratu

reof

atle

ast

75°

F(2

4°C

),th

efly

-aw

aytim

eis

2to

3ho

urs.

Whe

ncu

red

ata

tem

-pe

ratu

reas

low

as45

°F

(7°

C),

the

fly-a

way

time

is4

hour

sfo

rTy

peII

seal

ants

and

8ho

urs

for

Type

Ise

al-

ants

.T

his

seal

ant

shou

ldbe

stor

edat

ate

mpe

ratu

reno

tto

exce

ed+

80(F

orpo

orad

hesi

onw

illre

sult.

Type

I-

dich

rom

ate

cure

syst

emC

lass

B(t

hick

)-

for

seal

ant

gun

orsp

atul

aap

plic

atio

nL

owte

mp

cure

Type

II-

man

gane

secu

resy

stem

Serv

ice

Tem

p:-6

5°to

200°

F(-

54°

to+

93°

C)

Peel

stre

ngth

:10

inlb

wid

th(m

in)

No

corr

osio

nin

hibi

tors

;R

esis

tsfu

el,

oil,

and

hydr

aulic

fluid

.

TO 1-1-691

6-5

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

MIL

-S-2

9574

(SA

EA

MS-

S-29

574)

,Se

alin

gC

ompo

und,

Poly

thio

ethe

r,fo

rA

ircr

aft

Stru

ctur

es,

Fuel

and

Hig

hTe

mpe

ratu

reR

esis

tant

,Fa

stC

urin

gat

Am

bien

tan

dL

owTe

m-

pera

ture

s

Cla

ssA

(thi

n)-

for

brus

hap

plic

a-tio

nTw

oco

mpo

nent

Mul

ti-pu

rpos

eai

rcra

ftst

ruct

ure

and

inte

-gr

alfu

elta

nkse

alan

tsw

ithra

pid

am-

bien

tan

dlo

wte

mpe

ratu

recu

ring

ca-

pabi

litie

s.U

seof

man

ufac

ture

r’s

reco

mm

ende

dpr

imer

isre

quir

edpr

ior

toap

plyi

ngth

isse

alan

tfo

rpr

oper

adhe

sion

.Ty

peI

can

beus

edas

anal

tern

ate

for

SAE

AM

S-S-

8802

(MIL

-S-

8802

)in

fuel

tank

appl

icat

ions

and

Type

IIca

nbe

used

asan

alte

rnat

efo

rM

IL-S

-817

33.

Type

I(

No

corr

osio

nin

hibi

tors

inte

r-m

itten

tus

eto

+40

0°F

(204

°C

)G

rade

A(

gene

ral

use,

fuel

tank

san

dai

rcra

ftst

ruct

ures

Gra

deA

1(

ambi

ent

orim

med

iate

heat

cure

afte

rap

plic

atio

nat

tem

psup

to35

0°F

(175

°C

)C

lass

esB

&C

only

Gra

deB

(enh

ance

dcr

aze

resi

stan

cefo

rai

rcra

ftac

rylic

tran

s-pa

renc

ies

Cla

ssB

(thi

ck)

-fo

rse

alan

tgu

nor

spat

ula

Low

(dow

nto

+20

°F/

-7°

C)

and

ambi

ent

tem

pcu

ring

;Ty

peI,

Gra

deA

1on

ly-

can

behe

atcu

red

atte

mps

.up

to+

350°

F(+

175°

C)

Type

II(

Cor

rosi

onin

hibi

tive

inte

rmit-

tent

use

to36

0°F

(182

°C

)C

lass

C(s

emi-

thic

k)-e

xten

ded

as-

sem

bly

times

for

fayi

ngsu

rfac

ese

alin

g

Serv

ice

tem

p:-8

0°to

+30

0°F

(-68

°to

+15

0°C

)w

ithin

term

it-te

ntus

eto

+40

0°(+

204°

C)

for

Type

Ian

d+

360°

F(+

182°

C)

for

Type

IIPe

elst

reng

th:

20in

lbw

idth

(min

)C

orro

sion

inhi

bitin

g-

Type

IIon

lyTy

peI

has

noco

rros

ion

inhi

bi-

tors

Res

ists

fuel

,oi

l,an

dhy

drau

licflu

id.

TO 1-1-691

6-6

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

MIL

-A-4

6146

,Adh

esiv

e-

Seal

ants

,Si

licon

e,R

oom

Tem

pera

ture

Vul

ca-

nizi

ng(R

TV

),N

onco

rros

ive

(For

Use

With

Sens

itive

Met

als

and

Equ

ipm

ent)

Gro

upI

-G

ener

alpu

rpos

eO

neco

mpo

nent

Con

veni

ent

one

com

pone

nt,

non-

corr

osiv

e,R

TV

silic

one

seal

ant

for

use

with

sens

itive

met

als

and

equi

p-m

ent.

Not

tobe

used

whe

rere

sist

ance

tofu

els,

oils

,or

hydr

aulic

fluid

sis

requ

ired

.C

heck

man

ufac

ture

r’s

in-

stru

ctio

nsfo

rpr

imer

requ

irem

ents

onth

em

etal

subs

trat

ebe

ing

seal

ed,

and

appl

yth

esp

ecifi

edpr

imer

befo

reap

-pl

ying

the

seal

ant.

Gro

upII

-H

igh

stre

ngth

Roo

mte

mp

cure

Gro

upII

I-

Hig

hte

mpe

ratu

reE

ach

grou

pha

stw

oty

pes.

Serv

ice

tem

p-7

0°to

+40

0°F

(-57

°to

+20

4°C

)fo

rG

roup

sI

&II

,an

d-7

0°to

+60

0°F

(-57

°to

+31

6°C

)fo

rG

roup

III

Type

I-

Thi

xotr

opic

past

ein

lbs

Peel

stre

ngth

:G

roup

I,Ty

peI:

15in

lbs

wid

th(m

in)

Type

II:

4in

lbs

wid

th(m

in)

Gro

ups

II&

III

(bot

hty

pes)

:40

inlb

sw

idth

(min

)Ty

peII

-Se

lf-l

evel

ing

liqui

dN

oco

rros

ion

inhi

bito

rsL

ong

shel

flif

eSh

ort

cure

time.

SAE

AM

S32

55,

Seal

ing

Tape

,Po

ly-

tetr

afluo

roet

hyle

ne,

Exp

ande

d(E

PTFE

)O

ilan

dW

ater

Res

ista

nt;

(Sky

flex(

®)

Cla

ss1:

Con

tinuo

usR

ibbe

d,in

-cl

udes

:Sk

yflex

®PN

’s:

Pref

orm

edga

sket

tape

with

noad

hesi

veon

eith

ersi

deex

cept

asno

ted

in“I

nten

ded

Use

”co

l-um

n;

Seal

ing

offa

ying

surf

aces

,ac

cess

/re-

mov

able

pane

ls,

floor

boar

ds,

and

win

dscr

eens

.N

otfo

rfu

elso

aked

orve

ryhi

ghte

mpe

ratu

reap

plic

atio

n.N

on-h

azar

dous

alte

rnat

ive

tolo

wad

-he

sion

,tw

oco

mpo

nent

seal

ants

.So

me

ofth

ese

seal

ing

tape

sha

vea

low

peel

stre

ngth

adhe

sive

onon

esi

deto

hold

the

tape

inpl

ace

onon

esu

rfac

ew

hile

the

mat

ing

part

isbe

ing

inst

alle

d.

GU

A-1

071-

1fo

rfa

ysu

rfac

es≤1

inw

ide

No

mix

ing,

mas

king

,or

curi

ngre

quir

edG

UA

-100

1-1

for

fay

surf

aces

&;g

t;1

inw

ide

Serv

ice

tem

p:-6

5°to

+45

0°F

(-54

°to

+23

2°C

)w

ithsh

ort

term

expo

sure

to60

0°F

(315

°C

)G

UA

-100

1-2

for

fay

surf

aces

&;g

t;1in

wid

ew

here

thic

ker

tape

isne

eded

tofil

lfa

ysu

rfac

ega

p

Peel

stre

ngth

:2

lb/in

wid

th(m

ax)

for

side

with

adhe

sive

only

GU

A-1

017-

1fo

rfa

ysu

rfac

es≤

1in

wid

eN

oco

rros

ion

inhi

bito

rs

GU

A-1

401-

1fo

rfa

ysu

rfac

es≤

1in

wid

ein

dry

area

sof

floor

boar

dsan

dw

here

ath

icke

rta

peis

need

edto

fill

fay

surf

ace

gaps

Res

ists

wat

er,

fuel

,oi

l,an

dhy

-dr

aulic

fluid

TO 1-1-691

6-7

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

GSC

-21-

8076

7-00

-fo

rfa

ysu

rfac

es<

1in

inhi

ghm

oist

ure

area

sof

floor

boar

dsan

dw

here

thic

ker

tape

isne

eded

tofil

lfa

ysu

rfac

ega

psC

lass

2:C

ontin

uous

Non

-Rib

bed,

incl

udes

:Sk

yflex

PN’s

GU

A-1

003-

1-co

mpe

nsat

ion

tape

ana

rrow

un-r

ibbe

dta

peus

edto

fill

irre

gula

ritie

son

ase

alin

gsu

rfac

eor

repa

irm

inor

dam

age

toa

pre-

viou

sly

appl

ied

tape

seal

GU

A-1

057-

1-fo

rfa

ysu

rfac

es<

1in

wid

e,us

edas

shim

/bar

rier

tore

-si

stm

inor

chafi

ngG

UA

-105

8-1(

for

fay

surf

aces

<1

inw

ide,

used

asa

shim

/bar

rier

tore

sist

min

orch

afing

GU

A-1

059-

1fo

rfa

ysu

rfac

es>

1in

wid

e,

used

assh

im/b

arri

erto

resi

stm

inor

chafi

ngG

UA

-130

1-1-

for

fay

surf

ace

<1

inw

ide

with

thic

kga

ps.

Av-

Dec

®H

iTak

®Po

lyur

etha

neTa

peSe

alan

t(P

NH

T39

35-7

-XX

X)

Pref

orm

edga

sket

tape

with

adhe

-si

veon

both

side

san

dth

inpo

ly-

ethy

lene

rele

ase

film

onon

esi

de

For

fay

surf

ace

seal

ing

ofar

eas

whe

reflu

idin

trus

ion

isa

prob

lem

such

asai

rcra

ftflo

orpa

nels

and

carg

otie

dow

nfit

tings

.Fo

rm

axim

umse

alin

g,re

mov

eth

ere

leas

efil

mfo

rad

hesi

onto

both

surf

aces

.Fo

rea

sier

pane

lre

-m

oval

and

max

imum

reus

abili

ty,

leav

eth

ere

leas

efil

min

plac

eon

the

side

cont

actin

gth

ere

mov

able

pane

l.D

amag

edse

ctio

nsof

the

tape

are

eas-

ilyre

pair

edas

itha

sve

rygo

odad

he-

sion

toits

elf.

-100

for

fay

surf

aces

≤1

inw

ide

No

mix

ing,

mas

king

,or

curi

ngre

quir

ed

-150

for

fay

surf

aces

&;g

t;1

inup

to1.

5in

wid

eSe

rvic

eTe

mp:

(85°

to+

275°

F(6

5°to

+13

5°C

)w

illw

ithst

and

shor

tno

n-co

ntin

uous

expo

sure

tohi

gher

tem

pera

ture

s

-200

for

fay

surf

aces

>1.

5in

upto

2in

wid

ePe

elSt

reng

th:

1-4

inlb

wid

th

TO 1-1-691

6-8

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

-250

for

fay

surf

aces

>2

inup

to2.

5in

wid

eN

oco

rros

ion

inhi

bito

rs

Res

ists

wat

er,

deic

ing

fluid

s,fu

el,

oil,

and

hydr

aulic

fluid

(inc

lud-

ing

Skyd

rol

LD

-4)

Av-

Dec

®H

iTak

®T

ufSe

alT

MPo

lyur

e-th

ane

Tape

Seal

ant

(PN

HT

3000

-X

XX

)

Pref

orm

edga

sket

tape

with

adhe

-si

veon

one

side

and

ape

rma-

nent

Teflo

n(

film

baki

ngon

the

oppo

site

side

For

fay

surf

ace

seal

ing

ofno

n-pe

rman

ent

stru

ctur

esu

chas

acce

ssan

din

spec

tion

pane

ls/c

over

son

air-

craf

t,m

issi

les,

and

equi

pmen

tto

pre-

vent

fluid

entr

yin

toth

efa

ying

surf

ace

area

san

dth

eca

vitie

sov

erw

hich

the

pane

ls/c

over

sar

ein

stal

led.

The

Teflo

n(

back

ing

ishi

ghly

abra

sion

resi

stan

tan

dpe

rmits

slig

htm

ovem

ent

ofth

eco

vers

with

out

dam

agin

gth

est

ruct

ure

tow

hich

itis

atta

ched

.T

heta

peis

very

dura

ble,

soit

may

bere

used

man

ytim

eson

ceit

isin

stal

led,

and

dam

aged

sect

ions

are

easi

lyre

pair

edas

itha

sve

rygo

odad

hesi

onto

itsel

f.

-100

for

fay

surf

aces

≤1

inw

ide

No

mix

ing,

mas

king

,or

curi

ngre

quir

ed-1

50fo

rfa

ysu

rfac

es>

1in

upto

1.5

inw

ide

Serv

ice

Tem

p:(8

5°to

+27

5°F

(65°

to+

135°

C)

-200

for

fay

surf

aces

>1.

5in

upto

2in

wid

ePe

elSt

reng

th:

2-5

inlb

wid

thad

-he

sive

side

only

,th

eot

her

side

has

ape

rman

ent

Teflo

n(

film

back

ing

No

corr

osio

nin

hibi

tors

Res

ists

wat

er,

deic

ing

fluid

s,fu

el,

oil,

and

hydr

aulic

fluid

(inc

lud-

ing

Skyd

rol

LD

-4)

Av-

Dec

®Se

lfL

evel

ingT

M(

Gre

en(P

NH

T33

26-5

-XX

X)

and

Thi

xofle

x(

Ora

nge

Inje

ctab

le(P

NT

F221

9)Se

alan

ts

Self

Lev

elin

g(G

reen

(for

fillin

gvo

ids

and/

orca

vitie

son

hori

zont

alsu

rfac

esw

here

ase

lfle

velin

gliq

-ui

dm

aybe

used

;su

pplie

din

ei-

ther

50cc

(-05

0)or

200

(-20

0)ca

rtri

dges

Two

com

pone

ntse

alan

ts;

both

are

supp

lied

indu

alsy

ring

esco

n-ta

inin

gth

ere

quir

edam

ount

sof

resi

nan

dha

rden

erfo

rm

ixin

gon

site

The

Self

Lev

elin

gTM

(Gre

ense

alan

tis

inte

nded

tofil

lvo

ids/

cavi

ties

onho

ri-

zont

alsu

rfac

essu

chas

airc

raft

seat

trac

kde

pres

sion

sto

prev

ent

fluid

sfr

omac

cum

ulat

ing

inth

eman

dca

us-

ing

corr

osio

nw

hile

still

bein

gea

sily

rem

oved

for

requ

ired

insp

ectio

nsan

d/or

oper

atio

nal

use.

Als

ous

eful

tofil

lca

vitie

sar

ound

ante

nna

conn

ec-

tors

.

Thi

xofle

xTM

Ora

nge

-fo

rfil

ling

void

s/ca

vitie

son

hori

zont

al,

vert

i-ca

l,or

over

head

surf

aces

whe

rea

past

em

ater

ial

isre

quir

ed;

sup-

plie

din

50cc

cart

ridg

es

Mix

ing

and

disp

ensi

ngis

acco

m-

plis

hed

with

acce

ssor

ies

ob-

tain

edfr

omth

eve

ndor

per

the

vend

or’s

inst

ruct

ions

Serv

ice

Tem

p:-6

0°to

+26

0°F

(-51

°to

+12

7°C

)(

eith

erty

pe

TO 1-1-691

6-9

Tabl

e6-

1.Se

alin

gC

ompo

unds

-C

onti

nued

Spec

ifica

tion

Type

sA

vaila

ble

Prop

ertie

sIn

tend

edU

se

Peel

Stre

ngth

:bo

th1-

4in

lbw

idth

The

Thi

xofle

xTM

Ora

nge

seal

ant

isin

-te

nded

for

fillin

gth

esa

me

void

s/ca

vi-

ties

asab

ove

asw

ell

asth

ose

onve

r-tic

alan

dov

erhe

adsu

rfac

esw

hile

still

bein

gea

sily

rem

oved

for

requ

ired

insp

ectio

nsan

d/or

oper

atio

nal

use.

No

corr

osio

nin

hibi

tors

Res

ists

wat

er,

deic

ing

fluid

s,fu

el,

oil,

and

hydr

aulic

fluid

(inc

lud-

ing

Skyd

rol

LD

-4).

TO 1-1-691

6-10

6.3.4 Adhesion Promoters.

Solvent based adhesion promoters are hygro-scopic (absorb moisture) and must be kept awayfrom moisture. Discard material if it becomescloudy or a precipitate is formed.

Some sealing compounds may require the application of aspecial primer or adhesion promoter prior to sealant applica-tion in order to develop a good adhesive bond with thesurface. Use only those primers or adhesion promotersrecommended by the manufacturer for their product. Thesematerials are especially important for MIL-S-85420, SAEAMS-S 29574 (refer to MIL-S-29574) and some siliconebased sealants. Refer to Appendix A for a listing anddescription of adhesion promoters.

6.3.5 SAE AMS 3255 Oil and Water Resistant, Ex-panded Polytetrafluoroethylene Sealing Tape (EPTFE)Skyflex. The sealant tape consists of an extruded gasket(most of the time with several protruding ribs) with a pressuresensitive adhesive backing. No mixing is required and thereare no application life constraints or cure times involved. Thesealing tape does not require removal and replacement unlessdamaged. The adhesive backing is only required to hold thesealing tape in place until an access panel, floor panel, orcomponent is (re)installed. Tapes may be special orderedwithout adhesive backing for use in areas where fluidexposure (e.g. hydraulic fluid or fuel) is expected and appliedwith a fluid resistant rubber cement. Refer to Table 6-1 for ageneral description of these tapes.

NOTE

Use of the EPTFE (Skyflex) sealing tape requiresauthorization from the aircraft SPD or the missileor equipment SPM engineering authority.

6.3.6 Av-Dec® Polyurethane Sealant Tapes and TwoComponent Sealants. Av-Dec® sealing tapes are pre-cured polyurethane gasket tapes with the HT3935-7 serieshaving a tacky adhesive on both sides and the HT3000 serieshaving a tacky adhesive on one side and a permanent Teflonfilm backing on the other side. These tapes require no mixing,have unlimited application life, and require no cure time. TheHT3995-7 series tapes are particularly useful for sealing highmoisture areas such as aircraft floor panels. The HT3000series are useful for sealing frequently removed inspectionand access panels, since once applied they are totally reusableunless damaged; damaged areas only may be removed andreplaced. The HT3326-5 Self Leveling Green liquid and

TF2219 thick orange paste materials are two componentcurable sealants that are particularly useful in filling voidsand cavities to prevent moisture and fluid accumulation andsubsequent corrosion damage in areas where ease of removalfor inspection and/or operational requirements is necessary.

6.4 EQUIPMENT.

The following equipment is available:

NOTE

Avoid air bubbles as much as possible during thefilleting operation. Allow the sealant to cure to, atleast, the tack-free stage before moving theassembly.

6.4.1 Sealant Gun. The Semco® Model 250-A or itsequivalent (Figure 6-1), fitted with one of the nozzles fromFigure 6-2 is used for the application of fillet seals. Whenusing this gun, the nozzle tip must be pointed into the seamand maintained at a 45 degree angle to the line of travel,forcing the bead of sealing to precede the gun tip to minimizeentrapment of air. Use fairing/smoothing tools (i.e., spatulasand spreaders) shown in Figure 6-5 to work sealants andadhesives into seams.

6.4.2 Application Nozzles.

Care should be taken when using rivet nozzles toprevent sealant material from filling fastenerholes.

In addition to the standard, fillet, and ribbon nozzles in Figure6-2, the countersink and rivet nozzles in Figure 6-3 andFigure 6-4, respectively, can also be used with sealant guns.Countersink nozzles can be used to apply sealants into thecountersink of fastener holes prior to fastener installation.Rivet nozzles are suitable for use to apply sealants intocountersink and through hole prior to fastening part(s) withrivets. The rivet nozzles have a spring-loaded tip. It serves asa check valve and allows for dispensing the precise amount ofsealant material.

6.4.3 Injection Gun. Figure 6-6 illustrates two types ofinjection guns used for injecting sealant into confined holes,slots, structural voids, joggles, etc. Follow the proceduresoutlined in the applicable aircraft, missile, or equipmentsystem specific maintenance manual and the injection gunmanufacturer’s operation instructions for the proper prepara-tion and use of these guns. For hard to reach areas, attach anextension nozzle to the injection tip.

TO 1-1-691

Change 1 6-11

Figure 6-1. Pneumatic Sealant Gun

TO 1-1-691

6-12

Figure 6-2. Sealant Application Nozzles

TO 1-1-691

6-13

Figure 6-3. Countersink Application Nozzles

TO 1-1-691

6-14

Figure 6-4. Rivet Application Nozzles

TO 1-1-691

6-15

Figure 6-5. Sealant and Adhesive Smoothing Tools

TO 1-1-691

6-16

6.4.4 Sealant Kits (Semkits®).

Before using sealant materials, refer to the sealantMaterial Safety Data Sheet (MSDS) for informa-tion on handling precautions.

Certain types of sealants, such as SAE AMS-S-8802 (MIL-S-8802) and MIL-PRF-81733, are available as ready to usekits (Semkits®). These kits are compact, two-part mixingapplication units designed for convenient storage, easy mix-ing, and proper application of the sealant in small quantities.The base component of the sealant is packed in standard 2-½ounce and 6 ounce cartridges which are placed in a filletinggun or injection gun for application after mixing with theaccelerator/catalyst. There are two styles: the Barrier Style,

which holds proportioned amounts of the two componentsseparated by an aluminum barrier disc; and the InjectionStyle, which stores the accelerator/catalyst material withinthe injection rod to separate it from the base compound priorto use (Figure 6-7). When using Semkits®, note that thehandle or the injection/dasher rod contains a pre-measuredamount of accelerator/catalyst and should be retained untilthe ramrod has been operated to break the seal at the bottomof the injection/dasher rod releasing the accelerator/catalystinto the base component and mixing is completed. All of thematerials contained inside these two-component Semkit®packages are mixed within the cartridges. Follow the manu-facturer’s recommended storage instructions for these Sem-kits®.

6.4.5 Sealant Removal and Application Tools. Themost commonly used tools for removing or fairing outsealants are shown in Figure 6-5. Other tools may be

Figure 6-6. Sealant Injection Guns

TO 1-1-691

6-17

manufactured as needed to fit a specific situation. Only plasticshall be used to manufacture these sealant removal andapplication tools. The Pneumatic Vibro Gun Sealant RemovalKit may also be used.

6.5 SEALANT MIXING.

The proper weighing and mixing of components is essentialto assure proper curing and adhesion of sealants. Use anappropriate weight scale (refer to Appendix B) to accuratelymeasure the materials before blending. Accomplish all mix-ing in one designated central area in each organization.Polysulfide and polythioether sealants consist of two sepa-rately packaged components, a base compound (usually partB) and an accelerator/catalyst (usually part A) in ½ pint (6

oz), pint (12 oz), and quart (24 oz) kits. The base-to-accelerator/catalyst ratio varies with different manufacturersof the same type of sealant. It is important, therefore, to mixthe material according to the manufacturer’s instructionsrecommendations. Add accelerator/catalyst into the base inthe correct ratio and mix until a uniform color is obtained.Difficulties with curing and/or adhesion of poly-sulfide andpolythioether sealants are frequently caused by incompletemixing. Two component sealants are chemically cured and donot depend on solvent evaporation for curing. Slow handmixing is recommended for two-component can type kits. Ahigh speed mechanical mixer should not be used as internalheat will be generated thus reducing application life andintroducing air into the mixture. Refer to Figure 6-7 forinjection style Semkit® mixing instructions.

Figure 6-7. Injection Style Semkit®

TO 1-1-691

6-18 Change 1

6.5.1 Application Life. Application life and cure timesare dependant on environmental considerations. The applica-tion life of a sealant is the length of time that a mixed sealingcompound remains usable at 77° F (25° C) and 50 percentRelative Humidity (RH). This time (in hours), known as adash number, is denoted as the last number in a sealantdesignation (e.g. MIL-PRF-81733, Type II-2 has an applica-tion life of two hours). Table 6-2 indicates application times,tack-free times, and full cure times for each sealant type anddash number at 77° F ( 25° C) and 50% RH. For each 18°sF(10°sC) increase in the temperature above 77° F (25° C), theapplication, tack-free, and cure times are shortened by ap-proximately one-half; while for each 18°sF (10°sC) decreasein the temperature below 77° F (25° C), the application,tack-free, and cure times are lengthened by approximatelyon-half. For each 15% increase in RH above 50%, theapplication, tack-free, and cure times are shortened by ap-proximately one-half; while for each 15% decrease in RHbelow 50%, the application, tack-free, and cure times arelengthened by approximately one-half. Maintenance person-nel should be aware of the effects of temperature andhumidity on the application life of a sealant. Mix only theamount of material that can be applied during the rated worklife of the sealant.

6.5.1.1 Enhancement of Sealant Curing. There areseveral corrective measures that can be used to prevent and/orlessen sealant curing problems caused by various environ-mental conditions.

a. At a relative humidity of 30% RH or lower (sometimeseven 40% RH causes a problem), it is very difficult toproperly cure sealants. When these conditions are expe-rienced, adding water vapor to the air to increase thehumidity by either wetting down the floor of the facility,covering the area being sealed with a wet cloth withoutit touching the sealant surface and keeping the cloth wetduring the cure cycle, or some other convenient methodwill eliminate the problem.

Do not apply heat to sealants until 30 minutesminimum have elapsed at ambient temperatureafter application to allow the contained solventsto flash off. Most solvents are flammable andcould catch fire if the sealants are exposed tohigher temperatures before the solvents flash off.

NOTE

If sealants are heated to a temperature of 110° F(43° C) or greater as noted in Paragraph 6.5.1.1.bbelow no adjustment to the humidity is required.

b. Except for MIL-S-85420 and MIL-S-29574 (SAE AMS-S-29574) sealants that are designed to cure properlywith good adhesion at low temperatures, sealant curingis extremely slow when applied at ambient air tempera-tures of 50° F (10° C) and below and adhere very poorlyto metal structure having a surface temperature of 60° F(16° C) and below due to poor surface wetting proper-ties at the time of application. These problems can beeliminated by preheating the metal surfaces to which asealant will be applied to a temperature of 60° F (16° C)or higher and/or heating the sealant to a temperature of130° F ±10° F (54° C ±6° C) after application with hotair, infrared lamps, or some other approved method afterallowing the sealant to stand for minimum of 30 minutesat ambient temperature after it is applied to flash off itscontained solvents.

c. If sealants are applied to metal surfaces having a surfacetemperature of 100° F (37° C) or at ambient airtemperatures of 95° F (35° C) or greater, will very likelyhave bubbles in the cured sealant film, commonly called“solvent pop” due to too rapid evaporation of thesolvents contained in the sealant. Cool the metal surfacedown to a temperature of 90° F (32° C) or lower bywetting it down with water and then wiping the surfacedry or by some other approved method and/or relocatethe equipment to which sealant is to be applied to anarea having an ambient temperature of 90° F (32° C) orlower prior to applying the sealant and keep the equip-ment in this cooler condition for a minimum of 30minutes to allow the contained solvents to flash offbefore relocating the equipment in a hotter area orapplying heat to the sealant.

d. Sometimes sealant must be applied in areas where othermaintenance is being accomplished which leads tosealant smears in the area caused by walking on and/ordragging tools through sealant that is not completelycured. To minimize this problem, apply a polyethylenefilm over the uncured sealant after allowing a minimumof 30 minutes at ambient temperature after it is appliedto flash off its contained solvents and permit the film toremain in place until the sealant has completely cured.

Table 6-2. Time Requirements for Sealants When Used At 75 Degree F (24 Degree C) and 50 Precent RH

SpecificationType orClass1

AssemblyTime (Hr)

Tack-FreeTime (Hr)

ApproximateFly Away Time

(Hr) Application Method(s)

MIL-PRF-81733

I, CL 2-¼ - 4 - Brush

TO 1-1-691

Change 1 6-19

Table 6-2. Time Requirements for Sealants When Used At 75 Degree F (24 Degree C) and 50 Precent RH - Con-tinued


AssemblyTime (Hr)

Tack-FreeTime (Hr)



(SupersedesMIL-S-81733)

I-½ CL1-16CL2-8

- Brush

I-2 - CL1-24CL2-16

- Brush

II, CL 1-1/16 - 4 - Gun or spatulaII-¼ - CL1-8 CL2-1 - Gun or spatulaII-½ - CL1-16

CL2-2- Gun or spatula

II-2 - CL1-24CL2-12

- Gun or spatula

II-4 - 32 - Gun or spatulaIII-1 - 8 - SprayIV-4 8 40 - Brush or spatulaIV-12 24 120 - Brush or spatulaIV-24 48 180 - Brush or spatulaIV-40 120 600 - Brush or spatulaIV-48 168 1008 - Brush or spatula

SAE AMS-S-8802

A-½ - 10 40 Brush

(SupersedesMIL-S-8802)

A-1 - 20 55 Brush

A-2 - 40 72 BrushB-½ - 10 30 Gun or spatulaB-1 - 20 55 Gun or spatulaB-2 - 40 72 Gun or spatulaB-4 - 48 90 Gun or spatulaC-12 12 - - Brush or spatulaC-20 20 96 - Brush or spatulaC-80 80 120 - Brush or spatulaC-96 96 - - Brush or spatula

AMS 3276 A-½ - 10 30 Brush(Supercedes

MIL-S-83430)

A-2 - 24 72 Brush

A-4 - 36 90 BrushB-¼ - 6 16 Gun or spatulaB-½ - 10 30 Gun or spatulaB-1 - 12 36 Gun or spatulaB-2 - 24 72 Gun or spatulaB-4 - 36 90 Gun or spatulaB-6 - 48 120 Gun or spatulaB-12 - 120 240 Gun or spatulaC-½ - 10 30 Brush or spatulaC-2 - 24 72 Brush or spatula

TO 1-1-691

6-20 Change 1



AssemblyTime (Hr)

Tack-FreeTime (Hr)



C-8 20 96 120 Brush or spatulaD-¼ - 6 16 Gun or spatulaD-½ - 10 30 Gun or spatulaE 6 120 240 Used w/auto rivet equip.

PR-1773 (Su-percedesPR-1403G)

B-½ - 4 6 Gun or spatula

PRC-DeSotoInt.

B-2 - 8 16 Gun or spatula

AMS 3267 /1 A-½ - 10 24 Brush(Supersedes

MIL-S-8784)

/3 A-2 - 24 72 Brush

/2 B-½ - 10 24 Gun or spatula/4 B-2 - 24 72 Gun or spatula

AMS 3374 /1 1 -N/A - 6 14 days Gun or spatula(Supersedes /2 2 -4 - 24 7 days or 1day

@ 120° F(49° C)

Gun or spatula

MIL-S-38249) /3 3 -4 - 6 14 days Gun or spatula/4 4 -½ - 2 7 days Gun or spatula

MIL-S-85420 Ty I, ClA-1/6

- 2 (ST), 4(LT)2

4 (ST), 8 (LT)2 Brush

Ty I, ClB-1/6

- 2 (ST), 6(LT)2

4 (ST), 8 (LT)2 Gun or spatula

Ty II,ClA-1/6 - 2 (ST), 4(LT)2

4 (ST), 6 (LT)2 Brush

Ty II,ClB-1/6 - 1¼ (ST), 4(LT)2

4 (ST), 6 (LT)2 Gun or spatula

AMS-S-29574 A-¼ - 1 / 3 / 63 1.5 / 4 / 83 Brush(MIL-S-

29574)A-½ - 1.5 / 3 / 63 3 / 8 / 163 Brush

A-2 - 9 14 BrushB-¼ - 1 /3 / 63 1.5 / 4 / 83 Gun or spatulaB-½ - 2 / 6 / 63 3 / 8 / 163 Gun or spatulaB-2 - 9 14 Gun or spatulaC-4 8 - 24 Brush or spatula

MIL-A-46146 Gp I, Ty I - 5 - Gun or spatulaGp I, Ty II - 5 - PourGp II, Ty I - 5 - Gun or spatulaGp II, Ty II - 5 - PourGp III, Ty I - 5 - Gun or spatulaGp III, Ty II - 5 - Pour

TO 1-1-691

Change 1 6-21



AssemblyTime (Hr)

Tack-FreeTime (Hr)



AMS 3255-EPTFESealingTape (Sky-flex®)

Class 1 - 0 0 Peel and Stick

Av-DECTM

HT3935-7& HT3000Series

Class 2 - 0 0 Peel and Stick

PolyurethaneSealingTapes

- - 0 0 Peel and Stick

Av-DECTM

InjectablePolyure-thane Seal-ants

SelfLevel-ingTM

Green,HT3326-5

<20 (minutes) 45 (minutes)max

- Gun with syringe

ThixoflexTM

Orange,TF2219

<3 (minutes) 7 (minutes)max

- Gun with syringe

1 The number after the dash (-) indicates the room temperature working life of the sealant after it is mixed.2 (ST) =Standard Temperature of +75° F (+24° C); (LT) = Low Temperature of +45° F (+7° C).3 1st # @ +75° F (+24° C); 2nd # @ +40° F (+4° C); 3rd # @ +20° F (-7° C).

TO 1-1-691

6-22 Change 1

6.5.2 Storage Instructions. When large quantities ofsealants are used, such as for depot level maintenanceoperations, it may be advantageous to premix and freezesealants to provide a ready supply of mixed sealants whenthey are needed. Store two-part kits and Semkit® packagesealants according to instructions on the container. Storepolysulfide sealants in a pre-mixed and frozen (PMF) form ina freezer at -40° F (-40° C) or below for retention of optimalapplication properties and shelf life. Polythioether sealantsrequire extremely low temperature refrigeration at -80° F(-62° C) or below for optimal retention of applicationproperties and shelf life. Thawing of PMF sealants can beaccomplished in two ways. For ambient temperature thaw,place the PMF cartridge in a vertical position. Let stand at+70° to +80° F (+21° to +27° C) approximately 30 minutes.Dry any condensation from the exterior of the cartridge priorto use. For water bath thaw, place the PMF cartridge uprightin a +120° F (49° C) water bath for approximately 4 to 6minutes. Upon removal from the bath, carefully dry theexterior of the cartridge before using.

6.5.3 Mixing MIL-PRF-81733, Type III Spray-ableSealant Coating. The base component (Part B) of MIL-PRF-81733, Type III has a tendency to settle out duringstorage, so it requires thorough mixing with a standard paintshaker to obtain a uniform consistency before the addition ofthe accelerator component (Part A). The accelerator compo-nent (Part A) requires hand shaking or stirring with a woodstir paddle/stick in its container to obtain a uniform consis-tency before adding it to the base component (Part B). Afterboth components, base and accelerator, have been stirred/mixed separately, add the proper amount of the accelerator tothe base in its container and mix the combined materials,preferably with a paint shaker for 3 minutes in an uprightposition followed by 3 minutes in an inverted position for kitsup to 1 gallon, and for 5 to 10 minutes with an air drivenagitator in a pressure pot for kits greater than 1 gallon. Forproper application life and cure, the base and accelerator mustbe combined in the proper ratio and mixed prior to theaddition of any thinner (solvents). After mixing, the sealantmay be thinned for spraying to a viscosity of 20 to 25 secondsin a No. 2 Zahn cup (refer to TO 1-1-8 ) with a 20 to 30% byvolume addition of a 50% by volume mixture of MEKconforming to ASTM D 740 and Toluene conforming toA-A-59107, and stirring for 2 minutes with an air drivenagitator at 70 RPM.

6.6 SEALANT APPLICATION PROCEDURES.

• Solvents are flammable. Never use near igni-tion sources, i.e. lighted cigarettes, electricalarcing, heat sources, etc.

• When cleaning an area prior to applying asealant, apply a small amount of solvent to aclean cloth, wipe the surface, and follow bywiping with a clean, dry cloth. Immediatelyafter use, place used rags into an appropriateHAZMAT container, and then dispose of perlocal directives. This minimizes exposure ofpersonnel to and release of solvent vapors intothe environment.

• Sealants, with the exception of SAE AMS3255 (Skyflex®) EPTFE and Av-Dec® sealanttapes, are toxic to the skin, eyes, and respira-tory tract. Wear rubber or polyethylene glovesand chemical proof goggles and/or face shieldwhen using these materials, and make sureventilation is adequate in the area where theyare used. Wash hands thoroughly with soapand water before eating or smoking.

• MIL-PRF-81733 is not suitable for use on theinterior of integral fuel tanks and shall not beused for these applications. SAE AMS-S-8802(MIL-S-8802) and SAE AMS-S-29574 (MIL-S-29574) are the authorized sealants for theinterior of integral fuel tanks.

• No RTV sealant which produces acetic acidsuch as those conforming to MIL-S-46106shall be used on aircraft. No RTV sealant shallbe used in areas where exposure to fuels andoils will be encountered. If RTV sealants arerequired by the structural repair manual, en-sure that the sealant conforms to MIL-A-46146, Adhesives/Sealants, Silicone, RTV,Noncorrosive (for use on sensitive metals andequipment), and/or is listed in Appendix A asbeing a non-corrosive RTV silicone sealant.

TO 1-1-691

Change 1 6-22.1/(6-22.2 blank)

• SAE AMS-S-8802 (MIL-S-8802) sealantshould not be exposed to fuel or overcoateduntil it is tack-free as it will not cure properly.SAE AMS-S-8802 is used to fillet and brushseal on the inter-ior of integral fuel tanks only.

• Do not use AMS 3267 (MIL-S-8784) sealantin high temperature areas or for permanentstructural installations. These sealants have nohigh temperature resistance and very low peelstrength. Some typical uses of SAE AMS 3267(MIL-S-8784) sealants include sealing aircraftfloor panels and plates, and fuel tank inspec-tion plates.

6.6.1 Cleaning. If the surfaces have been contaminatedfollowing corrosion removal and surface treatment per in-structions in Chapter 5, clean the area with a clean CCC-C-440, Type I or II, Class 2 cheesecloth; an AMS 3819A, Class2, Grade A cleaning cloth; or a CCC-C-46, Type I, Grade 7non-woven cleaning cloth saturated with either A-A-59281,Type I or AMS 3166 solvent. Begin at the top of the area tobe sealed and work downward. Dry the surfaces immediatelywith a clean cloth. Do not allow solvent to evaporate from thesurface because it will allow some or all of the oil, dirt, etc.to redeposit, making it impossible to remove with a dry cloth.Use a stiff bristle brush to clean around bolts, rivets, etc.Always use clean cloth as each new area is cleaned.

NOTE

Always pour solvent on the cloth to avoid con-taminating the solvent supply. Reclaimed sol-vents or soiled cleaning cloths shall not be used.After surface treatment, do not contaminate areasto be sealed with soiled hands or tools.

6.6.2 Masking. To prevent sealant from contacting ad-jacent areas during application and smoothing out operations,the surrounding area not being sealed can be masked off withAMS-T-21595, Type I masking tape (Figure 6-8). In caseswhere the tape is likely to remain in place for more than twodays on items exposed to direct sunlight and where taperesidue on the surface cannot be tolerated, use AMS-T-22085,Type II (3M Co. PN 481 or 225) preservation and sealingtape. Masking tape is very useful during fillet sealing ofexterior surface lap and butt seams.

6.6.3 Adhesion Promoters. In some cases, it may benecessary to improve the adhesion of sealants by the use ofadhesion promoters. Adhesion promoters are solvents that

contain additives which leave a residue on the surface aftersolvent evaporation to promote adhesion. To apply, clean thearea per Paragraph 6.6.1, brush or wipe the surface to besealed with the liquid solution, and allow the treated surfaceto dry by evaporation without touching the treated areas for30 minutes to an hour before applying sealant. AMS 3100adhesion promoter (PN: PR-148 or PR-182) is essential torepairing integral fuel tanks where new polysulfide sealantwill be applied over aged, fuel soaked polysulfide sealant. Ifa polythioether sealant is to be applied over a polysulfidesealant, PN PR-186 is recommended for use at the sealantinterface. If the surface becomes contaminated or sealant isnot applied within two hours after applying an adhesionpromoter, re-clean the area and reapply the adhesion pro-moter per the above instructions. Refer to Appendix A forinformation relative to purchasing/ordering these adhesionpromoters.

6.6.4 Brush Spatula or Caulking Gun Application.Prior to masking and sealing, prepare and clean the surface inaccordance with Paragraph 6.6.1.

Do not contaminate areas to be sealed with hands,tools, etc. after surface treatment and primerapplication.

6.6.4.1 To prevent sealant from contacting adjacent areasduring application and smooth out, outline the areas beingsealed with masking tape (AMS-T-21595, Type I) so that eachtape strip is 1/16 to 3⁄8 in from the edge of butt seams and theupper surface edge of a lap seam, and ¼ to 3⁄8 in from thelower surface edge of a lap seam. If tape residue on thesesurfaces is excessive, remove adhesive residues using TT-N-95 aliphatic naphtha. Masking may be very beneficialduring fillet sealing of exterior surface lap seams and fillingexterior surface butt seams.

6.6.4.2 Apply sealant between the pieces of tape.

6.6.4.2.1 Thick sealants may be applied with a non-metallic spatula or spreader to fillet seal lap seams or flush fillbutt seams as shown in Figure 6-8. Avoid the entrapment ofair. Work sealant into recesses by sliding the edge of thespatula firmly back over recesses. Smoothing will be easier ifthe non-metallic spatula is first dipped in water.

6.6.4.2.2 Brushable sealants are applied with a brush andsmoothed until the desired thickness is reached.

TO 1-1-691

Change 1 6-23

6.6.4.2.3 Thick sealants may be applied with a caulkinggun, and if done carefully, will not usually require masking.This method is especially adaptable to filling seams or theapplication of form-in-place gaskets. On exterior surfaceswhere aerodynamic smoothness is required, masking is nec-essary to allow smoothing the sealant after applicationwithout smearing it onto surrounding surfaces.

6.6.4.3 Remove masking tape after the sealant has beenapplied and before it begins to set. Cure time depends on theapplication life of the sealant materials used, the temperature,and the RH. When sealant no longer feels tacky, prime andtopcoat as necessary and required by system specific techni-cal data per application instructions in TO 1-1-8.

6.6.4.4 d. Remove all uncured sealant residue by wipingthe area with an SAE AMS 3819A, Class 2, Grade A orequivalent cleaning cloth wetted with a liquid product knownas Sky Wash® distributed by AeroSafe Products Inc. andwiping dry with a clean, dry cloth of the same type.

NOTE

MEK conforming to ASTM D 740 may be usedas an alternate solvent for cleaning up uncuredsealant residues as long as it is not environmen-tally prohibited and the aircraft SPD and/or themissile or equipment SPM approves its use andrequires it in system specific technical data.

6.6.5 Spray Gun Application. Prior to masking andsealing, prepare surface in accordance with Paragraph 6.6.1.

If any dirt or oil residues accumulate after con-version coating, clean thoroughly with solvent toensure adequate adhesion of paint, primer, andsealant.

a. Mask off adjacent areas with either MIL-PRF-121, TypeI or II, or MIL-PRF-131, Class 1 barrier material held inplace with AMS T-21595, Type I masking tape tominimize overspray on adjacent areas.

b. Apply MIL-PRF-81733, Type III sprayable sealant in asolid, continuous pattern per the manufacturer’s instruc-tions and TO 1-1-8.

NOTE

The dry film thickness (DFT) of spray sealantcoatings shall be in the range of 3 to 5 mils (0.003to 0.005 in ).

6.6.6 Peel and Stick Application; AMS 3255 EPTFESkyflex® and Av-Dec® HT3935-7 and HT3000 SealingTapes. Prior to application, prepare surface in accordancewith Paragraph 6.6.1.

After surface treatment and any required primerapplication, do not contaminate areas to be sealedwith soiled hands or tools as contaminationprevents proper sealing tape adhesion.

6.6.6.1 Examine faying surfaces to be sealed and build upany uneven areas on the aircraft, missile, or equipment frameflange. Use Skyflex® PN GUA-1003-1 compensation tape ora small piece of the same type of Skyflex® tape that will beused for AMS 3255 sealing tape applications and a smallpiece of the same type of Av-DECTM tape that will be usedfor HT3935-7 and/or HT3000 sealing tape applications. Thiswill create a level faying surface for panel sealing.

6.6.6.2 Select the proper PN sealant tape so that it willcover the full width of the faying surface to be sealed. Tapemay be applied to either the aircraft, missile, or equipmentframe flange or to the panel faying surface.

a. Measure and cut the required length of sealant tape.

Figure 6-8. Non-metallic Spatula

TO 1-1-691

6-24 Change 1

b. For corners, cut the ends of the tape at a 30 degree angleso that the sealant tape from the converging side willoverlap by one-quarter to one-half inch. Do not fold thetape in corners as this will result in triple layer thickness.

Use care not to pull or stretch the sealant tape asit is applied. The stretched AMS 3255 EPTFEand Av-Dec® HT3000 tapes will retract even ifclamped between faying surfaces, and the Av-Dec® HT3935-7 tapes will be reduced in thick-ness. In either case, inadequate sealing mayresult.

c. Peel the non-stick backing paper off the sealant tape alittle at a time as the tape is applied to the aircraft,missile, or equipment frame flange or mating panelsurface.

NOTE

• Applying a small amount of extra pressure tothe upper surface of the sealant tape will causethe pressure sensitive adhesive to adhere betterto the faying surface on which it is beingapplied, and it will create indentations/discol-oration at the fastener holes allowing for easierlocation/identification. If done with Av-DEC®3935-7 sealant tapes, it must be done beforethe non-stick backing paper is removed.

• If an AMS 3255 sealant tape without a pres-sure sensitive adhesive backing has been or-dered for use in areas where fluid exposure isexpected, 3M Co. PN Scotchgrip® 847 or1099 plastic adhesive (refer to Appendix A)may be used to hold the sealing tape in placeduring panel installation.

d. After applying the full length of the sealant tape, runfingers back and forth on the upper surface of the sealanttape to press the tape against the aircraft, missile, orequipment frame flange or the access panel surface topromote adherence of the adhesive.

NOTE

For Av-Dec® HT3935-7 sealant tapes, this mustbe done before the non-stick backing is removed.

e. Puncture all fastener holes using an object with a sharppoint such as an awl or a scribe.

NOTE

As fasteners are installed, the sealant materialpushed into the fastener holes will help to sealagainst moisture intrusion.

f. Install the access door/panel.

NOTE

No curing time is required. All fasteners shouldbe wet installed with MIL-PRF-16173, Grade 4;MIL-PRF-63460 CPC material specified in thespecific aircraft, missile, or equipment systemspecific maintenance manual.

6.7 SEALING OF SPECIFIC AREAS.

6.7.1 Faying Surface Sealing. Faying surfaces aresealed by applying sealants to the connecting surfaces of twoor more parts (refer to Figure 6-9). It is a very effective sealand should be used for all assembly or reassembly. Whenpossible, it should be used in conjunction with fillet sealing.There are two types of faying surface seals: removable andpermanent. Removable seals are used around access doors,removable panels, inspection plates, etc. A removable sealcan be formed using a low adhesion sealant that adheres toboth surfaces, or by using a high adhesion sealant thatadheres to one surface and a parting agent on the matingsurface. Permanent seals are created using high adhesionsealants between permanently fastened structures. To create apermanent seal, coat either one or both mating surfaces witha high adhesion sealant before assembling the parts and thenassembling them while the sealant is still wet. Apply enoughsealant to force a bead to squeeze out along the joint afterassembly, and also install all fasteners wet with the sealant.Assemble parts within the rated application life and/orassembly life of the sealant while taking into account theeffects of temperature and humidity on these times.

6.7.1.1 For permanent structure, all faying surfaces,seams, and lap joints outside of fuel wet and high temperatureareas shall be protected with MIL-PRF-81733, Type II or IV,Class 1 or 2, Grade A sealant. Apply the sealing compound toone or both surfaces and squeeze the part together to ensurethe complete coating of the entire mating or faying surface.Excess material squeezed out shall be removed so that thefillet remains at the joint edges. The fillet width shall not beless that ¼ inch. For seams, the sealant shall fill the seamentirely up to flush with the surface. Joint, joggle, or cavityareas which could hold water shall be filled with MIL-PRF-81733, Type II, Class 1 or 2, Grade A, SAE AMS-S-8802,Class B, or SAE AMS-3276, Class B sealant.

6.7.1.2 If sealing is impossible because of mechanical orother factors, prime both surfaces with two coats of MIL-PRF-23377, Type I, Class C epoxy primer or TT-P-2760,Type I, Class C polyurethane primer per instructions in TO1-1-8.

6.7.1.3 Faying surfaces that are to be adhesive bondedshall be treated and processed as specified by the approvedbonding procedure in the applicable system specific mainte-nance manual.

TO 1-1-691

Change 1 6-25

6.7.1.4 On faying surfaces, seams, or joints which requiredisassembly for maintenance, either SAE AMS 3267 or PN:PR-1773 low adhesion sealant shall be used (PN: PR-1773sealant contains non-chromate corrosion inhibitors).

NOTE

SAE AMS 3255 (Skyflex®) sealing tapes orAv-Dec® HT3935-7 and HT3000 sealing tapesmay be used in lieu of the low adhesion curingtype sealants in many removable joint areasrequiring periodic disassembly for maintenancewhen approved by the aircraft SPD and/or themissile or equipment SPM.

6.7.1.5 On plastic components, the joints shall be suitablysealed and faired into the adjacent surfaces with MIL-PRF-81733, Type II or IV, Class 1 or 2, Grade A, SAE AMS-S-8802, Class B, or SAE AMS-3276 sealant, unless otherwise

specified in the applicable system specific maintenancemanuals, to stop the formation of pockets which will entrapmoisture, dirt, etc.

NOTE

MIL-PRF-81733, Type II or IV, Class 1 or 2,Grade A sealant shall be used for rivets thatrequire wet installation on plastic components.

6.7.2 Fillet Sealing. The fillet, or seam, as shown inFigure 6-10, is the most common type found on an aircraft,missile, or piece of equipment. Fillet seals are used to coverstructural joints or seams along stiffeners, skin butts, walls,spars, and longerons, and to seal around fittings and fasteners.This type of sealing is the most easily repaired. It should beused in conjunction with faying surface sealing and in placeof it if the assembly sequence restricts the use of fayingsurface sealing.

6.7.3 Injection Sealing. This type of seal, as shown inFigure 6-11, is used primarily to fill voids created bystructural joggles, gaps, and openings. Use only those seal-ants recommended by the aircraft, missile, or equipmentmanufacturer. Force sealant into the areas using a sealant gun.This method is a means of producing a continuous seal whereit becomes impossible to lay down a continuous bead of

sealant while fillet sealing. Clean the voids of all dirt, chips,burrs, grease, and oil before injection sealing.

6.7.4 Fastener Sealing. Figure 6-12 illustrates tech-niques used to seal different types of fasteners. Fasteners aresealed either during assembly or after assembly. Install them

Figure 6-9. Faying Surface Sealing

TO 1-1-691

6-26 Change 1

wet with sealant in accordance with requirements in theapplicable system specific maintenance manual for fastenersin permanent structures. To seal during assembly, apply thesealant to the hole or dip the fastener into sealant, and installfastener while sealant is wet. For removable parts, coat thelower side of the fastener head only. Do not coat the hole orthe fastener shank or threads, as this makes future removalalmost impossible without damage to the part. To seal afterassembly, cover the pressure side of the fastener with sealantafter installation. Corrosion damaged areas in the counter-sinks around removable and fixed fasteners may be filled withthe fastener in place. Cadmium coated fasteners that havebeen blasted or abraded during corrosion removal shall beprimed in accordance with the applicable system specificmaintenance manual and TO 1-1-8 and then coated withMIL-PRF-81733, Type I, Class 1 or 2, Grade A sealant.

6.7.5 Integral Fuel Cells/Tanks and Removable FuelTanks. Refer TO 1-1-3 and/or the aircraft’s system specificmaintenance manual for fuel area sealing procedures.

6.7.6 Form-In-Place (FIP) Gasket Sealant Repair.After removal of all loose sealant material, thoroughly cleanthe area to be re-sealed per Paragraph 6.6.1. Areas of the oldseal to which new sealant will be added must be cleaned andabraded using an abrasive mat or abrasive cloth (refer toAppendix A) to expose a clean, fresh surface.

a. Apply MIL-PRF-81733, Type II-½, Class I, Grade A;PR-1773, Class B-½; or SAE AMS-3276, Class B-½sealant, preferably with a sealant gun. The new sealantshould match the configuration of the removed sealantbut should be of sufficient depth to ensure contact withthe mating surface.

b. Apply a very thin film of MIL-PRF-32033 (VV-L-800)oil or VV-P-236 petrolatum to the mating surface of theaccess door/panel and close and/or install the accessdoor/panel. If installed with fasteners, lubricate themwith the same material used on the door/panel matingsurface, install ½ of the required fasteners (every otherfastener), and torque to ½ to ¾ of the specified torquefor the assembly.

c. Do not open or remove the door/panel for a minimum of24 hours.

NOTE

The main function of the pressure sensitive ad-hesive backing on the SAE AMS 3255 (Sky-flex®) sealant tape is to hold the EPTFE sealanttape in place during access door/panel assembly.The adhesive on one side of the Av-Dec®HT3000 sealant tape acts as a seal as well asholding the sealant tape in place. Peeling/delami-nation of the adhesive from the aircraft, missile,or equipment frame flange or access door/panelrequires replacement of the sealant tape if thetape is no longer located in the faying surface.Visually inspect sealant tape material for nicks,cuts, gouges and delamination/separation.

6.7.7 SAE AMS 3255 EPTFE (Skyflex®) and Av-Dec® HT3000 and HT3935-7 Sealing Tape GasketRepair. In order to preserve seal integrity, it is necessary toinspect the sealant tape each time an access panel is removed.

Figure 6-10. Typical Fillet Seal

TO 1-1-691

Change 1 6-27

NOTE

Av-Dec® HT3935-7 sealing tape requires com-plete replacement each time an access door/panelsealed with it is removed as it has an adhesive onboth sides. Scrape the old tape off with a plastictool, and apply a new length of tape as doneoriginally.

a. Cut and remove damaged section of sealant tape.

b. Measure and cut a new piece of SAE AMS 3255(Skyflex®) or Av-Dec® HT3000 sealant tape approxi-mately one inch longer than the removed section.

c. Peel the non-stick backing paper off and install a newsection of sealant tape so it overlaps the previously

installed sealant tape by one-quarter to one-half of aninch on each side of the repair site.

Figure 6-11. Typical Injection Seal

Figure 6-12. Typical Methods of Sealing Fasteners

TO 1-1-691

6-28

NOTE

Ends of the repair splice must overlap the exist-ing sealant tape to ensure seal integrity. Use carenot to pull or stretch the sealant tape patch as it isapplied. The stretched AMS 3255 EPTFE andAv-Dec® HT3000 sealant tape patches will re-tract even if clamped between faying surfaces,and inadequate sealing may result.

d. Once the sealant tape patch is applied, run fingers backand forth on the upper surface of the sealant tape patchto promote adherence of the adhesive. d.

NOTE

Applying a small amount of extra pressure to theupper surface of the sealant tape patch will causethe pressure sensitive adhesive to adhere better tothe faying surface and overlapped areas of oldsealant tape and it will create indentations/discol-oration at the fastener holes allowing for easierlocation/identification.

e. Puncture any affected fastener holes with a sharppointed object such as an awl or a scribe.

NOTE

As fasteners are installed, the sealant materialpushed into the fastener holes will help sealagainst moisture intrusion.

f. Install access panel.

NOTE

No curing time is required. All fasteners shouldbe wet installed with MIL-PRF- 16173, Grade 4CPC; MIL-PRF-63460 CPC; or CPC materialspecified in the specific aircraft, missile, or equip-ment system specific maintenance manual.

6.7.8 External Aircraft Structure. If, during normalmaintenance, it becomes necessary to remove and replacecomponents (wing planks, skin, spar caps, fasteners, fittings,etc.), they shall be sealed when reinstalled, even if they werenot sealed originally. The only exception to this requirementis a temporary repair accomplished for a one time flight to adepot or overhaul facility. Refer to Figure 6-13 throughFigure 6-16 for typical sealing methods.

6.7.9 Depressions. When the thickness of metal isreduced by more than 15 mils (0.015 in) in the removal ofcorrosion damage, fill the depression with MIL-PRF-81733,Type II, Class 1 or 2, Grade A sealant after applying achemical conversion treatment per Section II of Chapter 5.

NOTE

The above procedure does not apply to the use ofSAE AMS 3255 EPTFE and Av-Dec® HT3935-7or HT3000 sealing tapes; or to the use of SAEAMS-S-8802 (MIL-S-8802) sealant inside inte-gral fuel tanks

6.7.10 Damaged Sealant. Many areas on aircraft,missiles, and equipment are sealed either at the factory or bydepots during rework. Fresh sealant shall be applied when-ever the previously applied sealant is damaged. Remove thedamaged sealant with a plastic scraper and, if necessary,prepare the metal surface in accordance with Section II ofChapter 5. Slightly roughen a strip of the undamaged sealantapproximately one inch wide around the boundary of thestripped area with an A-A-58054, Type I, Grade C abrasivemat and then clean the area per Paragraph 6.6.1. Apply thenew sealant by brush, sealant gun, or spatula and then smoothout the surface with a spatula as required. The new sealantshould overlap onto the roughened area of the old sealant.

NOTE

• To assist with removal of damaged sealant, aliquid product known as Sky Restore® distrib-uted by AeroSafe Products Inc. (refer to Ap-pendix A) may be applied to the damaged areawith a non-metallic bristle brush, an SAEAMS 3819A, Class 2, Grade A or equivalentcleaning cloth, or a pump spray bottle andallowed to dwell for 15 to 50 minutes until thesealant is softened. A plastic scrapper maythen be used to remove the damaged sealant.This material has a fairly obnoxious odor so itmust be used either in a well ventilated area orpersonnel must wear an appropriate respiratorin all confined areas.

• After the damaged sealant is scrapped away,the area must be neutralized and cleaned witha liquid product known as Sky Wash® distrib-uted by AeroSafe Products Inc. (refer to Ap-pendix A) applied in the same manner asabove, scrubbed with the same type of brushor cloth as used above, and wiped dry

• Other tools useful for sealant removal are the3M Co. SR Radial Bristle Discs and plastic SRCutters mounted on a pneumatic drill motorand the Kell-Strom Toll Co. OZ7000 pneu-matic sealant removal kit; a vibro gun with aset of plastic scrapers and OZ7006 manualsealant removal kit; or a rubber palm supporthandle with a set of plastic scrapers (refer toappendix B).

TO 1-1-691

Change 1 6-29

6.7.11 Extensive Repair. If corrosion damage is soextensive that structural repair is necessary, all faying sur-faces between patches (or doublers) and skins shall receive asurface treatment per Section II of Chapter 5 before the repairparts are installed. Coat the faying surfaces with MIL-PRF-81733, Type IV, Class 1 or 2, Grade A sealant prior toinstallation of patch, and install all fasteners wet withMIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealant.

6.7.12 High Temperature Areas. In areas where thetemperature is expected to rise above 250° F (121° C), aone-part silicone sealant, MIL-A-46146, Type I or III, or SAEAMS 3374, Type 1, 2, 3, or 4 silicone sealant should be usedfor temperatures up to +400° F (+204° C). SAE AMS 3276(MIL-S-83430) sealant may be used in areas that experienceintermittent temperatures up to +360° F (+182° C). Applica-tion of these sealants is by spatula or sealant (caulking) gunper Paragraph 6.6.4.

6.7.13 Low Temperature Curing. When cold climatesinterfere with sealing operations by prolonging the sealantcuring reaction, use MIL-S-85420 or MIL-S-29574. Forbetter adhesion, an adhesion promoter can be used, refer toParagraph 6.3.3. SAE AMS 3255 EPTFE and Av-DECTM

HT3935-7 or HT3000 sealant tape gasket materials may beused for low temperature sealing operations when specified insystem specific technical data and/or is approved by theaircraft SPD and/or the missile or equipment SPM.

6.8 STORAGE/SHELF LIFE CONTROL OF SEAL-ANTS.

All sealants have a specified shelf life. The date of manufac-ture and the shelf life are listed on each container. The shelflife is dependant on storing the sealant in its original,unopened container in an area where the temperature does notexceed 80° F (27° C). Sealants shall not be stored in areaswhere the temperature exceeds 80° F (27° C). Prior to use,sealant containers shall be inspected to determine if thematerial has exceeded its shelf life. If a sealant has exceededits original shelf life then it shall not be used until the updatetesting has been performed. Sealants may be extended one-half of their original shelf life after passing the required tests.Updating may be repeated until sealant fails to pass testing.No sealant shall be used if it fails testing. Minimum updatetesting can be performed as follows.

a. Select one kit of sealant from each manufacturer’s batchof material to be tested for updating.

b. Visually examine the content of each can in the kit. Ifthe base polymer is lumpy or partially cured or cannotbe mixed with the curing agent, dispose of the openedkit and all kits from that batch of sealant.

c. If the kit can be blended to form a homogeneousmixture, determine whether the working time is suitable

Figure 6-13. Typical Lap Skin Sealing

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for the intended purpose by applying the mixture to aclean scrap of metal. If the working time is not accept-able, dispose of the opened kit and all others from thatbatch

d. If the working time is acceptable, the applied sealantshall be tested for proper cure time by periodicallychecking its hardness. The batch of sealant represented

by applied test sealant can be extended one-half itsoriginal shelf life if it achieves approximately the samehardness as sealant from kits of another batch which arewithin their established shelf life.

e. This updating process may be repeated until the sealantfails to pass any of the above tests.

Figure 6-14. Sealing Procedures for Typical Aircraft Fitting

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Figure 6-15. Typical Spar Cap Sealing

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Figure 6-16. Sealing of Access Doors

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CHAPTER 7TREATMENT OF SPECIFIC AREAS

7.1 INTRODUCTION.

This chapter describes the procedures recommended fortreating and protecting against corrosion in several specificareas known to be corrosion prone areas and containsillustrations to aid in inspections. This chapter is not allinclusive. Applicable system specific maintenance manualsfor specific aircraft, missiles, and/or equipment should beconsulted also to determine all corrosion prone areas on aspecific system, and the required treatment and preventivemeasures in these areas as well as any existing expanded oramplified instructions for areas covered by this chapter.

7.2 BATTERY COMPARTMENTS, BOXES, AND AD-JACENT AREAS.

Observe precautions listed in previous chapters(or references) for cleaning compounds, solvents,surface treatments, sealants, and paints as thesematerials can injure personnel if used improperly.

The battery, battery cover, battery box, and adjacent areas(especially areas below the battery compartment where bat-tery electrolyte may have seeped) are subject to the corrosiveaction of the battery electrolyte. Two different types ofbatteries are encountered on aerospace and non-aerospaceequipment: lead acid, having a sulfuric acid electrolyte; andnickel-cadmium, having a potassium hydroxide electrolyte.Methods for cleaning up and neutralizing spilled and/orleaked electrolytes are given in Table 3-2.

7.2.1 Preparation of Solutions for Cleaning and Neu-tralizing Battery Electrolytes.

• When handling electrolytes, chemical splashproof goggles and chemical resistant rubbergloves and aprons shall be worn. If anyelectrolyte contacts the skin or eyes, flood theaffected area immediately with water and re-port to the Base Medical Facility. An emer-gency shower and an eye wash station in thearea where work involving electrolytes isbeing performed are required.

• Isopropyl Alcohol (TT-I-735) is highly flam-mable. Use only in a well ventilated area andkeep away from all sources of ignition.

Both sulfuric acid and potassium hydroxide bat-tery electrolytes will cause severe corrosion ofmetallic structures. Avoid dripping electrolyte onor allowing contaminated gloves, rags, sponges,etc., to come in contact with aircraft, missile, orequipment structures. Place all items contami-nated with electrolyte in a leak-proof plasticcontainer prior to removing them from the area ofthe aircraft, missile or piece of equipment. Re-move any battery box which contains spilledelectrolyte from the aircraft, missile, or piece ofequipment prior to cleaning it. Electrolyte spilledon aircraft, missile or equipment structure shallbe cleaned up as soon as possible after it has beendetected.

NOTE

The use of indicating solutions can sometimes beavoided and/or at least limited in scope by usingtest strips of litmus paper. When trying to initiallydetect electrolyte spills from acid batteries (suchas lead- acid), apply a strip of blue litmus paper tothe wet surface. A color change to red indicatesan acid is present. When trying to detect spillsfrom alkaline batteries (such as nickel-cadmium),apply red litmus paper to the wet surface. A colorchange to blue indicates an alkaline solution ispresent.

7.2.1.1 There are four different solutions needed for thedetection, neutralization, and clean up of spilled and/orleaked battery electrolytes. Indicating solutions (litmus solu-tion for lead acid batteries and bromothymol blue solution fornickel cadmium batteries) are required for cleaning areassubjected to electrolyte spills to determine the location ofcontaminated areas and to indicate if these areas have beencompletely neutralized. A 10% by weight sodium bicarbonate(ordinary baking soda) solution is required to neutralizesulfuric acid from lead-acid batteries and a 3% by weightboric acid or monobasic sodium phosphate solution is re-quired to neutralize potassium hydroxide from nickel-cadmium batteries. These solutions are prepared per thefollowing procedures:

7.2.1.1.1 Litmus Indicating Solution. Pour one pint ofa mixture containing 70 percent by volume of TT-I-735isopropyl alcohol and 30 percent by volume distilled waterinto a plastic spray bottle with a hand squeeze pump. Add onetablespoon of litmus powder into the solution, and mixthoroughly until a deep blue color is observed.

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Change 1 7-1

7.2.1.1.2 Bromothymol Blue Indicating Solution.Pour one pint of bromothymol blue solution into a plasticbottle with a hand squeeze pump. Using an eye dropper, addone drop at a time of phosphoric acid into the solution withsubsequent mixing after each drop until the color of thesolution changes from blue to gold or amber.

7.2.1.1.3 Sodium Bicarbonate Neutralizing Solu-tion. Pour one pint of distilled water into a 500mlpolyethylene wash bottle, add ¾ of an ounce of ASTM D928sodium bicarbonate powder, and mix thoroughly.

7.2.1.1.4 Boric Acid and/or Monobasic Sodium Phos-phate Neutralizing Solutions. Pour one pint of distilledwater into a 500ml polyethylene wash bottle, add ¾ of anounce of either A-A-59282 boric acid powder or ANSI/AWWA B504 monobasic sodium phosphate powder, and mixthoroughly.

7.2.2 Cleaning and Neutralizing Procedures.

7.2.2.1 Determine the type of electrolyte involved bydipping a small strip of blue and a small strip of red litmuspapers into the liquid puddle. If the red litmus stays red andthe blue litmus turns red, the liquid is acid. If the blue litmusstays blue and the red litmus turns blue, the liquid is basic oralkaline.

7.2.2.2 Remove any standing liquid or puddles with asqueeze bulb type syringe, absorbent cloth, or sponge. Placethe used items in a leak proof container for disposal toprevent the contamination of other areas.

7.2.2.3 Spray the entire suspected area with the properindicator solution, using the minimum amount needed to wetthe entire surface. For spills/leaks from lead acid batteries,use the litmus solution which will change in color from deepblue to a bright red in areas contaminated by sulfuric acid.For spills/leaks from nickel-cadmium batteries, use the bro-mothymol blue solution which will change in color fromamber or gold to a deep blue in areas contaminated bypotassium hydroxide.

7.2.2.4 Apply the correct neutralizing solution to the areaswhere the indicating solution has been applied. For spills/leaks from lead-acid batteries, use a sodium bicarbonatesolution. For spills/leaks from nickel-cadmium batteries, useeither a boric acid or mono-basic sodium phosphate solution.Ensure that the area is well saturated including all seams andcrevices where electrolyte could collect. Use care to preventneutralizing solutions from spreading to adjacent areas; andon aircraft, ensure that bilge area drains are open. Allowfluids to flow overboard from these drains on aircraft. Allowthe neutralizing solution to remain on the surface for at leastfive minutes or until all bubbling action ceases, whichever islonger.

NOTE

When neutralizing sulfuric acid, the litmus indi-cating solution will change back from its brightred color to a light blue as the neutral point isreached. When neutralizing potassium hydroxide,the bromothymol blue indicating solution willchange back from its deep blue color to a lightamber color as the neutral point is reached.

7.2.2.5 Rinse the area thoroughly with a liberal amount ofclean tap water and remove any standing liquid or puddles, asspecified in Paragraph 7.2.2.2.

7.2.2.6 Reapply the indicator solution, as in Paragraph7.2.2.3. If the solution does not change color, rinse the area,as in Paragraph 7.2.2.5, and dry the area with clean cloths orrags. If the solution changes color, repeat Paragraph 7.2.2.4and Paragraph 7.2.2.5.

7.2.2.7 Remove any corrosion noted per procedures inSection I of Chapter 5, apply conversation coating treatmentper procedures in Section II of Chapter 5, apply sealantspecified by the applicable system specific maintenancemanual and Chapter 6 using procedures in Chapter 6, andapply primer and paint coatings per the applicable systemspecific maintenance manual using procedures in TO 1-1-8 ifbare metal is exposed. If bare metal was not exposed, or whenthe paint system applied is cured to a tack free state, apply aprotective film of either MIL-PRF-81309, Type II, or MIL-L-87177, Type I or II, Grade B CPC to the area.

7.2.3 Paint Systems. Special acid and/or alkali resis-tant coatings are usually required for battery compartments,boxes, and areas. Refer to the applicable system specificaircraft, missile, or equipment maintenance manual for thespecific paint system requirements.

7.3 RELIEF TUBE AREAS.

O-D-1435 disinfectant solutions are highly alka-line and can burn the eyes and the skin. Wearchemical resistant splash proof goggles and/orface shield and chemical resistant rubber gloveswhen using these solutions.

Interior and exterior relief tube areas shall be inspected andcleaned after each flight. Cleaning shall be accomplished byprocedures outlined in Chapter 3. After cleaning, the exposedareas shall be disinfected by wiping down with a cloth wettedwith an O-D-1435 disinfectant solution prepared per themanufacturer’s instructions. The interior of the tubes shall be

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7-2 Change 1

disinfected by pouring the solution through them. Rinse thedisinfectant solution from the area with fresh tap water, andwipe dry with a clean, dry cloth. After cleaning and disin-fecting, remove any corrosion noted per procedures in Sec-tion I of Chapter 5. For areas having exposed bare metal,apply the type of conversion coating material required for thespecific metal alloy involved per procedures in Section II ofChapter 5. Touch up the paint system in the area as requiredwith the primer and topcoat specified in the applicable systemspecific maintenance manual with application per proceduresin TO 1-1-8.

7.4 CORROSION TREATMENT FOR STEELCABLES.

• Consult the applicable system specific main-tenance manual for cable detensioning andtensioning requirements prior to performingany maintenance.

• Do not use metallic wools to clean installedsteel control cables. The use of metallic woolwill cause dissimilar metal particles to becomeembedded in the cables and create furthercorrosion problems (galvanic corrosion). Useonly a clean cloth dampened with A-A-59601,Type II or III, or MIL-PRF-680, Type II or IIIdegreasing solvent to clean steel controlcables. Excessive solvent will remove internalcable lubricant and allow the cable strands toabrade and further corrode.

If the surface of a cable is corroded, relieve cable tension andcarefully force the cable open by reverse twisting. Visuallyinspect the interior. Corrosion on the interior strands consti-tutes failure, and the cable must be replaced. If no internalcorrosion is detected, remove loose external rust and corro-sion with a clean, dry, coarse-weave rag or fiber brush. Cleanthe control cables with a clean cloth dampened with A-A-59601, Type II or III, or MIL-PRF-680, Type II or IIIdegreasing solvent. After thorough cleaning, apply a thin filmof either MIL-PRF-81309, Type II; MIL-L-87177, Type I orII, Grade B; or MIL-PRF-16173, Class II, Grade 3 waterdisplacing CPC to the cable surface by aerosol spray or acloth dampened with the CPC followed by a liberal applica-tion of MIL-PRF-16173, Class II, Grade 4 CPC with anon-metallic brush. Wipe off any excess CPC. If excessiveCPC is allowed to build up, it will interfere with the operationof cables at fairleads, pulleys, or grooved bell-crank areas.

7.5 PIANO TYPE HINGES.

Corrosion inhibiting solid film lubricants are often applied tohinge pins and nodes to provide lubrication and to reducecorrosion problems. Refer to Section II of Chapter 3 forprocedures on touch-up and replacement of these lubricantswhen hinges are disassembled. Each time an aircraft, missile

or piece of equipment is washed, make sure that all hinges arecleaned in accordance with Chapter 3. After washing, apply acoating of a water displacing CPC. Use either MIL-PRF-63460, or MIL-PRF-81309 Type II, or MIL-L-87177, Type Ior II, Grade B followed by MIL-PRF-32033 (VV-L-800) tothe node and hinge pin areas of all piano hinges includingthose coated with solid film lubricants.

7.6 INTEGRAL AND EXTERNAL FUEL TANKS ANDDROP TANKS.

For additional instructions on materials and procedures usedin aircraft fuel tank areas, refer to TO 1-1-3.

7.6.1 Corrosion Removal and Rework of Pitted Areasof Integral Fuel Tanks. Complete removal of corrosionproducts is required to prevent recurrence of corrosion in theaffected areas.

Power abrasive removal operations create air-borne particles. Eye protection is required. Goodgeneral ventilation is normally adequate.

7.6.1.1 Remove corrosion by mechanical methods inSection I of Chapter 5 using materials and procedures listedthere for aluminum alloys, except that abrasive blasting shallnot be used. In general, a power driven abrasive on a flexibleshaft is the most effective means of corrosion removal in thisarea. Corrosion removal shall be followed by hand sandingwith 280 grit abrasive paper or cloth followed by 400 gritabrasive paper or cloth to produce a smooth surface finish.The system specific aircraft -3 and -23 manuals shall beconsulted to assure structural limits are not exceeded.

To prevent injury to personnel, exercise cautionwhen using sharp or pointed tools.

7.6.1.2 After sanding operations are completed, cleanabrasive residue off reworked areas with a clean cloth, andinspect for small shiny patches which appear much brighterthan the base metal. These generally indicate exfoliationunderneath the exposed shiny surface below a blister fromwhich the top has been partially removed. As the surface isbeing sanded during rework, these blisters, being high points,receive most of the abrasive action, leaving the blister areamuch brighter than the surrounding base metal. To com-pletely remove this corrosion, the blisters must be brokenopen to fully expose the exfoliation and powdery corrosiondeposits underneath. It is usually much faster and easier topry the top off the blister with a sharp instrument. Thisoperation requires extreme caution to prevent unnecessarygouges or scratches in the base metal. Pitted and exfoliatedareas must be reworked to a depth sufficient to remove all the

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corrosion and the resulting depression must be blended intothe surrounding surface. All loosened material must beremoved from the fuel tank by vacuuming prior to furthertreatment.

7.6.1.3 Abrade the bare metal reworked area to remove theoxide film which forms on it and the surface of the SAEAMS-C-27725 (MIL-C-27725) fuel tank coating adjacent tothe reworked areas to remove the gloss from it with A-A-58054, Type I, Grade A abrasive mat.

A-A-59281 (MIL-C-38736) solvents are flam-mable and toxic to skin, eyes, and respiratorytract. Chemical resistant splash proof gogglesand/or face shield and chemical resistant rubbergloves are required. Respirators are requiredwhen using this solvent in enclosed areas.

7.6.1.4 Clean the areas thoroughly to remove all residue,oil, and grease with a clean, lint free cloth conforming toeither A-A-2522, Grade A, Color 1; CCC-C-440, Type I or II;or SAE AMS 3819A, Class 2, Grade A wetted with A-A-59281, Type I (MIL-C-38736, Type I) solvent. Do not allowsolvent to dry by evaporation; wipe the area dry with a cleancloth to prevent redepositing the soils on the surface.

7.6.1.5 Apply MIL-DTL-5541/MIL-DTL-81706, Class 1A, conversion coating to the reworked area per Section II ofChapter 5.

PR-148 adhesion promoter is flammable andtoxic to skin, eyes, and respiratory tract. Chemi-cal or splash proof goggles and rubber gloves arerequired. Respirators are required when using thismaterial in enclosed areas.

7.6.1.6 Apply PR-148 (PRC-DeSoto Int. Corp.) adhesionpromoter to the reworked area and the dulled area of thecoating around the reworked area, and allow it to dry for 30minutes minimum to 2 hours maximum.

MIL-PRF-81733 sealants are moderately toxic toskin and body (if ingested). Wear chemical resis-tant gloves and avoid other skin contact. Washhands thoroughly before eating, drinking, orsmoking after using these sealants.

7.6.1.7 Using an acid brush which has had the bristlesclipped off to half their original length, scrub MIL-PRF-81733, Type I or II sealant onto the reworked area whilemaking sure the sealant wets the entire area and overlapsslightly on to the dulled area of the coating around thereworked area. Add more sealant with the brush until a slightmound is formed and smooth the surface with the brush.

7.6.1.8 Replace any fillet or brush coat sealant removed tofacilitate rework of a corroded area per instructions in TO1-1-3.

Polyurethane coatings are flammable and toxic tothe skin, eyes, and respiratory tract. Chemicalresistant splash proof goggles and/or face shield,chemical resistant rubber gloves, and an organicvapor face mask are required. Avoid all skincontact. Exhaust ventilation is required whenusing this material in enclosed spaces/areas. Keepall open flames and any other sources of ignitionaway from the area in which this material is beingused.

7.6.1.9 When sealant applied in Paragraph 7.6.1.7 andParagraph 7.6.1.8. above is tack free, overcoat the sealantwith a MIL-C-83019 clear flexible polyurethane coating.Overlap of this coating onto the dulled area of the SAEAMS-C-27725 (MIL-C-27725) coating around the reworkedarea shall not exceed ¼ inch.

7.6.2 Removal of Corrosion and Rework of Alumi-num External Fuel Tanks/Drop Tanks. Complete re-moval of corrosion products is required to prevent recurrenceof corrosion in the affected areas.

7.6.2.1 Tank Exterior Surfaces.

Tanks which have contained fuel are hazardousuntil all vapors and residual fuel deposits havebeen removed. They are potential explosion andhealth hazards and should be treated as such.Refer to TO 1-1-3 for proper purging procedures.

Remove corrosion from these surfaces and rework the areaper the following procedure:

a. If painted, remove paint from area where corrosion issuspected per instructions in TO 1-1-8 such that amargin of good metal around the suspected area isexposed.

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b. Remove and treat corrosion using an appropriate me-chanical method in Section I of Chapter 5.

c. Apply MIL-C-5441/MIL-DTL-81706, Class 1A conver-sion coating to bare metal areas per procedures inSection II of Chapter 5.

d. Touch up area from which paint was removed perinstructions in the applicable system specific -23 aircrafttechnical order using procedures in TO 1-1-8.

7.6.2.2 Tank Interior Surfaces. Remove corrosionfrom these surfaces and rework the area per the followingprocedure:

NOTE

The interior surface of aluminum alloy tanksshall not be painted.

7.6.2.2.1 If a preservative mixture is present, remove itonly from the immediate area requiring corrosion removaland treatment. Mix 1 part MIL-C-87937, Type IV cleanerwith 9 parts fresh tap water by volume. Apply the cleanersolution to the area with a sponge, soft brush, or cloth. Scrubthe area thoroughly, remove preservative, and rinse with freshtap water. Use a clean, dry, lint free cloth to dry the area.

7.6.2.2.2 Remove and treat corrosion using an appropriatemechanical method in Section I of Chapter 5, except abrasiveblasting shall not be used.

7.6.2.2.3 Apply MIL-DTL-5541/MIL-DTL-81706, Class1A conversion coating to bare metal areas per procedures inSection II of Chapter 5.

7.6.2.2.4 Per direction of TO 00-85A-03-1, preserve theinterior of assembled tanks by fogging with preservative orapplying it with a clean, lint free cloth soaked in a preserva-tive solution. The preservative solution shall consist of onepart of MIL-C-6529, Type 1 CPC and three parts of MIL-PRF-6081, Grade 1010 oil. If spraying the preservative toprotect the entire tank interior, spray with a pressure spraythat provides complete atomization, and vent the tank at thefarthest practicable distance from the introduction point of theoil mixture during spraying operations. The amount ofpreservative shall be a minimum of 0.12 cc per square foot ofinternal surface.

NOTE

• Tanks containing foam baffling shall not bepreserved.

• This preservative compound is compatiblewith gasoline and jet type fuels, so it need notbe removed before placing tank in service.

7.7 FAYING SURFACES AND ATTACHMENTPOINTS.

NOTE

Treat and process faying surfaces of parts, com-ponents, or structures which are assembled byadhesive bonding in accordance with the appli-cable system specific aircraft, missile, or equip-ment maintenance manual that covers adhesivebonding.

7.7.1 Faying Surfaces, Joints, and Seams. Whenrepairs are made on equipment or accessories and/or compo-nents are installed or structures are reinstalled, the attachingor faying surfaces shall be protected by sealing all metal tometal and composite to metal contact surfaces. All permanentstructures shall be installed with faying surfaces wet withMIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealant.All removable structures such as access doors, inspectionplates, floor panels and plates, and other removable panels(components requiring frequent removal for maintenancerequirements) shall either be installed with faying surfaceswet with AMS 3367, Class A or B, or PR-1773, Class Bsealant or with SAE AMS 3255 (Skyflex®) or Av-DECTM

HT3935-7 or HT3000 sealant tape in the joints as specified bythe system specific maintenance manual. In addition to fayingsurface sealing, fillet seal all critical interior seams (those incorrosive areas such as aircraft bilges and latrines) and allexterior seams (those exposed to the outside environment) onpermanent structure so that fillet is flush with the surface forbutt seams and fairs smoothly into the adjoining surface forlap seams using MIL-PRF-81733, Type II, Class 1 or 2,Grade A sealant. Fillet seal all critical interior and all exteriorbutt and lap seams on removable structures that were fayingsurface sealed with SAE AMS 3367 or PR-1773 sealant in thesame manner with SAE AMS 3267, Class B, or PR-1773,Class B sealant. Refer to Chapter 6 for additional details onsealant selection and application procedures. The coatingsystem on all structures adjacent to the sealed seams andjoints shall be touched up after sealant installation to matchthe surrounding structure in accordance with the applicablesystem specific maintenance manual with application per TO1-1-8 procedures.

7.7.2 Attaching Parts and Hardware. Attaching parts,such as nuts (standard, speed, and self-locking), bushings,spacers, washers, screws (standard and self-tapping), sleevesfor shake-proof fastener studs, clamps, bolts, etc., do not needto be painted in detail except when dissimilar metal or woodcontact is involved with the materials being joined orexposure to a corrosive interior environment or the exteriorenvironment will occur in service. However, all parts shall beinstalled wet with sealant. For permanent installations, use

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Change 1 7-5

MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealantand coat the entire mating surface of the parts. For removableinstallations, use SAE AMS 3367, Class A or PR-1773, ClassB sealant and coat only the lower side of the heads of screwsand bolts with sealant. For removable installations, do notcoat the threads and shanks of screws and bolts or the holesinto which they are inserted because this will make futureremoval almost impossible without damaging the parts. As analternate for removable installations, the shanks, threads, andlower side of the heads of standard screws and bolts may becoated with MIL-PRF-63460; MIL-PRF-16173, Class II,Grade 3; or MIL-PRF-32033 (VV-P-800) CPC before theyare installed. Close tolerance bolts and parts shall be coatedwith corrosion inhibiting, solid film lubricant. Use SAEAS5272 (MIL-PRF-46010, heat curing type) on non-aluminum parts when 400° F (205° C) ovens are available.Use MIL-L-23398 or MIL-PRF-46147 (air curing type) onaluminum parts and on all types of metallic parts when 400°F (205° C) ovens are unavailable. The solid film lubricantshall be applied and completely cured prior to assembly (referto Section II of Chapter 3 for application and curing proce-dures). Bolts shall be coated on shanks and threads only. Athin bead of sealant shall be applied under the bolt head toimpart a wet seal. If possible, bolt head, nut, and bolt endshall be fillet sealed after installation. MIL-PRF- 81733, TypeII, Class 1 or 2, Grade A shall be used for sealing.

NOTE

The following does not apply to parts which arelubricated in the joint areas immediately beforeor after installation, or to close tolerance boltsand parts which are removed frequently formaintenance requirements.

7.7.2.1 All rivets shall be installed wet with MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealant. In fuelcontact areas, the exposed rivet head and approximately ¼ inof the adjacent structure shall be brush-over-coated with SAEAMS-S-8802 (MIL-S-8802), Class A sealant.

7.7.2.2 All machine screws, countersunk fasteners, bolts(head end), and nuts which are used in contact with magne-sium shall be installed with 5056 aluminum alloy washers.These parts, including the washers, shall be installed wet withMIL-PRF-81733, Type II, Class 1, Grade A sealant and shallbe completely fillet sealed with the same material afterinstallation.

7.7.2.3 Adjustable parts, such as tie rod ends and turn-buckles shall be installed as follows:

7.7.2.3.1 If possible, surfaces and threads shall be lubri-cated and protected before assembly with a film of SAEAS5272 (MIL-PRF-46010, heat curing type) or MIL-L-23398 or MIL-PRF-46147 (air curing type) corrosion inhib-iting, solid film lubricant which shall be completely curedprior to assembly (refer to Section II of Chapter 3 for

application and curing procedures). After installation, apply athin coating of DOD-L-25681 lubricant to all surfaces ofthese parts located in high temperature areas. Apply a thincoating of MIL-PRF-63460; MIL-PRF-16173, Class II,Grade 3; MIL-PRF-32033 (VV-L-800); MIL-PRF-81309,Type II; or MIL-L-87177, Type 1 or 2, Grade B waterdisplacing, CPC to all surfaces of these parts located in otherlower temperature areas.

7.7.2.3.2 If solid film lubricants cannot be applied, use athin coating of DOD-L-25681 lubricant on all surfaces beforeand after assembly when located in high temperature areas.Apply a thin coating of MIL-PRF-63460; MIL-PRF-16173,Class II, Grade 3; MIL-PRF-32033 (VV-L-800); MIL-PRF-81309, Type II; or MIL-L-87177, Type 1 or 2, Grade B waterdisplacing, CPC after assembly when located in other lowertemperature areas.

7.7.2.4 If possible, slip fit parts shall be assembled withmating surfaces wet with MIL-PRF-81733, Type I or IV,Class 1 or 2, Grade A sealant. If not possible, coat the ID ofthe holes in the receiving part, which is normally the largerstructure, with a corrosion inhibiting, solid film lubricantconforming to MIL-L-23398 or MIL-PRF-46147 (air curingtypes) and the OD of the mating part with one conforming toMIL-PRF-46010 (heat curing type) or one conforming toMIL-L-23398 or MIL-PRF-46147 (air curing types). Thesolid film lubricant shall be applied and completely curedprior to assembly (refer to Section II of Chapter 3 forapplication and curing procedures).

7.7.2.5 Press fit parts shall be installed with fayingsurfaces (the OD of the part and the ID of the hole) wet withMIL-PRF-81733, Type IV, Class 1 or 2, Grade A sealant, andthe edges of these parts shall be fillet sealed with MIL-PRF-81733, Type II, Class 1 or 2, Grade A sealant after installa-tion.

7.7.2.6 All cut edges and holes drilled or reworked forbolts, screws, rivets, studs, and bushings of aluminum alloyand magnesium alloy structures or parts shall receive achemical conversion coating treatment prior to the installa-tion of the fasteners or bushings and prior to installing orrefinishing the structure or parts. Apply a MIL-DTL-5541/MIL-C-81706, Class 1A chromate conversion coating toaluminum alloy parts and SAE AMS-M-3171 (MIL-M-3171), Type VI chromic acid brush-on pretreatment to mag-nesium alloy parts per procedures in Section II of Chapter 5.

7.7.3 Severely Corroded (Rusted) Hardware. Se-verely corroded common hardware such as screws, bolts, andwashers should be replaced. Economic consideration shall begiven to replacement of other corroded screws, bolts, nuts,washers, etc., instead of cleaning and recoating or replating.However, major replacements should be accomplished duringoverhaul and/or scheduled depot maintenance. When a pro-tective coating, such as cadmium plating on bolts, screws,

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etc., is damaged, immediate action shall be taken to apply anappropriate protective finish to prevent corrosion (rusting).Refer to Section III of Chapter 3 for proper corrosionpreventative materials.

7.8 NATURAL AND SYNTHETIC RUBBER PARTS.

Natural and synthetic rubber shall not be painted or oiled. Asa general rule, grease should not be applied to rubber parts,but some parts, such as O rings, require a grease coating(consult the appropriate system specific maintenancemanual). Many types of rubber are subject to fungus growth(e.g. mold, mildew) which can cause deterioration of therubber and corrosion of surrounding metal surfaces. If fungusis noted on rubber parts, clean the parts and remove thefungus per procedures in Section I of Chapter 3.

7.9 POTABLE WATER TANKS.

The interior surface of aluminum alloy potable water tanksshall not be painted or conversion coated. Remove corrosionby using the mechanical methods outlined in Section I ofChapter 5, and ensure all debris is removed.

7.10 SURFACES AND COMPONENTS EXPOSED TOEXHAUST GASES, GUN GASES AND ROCKETBLAST.

Residues from exhaust gases, gun gases, and rocket blast arevery corrosive and can cause deterioration of paint systems.Frequent cleaning of these areas to remove residue is requiredand shall be accomplished in accordance with Section I ofChapter 3.

7.11 ELECTRICAL AND ELECTRONIC EQUIPMENT.

Avionic and electrical equipment are easily damaged bycontamination with corrosion removal debris and by applica-tion of improper corrosion control materials. Many of theconventional corrosion treatment methods used on airframe,missile, and equipment structural components are also usedon areas adjacent to or supporting avionic equipment, elec-trical equipment, wire bundles, and other electrical parts.Personnel performing airframe corrosion control tasks on oraround this equipment shall be familiar with materials andprocedures used for corrosion prevention and control onelectrical and electronic equipment to ensure that no damageto electrical or avionic equipment will occur. For morespecific information, refer to TO 1-1-689, TO 00-25-234, TO1-1A-14, and the specific system specific equipment mainte-nance manuals.

7.11.1 Grounding and Bonding Connections. Afterthe grounding or bonding connection has been made, over-coat the entire connection, including all bare areas on themetal surface, with MIL-PRF-81733, Type II, Class 1 or 2,Grade A sealant.

7.11.2 Conduit and Junction Boxes. Electrical conduit(exterior) and junction boxes (interior and exterior) shall be

primed with two coats of MIL-PRF-23377, Type I, Class Cepoxy primer or TT-P-2760, Type I, Class C polyurethaneprimer applied per procedures in TO 1-1-8. If corrosion isfound, remove it by mechanical methods outlined in SectionI of Chapter 5. Before applying the primer, apply a MIL-DTL-5541/MIL-DTL-81706, Class 1A chromate conversioncoating to aluminum alloy parts and SAE AMS-M-3171(MIL-M-3171), Type VI chromic acid brush-on pretreatmentto magnesium alloy parts per procedures in Section II ofChapter 5 to all reworked areas and any other bare metalareas.

7.11.3 Wires and Cables. Electrical wires and cableshaving plastic jacket insulation and/or braided wire exteriorshielding shall not be painted or coated except as required formoisture and fungus proofing. Consult TO 1-1-689, TO1-1A-14, and TO 00-25-234 for additional information.

7.11.4 Corrosion Protection for Electrical Connectors,Lead-ins, etc. Almost all corrosion problems on electricaland electronic equipment are caused by moisture intrusion atthe connector or lead-in attachment points on cases andcovers. While the design of this equipment is fixed, corrosioncan be prevented by spraying MIL-PRF-81309, Type III orMIL-L-87177, Type I, Grade B avionics grade, water displac-ing, CPC into the pin and/or pin receptacle end of theconnectors prior to mating the connector halves, and on theconnector shells after mating the connector halves. ConsultSection III of Chapter 3 and TO 1-1-689 for additionalinformation.

7.11.5 Moisture and Fungus Proofing of Electricaland Electronic Equipment. Consult TO 1-1-689, TO1-1A-14, and TO 00-25-234 for information on fungusproofing this equipment.

7.11.6 Antennas. Dissimilar metal (Galvanic) corrosionoften occurs at antenna attach points. Refer to TO 1-1-689 forrepair information. Refer to the system specific maintenancemanuals for information on paint touch-up and finishing.Apply paint and coatings per procedures in TO 1-1-8.

7.12 STRUCTURAL TUBING MEMBERS AND AS-SEMBLIES.

Only non-powered mechanical procedures and materialsspecified in Section I of Chapter 5 shall be used to removecorrosion on structural tubing. Reworked areas shall alwaysbe polished to a smooth surface, using 400 to 600 gritabrasive mat, paper, or cloth as the final step in the corrosionremoval procedure. The following steps outline generalpractices for the protection of structural tubing:

7.12.1 Structural Aluminum Alloy Tubing. Treat andpaint the exterior surfaces of all tubing and the interiorsurfaces of open ended tubing closed off by riveted or boltedend surfaces with the finish system designated in the appli-cable system specific maintenance manual. Apply paint perprocedures in TO 1-1-8. All bolted or riveted caps orcomponents shall be installed with faying surfaces and

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fasteners wet with MIL-PRF-81733, Type I or IV, Class 1 or2, Grade A sealant. Interior surfaces of tubing closed bywelded end plugs or components shall be coated withMIL-PRF-16173, Class II, Grade 2 or 4 CPC using the filland drain method of application through holes located neareach end of the tubes. These holes shall subsequently beclosed by installing blind rivets wet with MIL-PRF-81733,Type II, Class 1 or 2, Grade A sealant and overcoating therivet head with the same material after installation.

7.12.2 Structural Magnesium Alloy Tubing. All sur-faces of magnesium tubing shall be treated with a SAEAMS-M-3171 (MIL-M-3171), Type VI chromic acidbrush-on pretreatment coating per procedures in Section II ofChapter 5, and painted with the finish system designated inthe applicable system specific maintenance manual withapplication per procedures in TO 1-1-8. Install all parts ontothe tubing with all faying surfaces and fasteners wet withMIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealant.

7.12.3 Structural Copper Alloys, Stainless Steel(CRES) Alloys, and Heat Resistant Alloy Tubing. Theinterior and exterior surfaces of these types of tubing do notrequire a finish system. However, to prevent galvanic corro-sion of other metals with which these types of tubing are incontact, install parts and attach tubing with faying surfacesand fasteners wet with MIL-PRF-81733, Type I or IV, Class1 or 2, Grade A sealant when located in areas not exposed tohigh temperatures or AMS-3374, Type 1, 2, 3, or 4 sealant forhigh temperature areas.

7.12.4 Structural Carbon Steel Tubing.

7.12.4.1 Exterior. All exterior surfaces of steel tubingassemblies shall be finished with one coat of MIL-PRF-26915, Type I or II, Class A or B, zinc-rich primer; MIL-PRF-23377, Type I, Class C, or MIL-PRF-85582, Type I,Class C2 epoxy primer; or TT-P-2760, Type I, Class Cpolyurethane primer followed by two coats of MIL-PRF-85285 polyurethane topcoat with the color as specified in theapplicable system specific maintenance manual. After corro-sion (rust) is removed and before applying a primer, apply anappropriate MIL-C-10578 film per Section I of Chapter 5, ora MIL-C-8514 or DOD-P-15328 wash primer coating to baremetal areas per procedures in TO 1-1-8. Apply primer andtopcoat materials per procedures in TO 1-1-8.

7.12.4.2 Interior. For tubing assemblies without weldedor crimped ends, coat all interior surfaces with MIL-PRF-23377, Type I, Class C epoxy primer or MIL-PRF-26915,Type I or II, Class A or B, zinc-rich primer using afill-and-drain procedure. Where practical, in lieu of thefill-and-drain procedure, two coats of primer may be sprayapplied to interior surfaces of all assemblies using a spray gunwith an extension wand.

7.12.4.3 Sealing. After coating the interior, clean theexterior surfaces of all assemblies adjacent to holes in thetube walls by solvent wiping to remove any oil, grease, orother contamination. Seal all holes in tube walls by installingblind rivets in the holes wet with MIL-PRF-81733, Type II,Class 1 or 2, Grade A sealant and overcoating the rivet headswith the same material after installation. Assemble all tubingassemblies manufactured by riveting or bolting memberstogether with fittings with faying surfaces and fasteners wetwith MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade Asealant.

7.13 NON-STRUCTURAL TUBING MEMBERS ANDASSEMBLIES.

Use the same procedures and materials specified for corrosionremoval on structural tubing members and assemblies inParagraph 7.12 to remove corrosion from non-structuraltubing.

7.13.1 Aluminum Alloy Tubing.

Do not use A-A-59601 and/or MIL-PRF-680degreasing solvents or other solvents that are notoxygen compatible in areas involving oxygenstorage, including transfer systems, and on thesurfaces of missiles using liquid propellant. Fail-ure to observe these precautions can result inserious or fatal injury to personnel and completedestruction of the equipment.

7.13.1.1 Protect aluminum tubing exposed directly to theoutside environment during either flight or ground operationsby applying the exterior finish system specified in theapplicable system specific maintenance manual with applica-tion per procedures in TO 1-1-8. Treat aluminum tubingaccording to the following procedure: Clean in accordancewith Section I of Chapter 3. Remove corrosion in accordancewith Paragraph 7.12, using non-powered mechanical methodsspecified in Section I of Chapter 5.

7.13.1.1.1 Apply a MIL-DTL-81706, Class 1A chemicalchromate conversion coating to all interior and exteriorsurfaces of tubing per procedures in Section II of Chapter 5;except coat only the exterior surfaces of oxygen lines. Fornew tubes, apply conversion coating to the entire tube afterfabrication and prior to the installation. If corrosion has beenremoved from tubing, apply conversion coating to all bare,reworked areas.

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No paint or corrosion preventive compound shallbe applied to any tubular interior surface. Takenecessary precautions to prevent primer or paintfrom entering the interior areas of tubing. Wheredouble flares are used (e.g., on oxygen systems),cap the ends and apply the finish system after theflaring operation. Paint end fittings after installa-tion on the aircraft, missile, or equipment. Useextreme care to prevent contamination of interiorsurfaces of hydraulic, oxygen, and air speedindicator tubing during painting operations.

7.13.1.1.2 No paint or corrosion preventive compoundshall be applied to any interior surfaces of non-structuraltubing. Apply the specified exterior finish system to allexterior surfaces or reworked areas of tubing exposed to theenvironment in the same sequence given above for structuralaluminum tubing. Touch-up any coating systems damagedduring tubing installation with the coating system specified inthe system specific maintenance manual with application perprocedures in TO 1-1-8.

7.13.2 Stainless Steel (CRES) Tubing.

• Do not use A-A-59601 or MIL-PRF-680 de-greasing solvents or other solvents that are notoxygen compatible in areas involving oxygenstorage, including transfer systems, and on thesurfaces of missiles using liquid propellant.Failure to observe these precautions can resultin serious or fatal injury to personnel andcomplete destruction of the equipment

• SAE AMS 3166 wipe solvent is flammableand toxic to the skin, eyes, and respiratorytract. Eye and skin protection is required. Useonly in a well ventilated area.

• Apply a small amount of AMS 3166 solvent toa clean cloth and wipe the surface. Follow bywiping with a clean cloth or dry rag. Thisminimizes the amount of solvent used as wellas preventing redepositing contamination onthe surface.

• To control solvent odor, used rags should beimmediately placed in sealed plastic bags orcovered containers and disposed of in accor-dance with local directives.

7.13.2.1 Protect stainless (CRES) steel tubing exposeddirectly to the outside environment, either during flight orground operations, by applying the exterior finish specified in

the applicable system specific maintenance manual withapplication per procedures in TO 1-1-8. Austenitic (3XXseries) stainless (CRES) steels are highly susceptible topitting, crevice corrosion, and stress corrosion cracking whenexposed to moist, salt-laden air and when deposits of dirt anddebris are allowed to collect on areas of the tubing covered bymetal brackets or parts. Treat stainless steel (CRES) tubingaccording to the following procedures:

a. Clean in accordance with Section I of Chapter 3.

b. Remove corrosion in accordance with Paragraph 7.12,using non-powered mechanical methods specified inSection I of Chapter 5.

c. Immediately before painting, wipe areas which will bepainted with a lint free cloth moistened with SAE AMS3166 wipe solvent; and dry with a clean cloth. Do notallow drying by evaporation, since soils will redepositon the surface.

d. Apply the finish system specified for stainless steel(CRES) tubing in the system specific technical manualsper TO 1-1-8 procedures.

7.13.3 Cadmium Plated Steel Tubing.

• SAE AMS 3166 wipe solvent is flammableand toxic to the skin, eyes, and respiratorytract. Eye and skin protection is required. Useonly in a well ventilated area.

• Apply a small amount of AMS 3166 solvent toa clean cloth and wipe the surface. Follow bywiping with a clean cloth or dry rag. This willminimize the amount of solvent used as wellas preventing redepositing contamination onthe surface.

• To control solvent odor, used rags should beimmediately placed in sealed plastic bags orcovered containers and disposed in accordancewith local directives.

7.13.3.1 Bare cadmium plating deteriorates rapidly whensubjected to abrasion, most bases (alkalis) and acids, andmarine, industrial, and very humid environments. It shouldalways be protected with a paint system to prevent corrosion.Treat cadmium plated steel tubing in accordance with thefollowing procedure:

a. Clean in accordance with Section I of Chapter 3.

b. Remove deteriorated plating and corrosion on basemetal (steel) in accordance with Paragraph 7.12, usingnon-powered mechanical methods specified in Section Iof Chapter 5.

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c. Immediately before painting, wipe areas which will bepainted with a lint free cloth moistened with SAE AMS3166 wipe solvent; and dry with a clean cloth. Do notallow drying by evaporation, since soils will redepositon the surface.

d. Apply the specified finish system for steel tubing in thesystem specific technical manuals per TO 1-1-8 proce-dures.

7.13.4 Special Instructions for Tubing Fittings andSleeves. Corrosion often occurs on sleeves and theirfittings and/or on the tubing in contact with them due to thecrevices present at their attachment points. Galvanic corro-sion often occurs because the type of sleeve or fitting chosenis not electrochemically compatible with the tubing. Whencorrosion is found on these areas or when tubing, fittings, orsleeves are replaced, consult the applicable system specificmaintenance manual to determine the proper types of sleevesand fittings. Fillet seal all fittings located in areas which areinaccessible for inspection and refinishing during operationalservice at the joint area with MIL-PRF-81733, Type II, Class1 or 2, Grade A sealant at the time of installation and prior topainting. After sealant is tack-free, paint the tubing, fittings,and sealant as directed in tubing in the system specifictechnical manuals per TO 1-1-8 procedures.

7.13.5 Removable Installations.

• Do not use MIL-PRF-16173 corrosion preven-tive compounds on any oxygen line fittings.These materials contain petroleum solventsthat are not Liquid Oxygen (LOX) compatible.Explosion may occur if oxygen contacts thesematerials and if the resulting mixture is sub-jected to sudden pressure or impact. Afterinstallation, apply the exterior paint systemspecified in the applicable system specificmaintenance manual with application per pro-cedures in TO 1-1-8 to exposed tubing,sleeves, and back portions of the B nuts ofthese fittings and a LOX compatible grease/lubricant to the gap at the front end of the Bnut and the adjacent tubing for a length of oneinch.

• Provide adequate ventilation when using A-A-59601 and/or MIL-PRF-680 degreasing sol-vents. Avoid repeated or prolonged skin con-tact of inhalation or vapors.

7.13.5.1 Do not apply the finish system on fittings andadjacent tubing for a distance of one inch from the back andfront ends of the fittings on tubing areas requiring periodic

removal and/or opening during service. Clean all old preser-vative coatings and dirt from the fitting, sleeves, and tubingends with a clean, lint free cloth wetted with either A-A-59601, Type II or III, or MIL-PRF-680, Type II or IIIdegreasing solvent and wipe dry with a clean, dry lint freecloth before reinstalling tubing and tightening fittings. Exceptfor oxygen line fittings, apply a MIL-PRF-81309, Type II;MIL-L-87177, Type I or II, Grade B; or MIL-PRF-16173,Class II, Grade 3 water displacing, CPC by spray or brush toall fitting surfaces after they are tightened, including theexposed areas of the sleeves and the unfinished areas of thetubing. Allow the CPC to dry for at least one hour, and applyMIL-PRF-16173, Class II, Grade 4, or MIL-DTL-85054 CPCover the same areas by spraying or brushing.

7.14 CORROSION REMOVAL FROM THIN METAL(0.0625 INCH THICKNESS AND LESS).

Do not allow metallic or corrosion particles tobuild up around the area being polished or on thepolishing tool (abrasive cloth or paper) during thepolishing operation. Damage to thin metal sur-faces may result.

Moderate to severe pitting and all intergranular and/or exfo-liation corrosion on thin metal requires removal by mechani-cal methods specified in Section I of Chapter 5 as appropriatefor the type of metal involved. Use extreme care and consultthe applicable system specific maintenance manual for struc-tural damage limits when removing corrosion from thinmetal. When stains, surface corrosion, and mild pitting arefound on thin structural skins (i.e., aircraft, missile, andequipment skins), chemical methods specified in Section I ofChapter 5, as appropriate for the type of metal involved, maybe used to remove the corrosion. In lieu of chemical corrosionremoval, the following convenient and effective mechanicalmethod for the removal of minor corrosion or stains on allmetals may be used:

a. Mix ground SS-P-821, Grade F pumice powder abrasivewith clean tap water to form a paste. Using a clean, softcloth (such as CCC-C-440 cheesecloth), apply the pasteto the area being treated and abrade the area with a lightrubbing motion.

b. When the pumice paste has dried to a white powder,wipe it off with a clean, dry, soft cloth. If corrosionproducts (observed as stubborn stains) still exist, use a600 grit wet or dry abrasive paper, cloth, or mat andwater to remove the remaining corrosion. Wipe cleanwith a clean, soft, dry cloth.

c. Refer to Section II of Chapter 5 for the required surfacetreatment on the type of metal involved, and touch-up

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the area with the finish system specified in the appli-cable system specific maintenance manual with applica-tion per procedures in TO 1-1-8.

7.15 AIR INTAKE DUCTS FOR JET AIRCRAFT.

Air intake ducts are fabricated from materials (usually 5000series aluminum) which have high corrosion resistance.Certain components of these ducts may be cast aluminum ormagnesium. Frequent cleaning of the ducts is usually suffi-cient to preclude attack by corrosion. Aircraft performing lowlevel missions or take-offs and landings over salt water or inhighly saline atmospheres may require the ducts to be paintedto reduce corrosion attack. A requirement for a coating asdetermined and/or recommended by the operating unit shallbe coordinated with the MAJCOM Corrosion Manager, theaircraft SPD, and the Air Force Corrosion Prevention andControl Office (AFCPCO). The MIL-PRF-23377, Type I,Class C epoxy primer/MIL-PRF-85285 or APC polyurethanetopcoat paint system, color to match the surrounding area, isusually recommended for painting the ducts, but the finaldetermination of the coating to be used shall be made by theaircraft SPD in conjunction with the AFCPCO.

7.16 CLOSELY COILED SPRINGS.

Springs which are so tightly coiled that the areas between thecoils can not be plated or painted for corrosion protectionshall be coated with a MIL-PRF-81309, Type II; MIL-L-87177, Type I or II, Grade B; or MIL-PRF-16173, Class II,Grade 3 water displacing CPC applied by spraying or dippingand allowing it to dry for at least one hour. After drying, acoating of MIL-PRF-16173, Class II, Grade 4 CPC shall beapplied to the springs by spraying or dipping.

NOTE

These requirements do not apply to springs op-erating in oil or hydraulic fluids.

7.17 CORROSION PREVENTION ON ASSEMBLIESAND PARTS REMOVED FROM AIRCRAFT DURINGMAINTENANCE, 30 DAY SHORT TERM STORAGE,AND OVER 30 DAY LONG TERM STORAGE REQUIRE-MENTS.

7.17.1 Short Term Storage. Short term storage isdefined as any period up to 30 days for the purposes of thismanual. When assemblies or parts are removed from theaircraft, missile, or equipment for repair, or to gain access toareas of the aircraft, missile, or equipment for maintenance,they shall be treated to prevent corrosion prior to placementinto short term storage. All items shall be stored indoors in acovered area to protect them from the elements. Refer to TO1-1-17 and the applicable system specific maintenancemanual and -17 storage manual for specific details on storageof a particular part or assembly.

7.17.1.1 Assemblies or parts having bare metal surfaces,such as internal and working surfaces on landing gearcomponents, shall be properly lubricated or protected bycoating with the aircraft, missile, or equipment greases,hydraulic fluids, or oils normally applied in operationalservice.

7.17.1.2 High strength steel components which arestripped of their protective coatings shall have a film ofMIL-PRF-81309, Type II; MIL-L-87177, Type I or II, GradeB; or MIL-PRF-16173, Class II, Grade 3 water displacingCPC applied to all bare surfaces whenever there is a lapse oftwo hours or more in the rework cycle. The part shall then beloosely over-wrapped with MIL-PRF-121, Type II, Grade A,Class 1 barrier paper.

7.17.1.3 Completely painted parts need no other specialprotective measures, except in marine or high humidityenvironments. In these cases, a MIL-PRF-81309, Type II;MIL-L-87177, Type I or II, Grade B; or MIL-PRF-16173,Class II, Grade 3 water displacing CPC shall be applied to thepart. The part shall then be loosely over-wrapped withMIL-PRF-121, Type II, Grade A, Class 1 barrier paper.

7.17.1.4 Prior to rework or reapplication of the requiredprotective coating, remove old CPC with solvent, and reapplythe appropriate aircraft, missile, or equipment lubricant toareas requiring lubrication. The CPC compound applied toprovide temporary protection shall not be used for lubricationin lieu of the appropriate lubricant specified for use on aparticular part or assembly.

7.17.2 Long Term Storage. If the storage of assembliesor parts will exceed 30 days, increased protective measuresare required, particularly on critical parts and high strengthsteel components. All items shall be stored indoors in acovered area to protect them from the elements. Refer to TO1-1-17 and to the applicable system specific maintenance and-17 storage manuals for specific details on storage of aparticular part or assembly.

7.17.2.1 All bare metal surfaces, and surfaces with dam-aged plating or paint, shall be coated with MIL-PRF-81309,Type II; MIL-L-87177, Type I or II, Grade B; or MIL-PRF-16173, Class II, Grade 3 water displacing CPC followed byapplication of a coating of MIL-PRF-16173, Class II, Grade4 long term CPC. The part shall then be over-wrapped withMIL-PRF-121, Type II, Grade A, Class 1 barrier paper.

7.17.2.2 Completely repainted parts need no other specialprotective measures, except in marine or high humidityenvironments. In these cases, surfaces shall be coated withMIL-PRF-81309, Type II; MIL-L-87177, Type I or II, GradeB; or MIL-PRF-16173, Class II, Grade 3 water displacingCPC followed by application of a coating of MIL-PRF-16173, Class II, Grade 4 long term CPC. The part shall thenbe over-wrapped with MIL-PRF-121, Type II, Grade A, Class1 barrier paper.

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7.17.2.3 Depending on the length of time in storage,reapplication of CPC’s may be required. Refer to Section IIIof Chapter 3 for time limitation information on CPC’s.

7.17.2.4 Prior to returning the part or assembly to service,remove CPC’s with solvent and reapply the appropriateaircraft, missile, or equipment lubricant to areas requiringlubrication. The CPC compound applied to provide tempo-rary protection shall not be used for lubrication in lieu of theappropriate lubricant specified for use on a particular part ofassembly.

7.18 DEPLETED URANIUM COUNTER-WEIGHTS.

Many aircraft control surfaces such as ailerons and elevatorsare equipped with counter-weights fabricated from depleteduranium for mass balancing purposes. Depleted uranium isused because of its very high weight per unit of volume(density). To protect the depleted uranium from corrosion,many of the counterweights are plated with a copper strike,followed with a nickel strike, followed by a full thicknesscadmium plate and then overcoated with the organic finish(paint) system specified for the specific aircraft. Thesecounter-weights are usually impression stamped for identifi-cation as follows; “Caution: Radioactive Material, DepletedUranium, High Salvage Value, Manufactured by - - -,Fabrication No. - - -, Finished Weight - - - lb. UnauthorizedAlterations Prohibited.” All personnel shall observe thefollowing requirements of the Nuclear Regulatory Commis-sion relative to depleted uranium.

To restrict radiation exposure to a maximum of10% of the Nuclear Regulatory Commission’sestablished limits for radioactive materials work-ers and to comply with the requirements in AFI40-201, observe these precautions to control ex-posure to radiation emitted from these weights.Failure to comply may result in overexposure toradiation and the need for medical attention.

a. All work on depleted uranium counterweights shallconform to the requirements of AFI 40-201.

b. Chemical or mechanical processing of depleted uraniumcounterweights, other than repair or restoration of plat-ing, organic finish system, and/or other covering, re-quires a Nuclear Regulatory Commission license.

c. Do not machine, grind, file, sand, drill, weld, or other-wise mechanically work these counterweights at field/organizational maintenance units. Depleted uranium andits oxide corrosion products in the form of dust, fumes,or particles are highly toxic if ingested.

d. If at all possible, remain at least two feet away from thedepleted uranium counterweights since radiation is al-most nil at this distance and greater. If any part of thebody comes within 1 foot of a depleted uranium

counterweight, keep a record of the exposure time; anddo not allow the total exposure time to exceed 40 hoursper calendar quarter. If it becomes necessary to touch adepleted uranium counterweight, keep a record of theexposure time; and do not allow the total exposure timeto exceed 13 hours per calendar quarter.

e. If an aircraft with control surfaces having depleteduranium counterweights is being transferred to anotherunit or the aircraft or one of its control surfaces is beingscrapped, notify the receiving unit and/or salvage per-sonnel of their presence and bring these precautions totheir attention.

f. Remove the depleted uranium counterweights and/or thecontrol surfaces containing them from the aircraft afterany aircraft accident.

g. Dispose of depleted uranium counterweights per direc-tions in AFI 40-201.

NOTE

Refer to applicable system specific maintenancemanual to determine the location of depleteduranium parts and to determine any specificdirections for work either on the counterweightsor in areas immediately adjacent to thecounterweights.

7.18.1 Corrosion and Finish Damage Treatment Pro-cedures. Follow these procedures when treating finishsystem and/or corrosion damage on depleted uranium coun-terweights:

7.18.1.1 Visually inspect the organic finish system (paint)for blisters and flaking. If found, peel away the paint flakesand inspect the plating for blisters and flaking. If found, peelaway the plating flakes and inspect the surface of the depleteduranium for pitting and/or intergranular exfoliation corrosion.The corrosion products are very dark brown to gray to blackcolor similar to rust on steel and will flake off in the samefashion.

7.18.1.2 Collect all of peeling and/or flaking paint and/orplating residue, check it for radioactivity, and dispose of it perinstructions in AFI 40-201 if radioactivity is noted.

7.18.1.3 Field/organizational units are not authorized toremove corrosion found on the depleted uranium itself.Field/organizational units are limited to the following actionson depleted uranium counterweights:

a. Accomplish Paragraph 7.18.1. and Paragraph 7.18.1.2above.

b. Apply one thick coat of MIL-PRF-81733, Type I or II,Class 1 or 2, Grade A sealant to the bare area with abrush per the manufacturer’s instructions.

c. After the sealant cures at least to a tack free state, applyone coat of MIL-PRF-85285 polyurethane in the color

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specified in the system specific technical data by brushper procedures in TO 1-1-8 over the sealant with a slightoverlap onto the surrounding paint surface.

d. Make an entry in the appropriate aircraft forms toindicate a requirement for depot level repair of theaffected counterweight at the next aircraft depot inputfor PDM or other depot level maintenance.

7.18.1.4 Depot facilities (ALC prime for the aircraft) canremove corrosion from depleted uranium counterweights andrework them, but only if properly licensed by the NuclearRegulatory Commission. If the prime ALC is not licensed toperform the work, the affected counterweights shall beremoved from the control surfaces and packaged for shipmentper instructions in AFI 40-201, and shipped to a properlylicensed facility for either rework or disposal as appropriate.If the prime ALC performs rework of depleted uraniumcounterweights after they are removed from the controlsurface, it shall be done in accordance with AFI 40-201 anda definitive process order developed and approved by theaircraft SPD in conjunction with the ALC corrosion preven-tion and control manager. This process order shall include thefollowing procedures as a minimum:

a. Remove the affected counterweight from the controlsurface per instructions in the applicable system specificmaintenance manual.

b. Remove the paint from the counterweight surfaces perprocedures in TO 1-1-8.

c. Remove the plating from the counterweight surfaces perprocedures in TO 42C2-1-7.

d. Remove any corrosion from the depleted uranium sur-faces using an appropriate mechanical method in Sec-tion I of Chapter 5 of this manual that is approved andlisted in the process order making sure to observe all theprecautions in the WARNING above and in AFI 40-201.

e. Check all residue for radioactivity, and dispose of anyresidue found to be radioactive per instructions in AFI40-201.

f. Replate the counterweight with the plating(s) specifiedin the applicable system specific technical data perprocedures in TO 42C2-1-7.

g. Apply a MIL-PRF-23377, Type I, Class C epoxy primerand MIL-PRF-85285 polyurethane topcoat in the colorspecified in the applicable system specific maintenancemanual per procedures in TO 1-1-8.

h. Reinstall the counterweight on the control surface perinstructions in the applicable system specific mainte-nance manual with faying surfaces and fasteners wetwith MIL-PRF-81733 Type I or IV, Class 1 or 2, GradeA sealant.

7.19 MONEL RIVETS.

Corrosion of nickel-copper alloy (monel) is evidenced bygreen corrosion products (patina). Removal of this type ofcorrosion is not required as the corrosion products are veryadherent and provide a degree of protection to the monel basemetal. If desired, corrosion products may be removed asfollows:

a. Scrub with a non-metallic bristle brush wet with solu-tion of 6 oz of ASTM D928 sodium bicarbonate pergallon of water.

b. Thoroughly rinse the affected area with fresh tap waterand wipe dry with a clean, lint free cloth or blow drywith oil free, low pressure air.

7.20 BERYLLIUM-COPPER ALLOYS, BERYLLIUM-ALUMINUM ALLOYS, AND BERYLLIUM OXIDE.

Dust, corrosion products (beryllium oxide), andother fine particles generated by beryllium andberyllium alloys are toxic when inhaled or al-lowed to contact skin. Severe poisoning canresult if beryllium dust and/or fumes are inhaledand cause delayed lung injury and/or death.OSHA regulations require use of Personal Pro-tective Equipment (PPE) suitable for the taskbeing performed. Consult the local Bioenviron-mental Engineer for determination of the type ofPPE required. Do not weld, drill, cut, file, sand,abrade, machine, or perform any other mechani-cal action on beryllium alloy parts that will createairborne dust particles from the operation withoutusing appropriate PPE and facility dust collectionsystems.

NOTE

Surface discoloration is normal and removal isneither advised nor is it necessary.

7.20.1 Corrosion Removal and Treatment. If it is notfeasible to remove the part from the aircraft, missile, or pieceof equipment for corrosion removal and treatment, theprocedure may be performed on an installed part in place. Tominimize the generation of fine beryllium, beryllium oxide,beryllium-copper alloy, and/or beryllium-aluminum alloydust particles when removing corrosion from beryllium-copper alloy fittings such as contacts, bushings, etc., andberyllium-aluminum alloy parts, proceed as follows:

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a. Wear disposable coveralls, gloves, hood, cartridge res-pirator, and other PPE as required by the local Bioen-vironmental Engineer.

b. Dampen an A-A-58054, Type I, Grade B abrasive matwith A-A-59601 or MIL-PRF-680, Type II or III de-greasing solvent, and abrade the corrosion productsfrom the surface.

c. To prevent the spread of toxic dust, keep mat wetthroughout the corrosion removal process.

d. Clean the surface with disposable towels dampened withdegreasing solvent after the completion of corrosionremoval, and wipe dry with a clean, dry towel.

e. Apply a film of MIL-PRF-81309, Type II, or MIL-L-87177, Type I, Grade B water displacing, CPC toberyllium-copper bushings and MIL-PRF-81309, TypeIII, or MIL-L-87177, Type I, Grade B to beryllium-copper contacts by spraying. Apply a MIL-DTL-81706/MIL-C-55441, Class 1A conversion coating to thesurface of beryllium-aluminum alloy parts per proce-dures in Section II of Chapter 5.

f. Wipe work area clean with disposable towels dampenedwith A-A-59601 or MIL-PRF-680, Type II or III de-greasing solvent, and wipe the area dry with a clean, drytowel.

g. Place disposable towels, abrasive mats, and coveralls ina plastic bag marked, “Beryllium Contaminated Waste”.

h. Close the plastic bag with SAE AMS-T-23397 (MIL-T-23397), Type II aluminum foil tape.

i. Discard all in accordance with local environmentaldirectives.

j. Wash hands with soap and water immediately aftercompletion of the task.

7.20.2 Depot Maintenance. If it is feasible, operation-ally acceptable, and replacement parts are readily available,beryllium alloy parts should not be reworked to removecorrosion by field/organizational level maintenance person-nel. The parts should be removed from the aircraft, missile, orpiece of equipment, properly packaged, and shipped to theresponsible depot (ALC) for rework using the followingprocedures:

a. Wear disposable coveralls, gloves, cartridge respiratorand other PPE as required by the local Bioenvironmen-tal Engineer.

b. Remove the corroded part, and place it in a plastic bagmarked, “Beryllium Alloy Part”.

c. Close the plastic bag with SAE AMS-T-23397 (MIL-T-23397), Type II aluminum foil tape.

d. Package the part for shipment to the responsible depot(ALC) for rework.

e. Clean the area from which the part was removed withdisposable towels dampened with A-A-59601 or MIL-PRF-680, Type II or III degreasing solvent, and wipe drywith a clean, dry towel.

f. Install a new replacement part in the area from whichthe old, corroded beryllium alloy part was removed perthe appropriate system specific technical data.

g. Place disposable towels and coveralls in a plastic bagmarked, “Beryllium Contaminated Waste”.

h. Close the plastic bag with SAE AMS-T-23397 (MIL-T-23397), Type II aluminum foil tape.

i. Discard all in accordance with local environmentaldirectives.

j. Wash hands with soap and water immediately aftercompletion of the task.

7.21 EMI SEALS AND GASKETS.

Radiated electromagnetic fields (produced by radar antennas;aircraft, and missile transmitters; certain poorly designedavionics units; electric motors; lightning; or any other naturaleffects) can interfere with aircraft avionics systems causingelectrical and/or electronic malfunctions. This radiation isknown as electromagnetic interference (EMI). To preventmalfunctions caused by EMI, electrically conductive shield-ing is either built into the avionic device or must be added toaccess panels, doors, or covers to: prevent emission of EMIfrom its own circuits and; prevent susceptibility to outsideEMI. EMI seals and gaskets may also act as environmentalseals in certain locations especially around doors and accesspanels. Since aluminum surfaces oxidize very easily, thusbecoming much less conductive and/or non-conductive, othermaterials have been used to make electrical contacts (i.e.,beryllium-copper, titanium, silver-plated aluminum, and tin-zinc coatings). However, since these contacts must provide aconductive path to an aluminum or graphite/epoxy skin,corrosion often occurs at the junction of these dissimilarmetals. When corrosion occurs, the conductive path is lostalong with the EMI protection, making the aircraft suscep-tible to electrical and electronic malfunctions caused byexternal radiation. Examples of system malfunctions aremicroprocessor bit errors, computer memory loss, false indi-cators (alarms, lights, read-outs), CRT ripple, false signalsand power loss. The result of such malfunctions can becatastrophic (e.g. EMI radiation was responsible for anaircraft jettisoning a bomb while taking off from a carrier).The following are typical EMI shielding materials: elasto-meric seals and gaskets with an embedded or attachedconductor (Figure 7-1), conductive elastomer gaskets (Figure7-2), metallic screens installed under composite covers (Fig-ure 7-3), bonding cables for access doors (Figure 7-4), andbonding washers for avionics enclosures (Figure 7-5).

7.21.1 Treatment of EMI Seals and Gaskets. Whencorrosion is observed in such areas, disassemble only the

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affected areas and remove the corrosion using the mildestavailable method necessary to remove the corrosion. Care-fully clean the area with a lint free cloth wet with TT-I-735isopropyl alcohol. Dry with a clean cloth. If replacement sealsare available, install them in accordance with the appropriateaircraft, missile, or equipment system specific maintenance

manual. If replacement seals are not available or do not exist,spray the contacting surfaces with a light coating of MIL-PRF-81309, Type III avionics grade, water displacing CPC,and then reassemble. Periodically inspect repaired areas andareas known to be chronic problems.

Figure 7-1. Beryllium-Copper Spiral Contact With Environmental Fluorosilicone Seal

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Figure 7-2. Dorsal Longeron EMI Seal

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Figure 7-3. Stainless Steel (CRES) EMI Screen

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Figure 7-4. Bonding Cable From Airframe To Graphite/Epoxy Avionics Bay Door

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Figure 7-5. EMI Bonding Washers in an Avionics Bay

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CHAPTER 8EMERGENCY PROCEDURES

8.1 PURPOSE.

This chapter describes emergency procedures to be followedafter aircraft, missile, or equipment incidents or accidentsinvolving exposure to gross amounts of salt water or fireextinguishing agents. The procedures described are used toprevent further damage before more extensive cleanup ateither organizational or intermediate maintenance can beperformed and/or further treatment at depot level mainte-nance can be accomplished.

8.2 RESPONSIBILITY.

Exposure to salt water, purple K powder (PKP/potassium bicarbonate), and/or protein type firefighting foam require immediate action to preventserious corrosion damage.

NOTE

In cases involving aircraft, missile, or equipmentaccidents, permission must be obtained from thesenior member of the accident investigationboard prior to the initiation of emergencyprocedures.

Under emergency conditions, all personnel are responsiblefor minimizing damage. Removal of equipment shall besupervised by the organizational unit maintenance officer inconjunction with the maintenance superintendent. They shalldesignate an officer or senior NCO as the corrosion controlofficer, whose duties will include organizing and supervisingan emergency reclamation team and directing the team toaccomplish salvage operations or corrosion control action.The size and composition of the team depends on the urgencyof the situation and/or workload. If required, additionalpersonnel from outside the maintenance squadron shall beselected and placed under the direction of the corrosioncontrol officer. In case of fire damage, the aircraft SPD and/orthe missile or equipment SPM and cognizant ALC corrosionprevention and control manager must be contacted to deter-mine the effects of heat or excessive salt water and/or fire

fighting material contamination prior to continued use orrepair of affected parts or components.

8.3 EMERGENCY PREPARATIONS.

Emergency preparations shall include the development ofpriority lists for removal of equipment, emergency reclama-tion team planning, and lists of required tools, materials, andequipment with notations of their location and availabilitywithin the organizational unit and/or where they can beobtained if not readily available at the unit.

NOTE

Each organizational unit maintenance officerand/or maintenance superintendent shall prepareor have access to a list of installed equipment/components indicating removal priority from af-fected aircraft, missiles, or equipment in emer-gency conditions.

8.3.1 Priority Removal List of Equipment and/orComponents.

Magnesium parts are particularly susceptible tocorrosive attack when exposed to salt water orfire extinguishing materials. Avionic, electronic,electrical, and ordnance equipment known tocontain magnesium components shall be givenhigh priority for cleaning. Contaminants shall beremoved promptly to prevent serious damage.

Table 8-1 is a tabulation of aircraft, missile, and equipmentcomponent groups arranged in order of suggested priority oftreatment. Among the factors considered in the developmentof the table were dollar value, corrosion rate, and probabilityof successful salvage. Whenever manpower or facility short-age prohibits simultaneous processing of all components,treatment shall be given in the order of the priority listing.The table should be considered as a guide, and operationsmay deviate from the assigned priority when directed byqualified organizational unit production planning personnel

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or maintenance officer and/or maintenance superintendent orthe cognizant ALC SPD and/or SPM engineering personnel.

NOTE

Table 8-1 is a priority guide for removing andprocessing equipment which has been exposed tocorrosive salt water or fire fighting chemicals.Variations in aircraft, missile, or equipment de-sign configurations and mission equipment instal-lations may make it necessary to contact theaffected aircraft SPD and/or missile or equipmentSPM and request them to furnish listings ofequipment and preferred priority of removal andtreatment. Priority of removal and treatmentshould always be oriented toward recovery ofsalvageable equipment

8.3.2 Emergency Reclamation Team. The emergencyreclamation team will provide expertise and facilities forprocessing equipment received from accident/incident sites atthe operational unit. This team shall be responsible forprocessing equipment received. The size of the team, itsorganization, and the specific equipment requirements will begeared to the size and needs of the reclamation operation athand. Recommended equipment includes wash/rinse facili-ties, drying ovens, dip tanks (for water displacing compoundsand preservatives), and cleaning compounds.

8.3.3 Emergency Reclamation Equipment. The avail-ability of the necessary tools, materials, and equipment forthe prompt removal, cleaning, and drying of avionic, elec-tronic, and electrical equipment will significantly aid inreducing damage. Refer to material and equipment lists inTable 8-2 and Appendices A and B. Certain useful items ofequipment are:

• Drying ovens

• Portable air blowers

• Heaters

• Backpack pumps

• Vacuum cleaners

• Hoses and washing equipment

8.3.4 Production Planning. Whenever possible, all sal-vageable components of the affected aircraft, missile, orequipment shall be treated simultaneously. To minimize

damage and ensure that the work is accomplished in athorough and competent manner, the most experienced per-sonnel available shall be assigned to disassemble and processthe aircraft, missile, or equipment. Whenever possible, ex-amination and evaluation personnel shall be assigned to workwith the disassembly and preservation crew in order thatthose items obviously beyond reclamation may be scrappedimmediately; and that only those areas exposed to corrosivesalt water or fire fighting chemicals are disassembled andtreated. The time saved by this procedure may be utilized toaccelerate preservation of salvageable components.

8.4 GENERAL PROCEDURES.

Before starting emergency treatment, particularlyin those instances where fuel cells have beenruptured and fuel or fuel vapors are present, it isimperative that a fuel system specialist and/or thesafety officer supervise purging or inerting pro-cedures and certify that the affected aircraft,missile, or equipment is fire and explosion safe.Qualified missile and/or ordnance personnel shallbe assigned to handle all missiles, ordnance andassociated items, such as ammunition andpyrotechnics.

For cases involving aircraft, missile, or equipment accidents,permission for any treatment shall be obtained from thesenior member of the accident investigation board prior toinitiating procedures for emergency reclamation to preventjeopardizing the ability to determine the cause of the incident.

NOTE

CBR decontamination procedures for aircraft,missiles, and equipment exposed to chemical,biological, and/or radiological materials arefound in TO 00-110A-1 and AFI 40-201.

a. Determine from the local fire department which fireextinguishing agent was used. A review of photographstaken by public affairs and/or other media personnelmay provide information concerning areas that wereactually exposed to corrosive fire extinguishing materi-als such as foam, and purple K (PKP).

Table 8-1. Priority Guide for Emergency Treatment of Aircraft, Missiles, & Equipment

PriorityNumber Reciprocating Engine Gas Turbine Engine

Turboprop, TurboshaftEngine Helicopters

1 Engine, propeller,and accessories

Engine and accessories Engine, propeller, pro-peller drive gearmechanisms, andaccessories

Rotor dynamic compo-nents

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Table 8-1. Priority Guide for Emergency Treatment of Aircraft, Missiles, & Equipment - Continued

PriorityNumber Reciprocating Engine Gas Turbine Engine

Turboprop, TurboshaftEngine Helicopters

2 Avionic and fire con-trol equipment

Avionic and fire controlequipment

Avionic and fire con-trol equipment

Engine, rotors, and acces-sories

3 Instruments Instruments Instruments Avionic and fire controlequipment

4 Fuselage, wings, andempennage

Fuselage, wings, and empen-nage

Fuselage, wings, andempennage

Instruments

5 Turrets, and rocketand missile launch-ers

Turrets, and rocket and mis-sile launchers

Turrets, and rocketand missile launch-ers

Fuselage

6 Drained fuel and oilsystems

Drained fuel and oil systems Drained fuel and oilsystems

Drained fuel and oil sys-tems

7 Photographic equip-ment

Photographic equipment Photographic equip-ment

Photographic equipment

8 Landing and arrestinggear

Landing and arresting gear Landing and arrestinggear

Landing gear or floats

9 Safety and survivalequipment

Safety and survival equip-ment

Safety and survivalequipment

Safety and survival equip-ment

10 Electrical equipment Electrical equipment Electrical equipment Electrical equipment11 Armament equipment Armament equipment Armament equipment Armament and rescue

equipment12 Fixed equipment

(seats, etc.)Fixed equipment (seats, etc.) Fixed equipment

(seats, etc.)Fixed equipment (seats,

etc.)13 Miscellaneous equip-

mentMiscellaneous equipment Miscellaneous equip-

mentMiscellaneous equipment

1 Warheads Engines and accessories2 Engines and accesso-

riesInstruments

3 Guidance systemsand sensors

Electronic and electricalequipment

4 Electrical equipment Drained fuel and oil systems5 Miscellaneous equip-

mentFixed equipment (seats, etc.)

6 Miscellaneous equip-ment

Suggested List of EmergencyReclamation Items

Table 8-2. Suggested List of Emergency Reclamation Items

PriorityNumber Accessories Order Info. Specification Part Number

1 Aircraft Grounding Straps - -2 Aircraft Washing Kits App. B, #1 3M Co. PN 2513 Cleaning & Scouring Pads, Non-

metallicApp.B, #2 A-A-3100

4 Soft Bristle Scrub Brushes App. B, #3 A-A-20745 Backpack Pump (5-gallon) App. B, #10 -6 Spray Gun, Pneumatic App. B, #11 MIL-G-952, Type I7 Drying Rags App. A, #37 CCC-C-4588 Leather Chamois App. A, #36 KK-C-300

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Table 8-2. Suggested List of Emergency Reclamation Items - Continued

PriorityNumber Accessories Order Info. Specification Part Number

9 Cleaning Sponges App. B, #1 A-A-207310 Air Nozzle Gun App. B, #31 A-A-5554311 Air Hose Assembly App. B, #32 ZZ-H-500 / ZZ-H-52112 Vacuum Cleaner, Pneumatic (Wet/D

Vac)App. B, #17 & 18 A-A-54943

13 Utility Pails, Plastic App. B, #21 A-A-5924314 Large Trash Cans & Plastic Liners - -15 Water Nozzle App. B, #8 A-A-5046116 Water Hose App. B, #9 A-A-5927017 Goggles, Chemical Resistance App. B, #101 A-A-111018 Face Shield, Industrial App. B, #99 ANSI Z87.119 Rubber Apron App. B, #98 A-A-310420 Rubber Gloves, Industrial App. B, #82 MIL-G-1222321 Leather Palm Gloves (for handling

composite materials, medium sizedonly)

NSN: 8415-00-268-8350 A-A-50016

22 Barrier Material App. A, #69 MIL-PRF-131, Class 123 Aircraft Preservation Tape App. A, #73 AMS-T-22085, Type II24 Full Face Piece Respirator & Car-

tridgesApp. B, #64 & 67 -

25 Disposal Coveralls (Bunny Suit). App. B, #88 A-A-55196, Type II26 Heater Gun, Electric App. B, #16 A-A-59435

Consumable Materials27 Corrosion Preventive Compound,

Water Displacing (5-gal min. )App. A, #43 & 44 MIL-PRF-81309,Type II & III;

& MIL-L-87177, Type I &II, Grade B

28 Aircraft Cleaning Compound App. A, #19 & 20 MIL-PRF-87937, Type IV;MIL-PRF-85570, Type II

29 Engine Gas Path Cleaner App. A, #22 MIL-PRF-85704, Type II RTU30 Degreasing Solvent App. A, #97 A-A-59601, Type II; MIL-PRF-

680, Type II31 Isopropyl Alcohol (IPA) App. A, #101 TT-I-73532 Fire Extinguishing Agent (AFFF) App. A, #59 MIL-F-24385

b. Ensure that the aircraft, missile, or equipment is safe formaintenance. Electrically ground the aircraft, missile, orequipment by attaching the ground lead to the aircraft,missile or equipment at a point outside the area thatcould contain explosive vapors. Turn off all electricalpower and disarm all explosive and/or firing systems ona missile or an aircraft, including the ejection seat(s) onan aircraft .

c. Closely inspect the aircraft, missile, or equipment todetermine areas affected. Traces of foam type extin-guishing agents may not be evident; however, moist

residues often indicate previous foam application. Drypowders may be present in joints, faying surfaces, etc.,so a careful examination will be necessary to determineif they are present.

d. Wherever possible, remove components from affectedareas. Open, loosen, or remove covers, access plates,inspection doors, etc. Allow any accumulated salt wateror other liquids to drain off. If dry chemical fireextinguishing materials have been used, refer to Para-graph 8.5.3.

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8-4 Change 1

e. Remove gross amounts of contaminants by flushingwith fresh water and draining.

f. Remove components and process in accordance withParagraph 8.4.2 and Paragraph 8.4.3.

g. Clean the aircraft in accordance with Paragraph 8.4.4.

h. Inspect aircraft, missile, or equipment and determinewhether it can return to operational service followinglocal organizational level maintenance action or whetheradditional higher level maintenance will be necessary. Ifaircraft is locally repairable, repairs must be permanentrepairs before the aircraft, missile, or equipment isreleased for unrestricted operational service.

8.4.1 Removal of Contaminated Installed Equip-ment. After salt water immersion or entry or exposure toany corrosive agents, equipment must be cleaned promptlyand thoroughly. Follow the procedures in this chapter fordecontaminating specific areas and equipment. Refer to Table8-1 for assigning priority to equipment removal and treat-ment.

8.4.2 Disassembly/Removal of Components.

8.4.2.1 The mechanical cutting of fuel, hydraulic and oillines, and electrical leads, and other drastic operations nec-essary to expedite removal of parts are left to the discretion ofthe maintenance officer and/or maintenance superintendentdirecting the operations.

8.4.2.2 When aircraft are involved in water crashes, itshall be assumed that all components, including hollowstructural and mechanical members, are contaminated inter-nally. All components shall be disassembled and treated orforwarded to the appropriate ALC depot for disassembly andtreatment as required. Ensure that all contaminants have beenremoved and that all corroded surfaces have been effectivelytreated to inhibit further attack prior to returning the aircraftto operational service.

8.4.3 Clean. Equipment and components shall becleaned by the team, in accordance with Paragraph 8.5,Paragraph 8.6, and Paragraph 8.7, and then delivered to thedesignated shops for further inspection and maintenance.Equipment that cannot be removed shall be cleaned in placeand inspected.

NOTE

All equipment subject to emergency reclamationteam procedures must be certified operationallyready before returning to serviceable status. In-spect equipment for corrosion, cracks and heatdamage. Obtain the maximum available engi-neering assistance to evaluate the extent of dam-age. Particular attention shall be given to dissimi-lar metal joints. Avionic, electronic, and electricalequipment usually contain dissimilar metals.

8.4.4 Tagging. All parts and components removed fromthe aircraft, missile, or equipment shall be “green” tagged(DD Form 1577-3) for identification, description of theaccident/incident experienced, listing of the contaminants andchemical materials to which they were exposed, and toindicate the type of CPC applied. CPC’s shall be removedprior to reusing the equipment.

8.5 GENERAL CLEANING PROCEDURES.

Contaminated areas may be cleaned by several methods. Theprimary method is fresh water flushing. Alternate methodsmay be used when fresh water is not available. Use themethods in Paragraph 8.6, and Paragraph 8.7 for emergencytreatment of specific components. Do not use the followinggeneral methods when specific methods are available.

8.5.1 Primary Method.

Prolonged breathing of vapors from organic sol-vents or materials containing organic solvents isdangerous. Prolonged skin contact with manyorganic solvents or solvent containing materialscan have toxic effect on exposed skin areas.Observe precautions listed in previous chapters,referenced manuals, and MSDSs for cleaningcompounds, solvents, surface treatment chemi-cals, sealants, primers, and paints.

Do not expose plastic or rubber items; avionic,electronic, or electrical components; wiring; orother components susceptible to heat damage totemperatures in excess of 130° F (54° C) andany/all other areas to temperatures in excess of150° F (66° C) during emergency cleaningprocedures.

NOTE

Always use the mildest cleaning cycle availablethat will ensure proper decontamination. Eventhough fresh water/detergent wash should notsignificantly affect accident investigations, per-mission must be obtained from the senior mem-ber of the appointed accident investigation boardbefore performing this operation.

The primary method of removing salt water is as follows:

a. Immerse removed unit or component in clean, freshwater whenever possible.

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b. Flush all areas with clean fresh water and allow them todrain.

c. Dry the item or areas by vacuum cleaning excess waterand/or blotting with a cloth or paper towels, or blowingdry with compressed air at a pressure not greater than 10PSI. If visual evidence of salt remains, a second clean-ing should be accomplished as follows:

(1) Mix a solution of one part of MIL-PRF-87937, TypeIV, or MIL-PRF-85570, Type II aircraft cleaningcompound in nine parts water.

(2) Apply the solution to the affected areas and scrubwith bristle brushes, sponges or cloths.

(3) Flush thoroughly with clean fresh water and drainthoroughly.

(4) Dry the item or areas as before.

d. After flushing and drying, apply MIL-PRF-81309, TypeIII, or MIL-L-87177, Type I or II, Grade B waterdisplacing CPC/preservative on all avionic, electronic,or electrical components and connectors. Ensure that allareas and crevices are coated. Apply a liberal amount ofMIL-PRF-81309, Type II, or MIL-L-87177, Type I or II,Grade B water displacing CPC to all other areas thatcannot be properly drained or contain recesses which aredifficult to reach. Ensure that all surfaces are coated.

NOTE

MIL-PRF-81309, Type II water displacing CPCdeposits a thin, nonconductive film which mustbe removed for proper function of contact pointsand other electromechanical devices where noslipping or wiping action is involved, but MIL-PRF-81309, Type III, and MIL-L-87177, Type Ior II, Grade B need not be removed as they do notinterfere with proper function of these items.CPC is easily removed with A-A-59601, or MIL-PRF-680, Type II or III degreasing/dry cleaningsolvent. Removal will be accomplished duringsubsequent maintenance or functional test priorto issue for use.

8.5.2 Alternate Methods. Use only when fresh water isnot available or is available only in limited supply or whentime prevents immediate flushing with fresh water.

8.5.2.1 Method One (preferred). Spray, brush, or wipethe exterior of the affected areas and components with liberal

amounts of MIL-PRF-81309, Type II, or MIL-L-87177, TypeI or II, Grade B water displacing CPC/preservative.

8.5.2.2 Method Two (alternate).

a. Apply a solution of one part MIL-PRF-87937, Type IV,or MIL-PRF-85570, Type II aircraft cleaning compoundin nine parts water by spray, brush, or cloth.

b. Brush affected areas until contaminants and cleanerbecome intermixed or emulsified.

c. Wipe off thoroughly with a clean cloth, to remove bothcontaminants and cleaner.

d. Apply a liberal amount of MIL-PRF-81309, Type II, orMIL-L-87177, Type I or II, Grade B water displacingCPC to affected areas.

8.5.3 Removing O-D-1407 Potassium Bicarbonate(Purple K Powder/PKP or Other Dry Chemical FireExtinguishing Agents. Remove powder as follows:

a. Remove as much as possible by vacuuming.

b. Use a soft bristle brush and air pressure not greater than10 PSI to dislodge contaminants between close-fittingcomponents.

c. Vacuum clean again.

d. Remove the residual film of dry powder adhering to thesurface by wiping, brushing, or spraying with a solutionof one part of MIL-PRF-87937, Type IV, or MIL-PRF-85570, Type II aircraft cleaning compound in nine partsof water.

e. Rinse thoroughly with fresh water.

f. Dry with cloths or paper towels and/or blow dry withdry, oil free compressed air at a pressure not greater than10 PSI.

g. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacingCPC to the affected area.

h. Enter a notation defining the affected areas and whereand how they were treated in the appropriate aircraft,missile, or equipment forms with a requirement for aspecial inspection as corrosion prone areas at a specifiedfuture time to determine if any corrosion has occurred.

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8.5.4 Removing MIL-F-24385 Aqueous Film FormingFoam (AFFF) Fire Extinguishing Agent. To removeresidues of burned materials and fresh water solutions ofAFFF, use the following procedure:

NOTE

• AFFF and fresh water mixtures usually do notpresent a corrosion problem, but cleanup ofresidues of burned materials after a fire isrequired for corrosion prevention.

• Enter a notation defining areas and compo-nents that are exposed to residue from burnedmaterials and MIL-F-24385 AFFF fire extin-guishing agent in the appropriate aircraft,missile, or equipment forms with a require-ment for a special inspection as corrosionprone areas or components at a specifiedfuture time to determine if any corrosion hasoccurred.

a. Flush all affected areas with fresh, clean water whiledraining at the same time. Whenever possible, units orcomponents which have been removed, should be im-mersed in fresh water and then flushed thoroughly withfresh, clean water. Drain away the water.

b. Clean surfaces with a solution of one part MIL-PRF-87937, Type IV, or MIL-PRF-85570, Type II aircraftcleaning compound in nine parts of water. Scrub af-fected areas and rinse with clean, fresh water. Drainaway excess water.

c. Dry with cloths, paper towels, and/or dry, oil freecompressed air at a pressure not greater than 10 PSI.

d. Apply MIL-PRF-81309, Type III, or MIL-L-87177,Type I or II, Grade B water displacing CPC to allavionic components and electrical connectors. Apply aliberal amount of MIL-PRF-81309, Type II, or MIL-L-87177, Type I or II, Grade B water displacing CPC to allother areas that cannot be properly drained or containrecesses which are difficult to reach.

e. Enter information on affected areas and/or componentsin the appropriate aircraft, missile, or equipment formsper the instructions in the above NOTE.

f. Dismantle engine to piece part component level for allcomponents exposed to inlet flow path air.

g. Clean engine components exposed to AFFF per theappropriate depot level component cleaning procedureor clean per Paragraph 8.5.6.

8.5.5 Removal of Carbon Dioxide (CO2), HFC-125,or Halon Fire Extinguishing Agents. CO2, HFC-125(Pentafluoroethane), Halon 1211 (MIL-DTL-38741, Bromo-chlorodifluoromethane), and Halon 1301 (ASTM D5632,Bromotrifluoromethane) evaporate rapidly. Therefore, nocleanup is required unless moisture or a high temperature was

present at the area of application; but ventilation shouldalways be provided to remove the vapors. If moisture or hightemperature was present, use the following clean up proce-dures for Halon materials:

NOTE

Even though carbon dioxide or Halon fire extin-guishing agents leave no residues; smoke,smudges, or other grime from a fire should beremoved from affected items that are to beretained for future use.

a. After a fire has been extinguished, purge area andsurfaces with clean, dry air (dust and oil free, lowmoisture content, compressed air).

b. Clean surfaces with a solution of one part MIL-PRF-87937, Type IV, or MIL-PRF-85570, Type II aircraftcleaning compound in nine parts of water. Scrub af-fected areas and rinse with clean, fresh water. Drainaway excess water.


d. Apply MIL-PRF-81309, Type III, or MIL-L-87177,Type I or II, Grade B water displacing CPC to allavionic components and electrical connectors. Apply aliberal amount of MIL-PRF-81309, Type II, or MIL-L-87177, Type I or II, Grade B water displacing CPC to allother areas that cannot be properly drained or containrecesses which are difficult to reach.

e. Enter a notation defining the affected areas, and whereand how they were treated in the appropriate aircraft,missile, or equipment forms with a requirement for aspecial inspection as corrosion prone areas at a specifiedfuture time to determine if any corrosion has occurred.

8.5.6 Removal of Protein Type Foam and Soda-AcidFire Extinguishing Agents. The residues left from the useof these materials can be very corrosive to aircraft, missiles,and equipment. Remove these residues as follows:

a. Thoroughly flush the affected area with fresh water.Ensure that the rinse water is completely flushed fromthe aircraft, missile, or equipment.

b. Clean surfaces with a solution of one part of MIL-PRF-87937, Type IV, or MIL-PRF-85570, Type II aircraftcleaning compound in nine parts of water. Scrub af-fected areas and rinse with clean, fresh water. Drainaway excess water.


d. Apply MIL-PRF-81309, Type III, or MIL-L-87177,Type I or II, Grade B water displacing CPC to allavionic components and electrical connectors. Apply aliberal amount of MIL-PRF-81309, Type II, or MIL-L-

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87177, Type I or II, Grade B water displacing CPC to allother areas that cannot be properly drained or containrecesses which are difficult to reach.

e. Enter a notation defining the affected areas, and whereand how they were treated in the appropriate aircraft,missile, or equipment forms with a requirement for aspecial inspection as corrosion prone areas at a specifiedfuture time to determine if any corrosion has occurred.

8.5.7 Treatment After Landing on a Foamed Run-way. Materials used to foam runways are corrosive toaircraft. As soon as possible after a landing on a foamedrunway, exterior areas, wheel wells, any interior areas ex-posed, and engines shall be cleaned. Clean the exterior andwheel wells, interior areas, and engines in accordance withSection I of Chapter 3.

8.5.8 Treatment After Exposure to Volcanic Ash. Theprimary concern in removing volcanic ash is the extremeabrasiveness of the ash. It is not a significantly corrosivematerial. Aircraft, missiles, and equipment which have beenexposed to volcanic ash should be cleaned using the follow-ing procedures before the next aircraft, missile, or equipmentoperation:

a. All static ports, fuel vents, engine inlets, air condition-ing inlets, etc., should be vacuumed to remove as muchash as possible and then suitably covered to precludeadditional ash entry. Special emphasis should be placedon ducting supplying cooling air to avionics, electronics,and electrical equipment.

b. After covering all openings where ash may enter, theexterior of the airframe, missile or equipment shouldhave ash removed initially using a vacuum, low pres-sure, compressed air (not to exceed 10 PSI), or bylightly dusting with clean rags. Avoid rubbing since thismay damage painted and bare metal surfaces due to theabrasiveness of the ash.

c. Wash entire aircraft, missile, or piece of equipmentusing a mild MIL-PRF-87937, Type IV, or MIL-PRF-85570, Type II alkaline cleaner and water solution (1part cleaner to 9 parts water) using procedures inSection I of Chapter 3 and rinse thoroughly with lowpressure water. Ensure that critical parts, such as flapscrews, tracks, and exposed hydraulic actuators areadequately cleaned. Again, caution should be takenwhen washing to avoid vigorous rubbing/scrubbing,since ash is even more abrasive when combined withwater to form a slurry.

d. Check windshield wiper blades to ensure that all con-taminants are removed prior to operation.

e. If ash penetration is evident in the aircraft interior (thecockpit, cargo area, avionics compartments, and otheraccessible interior areas) or interior areas and compart-ments of missiles and equipment; they should be thor-oughly vacuumed.

f. Check lower aircraft, missile, and/or equipment struc-tures for volcanic matter and water entrapment.

g. Clear all drains and air dry structures as much aspossible.

h. Uncover all openings which were covered during step a.

i. After washing, the aircraft, missile, or piece of equip-ment must be lubricated in accordance with applicablesystem specific maintenance manuals.

8.6 SPECIFIC INTERNAL AREAS.

The cockpit, ejection seats, avionic and electrical equipment,identification and modification plates, and photographicequipment require specific emergency cleaning procedures.

8.6.1 Aircraft Cockpit Area. Emergency cleaning pro-cedures for the aircraft cockpit are as follows:

a. If the interior is undrainable, drill out a few fasteners atlow points. If still undrainable, drill holes at low pointsas approved and directed by the aircraft SPD.

b. Remove avionics equipment, relay boxes, circuit break-ers and switches, and clean as specified in TO 1-1-689.

c. Clean ejection seats (refer to Paragraph 8.6.2).

d. Turn equipment over to the activity that has the author-ity and capability to disassemble, clean, and repair theequipment.

e. Dry equipment that has been cleaned as much aspossible with dry, oil free compressed air at a pressureless than 10 PSI, drying machines, electric fans, or handfans in a hot room of 150° F (66° C) maximum or in awell ventilated room where the humidity is low.

f. Apply MIL-PRF-81309, Type II, or MIL-L-87177, TypeI or II, Grade B water displacing CPC by spraying orbrushing onto all areas that cannot be properly drainedor contain recesses which are difficult to reach.

8.6.2 Aircraft Ejection Seats.

Disarm ejection seat mechanism before cleaning.Ensure that only authorized personnel disarmseats and perform cleaning operations.

The following emergency cleaning procedure shall be usedfor cleaning aircraft ejection seats:

a. Remove parachutes, drogue parachutes (where appli-cable), and seat pans. Return them to the local survivalequipment work center for cleaning and/or replacement.

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8-8 Change 1

b. Remove ejection seat in accordance with the applicablesystem specific maintenance manual.

c. Rinse seat thoroughly with fresh water. Continue rinsingwhile directing water into crevices and close fitting partsuntil contaminants are removed.

d. Wipe down cartridge activated devices, rockets, andinertia reels with fresh water. Disarm and remove fromseats. Cap all gas lines and ports.

e. Remove as much water as possible from equipment withvacuum or low pressure, clean, dry, oil free compressedair.

f. Dry off any remaining water with a clean cloth or papertowels.

g. Apply MIL-PRF-81309, Type II, or MIL-L-87177, TypeI or II, Grade B water displacing CPC by either spray orbrush application to critical metal surfaces and recessareas which may not be completely dry. Water displac-ing CPC protects equipment during necessary inspec-tions and/or inquiry and during transfer to the localsurvival equipment work center.

h. Wash all survival gear and pilot safety equipment withfresh water and dry thoroughly. Refer to applicablesystem specific maintenance requirements for detailedpreservation procedures. Lubricate and apply CPC’s inaccordance with the applicable system specific mainte-nance cards and Sections II and III of Chapter 3 in thismanual.

i. If necessary, send the entire ejection seat to the appro-priate ALC Depot for overhaul/repair.

j. Aircraft mounted escape system components (mechani-cally activated CADS) shall be wiped and dried with aclean cloth and fresh water. If internal contamination issuspected, remove and replace. Forward removed com-ponents to the appropriate ALC Depot for furtherdisassembly, inspection, and repair.

8.6.3 Avionic, Electronic and Electrical Equipment.

Ensure that all electrical power is disconnectedand all systems in the aircraft, missile, or equip-ment are deactivated before starting the cleaningoperation on avionics, electronic, or electricalequipment to prevent electrical shock.

Effective cleaning ensures that salt water, fire fighting chemi-cals, and other corrosive agents are completely removed toprevent corrosion damage. Refer to TO 1-1-689 for specificcleaning procedures.

8.6.4 Photographic Equipment. Use the following pro-cedure for cleaning photographic equipment:

a. Immediately rinse with fresh water, drain and rinseagain.

b. Apply MIL-PRF-81309, Type III, or MIL-L-87177,Type I, Grade B water displacing CPC by spraying.

c. Return to the appropriate photographic equipment tech-nician for prompt servicing.

8.6.5 Graphite or Carbon Fiber/Epoxy, Boron Fiber/Epoxy, and Tungsten Fiber/Epoxy Composite Materi-als.

• The inhalation of graphite, boron, or tungstencomposite fibers resulting from aircraft, mis-sile, or equipment fires and/or material dam-age may be harmful to personnel. Wear acartridge type respirator and goggles whenexposed to these materials, and, in addition,wear close weave cotton gloves when han-dling these materials. Request the assistanceof the local bioenvironmental engineer andsafety officer to provide specific informationregarding hazards to personnel during cleanupoperations involving these materials and therequired PPE.

• Do not put power to or start up any aircraft,missile, piece of equipment or other avionic/electronic/electrical equipment which havebeen exposed to debris until decontaminationby vacuuming and/or washing is completed.Failure to observe these procedures may resultin electrical short circuits and fires.

Aircraft, missile, or equipment constructed utiliz-ing graphite, boron, or tungsten fiber compositematerials in contact with metal structures orsubstructures create a high potential for establish-ing galvanic corrosion cells. This can result incorrosion of the metal components if the structureis exposed to an electrolyte medium, such as saltwater.

The graphite, boron, and/or tungsten fibers of compositematerials may be released into the atmosphere if their epoxybinder burns; this occurs at temperatures in excess of 600 F(316 C). In addition, fibers may be released during anexplosion or a high impact crash. Since graphite, boron, andtungsten are very conductive, these fibers can damage unpro-tected avionic, electronic, and electrical equipment withinseveral miles of the incident site by settling on and shortingout electrical contacts. The procedures for treating damagedcomposite materials are listed below. Refer to TO 1-1-690 foradditional information.

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Change 1 8-9

8.6.5.1 Cleanup. When damaged aircraft, missiles, orequipment have graphite, boron, or tungsten fiber compositesurfaces which are broken or burned, follow these proce-dures:

8.6.5.1.1 If ventilation inlets are exposed to debris, takeimmediate action to ensure that the filtration system isproperly operating. If the system is not operating properly,shut down the system and provide temporary filtration atoutlets leading to compartments with electrical, avionic, andelectronic equipment.

8.6.5.1.2 Warn the flight crew of adjacent in-flight aircraftand maintenance control for flight line operations that thesmoke may contain hazardous electrical contaminants.

8.6.5.1.3 Spray MIL-PRF-81309, Type II, or MIL-L-87177, Type I, Grade B CPC on damaged composite surfaces.This will prevent the spread of graphite, boron, or tungstenfiber contamination by causing the fibers to stick togetherand/or to the damaged surface. Cover damaged surfaces withplastic sheet and tape it securely in place.

8.6.5.1.4 Aircraft, missiles, facilities, clothing and equip-ment that have been exposed to debris from the aircraft,missile, or equipment fire must be vacuumed and/or washeddown prior to reuse or movement into a hanger.

8.6.5.1.5 Decontamination of the immediate area of theaircraft, missile, or equipment wreckage may require vacu-uming, washing, and bagging, of composite material frag-ments. Use a sealed industrial vacuum and store the collecteddebris in sealed plastic bags for the accident investigationboard. Dispose of the debris in accordance with applicableregulations when so directed by the investigation team.

8.6.5.1.6 If wrapping and secure taping of the aircraft,missile, or equipment wreckage is not possible, transportingthe wreckage must be planned to bypass heavily populatedand industrial areas. Aircraft, missiles, or equipment parkedor located along the planned route must have their canopiesand access doors closed and their engine inlet and exhaustopenings, air intakes and outlets, and all other vents and portscovered. In addition, the doors and windows of surroundingbuildings should be closed to minimize the probability ofhaving wind-blown fibers enter areas containing electricaland electronic equipment.

8.7 SPECIFIC EXTERNAL AREAS OF AIRCRAFT.

The following external aircraft areas require emergencycleaning after exposure to fire and fire fighting agents.

8.7.1 Airframes. Use the following procedure for clean-ing airframes:

a. Flush all areas with fresh, clean water while draining atthe same time. Whenever possible, units or componentsthat have been removed from the aircraft should beimmersed in fresh water and then flushed thoroughlywith clean, fresh water. Drain away the water and dry

the areas with cloths, paper towels, or dry, oil freecompressed air at a pressure of less than 10 PSI.

b. Clean with a solution of one part of MIL-PRF-87937,Type IV, or MIL-PRF-85570, Type II aircraft cleaner innine parts of water. Scrub affected areas with thesolution. Flush thoroughly with fresh water and drainaway the excess water. Dry with cloths, paper towels, ordry, oil free compressed air at a pressure of less than 10PSI.

c. Apply a liberal amount of MIL-PRF-81309, Type II, orMIL-L-87177, Type I or II, Grade B water displacingCPC by spraying or brushing to all other areas thatcannot be properly drained or contain recesses which aredifficult to reach, to aid in the removal of water.

d. If the aircraft fuselage, empennage, or wings are in arepairable condition, drain holes may be provided fordraining water by drilling out rivets at the lowest points.All repairable parts shall be collected and returned withthe aircraft when shipment is made.

8.7.2 Antennas. Remove antennas per instructions inthe system specific aircraft and/or specific equipment main-tenance manual. Treat in accordance with TO 1-1-689.Accomplish any in place cleaning as follows:

a. Check antenna insulators for damage or cracks.

b. Brush or spray a solution of one part MIL-PRF-87937,Type IV, or MIL-PRF-85570, Type II aircraft cleaningcompound in nine parts water onto the antenna and theaffected adjacent area, and scrub the area with a small,soft brush or wiping cloth dipped in the above cleaningsolution.

c. Rinse with clean, fresh water.

d. Dry the area with a clean, dry cloth.

8.7.3 Reciprocating Engines.

a. Determine the extent of contamination.

b. Drain all fluids. Partial disassembly is authorized toaccomplish thorough draining. Ensure that pressuresystems and cylinders are drained.

c. Thoroughly flush all surfaces and passages with freshwater.

d. Apply A-A-59601 or MIL-PRF-680, Type II or III drycleaning/degreasing solvent to the affected areas with abrush, cloth, or non-atomizing spray, and scrub the areawith a brush or cloth.

e. Flush all accessible interior surfaces and all passageswith either a solution of one part MIL-C-85704, Type IIturbine engine gas path cleaning compound in four partsfresh water or use the straight undiluted form of MIL-

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8-10 Change 1

C-85704, Type II ready to use (RTU) cleaner. Both theType II and Type II RTU are aqueous cleaners withoutany hydrocarbon solvents.

f. Thoroughly rinse all areas with fresh water.

g. Allow to thoroughly drain. Dry using paper towels,cloths, or dry, oil free compressed air at a pressure ofless than 10 PSI.

h. Apply a liberal amount of MIL-PRF-81309, Type II, orMIL-L-87177, Type I or II, Grade B water displacingCPC to all surfaces. This may be accomplished by fillingand draining (preferred), flushing, or spraying. Rotatethe propeller shaft to coat cylinder walls. Drain excessCPC.

i. Reassemble engine finger tight.

j. Lubricate any pressure lubrication points to displace allcontaminated lubricant.

k. For shipping, place engine in an approved dehydratedmetal container, using twice the normal amount ofdesiccant. Notify the engine SPM to arrange for specialhandling as required.

8.7.4 Turbine Engines. Engines which are contami-nated with small amounts of sea water entering the intakeshall be cleaned using MIL-PRF-85704 engine gas pathcleaner in accordance with Table 3-2 and the engine systemspecific technical/overhaul manuals. Decontaminate enginesthat have been completely submerged in fresh water or seawater as follows:

a. Drain all fluids. Partial disassembly is authorized toaccomplish thorough draining.

b. Thoroughly flush all surfaces and passages with freshwater.

c. Flush all accessible interior surfaces and all passageswith either a solution of one part MIL-PRF-85704, TypeII turbine engine gas path cleaning compound in fourparts fresh water or use the straight undiluted form ofMIL-C-85704, Type II RTU cleaner. Both Type II andType II RTU are aqueous cleaners without any hydro-carbon solvents.

d. Thoroughly rinse all areas with fresh water.

e. Drain thoroughly.

f. Apply a liberal amount of MIL-PRF-81309, Type II, orMIL-L-87177, Type I or II, Grade B water displacingCPC to all surfaces. This may be accomplished by fillingand draining (preferred), flushing, or spraying. Drainexcess CPC. Repeat this procedure until all traces ofwater have been removed.

g. Lubricate any pressure lubrication points to completelydisplace all contaminated lubricant.

h. For shipping, install in an approved dehydrated metalcontainer, using twice the normal amount of desiccant.Notify the engine SPM to arrange for special handlingas required.

8.7.5 Treatment for Engines Which Have IngestedFire Extinguishing Powder (Purple K/PKP, AqueousFilm Forming Foam (AFFF), and/or Sodium Bicarbon-ate).

a. With the ignition off/disconnected, vacuum up as muchof the loose powder/foam as possible followed bycranking the engine and rinsing it thoroughly withwater.

b. Wash the engine with MIL-PRF-85704 gas path cleanerper instructions in Table 3-2 and Paragraph 8.5.4 and8.5.7.

c. Flush all accessible interior surfaces and all passageswith either a solution of one part MIL-PRF-85704, TypeII turbine engine gas path cleaning compound in fourparts fresh water or use MIL-PRF-85701, Type II, RTUcleaner undiluted. Both Type II and Type II RTU areaqueous cleaners without any hydrocarbon solvents.

d. Based on the high-temp metals and unique coatings/finishing materials used in the manufacturing of theseend items, cleaning of engines exposed to any fire or fireextinguishing products, requires consulting the weaponsystem specific technical order, depot overhaul manual/procedures, original equipment manufacturer (OEM)manual, and the appropriate engine engineering author-ity for potential additional actions required such asdismantling of the engine.

e. Drain engine lubricant/oil and refill/service.

f. At the next inspection, recheck previously contaminatedareas and repeat the above procedure, if necessary.

8.7.6 Helicopter Transmission, Rotor Head, and Ro-tor Hub. Helicopter transmission, rotor head, and rotor hubcases are often constructed of magnesium. Magnesium partsexposed to salt water or fire fighting chemicals requireimmediate and thorough decontamination and preservation.

8.7.6.1 External Surface Contamination. Treat heli-copter transmissions, rotor heads, and rotor hubs with exter-nal surface contamination as follows:

a. Rinse with fresh water.

b. Wash with a solution of one part MIL-PRF-87937, TypeIV, or MIL-PRF-85570, Type II aircraft cleaning com-pound in nine parts fresh water or use MIL-C-43616,Class 1A aerosol type solvent emulsion aircraft cleanerper instructions in Section I of Chapter 3, and rinsethoroughly.

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Change 1 8-11

c. Apply a liberal amount of MIL-PRF-81309, Type II, orMIL-L-87177, Type I, or II, Grade B, water displacingCPC to all affected areas by spraying or brushing.

d. Lubricate all pressure lubrication points to displace allcontaminated lubricant.

8.7.6.2 Internal Surface Contamination. If internalsurface contamination of helicopter transmissions, rotorheads, and gearboxes is suspected, immediately contact theappropriate helicopter SPD for assistance with decontamina-tion procedures. Treat helicopter transmissions, rotor heads,rotor hubs, and gear boxes having internal contamination asfollows:

a. Drain all fluids. Partial disassembly is authorized toaccomplish thorough draining. Ensure that pressuresystems are drained.

b. Thoroughly flush all surfaces and passages with freshwater.

c. Flush all surfaces and passages with a solution of onepart MIL-PRF-87937, Type IV, or MIL-PRF-85570,Type II aircraft cleaning compound in nine parts freshwater per instructions in Section I of Chapter 3.

d. Thoroughly rinse all areas with fresh water.

e. Allow to drain thoroughly.

f. Apply a liberal amount of MIL-PRF-81309, Type I, orMIL-L-87177, Type I or II, Grade B water displacingCPC to all surfaces. This may be accomplished by fillingand draining (preferred), flushing, or spraying. With thehousing full of preservative, rotate the main shaftapproximately five revolutions. After the preservativehas remained in the housing for four hours, drain, andreplace plugs.

g. Service the transmission, rotor head, rotor hub, and/orgear box in accordance with the applicable systemspecific maintenance manual if going back in service orleave as preserved if the unit will be shipped out.

h. Lubricate all pressure lubrication points to displace allcontaminated lubricant.

8.7.7 Helicopter Main and Tail Rotor Blades. Heli-copter blades that have been exposed to an excessive amountof salt water or to liquid fire fighting chemicals shall betreated as follows:

NOTE

Some rotor blades have areas commonly knownas pockets or blade boxes with very small drainholes. The drain holes may require enlargement,if blades were salt water immersed, to facilitatedecontamination of the blade spar. Enlargingdrain holes destroys the affected pockets or bladeboxes and requires Depot Level repair before theblade can be reused. Enlargement of pocketaccess openings requires authorization from theappropriate helicopter SPD and blade SPM foreach blade involved. Where possible, flush pock-ets with MIL-PRF-81309, Type II, or MIL-L-87177, Type II, Grade B water displacing CPC.Preserve and package the blade properly beforesending it to the appropriate ALC Depot forengineering evaluation and necessary repair.

a. Thoroughly flush all contaminated surfaces with freshwater. Pay particular attention to recesses that tend totrap debris such as mud, dirt, or salt deposits.

b. Wash with a solution of one part MIL-PRF-87937, TypeIV, or MIL-PRF-85570, Type II aircraft cleaning com-pound in nine parts fresh water per instructions inSection I of Chapter 3.

c. Rinse thoroughly with fresh water.

d. Dry with a cloth, paper towels or dry, oil free com-pressed air at a pressure of less than 10 PSI.

8.7.8 Armament. The following instructions are forinitial treatment of armament equipment that has undergonesalt water immersion or been subjected to fire extinguishingchemicals.

8.7.8.1 Safety Precautions. Before performing anycleaning chores, make certain that preliminary safety precau-tions are followed:

a. Ensure that the aircraft, missile or piece of equipment issafe for maintenance.

b. Disconnect all electrical power and ensure that allarmament switches are in the OFF or SAFE positions.

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8-12 Change 1

NOTE

For removal of armament equipment, refer toapplicable system specific maintenance/technicalmanual for the respective aircraft, missile, orpiece of equipment.

c. Remove all ordnance from the aircraft or piece ofequipment, and all warheads from the missile andproperly dispose of contaminated ammunition and war-heads as required.

8.7.8.2 Cleaning Procedure. After complying with thesafety precautions, clean per the following procedure:

a. Rinse equipment with fresh water.

b. Disassemble as required and wipe away excess greasewith clean cloth dampened with A-A-59601 or MIL-PRF-680, Type II or III dry cleaning/degreasing sol-vents.

c. Immerse and agitate parts in a solution of one partMIL-PRF-87937, Type IV, or MIL-PRF-85570, Type IIaircraft cleaning compound in nine parts of fresh water.

d. Rinse parts with fresh water to ensure complete removalof contaminants.

e. Wipe away excess water with clean, dry cloth.

f. Blow dry the cleaned equipment/parts as thoroughly aspossible with clean, dry, oil free compressed air at apressure of less than 10 PSI.

g. Inspect the equipment to determine whether it should bereturned to service or forwarded to the appropriate ALCDepot for overhaul or repair.

h. Apply a liberal amount of MIL-PRF-81309, Type II, orMIL-L-87177, Type I or II, Grade B water displacingCPC by either spray, brush, dip, or fill and drainapplication.

i. If shipment to the prime ALC Depot for maintenance isrequired, wrap the equipment in MIL-PRF-131, Class 1barrier material, package it per the applicable instruc-tions, and forward it to the depot as directed.

8.7.9 Aircraft Fuel Systems. For emergency treatmentof aircraft fuel systems contaminated with water throughother than a water crash or fire damage, refer to TO 1-1-3.

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Change 1 8-13/(8-14 blank)

CHAPTER 9SOUTHWEST ASIA ENVIRONMENTS

9.1 INTRODUCTION.

The Southwest Asia (SWA) Area of Responsibility (AOR)consists of varied regions from Afghanistan to South Africa.The conditions range from seasonal high winds and highhumidity to arid areas and low winds. In many locations,there are negatively charged ions (called anions) in soils thatwhen combined with aggressive sand storms, can spreadthroughout SWA (refer to Figure 9-1). The extent that sandand dust can penetrate equipment is dependent on manyvariables such as wind speed and direction, size of the dustparticles, protective shelter availability at the site, and equip-ment problems such as bad seals, gaskets and bent doors.Although sandstorms are usually seasonal, during the periodsof relative calm there can be a significant amount of airborndust seen as a general haze in the atmosphere (refer to Figure9-2).

9.1.1 Climatic Conditions. SWA contains varied cli-matic and environmental conditions. Temperatures canchange drastically from day to night. A desert environment islargely typical of SWA with the exception of coastal areas andareas with bodies of water close by; such as rivers, streams,and lakes. In certain areas of SWA, where there is low relativehumidity and rainfall, the dry air tends to decrease thecorrosion initiation and propagation action. In contrast, flightsover bodies of water, and operations near coastal areas withhigher humidity and recurring fog, provide moisture toextract soluble anions. These environments assist in thedevelopment of electrolytes for corrosion initiation. Thepotential for corrosion increases when moisture in the form ofhigh humidity (greater than 70%), rainfall, dew, fog, etc,combine with fine dust and sand containing corrosive anionssuch as chlorides, sulfates, nitrates and fluorides. During thedaylight hours, the equipment stored outdoors will normally

heat-up causing expansion of panels allowing hot moist air tomigrate into enclosed areas or under non-breathable fabriccovers. When the equipment cools, moisture condenses andcombines with dust particles and sand settling on metalsurfaces which increases the potential for corrosion. Thesoluble materials in the sand form a crust as they dry, makingremoval difficult.

Figure 9-1. Soil Makeup in the SWA Area

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Change 1 9-1

9.1.2 Aircraft Wash. Aircraft shall be washed in accor-dance with Table 3-1. If the water quality does not meetcriteria established in Paragraph 3.1.1f (1-9), the unit mustrequest a waiver in accordance with the NOTE in Paragraph3.2.3.1.

9.1.3 Aircraft Clear Water Rinse (CWR). CWR re-quirements in Paragraph 3.2.3 are not applicable to SWAlocations. If units need to remove dust and sand for opera-tional or specific maintenance reasons, dry cleaning processessuch as vacuum, brush, compressed air, etc, should be used tothe greatest extent possible. In rare cases where rinse opera-tions must be performed to remove accumulated dust andsand, water must meet the quality specified in Paragraph2.1.1f (1-9). After these limited rinse operations have beencompleted, accumulated water must be removed to minimizeeffects of chlorides found in many of the dusts and sands ofthe SWA environment.

9.1.4 Effects of Desert Environment. Soils in many ofthe SWA operating locations will cause or accelerate existingcorrosion if left in contact with metal surfaces in highhumidity conditions or in the presence of other moisture.However, if some type of moisture is not present, these soils,although high in potentially corrosive salts, do not supportcorrosion cell initiation or propagation. In all cases, the soilsshould be considered suspect and be regularly removed whilein-country or as soon as practical after the equipment returnsto home station.

NOTE

Recommend specific System Program Director(SPD)/System Program Offices (SPO) in con-junction with affected MAJCOM CorrosionFunctional Managers to develop a detailed check-list for each weapon system. Standardized check-lists for each phase of a deployment for aircraftand associated equipment will greatly improvethe overall condition when operating in SWAenvironments and increase equipment survivabil-ity and serviceability. Some general requirementsin the absence of weapons systems guidance areincluded in Paragraph 9.3 and Paragraph 9.4.This list may not be inclusive of all tasks.

9.2 PRE-DEPLOYMENT RECOMMENDATIONS.

a. Inspect entire aircraft exterior for missing and chippedprimer and/or paint. Correct all discrepancies prior todeployment.

b. Inspect and replace any worn, torn or cracked seals andgaskets that will allow sand and dust intrusion.

c. Accomplish a complete wash prior to deployment.

d. Remove all standing water.

e. Inspect all drain holes and unplug if needed.

f. Minimize aircraft lubrication by removing all excessgreases to limit sand and dust entrapment.

9.3 RECOMMENDED ACTIONS WHILE DEPLOYED.

Soils in operating locations in SWA should be consideredsuspect and be regularly removed. A constant regimen ofvacuuming, brushing, etc to remove dust and sand accumu-lation is necessary to reduce potential corrosion problems.Limit the use of compressed air to areas that will not causethe sand and dust to migrate and settle on other areas andcomponents.

9.3.1 High Efficiency Particulate Air (HEPA) Filtra-tion. HEPA filtration vacuum cleaners should be used togreatest extent because SWA sand and dust particulates arecommonly 10 microns or smaller. Numerous manufacturersproduce commercial off-the-shelf vacuum systems that aresuitable for SWA sand and dust removal.

a. Pneumatic wheeled units. Air volume consumption is30-60 CFM. Used for cargo decks or large surfaceswhere space is available.

Figure 9-2. Global Dust Producing Regions

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9-2 Change 1

b. Pneumatic Backpack. Air volume consumption is 70CFM. Portable for difficult to access areas in flightdecks, latrines, medium sized wheel wells. It can beremoved from the backpack frame for hand-held use.

NOTE

The units above require large volumes of air andare used in situations where electricity is unavail-able or restricted for use.

c. Electric models in floor and backpack are available in110-460 Volts @ 60 Hertz.

d. Battery pack portable units, requires 12-18 Volt batterypacks. Used for extremely small/confined areas such ascockpits, avionics bays, main and nose landing gear offighter aircraft.

9.3.2 Areas to be Checked and Cleaned. Listedbelow are some of the areas that should be checked andcleaned.

a. Wheel Wells.

b. Exposed control cables, pulleys, and gears.

c. Flap wells, control surface wells, personnel restraintattach points.

d. Access doors and service compartments.

e. Crew entry and exit doors. Latch release doors andpanels.

f. Cockpit interior and flight decks.

g. Inside engine pylons and lower sections of nacelles.

h. Cargo ramps and recessed areas of cargo decks.

i. Avionic instruments, electrical panels and bays (refer toFigure 9-3), especially those with cooling vents andintake fans.

j. All areas susceptible to standing water. Keep all drainholes open by inserting a probe, such as a pipe cleanerbefore and after vacuuming.

NOTE

If sand is hard and crusted, gently break up withnon-metallic tool and remove with vacuum.

9.4 POST DEPLOYMENT.

a. Inspect all areas listed in Paragraph 9.3.2.

b. Remove as much entrapped sand and dust as practicalwith dry cleaning processes such as vacuum, brush,compressed air, etc.

c. Perform thorough aircraft wash (NLT 30 days) afterarrival to home station.

d. Remove all standing water.

e. Inspect exterior surfaces for areas of missing primer andpaint erosion. Correct all deficiencies.

9.5 CORROSION PREVENTIVE COMPOUNDS(CPC’S).

Corrosion preventive compounds are used to protect aircraft,missile, and equipment parts and components by preventingcorrosive materials from contacting and corroding bare metalsurfaces. Section IV, Chapter 3 of this TO lists CPC types andapplications. Recommend applying these products ahead ofscheduled deployment if known.

9.5.1 Recommended CPC’s. Since general purpose,soft, oily CPC such as MIL-PRF-81309, Type II and MIL-PRF-16173, Grades 1, 2 and 4, have a tendency to attract andhold sand and dust particles, they should not be used in SWAenvironments unless mandated in weapons system specificTO’s. In all cases, CPCs should be used sparingly and anyexcess removed at the time of application. MIL-L-87177 andMIL-PRF-81309, Type III deposit ultra-thin films that are lesssusceptible to sand and dust accumulation, so they shouldcontinue to be used in the all applications addressed in thisTO, TO 1-1-689 and all weapons specific TO’s. MIL-DTL-85054 (AMLGUARD) produces a dry, thin film that also doesnot attract and hold dust and sand particles. Apply this CPCto aircraft or equipment surfaces for temporary protection ifconventional primers and topcoats are not available or otherlimitations prevent their use. This CPC is not suitable for useon the interior of electrical or electronic equipment orconnectors.

Figure 9-3. Open Circuit Board

TO 1-1-691

Change 1 9-3/(9-4 blank)

APPENDIX ACONSUMABLE MATERIALS

A.1 INTRODUCTION.

Table A-2 provides consumable materials used for aircraft,missile, and equipment cleaning and corrosion preventionand control. Nomenclatures, specifications/part numbers, na-tional stock numbers, units of issue, and intended use ofmaterials are provided. Items are located by function in thefollowing groupings:

• Abrasives

• Conversion coating materials

• Cleaning compounds

• Cleaning pads/cloths

• Corrosion preventive compounds

• Lubricants

• Neutralizing agents

• Protective materials

• Sealants and sealant accessories

• Solvents

A.1.1 Shelf Life. Shelf life and its extension data (givenin months) for materials that have a shelf life are provided inAFMAN 23-110 and the Shelf-Life Extension Data (SLED)Program managed by WR-ALC/MADL at Robins AFB, GA

(HQ USAF/SLED; DSN 468-4005 or COM (478) 926-4005;FAX same prefixes and -1276; [email protected]). TO42C-1-12 covers qual-ity control procedures for chemical materials.

A.1.2 Consumable Materials Containers. Consum-able materials of a particular specification are provided invarious sized containers. If the particular sized containerrequired is not available or listed, ask supply department toprovide the next size container under the same specification.

A.1.3 Local Purchase. When local purchase is speci-fied, include all procurement information, source of supplyand GSA contract number available.

A.1.4 Local Environmental Laws and Regulations.Prior to the procurement/use of any of specified products forcleaning, corrosion prevention, touch-up painting, etc., deter-mine and comply with all local environmental requirements,i.e., laws and regulations.

A.1.5 Units of Issue Codes. The units of issue codes inthe unit issue column and their meaning are as follows inTable A-1:

Table A-1. Units of Issue Codes

CODE UNIT CODE UNIT CODE UNIT

BG Bag EA Each PG PackageBO Bolt FT Foot PR PairBT Bottle GL Gallon PT PintBX Box GR Gross QT QuartCA Cartridge JR Jar RO RollCB Carboy KG Kilogram SE SetCC Cubic Cent. KT Kit SH SheetCN Can L Liter TU TubeCO Container LB Pound YD YardCS Case LG LengthDR Drum MX ThousandDZ Dozen OZ Ounce

TO 1-1-691

A-1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Abr

asiv

es1

Abr

asiv

eM

ats,

Alu

mi-

num

Oxi

de,

Non

-w

oven

,N

on-

met

al-

lic

A-A

-580

54(s

uper

sede

sM

IL-

A-9

962)

Type

I,C

lass

1(9

x11

inSH

)

Alu

min

umox

ide

impr

egna

ted

nylo

nfib

erw

ebbi

ngus

edfo

rre

mov

ing

corr

osio

npr

oduc

tsan

dfo

rpa

int

scuf

fing

and

feat

heri

nged

ges

prio

rto

touc

h-in

gup

.G

rade

A(V

ery

Fine

)53

50-0

0-96

7-50

89PG

(10

SH)

Gra

deB

(Fin

e)53

50-0

0-96

7-50

93PG

(10

SH)

Gra

deC

(Med

ium

5350

-00-

967-

5092

PG(1

0SH

)2

Abr

asiv

ePa

per,

Alu

mi-

num

Oxi

de,

Non

-w

ater

proo

f

(9x

11in

SH)

Dry

sand

ing

tore

mov

elig

htto

mod

erat

eco

rros

ion

prod

ucts

.24

0G

rit

5350

-00-

829-

3981

PG(5

0SH

)18

0G

rit

5350

-01-

322-

1122

PG(5

0SH

)3

Abr

asiv

ePa

per,

Silic

onC

arbi

de,

Wat

erpr

oof

AN

SIB

74.1

8(s

uper

sede

sA

-A-1

047)

(9x

11in

SH)

Wet

ordr

ysa

ndin

gto

rem

ove

light

tom

oder

ate

cor-

rosi

onpr

oduc

ts.

180

Gri

t53

50-0

0-72

1-81

17PG

(50

SH)

240

Gri

t53

50-0

0-22

4-72

05PG

(50

SH)

320

Gri

t53

50-0

1-04

3-22

78PG

(50

SH)

4A

bras

ive

Pape

r,Si

licon

Car

bide

,N

on-

wat

erpr

oof

220

Gri

t53

50-0

0-22

4-72

09PG

(50

SH)

Dry

sand

ing

tore

mov

elig

htto

mod

erat

eco

rros

ion

prod

ucts

.32

0G

rit

5350

-00-

867-

7665

PG(5

0SH

)

5A

bras

ive

Pape

rD

iscs

,Pr

essu

reSe

nsiti

veB

acki

ng,

Silic

onC

ar-

bide

AN

SIB

74.1

8(s

uper

sede

sA

-A-2

697)

(6in

Ddi

sc)

Dry

sand

ing

tore

mov

elig

htto

mod

erat

eco

rros

ion

prod

ucts

.Fo

rus

ew

ithpn

eum

atic

drill

sor

orbi

tal

sand

ers

with

a6

inch

diam

eter

pad.

180

Gri

t53

45-0

1-07

4-94

04R

O(2

50E

A)

280

Gri

t53

45-0

1-07

4-94

06R

O(2

50E

A)

6A

bras

ive

Clo

th,A

lum

i-nu

mO

xide

,W

ater

-pr

oof

AN

SIB

74.1

8(s

uper

sede

sA

-A-1

048)

(9x

11in

SH)

Wet

ordr

ysa

ndin

gto

rem

ove

light

tom

oder

ate

cor-

rosi

onpr

oduc

ts.

240

Gri

t53

50-0

0-86

5-59

48PG

(25

EA

)32

0G

rit

5350

-00-

597-

5798

PG(2

5E

A)

7A

bras

ive

Clo

th,A

lum

i-nu

mO

xide

,N

on-

wat

erpr

oof

AN

SIB

74.1

8(s

uper

sede

sA

-A-1

048)

Dry

sand

ing

tore

mov

elig

htto

mod

erat

eco

rros

ion

prod

ucts

.

180

Gri

t(9

x11

inSH

)53

50-0

0-19

2-50

51PG

(50

EA

)18

0G

rit

(3x

150

ftR

O)

5350

-00-

229-

3095

RO

(50

YD

)24

0G

rit

(9x

11in

SH)

5350

-00-

161-

9715

PG(5

0E

A)

240

Gri

t(3

x15

0ft

RO

)53

50-0

0-22

9-30

80R

O(5

0Y

D)

320

Gri

t(9

x11

inSH

)53

50-0

0-24

6-03

30PG

(50

EA

)32

0G

rit

(2x

150

ftR

O)

5350

-00-

187-

6289

RO

(50

YD

)

TO 1-1-691

A-2

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

320

Gri

t(3

x15

0ft

RO

)53

50-0

0-22

9-30

92R

O(5

0Y

D)

8A

bras

ive

Clo

th,

Silic

onC

arbi

de,

Non

-w

ater

proo

f

AN

SIB

74.1

8(s

uper

sede

sA

-A-1

200)

Dry

sand

ing

tore

mov

elig

htto

mod

erat

eco

rros

ion

prod

ucts

.18

0G

rit

(9x

11in

SH)

5350

-00-

559-

7778

PG(5

0SH

)24

0G

rit

(9x

11in

SH)

5350

-00-

297-

6670

PG(5

0SH

)24

0G

rit

(2x

150

ftR

O)

5350

-00-

256-

5162

RO

(50

YD

)32

0G

rit

(2x

150

ftR

O)

5350

-00-

482-

5585

RO

(50

YD

)9

Alu

min

umW

ool

A-A

-104

4R

emov

ing

corr

osio

nfr

omal

umin

umal

loy

surf

aces

.Ty

peII

,C

lass

1,Fo

rmA

(Me-

dium

)53

50-0

0-28

6-48

51R

O(1

LB

)

Type

II,

Cla

ss3,

Form

A(F

ine)

5350

-00-

312-

6129

RO

(1L

B)

10C

oppe

rW

ool

A-A

-104

4R

emov

ing

corr

osio

nfr

omco

pper

allo

y,br

onze

,an

dbr

ass

surf

aces

.Ty

peI,

Cla

ss3

(Fin

e)53

50-0

0-25

5-77

36R

O(1

LB

)11

Stee

lW

ool,

Stai

nles

sA

-A-1

043

Rem

ovin

gco

rros

ion

from

stai

nles

sst

eel

surf

aces

.Ty

peIV

,C

lass

153

50-0

0-44

0-50

35R

O(1

LB

)12

Gla

ssB

ead

Med

ia,

Cle

anin

gan

dPe

en-

ing

SAE

AM

S24

31(A

MS

2431

/6=

AG

B-6

)(s

uper

-se

des

MIL

-G-9

954;

Size

13)

Gla

ssbe

adbl

astin

gm

edia

used

for

rem

ovin

gco

rro-

sion

from

alum

inum

surf

aces

byab

rasi

vebl

astin

g.

5350

-00-

576-

9634

BG

(50

LB

)13

Pum

ice

Abr

asiv

e,Po

w-

der

SS-P

-821

,G

rade

FFF

Rem

ovin

gst

ains

orco

rros

ion

onth

inm

etal

sur-

face

s.53

50-0

0-16

1-90

34C

N(5

LB

)

Che

mic

alC

onve

rsio

nC

oatin

g,C

orro

sion

Rem

oval

,an

dSu

rfac

eT

reat

men

tM

ater

ials

14C

orro

sion

Rem

ovin

gC

ompo

und

for

Air

-cr

aft

Surf

aces

SAE

AM

S16

40(s

uper

sede

sM

IL-C

-383

34)

Aco

ncen

trat

edph

osph

oric

acid

solu

tion

mix

ed1:

1w

ithw

ater

used

onal

umin

umal

loy

surf

aces

tore

mov

esu

rfac

eco

rros

ion/

oxid

atio

nan

dco

rros

ion

prod

ucts

from

corr

osio

npi

tsin

conj

unct

ion

with

A-A

-580

54ny

lon

abra

sive

mat

s.It

isus

edto

re-

mov

eth

eox

ide

film

from

alum

inum

allo

ysu

r-fa

ces

prio

rto

appl

icat

ion

ofa

chro

mat

eco

nver

-si

onco

atin

gdu

ring

pain

ting

oper

atio

ns.

6850

-00-

527-

2426

CN

(5G

L)

6850

-00-

300-

9008

DR

(55

GL

)

TO 1-1-691

A-3

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

15C

hem

ical

Con

vers

ion

Mat

eria

lsfo

rA

lum

i-nu

man

dA

lum

inum

Allo

ys

MIL

-DT

L-8

1706

(sup

erse

des

MIL

-DT

L-8

1706

)C

lass

1A,

Form

III

(rea

dyto

use

pre-

mix

edliq

uid)

8030

-00-

142-

9272

CN

(1PT

)T

reat

men

tof

clea

n,ba

real

umin

uman

dal

umin

umal

loys

toim

part

apr

otec

tive

chro

mat

eco

atin

g.U

sabl

efo

rap

plic

atio

nM

etho

dB

-bru

sh80

30-0

0-06

5-09

57C

N(1

QT

)

Form

II(p

owde

r)80

30-0

0-82

3-80

39C

N(1

GL

)C

lass

1Aco

atin

gspr

ovid

em

axim

umpr

otec

tion

agai

nst

corr

osio

nw

hen

left

unpa

inte

dan

dsu

pe-

rior

adhe

sion

whe

npa

int

syst

ems

are

appl

ied.

Usa

ble

for

appl

icat

ion

Met

h-od

sA

,B

,or

C-

spra

y,br

ush,

orim

mer

sion

8030

-01-

429-

9504

DR

(55

GL

)Po

wde

rfo

rms

(For

ms

IIan

dV

)ha

vean

inde

finite

shel

flif

eun

tilm

ixed

with

deio

nize

d(D

I)w

ater

.

Form

IV(

read

yto

use

pre-

mix

edliq

uid;

thix

otro

pic

solu

tion)

8030

-00-

057-

2354

JR(4

OZ

)

Usa

ble

for

appl

icat

ion

Met

hod

B-b

rush

8030

-00-

926-

9131

CO

(5L

B)

Cla

ss3

coat

ings

are

inte

nded

for

use

asa

corr

o-si

onpr

even

tive

film

for

elec

tric

alan

del

ectr

onic

appl

icat

ions

whe

relo

wer

resi

stan

ceco

ntac

tsar

ere

quir

ed.

Form

V(p

owde

r-pr

emea

sure

dam

ount

for

thix

otro

pic

solu

-tio

ns)

8030

-00-

720-

9739

CN

(12

LB

)

Suita

ble

for

appl

icat

ion

Met

hod

B-

brus

h80

30-0

0-66

3-98

47D

R(1

75L

B)

Touc

h-N

-Pre

p(T

NP)

Pen

with

Alo

dine

1132

Form

VI

(rea

dyto

use

pre-

mix

edliq

uid

inse

lfco

n-ta

ined

appl

icat

orde

vice

)

8030

-01-

043-

7644

CN

(5G

L)

Suita

ble

for

appl

icat

ion

Met

hod

D-t

ouch

upap

plic

a-to

rpe

n

8030

-01-

069-

3030

JR(1

QT

)Fo

rms

IVan

dV

are

thix

otro

pic

solu

tions

suita

ble

for

brus

hap

plic

atio

n(M

etho

dB

)on

vert

ical

and

over

head

alum

inum

allo

ysu

rfac

esan

dtit

aniu

mal

loy

surf

aces

Cla

ss3

8030

-01-

460-

0246

CS

(12

EA

)T

hese

appl

icat

orpe

nspr

ovid

ea

clea

n,ea

sy,

read

y-to

-use

met

hod

for

appl

icat

ion

ofM

IL-D

TL

-81

706

(MIL

-DT

L-8

1706

),C

lass

1Ach

emic

alco

nver

sion

coat

ing

mat

eria

lsto

alum

inum

allo

ysin

touc

h-up

oper

atio

ns.

The

trea

ted

surf

aces

dono

tre

quir

eri

nsin

gor

wip

eof

f.

Form

III

(rea

dyto

use

pre-

mix

edliq

uid)

Suita

ble

for

appl

icat

ion

Met

hod

B-b

rush

8030

-01-

451-

0284

CN

(1G

L)

TO 1-1-691

A-4 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

16C

hem

ical

Con

vers

ion

Mat

eria

lsfo

rA

lum

i-nu

man

dA

lum

inum

Allo

ys(n

on-

ferr

icya

nide

cata

-ly

zed)

MIL

-DT

L-8

1706

(sup

erse

des

MIL

-DT

L-8

1706

),C

lass

1A&

3

Non

-fer

ricy

anid

eco

nver

sion

coat

ing

for

the

trea

t-m

ent

ofcl

ean,

bare

alum

inum

allo

ysu

rfac

esto

impa

rta

chro

mat

eco

atin

gw

here

ferr

icya

nide

mat

eria

lsca

use

prob

lem

sfo

rth

elo

cal

was

tedi

spos

al/tr

eatm

ent

(sew

er)

syst

em.

Alo

dine

600,

Cla

ss1A

,Fo

rmII

,M

etho

dB

-bru

sh80

30-0

0-81

1-37

23B

T(2

LB

)

Alo

dine

600,

Cla

ss3,

Form

II,

Met

hod

B-b

rush

8030

-01-

018-

2838

CO

(10

LB

)

Tur

coat

Alu

mig

old,

Cla

ss1A

,Fo

rmII

,M

etho

dB

-bru

sh80

30-0

1-34

1-86

09C

B(1

25L

B)

17M

agne

sium

Allo

y,Pr

o-ce

sses

for

Pret

reat

-m

ent

and

Prev

entio

nof

Cor

rosi

onO

n(H

enke

lPr

oces

s)

SAE

AM

S-M

-317

1(s

uper

-se

des

MIL

-M-3

171)

Type

VI

(chr

omic

acid

brus

h-on

trea

tmen

t)

Tre

atm

ent

ofcl

ean,

bare

mag

nesi

uman

dits

allo

ysto

impa

rta

prot

ectiv

ech

rom

ate

coat

ing

usin

gth

isH

enke

lPr

oces

spr

emix

edre

ady

tous

ech

ro-

miu

mtr

ioxi

dean

dca

lciu

msu

lfat

em

ixtu

re.

The

inst

ruct

ions

for

prep

arin

gth

isso

lutio

nfr

ompo

wde

rs(C

hrom

ium

Tri

oxid

ean

dC

alci

umSu

l-fa

te)

-lis

ted

inIt

em#’

s18

and

19)

onsi

teca

nbe

foun

din

Cha

pter

5,Se

ctio

nII

ofth

ism

anua

l.

8030

-015

12–2

416

CO

(1Q

T)

18C

hrom

ium

Tri

oxid

e,Te

chni

cal

(Chr

omic

Aci

d)

A-A

-558

27(s

uper

sede

sO

-C-

303)

6810

-00-

264-

6517

CN

(5L

B)

One

oftw

och

emic

als

used

topr

epar

ea

mag

ne-

sium

conv

ersi

onco

atin

gso

lutio

n(S

AE

AM

S-M

-31

71,

Type

VI)

per

Cha

pter

5,Se

ctio

nII

ofth

ism

anua

l.19

Des

icca

nt,

Cal

cium

Sulf

ate,

Anh

ydro

us,

Tech

nica

l

O-D

-210

6810

-00-

242-

4066

CN

(1L

B)

One

oftw

och

emic

als

used

topr

epar

ea

mag

ne-

sium

conv

ersi

onco

atin

gso

lutio

n(S

AE

AM

S-M

-31

71,

Type

VI)

per

Cha

pter

5,Se

ctio

nII

ofth

ism

anua

l.

TO 1-1-691

Change 1 A-5

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

20C

orro

sion

Rem

ovin

gan

dM

etal

Con

ditio

n-in

gC

ompo

und

(Pho

spho

ric

Aci

dB

ase)

MIL

-C-1

0578

Aco

ncen

trat

edph

osph

oric

acid

solu

tion

whi

chis

dilu

ted

with

wat

eran

dus

edto

rem

ove

corr

osio

n/ru

stfr

omfe

rrou

sm

etal

surf

aces

and

slig

htly

etch

the

surf

ace

offe

rrou

san

dso

me

non-

ferr

ous

sur-

face

sto

prom

ote

adhe

sion

ofpa

int

syst

ems

and

CPC

’s.

Type

sI

&II

are

used

for

rust

rem

oval

from

ferr

ous

met

als

afte

rhe

avy,

encr

uste

dru

stis

rem

oved

mec

hani

cally

and

asa

surf

ace

cond

i-tio

ner

for

ferr

ous

and

som

eno

n-fe

rrou

sm

etal

surf

aces

prio

rto

pain

ting

orC

PCap

plic

atio

n.Ty

peI

rem

oves

mor

eru

stan

dre

quir

esri

nsin

gw

ithw

ater

,w

hile

Type

IIis

wip

edof

fw

ithcl

ean

rags

.Ty

peII

Iis

used

tore

mov

eru

stfr

omch

ro-

miu

mpl

ated

stee

lsu

rfac

es.

Type

Vis

used

tore

-m

ove

rust

from

ferr

ous

met

alpa

rts

imm

erse

din

adi

pta

nkaf

ter

all

grea

sean

doi

lha

vebe

encl

eane

dfr

omth

esu

rfac

es.

Type

I(W

ash-

off)

6850

-00-

270-

5551

BT

(1G

L)

6850

-00-

656-

1291

DR

(5G

L)

6850

-00-

926-

5298

DR

(15

GL

)

Tank

)Ty

peII

(Wip

e-of

f)68

50-0

0-17

4-96

72B

T(1

GL

)

6850

-00-

656-

1292

DR

(5G

L)

Type

III

(Inh

ibite

d)68

50-0

085

4-79

52D

R(5

GL

)

Type

V(I

mm

ersi

on68

50-0

1-10

7-25

51C

O(4

GL

)

6850

-00-

551-

9577

DR

(15

GL

)

Do

not

use

thes

em

ater

ials

onhi

ghst

reng

thst

eel

part

sas

they

can

caus

ehy

-dr

ogen

embr

ittle

men

t.

Cle

anin

gC

ompo

unds

21C

lean

ing

Com

poun

d:A

ircr

aft,

Ext

erio

rM

IL-P

RF-

8557

0

Type

I(G

ener

alpu

rpos

e,68

50-0

1-23

7-74

82C

N(5

GA

L)

Cle

anin

gof

pain

ted

and

unpa

inte

dai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

.C

heck

for

regu

lato

ryco

mpl

ianc

ebe

fore

usin

gTy

peI

beca

use

itco

n-ta

ins

arom

atic

solv

ents

.

arom

atic

solv

ent

base

d)68

50-0

1-23

7-80

03D

R(1

5G

AL

)

6850

-01-

237-

8004

DR

(55

GA

L)

Type

II(G

ener

alpu

rpos

e,68

50-0

1-23

9-05

71G

L(1

GA

L)

Cle

anin

gof

pain

ted

and

unpa

inte

dai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

.W

ater

base

dfo

rmul

am

aybe

used

onbo

thhi

ghgl

oss

and

cam

oufla

gepa

int

syst

ems.

non-

solv

ent

base

d)68

50-0

1-23

5-08

72C

N(5

GA

L)

6850

-01-

248-

9828

DR

(15

GA

L)

6850

-01-

236-

0128

DR

(55

GA

L)

TO 1-1-691

A-6

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Type

III

(Abr

asiv

esp

otcl

eane

r)68

50-0

1-23

2-91

64C

N(5

GL

)U

seon

high

glos

spa

int

sche

me

coat

ings

tore

mov

est

ubbo

rnco

ntam

inan

tssu

chas

boot

mar

ksan

dsm

udge

sas

wel

las

gun

blas

tan

dex

haus

ttr

ack

soil.

21 Con

t.Ty

peIV

(Rub

beri

zed

spot

clea

ner)

6850

-01-

235-

0873

CN

(5G

AL

)U

seon

low

glos

s,ca

mou

flage

pain

tsc

hem

eco

atin

gsto

rem

ove

stub

born

cont

amin

ants

such

asbo

otm

arks

and

smud

ges

asw

ell

asgu

nbl

ast

and

ex-

haus

ttr

ack

soil.

6850

-01-

248-

9829

DR

(15

GA

L)

6850

-01-

248-

9830

DR

(55

GA

L)

Type

V(G

el-t

ype

clea

ner)

6850

-01-

234-

0219

CN

(5G

AL

)C

lean

ing

ofw

heel

wel

ls,

win

gbu

tts,

and

othe

rar

eas

whe

reco

mpl

ete

rins

ing

with

wat

erca

nbe

tole

r-at

ed.

Thi

xotr

opic

clea

ner

clin

gsto

vert

ical

orov

erhe

adsu

rfac

es.

6850

-01-

248-

9831

DR

(15

GA

L)

6850

-01-

235-

7458

DR

(55

GA

L)

22C

lean

ing

Com

poun

d,A

eros

pace

Equ

ip-

men

t

MIL

-PR

F-87

937

Type

I(T

erpe

neba

sed,

solv

ent

emul

sion

,w

ater

dilu

tabl

e)68

50-0

1-39

0-78

08C

N(1

GL

)Te

rpen

eba

sed.

Goo

dge

nera

lcl

eane

rfo

rhe

avily

soile

dca

mou

flage

and

high

glos

spa

inte

dar

eas

and

unpa

inte

dm

etal

surf

aces

.R

equi

res

adeq

uate

vent

ilatio

nan

dco

mpl

ete

rins

ing

ofen

trap

men

tar

eas.

May

requ

ire

airc

raft

SPD

and/

orm

issi

leor

equi

pmen

tSP

Map

prov

albe

fore

itis

used

.

6850

-01-

390-

7811

CN

(5G

L)

6850

-01-

390-

7816

DR

(55

GL

)68

50-0

1-46

1-00

65B

T(2

4O

Z)

Spra

yT

rig-

ger

Type

II(W

ater

dilu

tabl

ecl

ean-

ing

com

poun

d)68

50-0

1-39

0-78

27C

N(1

GL

)A

tpr

esen

t,th

isis

the

prim

ary

gene

ral

clea

ner

for

cam

oufla

gean

dgl

oss

pain

ted

and

unpa

inte

dm

etal

surf

aces

onai

rcra

ft,

mis

sile

s,an

deq

uipm

ent.

Itw

illbe

dele

ted

in20

05an

dre

plac

eden

tirel

yby

the

Type

IVcl

eane

r.

6850

-01-

339-

5227

CN

(5G

L)

6850

-01-

339-

5228

DR

(55

GL

)

Type

III

(Gel

type

clea

ning

com

poun

d)68

50-0

1-39

0-95

30C

N(5

GL

)V

isco

us,

thix

otro

pic

gel

clea

ner

for

very

heav

ilyso

iled

area

ssu

chas

airc

raft

cont

rol

surf

ace

and

whe

elw

ells

whe

rea

long

dwel

ltim

eis

requ

ired

.U

seon

lyin

area

sth

atto

lera

tehe

avy

rins

ing.

6850

-01-

390-

9453

DR

(55

GL

)

TO 1-1-691

A-7

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

22 Con

t.Ty

peIV

(Hea

vydu

ty,

wat

erdi

luta

ble

clea

ning

com

-po

und)

6850

-01-

429-

2368

CN

(1G

L)

Hea

vydu

tycl

eane

req

ually

suite

dfo

rhe

avily

soile

dar

eas

and

asa

gene

ral

clea

ner

for

clea

ning

cam

-ou

flage

and

glos

spa

inte

dan

dba

rem

etal

surf

aces

ofai

rcra

ft,

mis

sile

s,an

deq

uipm

ent.

In20

05,

itw

illco

mpl

etel

yre

plac

eTy

peII

clea

ner.

6850

-01-

433-

0873

CN

(5G

L)

6850

-01-

429-

2371

DR

(55

GL

)68

50-0

1-46

1-00

60B

T(2

4O

Z)

Spra

yT

rig-

ger

6850

-01-

461-

0070

CN

(16

OZ

)A

eros

ol23

Cle

anin

gC

ompo

unds

,A

ircr

aft

Surf

ace

MIL

-C-4

3616

6850

-01-

045-

7929

CN

(5G

L)

Aso

lven

tem

ulsi

onty

pecl

eane

rfo

rre

mov

alof

oily

and

grea

syso

ils.

The

Cla

ss1A

aero

sol

mat

eria

lis

anex

celle

ntsp

otcl

eane

rfo

rth

ese

type

sof

soils

.C

lass

1(l

iqui

d)68

50-0

1-04

5-79

30D

R(1

5G

L)

6850

-01-

045-

7931

DR

(55

GL

)C

lass

1A(l

iqui

d/

aero

sol)

6850

-01-

005-

5305

CN

(16

OZ

)A

eros

ol24

Cle

anin

gC

ompo

und:

Eng

ine

Gas

Path

Cle

aner

MIL

-PR

F-85

704

Rem

oves

accu

mul

ated

salt,

dirt

,an

doi

lyre

sidu

esfr

omth

ega

spa

thof

engi

nes.

Type

I(S

olve

ntem

ulsi

oncl

eane

rco

ncen

trat

ew

/hy-

droc

arbo

nso

lven

t)

6850

-00-

181-

7594

CN

(5G

L)

Solv

ent

conc

entr

ate

for

clea

ning

the

com

pres

sor

sect

ion

ofga

stu

rbin

een

gine

s(e

ngin

eof

f-lin

e;st

arte

rcr

anke

d).

6850

-00-

181-

7597

DR

(55

GL

)

Type

II(A

queo

uscl

eane

rco

n-ce

ntra

te)

6850

-01-

372-

8303

CN

(5G

L)

Aqu

eous

conc

entr

ate

for

clea

ning

the

com

pres

sor

sect

ion

ofga

stu

rbin

een

gine

s(e

ngin

eof

f-lin

e;st

arte

rcr

anke

d).

6850

-01-

372-

8304

DR

(55

GL

)

Type

IIR

TU

(Rea

dy-T

o-U

se)

6850

-01-

370-

5245

CN

(5G

L)

Rea

dyto

use

aque

ous

clea

ner

for

clea

ning

gas

tur-

bine

engi

nes

(eng

ine

off-

line;

star

ter

cran

ked)

.68

50-0

1-37

0-52

44D

R(5

5G

L)

Type

III

(Aqu

eous

clea

ner

conc

entr

ate

w/o

hydr

ocar

-bo

nso

lven

t)

6850

-01-

433-

6436

CN

(5G

L)

Aqu

eous

conc

entr

ate.

With

nohy

droc

arbo

nso

lven

tsfo

ron

-lin

e(fi

red)

clea

ning

ofga

stu

rbin

een

gine

sIA

Wsp

ecifi

cen

gine

mai

nten

ance

inst

ruct

ions

.68

50-0

1-43

3-64

38D

R(5

5G

L)

24 Con

t.Ty

peII

IR

TU

(Rea

dy-T

o-U

se)

6850

-01-

472-

1845

CN

(5G

L)

6850

-01-

472-

1846

DM

(55

GL

)

TO 1-1-691

A-8

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

25C

lean

ing

Com

poun

d,fo

rPa

rts

Was

hers

and

Spra

yC

abin

ets

MIL

-PR

F-29

602

(SA

EA

MS-

C-2

9602

)D

eter

gent

for

use

inpa

rts

was

hers

and

spra

yca

bi-

nets

tocl

ean

avia

tion

wea

pons

syst

ems,

engi

ne,

and

supp

ort

equi

pmen

tco

mpo

nent

s.R

emov

esgr

ease

,oi

l,an

ddi

rtw

hich

are

pres

ent

ondi

sas-

sem

bled

com

pone

nts.

Type

I(W

ater

solu

ble

liqui

dco

ncen

trat

e)68

50-0

1-43

1-22

69C

N(1

GA

L)

6850

-01-

431-

2267

CN

(5G

AL

)68

50-0

1-43

1-22

68D

R(5

5G

AL

)D

SF-1

,Te

lech

emIn

t’l

Inc

6850

-01-

524-

2956

BX

(4G

LC

onta

iner

s)P/

ND

SF-1

Hea

vyD

uty

6850

-01-

524-

2978

CO

(5L

B)

Aqu

eous

Part

sW

ashe

r,C

lean

eran

dD

egre

aser

6850

-01-

524-

2980

DR

(55

GL

)

.Ty

peII

(Wat

erso

lubl

epo

w-

der)

TH

EM

AT

ER

IAL

SL

IST

ED

BE

LO

WA

RE

AP

PR

OV

ED

FO

RU

SEO

NL

AN

DIN

GG

EA

RC

OM

PO

NE

NT

SA

ND

IVD

CO

AT

ED

HIG

HST

RE

NG

TH

STE

EL

PAR

TS

6850

-01-

053-

2789

CO

(1L

B)

Do

not

use

thes

ecl

eane

rson

airc

raft

land

-in

gge

arco

mpo

nent

s,w

heel

s,an

dbr

akes

,or

any

IVD

alum

inum

coat

edhi

ghst

reng

thst

eel

part

sas

they

may

caus

ehy

drog

enem

britt

lem

ent.

Use

only

mat

eri-

als

appr

oved

byan

dlis

ted

onth

ela

test

revi

sion

ofA

FD

raw

ing

#98

2501

9on

airc

raft

land

ing

gear

com

pone

nts,

whe

els,

and

brak

es,

and

onan

yot

her

IVD

alum

i-nu

mco

ated

high

stre

ngth

stee

lpa

rts.

6850

-01-

431-

9025

CO

(50

LB

)68

50-0

1-43

1-90

24D

R(4

00L

B)

(Zip

Che

mic

alPr

oduc

tsC

o;C

age

Cod

e#

1KQ

X9)

PNC

alla

-296

(Con

cent

rate

dem

ulsi

fyin

gty

peliq

uid

clea

ner)

6850

-01-

485-

5972

CO

(1G

L)

6850

-01-

485-

5932

CO

(5G

L)

6850

-01-

485-

5950

DR

(55

GL

)PN

Cal

la60

2LF

(Con

cen-

trat

edno

n-em

ulsi

fyin

gty

peliq

uid

clea

ner)

6850

-01-

513-

5230

CO

(1G

L)

6850

-01-

513-

5237

CO

(5G

L)

6850

-01-

513-

5233

DR

(55

GL

)

TO 1-1-691

Change 1 A-9

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

26D

eici

ng/A

nti-

Icin

gFl

uid,

Air

craf

t,SA

ETy

peI

SAE

AM

S14

24(s

uper

sede

sM

IL-A

-824

3)68

50-0

1-43

5-64

71C

O(1

GL

)Fl

uid

isge

nera

llyus

edhe

ated

,ei

ther

dilu

ted

with

wat

eror

assu

pplie

d,fo

rth

ere

mov

alof

and

time-

limite

dpr

otec

tion

agai

nst

depo

sits

offr

ost,

ice,

and

snow

onex

teri

orai

rcra

ftsu

rfac

espr

ior

tota

ke-o

ff.

Itis

also

used

mix

edw

ithM

IL-P

RF-

8793

7,Ty

peIV

,or

MIL

-PR

F-85

570,

Type

IIso

lu-

tions

for

low

tem

pera

ture

clea

ning

per

Para

grap

h3.

5.2.

6.

6850

-01-

435-

6468

CN

(5G

L)

6850

-01-

435-

6465

DR

(55

GL

)

6850

-01-

449-

9469

CO

(275

GL

Tote

)

27D

ishw

ashi

ngC

om-

poun

d,H

and

(Syn

-th

etic

Det

erge

nt,

Solid

and

Liq

uid

Form

),

P-D

-410

Type

IIliq

uid

mix

edw

ithfr

esh

wat

erw

illre

mov

egr

ease

,oi

l,an

ddi

rtfr

oma

wid

eva

riet

yof

sur-

face

s.Ty

peII

(Con

cent

rate

dliq

uid,

clea

ror

opaq

uelo

tion,

non-

phos

phat

e)

7930

-00-

764-

5066

BT

(1Q

T)

7930

-00-

880-

4454

BT

(6E

A/

1G

L)

7930

-00-

899-

9534

CN

(5G

L)

28C

lean

ing

Com

poun

d,So

lven

tM

ixtu

res

A-A

-592

81(s

uper

sede

sM

IL-

C-3

8737

)Ty

peI

(Sol

vent

blen

dth

atco

ntai

nsan

aro-

mat

icso

lven

t)

Thi

sso

lven

tbl

end

isus

edto

clea

nal

lty

pes

ofso

ils(b

oth

pola

ran

dno

n-po

lar)

from

surf

aces

befo

reap

plyi

ngse

alan

ts.

6850

-00-

611-

7993

CN

(1PT

)68

50-0

0-53

8-09

29C

N(1

GL

)68

50-0

1-01

6-34

82D

R(5

5G

L)

29D

isin

fect

ant,

Gen

eral

Purp

ose

(Liq

uid

Phe-

nolic

Type

)an

d

A-A

-143

9T

reat

men

t,di

sinf

ectin

g/sa

nitiz

ing,

and/

orde

oder

iz-

ing

ofre

lief

tube

area

s,la

trin

ear

eas,

urin

als,

toi-

let

bow

ls,

latr

ine

buck

ets,

garb

age

rece

ptac

les,

sink

s,ga

lley

area

,an

dot

her

airc

raft

inte

rior

area

sre

quir

ing

disi

nfec

tion.

Sani

tizer

,Ph

enol

icTy

pe,

Con

cent

rate

O-D

-143

5Pr

emix

edL

iqui

d(e

ither

mat

eria

l)68

40-0

0-53

0-71

09B

X(

4E

A/

1GL

CO

)D

ilute

with

tap

wat

eras

dire

cted

byth

em

anuf

ac-

ture

ron

the

cont

aine

rbe

fore

use.

Pow

der

(O-D

-143

5on

ly)

6840

-00-

753-

4797

BX

(12

EA

/8

OZ

PG)

Mix

one

8O

ZPG

in2

QT

tap

wat

erfo

rcl

eani

ngla

trin

ebu

cket

s,ur

inal

s,an

dto

ilets

,an

don

e8

OZ

PGin

4G

Lta

pw

ater

for

all

othe

rcl

eani

ngpr

o-ce

sses

.D

isin

fect

ant

Cle

aner

for

Air

craf

tIn

teri

or(G

ener

alPu

rpos

eL

iqui

d)

SAE

AM

S14

53(E

coT

ru®

1453

TM

;Z

ipC

hem

ical

Prod

ucts

Co;

Cag

eC

ode

#1K

QX

9)

Com

mer

cial

Item

CO

(PT,

QT,

GL

,&

5G

L)

For

gene

ral

clea

ning

ofal

lai

rcra

ftin

teri

orar

eas

requ

irin

gdi

sinf

ectio

n.C

omes

read

y-to

-use

with

nom

ixin

gor

dilu

tion

requ

ired

.Fo

llow

the

man

u-fa

ctur

e’s

inst

ruct

ions

for

use.

30D

elet

ed

TO 1-1-691

A-10 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

31W

ater

Rep

elle

nt:

Win

-do

wan

dW

inds

hiel

d,G

lass

and

Plas

tic

SAE

AS

6882

(sup

erse

des

MIL

-W-6

882)

6850

-00-

139-

5297

BT

(8O

Z)

Ant

i-w

ettin

gfil

mfo

rex

teri

orgl

ass

orac

rylic

plas

ticw

indo

ws

and

win

dshi

elds

toas

sure

good

visi

bilit

yun

der

rain

yco

nditi

ons.

32Po

lish,

Met

al,A

lum

i-nu

mA

-A-5

9318

(sup

erse

des

MIL

-P-

6888

)Po

lishi

ngun

pain

ted

alum

inum

surf

aces

ofai

rcra

ft.

The

abra

sive

qual

ityof

the

polis

hen

able

sit

tore

mov

eta

rnis

han

dpr

oduc

ea

high

last

ing

shin

e.T

hepo

lish

shal

lno

tbe

used

onal

umin

umai

rcra

ftsu

rfac

esth

atar

eto

bepa

inte

d.

Type

I(L

iqui

d)79

30-0

0-26

6-71

31C

N(1

QT

)79

30-0

0-26

7-12

24C

N(1

GL

)Ty

peII

(Pas

te)

7930

-00-

734-

4010

CN

(1Q

T)

33Po

lish,

Plas

ticP-

P-56

0C

lean

ing

and

polis

hing

ofpl

astic

mat

eria

lsto

re-

mov

elig

htsc

ratc

hes,

and

inth

eap

plic

atio

nof

anan

tista

ticfil

mw

hich

will

prev

ent

the

elec

tros

tatic

attr

actio

nof

dust

,lin

t,as

h,et

c.,

toac

rylic

plas

ticsu

rfac

es.

Type

I(L

iqui

d)79

30-0

0-63

4-53

40B

T(1

PT)

7930

-00-

935-

3794

BX

(24

EA

8oz)

7930

-01-

133-

5375

BX

(1D

Z)

7930

-01-

115-

4744

CN

(1PT

)34

Era

sers

,R

ubbe

rA

-A-1

32(s

uper

sede

sZ

Z-E

-66

1)R

emov

alof

light

tarn

ish

orco

rros

ion

from

elec

tric

alco

nnec

tors

and

cont

acts

and

othe

rav

ioni

csco

m-

pone

nts.

Rec

tang

ular

with

beve

led

ends

(25/ 8

inL

x½

inW

x7/ 8

inT

7510

-00-

949-

5055

BX

(1D

Z)

Rec

tang

ular

(2in

Lx

¾in

Wx

7/ 8

inT

)75

10-0

0-32

3-87

88B

X(1

DZ

)

Cle

anin

gPa

ds/C

loth

s35

Face

Res

pira

tor

Cle

an-

ing

Wip

e(t

owel

ette

s)3M

Co.

PN50

4(C

age

Cod

e#

OT

1L6)

Hyg

ieni

ccl

eani

ngof

resp

irat

ors

and

othe

rpe

rson

alpr

otec

tive

gear

/equ

ipm

ent

(alc

ohol

-fre

efo

rmul

a).

11x

8.5

inW

ipes

4240

-01-

372-

3078

BX

(100

PK)

6510

-01-

397-

4339

CS

(5B

Xof

100

PK)

36C

lean

ing

Com

poun

d,O

ptic

alL

ens

(Rea

dyto

Use

)

A-A

-591

99(s

uper

sede

sM

IL-

C-4

3454

)C

lean

ing

ofex

pose

dop

tical

surf

aces

.

Type

I(2

0%al

coho

l)68

50-0

0-39

2-97

51B

T(2

OZ

)68

50-0

0-22

7-18

87B

T(1

QT

)Ty

peII

(57%

alco

hol)

6850

-00-

188-

9875

BT

(1Q

T)

37C

lean

er,

Pipe

PN:

8405

07(C

age

Cod

e#

6406

7)99

20-0

0-29

2-99

46B

X(1

344

EA

)C

lean

ing

smal

lor

ifice

san

dcr

evic

es

TO 1-1-691

A-11

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

38Pa

d,C

lean

ing

and

Pol-

ishi

ngN

on-m

etal

lic(f

orai

rcra

ftcl

eani

ngki

t)

A-A

-310

0(s

uper

sede

sM

IL-C

-83

957)

Non

-wov

en,

non-

met

allic

,no

n-ab

rasi

ve,

poly

este

rcl

eani

ngan

dpo

lishi

ngpa

ds(1

2″L

x6″

W)

for

use

onai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

.R

epla

cem

ent

pads

for

airc

raft

was

hki

t(A

ppen

dix

B,

Item

No.

1)

Type

I(3

/ 8in

T)

7920

-00-

151-

6120

PG(1

0SH

)

Type

II(1

inT

)79

20-0

0-17

1-15

34PG

(10

SH)

39A

ircr

aft

Cle

anin

gPa

ds3M

Co.

PN61

-500

1-87

94-5

6850

-01-

496-

4913

CS

(200

EA

)N

on-w

oven

,no

n-m

etal

lic,

non-

abra

sive

,po

lyes

ter

clea

ning

and

polis

hing

pads

with

impr

egna

ted

rubb

erpa

rtic

les

for

clea

ning

ofai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

.T

hese

pads

prov

ide

im-

prov

edcl

eani

ngef

ficie

ncy

over

the

Item

#38

pads

.

Scot

chbr

ite®

#33

(3½

x5

inpa

d

(Cag

eC

ode

#(I

m-

prov

edTy

pe)

7638

1)3M

#96

1;PN

61-5

000-

4615

-8(3

½x

5in

pad

hold

er-

hand

held

)

Loc

alPu

rcha

seC

S(1

0E

A)

3MC

o.PN

61-5

001-

8795

-268

50-0

1-49

6-49

03C

S(1

00E

A)

(45/ 8

x10

inpa

d3M

#250

;PN

61-5

000-

4913

-7(4

5/ 8

x10

inpa

dho

lder

-han

dhe

ld)

Loc

alPu

rcha

seC

S(5

EA

)

3MC

o.PN

61-5

001-

8796

-068

50-0

1-49

6-49

01C

S(5

0E

A)

(6x

12in

pad)

3M#2

61;

PN61

-500

0-32

35-6

(6x

12in

pad

hold

er-

hand

le

6850

-01-

499-

5307

CS

(1E

A)

Mel

amin

ePa

ds3.

5″X

5″X

1.2″

7920

-01-

526-

9015

BX

(200

EA

)4.

625″

X10

″X

1.3″

7920

-01-

526-

9007

BX

(100

EA

)4.

625″

X10

″X

1.2″

7920

-01-

526-

9003

BX

(10

EA

)6″

X12

″X

1.3″

7920

-01-

526-

9003

BX

(50

EA

)3″

X5″

X1″

6850

-00-

525-

7684

BX

(6E

A)

40C

ham

ois

Lea

ther

,Sh

eeps

kin,

Oil

Tann

ed

KK

-C-3

00G

ener

alpu

rpos

ew

ashi

ngan

dpo

lishi

ng

Gra

deB

,C

lass

2,Si

ze-

smal

l83

30-0

0-82

3-75

45PG

(5E

A)

TO 1-1-691

A-12 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

41C

hees

eclo

th,

Cot

ton,

Ble

ache

dan

dU

n-bl

each

ed

CC

C-C

-440

Cle

anin

gan

dpo

lishi

ngai

rcra

ft,

mis

sile

,an

deq

uip-

men

tsu

rfac

es.

Type

I,C

lass

2(b

leac

hed)

8305

-00-

262-

3321

BO

(36

inx

50Y

D)

8305

-00-

205-

3495

BO

(36

inx

100

YD

)Ty

peI,

Cla

ss1

(unb

leac

hed)

8305

-00-

222-

2423

PG(3

8.5

inx

1Y

D)

Type

II,

Cla

ss2

(ble

ache

d)83

05-0

0-20

5-34

96PG

(36

inx

10Y

D)

8305

-00-

267-

3015

PG(3

6in

x1

YD

)42

Clo

th,

Cle

anin

g,N

on-

wov

enFa

bric

CC

C-C

-46

Gen

eral

clea

ning

(e.g

.w

ipin

gup

grea

sean

dliq

uid

spill

s)w

here

low

resi

dual

surf

ace

cont

amin

atio

nis

requ

ired

.Ty

peI

(Unt

reat

ed)

Cla

ss1

(Lig

htdu

ty)

8305

-00-

753-

2967

RO

(36

inx

50Y

D)

Cla

ss4

(Ext

rahe

avy

duty

)79

20-0

0-29

2-92

04B

X(M

X)-

150

in2

EA

7920

-01-

130-

7738

PG(H

D)

-12

x15

inE

AC

lass

6(L

ight

duty

,pe

rfor

ated

orno

n-pe

rfor

ated

)79

20-0

0-40

1-80

34B

X(H

D)

-150

in2

EA

Cla

ss7

(Air

craf

tso

lven

tw

iper

)79

20-0

1-18

0-05

5618

BX

(150

EA

-8¾

x8¼

in)

7920

-01-

180-

0557

BX

(800

EA

-16

¾in

x20

¾in

)

TO 1-1-691

Change 1 A-13

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

43C

loth

es,

Cle

anin

gfo

rA

ircr

aft

Prim

ary

and

Seco

ndar

ySt

ruct

ural

Surf

aces

SAE

AM

S38

19;

Cla

ss2,

Gra

deA

(Dup

ont-

Sont

ara®

AC

TM

Air

craf

tW

ipes

;D

is-

trib

utor

-C

age

Cod

e#

1BL

94)

Use

dfo

rcl

eani

ngsu

rfac

esre

quir

ing

exce

ptio

nally

low

resi

dual

surf

ace

cont

amin

atio

n.

PNA

C91

6568

50-0

1-48

7-28

598B

X(1

00E

A-

9x

16½

in)

PNA

C12

165

6850

-01-

487-

2861

BX

(250

EA

-12

x16

½in

)44

Clo

th:

Flan

nel,

Cot

ton

(Blu

ein

colo

r)A

-A-5

0129

(sup

erse

des

CC

C-

C-4

58)

8305

-00-

913-

5817

BO

(50

YD

)C

lean

ing

and

polis

hing

ofpl

astic

surf

aces

such

asca

nopi

es,

win

dscr

eens

,et

c.45

Clo

th:

Cle

anin

g,L

ow-

Lin

tA

-A-5

9323

Hyd

raul

iccl

ean

room

and

fluid

syst

ems

clea

ning

.

(Whi

tein

colo

r)(s

uper

sede

sM

IL-C

-850

43)

Type

I(C

lean

room

use

-ultr

a-cl

ean,

low

lint

wip

es)

7920

-00-

165-

7195

BX

(10

LB

)

Do

not

use

thes

ecl

oths

with

flam

mab

leso

lven

tsas

fire

may

resu

ltw

hen

used

with

thes

eso

lven

ts.

Type

II(G

ener

alus

ere

quir

ing

low

lint,

high

lyab

sorb

ent

wip

esbu

tno

tto

clea

nro

omst

anda

rds)

7920

-00-

044-

9281

BX

(10

LB

)

Cor

rosi

onPr

even

tive

Com

poun

ds,

Oils

,G

reas

es,

and

Lub

rica

nts

46C

orro

sion

Prev

entiv

eC

ompo

und,

Solv

ent

Cut

back

,C

old

App

li-ca

tion

MIL

-PR

F-16

173

(sup

erse

des

MIL

-C-1

6173

)

Cla

ssII

,G

rade

1-

Har

dFi

lm(L

owV

OC

≤2.8

#/G

L)

8030

-01-

396-

5731

CN

(1PT

)T

hick

,w

ax-l

ike,

hard

film

cons

iste

ncy

for

long

term

prot

ectio

nof

met

alsu

rfac

esag

ains

tco

rros

ion

with

orw

ithou

tco

veri

ngs

(ind

oors

orou

tdoo

rs).

Thi

sm

ater

ial

will

crac

kan

dsp

all

off

the

surf

ace

ator

belo

wa

tem

pera

ture

of0°

F(-

18°

C).

8030

-01-

396-

5732

CN

(1G

L)

8030

-01-

347-

0970

CN

(5G

L)

8030

-01-

396-

5237

DR

(55

GL

)

TO 1-1-691

A-14 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

46 Con

t.C

lass

I,G

rade

2-

Soft

film

(Hig

hV

OC

>2.

8#/

GL

)80

30-0

0-11

8-06

66C

N(1

1O

Z)

Aer

osol

Thi

ck,

grea

se-l

ike

cons

iste

ncy

for

prot

ectin

gm

etal

surf

aces

agai

nst

corr

osio

ndu

ring

rew

ork

orst

or-

age.

Incl

udes

exte

nded

indo

orpr

otec

tion

ofin

te-

rior

orex

teri

orsu

rfac

esw

ithou

tth

eus

eof

barr

ier

mat

eria

ls.

For

outd

oor

prot

ectio

n,th

ism

ater

ial

can

only

beus

edfo

ra

limite

dtim

ew

here

tem

-pe

ratu

reis

not

extr

emel

yho

t.It

will

adhe

reto

surf

aces

and

prov

ide

prot

ectio

nat

tem

pera

ture

sdo

wn

to-4

0°F

(-40

°C

)

8030

-01-

149-

1731

CN

(1Q

T)

8030

-00-

244-

1297

CN

(1G

AL

)

8030

-00-

244-

1298

CN

(5G

AL

)

8030

-00-

244-

1295

DR

(55

GL

)

Cla

ssII

,G

rade

3-

Soft

oily

film

(Low

VO

C≤2

.8#/

GL

)80

30-0

1-39

6-57

35C

N(1

PT)

Soft

,oi

lym

ater

ial

used

todi

spla

cew

ater

,in

clud

ing

salt

wat

er,

from

met

alsu

rfac

esan

djo

int

area

san

dto

prot

ect

them

from

corr

osio

nfo

rlim

ited

peri

ods

(30

days

orle

ss).

Use

dto

prot

ect

criti

cal

bare

stee

lan

dph

osph

ated

stee

lsu

rfac

esof

part

saw

ait-

ing

repa

iror

bein

gsh

ippe

dto

ade

pot

for

repa

ir.Pr

ovid

esin

defin

itepr

otec

tion

for

part

sw

ithin

seal

edba

rrie

rm

ater

ial

cont

aine

rs.

8030

-01-

396-

5748

CN

(1G

L)

8030

-01-

347-

0971

CN

(5G

L)

8030

-01-

396-

5734

DR

(55

GL

)

Cla

ssII

,G

rade

4(T

rans

par-

ent,

non-

tack

yso

ftfil

m)

8030

-01-

396-

5738

CN

(1PT

)T

hin,

tran

spar

ent,

wat

erdi

spla

cing

,ta

ck-f

ree

prot

ec-

tive

film

for

prot

ectio

nof

met

alsu

rfac

esag

ains

tco

rros

ion

duri

ngin

door

stor

age

orw

hen

loca

ted

inin

teri

orar

eas

ofai

rcra

ft,

mis

sile

s,or

equi

pmen

tan

dfo

rlim

ited

outd

oor

pres

erva

tion.

Use

onco

n-tr

olca

bles

,fa

sten

ers,

bare

met

alar

eas,

oran

y-w

here

tem

pora

ry(3

0da

ysor

less

)pr

otec

tion

isne

eded

and

for

long

term

stor

age

ofpa

rts

with

inse

aled

barr

ier

mat

eria

lco

ntai

ner.

Itw

illad

here

tosu

rfac

esan

dpr

ovid

epr

otec

tion

atte

mpe

ratu

res

dow

nto

-40°

F(-

40°

C).

8030

-01-

396-

5743

CN

(1G

L)

8030

-01-

347-

0972

CN

(5G

L)

8030

-01-

396-

5736

DR

(55

GL

)

47C

orro

sion

Prev

entiv

eM

IL-D

TL

-850

54Te

mpo

rary

repa

irof

smal

lpa

int

dam

age

area

sfr

omch

ips,

scra

tche

s,or

crac

ks.

Inte

nded

for

use

onno

n-m

ovin

gpa

rts

not

requ

irin

ga

lubr

icat

edsu

r-fa

ce,

such

asfa

sten

ers,

seam

s,ac

cess

pane

ls,

join

ts,

unpa

inte

dm

etal

,et

c.D

ries

toa

hard

film

.

TO 1-1-691

Change 1 A-15

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

47 Con

t.C

ompo

und

(AM

L-

GU

AR

D)

Type

I(P

ress

uriz

ed/a

eros

olca

n)C

lass

134A

HC

FCpr

o-pe

llant

8030

-01-

066-

3971

CN

(12

OZ

)

8030

-01-

041-

1596

CN

(16

OZ

)80

30-0

1-34

7-09

79C

N(1

4O

Z)

Type

II(B

ulk

form

)80

30-0

1-34

7-09

83B

T(3

2O

Z-

pum

psp

ray)

8030

-01-

347-

0981

CN

(1Q

T)

8030

-01-

347-

0982

CN

(5G

L)

48C

orro

sion

Prev

entiv

eM

IL-P

RF-

8130

9W

ater

disp

laci

ngC

PCw

hich

may

beap

plie

dby

dipp

ing,

spra

ying

,br

ushi

ng,

orfr

ompr

essu

rize

dco

ntai

ners

.C

ompo

unds

,W

ater

Dis

plac

ing,

Ultr

a-T

hin

Film

Type

II(S

oft

film

)C

lass

1(N

on-p

ress

uriz

edco

n-ta

iner

/bul

k)80

30-0

0-21

3-32

79C

N(1

GL

)Su

itabl

efo

rus

eon

any

met

alsu

rfac

eex

cept

avio

n-ic

s/el

ectr

onic

sap

plic

atio

nsfo

rin

door

and

shor

tte

rmou

tdoo

rpr

otec

tion

whe

resu

rfac

esca

nbe

re-c

oate

dw

hen

requ

ired

.80

30-0

0-26

2-73

58C

N(5

GL

)N

OT

E

Itsh

ould

not

beus

edar

ound

LO

Xfit

tings

.

8030

-00-

524-

9487

DR

(55

GL

)C

lass

2,G

rade

CO

2(P

ress

ur-

ized

cont

aine

r-C

O2

prop

el-

lant

)

8030

-00-

938-

1947

CN

(16

OZ

)

Type

III

(Sof

tfil

m;A

vion

icgr

ade)

Wat

erdi

spla

cing

CPC

for

use

onav

ioni

ceq

uipm

ent,

elec

tric

alco

nnec

tor

plug

s,an

dco

ntac

tpo

ints

.C

lass

1(N

on-p

ress

uriz

edco

n-ta

iner

-bu

lk)

8030

-01-

347-

0978

CN

(1G

AL

)

Cla

ss2

(Pre

ssur

ized

cont

aine

r/ae

roso

l-

non

OD

Spr

opel

-la

nt)

8030

-00-

546-

8637

CN

(16

OZ

)

TO 1-1-691

A-16 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

49L

ubri

cant

s,C

orro

sion

Prev

entiv

eC

om-

poun

d,W

ater

Dis

-pl

acin

g,Sy

nthe

tic

MIL

-L-8

7177

Wat

erdi

spla

cing

CPC

whi

chm

aybe

appl

ied

bydi

ppin

g,br

ushi

ng,

orsp

rayi

ng(p

ump

spra

yer

orae

roso

lsp

ray)

.Su

itabl

efo

rus

eon

any

met

alsu

r-fa

cein

clud

ing

avio

nics

/ele

ctro

nics

equi

pmen

t,el

ectr

ical

conn

ecto

r/pl

ugs,

and

cont

act

poin

tsfo

rin

door

and

shor

tte

rmou

tdoo

rpr

otec

tion

whe

resu

rfac

esca

nbe

re-c

oate

dw

hen

requ

ired

.It

can

beus

edas

anal

tern

ate/

subs

titut

efo

rM

IL-P

RF-

8130

9,Ty

pes

IIan

dII

I.

Type

I(P

ress

uriz

edca

n/A

ero-

sol)

;G

rade

B(W

ithad

ded

corr

osio

nin

hibi

tor)

6850

-01-

328-

3617

CN

(16

OZ

)

Type

II(N

on-p

ress

uriz

edco

n-ta

iner

/bu

lk);

Gra

deB

(With

adde

dco

rros

ion

in-

hibi

tor)

6850

-01-

326-

7294

CN

(5L

)

Do

not

use

arou

ndL

OX

fittin

gsas

fire

may

resu

lt.

50C

orro

sion

Prev

entiv

eC

ompo

und

(Hig

hZ

inc

Dus

tC

onte

ntPa

int)

Com

mer

cial

Prod

uct

Ahi

ghzi

ncdu

stco

nten

tep

oxy

pain

tty

peco

rros

ion

prev

entiv

eco

mpo

und

(als

okn

own

as“c

old

galv

a-ni

ze”)

used

for

repa

irof

defe

cts

inga

lvan

ized

coat

ings

,to

over

coat

wel

ded

area

son

galv

aniz

edst

eel,

and

topr

ovid

eco

rros

ion

for

area

sw

here

corr

osio

nw

asre

mov

edon

stee

lst

ruct

ures

ofsu

p-po

rteq

uipm

ent,

elec

tron

icva

ns,

ante

nna

tow

ers,

and

vehi

cles

.

ZR

CPr

od.

Co.

(Cag

eC

ode

#07

957)

8030

-01-

384-

9932

CN

(1Q

T)

PN82

81-1

0002

ZR

CPr

od.

Co.

(Cag

eC

ode

#07

957)

8030

-01-

015-

1550

CN

(12

OZ

)A

eros

olPN

8281

-100

00D

evco

nC

orp.

(Cag

eC

ode

#160

59)

8010

-00-

501-

5798

CN

(16

OZ

)A

eros

olPN

DE

VC

ON

Z&

NH

CC

orp.

(Cag

eC

ode

#20

913)

PNH

Y-Z

INC

Dev

con

Cor

p.(C

age

Cod

e#

1605

9PN

’s17

03&

1203

080

10-0

0-36

0-33

69C

N(1

GL

)

TO 1-1-691

Change 1 A-17

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

51L

ubri

catin

gO

il,G

en-

eral

Purp

ose,

Pres

er-

vativ

e(W

ater

Dis

-pl

acin

g,L

owTe

mpe

ratu

re)

MIL

-PR

F-32

033

(sup

erse

des

VV

-L-8

00)

9150

-00-

836-

8641

BT

(½O

Z)

Age

nera

lpu

rpos

e,w

ater

disp

laci

ng,

low

tem

pera

-tu

rera

ted

(-40

°F

/-4

0°C

)oi

lth

atca

nbe

appl

ied

bydi

ppin

g,br

ushi

ng,

orsp

rayi

ngfo

rlu

bric

atin

gan

dsh

ort

term

corr

osio

npr

otec

tion

ofm

etal

part

s;ai

rcra

ft,

mis

sile

,an

deq

uipm

ent

hing

es;

and

smal

lar

ms.

9150

-00-

261-

8146

BT

(1O

Z)

9150

-00-

273-

2389

CN

(4O

Z)

9150

-00-

458-

0075

CN

(16

OZ

)A

eros

ol91

50-0

1-37

4-20

21B

T(1

6O

Z)

Pum

pSp

ray

9150

-00-

231-

6689

CN

(1Q

T)

9150

-00-

231-

9045

CN

(1G

L)

9150

-00-

231-

9062

CN

(5G

L)

9150

-00-

281-

2060

DR

(55

GL

)52

Lub

rica

nt,

Cle

aner

and

Pres

erva

tive

for

Wea

pons

and

Wea

p-on

sSy

stem

s(C

LP)

MIL

-PR

F-63

460

9150

-01-

102-

1473

BT

(½O

Z)

Lub

rica

tion

and

shor

tte

rmpr

eser

vatio

nof

airc

raft

,m

issi

le,

and

equi

pmen

thi

nges

,an

dsm

all

and

larg

eca

liber

wea

pons

.C

anbe

used

asan

alte

rnat

eor

subs

titut

efo

rM

IL-P

RF-

3203

3(V

V-L

-800

).91

50-0

1-07

9-61

24B

T(4

OZ

)

Do

not

use

MIL

-PR

F-63

460

onru

bber

orot

her

elas

tom

eric

mat

eria

lsas

itm

ayda

mag

eth

em.

Use

only

inar

eas

whe

reth

eco

ntai

ned

solv

ents

can

read

ilyev

apor

ate.

9150

-01-

054-

6453

BT

(16

OZ

)Pu

mp

Spra

y

9150

-01-

327-

9631

BT

(32

OZ

)Pu

mp

Spra

y

9150

-01-

053-

6688

BT

(1G

L)

TO 1-1-691

A-18 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

53C

orro

sion

Prev

entiv

eC

ompo

und,

Petr

o-le

um,

Hot

App

lica-

tion

MIL

-C-1

1796

Pres

erva

tion

ofin

teri

orsu

rfac

esof

unse

aled

stru

c-tu

ral

stee

lan

dal

umin

umal

loy

tubi

ngas

sem

blie

san

dot

her

met

alar

eas

that

mus

tre

mai

nba

rean

dar

eex

pose

dto

eith

erex

teri

oror

inte

rior

envi

ron-

men

tsin

serv

ice.

Cla

ss1

and

1Am

ater

ials

can

beus

edto

prot

ect

met

alpa

rts

inun

shie

lded

outd

oor

stor

age

orus

efo

rlim

ited

peri

ods

(90

days

)an

dun

limite

din

door

use

orst

orag

eei

ther

pack

aged

orun

pack

-age

d.C

lass

3m

ater

ials

can

beus

edto

prot

ect

part

ssu

chas

anti-

fric

tion

bear

ings

inin

-do

orst

orag

e.Pr

efer

ably

,us

eon

lyC

lass

1Am

ate-

rial

son

inse

rvic

est

ruct

ures

asth

eyar

eno

n-sl

ick

and

won

’tco

llect

dirt

asw

ell

asre

sist

ing

high

eram

bien

tte

mpe

ratu

res

(+15

0°F

/+

66°

C)

with

out

mel

ting

and

runn

ing

off

surf

aces

tow

hich

itis

appl

ied.

Cla

ss1

(Har

dfil

mco

mpo

und)

8030

-00-

231-

2354

CN

(5L

B)

8030

-00-

597-

3288

CN

(35

LB

)

8030

-00-

231-

2352

DR

(400

LB

)

Cla

ss1A

(Har

dfil

m,

non-

slic

kco

mpo

und)

8030

-00-

823-

8054

CN

(35

LB

)

8030

-00-

514-

1843

DR

(400

LB

)

Cla

ss3

(Sof

tfil

mco

mpo

und)

8030

-00-

598-

5915

CN

(1PT

)

8030

-00-

231-

2353

CN

(5L

B)

8030

-00-

285-

1570

CN

(35

LB

)

54L

inse

edO

il,B

oile

dA

STM

D26

0,Ty

peI

8010

-00-

244-

8961

CN

(1PT

)Pr

eser

vatio

nof

inte

rior

surf

aces

ofse

aled

stru

ctur

alca

rbon

stee

ltu

bing

asse

mbl

ies.

(sup

erse

des

A-A

-371

)80

10-0

0-15

2-32

45C

N(1

GL

)80

10-0

0-68

4-87

89C

N(5

GL

)80

10-0

0-24

2-61

14D

R(5

5G

L)

LU

BR

ICA

NT

S55

Gre

ase:

Air

craf

t,G

en-

eral

Purp

ose,

Wid

eTe

mpe

ratu

re

MIL

-PR

F-81

322

(sup

erse

des

MIL

-L-8

1322

)L

ubri

catin

gai

rcra

ftar

rest

ing

gear

shea

vesp

acer

san

dot

her

equi

pmen

tth

atop

erat

eun

der

high

con-

tact

load

san

dhi

ghsl

idin

gsp

eeds

.R

ange

(-65

°to

+35

0°F/

-54°

to+

177°

C)

NA

TO

Cod

eG

395

NG

LI

Gra

de1

9150

-01-

378-

0744

TU

(8O

Z)

9150

-01-

378-

0559

CN

(1.7

5L

B)

9150

-01-

378-

0693

CN

(6.5

LB

)N

GL

IG

rade

291

50-0

0-18

1-77

24T

U(8

OZ

)L

ubri

catin

gai

rcra

ftw

heel

bear

ings

and

inte

rnal

brak

ew

heel

asse

mbl

ies,

anti-

fric

tion

bear

ings

,ge

arbo

xes,

and

plai

nbe

arin

gs.

9150

-01-

262-

3358

CA

(14

OZ

)91

50-0

0-94

4-89

53C

N(1

.75

LB

)

TO 1-1-691

A-19

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

56G

reas

e:A

ircr

aft

and

Inst

rum

ent,

Gea

ran

dA

ctua

tor

Scre

w(-

100°

to+

250°

F/-

73°

to+

121°

C)

NA

TO

Cod

eG

354

MIL

-PR

F-23

827

(sup

erse

des

MIL

-G-2

3827

Lub

rica

ntfo

rus

ein

ball,

rolle

ran

dne

edle

bear

ings

,ge

ars,

and

onsl

idin

gan

dro

lling

surf

aces

ofsu

cheq

uipm

ent

asin

stru

men

ts,

cam

eras

,el

ectr

onic

gear

s,an

dai

rcra

ftco

ntro

lsy

stem

sth

atar

esu

bjec

tto

extr

eme

mar

ine

and

low

tem

pera

ture

cond

i-tio

ns.

It’s

extr

emel

ylo

wvo

latil

itypr

even

tsit

from

fogg

ing

upop

tical

inst

rum

ents

.It

can

beus

edfo

rro

lling

and

slid

ing

surf

aces

ofeq

uipm

ent

havi

nglo

wm

otiv

atin

gpo

wer

(low

torq

ueeq

uip-

men

t).A

lso

inte

nded

for

gene

ral

use

onai

rcra

ft,

mis

sile

,an

deq

uipm

ent

gear

s,ac

tuat

orsc

rew

s,an

dot

her

equi

pmen

tre

quir

ing

alu

bric

ant

with

high

load

carr

ying

capa

city

.

Type

I(M

etal

licso

apth

ick-

ened

)91

50-0

0-98

5-72

44T

U(4

OZ

)

9150

-00-

985-

7245

TU

(8O

Z)

9150

-00-

935-

4017

CA

(14

OZ

)

9150

-00-

985-

7246

CN

(1.7

5L

B)

9150

-00-

985-

7247

CN

(6.5

LB

)

9150

-00-

985-

7248

CN

(35

LB

)

57G

reas

e:Pl

ugV

alve

,G

asol

ine

Oil,

and

Wat

erR

esis

tant

SAE

AM

S-G

-603

2(s

uper

-se

des

MIL

-G-6

032)

Lub

rica

tion

ofta

pere

dpl

ugva

lves

.T

hetw

oty

pes

prov

ide

for

the

use

inhi

ghpr

essu

relu

bric

atio

neq

uipm

ent

orfo

rse

rvic

ing

thos

eva

lves

whi

chre

quir

ea

stic

kty

pelu

bric

ant.

Als

om

aybe

used

asa

gask

etlu

bric

ant

orse

alan

dfo

rge

nera

lpl

ugva

lve

serv

ice

insy

stem

sw

here

gaso

line,

oil,

alco

-ho

l,or

wat

erre

sist

ance

isre

quir

ed.

NA

TO

Cod

eG

363

Type

I(B

ulk

form

)91

50-0

0-19

0-09

26C

N(8

OZ

)

9150

-00-

257-

5360

CN

(1.7

5L

B)

Type

II(S

tick

form

)C

lass

A(¼

Dx

7/ 8

inL

)91

50-0

0-26

1-82

87B

X(2

4E

A)

Cla

ssB

(13/

32D

x1-

3/ 8

inL

)91

50-0

0-26

1-82

89B

X(2

4E

A)

Cla

ssC

(35/

64D

x2

inL

)91

50-0

0-26

1-82

90B

X(2

4E

A)

Cla

ssD

(21/

32D

x2-

7/16

inL

)91

50-0

0-26

1-82

91B

X(2

4E

A)

Cla

ssG

(55/

64D

x3-

3/ 8

inL

)91

50-0

0-26

1-82

92B

X(2

4E

A)

TO 1-1-691

A-20

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

58G

reas

e:A

ircr

aft

and

Inst

rum

ent,

Fuel

and

Oxi

dize

rR

esis

tant

MIL

-PR

F-27

617

(sup

erse

des

MIL

-G-2

7617

)L

ubri

catio

nof

tape

rpl

ugva

lves

,ga

sket

s,an

dbe

ar-

ings

infu

elsy

stem

sof

airc

raft

and

grou

ndsu

p-po

rteq

uipm

ent.

Als

osu

itabl

efo

rus

ein

LO

Xsy

s-te

ms

asa

lubr

ican

tfo

rva

lves

,th

read

s,an

dbe

arin

gsin

aero

spac

eve

hicl

esan

dsu

ppor

teq

uip-

men

t.M

ayno

tbe

suita

ble

for

alum

inum

and

mag

nesi

umdy

nam

icbe

arin

glu

bric

atio

nbe

caus

eof

poss

ible

igni

tion

haza

rds.

Type

III

ism

ore

com

mon

lykn

own

as“K

ryto

x”an

dis

LO

Xco

m-

patib

le.

Type

I-

NA

TO

Cod

e39

7(-

65°

to+

400°

F/-5

4°to

+20

4°C

)

9150

-01-

007-

4384

TU

(8O

Z)

9150

-01-

311-

9771

CN

(1.7

5L

B)

9150

-01-

088-

0498

TU

(2O

Z)

Type

II-

NA

TO

Cod

eG

398

(-40

°to

+40

0°F/

-40°

to+

204°

C)

9150

-00-

961-

8995

TU

(8O

Z)

9150

-01-

358-

5154

CN

(1L

B)

Type

III

-N

AT

OC

ode

G39

9(-

30°

to+

400°

F/-3

4°to

+20

4°C

)

9150

-01-

353-

5788

CR

(1L

B)

Type

IV-

NA

TO

Cod

eG

1350

(-10

0°to

+40

0°F/

-73°

to+

204°

C)

9150

-01-

393-

1749

TU

(2O

Z)

59G

reas

e:M

olyb

denu

mD

isul

fide,

Low

and

Hig

hTe

mpe

ratu

res;

NA

TO

Cod

eG

353

(-10

0°to

+25

0°F/

-73

°to

+12

1°C

)

MIL

-G-2

1164

9150

-00-

935-

4018

CA

(14

OZ

)L

ubri

cant

for

acce

ssor

ysp

lines

,he

avy

load

edsl

id-

ing

stee

lsu

rfac

es,

orfo

ran

ti-fr

ictio

nbe

arin

gsca

rryi

nghi

ghlo

ads

and

oper

atin

gth

roug

hw

ide

tem

pera

ture

rang

esw

here

mol

ybde

num

disu

lfide

will

prev

ent

orde

lay

seiz

ure

inth

eev

ent

ofin

ad-

equa

telu

bric

atio

n.Sh

ould

not

beus

edfo

rw

heel

bear

ings

orfo

rot

her

than

stee

lsu

rfac

esw

ithou

tau

thor

izat

ion.

9150

-00-

754-

2595

CN

(1.7

5L

B)

9150

-00-

223-

4004

CN

(6.5

LB

)

9150

-00-

965-

2003

CN

(35

LB

)

9150

-01-

219-

1629

DR

(20

KG

)

60G

reas

e:Pn

eum

atic

Sys-

tem

;N

AT

OC

ode

G39

2

SAE

AM

S-G

-434

3(s

uper

-se

des

MIL

-G-4

343)

9150

-00-

119-

9291

TU

(2O

Z)

Lub

rica

ntbe

twee

nru

bber

and

met

alpa

rts

ofpn

eu-

mat

icsy

stem

s.It

may

also

beus

edfo

rpr

essu

rize

dca

bin

bulk

-hea

dgr

omm

ets

and

othe

rm

echa

nism

sre

quir

ing

rubb

erto

met

allu

bric

atio

n.91

50-0

0-26

9-82

55C

N(1

.75

LB

)

TO 1-1-691

A-21

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

eci c

atio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

61G

reas

e:A

ircr

aft,

Hel

i-co

pter

Osc

illat

ing

Bea

ring

;N

AT

O

MIL

-G-2

5537

9150

-00-

478-

0055

CA

(14

OZ

)L

ubri

catio

nof

bear

ings

havi

ngos

cilla

tory

mot

ion

ofsm

all

ampl

itude

.

Cod

eG

366

(-65

°to

160°

F/-5

4°to

+71

°C

)

9150

-00-

616-

9020

CN

(1.7

5L

B)

9150

-00-

721-

8570

CN

(6.5

LB

)91

50-0

0-72

1-85

81C

N(3

5L

B)

62G

reas

e,A

ircr

aft,

Bal

lan

dR

olle

rB

eari

ng;

NA

TO

Cod

eG

372

(-10

0°to

450°

F/-7

3°to

+232

°C

)

MIL

-G-2

5013

9150

-00-

823-

8048

TU

(8O

Z)

Bal

lan

dro

ller

bear

ing

lubr

icat

ion.

Itm

aybe

used

onai

rcra

ftac

tuat

ors

and

gear

boxe

s,an

dot

her

sim

ilar

equi

pmen

tan

dan

ti-fr

ictio

nbe

arin

gsw

here

oper

atio

nof

low

torq

ueeq

uipm

ent

requ

ires

lubr

i-ca

tion

for

exte

nded

peri

ods

oftim

ew

hen

auth

o-ri

zed

byth

eap

plic

able

syst

emsp

eci c

mai

nte-

nanc

em

anua

l.

9150

-00-

935-

4019

CA

(14

OZ

)

9150

-01-

234-

5866

CN

(1L

B)

9150

-00-

141-

6770

CN

(1.7

5L

B)

9150

-00-

141-

6771

CN

(35

LB

)

63L

ubri

cant

,M

olyb

de-

num

Dis

ul d

e,Si

li-co

ne;

NA

TO

Cod

eS

1735

DO

D-L

-256

8191

50-0

0-54

3-72

20L

B(1

LB

)L

ubri

cant

for

use

onsl

ow-s

peed

slid

ing

surf

aces

inai

rcra

ftga

stu

rbin

een

gine

san

dot

her

area

sof

airc

raft

,m

issi

les

and

equi

pmen

tsu

bjec

tto

high

tem

pera

ture

s(u

pto

+752

°F/

+40

0°C

)an

das

anan

ti-se

ize

com

poun

don

thre

aded

part

sw

hich

op-

erat

eat

tem

pera

ture

sup

to+1

400°

F(7

60°

C).

64L

ubri

cant

:So

lidFi

lm,

Hea

t-C

ured

,C

orro

-si

onIn

hibi

ting

SAE

AS5

272,

Type

sI

&II

(rep

lace

sM

IL-P

RF-

4601

0,Ty

pes

I&

II)

Lub

rica

ntfo

rus

eto

redu

cew

ear

and

prev

ent

gall-

ing,

corr

osio

n,an

dse

izur

eof

met

als.

Idea

lfo

rsl

idin

gm

otio

nap

plic

atio

nssu

chas

plai

nan

dsp

heri

cal

bear

ings

, a

ptr

acks

,hi

nges

,th

read

,an

dca

msu

rfac

es.

Itis

also

usef

ulw

here

aso

lven

tre

sist

ant

coat

ing

isre

quir

ed,

lubr

icat

ion

and

corr

o-si

onpr

otec

tion

for

area

sth

atex

peri

ence

slig

htvi

brat

ory

mot

ion,

lubr

icat

ion

and

corr

osio

npr

o-te

ctio

nof

mec

hani

sms

havi

ngin

freq

uent

oper

a-tio

nin

terv

als

orlif

etim

elu

bric

atio

n,an

dw

here

long

-ter

mco

rros

ion

prot

ectio

nis

need

edun

der

stat

icco

nditi

ons.

TO 1-1-691

A-22 Change 1

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

64 Con

t.Ty

peI

(cur

e@

+30

0°F

/+14

9°C

)91

50-0

0-83

4-56

08C

N(1

PT)

NO

TE

SAE

AS5

272,

Type

Ian

dM

IL-P

RF-

4601

0cu

red

at+

300°

F(+

149°

C)

are

usab

leon

all

met

alsu

rfac

es,

but

SAE

AS5

272,

Type

IIan

dM

IL-P

RF-

4601

0cu

red

at+

400°

F(+

204°

C)

shou

ldno

tbe

used

onal

umin

umal

loys

orot

her

met

als

adve

rsel

yaf

fect

edby

expo

sure

toth

ishi

gher

tem

pera

ture

.B

efor

eus

ing

MIL

-PR

F-46

010

(alo

wV

OC

mat

eria

l)in

lieu

ofSA

EA

S527

2,Ty

pes

Ian

dII

,au

thor

i-za

tion

from

the

airc

raft

SPD

orth

em

is-

sile

oreq

uipm

ent

SPM

isre

quir

ed.

Do

not

use

thes

em

ater

ials

onro

ller

bear

ings

orin

area

sex

pose

dto

LO

X.

9150

-00-

985-

7255

CN

(1G

L)

Type

II(c

ure

@+

400°

F/+

205°

C)

9150

-00-

948-

6912

CN

(1Q

T)

9150

-00-

948-

7025

CN

(1G

L)

MIL

-PR

F-46

010

(sup

erse

des

MIL

-PR

F-46

010,

Type

III)

Col

or1

(Nat

ural

)91

50-0

1-41

6-95

06C

N(1

GL

)C

olor

2(B

lack

)91

50-0

1-41

6-95

09C

N(1

GL

)65

Lub

rica

nt,

Solid

Film

,A

ir-C

ured

,C

orro

sion

Inhi

bitin

g;N

AT

OC

ode

S74

9

MIL

-L-2

3398

Lub

rica

ntca

nbe

appl

ied

bydi

ppin

g,br

ushi

ng,

orsp

rayi

ngfo

rus

eon

stee

l,tit

aniu

m,

oral

umin

umbe

arin

gsu

rfac

esw

here

mod

erat

ew

ear

life

and

corr

osio

npr

otec

tion

isde

sire

d.It

issu

itabl

efo

rsl

idin

gm

otio

nap

plic

atio

nssu

chas

inpl

ain

sphe

rica

lbe

arin

gs,

flap

trac

ks,

hing

esan

dca

msu

rfac

es,

espe

cial

lyw

here

itis

not

feas

ible

tous

eth

ety

peof

solid

film

lubr

ican

tw

hich

requ

ires

baki

ngat

anel

evat

edte

mpe

ratu

re.

Use

dto

repa

irde

fect

sin

SAE

AS5

272

and

MIL

-PR

F-46

010

coat

ings

.

Type

I(B

ulk)

9150

-00-

954-

7422

CN

(1Q

T)

Type

II(P

ress

uriz

edSp

ray)

9150

-01-

260-

2534

CN

(16

OZ

)A

eros

ol

MIL

-PR

F-46

147

Type

I(1

8ho

urcu

re)

Form

1(B

ulk)

Col

or1

(Nat

ural

)91

50-0

1-36

0-19

07C

N(1

QT

)

9150

-01-

142-

9361

CN

(1G

L)

Col

or2

(Bla

ck)

9150

-01-

360-

1908

CN

(1Q

T)

9150

-01-

360-

1909

CN

(1G

L)

TO 1-1-691

Change 1 A-23

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Form

2(P

ress

uriz

edSp

ray)

Col

or1

(Nat

ural

)91

50-0

1-36

0-19

03C

N(1

2O

Z)

Aer

osol

9150

-01-

360-

1905

CN

(16

OZ

)A

eros

olC

olor

2(B

lack

)91

50-0

1-36

0-19

04C

N(1

2O

Z)

Aer

osol

9150

-01-

360-

1906

CN

(16

OZ

)A

eros

ol

Neu

tral

izin

gA

gent

san

dIn

dica

tor

Mat

eria

ls66

Fire

Ext

ingu

ishi

ngA

gent

,Aqu

eous

Film

Form

ing

Foam

(AFF

F)L

iqui

dC

on-

cent

rate

,fo

rFr

esh

and

Sea

Wat

er

MIL

-F-2

4385

Con

cent

rate

isin

tend

edfo

rus

ein

mec

hani

cal

foam

gene

ratin

geq

uipm

ent

such

asfir

efig

htin

gtr

ucks

orfo

amsp

rink

ler

syst

ems

for

extin

guis

hing

fires

.D

ilute

and

use

the

AFF

Fag

ent

with

fres

hw

ater

inth

efo

llow

ing

prop

ortio

nto

achi

eve

optim

umpe

rfor

man

ce:

Type

3-3

part

sof

conc

entr

ate

to97

part

sw

ater

byvo

lum

e;an

dTy

pe6-

6pa

rts

con-

cent

rate

to94

part

sw

ater

byvo

lum

e.

Type

342

10-0

1-13

9-49

72C

N(5

GA

L)

4210

-01-

144-

0291

DR

(55

GA

L)

Type

642

10-0

1-05

6-83

43C

N(5

GA

L)

4210

-01-

056-

0883

DR

(55

GA

L)

67A

mm

oniu

mH

ydro

xide

,Te

chni

cal

A-A

5937

0(s

uper

sede

sO

-A-

451)

Use

das

ane

utra

lizin

gag

ent

for

acid

sin

urin

e.

Type

I(2

0to

30%

asam

mo-

nia)

6810

-00-

584-

3793

BT

(1PT

)

6810

-00-

817-

9929

BT

(1G

L)

Type

III

(9to

10%

asam

mo-

nia)

6810

-00-

527-

2476

BT

(1Q

T)

68So

dium

Bic

arbo

nate

,Te

chni

cal

(Bak

ing

Soda

)

A-A

-374

(AST

MD

928)

6810

-00-

264-

6618

BX

(1L

B)

Use

dto

neut

raliz

esu

lfur

icac

idel

ectr

olyt

ede

posi

tsfr

omle

ad-a

cid

batte

ries

.68

10-0

0-29

7-00

92B

G(5

0L

B)

69So

dium

Phos

phat

e,M

onob

asic

,Anh

y-dr

ous,

Tech

nica

l

AN

SI/A

WW

AB

504

(sup

er-

sede

sM

IL-S

-137

27)

6810

-00-

281-

1858

BG

(100

LB

)U

sed

tone

utra

lize

pota

ssiu

mhy

drox

ide

elec

trol

yte

depo

sits

from

nick

el-c

adm

ium

batte

ries

.

70B

oric

Aci

dA

-A-5

9282

(sup

erse

des

O-C

-26

5)68

10-0

0-26

4-65

35B

T(5

00G

M)

Use

tone

utra

lize

pota

ssiu

mhy

drox

ide

elec

trol

yte

depo

sits

from

nick

el-c

adm

ium

batte

ries

.68

10-0

0-82

4-90

90B

T(3

KG

)68

10-0

0-97

3-57

16B

T(1

LB

)68

10-0

0-15

3-01

91B

X(2

5L

B)

TO 1-1-691

A-24

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

71Ph

osph

oric

Aci

d,Te

ch-

nica

l(O

rtho

phos

pho-

ric

Aci

d)

A-A

-558

20(s

uper

sede

sO

-O-

670)

One

oftw

oco

mpo

nent

sus

edto

mak

ebr

omot

hym

olbl

uein

dica

ting

solu

tion

tode

term

ine

the

loca

tion

ofco

ntam

inat

ion

(ele

ctro

lyte

spill

s)fr

omni

ckel

-ca

dmiu

mba

tteri

esan

dto

indi

cate

whe

ther

thes

ear

eas

have

been

com

plet

ely

neut

raliz

ed.

Cla

ss1

(85%

acid

)68

10-0

0-26

4-67

22B

T(7

LB

)

72B

rom

othy

mol

Blu

eIn

dica

tor

Solu

tion

MIL

-B-1

1845

6810

-01-

031-

4757

BT

(1PT

)O

neof

two

com

pone

nts

used

tom

ake

anin

dica

tor

solu

tion

for

dete

ctin

gni

ckel

-cad

miu

mba

ttery

spill

san

dto

dete

rmin

ew

heth

erar

eas

have

been

com

plet

ely

neut

raliz

ed.

6810

-00-

281-

4270

BT

(½L

)

6810

-00-

281-

4271

BT

(4O

Z)

73L

itmus

Pape

rC

omm

erci

alIt

em-C

AG

EC

ode

#22

537

Blu

eL

itmus

Pape

r66

40-0

0-29

0-01

46H

D(1

00SH

)C

olor

chan

geto

red

indi

cate

sac

idpr

esen

t(l

ead

acid

batte

ries

).R

edL

itmus

Pape

r66

40-0

0-29

0-01

47H

D(1

00SH

)C

olor

chan

geto

blue

indi

cate

sba

se/a

lkal

ipr

esen

t(n

icke

l-ca

dmiu

mba

tteri

es).

Prot

ectiv

eM

ater

ials

74B

arri

erM

ater

ials

,G

reas

epro

of,

Wat

er-

proo

f,Fl

exib

le,

Hea

t-Se

alab

le

MIL

-PR

F-12

1G

ener

alpu

rpos

em

aski

ngm

ater

ial

used

for

prot

ect-

ing

equi

pmen

tan

dsu

pplie

sdu

ring

tran

spor

tatio

nan

dst

orag

eun

der

all

clim

ate

cond

ition

s,an

dm

aski

ngar

eas

requ

irin

gpr

otec

tion

duri

ngcl

ean-

ing,

corr

osio

nre

mov

al,

surf

ace

trea

tmen

t,an

dpa

intin

gop

erat

ions

.

Type

I(H

eavy

duty

)G

rade

A,

Cla

ss1

8135

-00-

292-

9719

RO

(36

inx

100

YD

)81

35-0

0-23

3-38

71R

O(3

6in

x20

0Y

D)

8135

-00-

543-

6574

RO

(48

inx

100

YD

)Ty

peII

(Med

ium

duty

)G

rade

A,

Cla

ss1

8135

-00-

224-

8885

RO

(36

inx

200

YD

)81

35-0

0-54

3-65

73R

O(1

2in

x20

0Y

D)

75B

arri

erM

ater

ial,

Flex

-ib

le,

Gre

asep

roof

Wat

erR

esis

tant

,H

eat-

Seal

able

MIL

-PR

F-13

1(s

uper

sede

sM

IL-B

-131

)U

sed

for

pres

erva

tion

(e.g

.se

alin

gai

rcra

ft,

mis

sile

,or

equi

pmen

top

enin

gs,

prot

ectio

nof

cano

pies

,te

mpo

rary

wal

kway

prot

ectio

n)du

ring

clea

ning

,co

rros

ion

rem

oval

,su

rfac

etr

eatm

ent,

and

pain

ting

oper

atio

ns.

Itis

also

used

topr

otec

tpa

rts

inst

or-

age

orbe

ing

tran

spor

ted

whi

chre

quir

ean

abso

-lu

tem

oist

ure

vapo

rpr

oof

barr

ier.

Cla

ss1

(Non

-wov

enpl

astic

back

)81

35-0

0-28

2-05

65R

O(3

6in

x20

0Y

D)

TO 1-1-691

Change 1 A-25

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

NO

TE

Alw

ays

inst

all

with

the

plas

ticco

ated

side

tow

ard

the

part

and/

orsu

rfac

e.

76K

raft

Pape

r,U

ntre

ated

,(B

row

nin

colo

r)A

-A-2

03(s

uper

sede

sU

U-P

-26

8)G

ener

alw

rapp

ing

appl

icat

ions

and

prot

ectio

nof

surr

ound

ing

surf

ace

area

sdu

ring

abra

sive

blas

t-in

g,sp

ray

pain

ting,

seal

ant

appl

icat

ion,

etc.

,w

here

aw

ater

proo

fan

d/or

moi

stur

eva

por

proo

fm

aski

ngm

ater

ial

isno

tre

quir

ed.

Styl

e1

(She

ets)

30po

und

basi

sw

eigh

t81

35-0

0-29

0-34

08SH

(2x

3ft

;85

0E

A)

70po

und

basi

sw

eigh

t81

35-0

0-29

0-55

04SH

(3x

4ft

;20

0E

A)

Styl

e2

(Rol

ls)

50po

und

basi

sw

eigh

t81

35-0

1-33

7-53

70R

O(3

x20

0ft

)76 Con

t.81

35-0

0-16

0-77

64R

O(3

x98

0ft

)60

poun

dba

sis

wei

ght

8135

-00-

160-

7768

RO

(3x

820

ft)

8135

-00-

160-

7769

RO

(4x

820

ft)

70po

und

basi

sw

eigh

t81

35-0

0-16

0-77

71R

O(3

x70

0ft

)81

35-0

0-16

0-77

72R

O(4

x70

0ft

)80

poun

dba

sis

wei

ght

8135

-00-

160-

7776

RO

(3x

615

ft)

8135

-00-

160-

7778

RO

(4x

615

ft)

77Pa

int

Mas

king

Pape

rw

ithA

dhes

ive

Bac

k(L

ight

brow

nin

colo

r)

Rea

dy-M

askt

TM

(3M

Co.

/CA

GE

Cod

e#

5215

2PN

850D

C)

Ope

nPu

rcha

seR

O(2

inx

180

ft)

Pape

rm

aski

ngta

pew

ithad

hesi

veal

ong

one

edge

.Pr

otec

tssu

rfac

esfr

ompa

int

spla

tters

and

over

-sp

ray.

Eas

yto

appl

yan

dco

mes

off

clea

nly

with

noad

hesi

vetr

ansf

er.

Ope

nPu

rcha

seR

O(3

inx

400

ft)

Ope

nPu

rcha

seR

O(3

¼in

x75

ft)

TO 1-1-691

A-26

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

78Pl

astic

Shee

t,Po

lyol

e-fin

(Cle

ar)

A-A

-317

4(s

uper

cede

sL

-P-

378)

8135

-01-

066-

3217

RO

(6ft

x10

0ft

)Pr

otec

tion

ofac

rylic

airc

raft

cano

pies

duri

ngw

ash-

ing

oper

atio

ns.

Type

I(N

orm

alst

reng

thpo

ly-

ethy

lene

),C

lass

1(n

on-f

ood

use)

,G

rade

A(l

owsl

ip),

Fini

sh1

(unt

reat

ed)

79Ta

pes,

Pres

sure

Sens

i-tiv

eA

dhes

ive,

Pres

-er

vatio

nan

dSe

alin

g(B

lack

inco

lor)

SAE

AM

S-T-

2208

5(s

uper

-se

des

MIL

-T-2

2085

)75

10-0

0-85

2-81

79R

O(1

inx

36Y

D)

Plas

ticpr

eser

vatio

nan

dse

alin

gta

peus

edfo

rho

ld-

ing

mos

tba

rrie

rm

ater

ials

inpl

ace

duri

ngst

orag

eor

ship

men

tan

dcl

eani

ngan

dco

rros

ion

rem

oval

oper

atio

ns.

Eff

ectiv

efo

rm

any

outd

oor

appl

ica-

tions

and

can

beus

edon

met

als

orpa

inte

dsu

r-fa

ces

with

clea

nre

mov

alup

to2

year

saf

ter

ini-

tial

use.

7510

-00-

852-

8180

RO

(2in

x36

YD

)Ty

peII

(use

w/

orw

/oan

over

coat

ing)

7510

-00-

885-

3510

RO

(2½

inx

36Y

D)

7510

-00-

926-

8939

RO

(3in

x36

YD

)(3

MC

o./C

AG

EC

ode

#52

152

PN48

1)75

10-0

0-91

6-96

59R

O(4

inx

36Y

D)

7510

-00-

926-

8941

RO

(6in

x36

YD

)N

OT

E

Do

not

use

onac

rylic

orpo

lyca

rbon

ate

cano

pies

and

win

dscr

eens

.

TO 1-1-691

A-27

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

80Ta

pes,

Pres

sure

Sens

i-tiv

eA

dhes

ive,

Mas

k-in

g,N

on-S

tain

ing,

for

Air

craf

tPa

intin

gA

pplic

atio

ns

SAE

AM

S-T-

2159

5(s

uper

-se

des

MIL

-T-2

1595

)C

onfo

rmab

lecr

eped

pape

rta

peus

edfo

rm

aski

ngof

eith

erfla

tor

cont

oure

dsu

rfac

espr

ior

topa

intin

gan

dse

alan

tap

plic

atio

ns.

Tape

can

beus

edat

bak-

ing

tem

pera

ture

sup

to+

250°

F(+

121°

C)

for

one

hour

and

can

bere

mov

edw

ithou

tad

hesi

vetr

ans-

fer.

Tape

shal

lno

tbe

subj

ecte

dto

prol

onge

dpe

ri-

ods

ofou

tdoo

rex

posu

reor

sunl

ight

beca

use

itw

illbe

com

eve

rydi

fficu

ltto

rem

ove

and

will

leav

eta

pean

dad

hesi

vere

sidu

es.

Type

I(C

repe

dpa

per

back

ing)

(3M

Co.

/CA

GE

Cod

e#

5215

2PN

231/

Nat

ural

Col

or)

7510

-01-

371-

3239

RO

(½in

x60

YD

)75

10-0

1-37

1-32

34R

O(¾

inx

60Y

D)

7510

-01-

371-

3238

RO

(1in

x60

YD

)75

10-0

1-37

1-32

36R

O(1

½in

x60

YD

)75

10-0

1-37

1-32

37R

O(2

inx

60Y

D)

7510

-01-

371-

3235

RO

(3in

x60

YD

)Ty

peII

I(P

last

icba

ckin

g)(3

MC

o./C

AG

EC

ode

#52

152

PN21

8/L

ight

Gre

enC

olor

;Fi

neL

ine

Tape

®)

7510

-01-

158-

0035

RO

(¼in

x60

YD

)T

hin

plas

ticta

peus

edfo

rfin

elin

em

aski

ng,

inpa

r-tic

ular

whe

reco

lor

sepa

ratio

nis

invo

lved

,an

ddu

ring

pain

tto

uch-

up,

and

for

othe

rm

aski

ngan

dho

ldin

gap

plic

atio

ns.

Tape

shal

lno

tbe

subj

ecte

dto

prol

onge

dpe

riod

sof

outd

oor

expo

sure

orsu

n-lig

htbe

caus

eit

will

beco

me

very

diffi

cult

tore

-m

ove,

and

will

leav

eta

pean

dad

hesi

vere

sidu

es

7510

-01-

158-

6606

RO

(½in

x60

YD

)75

10-0

1-15

8-77

78R

O(¾

inx

60Y

D)

7510

-01-

158-

6605

RO

(1in

x60

YD

)75

10-0

1-15

8-66

04R

O(1

½in

x60

YD

)75

10-0

1-15

8-66

03R

O(2

inx

60Y

D)

7510

-01-

158-

6607

RO

(3in

x60

YD

)

TO 1-1-691

A-28

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

81Ta

pes,

Pres

sure

Sens

i-tiv

eA

dhes

ive,

for

Mas

king

Dur

ing

Pain

tR

emov

alO

p-er

atio

ns

SAE

AM

S-T-

2339

7(s

uper

-se

des

MIL

-T-2

3397

)A

lum

inum

foil

back

mas

king

tape

used

for

prot

ect-

ing

surr

ound

ing

surf

aces

duri

ngpa

int

rem

oval

oper

atio

nsan

dch

emic

alan

dso

me

mec

hani

cal

corr

osio

nre

mov

alop

erat

ions

.Alu

min

umba

ckin

gpr

ovid

esex

celle

ntre

flect

ion

ofbo

thhe

atan

dlig

ht.

Tape

can

beus

edei

ther

indo

ors

orou

tdoo

rsfo

rm

any

long

term

appl

icat

ions

.U

seta

pean

dde

cal

appl

icat

or,

Item

#84

,to

appl

yth

ista

peto

surf

aces

.

Type

II(A

lum

inum

foil

back

-in

g-

72ho

urpr

otec

tion)

7510

-00-

806-

4669

RO

(½in

x60

YD

)75

10-0

0-65

4-98

11R

O(¾

inx

60Y

D)

7510

-00-

720-

7516

RO

(1in

x60

YD

)(3

MC

o./C

AG

EC

ode

#52

152

PN42

5)75

10-0

0-68

4-88

03R

O(2

inx

60Y

D)

NO

TE

Use

only

3mC

o.PN

425

tape

for

airc

raft

chem

ical

pain

tre

mov

alop

erat

ions

,as

all

othe

rta

pes

will

not

hold

upfo

rth

ese

ex-

tend

eddw

ell

time

oper

atio

ns.

7510

-00-

816-

8077

RO

(3in

x60

YD

)75

10-0

0-98

2-39

55R

O(4

inx

60Y

D)

7510

-01-

179-

0662

RO

(6in

x60

YD

)82

Tape

s,Pr

essu

reSe

nsi-

tive

Adh

esiv

e,M

ask-

ing

A-A

-883

(sup

erse

des

PPP-

T-42

)Ty

peII

(Fla

tpa

per

back

ing)

7510

-01-

026-

4661

RO

(½in

x60

YD

)T

his

solv

ent

resi

stan

tta

peis

idea

lfo

rst

raig

htlin

epa

int

mas

king

oper

atio

ns.

The

1in

wid

thof

the

3MC

o.PN

250

tape

isth

ere

quir

edta

pefo

rpe

r-fo

rmin

gth

epa

int

wet

tape

adhe

sion

test

.B

ecau

seof

itshi

ghst

reng

th,

itis

good

for

hold

ing,

bun-

dlin

g,an

dw

rapp

ing

ona

vari

ety

ofsu

rfac

es.

Itis

not

reco

mm

ende

dfo

rou

tdoo

rex

posu

rebe

caus

eit

beco

mes

very

diffi

cult

tore

mov

e.

7510

-00-

290-

2024

RO

(¾in

x60

YD

)(3

MC

o./C

AG

EC

ode

#52

152

PN25

0-T

anC

olor

)75

10-0

0-28

3-06

12R

O(1

inx

60Y

D)

7510

-00-

290-

2027

RO

(1½

inx

60Y

D)

7510

-00-

290-

2026

RO

(2in

x60

YD

)75

10-0

0-26

6-66

94R

O(3

inx

60Y

D)

TO 1-1-691

A-29

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

83A

bras

ive

Bla

stin

gTa

pe,

Impa

ctR

esis

-ta

nt(L

ight

Gre

enin

colo

r)

Com

mer

cial

Prod

uct

3MC

o./

CA

GE

Cod

e#

5215

2PN

500

7510

-01-

300-

2124

RO

(1in

x10

YD

)U

sed

for

mas

king

topr

otec

tai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

duri

ngab

rasi

vebl

astin

gco

rro-

sion

rem

oval

oper

atio

ns.

7510

-01-

300-

2125

RO

(2in

x10

YD

)75

10-0

1-30

0-21

26R

O(3

inx

10Y

D)

7510

-01-

300-

2127

RO

(4in

x10

YD

)84

App

licat

or,

Tape

and

Dec

al(m

ade

ofha

rdpl

astic

)

Com

mer

cial

Prod

uct

5120

-00-

628-

5569

BX

(25

EA

)Id

eal

for

appl

ying

mas

king

tape

s(e

spec

ially

the

Item

#81

alum

inum

foil

tape

),an

ti-er

osio

nle

ad-

ing

edge

tape

,de

cals

,et

c.3M

Co.

/CA

GE

Cod

e#

7638

1PN

P.A

.-1

(Har

dpl

astic

tool

with

tape

red

edge

s;4

inL

x2¾

inW

)Ta

pe,

Pres

sure

Sens

i-tiv

e,fo

rW

etTa

pePa

intA

dhes

ion

Test

-in

g

3MC

o./C

AG

EC

ode

#78

381

PN25

075

10-0

0-26

6-66

94R

O(1

inW

x60

YD

L)

Use

dto

perf

orm

wet

tape

adhe

sion

test

ing

onne

wly

appl

ied

and

old

pain

tsy

stem

sto

dete

rmin

epr

oper

pain

tad

hesi

on.

Seal

ants

and

Seal

ing

Acc

esso

ries

KT

-Tw

o-Pa

rtC

anK

it(B

ase

and

Acc

eler

ator

)PM

F-

Prem

ixed

and

Froz

enSC

-Se

mki

tC

artr

idge

85Se

alin

gan

dC

oatin

gC

ompo

und,

Cor

ro-

sion

Inhi

bitiv

e

MIL

-PR

F-81

733

(sup

erse

des

MIL

-S-8

1733

)C

lass

1(P

olys

ulfid

e);

Gra

deA

(Chr

omat

eIn

ibito

rs)

Type

I(B

rush

able

)

Use

dfo

rse

alin

gfa

ying

surf

aces

and

wet

inst

alla

tion

offa

sten

ers

onpe

rman

ent

stru

ctur

es.

Itis

also

the

pref

erre

dse

alan

tfo

rfo

rmin

-pla

ce(F

IP)

seal

son

door

s,re

mov

able

pane

ls,

and

seal

ing

gaps

and

seam

s.85 Con

t.I-

½80

30-0

0-00

8-72

07K

T(1

PT)

NO

TE

Do

not

use

onin

side

ofin

tegr

alfu

elta

nks.

8030

-00-

009-

5022

KT

(1Q

T)

TO 1-1-691

A-30

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

I-2

8030

-00-

008-

7196

KT

(1PT

)80

30-0

0-76

2-88

07K

T(1

QT

)80

30-0

1-36

3-65

01PM

F(6

OZ

CA

)80

30-0

1-36

1-18

14SC

(3½

OZ

)Ty

peII

(Gun

orsp

atul

aap

pli-

catio

n)II

-½80

30-0

0-00

8-71

98K

T(1

PT)

8030

-00-

470-

9154

KT

(1Q

T)

8030

-01-

097-

4519

KT

(1G

L)

8030

-01-

184-

0328

SC(2

½O

Z)

8030

-01-

184-

0329

SC(6

OZ

)II

-280

30-0

1-12

4-76

22K

T(½

PT)

8030

-00-

009-

5023

KT

(1PT

)85 Con

t.80

30-0

0-00

8-72

00K

T(1

QT

)

8030

-01-

518-

3439

KT

(1G

L)

8030

-01-

333-

3954

PMF

(2½

OZ

CA

)80

30-0

1-33

3-48

21PM

F(6

OZ

CA

)80

30-0

1-19

6-19

58SC

(2½

OZ

)80

30-0

1-18

4-03

30SC

(6O

Z)

II-4

8030

-00-

008-

7201

KT

(1PT

)80

30-0

0-00

8-72

02K

T(1

QT

)Ty

peII

I(S

pray

gun

appl

ica-

tion)

III-

180

30-0

0-00

8-72

03K

T(1

PT)

8030

-00-

008-

7204

KT

(1Q

T)

8030

-00-

871-

8489

KT

(1G

L)

Type

IV(F

ayin

gsu

rfac

eap

-pl

icat

ions

;gu

nor

spat

ula;

exte

nded

cure

time)

TO 1-1-691

A-31

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

85 Con

t.IV

-12

8030

-01-

395-

2726

KT

(1PT

)

8030

-00-

008-

7205

KT

(1Q

T)

8030

-00-

151-

9973

KT

(1G

L)

IV-2

480

30-0

1-39

5-27

28K

T(1

PT)

8030

-00-

008-

7206

KT

(1Q

T)

8030

-01-

363-

6504

PMF

(6O

ZC

A)

IV-4

880

30-0

1-19

2-28

07K

T(½

PT)

8030

-01-

395-

2729

KT

(1PT

)80

30-0

0-02

8-84

95K

T(1

QT

)86

Seal

ing

Com

poun

d,Te

mpe

ratu

reR

esis

-ta

nt,

Inte

gral

Fuel

Tank

san

dFu

elC

ell

Cav

ities

,

SAE

AM

S-S-

8802

(sup

erse

des

MIL

-S-8

802)

Type

II(M

an-

gane

sedi

oxid

ecu

red)

Use

dfo

rfil

let

and

brus

hse

alin

gin

inte

gral

fuel

tank

san

dfu

elce

llca

vitie

s.T

his

seal

ant

ism

anga

-ne

sedi

oxid

ecu

red

and

does

n’t

cont

ain

any

chro

-m

ates

orot

her

corr

osio

nin

hibi

tors

.

Hig

hA

dhes

ion

(Pol

ysul

fide)

Cla

ssA

(Bru

shab

le)

86 Con

t.A

-½80

30-0

0-75

3-45

96K

T(½

PT)

8030

-00-

965-

2004

KT

(1PT

)80

30-0

0-84

2-81

27K

T(1

GL

)80

30-0

0-75

3-50

08SC

(2½

OZ

)80

30-0

0-75

3-50

10SC

(6O

Z)

A-1

8030

-01-

386-

3656

KT

(1Q

T)

A-2

8030

-00-

753-

4598

KT

(½PT

)80

30-0

0-75

3-53

43K

T(1

PT)

8030

-00-

723-

5344

KT

(1Q

T)

8030

-00-

841-

6832

KT

(1G

L)

8030

-01-

363-

6671

PMF

(2½

OZ

CA

)80

30-0

1-36

3-65

05PM

F(6

OZ

CA

)80

30-0

0-75

3-50

03SC

(2½

OZ

)80

30-0

0-75

3-50

09SC

(6O

Z)

TO 1-1-691

A-32

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Cla

ssB

(Gun

and

spat

ula

ap-

plic

atio

n)86 Con

t.B

-½80

30-0

0-75

3-45

97K

T(½

PT)

8030

-00-

174-

2599

KT

(1PT

)80

30-0

0-08

0-15

49K

T(1

QT

)80

30-0

0-84

1-68

31K

T(1

GL

)80

30-0

0-75

3-50

07SC

(2½

OZ

)80

30-0

0-75

3-50

04SC

(6O

Z)

B-1

8030

-01-

337-

9408

SC(2

½O

Z)

8030

-01-

376-

8504

KT

(1G

L)

B-2

8030

-00-

753-

4599

KT

(½PT

)80

30-0

0-72

3-27

46K

T(1

PT)

8030

-00-

685-

0915

KT

(1Q

T)

8030

-00-

579-

8453

KT

(1G

L)

8030

-01-

333-

4823

PMF

(24

EA

,2½

OZ

CA

)80

30-0

1-33

3-48

22PM

F(2

4E

A,

6O

ZC

A)

8030

-00-

753-

5006

SC(2

½O

Z)

8030

-00-

753-

5005

SC(6

OZ

)86 Con

t.B

-480

30-0

0-17

4-25

98K

T(1

PT)

8030

-00-

850-

5717

KT

(1Q

T)

8030

-00-

850-

0759

SC(2

.5O

Z)

8030

-00-

850-

0758

SC(6

OZ

)C

lass

C(E

xten

ded

asse

mbl

ytim

e)C

-20

8030

-01-

048-

3772

KT

(1PT

)80

30-0

0-42

7-26

61K

T(1

GL

)80

30-0

0-15

2-00

12SC

(6O

Z)

C-8

080

30-0

0-70

9-32

78K

T(1

QT

)80

30-0

0-43

2-15

44K

T(1

GL

)

TO 1-1-691

A-33

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

87Se

alin

gC

ompo

und,

Inte

gral

Fuel

Tank

s,an

dG

ener

alPu

rpos

e,In

term

itten

tU

seTo

360°

F(1

82°

C)

(Pol

ysul

fide)

SAE

AM

S32

76(s

uper

sede

sM

IL-S

-834

30)

Use

for

fille

tse

alin

gof

join

tsan

dse

ams

and

brus

hse

alin

gor

over

coat

ing

offa

sten

ers

inin

tegr

alfu

elta

nks

and

fuel

cell

cavi

ties,

inpa

rtic

ular

whe

rete

mpe

ratu

res

of36

0°F

(182

°C

)ar

eex

peri

ence

don

anin

term

itten

tba

sis.

Thi

sse

alan

tis

man

ga-

nese

diox

ide

cure

dan

ddo

esn’

tco

ntai

nan

ych

ro-

mat

esor

othe

rco

rros

ion

inhi

bito

rs.

Cla

ssA

(Bru

shab

le)

A-½

8030

-00-

602-

0107

KT

(½PT

)80

30-0

1-39

5-54

74K

T(1

PT)

8030

-01-

036-

6936

KT

(1Q

T)

8030

-00-

312-

6128

SC(6

OZ

)A

-280

30-0

0-60

2-00

49K

T(½

PT)

8030

-00-

602-

0051

KT

(1G

L)

8030

-01-

387-

1001

PMF

(6O

Z)

Cla

ssB

(Gun

orsp

atul

aap

pli-

catio

n)B

-¼80

30-0

1-21

4-03

74SC

(6O

Z)

87 Con

t.B

-½80

30-0

0-60

2-00

39K

T(½

PT)

8030

-00-

348-

7888

KT

(1PT

)80

30-0

1-25

2-79

63SC

(2½

OZ

)80

30-0

0-60

2-00

45SC

(6O

Z)

B-2

8030

-00-

485-

3237

KT

(1PT

)80

30-0

1-06

6-64

44K

T(1

QT

)80

30-0

0-58

5-49

00K

T(1

GL

)80

30-0

1-38

3-41

85PM

F(2

½O

Z)

8030

-01-

383-

3953

PMF

(6O

ZC

A)

8030

-00-

560-

8758

SC(6

OZ

)B

-480

30-0

1-19

5-06

55K

T(1

QT

)B

-680

30-0

0-60

2-00

35SC

(6O

Z)

8030

-01-

387-

1061

PMF

(6O

ZC

A)

C-½

8030

-01-

311-

5653

KT

(1Q

T)

TO 1-1-691

A-34

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

88Se

alin

gC

ompo

und,

Low

Adh

esio

n,C

or-

rosi

onIn

hibi

ting

(Non

-Chr

omat

e),

Poly

sulfi

de

PN:

PR-1

773;

CA

GE

Cod

e#

8357

4(s

uper

sede

sPR

-14

03G

)

Thi

sm

ater

ial

isa

two-

part

,no

n-ch

rom

ate

type

cor-

rosi

onin

hibi

ting,

low

adhe

sion

,fu

elre

sist

ant

seal

-an

tus

edfo

rfa

ysu

rfac

ese

alin

gof

acce

ssdo

ors,

rem

ovab

lepa

nels

and

stru

ctur

es,

and

the

head

sof

thei

rat

tach

ing

fast

ener

s.It

can

also

beus

edto

mak

eFI

Pga

sket

san

dre

pair

dam

aged

area

sof

FIP

gask

ets.

Itsh

ould

not

beus

edfo

rse

alin

gin

-si

dein

tegr

alfu

elta

nks,

inhi

ghte

mpe

ratu

rear

eas,

oron

perm

anen

tlyin

stal

led

stru

ctur

es.

Cla

ssB

(Gun

orsp

atul

aap

pli-

catio

n)B

-½80

30-0

1-41

8-54

14SC

(2½

OZ

)80

30-0

1-41

8-54

18SC

(6O

Z)

B-2

8030

-01-

104-

5396

KT

(1Q

T)

8030

-01-

418-

5415

SC(2

½O

Z)

8030

-01-

418-

5417

SC(6

OZ

)89

Seal

ing

Com

poun

d,L

owA

dhes

ion,

Cor

-ro

sion

Inhi

bitin

g,fo

rR

emov

able

Pane

lsan

dFu

elTa

nkIn

-sp

ectio

nPl

ates

SAE

AM

S32

67(s

uper

sede

sM

IL-S

-878

4)T

his

mat

eria

lis

atw

o-pa

rt,

low

adhe

sion

,fu

elre

sis-

tant

seal

ant

that

does

n’t

cont

ain

any

corr

osio

nin

hibi

tors

.It

can

beus

edfo

rfa

ysu

rfac

ese

alin

gof

rem

ovab

lest

ruct

ures

such

asac

cess

door

s,flo

orpa

nels

and

plat

es,

fuel

tank

insp

ectio

npl

ates

,an

dot

her

rem

ovab

lepa

nels

.It

shou

ldno

tbe

used

for

seal

ing

insi

dein

tegr

alfu

elta

nks,

inhi

ghte

mpe

ratu

rear

eas,

oron

perm

anen

tlyin

-st

alle

dst

ruct

ures

.

Cla

ssA

(Bru

shab

le)

A-½

8030

-00-

291-

8380

KT

(½PT

)

A-2

8030

-00-

584-

4399

KT

(½PT

)

8030

-01-

127-

8281

KT

(1PT

)80

30-0

0-15

2-00

62SC

(2½

OZ

)C

lass

B(G

unor

spat

ula

appl

i-ca

tion)

B-½

8030

-00-

598-

2910

KT

(½PT

)80

30-0

0-88

1-39

33K

T(1

PT)

8030

-01-

028-

4336

KT

(1Q

T)

8030

-01-

065-

0306

KT

(1G

L)

8030

-00-

152-

0022

SC(2

.5O

Z)

8030

-01-

365-

3912

SC(6

OZ

)89 Con

t.80

30-0

0-15

2-00

21SC

(8O

Z)

B-2

8030

-00-

616-

9191

KT

(½PT

)80

30-0

0-68

0-20

41K

T(1

PT)

8030

-01-

371-

9247

PMF

(24

EA

;2½

OZ

CA

)

TO 1-1-691

A-35

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

8030

-01-

371-

9246

PMF

(24

EA

;6

OZ

CA

)80

30-0

1-38

3-49

93SC

(6O

Z)

90Se

alin

gC

ompo

und,

Air

craf

t,Fi

rew

all

SAE

AM

S33

74(s

uper

sede

sM

IL-S

-382

49)

Seal

ing

airc

raft

firew

all

stru

ctur

esex

pose

dto

very

high

tem

pera

ture

sto

prev

ent

the

pass

age

ofai

ran

dva

pors

.It

will

with

stan

d40

0°F

(204

°C

)co

ntin

uous

lyan

d20

00°

F(1

093°

C)

for

atle

ast

15m

inut

es.

Type

1(O

neco

mpo

nent

;si

li-co

ne)

8040

-01-

168-

0077

CA

(12

OZ

)

Type

4(t

wo

com

pone

nt;

SAE

AM

S33

74/4

and/

orM

IL-S

-38

249,

Type

I)

8030

-00-

783-

8898

KT

(½PT

)

8030

-00-

723-

5345

KT

(1PT

)80

30-0

1-03

3-34

85K

T(1

GL

)80

30-0

1-36

4-73

62PM

F(2

4E

A;

2½O

ZC

A)

8030

-01-

365-

0049

PMF

(24

EA

;6

OZ

CA

)80

30-0

1-36

4-73

59SC

(2½

OZ

)90 Con

t.80

30-0

0-78

3-88

86SC

(6O

Z)

91Se

alin

gC

ompo

und,

Poly

thio

ethe

r,fo

rA

ircr

aft

Stru

ctur

es,

Fuel

and

Hig

hTe

m-

pera

ture

Res

ista

nt,

Fast

Cur

ing

atA

mbi

-en

tan

dL

owTe

m-

pera

ture

s

SAE

AM

S-S-

2957

4;M

IL-S

-29

574;

and/

orSA

EA

MS

3277

,G

rade

A

Use

dfo

rfa

ysu

rfac

ese

alin

gan

dre

pair

ing

fille

tan

dfa

sten

erse

als

inin

tegr

alfu

elta

nks.

Itca

nal

sobe

used

for

over

coat

ing

fast

ener

san

dse

alin

gse

ams

and

join

ts.

Type

I(F

uel

resi

stan

t-

use

at-8

0°to

+30

0°F/

-62°

to+

149°

Cco

ntin

uous

and

inte

rmitt

ent

to+

400°

F/+

204°

C

NO

TE

•Ty

peI

com

poun

dsre

quir

eth

eus

eof

anad

hesi

onpr

omot

er(e

.g.

PR-1

86)

whe

reas

Type

IIco

mpo

unds

dono

t.

•N

otfo

rus

eon

airc

raft

win

dshi

elds

and

cano

pies

.

Cla

ssA

(Bru

shab

le)

A-½

8030

-01-

330-

6568

SC(2

½O

Z)

8030

-01-

330-

0730

SC(6

OZ

)A

-180

30-0

1-33

0-07

35SC

(2½

OZ

)C

lass

B(G

unor

spat

ula

appl

i-ca

tion)

TO 1-1-691

A-36

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

91 Con

t.B

-¼80

30-0

1-29

0-51

34SC

(2½

OZ

)

8030

-01-

290-

5135

SC(6

OZ

)B

-½80

30-0

1-29

0-51

36SC

(2½

OZ

)80

30-0

1-29

0-51

37SC

(6O

Z)

B-2

8030

-01-

290-

5138

SC(2

½O

Z)

8030

-01-

290-

5139

SC(6

OZ

)Ty

peII

(Fue

lre

sist

ant.

Cor

ro-

sion

inhi

bitin

g;us

eat

-80°

to+

300°

F(-

62°

to+

149°

C)

cont

inuo

usan

din

term

it-te

ntto

+36

0°F(

+18

2°C

)C

lass

B(G

unor

Spat

ula

ap-

plic

atio

n)B

-¼80

30-0

1-36

4-38

83SC

(2½

OZ

)80

30-0

1-36

4-38

86SC

(6O

Z)

B-½

8030

-01-

364-

3882

SC(2

½O

Z)

8030

-01-

364-

3885

SC(6

OZ

)91 Con

t.B

-280

30-0

1-36

4-38

81SC

(2½

OZ

)

8030

-01-

364-

3884

SC(6

OZ

)92

Adh

esiv

es-S

eala

nts,

Silic

one,

RT

V,

Non

-C

orro

sive

(for

Use

With

Sens

itive

Met

-al

san

dE

quip

men

t)

MIL

-A-4

6146

Gro

upI

(Gen

eral

purp

ose)

Type

I(T

hixo

trop

ic/p

aste

type

)

The

sear

ero

omte

mpe

ratu

revu

lcan

izin

g(R

TV

)si

li-co

nese

alan

tsus

edon

sens

itive

met

als

and

equi

p-m

ent,

inpa

rtic

ular

onel

ectr

onic

seq

uipm

ent

and

ante

nnas

,at

tem

pera

ture

sup

to+

400°

F(2

04°

C).

The

ycu

reat

room

tem

pera

ture

upon

cont

act

with

moi

stur

ein

the

air.

Toim

prov

ead

hesi

on,

use

thes

ese

alan

tsaf

ter

appl

ying

apr

imer

(Ite

m#

93)

spec

ified

byth

em

anuf

actu

rer

toth

esu

rfac

es.

Kit

(KT

)in

clud

esth

ere

quir

edpr

imer

,bu

ttu

be(T

U)

and

cart

ridg

e(C

A)

dono

t.W

hite

8040

-01-

331-

7133

TU

(3O

Z)

NO

TE

The

sese

alan

tsar

eno

tfu

elre

sist

ant,

and

they

shal

lno

tbe

used

infu

elw

etar

eas

TO 1-1-691

A-37

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Whi

te80

40-0

1-33

1-80

46C

A(1

2O

Z)

92 Con

t.W

hite

8040

-00-

118-

2695

KT

(3O

Z;

TU

w/½

OZ

BT

prim

er)

Whi

te80

40-0

1-93

8-15

35K

T(1

2O

ZC

Aw

/10

OZ

BT

prim

er)

Gra

y80

40-0

1-05

7-00

91C

N(1

PT)

Gra

y80

40-0

1-39

4-20

26K

T(5

GL

CO

w/½

GL

BT

prim

er)

Cle

ar80

40-0

1-14

8-17

59C

N(1

PT)

Cle

ar80

40-0

1-38

0-64

28T

U(3

OZ

)C

lear

8040

-01-

227-

3787

CA

(12

OZ

)C

lear

8040

-01-

394-

2024

KT

(5G

LC

Ow

/½G

LB

Tpr

imer

)Ty

peII

(Sel

f-le

velin

gliq

uid

type

)C

lear

8040

-01-

331-

7127

TU

(3O

Z)

Cle

ar80

40-0

1-33

1-71

34C

N(1

PT)

Cle

ar80

40-0

0-92

7-15

13K

T(1

PTC

Nw

/10

OZ

BT

prim

er)

Cle

ar80

40-0

1-00

9-15

62K

T(3

OZ

TU

w/½

OZ

BT

prim

er)

Gro

upII

(Hig

hst

reng

th)

92 Con

t.Ty

peII

I;Ty

peI

for

old

spec

i-fic

atio

n;(T

hixo

trop

ic/

past

ety

pe)

Cle

ar80

40-0

0-11

7-85

10T

U(3

OZ

)C

lear

8040

-01-

394-

3735

TU

(3O

Z)

Cle

ar80

40-0

1-45

0-40

13T

U(3

OZ

)C

lear

8040

-01-

375-

4803

CA

(6O

Z)

TO 1-1-691

A-38

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Cle

ar80

40-0

1-08

2-91

28C

A(1

2O

Z)

Gra

y80

40-0

0-14

5-00

20T

U(3

OZ

)G

ray

8040

-01-

375-

4805

TU

(3O

Z)

Gra

y80

40-0

1-33

1-71

28C

A(1

2O

Z)

Gra

y80

40-0

1-27

5-50

52K

T(1

2O

ZC

Aw

/1O

ZB

Tpr

imer

)T

rans

luce

nt80

40-0

1-45

0-54

19C

A(6

OZ

)T

rans

luce

nt80

40-0

1-45

0-91

84K

T(5

GL

CO

w/½

GL

BT

prim

er)

Type

II(S

elf-

leve

ling

liqui

dty

pe)

Cle

ar80

40-0

1-44

1-06

71K

T(3

OZ

TU

w/½

OZ

BT

prim

er)

92 Con

t.G

roup

III

(Hig

hte

mpe

ratu

re)

Type

I(T

hixo

trop

ic/p

aste

type

)G

ray

8040

-01-

450-

6545

TU

(3O

Z)

93Pr

imer

for

RT

VSi

li-co

neA

dhes

ive-

Seal

ants

(for

use

with

Item

#92

)

GE

Co.

(CA

GE

Cod

e#

0113

9)U

sed

for

impr

ovin

gad

hesi

onof

RT

Vsi

licon

ead

hesi

ve-s

eala

nts

(Ite

m#

92).

PNSS

4004

Stra

w80

40-0

0-89

3-48

15C

N(1

PT)

PNSS

4004

Pink

8040

-00-

083-

8403

CN

(1PT

)D

owC

orni

ngC

o.(C

AG

EC

ode

#71

984)

PND

C12

00R

ed80

40-0

0-11

1-26

82C

N(1

PT)

PND

C12

00C

lear

8040

-00-

845-

4304

CN

(1PT

)PN

DC

1200

Red

8040

-00-

870-

0877

CN

(1Q

T)

PND

C12

00Pi

nk80

40-0

0-91

4-69

70C

N(1

GL

)PN

DC

1204

Cle

ar80

40-0

1-04

2-14

22C

N(1

PT)

PND

C12

04C

lear

8040

-01-

063-

7509

CN

(1G

L)

TO 1-1-691

A-39

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

94Se

alin

gTa

pe,

Poly

tet-

raflu

oro

ethy

lene

,E

xpan

ded

(EPT

FE),

SAE

AM

S32

55C

lass

1(R

ibbe

d)Se

alin

gof

fayi

ngsu

rfac

es,

pres

suri

zed

and

non-

pres

suri

zed

acce

sspa

nels

,flo

orbo

ards

,an

dw

ind-

scre

ens

whe

nap

prov

edby

the

airc

raft

SPD

orth

em

issi

leor

equi

pmen

tSP

M.

Do

not

use

inin

tegr

alfu

elta

nks,

fuel

soak

edor

high

tem

pera

ture

appl

i-ca

tions

(+25

0°F

/+

121°

Cor

high

er).

Env

iron

-m

enta

llypr

efer

red

non-

haza

rdou

sal

tern

ativ

eto

two-

com

pone

nt,

solv

ent-

base

dse

alan

ts.

The

Cla

ss1/

Rib

bed

tape

sar

epr

efer

red

for

mos

tse

alin

gop

-er

atio

nsw

here

thes

eta

pes

are

appr

oved

for

use.

Oil

and

Wat

erR

esis

tant

(Sky

flex

Tape

-W

.L

.G

ore

Ass

ocia

tes

Inc.

-C

AG

EC

ode

#0A

MD

8&

1721

7)

PNG

UA

-100

1-1

8030

-01-

367-

7357

RO

(15/ 8

inx

100

ft)

PNG

UA

-100

1-2

8030

-01-

475-

1368

RO

(1½

inx

100

ft)

PNG

UA

-101

7-1

8030

-01-

368-

7208

RO

(1in

x10

0ft

)PN

GU

A-1

401-

1(3

ribs

)80

30-0

1-45

4-74

19R

O(1

.1in

x10

0ft

)94 Con

t.PN

GSC

-21-

8076

7-00

(5ri

bs)

8030

-01-

454-

7418

RO

(1.1

inx

100

ft)

Cla

ss2

(Non

-rib

bed)

PNG

UA

-100

3-1

8030

-01-

368-

7207

RO

(¼in

x10

0ft

)C

ompe

nsat

ion

tape

:fil

lsga

psan

dre

pair

sm

inor

seal

defe

cts

PNG

UA

-105

8-1

8030

-01-

381-

1584

RO

(½in

x10

0ft

)T

hin:

use

assh

imto

prev

ent

chafi

ng.

PNG

UA

-105

7-1

8030

-01-

377-

3084

RO

(1in

x10

0ft

)T

hin:

use

assh

imto

prev

ent

chafi

ng.

PNG

UA

-103

8-1

8030

-01-

463-

6459

RO

(1.4

2in

x10

0ft

)T

hin:

use

assh

imto

prev

ent

chafi

ng.

PNG

UA

-105

9-1

Ope

nPu

rcha

seR

O(1

½in

x10

0ft

)T

hin:

use

assh

imto

prev

ent

chafi

ng.

PNG

UA

-130

1-1

Ope

nPu

rcha

seR

O(1

inx

100

ft)

Thi

ck:

use

for

fayi

ngsu

rfac

esw

ithw

ide

gaps

.

TO 1-1-691

A-40

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

95A

v-D

ec®

Poly

uret

hane

Tape

s&

Seal

ants

(CA

GE

Cod

e#

1NPE

1)95 Con

t.H

iTak

TM

Poly

uret

hane

Tape

with

adhe

sive

onbo

thsi

des

PNH

T39

35-7

-100

8030

-01-

494-

5206

RO

(1in

x12

ft)

Fay

surf

ace

seal

ing

area

sw

here

fluid

intr

usio

nis

apr

oble

mbu

tea

seof

com

pone

ntre

mov

alis

re-

quir

ed;

such

asai

rcra

ftflo

orpa

nels

and

tiedo

wn

fittin

gs.

For

max

imum

seal

ing,

rem

ove

the

rele

ase

film

sobo

thsi

des

ofth

eta

pead

here

toth

esu

r-fa

ces.

For

easi

erpa

nel

rem

oval

,le

ave

the

rele

ase

film

inpl

ace

onth

esi

deof

the

tape

inco

ntac

tw

ithth

ere

mov

able

pane

l.D

amag

edar

eas

are

eas-

ilyre

pair

edas

the

tape

adhe

res

wel

lto

itsel

f.

PNH

T39

35-7

-150

8030

-01-

494-

5209

RO

(1½

inx

12ft

)

PNH

T39

35-7

-200

8030

-01-

494-

5207

RO

(2in

x12

ft)

PNH

T39

35-7

-250

8030

-01-

494-

4136

RO

(2½

inx

12ft

)

95 Con

t.T

ufSe

alFR

TM

Poly

ure-

than

eTa

pew

ithPe

r-m

anen

tTe

flon®

Bac

king

On

One

Side

PNH

T30

00-1

00O

pen

Purc

hase

RO

(1x

12ft

)Fa

ysu

rfac

ese

alin

gof

non-

perm

anen

tst

ruct

ures

;su

chas

acce

ssan

din

spec

tion

pane

ls/c

over

son

airc

raft

,m

issi

les,

and

equi

pmen

tto

prev

ent

fluid

entr

yin

toth

efa

ying

surf

ace

area

san

dth

eca

vitie

sco

vere

dby

the

inst

alle

dpa

nels

/cov

ers.

The

Te-

flon®

back

ing

ishi

ghly

abra

sion

resi

stan

tan

dpe

rmits

slig

htm

ovem

ent

(vib

ratio

n,et

c.)

ofth

epa

nels

/cov

ers

with

out

dam

agin

gth

est

ruct

ure

tow

hich

they

are

atta

ched

.T

his

tape

isve

rydu

-ra

ble,

soit

can

bere

used

inpl

ace

man

ytim

esaf

ter

initi

alin

stal

latio

n.D

amag

edse

ctio

nsar

eea

sily

repa

ired

bycu

tting

them

out

and

splic

ing

ina

new

sect

ion

that

slig

htly

over

laps

onto

the

cut

edge

sof

the

old

tape

seal

.

PNH

T30

00-1

50O

pen

Purc

hase

RO

(1½

inx

12ft

)PN

HT

3000

-200

Ope

nPu

rcha

seR

O(2

inx

12ft

)PN

DR

4000

FR-1

0080

30-0

1-49

8-90

79R

O(1

x12

ft)

PND

R40

00FR

-150

8030

-01-

498-

8779

RO

(1½

inx

12ft

)PN

DR

4000

FR-2

0080

30-0

1-49

8-90

78R

O(2

inx

12ft

)PN

DR

4000

FR-2

5080

30-0

1-49

8-90

76R

O(2

½in

x12

ft)

95 Con

t.Se

lfL

evel

ingT

MG

reen

Poly

uret

hane

Seal

ant

PNH

T33

26-5

-50

8030

-01-

494-

9650

CA

(50

CC

)T

his

seal

ant

isin

tend

edfo

rfil

ling

void

s/ca

vitie

son

hori

zont

alsu

rfac

es,

such

asai

rcra

ftse

attr

ack

de-

pres

sion

s,to

prev

ent

fluid

from

accu

mul

atin

gin

them

and

caus

ing

corr

osio

nw

hile

still

bein

gea

syto

rem

ove

for

requ

ired

insp

ectio

nsan

d/or

oper

a-tio

nal

use.

Itis

also

usef

ulfo

rfil

ling

cavi

ties

arou

ndan

tenn

aco

nnec

tors

.

TO 1-1-691

A-41

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Thi

xofle

xTM

Ora

nge

Poly

uret

hane

Seal

ant

PNT

F221

9-50

8030

-01-

494-

7677

CA

(50

CC

)T

his

seal

ant

isin

tend

edfo

rfil

ling

the

sam

ety

pes

ofvo

ids/

cavi

ties

asth

eSe

lfL

evel

ingT

MG

reen

seal

-an

t,bu

tit

can

also

beus

edon

vert

ical

and

over

-he

adsu

rfac

esas

itis

ave

ryth

ick

mat

eria

lth

atw

illre

mai

nin

plac

ew

ithou

tru

nnin

gw

hile

itcu

res.

Itis

also

easi

lyre

mov

edfo

rre

quir

edin

-sp

ectio

nsan

d/or

oper

atio

nal

use.

Seal

ant

Dis

pens

erPN

UG

9811

08-0

1(5

0C

Cca

paci

ty)

5120

-01-

494-

7678

EA

96A

dhes

ion

Prom

oter

for

Poly

sulfi

deSe

alin

gC

ompo

unds

96 Con

t.So

lven

tB

ased

(Blu

eso

lutio

n)SA

EA

MS

3100

/1(P

NPR

-14

8;C

AG

EC

ode

#83

574)

8030

-00-

560-

8756

CN

(1PT

)So

lven

tba

sed

solu

tion

for

enha

ncin

gth

ead

hesi

onof

poly

sulfi

deco

mpo

unds

toa

wid

eva

riet

yof

subs

trat

es(e

.g.

inte

gral

fuel

tank

s).A

pply

bybr

ush

orcl

ean

clot

h.M

ater

ial

drie

sat

room

tem

pin

appr

oxim

atel

y30

min

utes

leav

ing

atit

anat

efil

mon

the

surf

ace

that

enha

nces

seal

ant

adhe

-si

on.

Wat

erB

ased

(Pin

kso

-lu

tion)

SAE

AM

S31

00/3

(PN

PR-

182;

CA

GE

Cod

e#8

3574

)80

30-0

1-13

1-32

28C

N(1

PT)

VO

Cco

mpl

iant

solu

tion

for

enha

ncin

gad

hesi

onof

poly

-sul

fide

seal

ants

tow

ide

vari

ety

subs

trat

es(e

.g.

inte

gral

fuel

tank

s).A

pply

bybr

ush

orcl

ean

clot

h.It

drie

sat

room

tem

pin

30m

inut

esle

avin

gan

adhe

sion

enha

ncin

gfil

m.

97A

dhes

ion

Prom

oter

for

Poly

thio

ethe

rSe

al-

ing

Com

poun

dsSo

l-ve

ntB

ased

Sila

neSo

lutio

n(Y

ello

wso

lutio

n)

PNPR

-186

-C

AG

EC

ode

#83

574

8030

-01-

363-

6682

BT

(1O

Z)

Solv

ent

base

dsi

lane

solu

tion

for

enha

ncin

gth

ead

-he

sion

ofpo

lyth

ioet

her

seal

ants

tocu

red

poly

sul-

fide

orpo

lyth

ioet

her

seal

ants

and

ava

riet

yof

coat

edm

etal

surf

aces

(e.g

.in

tegr

alfu

elta

nks)

.A

pply

bybr

ush

orcl

ean

clot

h.M

ater

ial

drie

sat

room

tem

pin

appr

oxim

atel

y30

min

utes

leav

ing

asi

lane

film

that

enha

nces

seal

ant

adhe

sion

.

8030

-01-

363-

6679

BT

(2O

Z)

8030

-01-

363-

6678

BT

(16

OZ

)

TO 1-1-691

A-42

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

98Pl

astic

Adh

esiv

efo

rSA

EA

MS

3255

EPT

FE(S

kyfle

x®)

Seal

ing

Tape

with

noad

hesi

ve

Use

toho

ldE

PTFE

seal

ing

tape

with

noad

hesi

veba

ckin

gin

plac

e.Fa

stdr

ying

and

resi

sts

wea

ther

-in

g,w

ater

,oi

l,pl

astic

izer

mig

ratio

nan

dal

ipha

ticfu

els.

Bac

king

(Red

-bro

wn

inco

lor)

Scot

ch-G

rip

847

(Liq

uid)

8040

-01-

033-

7507

TU

(5O

Z)

CA

GE

Cod

e#1

A9T

3(A

mbe

rin

colo

r)M

MM

-A-1

89Sc

otch

-Gri

p10

99(B

rush

orSp

ray)

8040

-01-

126-

1422

CN

(1Q

T)

(CA

GE

Cod

e#1

A9T

3)Sc

otch

-Gri

p10

99-L

(Bru

sh)

8040

-00-

043-

1717

TU

(2O

Z)

(CA

GE

Cod

e#1

A9T

3)So

lven

ts99

Dry

Cle

anin

gan

dD

e-gr

easi

ngSo

lven

tsA

-A-5

9601

Type

II68

50-0

0-11

0-44

98C

N(1

PT)

Gen

eral

purp

ose

clea

ning

solv

ent

for

rem

ovin

goi

l,gr

ease

,pa

intin

gpr

eser

vatio

nco

mpo

unds

,et

c.,

from

pain

ted

orun

pain

ted

met

alsu

rfac

es.

Do

not

use

asa

final

clea

ner

prio

rto

.

(Hig

hFl

ash

Poin

t+

140°

F/+

61°

C)

6850

-00-

637-

6135

GL

(1G

L)

6850

-00-

274-

5421

CN

(5G

L)

6850

-00-

285-

8011

DR

(55

GL

)Ty

peII

I68

50-0

1-37

7-19

16C

N(4

OZ

)Id

eal

for

use

inlo

calit

ies

whe

reTy

peII

ofth

ism

a-te

rial

isre

stri

cted

orpr

ohib

ited

due

toits

high

erV

OC

cont

ent,

vapo

rpr

essu

re,

and/

orlo

wer

flash

poin

t.(V

ery

Hig

hFl

ash

Poin

t+

200°

F/+

93°

C)

6850

-01-

377-

1811

CN

(1PT

)N

OT

E

Thi

sso

lven

tm

ust

bew

iped

off

the

sur-

face

com

plet

ely

asit

has

ave

rysl

owev

apor

atio

nra

te.

6850

-01-

377-

1808

CN

(1Q

T)

6850

-01-

377-

1809

CN

(1G

L)

6850

-01-

331-

3349

CN

(5G

L)

6850

-01-

331-

3350

DR

(55

GL

)

MIL

-PR

F-68

0

TO 1-1-691

A-43

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

99 Con

t.Ty

peII

Gen

eral

purp

ose

clea

ning

solv

ent

for

rem

ovin

goi

l,gr

ease

,et

c.,

from

met

alsu

rfac

es.

Do

not

use

asa

final

clea

ner

prio

rto

pain

ting

orap

plyi

ngpr

eser

-va

tion

com

poun

ds,

etc.

onpa

inte

dor

unpa

inte

dsu

rfac

es.

Sam

eas

A-A

5960

1,Ty

peII

.

(Hig

hFl

ash

Poin

t+

140°

F/+

61°

C)

6850

-01-

474-

2319

CN

(1G

L)

6850

-01-

474-

2317

CN

(5G

L)

6850

-01-

474-

2316

DR

(55

GL

)Ty

peII

I68

50-0

1-47

4-23

18C

N(1

GL

)Id

eal

for

use

inlo

calit

ies

whe

reTy

peII

ofth

ism

a-te

rial

isre

stri

cted

orpr

ohib

ited

due

toits

high

erV

OC

cont

ent,

vapo

rpr

essu

re,

and/

orlo

wer

flash

poin

t.Sa

me

asA

-A-5

9601

,Ty

peII

I.(V

ery

Hig

hFl

ash

Poin

t+

200°

F/+

93°

C)

6850

-01-

474-

2320

CN

(5G

L)

NO

TE

Thi

sso

lven

tm

ust

bew

iped

off

the

sur-

face

com

plet

ely

asit

has

ave

rysl

owev

apor

atio

nra

te.

6850

-01-

474-

2321

DR

(55

GL

)

100

Wip

eSo

lven

t,L

owV

apor

Pres

sure

P-W

-289

1C

lean

ing

ofai

rcra

ftsu

rfac

espr

ior

topa

intin

g,se

al-

ing,

non-

stru

ctur

alad

hesi

vebo

ndin

g,et

c.,

asan

alte

rnat

ive

for

ME

K,

MIB

K,

MIL

-T-8

1772

,an

dA

-A-5

9281

.Ty

peII

,C

lass

Bm

ater

ials

are

safe

tous

eon

win

dow

s,w

inds

hiel

ds/

win

dscr

eens

,an

dca

nopi

es.

Type

I(F

ast

Eva

pora

tion;

Flas

hPo

int

+10

0°F/

+38

°C

min

imum

)C

lass

A(i

ncom

patib

lew

/acr

ylic

s&

poly

carb

on-

ates

)

7930

-01-

436-

8085

CN

(1PT

)

7930

-01-

436-

8023

CN

(1Q

T)

7930

-01-

436-

8077

CN

(1G

L)

7930

-01-

436-

7959

CN

(5G

L)

7930

-01-

436-

8019

DR

(55

GL

)Ty

peII

(Slo

wE

vapo

ratio

n;H

igh

Flas

hPo

int

+14

0°F/

+61

°C

min

imum

)C

lass

B(A

cryl

ican

dpo

lyca

rbon

-at

eco

mpa

tible

)

7930

-01-

436-

8024

CN

(1Q

T)

7930

-01-

436-

7904

CN

(1G

L)

7930

-01-

436-

7953

BX

(4E

A,

1G

LB

T)

7930

-01-

436-

7944

CN

(5G

AL

)79

30-0

1-43

6-80

13D

R(5

5G

L)

TO 1-1-691

A-44

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

101

Solv

ents

,C

lean

ing,

for

Cle

anin

gPr

ior

toSe

alan

tApp

licat

ion

SAE

AM

S31

66PN

DS-

108

(CA

GE

Cod

e#3

0256

)79

30-0

1-36

7-09

94B

X(2

4E

A,

1PT

BT-

Sque

eze

Tri

gger

)

Cle

anin

gof

airc

raft

,m

issi

le,

and

equi

pmen

tpr

imar

yan

dse

cond

ary

stru

ctur

al(i

.e.,

met

alan

dco

mpo

s-ite

)su

rfac

espr

ior

tose

alin

g,bo

ndin

g,an

dap

pli-

catio

nof

adhe

sion

prom

oter

s,et

c.79

30-0

1-36

7-09

95B

X(4

EA

,1

GL

BT

)79

30-0

1-36

7-09

96C

O(5

GL

)79

30-0

1-36

7-09

97D

R(5

5G

L)

102

Isop

ropy

lAlc

ohol

,Te

chni

cal

(IPA

,2-

Prop

anol

,an

d/or

Isop

ropa

nol)

TT-

I-73

568

10-0

0-75

3-49

93C

N(½

PT)

Use

dfo

rre

mov

alof

fung

i(m

olds

)an

dcl

eani

ngof

elec

tric

alan

del

ectr

onic

com

pone

nts

and

conn

ec-

tors

.68

10-0

0-98

3-85

51C

N(1

QT

)

6810

-00-

286-

5435

CN

(1G

L)

Do

not

use

onac

rylic

plas

ticm

ater

ials

asit

may

caus

ecr

azin

g.

6810

-00-

543-

7915

CN

(5G

L)

6810

-00-

586-

6647

DR

(55

GL

)

103

Alip

hatic

Nap

htha

TT-

N-9

5,Ty

peII

(For

Cle

an-

ing

Acr

ylic

Plas

tics)

6810

-00-

238-

8119

CN

(1G

L)

Use

dfo

rcl

eani

ng/d

egre

asin

gac

rylic

plas

tics

(i.e

.,w

inds

cree

nsan

dca

nopi

es).

6810

-00-

265-

0664

CN

(5G

L)

6810

-00-

238-

8117

DR

(55

GL

)10

4Se

alan

tR

emov

er,

Che

mic

alTy

peA

eros

afe

Prod

ucts

Inc.

CA

GE

Cod

e#

1LFP

0C

omm

erci

alIt

ems

104

Con

t.Sk

yR

esto

re®

Use

dto

assi

stin

poly

sulfi

dese

alan

tre

mov

alby

soft

enin

gth

ese

alan

tbe

fore

usin

ga

plas

ticsc

rape

ror

tool

.App

lied

byno

n-m

etal

licbr

ush,

clot

h,or

pum

psp

ray.

PNL

M30

6/1

(Thi

nso

lutio

n)80

30-0

1-46

6-44

32PG

(6E

A,

1L

BT

)PN

LM

307/

1(T

hick

solu

tion)

8030

-01-

466-

4433

PG(6

EA

,1

LB

T)

Thi

sm

ater

ial

has

anob

noxi

ous

odor

.U

sein

aw

ell

vent

ilate

dar

eaan

d/or

requ

ire

pers

onne

lto

wea

ran

appr

opri

ate

resp

ira-

tor

ifin

aco

nfine

dar

ea.

TO 1-1-691

A-45

Tabl

eA

-2.

Con

sum

able

Mat

eria

ls-

Con

tinu

ed

Item No

Nom

encl

atur

eSp

ecifi

catio

n/Pa

rtN

umbe

rN

atio

nal

Stoc

kN

umbe

rU

nit

ofIs

sue

Inte

nded

Use

Sky

Was

h®U

sed

tone

utra

lize

the

area

from

whi

chse

alan

tw

asre

mov

edw

ithth

eab

ove

mat

eria

l.A

pplie

dby

non-

met

allic

brus

h,cl

oth,

orpu

mp

spra

y,sc

rubb

edw

itha

non-

met

allic

brus

hor

acl

oth,

and

then

wip

eddr

yw

itha

clot

h.

PNL

M30

8/1

8030

-01-

466-

4431

PG(6

EA

,1

LB

T)

TO 1-1-691

A-46

APPENDIX BEQUIPMENT FOR CLEANING AND CORROSION PREVENTION AND CON-

TROL

B.1 INTRODUCTION.

Table B-2 provides a list of accessories used for aircraft,missile, and equipment cleaning and corrosion preventionand control. Refer to AFMAN 23-110, Volume 2, Part 2,Chapter 22 for EAID authorization of additional equipment.The Table B-2 column headings list: Nomenclature, Specifi-cations/Part Numbers, National Stock Numbers, Units ofIssue, and Intended Use. Items are divided into functionalgroupings as follows:

• Cleaning accessories

• Corrosion removal accessories

• Conversion coating accessories

• Lighting accessories

• Safety accessories

• Sealing accessories

B.1.1 Unit Of Issue Codes. The unit of issue codesused under the unit issue column are shown and explained asfollows in Table B-1:

Table B-1. Unit Of Issue Codes

CODE UNIT CODE UNIT CODE UNIT

BG Bag EA Each PG PackageBO Bolt FT Foot PR PairBT Bottle GL Gallon PT PintBX Box GR Gross QT QuartCA Cartridge JR Jar RO RollCB Carboy KG Kilogram SE SetCC Cubic Cent. KT Kit SH SheetCN Can L Liter TU TubeCO Container LB Pound YD YardCS Case LG LengthDR Drum MX ThousandDZ Dozen OZ Ounce

TO 1-1-691

B-1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

Cle

anin

gE

quip

men

t1

Air

craf

tW

ashi

ngK

it,E

xter

ior,

Con

form

-ab

le

3MC

o.(C

AG

EC

ode

#763

81)

Gen

eral

clea

ning

ofai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

.U

ses

12in

Lx

6in

Wx

1in

orus

ere

plac

emen

tpa

dslis

ted

asIt

em#

38in

App

endi

xA

.PN

251

(Con

form

able

appl

ica-

tor

head

&2

EA

ofea

chty

peof

pad)

7920

-00-

490-

6046

KT

2Sp

onge

,Sy

nthe

ticL

-S-6

26,

Cla

ss1,

Gra

deB

orA

-A-2

073,

Type

I,St

yle

B,

Cla

ss1

7920

-00-

633-

9915

EA

(7in

Lx

4¼in

Wx

23⁄8

inT

)

Fine

pore

synt

hetic

spon

gefo

rap

plic

atio

nof

clea

n-in

gco

mpo

unds

onan

dsc

rubb

ing

ofpa

inte

dan

dun

pain

ted

surf

aces

byha

nd.

3Sc

rub

Bru

shA

-A-2

074

(sup

erse

des

H-B

-14

90)

App

licat

ion

ofcl

eani

ngco

mpo

unds

and

scru

bbin

gof

pain

ted

and

unpa

inte

dai

rcra

ft,

mis

sile

and

equi

pmen

tsu

rfac

es.

Type

I,St

yle

A(N

ylon

Bri

stle

s)79

20-0

0-61

9-91

62E

A(4

½in

x1¾

in)

Type

II,

Styl

eC

(Tam

pico

Bri

stle

s)79

20-0

0-28

2-24

70E

A(1

0¾in

x2¾

in)

Type

IV,

Styl

eB

(Nyl

onB

rist

les)

7920

-00-

061-

0037

EA

(8½

inx

5in

)Ty

peIV

,St

yle

D(P

alm

yra

Bri

stle

s)79

20-0

1-06

7-62

03E

A(8

½in

D)

TO 1-1-691

B-2 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

4B

rush

,Air

craf

tC

lean

-in

gM

IL-B

-239

58Ty

peI

(Nyl

onB

rist

les)

App

licat

ion

ofcl

eani

ngco

mpo

unds

and

scru

bbin

gof

pain

ted

and

unpa

inte

dai

rcra

ft,

mis

sile

and

equi

pmen

tsu

rfac

es.

Styl

e1

7920

-00-

054-

7768

EA

(53⁄8

inD

)St

yle

279

20-0

0-05

1-43

86E

A(6

inx

2in

)St

yle

379

20-0

0-05

1-43

83E

A(1

2in

x3½

in)

Type

II(T

ampi

coB

rist

les)

Styl

e2

7920

-00-

957-

5945

EA

(6in

x2½

in)

Type

III

(Nyl

on/

Tam

pico

Bri

stle

s)St

yle

179

20-0

0-05

1-43

84E

A(5

3⁄8

inD

)St

yle

279

20-0

0-05

1-43

87E

A(6

inx

2in

)St

yle

379

20-0

0-05

1-43

85E

A(1

2in

x3½

in)

Type

IV(H

orse

hair

/Syn

-the

ticB

rist

les)

Styl

e4

7920

-00-

685-

5969

EA

(10

inx

2¾in

)5

Win

dow

Bru

sh,

Wat

er-

proo

f(H

orse

hair

Bri

stle

s)

Type

I(R

ound

)Sc

rubb

ing

airc

raft

,m

issi

le,

and

equi

pmen

tpa

inte

dan

dun

pain

ted

surf

aces

,w

indo

ws,

win

dshi

elds

,an

d/or

win

dscr

eens

.79

20-0

0-24

0-71

76E

A(4

.5in

D)

7920

-00-

297-

1509

EA

(8in

D)

Type

II(R

ecta

ngul

ar)

7920

-01-

136-

8892

EA

(6in

x4

in)

6To

othb

rush

,So

ftB

rist

le,

Stra

ight

Lin

eD

esig

n.

A-A

-59

(Chi

ldre

n’s

-30

Tuf

ts)

8530

-01-

293-

1388

DZ

Cle

anin

gin

tric

ate

part

s.B

efor

eus

ing,

ensu

rech

emi-

cals

will

not

diss

olve

orso

ften

brus

hha

ndle

and

bris

tles.

A-A

-123

(Adu

lt’s

-30

Tuf

ts)

8530

-01-

293-

1387

DZ

TO 1-1-691

Change 1 B-3

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

7H

andl

es,

Woo

d,A

cme

Thr

eade

dan

dTa

-pe

red

End

s

A-A

-308

2(s

uper

sede

sN

N-H

-10

4)H

andl

esfo

rus

ew

ithsc

rub/

clea

ning

brus

hes

(Ite

ms

3&

4)an

dai

rcra

ftw

ashi

ngki

t(I

tem

1).

Type

I(T

hrea

ded

met

alen

d)7/ 8

inD

x4

ftL

7920

-00-

982-

6512

EA

Type

II(T

aper

eden

d)15

/16

inD

x4½

L79

20-0

0-17

7-51

06E

A15

/16

inD

x5

ftL

7920

-00-

263-

0328

EA

1in

Dx

4½L

7920

-00-

141-

5452

EA

1in

Dx

8ft

L79

20-0

0-26

3-03

27E

A1

inD

x4¼

ftL

7920

-00-

263-

0324

EA

8H

andl

e,A

cme

Thr

eade

dE

nd(T

ele-

scop

ic)

A-A

-146

4(7

/ 8in

D)

7920

-00-

926-

5146

EA

A5

ftto

10ft

exte

ndab

leal

umin

umha

ndle

for

scru

b/cl

eani

ngbr

ushe

s(I

tem

s3

&4)

orai

rcra

ftw

ashi

ngki

t(I

tem

1)to

clea

nhi

ghsu

rfac

eson

airc

raft

oreq

uipm

ent.

9N

ozzl

es,

Gar

den

Hos

e(F

or5/ 8

and

¾in

Hos

e)A

djus

tabl

e

A-A

-504

61Sp

rayi

ngan

dri

nsin

gof

airc

raft

,m

issi

les,

and

equi

p-m

ent

duri

ngcl

eani

ngop

erat

ions

.St

raig

ht,A

djus

tabl

eSp

ray

(Bra

ss)

4730

-00-

223-

6731

EA

Pist

olG

rip,

Adj

usta

ble

(Cop

-pe

rA

lloy

w/R

ubbe

rC

over

)PN

1085

5;C

AG

EC

ode

#97

141

4730

-00-

900-

0733

EA

10H

ose

and

Hos

eA

ssem

-bl

ies,

Non

-Met

allic

(Rub

ber,

Plas

tic)

A-A

-592

70(s

uper

sede

sL

-H-

520)

Spra

ying

and

rins

ing

ofai

rcra

ft,

mis

sile

s,an

deq

uip-

men

tdu

ring

clea

ning

oper

atio

ns.

Type

I,C

lass

I(R

ubbe

r)5/ 8

inID

x50

ftL

4720

-00-

203-

3920

EA

¾in

IDx

50ft

L47

20-0

0-20

3-39

12E

ATy

peII

,G

rade

A(P

VC

)5/ 8

inx

50ft

4720

-00-

729-

5334

EA

¾in

x50

ft47

20-0

0-72

9-53

38E

A11

Pum

p,B

ackp

ack

PN:

5100

-254

B43

20-0

0-28

9-89

12E

AL

ocal

ized

smal

lar

eacl

eani

ngan

dri

nsin

gof

air-

craf

t,m

issi

le,

and

equi

pmen

tsu

rfac

es.

(5G

Lca

paci

ty)

CA

GE

Cod

e#

0402

412

Spra

yers

Inse

ctic

ide,

Man

ually

-Car

ried

,H

and

Ope

rate

d-C

ompr

essi

on

A-A

-557

4837

40-0

0-19

1-36

77E

A(1

GL

ca-

paci

ty)

Use

dto

appl

yso

ilba

rrie

rm

ater

ial

onai

rcra

ftsu

r-fa

ces

(sup

erse

des

MIL

-S-1

4102

)37

40-0

0-64

1-47

19E

A(2

GL

ca-

paci

ty)

TO 1-1-691

B-4

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

13G

uns,

Spra

y,O

ilsan

dSo

lven

tSA

EA

MS-

G-9

52(s

uper

sede

sM

IL-G

-952

)Ty

peI

4940

-00-

248-

0866

EA

Non

-ato

miz

ing,

trig

ger

oper

ated

spra

yno

zzle

for

spra

ying

clea

ning

com

poun

dson

airc

raft

,m

issi

les,

and

equi

pmen

t.14

Cle

anin

gU

nit,

Por-

tabl

e,Fo

amG

ener

at-

ing

Stai

nles

sSt

eel

Tank

(Por

ta-F

oam

er)

PN00

20SS

CA

GE

Cod

e#

2136

149

40-0

1-05

8-52

67E

A(1

5G

Lca

paci

ty)

Foam

appl

icat

orfo

rM

IL-P

RF-

8793

7an

dM

IL-P

RF-

8557

0cl

eani

ngco

mpo

unds

for

clea

ning

airc

raft

,m

issi

le,

and

equi

pmen

tex

teri

ors.

Use

sco

m-

pres

sed

air

tosp

ray

wat

erde

terg

ent

solu

tions

.M

ayal

sobe

used

toap

ply

clea

ning

solv

ents

for

clea

ning

engi

nes

and

othe

req

uipm

ent.

Agu

nty

pesp

ray

wan

dan

dno

zzle

isin

clud

ed.

PN94

88-7

023

CA

GE

Cod

e#

8588

449

40-0

1-04

1-56

80E

A(4

5G

Lca

paci

ty)

15C

lean

er,

Pres

sure

,So

lven

t-W

ater

(Uni

-ve

rsal

Was

hU

nit)

PN21

C24

38G

01C

AG

EC

ode

#99

207

4940

-01-

185-

6215

EA

Use

dto

appl

ycl

eani

ngco

mpo

und

solu

tions

ina

non-

foam

stat

eto

airc

raft

,m

issi

le,

and

equi

pmen

tex

teri

orsu

rfac

esat

ara

teof

2½G

L/

min

.at

30PS

Ipr

essu

re.

16C

art,

Cor

rosi

onC

ontr

ol(T

urbi

neE

ngin

eC

lean

ing)

Mod

el#

6255

5PN

65A

102J

1C

AG

EC

ode

#0G

ZN

849

20-0

0-93

0-18

01E

APo

rtab

lecl

eani

ngm

achi

nefo

rcl

eani

ngan

dri

nsin

gai

rcra

fttu

rbin

een

gine

s.

17D

eice

r,A

ircr

aft

(Tru

ckM

ount

ed)

Mod

el#

5832

3PN

D40

-DC

AG

EC

ode

#’s

5832

3&

9340

8

1730

-01-

093-

6517

EA

Tru

ckm

ount

edsp

ray

unit

used

tosp

ray

deic

ing

and

anti-

icin

gflu

ids

onai

rcra

ftex

teri

orsu

rfac

es.

18H

eate

r,G

un,

Ele

ctri

cTy

peA

-A-5

9435

Toth

awor

dry

equi

pmen

t/com

pone

nts

orto

shri

nkhe

atsh

rink

type

insu

latin

gtu

bing

asso

ciat

edw

ithel

ectr

ical

appl

icat

ions

.Ty

peI

(350

°-5

00°

F)49

40-0

0-35

7-13

69E

ATy

peII

(500

°-7

50°

F)49

40-0

1-02

8-74

93E

ATy

peII

I(7

50°-

1000

°F)

4940

-01-

391-

7046

EA

19V

acuu

mC

lean

er,

Pneu

-m

atic

PNA

T56

0AC

F-18

CA

GE

Cod

e#

0078

451

30-0

1-36

8-58

61E

ASm

all,

light

-wei

ght,

alum

inum

,ve

ntur

ity

pe,

hand

held

vacu

umcl

eane

rw

ith18

inL

flexi

ble

hose

for

rem

ovin

gdi

rtan

dde

bris

from

airc

raft

,m

is-

sile

,an

deq

uipm

ent

inte

rior

s.20

Vac

uum

Cle

aner

(with

atta

chm

ents

)Pn

eum

atic

Type

PN15

-A10

80C

AG

EC

ode

#58

150

7910

-00-

807-

3704

EA

For

rem

ovin

gdi

rt,

debr

is,

and

fluid

sfr

omai

rcra

ft,

mis

sile

,an

deq

uipm

ent

inte

rior

s.E

lect

ric

Type

(A-A

-549

43)

PNC

8398

5-01

CA

GE

Cod

e#

1689

3

7910

-01-

236-

0893

EA

For

rem

ovin

gdi

rt,

debr

is,

and

fluid

sfr

omai

rcra

ft,

mis

sile

,an

deq

uipm

ent

inte

rior

s.T

his

vacu

umcl

eane

rca

nal

sobe

used

tore

mov

ein

fect

ious

was

tem

ater

ials

.

TO 1-1-691

B-5

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

21B

ottle

,App

licat

or,

16O

ZC

apac

ity(A

d-ju

stab

leSp

ray

Noz

zle)

A-A

-280

681

25-0

0-48

8-79

52E

ASp

rayi

ngof

clea

ning

com

poun

dso

lutio

nson

smal

lar

eas

ofai

rcra

ft,

mis

sile

,an

deq

uipm

ent

surf

aces

.

22Sp

ray

Kit,

Self

Pres

sur-

ized

Tri

gger

Spra

y,Po

ly-e

thyl

ene

Bot

tle(3

2O

ZC

apac

ity)

PN43

82T

1C

AG

EC

ode

#39

428

4940

-01-

364-

8761

EA

Spra

ying

ofcl

eani

ngco

mpo

und

solu

tions

onsm

all

area

sof

airc

raft

,m

issi

le,

and

equi

pmen

tsu

rfac

es

23U

tility

Pail,

Plas

tic(3

GL

Cap

acity

)A

-A-5

9253

(sup

erse

des

L-P

-65

)Si

ze4;

Styl

eB

7240

-00-

246-

1097

EA

Con

tain

erfo

rho

ldin

gw

ater

and

chem

ical

solu

tions

for

clea

ning

and

corr

osio

ntr

eatm

ent

oper

atio

ns.

Con

vers

ion

Coa

ting

Equ

ipm

ent

24B

rush

,Aci

dSw

abbi

ng(M

etal

Han

dle/

Hor

seha

ir&

Hog

Bri

stle

Bru

sh)

A-A

-289

,Ty

peII

,C

lass

1,Si

ze1

7920

-00-

514-

2417

GR

(5¾

inL

x3⁄8

inW

)D

ispo

sabl

ebr

ush

for

appl

ying

chem

ical

conv

ersi

onco

atin

gso

lutio

nsan

dso

me

brus

habl

ese

alan

ts.

25M

oist

ener

,Pa

per

Seal

-in

g,Fo

unta

in-T

ype

(Spo

nge

Moi

sten

erSt

ick)

A-A

-137

(sup

erse

des

GG

-M-

571)

7520

-00-

241-

2981

EA

App

licat

ion

ofch

emic

alco

nver

sion

coat

ing

solu

-tio

nsto

smal

lar

eas.

26W

ash

Bot

tle,

Lab

ora-

tory

,Po

lyet

hyle

ne(2

50m

l.C

apac

ity)

Com

mer

cial

Item

CA

GE

Cod

e#

2551

866

40-0

0-29

9-84

93E

AB

X(1

2E

A)

Use

dfo

rri

nsin

gch

emic

ally

trea

ted

surf

aces

.

Cor

rosi

onR

emov

alE

quip

men

t27

Dri

ll,Pn

eum

atic

,Po

r-ta

ble

(¼in

Chu

ck;

3200

RPM

)

OO

-D-6

91C

orro

sion

rem

oval

and

scuf

fsa

ndin

g.

Type

I,St

yle

C(S

trai

ght

Dri

ve,

Pist

olG

rip)

5130

-00-

294-

9511

EA

Type

I,St

yle

A(9

0°A

ngle

Dri

ve,

Bod

yG

rip)

5130

-00-

293-

1977

EA

28K

ey,

Dri

llC

huck

(¼in

Dri

ve)

A-A

-509

66PN

K1

CA

GE

Cod

e#

7507

834

60-0

0-26

4-55

77E

ASe

curi

ngor

rele

asin

gdr

illbi

t.Fo

rus

ew

ithIt

em#

27dr

illm

otor

.29

Sand

er,

Pad,

Pneu

mat

ic(O

rbita

lM

otio

n)6,

000

-9,

000

RPM

A-A

-268

7(O

O-S

-101

,Ty

peI,

Styl

e1)

5130

-00-

606-

9694

EA

Cor

rosi

onre

mov

alan

dbl

end

out

asw

ell

assc

uff

sand

ing,

finis

hsa

ndin

g,an

dfe

athe

red

ging

/ble

nd-

ing

ofpa

int

surf

aces

.

TO 1-1-691

B-6 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

30Sa

nder

,D

isc,

Pneu

-m

atic

,Po

rtab

le(R

an-

dom

Orb

ital)

A-A

-269

0(O

O-S

-101

,Ty

peII

,St

yle

3)51

30-0

0-20

4-06

23E

AC

orro

sion

rem

oval

and

blen

dou

tas

wel

las

scuf

fsa

ndin

g,fin

ish

sand

ing,

and

feat

her

edgi

ng/b

lend

-in

gof

pain

tsu

rfac

es.

The

sand

er’s

rand

omor

bita

lac

tion

prev

ents

scra

tche

san

dsw

irl

mar

ks.

Dua

lm

otio

n,ve

rtic

aldr

ive

with

6in

Dm

axpa

d&

7000

RPM

max

(unl

oade

d)31

Sand

er,

Dis

c,Pn

eu-

mat

ic,

Port

able

(Rig

htA

ngle

)R

ight

angl

edr

ive

with

7in

Dpa

dm

ax&

6000

RPM

max

(unl

oade

d)

A-A

-268

9(O

O-S

-101

,Ty

peII

,St

yle

2)51

30-0

0-59

6-11

76E

AC

orro

sion

rem

oval

and

blen

dou

t.R

ight

angl

edr

ive

mak

esit

easi

erto

use

inco

rner

s,al

ong

edge

s,an

din

tight

spac

es.

32D

ryH

onin

gM

achi

ne,

Port

able

,Air

-O

pera

ted

(Vac

u-B

last

er)

PN41

303

CA

GE

Cod

e#

6255

549

40-0

0-87

2-17

12E

AA

com

pact

,se

lf-c

onta

ined

,lig

htw

eigh

tab

rasi

vebl

astin

gun

itus

edfo

rth

esa

fean

dco

nven

ient

re-

mov

alof

corr

osio

npr

oduc

tsfr

omai

rcra

ft,

mis

sile

and

equi

pmen

tsu

rfac

esan

dth

eir

com

pone

nts

with

noha

zard

ous

part

icle

emis

sion

s.A

llab

rasi

vepa

rtic

les,

corr

osio

npr

oduc

ts,

and

pain

tch

ips

are

draw

nba

ckin

toth

em

achi

new

here

resi

dues

are

filte

red

out

and

colle

cted

for

disp

osal

,an

dth

eab

rasi

vepa

rtic

les

are

recy

cled

.33

Ele

ctri

cal

Pum

pK

itfo

rD

ryH

onin

gM

achi

ne(I

tem

#32

)

PN91

8708

CA

GE

Cod

e#

6255

549

40-0

0-94

8-38

10E

AT

heel

ectr

icpu

mp

for

the

Dry

Hon

ing

Mac

hine

al-

low

sus

eof

low

pres

sure

/low

volu

me

air

toop

er-

ate

inst

ead

ofth

elo

wpr

essu

re/h

igh

volu

me

air

requ

ired

toop

erat

eun

itseq

uipp

edw

ithth

eai

rej

ecto

rpu

mp.

34G

un,A

irB

low

,(B

last

Cle

anin

g)A

-A-5

5543

(sup

erse

des

GG

G-

G-7

70)

Use

tore

mov

ech

ips,

dirt

,an

dw

aste

mat

eria

lfr

omm

achi

nes,

wor

kpi

eces

,or

benc

hes.

Type

II(p

ush

butto

n),

Styl

eB

(3⁄8

inIn

t.T

hd.)

4940

-00-

223-

8972

EA

Type

II(p

ush

butto

n),

Styl

eA

(¼in

Int.

Thd

.)49

40-0

0-33

3-55

41E

A

TO 1-1-691

Change 1 B-7

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

35A

irH

ose

Ass

embl

ies,

Gen

eral

Purp

ose

Hos

ean

dH

ose

As-

sem

blie

s,N

on-

Met

allic

Spra

y

A-A

-596

13H

ose

asse

mbl

ies

used

with

pneu

mat

icto

ols,

pain

tsp

ray

guns

,an

ddr

yho

ning

mac

hine

s.

3⁄8

inID

x50

ft47

20-0

0-28

9-34

29FT

Hos

e,R

ubbe

r,an

dH

ose

Ass

embl

ies,

Rub

ber,

Pneu

mat

ic(Y

arn

and

Fabr

icR

einf

orce

d)

A-A

-595

65

½in

IDx

50ft

4720

-00-

278-

4889

FT5/ 8

inID

x50

ft47

20-0

0-27

8-48

90FT

¾in

IDx

50ft

4720

-00-

278-

4891

FT

36C

oupl

ing

Hal

ves,

Qui

ck-D

isco

nnec

tA

-A-5

9439

(sup

erse

desM

IL-

C-4

109)

Type

II(M

ale)

¼in

NPT

/Men

d(S

tyle

1)47

30-0

0-49

4-32

71E

AM

ale

quic

kdi

scon

nect

halv

esfo

rus

ew

ithpn

eu-

mat

icto

ols

and

pain

tsp

ray

guns

.3⁄8

inN

PT/F

end

(Sty

le2)

4730

-00-

293-

7182

EA

3⁄8

inSh

ank

end

(Sty

le3)

4730

-00-

277-

5679

EA

½in

NPT

/Men

d(S

tyle

1)47

30-0

0-29

3-71

65E

AM

ale

quic

kdi

scon

nect

halv

esfo

rus

ew

ithpo

rtab

ledr

yho

ning

mac

hine

s.½

inN

PT/F

end

(Sty

le2)

4730

-01-

233-

3434

EA

¾in

NPT

/Men

d(S

tyle

1)47

30-0

0-29

3-71

80E

ATy

peI

(Fem

ale)

¼in

NPT

/Fen

d(S

tyle

2)47

30-0

1-17

7-09

87E

AFe

mal

equ

ick

disc

onne

ctha

lves

for

use

with

pneu

-m

atic

tool

san

dpa

int

spra

ygu

ns.

3⁄8

inN

PT/M

end

(Sty

le1)

4730

-00-

203-

0178

EA

3⁄8

inSh

ank

end

(Sty

le3)

4730

-00-

494-

3272

EA

½in

NPT

/Men

d(s

tyle

1)47

30-0

0-20

3-48

47E

AFe

mal

equ

ick

disc

onne

ctha

lves

for

use

with

por-

tabl

edr

yho

ning

mac

hine

s.½

inSh

ank

end

(Sty

le3)

4730

-00-

905-

9794

EA

¾in

NPT

/Men

d(S

tyle

1)47

30-0

0-29

3-70

43E

A37

Hos

eC

lam

pA

-A-5

2506

(sup

erse

des

WW

-C

-440

)47

30-0

0-82

6-42

68E

AM

etal

hose

clam

pus

edfo

rho

ldin

gfle

xibl

edu

cts

orho

ses

onto

am

ale

end

ora

38H

and

Pad

Hol

der

(for

use

with

Item

#1,

App

endi

xA

)

3MC

o.PN

952

(IN

STA

-L

OK

)C

AG

EC

ode

#28

124

Com

mer

cial

Item

Ope

nPu

rcha

seE

AH

and

tool

for

hold

ing

abra

sive

pads

.

TO 1-1-691

B-8 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

39H

olde

r,D

isk

Pad,

Hoo

kan

dL

oop

Type

(for

use

with

Item

#47

)

3MC

o.(C

AG

EC

ode

#28

124)

Bac

k-up

pad

toru

nsu

rfac

eco

nditi

onin

gdi

scs

ona

drill

mot

or.

PN92

15C

omm

erci

alIt

emE

A(1

½in

Don

¼in

shan

k)O

pen

Purc

hase

PN04

8011

-074

94-8

Com

mer

cial

Item

CS

(10

EA

)(2

inD

on¼

insh

ank)

Ope

nPu

rcha

sePN

923

(3in

Don

¼in

shan

k)53

45-0

1-34

2-59

32E

APN

0480

11-0

7492

-4C

omm

erci

alIt

emC

S(5

EA

)(4

inD

on¼

insh

ank)

Ope

nPu

rcha

sePN

0480

11-0

5680

-7C

omm

erci

alIt

emE

A(5

inD

on¼

insh

ank)

Ope

nPu

rcha

se40

Pad,

Abr

asiv

eD

isk

Hol

der

(for

use

with

Item

#5,

App

endi

x.A

)

3MC

o.(C

AG

EC

ode

#28

124)

Bac

k-up

pad

toru

n6

inD

abra

sive

pape

rdi

scs

ona

dual

mot

ion

type

sand

er.

PN05

1144

-055

7651

30-0

1-07

5-81

37E

A

41M

andr

els

(for

use

with

Item

#’s

42an

d43

)3M

Co.

(CA

GE

Cod

e#

2812

4)PN

990

(3⁄8

insh

ank)

Ope

nPu

rcha

seB

X(5

EA

)Fo

rus

ew

ith2

-3

inD

radi

albr

istle

disc

sst

acke

dfr

om1⁄8

to½

inW

PN99

1(3

⁄8in

shan

k)O

pen

Purc

hase

BX

(5E

A)

For

use

with

2-

3in

Dra

dial

bris

tledi

scs

stac

ked

from

¾in

to1

inW

PN93

334

60-0

1-04

4-26

26E

AFo

rus

ew

ith2

to3

inD

abra

sive

disc

s.(2

inL

;¼

insh

ank

w/1

inD

was

her)

PN93

4,34

60-0

0-15

0-71

64E

AFo

rus

ew

ith3

to6

inD

abra

sive

disc

s.(3

1/16

inL

;¼

insh

ank

w/

2½in

Dw

ashe

r)PN

935,

Split

Min

iM

andr

el34

60-0

0-15

0-71

63E

AFo

rus

ew

ith1

inW

x1½

inL

piec

esof

abra

sive

mat

eria

lto

fitin

totig

htar

eas

for

corr

osio

nre

-m

oval

.(2

inL

;¼

insh

ank)

TO 1-1-691

Change 1 B-9

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

42R

oloc

TM

Dis

cPa

dH

olde

rsfo

rIn

Lin

eB

rist

leD

iscs

(Ite

m#

45)

and

Rol

ocT

M-

Coa

ted

Abr

asiv

eD

iscs

(Ite

m#

46)

3MC

o.(C

AG

EC

ode

#28

124)

Com

mer

cial

Item

sU

sed

toho

ldR

oloc

TM

in-l

ine

bris

tledi

scs

and

coat

edab

rasi

vedi

scs

for

inst

alla

tion

onei

ther

inlin

eor

righ

tan

gle

drill

mot

ors.

PN05

1144

-451

01O

pen

Purc

hase

BX

(5E

A)

(1in

DH

olde

r)PN

0511

44-4

5095

-4O

pen

Purc

hase

BX

(5E

A)

(2in

DH

olde

r)PN

0511

44-4

5092

-3O

pen

Purc

hase

BX

(5E

A)

(3in

DH

olde

r)PN

0511

44-4

5179

-1O

pen

Purc

hase

BX

(5E

A)

(4in

DH

olde

r)PN

0511

44-4

5102

-9O

pen

Purc

hase

EA

(¼in

Dth

read

edsh

aft)

43W

heel

,Fl

apB

rush

,A

bras

ive

(Non

-w

oven

nylo

nfla

psw

ithal

umin

umox

ide

abra

sive

;M

aroo

nin

colo

r)(6

inD

x1

inW

x2

inar

bor

hole

)

3MC

o.(C

AG

EC

ode

#28

124)

Com

mer

cial

Item

sR

emov

ing

mild

corr

osio

nfr

oman

dpo

lishi

ngof

surf

aces

.Als

ofo

rm

echa

nica

lre

mov

alan

dfe

ath-

erin

gof

pain

tsy

stem

s.M

axim

umop

erat

ing

spee

d(M

OS)

is34

00R

PM.

Use

don

PN93

4m

andr

el(I

tem

#41

abov

e).

PN5A

FN6X

1X2

(fine

grit)

5345

-00-

151-

7936

EA

PN5A

MD

6X1X

2(m

ediu

mgr

it)53

45-0

0-15

7-97

90E

A

TO 1-1-691

B-10

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

44St

acka

ble

Rad

ial

Bri

stle

Dis

cs,

(Re-

galit

eTM

/Alu

min

umO

xide

&C

ubitr

onA

bras

ive)

3MC

o.(C

AG

EC

ode

#28

124)

Com

mer

cial

Item

sR

emov

ing

mild

corr

osio

nan

dpo

lishi

ngsu

rfac

esan

dde

-bur

ring

.Als

ofo

rm

echa

nica

lre

mov

alof

cure

dse

alan

ts,

adhe

sive

s,pa

ints

,an

dfe

athe

ring

ofpa

int

syst

ems.

Use

with

adr

illan

da

#93

4,99

0,or

991

man

drel

asap

prop

riat

e.C

anbe

used

tore

ach

into

deep

depr

esss

ions

and

cavi

ties.

Can

beus

edon

in-l

ine

orri

ght

angl

edr

illm

otor

s.T

heM

OS

is25

,000

RPM

.

3in

D-

Man

drel

Mou

nted

PN04

8011

-242

79-8

(Gra

de50

-G

reen

Col

or)

Ope

nPu

rcha

seC

S(4

0E

A)

PN04

8011

-242

80-4

Ope

nPu

rcha

seC

S(4

0E

A)

(Gra

de80

-Y

ello

wC

olor

)PN

0480

11-2

4281

-1(G

rade

120

-W

hite

Col

or)

Ope

nPu

rcha

seC

S(4

0E

A)

PN05

1131

-075

44-3

3460

-01-

509-

1789

CS

(40

EA

)(G

rade

120

-W

hite

Col

or;

Thi

ckB

rist

les)

Rol

ocT

MD

isc

Pad

Hol

der

Mou

nted

PN04

8011

-242

76-7

(Gra

de50

-G

reen

Col

or)

Ope

nPu

rcha

seS

(40

EA

)

PN04

8011

-242

77-4

(Gra

de80

-Y

ello

wC

olor

)O

pen

Purc

hase

CS

(40

EA

)

PN04

8011

-242

78-1

(Gra

de12

0-

Whi

teC

olor

)O

pen

Purc

hase

CS

(40

EA

)

Rol

ocT

MD

isc

Pad

Hol

der

for

thes

eR

adia

lB

rist

leD

iscs

PN05

1144

-451

01-2

Ope

nPu

rcha

seB

X(5

EA

)

TO 1-1-691

B-11

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

45R

oloc

TM

InL

ine

Bri

stle

Dis

cs3M

Co.

(CA

GE

Cod

e#

2812

4)C

omm

erci

alIt

ems

Rem

ovin

gm

ildco

rros

ion

and

polis

hing

surf

aces

and

de-b

urri

ng.A

lso

for

mec

hani

cal

rem

oval

ofcu

red

seal

ants

,ad

hesi

ves,

and

pain

tsan

dfe

athe

r-in

gof

pain

tsy

stem

s.C

anbe

used

onin

line

orri

ght

angl

edr

illm

otor

saf

ter

mou

ntin

gon

anap

-pr

opri

ate

Rol

ocT

Mdi

scpa

dho

lder

(Ite

m#

42)

The

max

imum

oper

atin

gsp

eed

(MO

S)de

pend

son

the

diam

eter

ofth

edi

sc.

(Reg

alite

Rol

ocT

M/A

lu-

min

umO

xide

&C

u-bi

tron

Abr

asiv

e)

1in

Dw

/5/ 8

inL

bris

tles

PN04

8011

-186

98-6

Ope

nPu

rcha

seC

S(8

0E

A)

(Gra

de50

-G

reen

Col

or)

PN04

8011

-187

06-8

Ope

nPu

rcha

seC

S(8

0E

A)

(Gra

de80

-Y

ello

wC

olor

)PN

0480

11-1

8710

-5O

pen

Purc

hase

CS

(40

EA

)(G

rade

120

-W

hite

Col

or)

2in

Dw

/5/ 8

inL

bris

tles

PN04

8011

-187

30-3

Ope

nPu

rcha

seC

S(4

0E

A)

(Gra

de50

-G

reen

Col

or)

PN04

8011

-187

32-7

5345

-01-

432-

3032

CS

(40

EA

)(G

rade

80-

Yel

low

Col

or)

PN04

8011

-187

33-4

3460

-01-

509-

1806

(Gra

de12

0-

Whi

teC

olor

)3

inD

w/

5/ 8

inL

bris

tles

PN04

8011

-187

34-1

Ope

nPu

rcha

seC

S(4

0E

A)

(Gra

de50

-G

reen

Col

or)

PN04

8011

-187

36-5

Ope

nPu

rcha

seC

S(4

0E

A)

(Gra

de80

-Y

ello

wC

olor

)PN

0480

11-1

8737

-234

60-0

1-50

9-18

29C

S(4

0E

A)

(Gra

de12

0-

Whi

teC

olor

)

TO 1-1-691

B-12

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

46R

oloc

TM

Coa

ted

Abr

a-si

veD

iscs

(Re-

galit

eTM

/Alu

min

umO

xide

&C

ubitr

onA

bras

ive)

and

Nyl

onM

atD

iscs

(Alu

mi-

num

Oxi

deA

bra-

sive

);Fo

rus

ew

ithIt

em#

42

3MC

o.(C

AG

EC

ode

#28

124)

Com

mer

cial

Item

sFo

rre

mov

alof

mod

erat

eto

seve

reco

rros

ion

from

thic

kcr

oss

sect

ion

alum

inum

,st

eel,

and

mag

ne-

sium

stru

ctur

esw

hen

mou

nted

onIt

em#

42di

scpa

dho

lder

san

din

stal

led

onei

ther

in-l

ine

orri

ght

angl

edr

illm

otor

s.U

seof

thes

eab

rasi

vedi

scs

shou

ldbe

follo

wed

bysm

ooth

ing

out

the

area

with

ale

ssag

gres

sive

abra

sive

disc

such

asan

Item

#47

surf

ace

cond

ition

ing

disc

(ver

yfin

egr

it).

Gra

de-

80gr

itPN

0511

44-1

4661

-153

45-0

1-42

0-14

57C

S(2

00E

A)

(2in

Ddi

sc)

PN-0

5114

4-76

634-

5O

pen

Purc

hase

CS

(200

EA

)(3

inD

disc

)PN

0511

44-8

3693

-2O

pen

Purc

hase

CS

(100

EA

)(4

inD

disc

)G

rade

-10

0gr

itPN

0511

44-8

0508

-2O

pen

Purc

hase

CS

(200

EA

)(2

inD

disc

)PN

0511

44-8

0509

-9O

pen

Purc

hase

CS

(200

EA

)(3

inD

disc

)PN

0511

44-8

3694

-9O

pen

Purc

hase

CS

(100

EA

)(4

inD

disc

)G

rade

-12

0gr

itPN

0511

44-8

0512

-953

45-0

1-42

0-14

53C

S(2

00E

A)

(2in

Ddi

sc)

PN05

1144

-805

13-6

Ope

nPu

rcha

seC

S(2

00E

A)

(3in

Ddi

sc)

PN05

1144

-836

95-6

Ope

nPu

rcha

seC

S(1

00E

A)

(4in

Ddi

sc)

Ver

yFi

neG

rit

(Blu

eC

olor

)PN

0480

11-0

5523

5345

-01-

367-

7680

CS

(200

EA

)(2

inD

-Sco

tch

Bri

teD

isc)

PN04

8011

-055

3053

45-0

1-39

7-52

53C

S(1

00E

A)

(3in

DSc

otch

Bri

teD

isc)

TO 1-1-691

B-13

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

47Su

rfac

eC

ondi

tioni

ngD

iscs

,Alu

min

umO

xide

(for

use

with

Item

#39

)

3MC

o.(C

AG

EC

ode

#28

124)

Com

mer

cial

Item

sC

orro

sion

rem

oval

and

surf

ace

prep

arat

ion.

The

disc

spr

oduc

em

inim

alm

etal

/sub

stra

tere

mov

al.

The

ype

rfor

mbe

ston

righ

tan

gle

type

drill

mo-

tors

,bu

tca

nbe

used

succ

essf

ully

onin

-lin

edr

illm

otor

s.D

iscs

are

mou

nted

onth

eap

prop

riat

esi

zed

disc

pad

hold

er(I

tem

#39

)w

hich

isth

enm

ount

edin

toei

ther

anin

-lin

eor

ari

ght

angl

edr

illm

otor

.

Ver

yFi

neG

rit

(Blu

eC

olor

)PN

0480

11-0

4T75

-6O

pen

Purc

hase

CS

(200

EA

)(1

½in

D)

PN04

8011

-04T

77-0

Ope

nPu

rcha

seC

S(1

00E

A)

(3in

D)

PN04

8011

-042

78-7

Ope

nPu

rcha

seC

S(1

00E

A)

(4in

D)

PN04

8011

-043

03-6

Ope

nPu

rcha

seC

S(5

0E

A)

(5in

D)

Med

ium

Gri

t(M

aroo

nC

olor

)PN

0480

11-0

4122

-3O

pen

Purc

hase

CS

(200

EA

)(1

½in

D)

PN04

8011

-074

59-7

Ope

nPu

rcha

seC

S(2

00E

A)

(2in

D)

PN04

8011

-041

24-7

Ope

nPu

rcha

seC

S(1

00E

A)

(3in

D)

PN04

8011

-074

51-1

Ope

nPu

rcha

seC

S(1

00E

A)

(4in

D)

PN04

8011

-006

43-7

Ope

nPu

rcha

seC

S(5

0E

A)

(5in

D)

48C

OM

BI-

SW

heel

with

Spin

dle

Mou

nt,A

lu-

min

umO

xide

,M

a-ro

onC

olor

(3in

Dx

1¾in

Ww

/¼in

Dsh

ank)

3MC

o.(C

AG

EC

ode

#28

124)

Com

bina

tion

ofal

umin

umox

ide

coat

edab

rasi

vean

dno

n-w

oven

nylo

nm

ater

ial

used

for

finis

hing

,bl

endi

ng,

and

rem

ovin

glig

htto

med

ium

corr

o-si

on.

MO

Sis

8000

RPM

.12

0gr

itPN

0511

44-8

0678

Ope

nPu

rcha

seE

A18

0gr

itPN

0511

44-8

0799

Ope

nPu

rcha

seE

A

TO 1-1-691

B-14

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

49A

bras

ive

Whe

els,

Non

-W

oven

Nyl

on,

Res

inR

einf

orce

d(A

lum

i-nu

mO

xide

Abr

asiv

e)

A-A

-592

92(S

uper

sede

sM

IL-

W-8

1319

,Ty

peI)

Cla

ss2

(Lam

inat

ed)

Rem

ovin

gm

ediu

mto

seve

reco

rros

ion

(e.g

.in

ter-

gran

ular

,ex

folia

tion)

from

thic

km

ater

ials

.

Gra

deC

(Med

ium

)-1

50gr

it(3

inD

x¾

inW

on¼

inD

shaf

t)

5345

-00-

732-

9989

EA

The

sew

heel

sar

eve

ryag

gres

sive

and

will

rem

ove

met

alsu

bstr

ate

asw

ell

asco

rro-

sion

prod

ucts

.

Gra

deA

(Ver

yFi

ne)

-28

0gr

it(2

inD

x½

inW

on¼

inD

shaf

t)

5345

-00-

935-

7869

EA

Gra

deB

(Fin

e)-

180

Gri

t(6

inD

x¾

inW

with

½in

arbo

rho

le)

3460

-01-

479-

5941

EA

50A

bras

ive

Dis

kK

it(C

ompo

site

Mat

eria

lR

epai

r)

PN65

001

CA

GE

Cod

e#

0017

953

45-0

1-01

5-14

19K

TFo

rus

ein

repa

irof

com

posi

tean

dho

neyc

omb

ma-

teri

als

ON

LY.

Com

esw

ith3

disc

hold

ers

(1in

,2

in,

and

3in

Dsi

zes)

and

150

disc

sof

asso

rted

grits

(50

inea

chsi

ze).

51Fi

les,

Rot

ary,

Con

eSh

ape,

Hig

hSp

eed

Stee

lor

Tun

gste

nC

arbi

de

A-A

-511

76R

emov

ing

seve

reco

rros

ion

(e.g

.in

terg

ranu

lar

and

exfo

liatio

n)an

dun

derl

ying

met

al;

atta

chto

ast

raig

htin

-lin

epn

eum

atic

drill

.Ty

peII

(Tun

gste

nC

arbi

de)

Styl

eA

(RH

spir

alflu

te),

3455

-00-

293-

3560

EA

Cla

ssB

(med

ium

),Si

ze5

(¼in

Dx

½in

L)

Styl

eB

(RH

spir

alflu

tew

/chi

pbr

eake

r),

Cla

ssC

(Fin

e),

Size

6(¼

inD

x¾

inL

)

3455

-00-

293-

3559

EA

Rot

ary

files

are

extr

emel

yag

gres

sive

tool

san

dca

nea

sily

rem

ove

too

muc

hm

etal

subs

trat

e.Pa

yst

rict

atte

ntio

n,an

dta

keex

tra

care

whe

nus

ing

thes

eto

ols.

Styl

eA

,C

lass

C,

Size

7(¼

inD

x1

inL

)34

55-0

0-29

3-35

61E

A

TO 1-1-691

B-15

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

52A

ircr

aftA

dhes

ive

and

Dec

alR

emov

alD

isc

(AA

DR

),N

on-

abra

sive

3MC

o.(C

AG

EC

ode

#52

152)

Com

mer

cial

Item

sU

sed

ona

pneu

mat

icdr

illto

rem

ove

adhe

sive

s,se

alan

ts,

deca

ls,

grap

hics

,vi

nyl

stri

ppin

gta

pes,

doub

le-s

ided

mol

ding

tape

s,an

dle

adin

ged

geta

pes

with

out

rem

ovin

g/da

mag

ing

the

unde

r-co

atin

gs.

Rec

omm

ende

dop

erat

ing

spee

dis

2600

RPM

;do

not

exce

ed40

00R

PM.

PN05

1131

-074

98(6

inD

x5⁄8

inW

onR

oloc

TM

Hol

der

w/3

⁄8in

Dsh

ank)

3460

-01-

447-

8021

CS

(5E

AD

iscs

w/1

Hol

der)

PN04

8011

-241

05-0

(1E

A2

in,

3in

,4,

5,6

inD

x5⁄8

inW

Dis

cw

/1E

AR

oloc

TM

Hol

der

w/3

⁄8in

Dsh

ank)

Ope

nPu

rcha

seC

S(5

EA

Dis

csw

/1H

olde

r)N

OT

E

Do

not

use

onac

rylic

lacq

uer

pain

tsan

dpo

lyca

rbon

ate

orac

rylic

plas

tics

(can

o-pi

es,

win

dow

s,an

dw

inds

cree

ns).

TO 1-1-691

B-16 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

53Se

alan

t(M

astic

)R

e-m

oval

Kits

Kel

l-St

rom

Tool

Co,

Inc.

(CA

GE

Cod

e#

7524

5)C

omm

erci

alIt

ems

Use

dto

rem

ove

cure

dse

alan

tth

atov

er-c

oats

fas-

tene

rpa

ttern

sor

fille

tse

als

atst

ruct

ure

edge

sw

ithsh

arpe

ned

plas

tican

d/or

stee

lbl

ades

mou

nted

ina

pneu

mat

icpo

wer

edvi

brat

ory

tool

ora

man

ual

hand

held

supp

ort

hand

le.

Can

also

beus

edto

rem

ove

anti-

skid

mat

eria

lsfr

omai

rcra

ftflo

ors/

deck

s.

Pneu

mat

icV

ibro

-Gun

Seal

ant

Rem

oval

Kit

-C

ase

cont

aini

ng1

Vib

ro-G

unw

ithai

rho

se,

blad

esh

arpe

ner

with

aggr

egat

edi

scan

dva

cuum

,ex

tra

disc

PNO

Z70

05)

and

vacu

umba

gsPN

OZ

7004

),6

EA

1in

W(P

NO

Z70

01)

&2

EA

½in

W(P

NO

Z70

02ri

gid

plas

ticbl

ades

,&

1E

A2

inW

(PN

OZ

7003

)fle

xibl

est

eel

blad

e

PNO

Z70

00(V

ibro

-Gun

Seal

-an

tR

emov

alK

it49

20-0

1-50

0-80

87E

A

PNO

Z70

06(V

ibro

-Gun

only

)49

20-0

1-50

0-80

84E

A

PNO

Z70

07(H

and

Type

Seal

-an

tR

emov

alK

it)49

20-0

1-50

0-80

90E

A

Han

dTy

pese

alan

tR

e-m

oval

Kit

-C

ase

cont

aini

ng1

EA

pad-

ded

palm

supp

ort

hand

le(P

NO

Z70

08);

6E

A1

inW

(PN

OZ

7001

),3

EA

½in

W(P

NO

Z70

02),

3E

A1½

inW

(PN

OZ

7010

),&

3E

A1

inW

(bu

tton

head

rive

tad

apta

ble)

rigi

dpl

as-

ticbl

ades

;2

EA

shar

peni

ngst

ones

(PN

OZ

7009

);&

2E

Asm

all

clea

ning

brus

hes

Ant

iSt

atic

Air

Hos

es

PNO

Z70

13(5

0ft

L)

Ope

nPu

rcha

seE

A

PNO

Z70

14(1

00ft

L)

Ope

nPu

rcha

seE

A

Rep

lace

men

tpa

rts

-us

ePN

’sat

left

toor

der

Ope

nPu

rcha

se

TO 1-1-691

B-17

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

54Se

alan

tR

emov

alTo

ols

(Dri

llM

otor

Mou

nted

SRC

utte

rs&

Dis

cs)

3MC

o.(C

AG

EC

ode

#76

381)

Com

mer

cial

Item

sT

hese

plas

ticcu

tters

and

smal

lbr

istle

disc

sar

epa

r-tic

ular

lyus

eful

for

rem

oval

ofse

alan

tco

atin

gson

and

arou

ndpr

otru

ding

fast

ener

san

dla

pty

pese

ams.

The

ypr

ovid

eef

fect

ive

seal

ant

rem

oval

whi

lem

inim

izin

gco

ntam

inat

ion

ofth

esu

rrou

nd-

ing

area

and

the

subs

eque

ntre

quir

edcl

ean

up.

PN61

-500

1-75

76-7

(#8

SRC

utte

r-

1in

D)

3455

-01-

509-

1769

BX

(40

EA

)

PN61

-500

1-75

77-5

(#3

SRR

otar

yC

utte

r)34

55-0

1-50

9-17

79B

X(4

0E

A)

PN61

-500

1-75

78-3

(2in

SRR

adia

lB

rist

leD

isc)

3460

-01-

509-

1794

BX

(40

EA

)

PN61

-500

1-75

79-1

(3in

SRR

adia

lB

rist

leD

isc)

3460

-01-

509-

1791

BX

(40

EA

)

PN61

-500

0-78

16-9

(Rol

ocT

M

Pad

&#

1Pl

astic

Hol

der)

3460

-01-

509-

1784

BX

(5E

A)

PN61

-500

0-74

12-7

(Rol

ocT

M

Pad

&#

7Pl

astic

Red

But

-to

nfo

rH

olde

r)

3460

-01-

509-

1812

BX

(5E

A)

PN61

-500

0-73

34-3

(#99

0M

andr

el)

3460

-01-

493-

7924

BX

(5E

A)

Env

isio

nPn

eum

atic

Seal

ant

Rem

oval

Kit

(In-

clud

es:

1E

AIn

gers

oll-

Ran

d10

00R

PMri

ght

angl

edr

ive,

¼in

thre

aded

chuc

kpn

eum

atic

drill

mot

or;

1tu

bew

ith5

EA

#8

SRcu

tters

;an

d1

tube

with

5E

A#

3SR

cutte

rs

PNQ

A08

59D

-1C

AG

EC

ode

#2A

178

5130

-01-

514-

0853

Kit

55O

ptic

alD

epth

Mi-

crom

eter

Kit

(Dig

ital

read

-out

)PR

E-

FER

RE

DT

OO

L

PN84

00K

CA

GE

Cod

e#

6595

666

50-0

1-22

0-89

42E

AIn

spec

tion

ofan

dde

pth,

wid

th,

and

leng

thm

easu

re-

men

tsof

corr

osio

nda

mag

ean

dco

rros

ion

grin

dou

tar

eas.

TO 1-1-691

B-18 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

56O

ptic

alD

epth

Mi-

crom

eter

Kit

(Ana

-lo

g,m

echa

nica

lre

ad-

out)

ALT

ER

NA

TE

TO

OL

PN96

6A1

CA

GE

Cod

e#

9254

166

50-0

0-83

1-55

32E

AIn

spec

tion

ofan

dde

pth,

wid

th,

and

leng

thm

easu

re-

men

tsof

corr

osio

nda

mag

ean

dco

rros

ion

grin

dou

tar

eas.

57D

epth

Gau

ge,

Nee

dle

Poin

tD

ial

Indi

cato

rPN

6527

281

CA

GE

Cod

e#

7016

852

10-0

0-71

0-43

59E

APr

ecis

ion

mea

sure

men

tof

corr

osio

nda

mag

ean

dco

rros

ion

grin

dou

tde

pth

with

ina

rang

eof

0.0i

nto

0.12

5in

.58

Mag

nify

ing

Gla

ss,

Fold

ing

Pock

etT

ripl

eL

ens

Type

(Cir

cula

rsh

ape

-½

inD

)

PN81

-23-

95C

AG

EC

ode

#06

175

6650

-00-

530-

1880

EA

Insp

ectio

nof

corr

osio

n.M

agni

fyin

gpo

wer

ofth

ele

nses

are

5X,

7X,

and

10X

.L

ense

spi

vot

for

ei-

ther

sing

leor

com

bina

tion

use.

59In

spec

tion

Mir

ror

GG

G-M

-350

,Ty

peII

(plu

nger

activ

ated

),C

lass

3(r

ecta

n-gu

lar)

Aid

for

insp

ectin

gha

rdto

see

area

sfo

rco

rros

ion.

Size

1(1

½in

Lx

1¼in

W)

5120

-00-

278-

9926

EA

Size

2(2

inL

x1¾

inW

)51

20-0

0-61

8-69

02E

A60

Penc

il,A

ircr

aft

Mar

k-in

g(N

on-C

orro

sive

-7

inL

)

MIL

-P-8

3953

Iden

tifica

tion/

mar

king

ofco

rrod

edar

eas.

Yel

low

7510

-00-

537-

6930

DZ

Red

7510

-00-

537-

6935

DZ

Blu

e75

10-0

1-17

7-15

27D

Z61

Bru

sh,

Plat

er’s

Han

dTy

pe(C

urve

dH

andl

eSt

yle)

A-A

-311

8,Ty

peI,

Cla

ss2

(sup

erce

des

H-B

-178

)79

20-0

0-24

4-74

31E

AA

13in

over

all

leng

thbr

ush

with

a5¼

inL

x1¼

inW

brus

har

eaha

ving

4ro

ws

of1

inL

bris

tles

used

tore

mov

elo

ose

corr

osio

npr

oduc

tsan

dfla

k-in

gpa

int

and

toap

ply

clea

ning

solv

ents

and

com

-po

unds

.62

Han

dB

rush

,W

oode

nH

andl

e,(S

tain

less

Stee

lFi

ll)

PN15

SSC

AG

EC

ode

#17

987

7920

-00-

900-

3577

EA

A7¾

inov

eral

lle

ngth

brus

hw

itha

brus

har

eaof

7/16

inus

edto

rem

ove

corr

osio

nfr

omal

umin

umal

loy

surf

aces

.63

Flas

hlig

ht,A

djus

tabl

eB

eam

,M

etal

/Pla

stic

Cas

e

TO 1-1-691

Change 1 B-19

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

Non

-Rec

harg

eabl

ePN

101-

000-

002

CA

GE

Cod

e#

0613

462

30-0

1-24

7-75

49E

AU

sefo

rco

rros

ion

insp

ectio

n.

Rec

harg

eabl

ePN

106-

000-

003

CA

GE

Cod

e#

0613

462

30-0

1-15

2-59

52E

A

64Sh

ears

and

Scis

sors

GG

G-S

-278

Stra

ight

Shea

rs(9

inL

)51

10-0

0-16

1-69

12E

AC

uttin

gta

pes,

chee

se-c

loth

,m

aski

ngm

ater

ials

,el

ec-

tric

alw

ires

,et

c.E

lect

rici

an’s

Scis

sors

(5in

Lw

/wir

est

rip

notc

hes)

5110

-00-

212-

7455

EA

65Se

para

tors

,Air

and

Wat

er,

Com

pres

sed

Air

(air

regu

lato

ras

sem

bly)

A-A

-594

36(s

uper

sede

sM

IL-

S-12

928)

Wal

l-m

ount

edse

para

tors

desi

gned

tore

mov

eoi

l,w

ater

,an

dfo

reig

npa

rtic

les

from

com

pres

sed

air,

and

tore

gula

teth

ede

liver

ypr

essu

reof

air

used

for

spra

ypa

int

guns

and

pneu

mat

icto

ols.

Cla

ss1

(1re

gula

tor,

2ou

tlets

)49

40-0

0-24

2-41

00E

AC

lass

2(2

regu

lato

rs,

4ou

t-le

ts)

4940

-00-

242-

4101

EA

66Pa

int

Bru

sh,

Flat

,M

etal

Bou

nd,

Syn-

thet

icFi

ber

H-B

-420

,Ty

peII

,G

rade

BU

sed

toap

ply

brus

habl

ese

alan

tsan

dad

hesi

ves.

1in

W80

20-0

0-26

3-38

66E

A

2in

W80

20-0

0-55

0-83

59E

A67

Mix

ers,

Liq

uid,

Re-

volv

ing

Shaf

tan

dA

gita

tor

Type

s

A-A

-594

33(s

uper

sede

s(s

u-pe

rsed

esM

IL-M

-307

0)U

sed

tom

ixtw

oco

mpo

nent

seal

ants

befo

reap

plic

a-tio

n.Ty

peI

-R

evol

ving

Shaf

t49

40-0

0-22

1-17

07E

AC

lass

1-

½hp

(115

V)

elec

tric

mot

or68

Spra

yK

it,Se

lfPr

essu

r-iz

ed(K

itco

ntai

ns4

EA

spra

yde

vice

s,20

EA

dip

tube

s,4

EA

jar

cont

aine

rsfo

rm

ater

ials

,an

d10

EA

cans

ofno

n-C

lass

1O

DS

prop

ella

nt)

SAE

AS2

2805

(sup

erse

des

MIL

-S-

2280

5)U

sefo

rap

plyi

ngpa

ints

,de

grea

sing

com

poun

ds,

pres

erva

tives

(CPC

’s),

and

othe

rto

uchu

pm

ater

i-al

sw

hen

othe

rsp

ray

appl

icat

ion

equi

pmen

tis

impr

actic

al.

Mod

el80

11Po

wer

Pak

4940

-00-

803-

6444

KT

69Ps

ychr

omet

erA

-A-2

579

Mea

sure

men

tof

rela

tive

hum

idity

and

dew

poin

tto

assi

stin

dete

rmin

atio

nof

cure

time

for

seal

ants

,ad

hesi

ves,

and

pain

ts.

Slin

g,Po

cket

Type

6685

-00-

826-

1662

EA

Psyc

hro-

Dyn

e;PN

WE

-220

14;

CA

GE

Cod

e#66

420

6685

-01-

263-

8370

EA

Safe

tyE

quip

men

t(R

efer

toFi

gure

B-1

thru

B-3

atth

een

dof

this

appe

ndix

for

illus

trat

ion

ofso

me

item

sin

this

sect

ion)

TO 1-1-691

B-20

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

NO

TE

Con

sult

loca

lSa

fety

and

Bio

envi

ronm

enta

lE

ngin

eeri

ngO

ffice

sfo

rPe

rson

alPr

otec

tive

Equ

ipm

ent

(PPE

)re

quir

emen

ts.

The

seof

fices

have

au-

thor

ityto

subs

titut

eeq

uiva

lent

safe

tyeq

uipm

ent

whe

nap

prop

riat

e.

70Pa

rtic

ulat

eR

espi

rato

r(½

Face

piec

eM

ask)

,D

ispo

sabl

eTy

pe

3MC

o.(C

AG

EC

ode

#503

78)

Pers

onne

lpr

otec

tion

from

inha

latio

nof

dust

and

part

icul

ates

duri

nglig

htsa

ndin

gan

dgr

indi

ngop

-er

atio

ns.

PN85

1142

40-0

1-24

7-23

48B

X(8

0E

A)

71Fu

llFa

cepi

ece

Res

pira

-to

r,A

irFi

lteri

ng(w

/oC

artr

idge

sor

Ret

aine

rs)

3MC

o.(C

AG

EC

ode

#50

378)

Pers

onne

lpr

otec

tion

from

inha

latio

nof

orga

nic

va-

pors

,du

st,

part

icul

ates

,an

dpa

int

spra

ysin

non-

confi

ned

area

sdu

ring

spra

ying

,sa

ndin

g,an

dgr

indi

ngop

erat

ions

.PN

7800

S-S

(Sm

all)

4240

-01-

314-

2780

EA

PN78

00S-

M(M

ediu

m)

4240

-01-

342-

5239

EA

PN78

00S-

L(L

arge

)42

40-0

1-30

1-32

00E

A72

Full

Face

piec

eR

espi

ra-

tor,

Air

Filte

ring

(w/o

Car

trid

ges

orR

etan

ers)

3MC

o.(C

AG

EC

ode

#50

378)

Pers

onne

lpr

otec

tion

from

inha

latio

nof

orga

nic

va-

pors

,du

st,

part

icul

ates

and

pain

tsp

rays

inno

n-co

nfine

dar

eas

duri

ngsp

rayi

ng,

sand

ing,

and

grin

ding

oper

atio

ns.

PN67

00(S

mal

l)42

40-0

1-45

4-85

31B

X(4

EA

)PN

6800

(Med

ium

)42

40-0

1-45

4-85

35B

X(4

EA

)PN

6900

(Lar

ge)

4240

-01-

454-

8538

BX

(4E

A)

73H

alf

Face

piec

eR

espi

-ra

tor,

Air

Filte

ring

(w/o

Car

trid

ges

orR

etai

ners

)

3MC

o.(C

AG

EC

ode

#50

378)

Pers

onne

lpr

otec

tion

from

inha

latio

nof

orga

nic

va-

pors

,du

st,

part

icul

ates

,an

dpa

int

spra

ysin

non-

confi

ned

area

sdu

ring

spra

ying

,sa

ndin

g,an

dgr

indi

ngop

erat

ions

.PN

6100

(Sm

all)

4240

-01-

342-

2852

BX

(24

EA

)PN

6200

(Med

ium

)42

40-0

1-34

2-28

53B

X(2

4E

A)

PN63

00(L

arge

)42

40-0

1-34

2-28

54B

X(2

4E

A)

74Fi

lter

Car

trid

ges

(Or-

gani

cV

apor

/P1

00Ty

pe)

3MC

o.(C

AG

EC

ode

#50

378)

For

use

with

3MC

o.ha

lfan

dfu

llfa

ce-p

iece

(600

0&

7000

Seri

es)

resp

irat

ors.

PN60

921

4240

-01-

455-

7353

BX

(60

EA

)75

Res

pira

tor

Len

sA

s-se

mbl

yfo

r3M

Co.

Full

Face

piec

eR

es-

pira

tors

(With

Plas

ticFi

lmC

over

s)

3MC

o.(C

AG

EC

ode

#50

378)

PN78

8442

40-0

1-24

7-89

29B

X(5

EA

)R

epla

cem

ent

lens

for

7800

SSe

ries

resp

irat

ors.

PN68

98O

pen

Purc

hase

BX

(5E

A)

Rep

lace

men

tle

nsfo

r60

00Se

ries

resp

irat

ors.

TO 1-1-691

B-21

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

76L

ens

Cov

ers

for

3MC

o.Fu

llFa

cepi

ece

Res

pira

tors

(Pee

l-A

way

Plas

ticFi

lm)

3MC

o.(C

AG

EC

ode

#50

378)

PN78

99-2

542

40-0

1-24

8-46

34B

X(2

5E

A)

Len

sco

vers

for

7800

SSe

ries

resp

irat

ors.

PN78

99-1

0042

40-0

1-24

8-64

35B

X(1

00E

A)

Len

sco

vers

for

7800

SSe

ries

resp

irat

ors.

PN68

8542

40-0

1-45

5-27

87B

X(1

00E

A)

Len

sco

vers

for

6800

Seri

esre

spir

ator

s.77

Inha

latio

nV

alve

for

3MC

o.Fu

llFa

ce-

piec

eR

espi

rato

rs

3MC

o.(C

AG

EC

ode

#50

378)

PN72

8242

40-0

1-24

8-26

07B

X(2

00E

A)

Rep

lace

men

tva

lves

for

7800

SSe

ries

resp

irat

ors.

PN68

9342

40-0

1-45

5-28

11B

X(2

00E

A)

Rep

lace

men

tva

lves

for

6800

Seri

esre

spir

ator

s.78

Exh

alat

ion

Val

vefo

r3M

Co.

Full

Face

-pi

ece

Res

pira

tors

3MC

o.(C

AG

EC

ode

#50

378)

PN72

8342

40-0

1-24

8-26

08B

X(5

0E

A)

Rep

lace

men

tva

lves

for

7800

SSe

ries

resp

irat

ors.

PN68

8942

40-0

1-45

5-28

09B

X(1

0E

A)

Rep

lace

men

tva

lves

or68

00Se

ries

resp

irat

ors.

79Ty

vekT

MSh

roud

for

3MC

o.Fu

llFa

ce-

piec

eR

espi

rato

rs

3MC

o.(C

AG

EC

ode

#50

378)

Use

dw

ithfu

llfa

cepi

ece

resp

irat

ors

topr

otec

tth

ehe

adan

dne

ckfr

ompa

intin

gan

d/or

abra

sive

blas

ting

over

spra

y.PN

7915

-542

40-0

1-32

0-19

57PG

(5E

A)

80Sp

ecta

cle

Kit

for

3MC

o.Fu

llFa

cepi

ece

Res

pira

tors

3MC

o.(C

AG

EC

ode

#50

378)

Con

sist

sof

fram

ean

dre

tain

ercl

ip.

PN68

7842

40-0

1-45

5-23

46E

AFo

rus

eon

6000

Seri

esfu

llfa

cepi

ece

resp

irat

ors.

PN79

2542

40-0

1-39

5-41

28E

AFo

rus

ew

ithpr

escr

iptio

nle

nses

with

7800

SSe

ries

full

face

piec

ere

spir

ator

s.81

Res

pira

tor

Cle

anin

gW

ipes

(alc

ohol

-fre

eto

wel

ette

s)

3MC

o.(C

AG

EC

ode

#’s

5037

8&

OT

1L6)

Hyg

ieni

ccl

eani

ngof

resp

irat

ors

and

othe

rpe

rson

alpr

otec

tive

gear

/equ

ipm

ent.

PN50

442

40-0

1-37

2-30

78B

X(1

00E

A)

6510

-01-

397-

4339

BX

(500

EA

)

Do

not

use

shop

air

for

brea

thin

gor

asin

let

air

for

thes

ebr

eath

able

air

pum

ps.

Itco

ntai

nsoi

l,pa

rtic

ulat

es,

and

harm

ful

gase

s.R

ead

and

follo

weq

uipm

ent

inst

ruct

ions

tode

term

ine

the

max

imum

num

ber

ofai

rlin

esto

beus

edw

itha

sing

lepu

mp.

TO 1-1-691

B-22

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

82Pu

mp/

Com

pres

sor,

Bre

atha

ble

Air

,Pn

eu-

mat

ic(A

irM

otor

)D

rive

n,Po

rtab

le

Rhi

neA

ir,

Inc.

(CA

GE

Cod

e#

5850

1)U

sed

tosu

pply

brea

thab

leai

rto

hood

san

dfu

llfa

cepi

ece

resp

irat

ors

for

abra

sive

blas

ting

and

othe

rco

rros

ion

rem

oval

oper

atio

nsas

requ

ired

and

pain

ting

oper

atio

ns.

The

sesm

all,

air

driv

en,

port

able

com

pres

sors

are

very

conv

enie

ntas

they

may

beea

sily

tran

spor

ted

and

set

upal

mos

tan

y-w

here

tosu

pply

brea

thab

leai

r.

PNN

F-11

00su

perc

edes

4240

-01-

363-

4699

EA

PNN

F15-

3B

ulla

rdC

o.(C

AG

EC

ode

#09

729

PNA

DP-

16/A

DP-

2043

10-0

1-16

8-73

02E

A

NO

TE

Use

MIL

-PR

F-32

033

oil

(NSN

9150

-00-

231-

6689

/1Q

TC

N)

orM

IL-H

-176

72hy

drau

licflu

id/1

0w

t.oi

leq

uiva

lent

(NSN

9150

-00-

985-

7231

/1Q

TC

N)

tofil

lin

-lin

eoi

ler

ofai

rm

otor

afte

rea

chus

e,as

requ

ired

,to

mai

ntai

nlu

bric

atio

nan

dpr

even

tm

otor

oxid

atio

n.

83R

epla

cem

ent

Filte

rC

artr

idge

sfo

rB

reat

habl

eA

irPu

mps

Rhi

neA

ir,

Inc.

(CA

GE

Cod

e#

5850

1R

epla

cem

ent

filte

rsfo

rus

ew

ithR

hine

Air

’sN

F-11

00an

dN

F15-

3pu

mps

.

PNC

F808

042

40-0

1-08

4-09

21B

X(1

0E

A)

84C

ompr

esse

dA

irIn

let

Hos

eA

ssem

bly,

½in

ID

Hos

ew

/3⁄8

inI

DO

rific

eFi

tting

s

Rhi

neA

ir,

Inc.

(CA

GE

Cod

e#

5850

1U

sed

only

for

supp

lyin

gfr

esh,

brea

thab

leai

rto

the

air

mot

oron

the

brea

thab

leai

rpu

mp

unit.

PNE

D13

13B

-50

(50

ftL

)42

40-0

1-25

1-81

59E

APN

ED

1313

B-1

00(1

00ft

L)

4240

-01-

251-

8160

EA

The

sein

let

hose

asse

mbl

ies

can

beus

edw

ithbo

thR

hine

Air

and

Bul

lard

units

.85

Qui

ckD

isco

nnec

tFi

t-tin

gsfo

rIn

let

Hos

eC

AG

EC

ode

#73

992

3L25

(Mal

ePl

ug)

4730

-01-

442-

1809

EA

Rep

lace

men

tfit

tings

for

the

Rhi

neA

irPN

ED

1313

Bin

let

air

hose

asse

mbl

ies.

3R25

(Fem

ale

Cou

pler

)47

30-0

1-44

2-18

08E

A86

Out

let

Man

ifol

d,Q

uick

Dis

conn

ect

(Fem

ale

Cou

pler

Ass

embl

y)

Rhi

neA

ir,

Inc.

(CA

GE

Cod

e#

5850

1)C

onne

cts

resp

irat

orai

rho

seas

sem

blie

sto

the

brea

thab

leai

rpu

mp.

Can

beus

edw

ithbo

thR

hine

Air

and

Bul

lard

units

.PN

ED

-06-

430

Ope

nPu

rcha

seE

A87

Glo

ves,

Men

’s&

Wom

en’s

(Wor

kC

ot-

ton

Flan

nel;

Nat

ural

inC

olor

)

A-A

-166

5G

ener

alpu

rpos

epr

otec

tive

wor

kgl

oves

for

hand

prot

ectio

ndu

ring

vari

ous

mai

nten

ance

oper

atio

ns.

Styl

e1

(Kni

tC

uff/

Reg

.)84

15-0

0-26

8-83

30PR

Styl

e2

(Gau

ntle

t/Reg

)84

15-0

0-63

4-50

27PR

Styl

e3

(Rev

ersi

ble

Palm

/Kni

tC

uff/

Lar

ge)

8415

-00-

559-

5613

PR

TO 1-1-691

Change 1 B-23

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

88G

love

s,C

loth

,V

inyl

Dip

ped

(Bla

ckin

Col

or)

A-A

-503

70(s

uper

sede

sM

IL-

G-8

2253

)G

ener

alpu

rpos

elig

htdu

tyty

pech

emic

alan

doi

lpr

otec

tive

glov

esus

edfo

rha

ndpr

otec

tion

duri

ngcl

eani

ngan

dch

emic

al,

solv

ent,

and

oil/p

rese

rva-

tive

appl

icat

ions

.R

ubbe

rize

dfo

rbe

tter

grip

.Ty

pe1

(Gau

ntle

t/Med

.)84

15-0

0-91

6-28

17PR

Type

1(G

aunt

let/L

arge

)84

15-0

0-91

6-28

18PR

Type

2(

Kni

tW

rist

/Uni

vers

alon

e-si

zefit

sal

l)84

15-0

0-93

5-28

33PR

89G

love

s,To

xico

logi

cal

Age

nts,

Prot

ectiv

e(B

lack

inC

olor

)

MIL

-G-1

2223

Type

II(1

4in

Gau

ntle

t)H

eavy

duty

indu

stri

algr

ade

synt

hetic

rubb

ergl

oves

used

for

hand

prot

ectio

nw

hile

hand

ling

solv

ents

,ch

emic

alpa

int

rem

over

s,pa

ints

,se

alan

ts,

orot

her

mat

eria

lsw

hich

may

bein

juri

ous

toth

esk

in.

X-S

mal

l(8

)84

15-0

0-75

3-65

50PR

Smal

l(9

)84

15-0

0-75

3-65

51PR

NO

TE

The

segl

oves

are

not

desi

gned

for

prot

ec-

tion

inel

ectr

ical

appl

icat

ions

orch

emic

alw

arfa

reac

tiviti

es.

Med

ium

(10)

8415

-00-

753-

6552

PR

Lar

ge(1

1)84

15-0

0-75

3-65

53PR

X-L

arge

(12)

8415

-00-

753-

6554

PR

90G

love

s,C

hem

ical

and

Oil

Prot

ectiv

e(G

reen

inC

olor

)

MIL

-G-8

7066

(Gau

ntle

tC

uff;

Floc

kL

inin

g)Sy

nthe

ticru

bber

glov

esw

itha

high

degr

eeof

abra

-si

onre

sist

ance

and

resi

stan

ceto

chem

ical

ssu

chas

wat

er,

gaso

line,

oils

,al

kalis

,an

dac

ids.

The

yar

eus

edto

prot

ect

the

hand

sdu

ring

airc

raft

,m

is-

sile

and

equi

pmen

tw

ashi

ngop

erat

ions

.

XX

-Sm

all

(7)

8415

-01-

147-

6263

PRX

-Sm

all

(8)

8415

-01-

147-

9540

PRSm

all

(9)

8415

-01-

012-

9294

PRM

ediu

m(1

0)84

15-0

1-01

3-73

82PR

Lar

ge(1

1)84

15-0

1-01

3-73

84PR

91G

love

s,D

ispo

sabl

e,N

itrile

Rub

ber,

Pre-

Pow

der-

ed,A

mbi

-de

xtro

us(L

ight

Blu

ein

Col

or)

CA

GE

Cod

e#’

s62

538

&4X

954

Gen

eral

purp

ose

prot

ectiv

ew

ear

for

the

hand

sdu

r-in

gva

riou

scl

eani

ngan

dco

rros

ion

trea

tmen

top

-er

atio

ns.

The

segl

oves

are

heav

ier

duty

and

have

bette

rre

sist

ance

toso

me

chem

ical

sth

anth

ela

tex

rubb

ergl

oves

(Ite

m#9

2).

PN70

05S

(Sm

all)

8415

-01-

352-

6556

PG(2

0B

X/

100

EA

)PN

7005

M(M

ediu

m)

8415

-01-

352-

6553

PG(2

0B

X/

100

EA

)PN

7005

L(L

arge

)84

15-0

1-35

2-65

54PG

(20

BX

/10

0E

A)

PN70

05X

L(X

-Lar

ge)

8415

-01-

352-

6555

PG(2

0B

X/

100

EA

)

TO 1-1-691

B-24

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

92G

love

s,D

ispo

sabl

e,L

atex

Rub

ber,

Pre-

Pow

dere

d,A

mbi

dex-

trou

s(N

atur

alin

Col

or)

A-A

-535

13G

ener

alpu

rpos

epr

otec

tive

wea

rfo

rth

eha

nds

dur-

ing

vari

ous

clea

ning

and

corr

osio

ntr

eatm

ent

op-

erat

ions

.T

hese

glov

esar

elig

hter

duty

and

have

som

ewha

tle

ssre

sist

ance

toso

me

chem

ical

sth

anth

eni

trile

rubb

ergl

oves

(Ite

m#9

1).

Smal

l65

15-0

1-36

5-61

83PG

(100

EA

)

Med

ium

6515

-01-

364-

8553

PG(1

00E

A)

Lar

ge65

15-0

1-36

4-85

54PG

(100

EA

)

93C

over

alls

,C

otto

n,H

ook-

Pile

Fast

ener

Tape

(Gre

enin

Col

or)

MIL

-C-2

202

Type

I(O

live

Gre

en)

Prot

ectiv

ecl

othi

ngfo

rco

rros

ion

mai

nten

ance

and

insp

ectio

npe

rson

nel.

Des

igne

dpr

imar

ilyfo

rw

ear

over

regu

lar/

stre

etcl

othi

ng.

Smal

l(4

2)84

05-0

0-13

1-65

07E

AM

ediu

m(4

6)84

05-0

0-13

1-65

08E

AL

arge

(50)

8405

-00-

131-

6509

EA

X-L

arge

(54)

8405

-00-

131-

6510

EA

XX

-Lar

ge(5

8)84

05-0

0-13

1-65

11E

A94

Cov

eral

ls,

Dis

posa

ble,

Gen

eral

Purp

ose

(Whi

tein

Col

or)

A-A

-503

58Pr

otec

tive

clot

hing

for

corr

osio

nm

aint

enan

cepe

r-so

nnel

topr

otec

tag

ains

tdi

rt,

grea

se,

pain

t,an

dlo

w-h

azar

dco

ntam

inan

ts.

The

yar

eon

e-pi

ece,

fron

top

enin

g(s

lide

type

clos

ure)

cove

ralls

mad

eof

fire

resi

stan

tan

dw

ater

repe

llent

mat

eria

ls,

and

they

are

inte

nded

tobe

thro

wn

away

whe

ndi

rty.

X-S

mal

l84

15-0

0-60

1-07

92E

ASm

all

8415

-00-

601-

0793

EA

Med

ium

8415

-00-

601-

0794

EA

Lar

ge84

15-0

0-60

1-07

97E

AX

-Lar

ge84

15-0

0-60

1-08

01E

AX

X-L

arge

8415

-00-

601-

0802

EA

95C

over

alls

,D

ispo

sabl

e(W

hite

inC

olor

)A

-A-5

5196

(sup

erse

des

MIL

-C

-870

69)

Prot

ectiv

eol

efin

cove

ralls

with

anat

tach

edho

odha

ving

adr

awst

ring

clos

ure

and

atta

ched

boot

ies

for

mai

nten

ance

pers

onne

lpe

rfor

min

gw

ork

arou

ndas

best

osm

ater

ials

orw

ithfib

ergl

ass

and

othe

rco

mpo

site

mat

eria

ls.

The

yar

ein

tend

edto

beth

row

naw

ayaf

ter

use.

Type

I(W

ithH

ood)

Smal

l/Med

ium

8415

-01-

445-

6565

EA

Lar

ge/X

-Lar

ge84

15-0

1-44

5-65

68E

AX

X-L

arge

8415

-01-

445-

6588

EA

96T

rous

ers,

Wet

Wea

ther

(Gre

enin

Col

or)

MIL

-T-8

7099

(sup

erse

des

MIL

-O-2

2776

)W

ater

proo

fcl

orop

rene

rubb

erco

ated

nylo

ntw

illtr

ouse

rsfo

rus

ein

conj

unct

ion

with

aw

etw

eath

erpa

rka

(Ite

m#

97)

for

airc

raft

,m

issi

le,

and

equi

p-m

ent

mai

nten

ance

oper

atio

nsfo

rpe

rson

nel

pro-

tect

tion

inw

etor

wet

/col

dco

nditi

ons.

XX

-Sm

all

8405

-01-

276-

1532

PRX

-Sm

all

8405

-01-

276-

1533

PRSm

all

8405

-01-

276-

1534

PRM

ediu

m84

05-0

1-27

6-15

35PR

Lar

ge84

05-0

1-27

6-15

36PR

X-L

arge

8405

-01-

276-

1537

PR

TO 1-1-691

B-25

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

97Pa

rka,

Wet

Wea

ther

(Gre

enin

Col

or)

MIL

-P-8

7098

(sup

erse

des

MIL

-P-8

2277

)W

ater

proo

fcl

orop

rene

rubb

erco

ated

nylo

ntw

illpa

rka

for

use

inco

njun

ctio

nw

ithw

etw

eath

ertr

ouse

rs(I

tem

#96

)fo

rai

rcra

ft,

mis

sile

,an

deq

uipm

ent

mai

nten

ance

oper

atio

nsfo

rpe

rson

nel

prot

ectio

nin

wet

orw

et/c

old

cond

ition

s.

XX

-Sm

all

8405

-01-

276-

4187

EA

X-S

mal

l84

05-0

1-27

6-41

88E

ASm

all

8405

-01-

276-

4189

EA

Med

ium

8405

-01-

276-

4190

EA

Lar

ge84

05-0

1-27

6-41

91E

AX

-Lar

ge84

05-0

1-27

6-41

92E

A98

Park

aan

dT

rous

ers,

Wet

Wea

ther

(Woo

d-la

ndC

amou

flage

Patte

rn)

MIL

-P-4

3907

Cla

ss2

(Wdl

dC

amPa

t)W

ater

proo

fpo

lyur

etha

neco

ated

nylo

ntw

illpa

rka

(with

hood

)an

dtr

ouse

rsfo

rus

eov

erou

ter

gar-

men

ts(h

otor

cold

wea

ther

)du

ring

airc

raft

,m

is-

sile

,an

deq

uipm

ent

mai

nten

ance

oper

atio

nsfo

rpe

rson

nel

prot

ectio

nin

wet

orw

et/c

old

cond

ition

sw

hen

cam

oufla

gepa

ttern

clot

hing

isre

quir

ed.

Park

aX

X-S

mal

l84

05-0

1-05

3-92

02E

AX

-Sm

all

8405

-00-

001-

1547

EA

Smal

l84

05-0

0-00

1-15

48E

AM

ediu

m84

05-0

0-00

1-15

49E

AL

arge

8405

-00-

001-

1550

EA

X-L

arge

8405

-00-

001-

1551

EA

Tro

user

sX

X-S

mal

l84

05-0

1-05

3-94

00PR

X-S

mal

l84

05-0

0-00

1-80

25PR

Smal

l84

05-0

0-00

1-80

26PR

Med

ium

8405

-00-

001-

8027

PRL

arge

8405

-00-

001-

8028

PRX

-Lar

ge84

05-0

0-00

1-80

29PR

99Ja

cket

,E

xtre

me

Col

dW

eath

er,

Impe

rme-

able

(Gre

enin

Col

or)

MIL

-J-8

2299

Prot

ectiv

eou

terw

ear

for

airc

raft

,m

issi

le,

and

equi

p-m

ent

mai

nten

ance

oper

atio

nsat

tem

pera

ture

sbe

-lo

w+

14°

F(-

10°

C).

Use

din

conj

unct

ion

with

extr

eme

cold

wea

ther

trou

sers

(Ite

m#

100)

and

aho

od.

Smal

l84

15-0

0-34

9-93

13E

AX

-Lar

ge84

15-0

0-34

9-93

16E

A

TO 1-1-691

B-26

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

100

Tro

user

s,E

xtre

me

Col

dW

eath

er,

Impe

rme-

able

(Gre

enin

Col

or)

MIL

-T-2

1705

Prot

ectiv

eou

terw

ear

for

airc

raft

,m

issi

le,

and

equi

p-m

ent

mai

nten

ance

oper

atio

nsat

tem

pera

ture

sbe

-lo

w+

14°

F(-

10°

C).

Use

din

conj

unct

ion

with

anex

trem

eco

ldw

eath

erja

cket

(Ite

m#

99)

and

aho

od.

Smal

l(S

ize

27to

30)

8415

-00-

575-

1225

EA

X-L

arge

(Siz

e39

to42

)84

15-0

0-57

5-12

46E

AX

X-L

arge

(Siz

e43

to46

)84

15-0

0-57

5-12

47E

A10

1Pa

ds,

Kne

e,In

dust

rial

PN31

861

4240

-00-

595-

3861

PRK

nee

prot

ectio

ndu

ring

mai

nten

ance

oper

atio

ns.

Mad

eof

hard

rubb

erw

itha

spon

geru

bber

liner

and

atta

ched

with

two

adju

stab

lew

ebst

raps

with

reta

inin

gbu

ckle

s.

(CA

GE

Cod

e#

5579

9)PN

5402

T13

Sam

e(C

AG

EC

ode

#39

428)

PN71

H17

18Sa

me

(CA

GE

Cod

e#

5380

0)

TO 1-1-691

B-27

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

102

Fire

men

’sB

oots

,(B

lack

inC

olor

)A

-A-5

0371

Prot

ectiv

eou

ter

foot

wea

rfo

rai

rcra

ftm

aint

enan

ceop

erat

ions

such

asai

rcra

ft,

mis

sile

,an

deq

uipm

ent

was

hing

.Ty

peII

(Kne

eL

engt

h-13

½in

Hig

h)Si

ze5

8430

-00-

753-

5935

PRSi

ze6

8430

-00-

753-

5936

PRSi

ze7

8430

-00-

753-

5937

PRSi

ze8

8430

-00-

753-

5938

PRSi

ze9

8430

-00-

753-

5939

PRSi

ze10

8430

-00-

753-

5940

PRSi

ze11

8430

-00-

753-

5941

PRSi

ze12

8430

-00-

753-

5942

PRSi

ze13

8430

-00-

753-

5943

PRSi

ze14

8430

-00-

753-

5944

PRSi

ze15

8430

-00-

753-

5945

PRTy

peI

(¾L

engt

h-29

inH

igh)

Size

584

30-0

0-75

3-61

05PR

Size

684

30-0

0-14

7-10

32PR

Size

784

30-0

0-14

7-10

33PR

Size

884

30-0

0-14

7-10

34PR

Size

984

30-0

0-14

7-10

35PR

Size

1084

30-0

0-14

7-10

36PR

Size

1184

30-0

0-29

9-03

42PR

Size

1284

30-0

0-14

7-10

38PR

Size

1384

30-0

0-08

2-54

90PR

Size

1484

30-0

0-08

2-54

91PR

Size

1584

30-0

0-08

2-54

92PR

103

Foot

wea

rC

over

s,A

ir-

craf

tW

ashd

own

(Cha

rcoa

lG

ray

inC

olor

)

PNM

(CA

GE

Cod

e#

2922

3)W

ater

repe

llant

cove

rsw

orn

over

boot

sto

incr

ease

trac

tion

and

prev

ent

mak

ing

boot

mar

kson

air-

craf

tsu

rfac

esw

hen

wal

king

onth

emdu

ring

mai

nten

ance

and

was

hing

oper

atio

ns.

Med

ium

8430

-00-

911-

2458

PRL

arge

8430

-00-

911-

2459

PRX

-Lar

ge84

30-0

0-91

1-37

71PR

TO 1-1-691

B-28

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

104

Foot

wea

rC

over

,C

hem

ical

Prot

ectiv

e(O

verb

oots

Bla

ckin

Col

or)

MIL

-F-4

3987

Ove

rboo

tsfo

rfo

otw

ear

(sho

esan

dbo

ots)

used

topr

otec

tth

emfr

omch

emic

alat

tack

duri

ngm

aint

e-na

nce

oper

atio

nsw

hich

requ

ire

use

ofch

emic

als.

The

yar

eac

id,

fuel

,oi

l,an

dfir

ere

sist

ant.

The

smal

lsi

zeis

for

use

over

size

s3

to7½

com

bat

boot

s,an

dth

ela

rge

size

isfo

rus

eov

ersi

zes

8to

14co

mba

tbo

ots.

Smal

l84

30-0

1-11

8-87

12PR

Lar

ge84

30-0

1-02

1-59

78PR

105

Ove

rsho

es,

Men

’sR

ub-

ber,

5B

uckl

eTy

pe(B

lack

inC

olor

)

A-A

-503

62(s

uper

sede

sM

IL-

O-8

36)

Med

ium

wei

ght

over

shoe

sto

prot

ect

regu

lar

foot

-w

ear

from

wat

eran

dot

her

liqui

dsdu

ring

mai

nte-

nanc

eop

erat

ions

orou

tsid

eac

tiviti

esdu

ring

in-

clem

ent

wea

ther

cond

ition

s.Si

ze5

8430

-00-

144-

1672

PRSi

ze6

8430

-00-

144-

1673

PRSi

ze7

8430

-00-

144-

1674

PRSi

ze8

8430

-00-

144-

1643

PRSi

ze9

8430

-00-

144-

1644

PRSi

ze10

8430

-00-

144-

1645

PRSi

ze11

8430

-00-

144-

1646

PRSi

ze12

8430

-00-

144-

1647

PRSi

ze13

8430

-00-

144-

1648

PRSi

ze14

8430

-00-

144-

1649

PRSi

ze15

8430

-00-

144-

1682

PR10

6A

pron

,U

tility

(Lab

ora-

tory

Bla

ckin

Col

or)

A-A

-310

4(s

uper

sede

sZ

Z-A

-60

5)(4

5in

Lx

35in

W)

8415

-00-

634-

5023

EA

Afu

llle

ngth

chlo

ropr

ene

rubb

er(a

cid

resi

stan

t)pr

o-te

ctiv

eap

ron

used

topr

otec

tco

rros

ion

mai

nte-

nanc

epe

rson

nel

and

thei

rcl

othi

ngag

ains

tch

emi-

cal

spla

shes

whe

nha

ndlin

gch

emic

als.

107

Face

Shie

ld,

Indu

stri

al,

(Adj

usta

ble

Stra

p,C

lear

lens

)

AN

SIZ

87.1

(sup

erse

des

L-F

-36

)(9

inL

x18

inW

Plas

-tic

Win

dow

/L

ens)

4240

-00-

542-

2048

EA

Use

dto

prov

ide

eye

and

face

prot

ectio

nw

hen

cut-

ting,

grin

ding

,or

chip

ping

met

alor

whe

nha

n-dl

ing

haza

rdou

sch

emic

als.

NO

TE

Face

shie

ldis

not

for

prim

ary

prot

ectio

nan

dsh

ould

alw

ays

beus

edw

ithgo

ggle

s.

108

Gog

gles

,In

dust

rial

,Pl

astic

AN

SIZ

87.1

(sup

erse

des

A-A

-11

10)

Stan

dard

Safe

tyG

oggl

es

TO 1-1-691

B-29

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

(adj

usta

ble

head

band

,si

ngle

clea

rpo

lyca

r-bo

nate

plas

ticle

ns,

vent

edcl

ear

plas

ticfr

ame)

4240

-00-

052-

3776

PRTo

prov

ide

eye

prot

ectio

nfr

omfly

ing

part

icle

sin

indu

stri

alen

viro

nmen

ts.

Can

bew

orn

over

eye-

glas

ses.

Gog

gles

are

vent

ilate

dto

redu

cefo

ggin

g.

Spla

sh-P

roof

Gog

gles

(adj

usta

ble

head

band

,si

ngle

gree

npo

lyca

r-bo

nate

plas

ticle

ns,

light

-gre

enpl

astic

fram

ew

ithin

dire

ctve

ntin

g)

4240

-01-

082-

8928

PRTo

prot

ect

eyes

from

chem

ical

spla

shes

,im

pact

s,an

dsp

arks

.C

anbe

wor

nov

erey

egla

sses

.V

enti-

late

dfo

rco

mfo

rtan

dto

prov

ide

airfl

owto

min

i-m

ize

lens

fogg

ing.

109

Gog

gles

,C

hem

ical

Spla

shPr

oof

Type

(adj

usta

ble

head

band

,do

uble

clea

rgl

ass

lens

,un

vent

edcl

ear

plas

ticfr

ame

with

rubb

erfa

cepa

ds)

AN

SIZ

87.1

Com

mer

cial

Item

sC

omm

only

know

nas

“Nod

and

Shak

e”go

ggle

s,th

eyar

epa

rtic

ular

lyus

eful

for

eye

prot

ectio

ndu

r-in

gai

rcra

ft,

mis

sile

,an

deq

uipm

ent

was

hing

op-

erat

ions

.T

hey

also

prov

ide

exce

llent

eye

prot

ec-

tion

duri

ngch

emic

alco

rros

ion

rem

oval

and

met

alsu

rfac

etr

eatm

ent

oper

atio

ns.

PNA

883F

Ope

nPu

rcha

sePR

(CA

GE

Cod

e#

6M64

4)

PN55

1O

pen

Purc

hase

PR

(CA

GE

Cod

e#

1602

9)

110

Plug

,E

arD

ispo

sabl

e,(Y

ello

win

Col

or)

PN4-

375

(CA

GE

Cod

e#’

s89

875

&U

3216

)65

15-0

0-13

7-63

45B

X(4

00E

A)

(200

EA

wra

pped

pair

s)

Com

pres

sibl

evi

nyl

foam

mat

eria

lth

atex

pand

sto

fitth

eea

rca

nal

and

prov

ide

am

oder

ate

degr

eeof

hear

ing

prot

ectio

nin

high

nois

ein

dust

rial

envi

-ro

nmen

ts.

111

Prot

ecto

r,H

eari

ng(H

ead-

phon

eci

rcua

u-ra

l/ear

muf

fst

yle,

com

esw

ithex

tra

set

ofse

als)

A-A

-580

8442

40-0

0-02

2-29

46E

AFi

tsse

cure

lyov

erth

eea

rsto

prov

ide

ahi

ghde

gree

ofhe

arin

gpr

otec

tion

tohe

lppr

even

the

arin

glo

ssor

dam

age

inlo

udw

ork

area

s.

112

Aur

alPr

otec

tor,

Soun

dSA

EA

S23

899

(sup

erse

des

MIL

-A-2

3389

)Fi

tsse

cure

lyov

erth

eea

rsto

prov

ide

ahi

ghde

gree

ofhe

arin

gpr

otec

tion

tohe

lppr

even

the

arin

glo

ssor

dam

age

inlo

udw

ork

area

s.E

arm

uff

asse

mbl

y42

40-0

0-75

9-32

90E

AR

epla

cem

ent

Seal

s42

40-0

0-97

9-40

40PR

Seal

antA

pplic

atio

nE

quip

men

t(T

ools

)11

3Se

alan

tD

ispe

nsin

gG

unw

ith2.

5O

zM

etal

Ret

aine

r(M

anua

lTy

pe)

CA

GE

Cod

e#

9210

8A

pplic

atio

nof

seal

ants

and

adhe

sive

s.

PN22

1824

(Sem

co®

Mod

el#

850-

2.5M

)51

20-0

1-13

5-83

44E

A

TO 1-1-691

B-30

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

114

Seal

ant

Dis

pens

ing

Gun

with

6O

zM

etal

Ret

aine

r(M

anua

lTy

pe)

CA

GE

Cod

e#

9210

8A

pplic

atio

nof

seal

ants

and

adhe

sive

s.

PN22

1830

(Sem

co®

Mod

el#

850-

6M)

5120

-00-

952-

3507

EA

115

Seal

ant

Dis

pens

ing

Gun

with

12O

zM

etal

Ret

aine

r(M

anua

lTy

pe)

CA

GE

Cod

e#

9210

8A

pplic

atio

nof

seal

ants

and

adhe

sive

s.

PN22

1836

(Sem

co®

Mod

el#

850-

12M

)51

20-0

1-37

3-38

05E

A

116

Seal

ant

Dis

pens

ing

Gun

with

2.5

Oz

Met

alR

etai

ner

(Pne

umat

icTy

pe)

CA

GE

Cod

e#

9210

8A

pplic

atio

nof

seal

ants

and

adhe

sive

s.G

unha

ndle

isre

mov

able

toal

low

for

easi

erac

cess

inco

n-fin

edar

eas.

Ref

erto

Figu

re6-

1.PN

2502

55(S

emco

®M

odel

#25

0A-2

½)

5130

-00-

323-

2287

EA

117

Seal

ant

Dis

pens

ing

Gun

with

6O

zM

etal

Ret

aine

r(P

neum

atic

Type

)

CA

GE

Cod

e#

9210

8A

pplic

atio

nof

seal

ants

and

adhe

sive

s.G

unha

ndle

isre

mov

able

toal

low

for

easi

erac

cess

inco

n-fin

edar

eas.

Ref

erto

Figu

re6-

1.PN

2500

65(S

emco

®M

odel

#25

0A-6

)51

30-0

0-92

4-63

96E

A

118

Seal

ant

Dis

pens

ing

Gun

with

12O

zM

etal

Ret

aine

r(P

neum

atic

Type

)

CA

GE

Cod

e#

9210

8A

pplic

atio

nof

seal

ants

and

adhe

sive

s.G

unha

ndle

isre

mov

able

toal

low

for

easi

erac

cess

inco

n-fin

edar

eas.

Ref

erto

Figu

re6-

1.

PN25

0125

(Sem

co®

Mod

el#

250A

-12)

Ope

nPu

rcha

seE

A

119

Rep

air

Kit

for

Seal

ant

Dis

pens

ing

Gun

(Pne

umat

icTy

pe)

CA

GE

Cod

e#

9210

8V

alve

repa

irki

tfo

rSe

mco

®M

odel

#25

0-A

seal

ant

disp

ensi

nggu

ns.

PN24

0020

Ope

nPu

rcha

seK

T

120

Rep

lace

men

tC

artr

idge

Ret

aine

rsfo

rSe

mco

®M

odel

#85

0M

anua

lSe

alan

tD

ispe

nsin

gG

uns

CA

GE

Cod

e#

9210

8Se

mco

®M

odel

#85

0R

e-ta

iner

sPN

2268

1951

20-0

1-24

7-16

39E

AR

epla

cem

ent

met

alre

tain

er;

2.5

Oz

guns

.PN

2268

2053

40-0

1-38

4-61

20E

AR

epla

cem

ent

met

alre

tain

er;

6O

zgu

ns.

PN22

6822

Ope

nPu

rcha

seE

AR

epla

cem

ent

met

alre

tain

er;

12O

zgu

ns.

121

Rep

lace

men

tC

artr

idge

Ret

aine

rsfo

rSe

mco

®M

odel

#25

0APn

eum

atic

Seal

ant

Dis

pens

ing

Gun

s

CA

GE

Cod

e#

9210

8Se

mco

®M

odel

#25

0AR

etai

ners

TO 1-1-691

B-31

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

PN22

0256

5120

-00-

693-

8069

EA

Rep

lace

men

tm

etal

reta

iner

;2.

5O

zgu

ns.

PN22

0928

5120

-00-

693-

8070

EA

Rep

lace

men

tm

etal

reta

iner

;6

Oz

guns

.PN

2209

2351

20-0

0-69

3-80

71E

AR

epla

cem

ent

met

alre

tain

er;

12O

zgu

ns.

122

Hos

eA

ssem

blie

sfo

rSe

mco

®M

odel

#25

0APn

eum

atic

Seal

ant

Dis

pens

ing

Gun

s

CA

GE

Cod

e#

9210

8R

epla

cem

ent

hose

asse

mbl

ies

and

fittin

gsfo

rSe

mco

®M

odel

#25

0-A

pneu

mat

icse

alan

tdi

s-pe

nsin

ggu

ns.A

llho

seas

sem

blie

sco

me

with

aB

-nut

fittin

gan

da

quic

kdi

scon

nect

atta

chm

ent

Hos

eA

ssem

bly

with

Han

sen

Con

nect

orA

ssy.

(5ft

L)

PN28

0000

Ope

nPu

rcha

seE

A(1

0ft

L)

PN28

0001

4720

-00-

956-

5313

EA

(15

ftL

)PN

2800

02O

pen

Purc

hase

EA

(20

ftL

)PN

2800

0347

20-0

1-32

9-86

02E

A(2

5ft

L)

PN28

0004

4720

-00-

080-

5159

EA

(30

ftL

)PN

2800

05O

pen

Purc

hase

EA

Han

son

Con

nect

orA

ssy.

PN22

9186

Ope

nPu

rcha

seE

AB

-Nut

Ass

y.(G

unE

nd)

PN22

9189

4730

-01-

267-

5307

EA

123

Wre

nch

for

Sem

co®

Mod

el#

250-

APn

eum

atic

Seal

ant

Dis

pens

ing

Gun

s

CA

GE

Cod

e#

9210

8Se

rvic

ew

renc

hfo

rad

just

ing

Sem

co®

Mod

el#

250-

Apn

eum

atic

seal

ant

disp

ensi

nggu

ns.

PN24

0018

5120

-00-

996-

1565

EA

TO 1-1-691

B-32

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

124

Sem

co®

Dis

posa

ble

Plas

ticC

artr

idge

s,Pl

unge

rs,

Seal

s,an

dC

aps

for

Man

ual

and

Pneu

mat

icSe

alan

tD

ispe

nsin

gG

uns

CA

GE

Cod

e#

9210

8C

artr

idge

s(H

DPo

lyet

hyle

ne)

Em

pty

cart

ridg

esfo

rfil

ling

with

and

disp

ensi

ngof

two-

part

seal

ants

usin

gth

eSe

mco

®M

odel

#’s

250-

Aan

d85

0se

alan

tdi

spen

sing

guns

.PN

2203

16(2

.5O

z)51

20-0

0-69

4-90

82E

APN

2203

17(6

Oz)

5120

-00-

673-

1886

EA

PN22

0318

(12

Oz)

5120

-01-

454-

4210

EA

Wip

erPl

unge

rsU

sed

toas

sure

com

plet

edi

spen

sing

ofse

alan

tsan

del

imin

atio

nof

was

tean

d/or

leak

age

from

the

back

end

ofth

eca

rtri

dge.

Fits

eith

er2.

5O

z,6

Oz

,or

12O

zca

rtri

dges

.

(LD

Poly

ethy

lene

)PN

2202

5951

20-0

0-27

6-94

22E

AW

P(W

iper

Plun

ger)

Thr

eade

dC

apU

sed

tosc

rew

into

and

cap

the

neck

orfr

ont

end

ofth

eca

rtri

dge

topr

even

tle

akag

e.Fi

tsei

ther

2.5

Oz,

6O

z,

or12

Oz

cart

ridg

es.

PN23

4411

5365

-01-

107-

7863

EA

TC

-Sea

lC

apFl

ange

Cap

Use

dto

snap

onto

the

back

end

ofth

eca

rtri

dge

topr

even

tco

ntam

inat

ion

ofth

ese

alan

t.Fi

tsei

ther

2.5

Oz,

6O

z,

or12

Oz

cart

ridg

es.

PN22

0238

8125

-00-

410-

8501

EA

F-Fl

ange

(Sna

pO

n)C

ap12

5M

echa

nica

lB

eam

Ana

-ly

tical

Bal

ance

(Oha

usD

ial-

O-G

ram

Bal

ance

)

CA

GE

Cod

e#

8597

3(O

haus

Cor

p.)

Use

for

wei

ghin

gou

tth

epr

oper

ratio

ofba

sean

dac

cele

rato

rco

mpo

unds

topr

epar

ean

dm

ixtw

oco

mpo

nent

seal

ants

.PN

1650

6670

-00-

957-

3781

EA

TO 1-1-691

B-33

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

126

Sem

co®

Seal

ant

Smoo

thin

gTo

ols

(Fib

ergl

ass

Rei

n-fo

rced

Plas

tic)

CA

GE

Cod

e#

9210

8Sp

atul

asan

dsp

read

ers

for

tool

ing

and

smoo

thin

gse

alan

tsan

dad

hesi

ves.

For

addi

tiona

lin

form

atio

nre

fer

toFi

gure

6-5.

Seal

ant

Spat

ulas

PN23

1349

5120

-01-

337-

9415

EA

9½in

L;

roun

ded

ends

-9/

16in

D&

¼in

DPN

2262

4151

20-0

1-29

7-70

15E

A7¼

inL

;sq

end-

3/16

inW

&rd

.en

d-3⁄8

inD

PN22

6242

5120

-01-

297-

7016

EA

7¼in

L;

sqen

d-9/

32in

W&

rd.

end

1⁄8

inD

PN22

6243

5120

-01-

297-

7017

EA

7¼in

L;

sqen

ds-

3⁄8

inW

&15

/32

inW

Spat

ula

Kit

The

kit

incl

udes

spat

ulas

PN’s

2262

41,

2262

42,

and

2262

43sp

atul

as.

PN22

6244

5120

-00-

056-

3237

KT

Seal

ant

Scra

per

Use

dfo

rei

ther

spre

adin

gor

rem

oval

ofse

alan

tfr

omal

lsu

rfac

es(5

13/1

6in

L;

one

sqen

d-¾

inW

).PN

2343

5051

20-0

1-29

8-61

21E

A

Seal

ant

Spre

ader

Use

dfo

rsp

read

ing

seal

ants

orad

hesi

ves

onto

flat

surf

aces

,in

part

icul

aron

ala

rge

area

(4in

Lx

23/

16in

W).

PN22

9394

5120

-01-

337-

9416

EA

Com

bSp

read

erU

sed

tosp

read

seal

ants

orad

hesi

ves

whi

lem

ain-

tain

ing

aun

ifor

mth

ickn

ess

and

agr

oove

dpa

ttern

(3in

Lx

3in

Ww

ithsa

wto

oth

edge

s).

PN22

9395

Ope

nPu

rcha

seE

A

127

Plas

ticN

ozzl

es,

Dis

-po

sabl

e(¼

inor

½in

NPT

mal

eth

read

eden

d)

CA

GE

Cod

e#

9210

8(S

emco

®M

odel

#’s)

Noz

zles

used

for

disp

ensi

ngse

alan

tsw

hen

atta

ched

toSe

mco

®ca

rtri

dges

(Ite

m#

124)

.R

efer

toFi

g-ur

e6-

2fo

rno

zzle

shap

esto

dete

rmin

eth

eap

pro-

pria

teM

odel

#fo

rth

ejo

b.St

anda

rdN

ozzl

esA

pply

ing

seal

ant

inbu

ttse

amga

ps.

No.

252

(PN

2205

38)

5120

-00-

167-

0150

EA

St2½

inL

with

1/16

inor

ifice

.N

o.25

4(P

N22

0540

)51

20-0

0-67

3-18

85E

ASt

2½in

Lw

ith1⁄8

inor

ifice

.N

o.25

5(P

N23

3495

)O

pen

Purc

hase

EA

St2½

inL

with

noor

ifice

(cut

tosu

it).

No.

410

(PN

2205

42)

5120

-00-

801-

0949

EA

St4

inL

with

1/32

inor

ifice

.N

o.41

0(P

N22

0543

)51

20-0

0-05

5-40

63E

A45

°an

gle

with

1/32

inor

ifice

.N

o.41

5(P

N22

7613

)51

20-0

1-38

6-44

80E

ASt

4in

Lw

ithno

orifi

ce(c

utto

suit)

.N

o.42

0(P

N22

0544

)51

20-0

0-04

2-65

77E

ASt

4in

Lw

ith1/

16in

orifi

ce.

No.

430

(PN

2205

48)

5120

-00-

967-

8151

EA

St4

inL

with

3/32

inor

ifice

.N

o.43

0(P

N22

0549

)51

20-0

0-05

5-40

62E

A45

°an

gle

with

3/32

inor

ifice

.N

o.44

0(P

N22

0550

)51

20-0

0-77

3-37

91E

ASt

4in

Lw

ith1⁄8

inor

ifice

.N

o.62

0(P

N22

0553

)51

20-0

0-16

7-01

52E

ASt

6in

Lw

ith1/

16in

orifi

ce.

No.

620

(PN

2205

54)

5120

-00-

966-

5373

EA

45°

angl

ew

ith1/

16in

orifi

ce.

TO 1-1-691

B-34 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

127 C

ont.

No.

640

(PN

2205

55)

5120

-00-

822-

7194

EA

St6

inL

with

1⁄8

inor

ifice

.

No.

640

(PN

2205

56)

5120

-00-

167-

0153

EA

30°

angl

ew

ith1⁄8

inor

ifice

.N

o.64

0(P

N22

0551

)51

20-0

0-67

0-11

86E

A45

°an

gle

with

1⁄8

inor

ifice

.N

o.65

0(P

N22

4494

)O

pen

Purc

hase

EA

St6

inL

with

1⁄8

inor

ifice

.N

o.82

0(P

N22

0557

)51

20-0

0-96

6-82

70E

ASt

8in

Lw

ith1/

16in

orifi

ce.

No.

820

(PN

2205

58)

5120

-00-

966-

5371

EA

45°

angl

ew

ith1/

16in

orifi

ce.

No.

840

(PN

2205

59)

5120

-00-

966-

5372

EA

St8

inL

with

1⁄8

inor

ifice

.N

o.84

0(P

N22

0560

)51

20-0

0-96

6-53

82E

A45

°an

gle

with

1⁄8

inor

ifice

.N

o.86

90(P

N22

0606

)51

20-0

0-96

6-82

43E

A9

inve

ntdu

ckno

zzle

with

3/32

inor

ifice

.N

o.10

02(P

N22

0561

)51

20-0

0-05

5-40

55E

ASt

10in

Lw

ith1/

16in

orifi

ce.

No.

1004

(PN

2205

63)

5120

-00-

055-

4054

EA

St10

inL

with

1⁄8

inor

ifice

.N

o.10

10(P

N22

0565

)51

20-0

0-05

5-40

58E

ASt

10in

Lw

ith5/

16in

orifi

ce.

Fille

tN

ozzl

esA

pply

ing

seal

ant

fille

tsov

erla

pjo

ints

.N

o.42

5(P

N23

2499

)51

20-0

1-38

6-42

74E

ASt

4in

Lw

ith3⁄8

inx

1⁄8

inor

ifice

.N

o.42

6(P

N23

2500

)O

pen

Purc

hase

EA

St4

inL

with

3⁄8

inx

1⁄8

inor

ifice

.N

o.42

7(P

N23

2501

)O

pen

Purc

hase

EA

St4

inL

with

3⁄8

inx

1⁄8

inor

ifice

.N

o.42

8(P

N23

2502

)O

pen

Purc

hase

EA

St4

inL

with

3⁄8

inx

1⁄8

inor

ifice

.N

o.42

9(P

N23

2590

)O

pen

Purc

hase

EA

St4

inL

with

1/16

inx

½in

orifi

ce.

Rib

bon

Noz

zles

App

lyin

gse

alan

tfo

rfa

ysu

rfac

ese

alin

g.N

o.86

07(P

N22

0568

)51

20-0

0-96

6-53

81E

ASt

57/ 8

inL

with

1/16

inx

¼in

orifi

ce.

No.

8608

(PN

2205

69)

5120

-00-

966-

8244

EA

St4

inL

with

11/6

4in

orifi

ce(fl

ared

tip)

No.

8610

(PN

2205

70)

5120

-00-

299-

6790

EA

St41

⁄8in

Lw

ith3/

64in

x9/

64in

orifi

ce.

No.

8613

(PN

2205

72)

5120

-00-

966-

5379

EA

St5

inL

with

3/64

inx

3⁄8

inor

ifice

.N

o.86

15(P

N22

0574

)51

20-0

0-96

6-53

78E

ASt

4in

Lw

ith1/

16in

x½

inor

ifice

.N

o.86

16(P

N22

0577

)51

20-0

1-38

5-50

74E

A2

3/16

inL

with

7/32

inor

ifice

(for

win

dshi

eld

fil-

lets

).N

o.86

30(P

N22

0589

)51

20-0

0-96

6-53

77E

ASt

4in

Lw

ith1⁄8

inx

1¾in

orifi

ce.

No.

8630

-9(P

N22

0582

)51

20-0

0-96

6-53

76E

ASt

47⁄8

inL

with

1⁄8

inx

1¾in

orifi

ce&

anat

-ta

ched

brus

hsp

read

er.

No.

8642

(PN

2205

85)

5120

-00-

293-

4676

EA

St4

inL

with

3/16

inor

ifice

.N

o.86

43(P

N22

0586

)51

20-0

0-77

5-16

70E

ASt

43⁄8

inL

with

1⁄8

inx

¾in

orifi

ce&

spat

ula

like

exte

nsio

nsp

read

er.

TO 1-1-691

Change 1 B-35

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

127 C

ont.

No.

8645

(PN

2205

87)

5120

-00-

138-

1658

EA

St4

3/16

inL

with

1⁄8

inx

1in

orifi

ce&

spat

ula

like

exte

nsio

nsp

read

er.

No.

8646

(PN

2205

88)

5120

-00-

966-

5374

EA

St3

15/1

6in

Lw

ith1⁄8

inx

¾in

orifi

ce&

saw

-to

oth

trow

elex

tens

ion

spre

ader

.N

o.86

48(P

N22

0589

)51

20-0

0-96

6-53

75E

ASt

53/

16in

Lw

ith1⁄8

inx

¾in

orifi

ce&

spat

ula

like

exte

nsio

nsp

read

er.

Ext

ensi

onN

ozzl

eN

o.60

0E(P

N22

0552

)51

20-0

0-67

0-11

87E

A6

3⁄8

inL

roun

dex

tens

ion

tube

.Fl

oorb

oard

Noz

zle

App

lyin

gse

alan

ton

floor

boar

dfa

ying

surf

aces

PN23

1674

Ope

nPu

rcha

seE

ASt

13⁄8

inL

with

½in

Dct

r.bu

tton

surr

ound

edw

ith12

EA

1/32

inor

ifice

sFu

nnel

Noz

zle

Filli

ngla

rge

cavi

ties

with

seal

ant.

1in

(PN

2317

18)

Ope

nPu

rcha

seE

ASt

13⁄8

inL

with

½in

funn

elty

peor

ifice

.2

in(P

N23

1348

)O

pen

Purc

hase

EA

St31

⁄8in

Lw

ith1

27/3

2in

funn

elty

peor

ifice

.N

ozzl

eA

dapt

erPN

2293

06O

pen

Purc

hase

EA

¼in

NPT

mal

eth

read

&½

inN

PTfe

mal

eth

read

tore

ceiv

e½

inN

PTth

read

nozz

le.

Edg

eFi

llN

ozzl

eN

o.44

4(P

N23

4164

)O

pen

Purc

hase

EA

A0.

40in

thic

kfla

nge

guid

esit

alon

ga

pane

led

ge/

corn

erto

prov

ide

asl

ight

lyro

unde

ded

ge/c

orne

rfil

l.

TO 1-1-691

B-36 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

128

Fast

ener

Seal

ing

Noz

zles

(Cou

nter

sink

Noz

zles

)

CA

GE

Cod

e#

9210

8U

sed

toap

ply

the

requ

ired

amou

ntof

seal

ant

inth

eco

unte

rsin

kar

eaof

fast

ener

hole

spr

ior

toin

stal

la-

tion

ofth

efa

sten

ers.

The

yha

veth

read

eden

dsto

fitin

toth

eSe

mco

®pl

astic

cart

ridg

es(I

tem

#12

4).

The

nozz

les

are

colo

rco

ded

for

iden

tifica

-tio

n.R

efer

toFi

gure

6-3d

eter

min

eth

eap

prop

riat

eno

zzle

confi

gura

tion

and

size

for

the

job

asw

ell

asop

erat

ion

inst

ruct

ions

.

PN23

3244

Ope

nPu

rcha

seE

ASi

ze:

3/32

in-1

⁄8in

(Red

)PN

2332

43O

pen

Purc

hase

EA

Size

:3/

16in

-¼in

(Whi

te)

PN23

3451

Ope

nPu

rcha

seE

ASi

ze:

5/16

in-3

⁄8in

(Blu

e)PN

2313

19O

pen

Purc

hase

EA

Size

:¼

inho

le(Y

ello

w)

PN23

1320

Ope

nPu

rcha

seE

ASi

ze:

5/16

inho

le(G

rey)

PN23

1321

Ope

nPu

rcha

seE

ASi

ze:

3⁄8

inho

le(G

reen

)PN

2315

60O

pen

Purc

hase

EA

Size

:7/

16in

hole

(Red

)PN

2315

59O

pen

Purc

hase

EA

Size

:½

inho

le(B

lue)

TO 1-1-691

Change 1 B-37

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

129

Riv

etN

ozzl

esC

AG

EC

ode

#92

108

Use

dto

appl

yth

ere

quir

edam

ount

ofse

alan

tin

the

coun

ter

sink

and

hole

prio

rto

fast

enin

gpa

rts

with

rive

ts.

The

spri

ng-l

oade

dtip

ofth

eno

zzle

acts

asa

chec

kva

lve

allo

win

gpr

ecis

esh

ots

ofm

ater

ial

tobe

disp

ense

d.T

hey

have

thre

aded

ends

tofit

into

the

Sem

co®

plas

ticca

rtri

dges

.T

heno

zzle

sar

eco

lor

code

dfo

rid

entifi

catio

n.R

efer

toFi

gure

6-4

tode

term

ine

the

appr

opri

ate

nozz

leco

nfigu

ra-

tion

and

size

for

the

job

asw

ell

asop

erat

ion

in-

stru

ctio

ns.

PN23

4285

Ope

nPu

rcha

seE

ASi

ze:

3/32

in(G

erm

aine

Gre

en)

PN22

6837

5130

-01-

413-

8733

EA

Size

:1⁄8

in(B

lue)

PN22

6838

Ope

nPu

rcha

seE

ASi

ze:

5/32

in(B

lack

)PN

2268

39O

pen

Purc

hase

EA

Size

:3/

16in

(Whi

te)

PN23

4260

Ope

nPu

rcha

seE

ASi

ze:

3/16

info

r12

0°co

unte

r-si

nk(G

reen

)PN

2342

84O

pen

Purc

hase

EA

Size

:7/

32in

(Lig

htB

lue)

PN22

6840

5120

-01-

416-

1683

EA

Size

:¼

in(R

ed)

PN23

3051

Ope

nPu

rcha

seE

ASi

ze:

5/16

in(O

rang

e)PN

:23

3052

Ope

nPu

rcha

seE

ASi

ze:

3⁄8

in(Y

ello

w)

130

Rol

ler

Noz

zles

(¼

inN

PTm

ale

thre

aded

end)

CA

GE

Cod

e#

9210

8U

sed

toap

ply

adhe

sive

san

dse

alan

tsev

enly

over

wid

ear

eas

ofsu

bstr

ate

(e.g

.fa

ying

surf

ace)

.T

hey

have

thre

aded

ends

tofit

into

the

Sem

co®

plas

ticca

rtri

dges

.T

hey

can

beso

lven

tcl

eane

dfo

rre

-use

.R

olle

rN

ozzl

eA

ssem

bly

PN23

2693

Ope

nPu

rcha

seE

A(1

inW

Rol

ler)

PN23

2692

Ope

nPu

rcha

seE

A(2

inW

Rol

ler)

Rep

lace

men

tR

olle

r

PN23

2701

5120

-01-

440-

6984

EA

(1in

WR

olle

r)PN

2327

02O

pen

Purc

hase

EA

(2in

WR

olle

r)

TO 1-1-691

B-38 Change 1

Tabl

eB

-2.

Equ

ipm

ent

For

Cle

anin

gan

dC

orro

sion

Pre

vent

ion

and

Con

trol

-C

onti

nued

Item No.

Nom

encl

atur

eSp

ecifi

catio

ns/P

art

Num

ber

Nat

iona

lSt

ock

Num

ber

Uni

tIs

sue

Inte

nded

Use

131

Cha

lk,

Mar

king

As-

sort

edC

olor

sA

-A-8

075

10-0

0-28

2-69

24A

TId

entifi

catio

n/M

arki

ngof

corr

oded

area

s.

Whi

teA

-A-3

1875

10-0

0-22

3-67

06G

R

TO 1-1-691

Change 1 B-39

Figure B-1. Back Mounted Full Facepiece Respirator

TO 1-1-691

B-40

Figure B-2. Front Mounted Full Facepiece Respirator

TO 1-1-691

B-41

Figure B-3. Hooded Air Respirator System

TO 1-1-691

B-42

GLOSSARY

A

Active metal — A metal prone to corrode or being corroded.

Additive — A compound added for a particular purpose; forexample, additives in fuel and lubricants can preventcorrosion, gum formation, varnishing, sludge formation,and knocking.

Aeration (Oxygen Concentration) Cell — An electrolyticcell in which the driving force to cause corrosion resultsfrom a difference in the amount of oxygen in solution at onepoint as compared to another. Corrosion is accelerated inareas where the oxygen concentrated is least, for example,in a crevice or under packing or gaskets.

Alkaline — Having a pH of more than 7.

Alloy — A combination of two or more metals.

Anaerobic — A process which is capable of occurring in theabsence of oxygen.

Anion — A negatively charged ion of an electrolyte whichmigrates toward the anode. The chloride ion in sea water isan anion.

Anode — The electrode of a corrosion cell at which oxida-tion or corrosion occurs. It may be a small area on thesurface of a metal or alloy, such as that where a pit develops,or it may be the more active metal in a cell composed of twodissimilar metals, (i.e., the one with the greater tendency togo into solution). The corrosion process involves the changeof metal atoms into cations with a liberation of electronsthat migrate through the metal to the cathode of the cell.

Anodic protection — The reduction or elimination of corro-sion of a metal achieved by making current flow from it tothe solution by connecting it to the positive pole of a sourceof current. Under most conditions, as the potential of aninitially active metal is gradually shifted in a more nobledirection, such as by potentiostatic means, the corrosioncurrent gradually increases. However, with suitable combi-nations of metal and solution, a critical potential is soonreached. Imposing a potential higher than the criticalpotential, causes the current to drop to a very low value, andthe metal becomes passive. The potential of metal has to beregulated by a potentiostat.

Anodize — To subject (a metal) to electrolytic action as theanode of a cell in order to coat with a protective ordecorative film (anodic oxidation film).

Austenitic — A term applied to that condition of ironassociated with a change in crystal structure that makes itnon-magnetic. This occurs with ordinary iron at an elevatedtemperature. When sufficient chromium and nickel arepresent, steel becomes austenitic (non-magnetic) at atmo-sphere temperatures. This is the case with the many stainlessalloys that combine about 18% chromium and 8% or morenickel with iron.

C

Cathode — The less active electrode of a corrosion cell,where the action of the current causes reduction and nearlycomplete elimination of corrosion.

Cathodic Protection — The reduction or elimination ofcorrosion of a metal that is achieved by making current flowto it from a solution, such as connecting it to the negativepole of some source current. The source of the protectivecurrent may be sacrificial metal, such as magnesium, zinc,or aluminum. The current may also be derived from arectifier, generator, or battery applied through an appropri-ate anode which may be connected by the applied current(as in the case of steel), or which remains substantiallyunaffected by the current, as in the case of platinum.Cathodic protection becomes complete when anodic reac-tions are completely suppressed and only cathodic reactionsoccur on the metal surface.

Cation — A positively charged ion in an electrolyte whichmigrates toward the cathode. Metallic ions, such as iron orcopper, are cations.

Caustic Embrittlement — The result of the combined actionof tensile stress and corrosion in an alkaline solution thatcauses embrittlement. This is the most frequently encoun-tered in the laps of riveted boilers where the requiredconcentration of the alkali in the boiler water occurs.

Cell — In corrosion processes, a cell is a source of electricalcurrent that is responsible for corrosion. It consists of ananode and a cathode immersed in an electrolyte andelectrically joined together. The anode and cathode may beseparate metals dissimilar areas on the same metal.

Chemical Conversion Coating — A film deliberately pro-duced on a metal by immersing it in, brushing it with, orspraying it with a selected chemical solution for the purposeof providing improved corrosion resistance to the metal orincreasing the adhesion of organic coatings to be appliedlater. Coatings covered by MIL-DTL-5541 are examples.

TO 1-1-691

Change 1 Glossary 1

Clear water — Colorless water containing no visiblesuspended particles.

Combustible Liquid — Any liquid having a flashpoint ator above 100° F, but below 200° F.

Concentration Cell — An electrolytic cell consisting ofan electrolyte and two electrodes of the same metal oralloy that develops a difference in potential as a resultof a difference in concentration of ions (most oftenmetal ions) or oxygen at different points in a solution.

Corrosion Fatigue — A reduction in the ability of ametal to withstand cyclic stress caused by its exposureto a corrosive environment.

Corrosion Rate — The speed of corrosion attack. It isusually expressed in terms of weight loss per unit oftime.

Couple — Two or more metals or alloys in electricalcontact with each other so that they can act as theelectrodes of a cell if they are immersed in an electro-lyte.

Cracking —

a. — Localized breaking of a paint film to expose theunderlying material.

b. — Breaking of metal or alloy in a brittle fashion alonga narrow path or network.

Crevice Corrosion — Corrosion occurring within acrevice formed by two or more parts of the same ordifferent metals or formed by a metal and non-metallicmaterial. Stainless steel and aluminum alloys are par-ticularly susceptible to crevice corrosion.

Critical Humidity — The relative humidity, under a spe-cific set of conditions, at which a metal or an alloy willbegin to corrode. In the presence of hygroscopic(moisture absorptive) solids or corrosion products, thecritical humidity will be lowered. Steel will not corrode ifthe relative humidity is less than 30% in a marineatmosphere.

D

Deposit Attack — When foreign material (dirt, corro-sion products, etc.) is deposited on the surface of ametal, it may shield the metal from the oxygen neces-sary to regenerate a protective oxide layer. An oxygen

concentration cell is formed, and serious corrosionmay result. Also called an active-passive cell.

E

Electrochemical Corrosion — Corrosion which occurswhen current flows between cathodic and anodic areason metallic surfaces.

Electrode — A metal or alloy that is in contact withelectrolyte and serves as the site where electricitypasses in either direction between the electrolyte andmetal. The current in the electrode itself is a flow ofelectrons, whereas, in the electrolyte, ions carry elec-tric charges and their orderly movement in solutionconstitutes a flow of current in the electrolyte.

Electrolysis — In the strict sense of the term, electroly-sis concerns chemical changes in the solution orelectrolyte due to the passage of current. Its relation tocorrosion arises only if the corrosion process alters themake-up of the solution. Hence, since the term is mostclosely related to the solution phenomena than tocorrosion, its use to indicate corrosion should bediscouraged.

Electrolyte — Any substance which, in solution orfused, exists as electrically charged ions that renderthe liquid capable of conducting a current. Solubleacids, bases, and salts, such as sea water, are elec-trolytes.

Electromagnetic Interference (EMI) — Radiation gen-erated from electromagnetic fields which are producedby radar antennas, Radio Frequency (RF) antennas,onboard transmitters, certain poorly designed avionicsunits, electric motors, and lightning and other naturaleffects. This type of radiation can interfere with aircraftavionics systems causing electrical malfunctions.

Electromotive Force (EMF) Series — A list of ele-ments according to their standard electrode potentials.The more negative the potential the greater the ten-dency of the metal to corrode. This series is useful instudies of thermodynamic properties, but does notindicate the rates of corrosion. A hydrogen gas elec-trode is the standard reference and its potential isdesignated as zero. All potentials are positive or nega-tive with respect to the hydrogen electrode. In thiscountry, the potentials of zinc and iron are designatedas negative and those of copper and platinum aspositive.

TO 1-1-691

Glossary 2

Embrittlement — Severe loss of ductility of a metalalloy that results in a brittle fashion.

Erosion — Destruction of a metal by the combinedaction of corrosion and abrasion or attrition by a liquidor gas with or without suspended matter.

Exfoliation — The breaking away of material from itssurface in flakes or layers.

F

Faying Surfaces — The common surfaces betweenmating parts.

Filiform Corrosion — Corrosion that develops undercoatings on metals in fine ragged hairlines, usuallywavy or curved and randomly distributed.

Film — A thin layer of material that may or may not bevisible.

Flammable Liquid — Any liquid having a flash point of100° F or less.

Flashpoint — The minimum temperature at which aliquid gives off an ignitable vapor in any one of theclosed cup flashpoint testers (Penssky-Martens, Tagli-bue, or Seta-Flash).

Fretting Corrosion — Corrosion at the interface of twoconnecting surfaces, usually under high pressure andsubject to very minute slippage due to relative vibrationof surfaces that ordinarily are not supposed to moverelative to each other, such as a shrink fit.

G

Galvanic — The flow of direct current between dissimi-lar metals.

Galvanic Corrosion — The accelerated corrosion of anactive metal caused by the presence of a less activemetal in the same solution and in contact with the moreactive metal.

Galvanic Series — A list of metals and alloys arrangedin order of their relative potentials in a given environ-ment. The order of their arrangement in this list may bedifferent in other environments.

H

Hazardous Material — A material which may pose athreat to human health or the environment when im-properly handled or disposed of.

Hazardous Waste — Waste which is characterized bythe Environmental Protection Agency (EPA) as 1)ignitable, 2) corrosive, 3) reactive, or 4) toxic, asdefined in 40 CFR 261, or is a listed hazardous wasteidentified in that regulation.

Hydrogen Embrittlement — Loss of ductility of a metal,caused by the entrance or absorption of hydrogen ionsinto the metal, as in the pickling of metal.

I

Inhibitor — As applied to corrosion, a chemical sub-stance or mixture which, when added in small amountsto a solution, markedly decreases corrosion.

Inorganic Coatings — Electroplated coatings, conver-sion coatings, anodic coatings, phosphate coatings,and oxide coatings.

Ion — An electrically charged atom or group of atoms.The sign of the charge is positive in the case of cationsand negative in the case of anions.

L

Local Cell — A cell in which the driving force is due toa difference in potential between areas on a metal oralloy surface immersed in an electrolyte. The potentialdifference may be due to inclusions, lack of homoge-neity, varying concentration of the solution with respectto oxygen or metal ions, etc.

M

Metal Ion Concentration Cell — A cell established on ametal surface due to different concentrations of its ionsin the electrolyte which is in contact with the metalsurface. These variations in concentration result inlocal differences in potential, thus allowing the estab-lishment of a local cell.

Mill Scale — The heavy oxide layer formed during hotfabrication or heat treatment of metals. The term ismost frequently applied to the scale of mixed ironoxides on iron and steel.

Mottling — Appearance of spotting or blotches of dif-ferent color or shades of coloring.

N

Noble Metal — A metal usually found as an uncom-bined metal in nature. Platinum, gold, and silver arenoble metals.

TO 1-1-691

Glossary 3

Non-Destructive Inspection — A method used tocheck the soundness of a material or a part withoutimpairing or destroying the serviceability of the part.

O

Organic Coatings — Paints, lacquers, plastics,greases, etc.

Oxidation — Any change involving the loss of electronsby an atom. Any corrosion process involves oxidationof the metal in a true chemical sense. It also may implythe destruction of metal or alloy as a result of the directaction of oxygen on the metal, e.g., the scaling of steelat high temperatures.

Ozone — A triatomic (O3) form of oxygen.

R

Room Temperature Vulcanizing (RTV) — A processfor curing of synthetic rubber or plastic materials whichoccurs at room temperature.

S

Solvent — A liquid substance capable of dissolving ordispersing one or more other substances.

T

Thixotropic — Gel-like in physical property.

Titration — A method or the process of determining theconcentration of a dissolved substance in terms of thesmallest amount of reagent of known concentrationrequired to bring about a given effect or reaction with aknown volume of the test solution.

U

Ultraviolet (UV) Light — Light (electromagnetic radia-tion) of a wavelength shorter than visible light butlonger than X-ray radiation. Long wavelength UV fromthe sun causes sunburn. Short wavelength UV fromunfiltered UV lamps can damage unprotected eyes.

Uniform Surface Corrosion — Corrosive etching ofmetal involving only the surface.

W

Wording — The following definitions are adhered to inpreparing this manual:

May — is used only when a procedure is optional.

Shall — is used only when a procedure is mandatory.

Should — is used only when a procedure is recom-mended but not mandatory.

Will — is used to indicate future action but never toindicate a mandatory procedure.

TO 1-1-691

Glossary 4

INDEXSubject Paragraph, Figure,

Table Number

AAIR INTAKE DUCTS FOR JET AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.15APPLICATION OF POLISH AND WAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.8APPLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.2

BBATTERY COMPARTMENTS, BOXES, AND ADJACENT AREAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2

Cleaning and Neutralizing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2.2Paint Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2.3

BERYLLIUM-COPPER ALLOYS, BERYLLIUM-ALUMINUM ALLOYS, AND BERYLLIUM OXIDE . . . . . . 7.20Corrosion Removal and Treatment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.20.1Depot Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.20.2

CCHEMICAL DEFINITIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3

Atom . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.1Electrolyte . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.4Electron . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.2Ions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.3

CLEANING COMPOUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3Alkaline Cleaners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.1Aqueous Parts Washer Cleaning Solutions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.3Dilution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.7Miscellaneous Cleaning Agents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.5Solvents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.4Steam Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.6

CLEANING EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4Aqueous Parts Washers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.9High Pressure/Hot Water Wash Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.1Miscellaneous Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.10Miscellaneous Large Cleaning Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.5Pneumatic Vacuum Cleaner . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.7Portable, 15 Gallon, Foam Generating, Cleaning Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.2Portable, 45 Gallon, Foam Generating Cleaning Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.3Spray Cleaning Guns for Solvents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.6Turbine Engine Compressor Cleaning Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.4Universal Wash Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.8

CLEANING PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5Cleaning Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.2Clear Water Rinsing of Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.3Fungus Growth Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.6Post Cleaning Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.4Soil Barriers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.7Treatment and Disposal of Wash Rack Waste . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.5Warnings and Cautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.1

CLOSELY COILED SPRINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.16Long Term Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.17.2Short Term Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.17.1

COMMON AREAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5

TO 1-1-691

Index 1

Battery Compartments and Battery Vent Openings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.14Bilge Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.13Control Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.10Electrical Connectors and Other Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.16Engine Exhaust and Gun Gas Impingement Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.4Engine Frontal Areas and Air Inlet Ducts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.7Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.1Faying Surfaces and Crevices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.2Flap and Slat Recesses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.6Hinges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.9Magnesium Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.15Relief Tube Outlets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.11Spot-Welded Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.3Water Entrapment Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.12Wheel Wells and Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.5

CORRECTIVE ACTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.3CORROSION CONTROL PROGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1

Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1.3Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1.2Training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1.1

CORROSION PREVENTIVE COMPOUNDS (CPC’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.5CORROSION REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5

Abrasive Blasting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.4Mechanical Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.1Non-Powered Tools and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.2Power Tools and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.3

CORROSION REMOVAL FROM THIN METAL (0.0625 INCH THICKNESS AND LESS) . . . . . . . . . . . . . . . . 7.14CORROSION REMOVAL PROCEDURES-MECHANICAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8

Abrasive Blasting Corrosion Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8.4Non-Powered Mechanical Corrosion Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8.2Powered Mechanical Corrosion Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8.3Warnings and Cautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.8.1

CORROSION REMOVAL-CHEMICAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.1Copper And Copper Based Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.5Magnesium Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.2Plated And Phosphated Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.7Stainless Steel (Cres) And Nickel Based Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.4Titanium and Titanium Based Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.6

CORROSION TREATMENT FOR STEEL CABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.4CORROSIVE ENVIRONMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9

Animal Damage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.14Climate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.8Factors of Influence in Tropical Environments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.9Industrial and Ship Emitted Air Pollutants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.13Manufacturing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.10Micro-Organisms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.15Moisture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.1Other Industrial Pollutants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.5Ozone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.4Salt Atmospheres . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.3

TO 1-1-691

INDEX - CONTINUEDSubject Paragraph, Figure,

Table Number

Index 2 Change 1

Sand, Dust, and Volcanic Ash . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.6Shipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.12Solar Radiation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.7Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.11Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.2

DDEFINITION OF CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2DEGRADATION OF NON-METALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10DEGREES OF CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4

Light Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.1Moderate Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.2Severe Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.4.3

DEPLETED URANIUM COUNTER-WEIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.18Corrosion and Finish Damage Treatment Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.18.1

DEVELOPMENT OF CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5Corrosion Under Painted Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5.1

EELECTRICAL AND ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11

Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11.6Conduit and Junction Boxes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11.2Grounding and Bonding Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11.1Wires and Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11.3

EMERGENCY PREPARATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3Emergency Reclamation Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3.3Emergency Reclamation Team . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3.2Priority Removal List of Equipment and/or Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3.1Production Planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3.4

EMI SEALS AND GASKETS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.21Treatment of EMI Seals and Gaskets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.21.1

EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4Application Nozzles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.2Injection Gun . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.3Sealant Gun . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.1Sealant Kits (Semkits®) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.4Sealant Removal and Application Tools . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.5

EVALUATION OF CORROSION DAMAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.3

FFACTORS INFLUENCE CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6

Anode and Cathode Surface Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.3Biological Organisms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.9Dissimilar Metal Coupling (Galvanic Corrosion) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.2Electrolyte Concentration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.8Electrolytes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.6Heat Treatment and Grain Direction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.5Mechanical Stress . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.10Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.7Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.4

TO 1-1-691


Table Number

Index 3

Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.11Type of Metal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.1

FAYING SURFACES AND ATTACHMENT POINTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.7Attaching Parts and Hardware . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.7.2Faying Surfaces, Joints, and Seams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.7.1Severely Corroded (Rusted) Hardware . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.7.3

GGENERAL CLEANING PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5

Alternate Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.2Primary Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.1Treatment After Exposure to Volcanic Ash . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.8Treatment After Landing on a Foamed Runway . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.7

GENERAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4Clean . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.3Disassembly/Removal of Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.2Removal of Contaminated Installed Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.1Tagging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.4

GENERAL SAFETY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

IINSPECTION METHODS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2

Depth Gauge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.2Eddy Current Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.6Fluorescent Penetrant Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.5Optical Depth Micrometers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.4Radiographic Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.8Ultrasonic Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.7Visual inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.1Visual Inspection with a Borescope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.3

INTEGRAL AND EXTERNAL FUEL TANKS AND DROP TANKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2

Aircraft Clear Water Rinse Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.3Immediate Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.4Reasons for Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.1When to Accomplish Work . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.2

INTRODUCTION TO CORROSION THEORY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6

Application of Conventional Lubricants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6.3Conventional Lubricants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6.1Solid Film Lubricants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6.2

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7Description of CPC’s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.5Non-Operational Preservation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.2Operational Preservation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.1Preservation Application Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.7Preservation of Specific Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.6Time Limitations of CPC’s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.4Types of CPC’s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.3

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.1

TO 1-1-691


Table Number

Index 4 Change 1

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1Aircraft Clear Water Rinse (CWR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1.3Aircraft Wash . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1.2Climatic Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1.1Effects of Desert Environment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.1.4

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1Consumable Materials Containers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1.2Local Environmental Laws and Regulations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1.4Local Purchase . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1.3Shelf Life . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1.1Units of Issue Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1.5

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B.1Unit Of Issue Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B.1.1

MMATERIALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3METALS AFFECTED BY CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8

Aluminum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.3Anodized Aluminum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.4Cadmium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.7Copper and Copper Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.6CRES/Stainless Steel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.8Graphite/Carbon Fiber Composites . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.11Magnesium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.1Nickel and Chromium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.9Silver, Platinum, and Gold . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.10Steel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.2Titanium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.5

MONEL RIVETS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.19

NNATURAL AND SYNTHETIC RUBBER PARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.8NON-STRUCTURAL TUBING MEMBERS AND ASSEMBLIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13

Aluminum Alloy Tubing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13.1Cadmium Plated Steel Tubing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13.3Removable Installations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13.5Special Instructions for Tubing Fittings and Sleeves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13.4Stainless Steel (CRES) Tubing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13.2

PPAINT REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.4PEENING OF METAL SURFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.11

Roto-Peening (Rotary Flap Peening) Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.11.2Types of Peening . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.11.1

PIANO TYPE HINGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.5POST DEPLOYMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.4POTABLE WATER TANKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.9PRE-DEPLOYMENT RECOMMENDATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.2PREVENTIVE MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.11PREVENTIVE MAINTENANCE PROGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1

TO 1-1-691


Table Number

Change 1 Index 5

Preventive Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.1.1PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Detailed Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.4Frequency of Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.2General Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.3Responsibility . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.1Usage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1

PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.1PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10

Application of Surface Treatments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.4Chemical Prepaint Treatments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.1Notes on Conversion Coating/Surface Treatment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.5Post Treatment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.6Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.3Surface Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.2Temporary Preservation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.7

PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.1PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.1Pitting on Critical Structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.7Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1

RRECOMMENDED ACTIONS WHILE DEPLOYED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3

Areas to be Checked and Cleaned . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3.2High Efficiency Particulate Air (HEPA) Filtration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3.1

RELIEF TUBE AREAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.3RESPONSIBILITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.2RESPONSIBILITY FOR CHANGES TO THIS MANUAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

Recommended Changes, Corrections, or Deletions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1RESPONSIBILITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.2Related Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

SSAFETY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2

Materials Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2.2Responsibility of Supervisors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2.1

SAFETY PRECAUTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3SCOPE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

Alphabetical Index . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.14Appendix A, Consumable Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.11Appendix B, Equipment for Cleaning and Corrosion Prevention and Control . . . . . . . . . . . . . . . . . . . . . . . . 2.12Chapter 1, Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3Chapter 2, Corrosion Theory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4Chapter 3, Preventive Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.5Chapter 4, Inspection and Corrosion Prone Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6Chapter 5, Corrosion Removal and Surface Treatment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7Chapter 6, Sealants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8Chapter 7, Treatment of Speci c Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9Chapter 8, Emergency Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10Foreword . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1

TO 1-1-691


Table Number

Index 6 Change 1

Glossary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.13Safety Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.2

SEALANT APPLICATION PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6Adhesion Promoters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.3Brush Spatula or Caulking Gun Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.4Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.1Masking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.2Spray Gun Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.5

SEALANT MIXING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.5Application Life . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.5.1Mixing MIL-PRF-81733, Type III Spray-able Sealant Coating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.5.3

TO 1-1-691


Table Number

Change 1 Index 6.1/(6.2 blank)

Storage Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.5.2SEALING COMPOUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3

Adhesion Promoters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.4Polysulfide, Polyurethane, and Polythioether Sealing Compounds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.2Sealant Packaging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.1Silicone Sealing Compounds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.3

SEALING OF SPECIFIC AREAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7Damaged Sealant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.10Depressions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.9Extensive Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.11External Aircraft Structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.8Fastener Sealing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.4Faying Surface Sealing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.1Fillet Sealing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.2Form-In-Place (FIP) Gasket Sealant Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.6High Temperature Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.12Injection Sealing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.3Integral Fuel Cells/Tanks and Removable Fuel Tanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.5Low Temperature Curing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.13

SPECIFIC EXTERNAL AREAS OF AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7Aircraft Fuel Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.9Airframes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.1Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.2Armament . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.8Helicopter Main and Tail Rotor Blades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.7Helicopter Transmission, Rotor Head, and Rotor Hub . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.6Reciprocating Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.3Turbine Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.4

SPECIFIC INTERNAL AREAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6Aircraft Cockpit Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6.1Aircraft Ejection Seats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6.2Avionic, Electronic and Electrical Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6.3Photographic Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6.4

STORAGE/SHELF LIFE CONTROL OF SEALANTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.8STRUCTURAL TUBING MEMBERS AND ASSEMBLIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12

Structural Aluminum Alloy Tubing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12.1Structural Carbon Steel Tubing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12.4Structural Magnesium Alloy Tubing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12.2

SURFACE FINISH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.6

TTHEORY OF CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4

Anode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.1Cathode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.2Electrical contact . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.4Electrolyte . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.3

TYPES OF CORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7Corrosion Fatigue . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.7Crevice/Concentration Cell Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.6Exfoliation Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.5

TO 1-1-691


Table Number

Index 7

Filiform Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.8Fretting Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.9Galvanic Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.2High Temperature Oxidation (Hot Corrosion) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.10Intergranular Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.4Pitting Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.3Uniform Surface Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.1

WWARNINGS, CAUTIONS, AND NOTES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

TO 1-1-691


Table Number

Index 8

Documents

TO 1-1-691sbe85fe43e9b86f2d.jimcontent.com/download/version... · TO 1-1-691 TECHNICAL MANUAL CLEANING AND CORROSION PREVENTION AND CONTROL, AEROSPACE AND NON-AEROSPACE EQUIPMENT