TM 1-1520-237-PMS PREVENTIVE MAINTENANCE SERVICE 21-MARCH-2007

*TM 1-1520-237-PMS

TECHNICAL MANUAL

40-HOUR INSPECTION CHECKLISTFOR

UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS

* This manual supersedes TM 1-1520-237-PMS, dated 17 April 2006, including all changes.

DISTRIBUTION STATEMENT D: – Distribution authorized to the DOD and DOD contractors only to protect critical technology effective as of 15 June 2003. Other requests must be referred to Commander, USArmy Aviation and Missile Command, ATTN: SFAE-AV-UH/L, Redstone Arsenal, AL 35898-5000.

WARNING – This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C. Sec. 2751 et seq.) or the Export Administration Act of 1979, as amended, Title 50,U.S.C., App. 2401 et seq. Violation of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DOD Directive 5230.25.

DESTRUCTION NOTICE –Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

HEADQUARTERS, DEPARTMENT OF THE ARMY

21 MARCH 2007

PREVENTIVE MAINTENANCE SERVICES

TM 1-1520-237-PMS

LIST OF EFFECTIVE PAGES/WORK PACKAGES

INSERT LATEST UPDATED PAGES/WORK PACKAGES. DESTROY SUPERSEDED DATA.

NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line in the outer margin of the page. Changes toillustrations are indicated by a vertical line in the outer margin of the page next to the illustration title.Insert latest change pages; dispose of superseded pages in accordance with regulations.

Dates of issue for original and changed pages/work packages are:

Original ......... 0.........21 March 2007

THE TOTAL NUMBER OF PAGES FOR FRONT AND REAR MATTER IS 4. THE TOTALNUMBER OF WORK PACKAGES IN THIS MANUAL IS 8 CONSISTING OF THE FOLLOWING:

Page / WP *Change Page / WP *Change Page / WP *Change Page / WP *ChangeNo. No. No. No. No. No. No. No.Title...............................................0Blank.............................................0A ................................................... 0B Blank..........................................0

i - ii ... .............................................0Chp 1 title page..............................0WP 0001 00 (4 pgs).......................0Chp 2 title page..............................0

WP 0002 00 (6 pgs).......................0WP 0003 00 (14 pgs).....................0WP 0004 00 (4 pgs).......................0WP 0005 00 (2 pgs).......................0

WP 0006 00 (4 pgs).......................0WP 0007 00 (18 pgs).....................0WP 0008 00 (2 pgs).......................0

* Zero in this column indicates an original page or work package

A

TM 1-1520-237-PMS

PREVENTIVE MAINTENANCE SERVICES40-HOUR INSPECTION CHECKLIST

FORUH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS

HOW TO USE THIS MANUAL

Inspection Requirements

This manual contains complete requirements for the 40 hour PMS inspection for the UH-60A, UH-60L, EH-60A, HH-60A, and HH-60L helicopter. It does not contain in-structions for repair, adjustments, or other means of rectifying conditions, nor does it contain instructions for troubleshooting to find causes for malfunctioning. Specifictolerances, limits, etc., can be found in the applicable maintenance manuals. Use of the alphabetical index in the applicable manuals will facilitate locating the requiredinformation.

This manual may contain inspection requirements applicable to specific equipment not installed on individual helicopters. When this situation is met, those requirementsthat are not applicable should be disregarded.

DA Form 2408-13-1 will be used to record all deficiencies and shortcomings discovered during the PMS/40hr inspections.

A 1-inch space following each area of inspection is provided to allow insertion of special inspection items resulting from TBs, MWOs, etc., and local command inspectionitems.

Accessing procedures and detailed inspection criteria can be found in the applicable maintenance manuals. Unless otherwise directed opened doors will be closed uponcompletion of each area inspection. All inspections are visual unless otherwise noted.

Requests for Engineering Authorization

All requests for engineering authorization, when required by this manual, will be forwarded to Commander, U.S. Army Aviation and Missile Command, ATTN: AMSRD-AMR-AE-U, Redstone Arsenal, AL 35898. Urgent requests shall be clearly identified to ensure priority handling and response. The requests shall include detailed infor-mation on the problem, e.g., sketches, photographs, dimensional data, etc., to assist in the evaluation and prompt reply.

Kapton Wires

Some UH-60A helicopters have wires that are Kapton insulated. The outer jacket of this type wire is dark-yellow and provides a surface for wire identification. Under thedark-yellow jacket is the copper-colored Kapton insulation. Beneath the insulation is the silver-coated electrical wire. If the outer jacket wears or peels, the copper-col-ored insulation may become visible. Exposure of copper-colored insulation is not a failure. Wire repair/replacement is required only if the insulation is damaged and/orthe electrical wire is exposed.

i

TM 1-1520-237-PMS

HOW TO USE THIS MANUAL– ContinuedUse Of Icon’s

Inspection intervals, ranges of helicopter effectivity, MWOs, and production line modifications referenced throughout this manual shall be identified by an icon. Icons usedin this manual are described as follows:

External Stores Support System ESSS >

UH-60A serial numbers 82-23748 and subsequent, EH-60A, UH-60L are provisioned for ESSS. Icon shown as ESSS > . UH-60A prior to serial number 82-23748 are notprovisioned for ESSS. Icon shown as W/O ESSS > .

Hover Infrared Suppressor System HIRSS > .

UH-60A serial numbers 86-24560 and subsequent, UH-60L, and EH- 60A, or UH-60A modified by MWO 1-1520-237-50-63. Icon shown as HIRSS > . UH-60A prior toserial number 86-24560 not modified by MWO 1-1520-237-50-63. Icon shown as W/O HIRSS > .

Modification of Dowel Pin Retention, Main Gear box MWO 50-43 > . UH-60A serial numbers 87-27004 and subsequent, UH-60L and EH-60A serial numbers 87-24663and subsequent, or UH-60A and EH-60A modified by MWO 55- 1520-237-50-43. Icon shown as MWO 50-43 > . UH-60A prior to serial number 87-27004 and EH-60Aprior to serial number 87-24663 not modified by MWO 55-1520-237-50-43. Icon shown as W/O MWO 50-43 > .

Roll Vibration Absorber ROLL >

UH-60L serial numbers 90-26278 and subsequent, or modified by MWO 1-1520-237-50-60 and EH-60A serial numbers 87-24669 and subsequent. Icon shown asROLL> .

HH-60A MEDEVAC Helicopter HH-60A > .

UH-60A helicopters modified to provide MEDEVAC missions. Icon shown as HH-60A > .

HH-60L MEDEVAC HelicopterHH-60L > MEDEVAC Helicopter.

UH-60L helicopters modified to provide MEDEVAC missions. Icon shown as HH-60L > .

Cockpit Air Bag System CABS > .

UH-60 helicopters modified by MWO 1-1520-237-50-82. Icon shown as CABS > .

ii

TM 1-1520-237-PMS

CHAPTER 1

GENERAL INFORMATION,

EQUIPMENT DESCRIPTION AND THEORY OF OPERATION


TM 1-1520-237-PMS0001 00

PREVENTIVE MAINTENANCE SERVICES40–HOUR INSPECTION CHECKLIST


GENERAL INFORMATION

SCOPEThe inspections prescribed by this manual will be performed at a 40 +/- 2-hour interval by AVUM activities with the assistance of AVIM activities when required. The 40hour PMS inspection interval may be extended to complete a scheduled flight. The inspection, when due, need not interrupt the flight during which the inspection becomesdue. In no case will the helicopter intentionally be scheduled for a flight that will cause it to exceed the 40 hour PMS inspection by more than 2 hours.

GENERAL INFORMATION

NOTE

Inspection items contained in this manual are considered the minimum requirements for performing a PMS inspection and must be performed.The cumulative effects of inspection deferrals are unknown and could result in catastrophic failure or increased maintenance at a later date.

The inspection requirements herein establish when certain equipment is to be inspected and what conditions are desired. The requirements must be followed, in order tomake sure that damage is discovered and corrected before malfunctioning or serious trouble results. In order to arrange inspection requirements as nearly as possibleaccording to the manner in which work will be done, the requirements in each area are divided into groups under area headings (Figure 1). An area title indicates a spe-cific helicopter location, which may include several systems or groups of related components within this given area. Refer to Army Regulations and Operator’s Manualfor personnel requirements and procedures for ground run and flight checking the helicopter.

OZONE DEPLETING CHEMICAL INFORMATION. To be determined.

HAZARDOUSMATERIAL INFORMATION. To be determined.

REPORTINGOF ERRORS. Reporting Errors And Recommending Improvements. You can help improve this manual. If you find any mistakes or if you know of a wayto improve these procedures, please let us know. Mail your letter or DA Form 2028 (Recommended Changes to Publications and Blank Forms) located in the back of thismanual, directly to: Commander, US Army Aviation and Missile Command, ATTN: AMSAM-MMC-MA-NP, Redstone Arsenal, AL 35898-5000. A reply will be furnishedto you. You may also provide DA Form 2028 information to AMCOM via e-mail, fax, or the World Wide Web. Our fax number is: DSN 788-6546 or Commercial 256-842-6546. Our e-mail address is: [email protected]. Instructions for sending an electronic 2028 may be found at the back of this manual immediately preceding thehard copy 2028. For the World Wide Web use: https://amcom2028.redstone.army.mil.

0001 00-1

TM 1-1520-237-PMS 0001 00

GENERAL INFORMATION– CONTINUED

Inspection Areas

Inspection Areas. Inspection areas are shown in Figure 1.

Figure 1. Area Diagram (Sheet 1 of 2)

0001 00-2

TM 1-1520-237-PMS0001 00


Figure 1. Area Diagram (Sheet 2 of 2)

0001 00-3

TM 1-1520-237-PMS 0001 00


AREA NO. 1: Cockpit Section All surfaces, material, components, and equipment inside and outside of the cockpit and electronics compart-ment, and extending rear to manufacturing break point at fuselage STA 247.0.

AREA NO. 2: Cabin Section All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 247.0 to STA379.0 (includes, but not limited to, main landing gear, HH-60A HH-60L > rescue hoist, and medical interior < ).

AREA NO. 3: Transition Section All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 379.0 to STA485.0.

AREA NO. 4: Tail Cone Section All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 485.0 to STA648.0.

AREA NO. 5: Tail Rotor Pylon Section All surfaces, material, components, and equipment inside and outside rear of STA 648.0 (includes, but notlimited to, horizontal stabilator, tail rotor and blades, tail gear box, intermediate gear box).

AREA NO. 6: Main Rotor Pylon All surfaces, material, components, and equipment inside and outside, above cabin section (includes, but notlimited to, main transmission, main rotor head, main rotor blades).

0001 00-4

TM 1-1520-237-PMS

CHAPTER 2

MAINTENANCE INSTRUCTIONS


TM 1-1520-237-PMS0002 00



UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60LHELICOPTERS

COCKPIT SECTION

INITIAL SETUP:

Tools and Special ToolsAircraft Mechanic’s Toolkit, SC 5180-99-B01

Materials/PartsBrush, Cleaning, Item 59 WP 1803 00Lubricating Oil, General Purpose, Item 185, WP 1803 00Towel, Machinery Wiping, Item 344, WP 1803 00

Personnel RequiredUH-60 Helicopter Repairer MOS 15T (2)

ReferencesPAM 738-751TM 1-1520-237-23WP 1803 00

NOTE

• The 40 Hour inspection is normally done by two Tactical Transport Helicopter Repairers, MOS 15T. The two MOS 15T’s are called A and B. Each inspectionitem is to be done by either mechanic. A or mechanic B as called out opposite the inspection procedure. Where both A and B are called for in the same proce-dure, A should do the inspection on the left side of the helicopter and B should do it on the right side. MOS 15N personnel will be required for power-on checks.• Before starting this inspection, review aircraft forms and records for discrepancies (PAM 738-751).• Review cleaning requirements in TM 1-1520-237-23.• Review lubrication requirements in TM 1-1520-237-23. Lubrication requirements posted in TM 1-1520-237-23 are aminimum. When operating in dry, dusty, and/or sandy conditions, special attention should be given toexposed areas particularly; the main and tail gear struts and the exposed stabilator actuator piston.• Refer to TM 1-1520-237-23 for specific inspection procedures and accept/reject criteria.

0002 00-1

TM 1-1520-237-PMS 0002 00

Seq.No. Item and Procedure MOS

15TMHA B

COCKPIT SECTION

1.1 0.02 BInspect nose door HH-60A HH-60L > FLIR, and nose avionics compartment as follows: <

Open nose door.

HH-60A UH-60L EH-60A > Inspect nose door and Doppler/GPS computer for obstructions. <

Check nose door for damage and seal for adhesion, cleanness, and any deterioration.

Inspect nose door hinges for cracks.

In avionics compartment and avionics compartment door, inspect avionics components, electrical connectors,and wiring for excessive wear, security, and damage.

HH-60A HH-60L > Remove FLIR fairing. <

HH-60A HH-60L > Check condition of FLIR and fairings. Check for dents, cracks, missing hardware, corro-sion, and damage. Inspect wiring for proper connection, burns, chafing, and security. <

HH-60A HH-60L > Install FLIR fairing. <

Inspect shock mounts for bottoming, corrosion, and security.

0002 00-2

TM 1-1520-237-PMS0002 00


15TMHA B

Inspect interior ducts and lines for security.

Close door and check for positive latching. Secure both latches.

1.2 Inspect cockpit exterior as follows: 0.01 B

Inspect cockpit drain holes for blockage.

Inspect cockpit exterior skin for corrosion, dents, cracks, and missing rivets.

Inspect wire strike guides for corrosion, security, and damage.

Inspect windshield, windshield wiper arms and blades for security, wear, cracks, and deterioration.

Lubricate windshield wiper studs and converters.

1.3 0.04 A BInspect all AREA No. 1 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.

1.4 0.01 A BCheck pilot’s and copilot’s step assemblies for cracks, corrosion and missing hardware. Check for evidence of lightningstrikes.

1.5

NOTEEvidence of a lightning strike will appear as a blackened surface, pit or hole with a burned rim.

Inspect cockpit interior as follows: 0.04 B

0002 00-3

TM 1-1520-237-PMS 0002 00


15TMHA BA BObserve entire cockpit interior for general cleanness, corrosion damage and for evidence of oil leakage from

ceiling, security of fasteners and structure for cracks.

Check crew doors for proper operation and damage. Inspect seals for deterioration, loosening of bonds andsigns of leakage.

Check armored wing panels, slide tubes, and bushings for security, damage cleanliness, and ease of opera-tion.

Check latches and hinges for condition and security.

Check jettison mechanism for security.

1.6 Inspect pilot’s and copilot’s seats as follows: 0.01 A B

Check pilot and copilot’s seats for damage, security, positive movement, and locking in all positions.

Inspect spherical bearing (resilient mounts) for cracks.

Check lap belts for corrosion, cuts, fraying, and security.

Check crotch belt for corrosion, cuts, fraying, and security.

Check shoulder harness for corrosion, cuts, fraying, and security.

Check inertia reel for damage, security, and positive locking and unlocking.

0002 00-4

TM 1-1520-237-PMS 0002 00


15TMHA B

1.7 0.01 A B

NOTECheck that No. 1 and No. 2 ENG POWER CONTROL and No. 1 and No. 2 ENG FUEL SYSlevers are shut off and that #1 and #2 ENG EMER OFF T-handles are fully forward.

Inspect engine control quadrant for general condition.

1.8 Inspect pilot’s and copilot’s collective sticks, cyclic sticks, and yaw control pedals as follows: 0.01 A B

Inspect pilot and copilot’s collective and cyclic sticks for general condition.

Check boots at base of sticks for loose fit, cracks, splitting, or damage. Make sure that there are no openingsthrough which foreign objects may enter flight control linkage area below.

Inspect grips for cracks and loose switches, and check that all lettering is readable.Inspect pilot and copilot’s yaw control pedals for dirt or mud accumulation.Check boots at base of pedals for loose fit, cracks, splitting, or damage. Make sure that there are no openingsthrough which foreign objects may enter flight control linkage area below.

Open boots. Check brake master cylinders for leakage. Close boots.

1.9 0.01 A BInspect components, electrical connectors, and wiring installed under pilot’s and copilots seat for excessive wear,damage and security.

1.10 0.02 BHH-60A HH-60L > Inspect Turret FLIR Unit (TFU) Scan Cavity (BIT/FIT Indication).

1.11 Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection areclosed or reinstalled.

END OFWORK PACKAGE

0002 00-5/6 blank

TM 1-1520-237-PMS0003 00


FORUH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L

CABIN SECTION

INITIAL SETUP:




ReferencesTM 1-1520-237-23WP 1803 00

Seq.No. Item and Procedure MH MOS

15TA B

CABIN SECTION

2.1 0.02 A BOpen troop/cargo doors. Inspect exterior for corrosion, distortion, cracks, and for loose or missing fasteners. Check opera-tion through full range with no binding and that the door remains secure in the tracks.

Check jettison mechanism for damage and proper position.

Check upper and lower roller support fittings for wear. Check front and rear door latches for positive latching. Inspectlower track for presence of eight wear strips each. Visually check for wear and damage.

0003 00-1

TM 1-1520-237-PMS 0003 00


15TA B

Inspect upper track for wear and damage.

Inspect door seals for deterioration, damage and separation.

2.2 HH-60A UH60L EH60A > < 0.01 A BOpen and close gunners’ windows. Inspect exterior frames, transparent panel, and tracks for damage. Inspect forloose or missing fasteners and seals for separation. Check for smooth operation and secure closure.

If gun mounts and ammo boxes are installed, inspect for security, damage, and stowage.

2.3 0.03 A BInspect HH-60A UH-60L > troop and gunners’ seats and OR EH-60 > observers’ seat < as follows:

Inspect for frayed or broken cables and for cleanness.

Check floor and ceiling attachment points for security.

Check troop/observer seat lap belts and shoulder harness for corrosion, cuts, fraying, and security.

Check gunner’s seat lap belts and shoulder harness for corrosion, cuts, fraying, and security.

Inspect gunner’s seat inertia reels for proper operation.

Inspect seat tubing and attenuators for damage and security.

0003 00-2

TM 1-1520-237-PMS0003 00


15TA B

2.4 0.1 A BEH-60 > Inspect mission operator’s seat as follows: <

Check mission operator’s seat for damage, security, positive movement, and locking in all positions.

Check lap belts and shoulder harness for corrosion, cuts, fraying, and security.


2.5 0.1 A BHH-60A HH-60L > Inspect medical attendant’s seats as follows: <

Check seats for damage, security, positive movement, and locking in all positions.

Check lap belt, crotch and shoulder harness for corrosion, cuts, fraying, and security.


Check seats for freedom of movement on seat tracks and positive locking.

2.6 0.1 A BEH60A > Inspect AN/ALQ-151 system as follows: <

Check AN/ALQ-151 mission consoles and equipment racks for equipment condition, security, and cleanness.

Check cable tunnel covers for security.

2.7 HH-60A HH-60L > Inspect cabin medical interior as follows: < A

0003 00-3

TM 1-1520-237-PMS 0003 00


15TA B

Inspect overhead, left side door post, and right side door post electronic components for damage and security.

Inspect medical cabinet for security of mounting.

Inspect medical cabinet electronic components for damage and security.

2.8 Inspect cabin ceiling as follows: 0.02 A B

HH-60A HH-60L > Remove overhead light panel. <

Lower soundproofing panels from ceiling.

Inspect beaded panel for buckling and cracks.

Check APU accumulator gage access cover hinge and fasteners for damage and security.

Check cabin ceiling for cracks, damage, or loose rivets. Visually inspect the support beam at STA. 308 for cracks.

2.9 Inspect cargo hook as follows: 0.01 A B

Check cargo hook for positive latching.

Check that hook is free to pivot from side to side.

Check cargo hook electrical connectors for security and damage.

0003 00-4

TM 1-1520-237-PMS0003 00


15TA B

Check cargo hook manual release lever spring for proper installation and distortion. Make sure spring provides positivepressure on manual release lever.

2.10 Check cargo hook support structure for damage corrosion and cracks. 0.01 A

Visually inspect cargo hook load arm for cracks.

2.11 Inspect tail rotor control cables and pulleys as follows: 0.01 ACheck tail rotor control cables for wear, fraying, corrosion and loose or missing plastic coating, particularly in pulleyarea.

Inspect cable guard pins for wear. Check that cables are riding properly in pulleys and that cable guard pins areinstalled.

Inspect tail rotor control cable pulleys for damage and security.

2.12 Inspect ESSS > as follows: < 0.01 A B

Check fuel lines in cabin for security, chafing, damage, or signs of leaks.

Check for security of bonding jumpers, dummy receptacles, caps, and lanyards.

Check electrical harnesses in cabin for proper connection, chafing, and security. Check backshells, on connectors fordamage.

Check fuel management control panel on center console for damage, cleanness, and security.

2.13 Inspect APU accumulator as follows: 0.01 A

0003 00-5

TM 1-1520-237-PMS 0003 00


15TA B

Check APU accumulator for proper pressure.

Inspect hydraulic handpump for security and leakage.

Check APU accumulator tape for correct percentage of fluid volume.

2.14 Inspect cabin soundproofing panels for damage and fasteners for security. 0.2 A B

Secure cabin soundproofing panels on ceiling.

HH-60A HH-60L > Install overhead light panel. <

2.15 Inspect battery as follows: 0.01 A

HH-60A UH60L EH60A > Remove battery cover. <

Check electrical connector, case mounting clamps, and covers for damage, proper position, and security.

HH-60A UH60L EH60A > Check vent lines for damage, cleanness, corrosion and obstructions. <

HH-60A UH60L EH60A > Install battery cover. <

2.16 Inspect auxiliary cabin heater as follows:

Inspect temperature controller for damage and security.

0003 00-6

TM 1-1520-237-PMS0003 00


15TA B

Inspect harness for proper connection, chafing, security, and backshell for damage.

2.17 Inspect main landing gear shock struts, drag beams, and brakes as follows: 0.02 A BRemove main landing gear upper fairing.

Inspect main landing gear shock struts upper and lower stages for dirt, corrosion, and correct inflation.

Wipe clean and lube exposed main landing gear strut pistons.

Inspect main landing gear shock strut attachment points for distortion and wear.

Check wire cutters for security, damage and corrosion.

Check ground wire for security and contact with ground.

Check drag beam switches for security and damage.

Check drain lines for obstruction.

Check brake wear indicator pins for minimum length.

Check brake and brake lines for damage or leaks.

Install main landing gear upper fairing.

2.18 Visually inspect main wheels for missing or damaged hardware. 0.01 A B

0003 00-7

TM 1-1520-237-PMS 0003 00


15TA B

2.19 Visually inspect main wheel tire for wear, cuts, or cracks. Check tire pressure with a gauge. Service as necessary.

2.20 Inspect cabin exterior as follows: 0.02 A B

Examine cabin exterior skin for corrosion, cracks, dents, and missing rivets.

Check lower cabin skin drain holes for obstruction.

Check that external ICS connector covers are in place.

Check external power receptacle for burned pins (right side only). Check cover for secure closure.

2.21 ESSS > Inspect W/Tanks installed as follows: < 0.03 A B

Remove HSS wing upper/lower root, front/rear VSP, trailing edge, and saddle assembly fairings.

Check fuselage attachment fittings for security and cracks.

Check all expandable pins for security and cracked washers. Make sure handle is securely snapped over end of pin,and that locking ring is fully visible and expanded.

Check expandable pin bonding jumpers for security and corrosion.

Check electrical harnesses and connectors for security and chafing.

0003 00-8

TM 1-1520-237-PMS0003 00


15TA B

Check breakaway lanyards for proper installation.

Check root-to-fuselage fuel hose for security, chafing, damage, or signs of leaks.

Check root-to-fuselage pneumatic hose for security, chafing, damage, or signs of leaks.

Check horizontal stores support fuel hoses, fuel tube assembly, and fuel tee union for security, chafing, damage, orsigns of leaks.

Check horizontal stores support pneumatic hoses and pneumatic check valve for security, chafing, damage, or signsof leaks.

Check vertical support pylon pneumatic hose and elbow for security, chafing, damage, or signs of leaks.

Check vertical support pylon fuel hose, fuel tube, and isolation check valve for security, chafing, damage, or signs ofleaks.

Check support struts for security, cracks, delamination, and chipping. Check clevis locknuts for security.

Check support strut bonding jumpers for security and corrosion.

Visually check upper and lower surfaces of horizontal stores support for cracks, chipping, or delamination.

Check leading and trailing edge fairings for cracks, dents, and damage.

Check vertical support pylons for security.

Check that locking pin on expandable bolts is securely snapped into tab, and that locking ring is fully visible andexpanded.

0003 00-9

TM 1-1520-237-PMS 0003 00


15TA B

Check fuel shutoff valves for security and leaks.

Check fuel tanks for proper installation, leaks, and damage.

Do torque check of sway brace locknuts. If locknut slips, retorque screws and locknuts.

Install HSS wing fairings.

2.22 ESSS > W/O tanks installed inspect as follows: < 0.2 A B

Remove upper and lower root fairings and check for cracks, dents, and damage.

Remove front and rear vertical support pylon fairings, and check for cracks, dents, and damage.

Check fuselage attachment fittings for security and cracks.

Check all expandable pins for security and make sure handle is secure. Make sure handle is securely snapped overthe end of pin, and that locking ring is fully visible and expanded.

Check expandable pin bonding jumpers for security and corrosion

Check root-to-fuselage electrical harness and connectors for security and chafing.

Check breakaway lanyards for installation.

0003 00-10

TM 1-1520-237-PMS0003 00


15TA B

Check root-to-fuselage fuel hose for security, chafing, and damage.

Check root-to-fuselage pneumatic hoses for security, chafing, and damage.

Check support struts for security, cracks, delamination, and chipping.

Check clevis locknuts for security.

Check support strut bonding jumpers for security and corrosion.

Visually check upper and lower surfaces of horizontal stores support for cracks, chipping, and delamination.

Check leading and trailing edge fairings for security, cracks, dents, and damage.

Check vertical support pylons for security.

Check that the locking pin on the expandable bolts is securely snapped into tab, and that the locking ring is fully visibleand expanded.

Install fairings.

2.23 0.5 A B

NOTEThe following procedure is required when operating in dry, dusty and/or sandy environment.

Clean Horizontal Stores Support (HSS) Pneumatic Check Valves.

0003 00-11

TM 1-1520-237-PMS 0003 00


15TA B

2.24 0.1 BHH-60A HH-60L UH-60 > Inspect external rescue hoist as follows: <

Remove support arm fairings.

Inspect rescue hoist for cracks, corrosion and security.

Check hoist support for cracks, corrosion, damage, and security.

Check hoist cowlings and fairings for damage and security and screw heads for corrosion.

Check hook assembly for free rotation and security.

Check spring bumper grommet for security.

Check electrical connectors and wiring for security, damage, and chafing.

Check cabin RESCUE HOIST control panels for security, controls and switches for binding, and lettering for readability.

Check hydraulic fittings on hydraulic equipped hoists for signs of leakage.

2.25 0.1 BUH-60 > Inspect internal hoist if installed as follows:

Inspect rescue hoist for cracks, corrosion, and security.

Check hoist floor and ceiling mounts for cracks corrosion, damage and security.

0003 00-12

TM 1-1520-237-PMS 0003 00


15TA B

Check hook assembly for free rotation and security.

Check spring bumper grommet for security.

Check electrical connectors and wiring for security, damage and chafing.

Check cabin RESCUE HOIST control panels for security, controls and switches for binding and lettering for readability.

2.26 0.04 A BInspect all AREA No. 2 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.

2.27 Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed orreinstalled.

END OFWORK PACKAGE

0003 00-13/14 blank

TM 1-1520-237-PMS0004 00



TRANSITION SECTION

INITIAL SETUP:




ReferencesTM 1-1520-237-23WP 1803 00


15TA B

TRANSITION SECTION

3.1 Inspect as follows: 0.01 A B

Remove soundproofing panels and fuel line enclosure panel from rear bulkhead.

ESSS > Check flow sensor panel for security and leaks. <

Check fuel hoses, electrical harnesses, and bonding jumpers for proper connection, security, and chafing.

0004 00-1

TM 1-1520-237-PMS 0004 00


15TA B

Install fuel line enclosure panels and soundproofing panels.

3.2 Inspect external air start connector on left side as follows: 0.03 A

Inspect external air start connector for security.

Check flapper valve for free movement.

Check access cover for secure closure.

3.3 Inspect drain line and vent line exit ports underneath helicopter for obstruction. 0.05 A B

Check for water and contamination in both fuel tanks using siphoning sample kit or draining 1 pint of fuel from bothsump drains.

3.4 0.01 A BVisually inspect exterior of sump drain access panels and surrounding area for signs of fuel leakage. Check transition areadrains for obstruction.

3.5 Inspect transition section skin for corrosion, cracks, dents, or missing rivets. 0.01 A B

3.6 0.06 AEH60A HH-60A HH60L > Inspect transition section avionics compartment as follows: <

Open avionics access door.

Inspect avionics access door and access panels for condition, damage, and security of latching.

0004 00-2

TM 1-1520-237-PMS 0004 00


15TA B

Check security of ECS pallets.EH60A > Check IINS, INU, and NPU shelves for condition and security. <

EH60A > Check INU, and NPU components for security in mounts. <

HH-60A HH60L > Check OBOGS components for damage and security. <

HH-60A HH60L > Inspect avionics components, electrical connectors, and wiring for excessive wear, security, anddamage. <

EH60A > Check IINS filter and cooling ducts. <

EH60A > Check IINS battery for security and condition. <

Close and secure avionics access door.

3.7 0.04 A BInspect all area No. 3 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.


END OFWORK PACKAGE

0004 00-3/4 blank

TM 1-1520-237-PMS0005 00



TAIL CONE SECTION

INITIAL SETUP:




ReferencesTM 1-1520-237-23WP 1803 00


15TA B

TAIL CONE SECTION

4.1 0.01 BInspect tail landing gear tire for wear, cuts and cracks. Check tire pressure with a gage. Service as necessary.

4.2 Inspect tail landing gear shock strut and yoke area as follows: 0.03 B

Check wire strike deflector for security and damage.

Remove right or left side tail cone access panel.

0005 00-1

TM 1-1520-237-PMS 0005 00


15TA B

Inspect pylon step fitting.

Inspect cable guide.

Inspect shock strut for leakage, dirt, corrosion and strut under inflation.

Inspect tail landing gear shock strut attachment points for chafing damage, cracks, and security.

Wipe clean and lube exposed tail landing gear strut pistons.

Install access panel.

4.3 Inspect tail cone exterior as follows: 0.02 A B

Inspect tail cone skin for corrosion, dents, cracks, and missing rivets.

Check tail cone skin drain hole for obstruction.

Inspect tail cone anti-collision light for security. Check lens for cracks, breakage, and cleanness.

Check chaff and flare dispenser payload modules and mounts for condition, security, corrosion and cleanness.

4.4 Inspect tail cone interior for condition. 0.05 A

0005 00-2

TM 1-1520-237-PMS 0005 00


15TA B


4.6 Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closedor reinstalled.

END OFWORK PACKAGE

0005 00-3/4 blank

TM 1-1520-237-PMS0006 00



TAIL ROTOR PYLON SECTION

INITIAL SETUP:




ReferencesTM 1-1520-237-23WP 1803 00


15TA B

TAIL ROTOR PYLON SECTION

5.1 Inspect intermediate gear box as follows: 0.01 B

Remove intermediate gear box cover.

Inspect intermediate gear box, gear box mounting feet, and mounting area for cracks, dents, nicks, corrosion andsecurity.

Check intermediate gear box chip detector electrical connector for security.

0006 00-1

TM 1-1520-237-PMS 0006 00


15TA B

Inspect drain holes for obstruction.

Reinstall gear box cover.

5.2 Inspect tail rotor pylon area as follows: 0.01 B

Open tail rotor pylon drive shaft cover.

Examine pylon skin for corrosion, dents, and missing rivets.

Check electrical wiring for condition and security.

Inspect anti-collision light and position light for security and cracked, broken, or dirty lenses.

Close pylon drive shaft cover.

5.3 Inspect stabilator as follows: 0.01 B

Remove inspection panels.

Inspect spar for cracks using a flashlight and mirror.

Check stabilator and actuator attachment points for cracks, corrosion, security, and play.

0006 00-2

TM 1-1520-237-PMS0006 00


15TA B

Check limit switch attachment for security.

Wipe clean and lube exposed portions of stabilator actuator.

Install inspection panels.

5.4 Inspect static discharge wicks for security and general condition. 0.01 A

5.5 Inspect tail rotor deice system as follows: 0.01 B

Check tail rotor deice slipring environmental shield, wire harness, and connectors for chafing or damaged insulationand security.

Check drain holes in rotor and stator for blockage.

Check tail rotor deice brushes for wear.

Check tail rotor deice cable brackets for cracks.

5.6 Inspect Tail rotor pitch control rods with spherical bearings as follows: 0.05 B

Inspect tail rotor pitch control rod end bearings for wear using 0.010- inch side of locally made plastic feeler gage.

0006 00-3

TM 1-1520-237-PMS 0006 00


15TA B

NOTEDo the following inspections every 15- flight hours only on bearings that have failed the0.010-inch feeler gage inspection.

Inspect tail rotor pitch control rod end bearings for wear using 0.015- inch side of locally made plastic feeler gage.

5.7 Inspect all area No. 5 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware. 0.04 A B


END OFWORK PACKAGE

0006 00-4

TM 1-1520-237-PMS0007 00



MAIN ROTOR PYLON

INITIAL SETUP:




ReferencesTM 1-1520-237-23WP 1803 00


15TA B

MAIN ROTOR PYLON

6.1 Inspect main rotor pylon sliding cover as follows: 0.02 A B

Open main rotor pylon sliding cover.

Inspect main rotor pylon sliding cover for cracks and distortion.

Inspect rollers and tracks for damage and wear.

0007 00-1

TM 1-1520-237-PMS 0007 00


15TA B

Check main rotor pylon sliding cover screen for obstructions.

Inspect wire strike guides and cutters for security, damage and corrosion.

Inspect pin receivers, support structure, skin, stringers, and intercostals at stations 247. 0 and 267. 0 for cracks.

6.2 Inspect pitot-static tube as follows: 0.01 A B

Inspect pitot-static tube openings for any obstructions, such as dirt or insects.

Inspect for discoloration beyond that normally cause by pitot heater.

6.3 Inspect flight controls and heating/ventilation system as follows: 0.02 A B

Visually inspect all flight control rod assemblies for external corrosion.

Inspect flight control rods, jamnuts, bellcranks, and supports for cracks, wear, distortion, and security of attachment.Inspect for looseness between the control tube body and jamnuts by moving the control rod assembly in anydirection.

Inspect flight control mixer for cracks, wear, distortion, and security of attachment.

Inspect heating bleed-air tubes for cracks and damage.

Check ventilation blower and heater mixing valve for damage.

0007 00-2

TM 1-1520-237-PMS0007 00


15TA B

Check temperature sensing tube to heater mixing valve for security and cracks.

Check heater mixing valve duct inlet screen for blockage.

6.4 0.02 A BInspect primary servos, yaw, and collective boost servos, pitch trim assembly, and roll assembly as follows:

Check primary servos, yaw and collective boost servos, pitch trim assembly, roll assembly, yaw boost SAS actuator,pitch trim SAS actuator, and roll assembly SAS actuator for leakage. Special attention should be given to the upperand lower surfaces of the output links. Check all SAS actuators for any visible gouging, or damage resulting fromcontact with safety cables or wire installed between the actuator housing and the output piston-retaining nut.

Inspect three primary servos for damage and security of mounting. Special attention should be given to the threadundercut area of all servo piston rods on the shaft immediately adjacent to output clevis.

Inspect pitch trim assembly and roll assembly for damage and security of mounting.

Inspect both ends of collective boost servo for cracks at cylinder ends, and cracks on power piston shafts. Specialattention should be given to the thread undercut area of all servo piston rods on the shaft immediately adjacent tooutput clevis.

Inspect both ends of yaw boost servo for cracks at cylinder ends, and cracks on power piston shafts. Specialattention should be given to the thread undercut area of all servo piston rods on the shaft immediately

Inspect yaw boost SAS actuator, pitch trim SAS actuator, and roll assembly SAS actuator for damage and security.

0007 00-3

TM 1-1520-237-PMS 0007 00


15TA B

6.5 0.01 A BInspect accessory module for oil seepage, paying particular attention to area around main generator.

6.6 0.01 A BInspect input and accessory module housings for paint discoloration from aluminized gray to brown.

6.7 0.01 A BInspect accessory module chip detector electrical connectors, Nr speed sensor electrical connector, and low oil pressuresensor electrical connector for security.

6.8 Inspect main rotor pitch control rod spherical bearings as follows: 0.02 A B

Inspect main rotor head upper pitch control rod end bearings for wear using 0.010-inch side of locally made plasticfeeler gage.

Inspect main rotor head lower pitch control rod end bearing for wear using 0.010-inch side of locally made plasticfeeler gage.

Inspect main rotor pitch control rods for any obvious damage or deformation.

NOTEDo the following inspections every 15- flight hours only on bearings that have failed the 0.010feeler gage inspection.

Inspect main rotor head upper pitch control rod end bearings for wear using 0.015-inch side of locally made plasticfeeler gage.

0007 00-4

TM 1-1520-237-PMS0007 00


15TA B

Inspect main rotor head lower pitch control rod end bearing for wear using 0.015-inch side of locally made plasticfeeler gage.

6.9 0.01 A BMain Rotor Pitch Control Rod Elastomeric Bearings.Inspect main rotor head lower pitch control rod end bearing for wearusing 0.015-inch side of locally made plastic feeler gage.

NOTEElastomeric rod end bearing plastic feeler gage should only be used if possible separationexists based on visual inspection of bearing surfaces.

Inspect main rotor head upper pitch control rod end bearings for elastomeric cracks or separation, if a concentrationor pileup of eraser type wear is present, if an extrusion is detected, if cracking or disbonding of elastomer from shiminner or outer member is suspected. Visually check for signs of inner member separation using hand force, shakingcontrol rod. Check for gaps or cracks in areas other than manufactured shim gaps.

Inspect main rotor head lower pitch control rod end bearings for elastomeric cracks or separation, if a concentrationor pileup of eraser type wear is present, if an extrusion is detected, if cracking or disbonding of elastomer from shiminner or outer member is suspected. Visually check for signs of inner member separation using hand force, shakingcontrol rod. Check for gaps or cracks in areas other than manufactured shim gaps.

6.10 Inspect main rotor hub and spindle as follows: 0.10 A B

Inspect main rotor hub for cracks and damage.

Visually check spindle shaft shrink tubing for evidence of looseness or movement.

Check inner race slippage mark for movement.

0007 00-5

TM 1-1520-237-PMS 0007 00


15TA B

6.11 Inspect main rotor head dampers bearing as follows: 0.10 A B

NOTERemoval of damper assembly is not required for feeler gage inspection.

Inspect inboard and outboard main rotor head damper rod end bearings for wear using 0.010-inch side of locallymade plastic feeler gage.

NOTEDo the following inspections every 15 flight hours only on bearings that have failed the0.010-inch feeler gage inspection.

Removal of damper assembly is not required for feeler gage inspection.

Inspect inboard and outboard main rotor head damper rod end bearings for wear using 0.015-inch side of locallymade plastic feeler gage.

6.12 Inspect droop stops as follows: 0.02 A B

Check droop stop lugs for cracks.

Check droop stop ring nut for looseness, and sleeve bearing (inner race) for cracks, on spindle assemblies 70070-10030-041, 70070-10030-042, 70070-10030-045, 70070-10030-046, 70102-08200-041 through 70102-08200-044, and 70102-08200-063.

Check droop stop support for cracks. Visually inspect droop stop support for cracks at upper and lower pullergrooves.

0007 00-6

TM 1-1520-237-PMS0007 00


15TA B

Check droop stop and droop stop retaining pin bushings for damage and security.

Visually inspect droop stop spring and attaching hardware for signs of corrosion.

6.13 Inspect anti-flap assemblies as follows: 0.11 A

Check anti-flap assembly for damage, security, and freedom of operation.

Visually inspect for interference or contact between the anti-flap cam and the anti-flap stop plate.

Visually inspect for contact of the droop stop cam and horn attachment bolts.

6.14 Inspect main rotor spindle elastomeric bearings as follows: 0.11 A

A

NOTEThe spindle elastomeric bearing consists of a spherical bearing and a thrust bearing. Wear ofeither bearing is a gradual process that will take several hundreds of hours from first detectionof rubber damage to point where bearing must be replaced. Visual comparison of the bearingsin the applicable technical manual is the criterion for acceptance or rejection.

Using a flashlight and mirror visually inspect inner and outer surface of spherical bearing for wear, laminate separa-tions, and cracked shims through the 2-inch diameter inspection hole.

0007 00-7

TM 1-1520-237-PMS 0007 00


15TA B

A

NOTEDo not remove spindle to inspect inner surface of thrust bearing.

Using a flashlight and mirror visually inspect outer surface thrust bearing for elastomeric extrusion paying particularattention to the 6 o’clock position and surface areas furthest inboard. Replace thrust bearing within the next 30 flighthours if any elastomer debris is found.

AInspect thrust bearing for laminate separations and cracked shims. Cracks will appear in the edge of metal shims.No cracks allowed. (A white wax-like substance on rubber surface is normal and should not be removed.)

ACheck elastomeric bearings for surface cracking or crazing of rubber. Small hairline surface cracking or crazing ofrubber is acceptable.

AIf droop stop pounding is experienced, inspect droop stop ears on spherical elastomeric bearing endplate for cracks.

Check thrust elastomeric bearing endplate for cracks. A

Inspect hub arm for signs of contact with spindle retention nut. A

6.15 Inspect bifilar as follows: 0.01 A B

Inspect bifilar for cracks, visible damage, wear, and security.

Inspect bifilar weights for cracks between and adjacent to bushing bores on both upper and lower surfaces.

0007 00-8

TM 1-1520-237-PMS0007 00


15TA B

Inspect top and bottom bonded joints of bifilar weights for cracks.

Clean tapered bifilar washers, bushings, and pins.

Visually inspect tapered bifilar washers for wear and damage.

Relubricate bifilar washers, pins, and bushings.

6.16 Inspect bifilar weights as follows: 0.05 A B

Inspect weights for nicks, gouges, and cracks in AREAS A, B, and C per applicable technical manual.

NOTECracked paint in area C of weights with "UT" marked in area of part number is acceptable.

Inspect weight marked "UT" in area of part number for cracks in paint in AREAS A and B. Inspect weight without"UT" marked in area of part number for cracks in paint in AREAS A, B, and C. If cracks in paint are found, refer toapplicable technical manual.

6.17 Inspect main rotor blades as follows: 0.04 A B

Test main rotor blade pressure indicators.

6.18 Inspect main rotor blade expandable pins for security and tension as follows:

0007 00-9

TM 1-1520-237-PMS 0007 00


15TA B

NOTEThere must not be any binding of the expandable pin by the main rotor blade when thetension is checked. The main rotor blades and blade pins do not have to be removed for thisinspection.

Raise main rotor blade and remove any binding of expandable pins.

Release expandable pin handle from lower nut and open handle.

Pull pin out far enough for top two expandable segments to be visible above blade cuff. Verify that pin is not fracturedby observing corresponding movement of lower end of core pin. DO NOT COMPLETELY REMOVE PIN.

If pin is not defective, reinstall and check closing tension on handle per (applicable technical manual).

6.19 Inspect swashplate as follows: 0.02 A BInspect swashplate and scissors assemblies for cracks, dents, distortion, corrosion and security.

Inspect swashplate uniball for cleanness.

6.20 Inspect swashplate link assemblies as follows: 0.1 A B

Make sure all electrical and hydraulic power is turned off or disconnected from the aircraft.

CAUTION

Any swashplate link assembly, which exceeds or does not conform to accept/reject criterialisted in the applicable technical manual, is to be replace.

0007 00-10

TM 1-1520-237-PMS0007 00


15TA B

NOTE• The following inspection is required on helicopters, which have the swashplate link assembliesspecified in following step. If these swashplate links are not installed, this inspection is not required.• Cracks of spherical bearing will be found on uniball surface usually starting atthe outer lip and running parallel to the bolt axis across the bearing.

With expandable pin installed, visually inspect spherical bearings of forward longitudinal swashplate link as-semblies, 70400-08110-048, 70400-08110-049, and 70400-08110-053; aft longitudinal swashplate link assem-blies, 70400-08110-048, 70400-08110-050, and 70400-08110-054; and lateral swashplate link assemblies,70400-08151-046, 70400-08151-048, and 70400-08151-050 for cracks. If no cracks are found and expandable pinis properly installed, inspection is complete.

If one crack is found, do this:

Check Teflon liner for deterioration or extrusion between spherical bearing outer race. NONE ALLOWED. Replaceswashplate link if liner deterioration or extrusion is found.

Check spherical bearing for radial play. NONE ALLOWED. Replace swashplate link if radial play is found.

Check gap under expendable pin washer using feeler gage, while pin is installed. GAP SHALL NOT EXCEED 0.002-INCH. If gap exceeds 0.002-INCH reinstall expandable pin to obtain correct gap.

If expandable pin has passed gap check, perform torque check while pin is installed as follows: (a) Remove cotterpin from expandable pin. (b) Insert 1/4-inch Allen wrench into end of expandable pin. (c) While holding Allenwrench firmly, apply 300 inch pounds of torque to expandable pin nut. MINIMUM TORQUE OF 300 INCH-POUNDSMUST BE ACHIEVED WITHOUT MOVEMENT OF NUT. If nut moves before minimum torque is reached, replaceswashplate link. (d) If minimum torque is achieved, remove Allen wrench and install new cotter pin.

0007 00-11

TM 1-1520-237-PMS 0007 00


15TA B

If all of the above conditions are met, swashplate link may remain in use for an additional 10 flight hours beforereplacement is required.

6.21 Inspect main rotor scissors as follows: 0.5 A

Using a dial indicator inspect scissors attachment bearings on swashplate for radial and axial play.

Using a dial indicator inspect upper rotating scissors bearings for radial and axial play.

Using a dial indicator inspect lower rotating scissors bearings for radial and axial play.

6.22 Inspect main transmission as follows: 0.10 A B

Inspect main transmission mounting lugs for cracks, dents, nicks, corrosion, and security.

Check engine input seal area for oil leaks.

MWO 50-43 > Inspect dowel pin retention bolts and retaining angles for deformation and security. <

W/O MWO 50-43 > Inspect dowel pins for signs of axial or rotational play on main gear box with slippage strip. <

W/O MWO 50-43 > Inspect sealing compound covering dowel pins for bulging, blistering, and cracking. <

6.23 Inspect gust lock as follows: 0.01 B

Engage gust lock.

0007 00-12

TM 1-1520-237-PMS0007 00


15TA B

Inspect gust lock for damage, wear, and security.

Release gust lock.

6.24 Inspect oil cooler and radiator as follows: 0.04 B

Remove oil cooler duct access cover.

Inspect oil cooler drive shaft for cracks, corrosion, damage and security.

Inspect oil cooler duct interior for debris and obstructions.

Inspect oil cooler fan for obstructions. Inspect fan rotor for debris trapped inside pockets between fan blades. Donot remove epoxy in pockets used for balancing rotor.

Inspect radiator for dirt and debris.

Inspect support structure for cracks (pay particular attention to bulkhead attachment flanged brazed area).

Inspect outer fuselage skin and external brackets of driveshaft viscous damper supports for cracks.

Inspect drive shaft bearing supports for cracks and security.

Inspect fuel crossfeed breakaway valves and tee breakaway valves for visible yellow line around center of valve.

0007 00-13

TM 1-1520-237-PMS 0007 00


15TA B

On helicopters with sleeve adapter, 70361-03011-105 installed, inspect slots in sleeve adapter for obstructions anddebris.

6.25 Inspect oil cooler viscous damper bearing for debris, damage, or overheating as follows: 0.01 B

Turn main rotor blades as required to gain access to oil cooler and engage gust lock.

NOTEMovement of the viscous damper bearing tube assembly is not cause for replacement ofbearing.

Grease purged from viscous damper bearing assembly, with no accompanying discoloration or indication of damageto bearing, is not cause for replacement.

On helicopters with sleeve adapter, 70361-03011-041, remove access panel at rear of oil cooler duct. Using aninspection mirror and flashlight, inspect area inside of duct for debris. Use flexible borescope to inspect area atforward end of viscous damper bearing and between viscous damper bearing assembly and duct.

On helicopters with sleeve adapter, 70361-03011-105, using slots in sleeve, inspect inside of duct for debris locatedat the forward end of viscous damper bearing, and between viscous damper bearing assembly and duct.

If debris is present at forward end of viscous damper bearing or between bearing and duct clean out debris perapplicable maintenance manual.

Check bearing for evidence of overheating (temperature discoloration) and debris damage. Pay particular attentionto bearing seal.

0007 00-14

TM 1-1520-237-PMS0007 00


15TA B

Inspect bearing assembly for proper fluid level, indicated by bubbles in the fluid.

Inspect viscous damper bearing for fluid leakage.

Install oil cooler duct access cover.

6.26 Inspect AN/ALQ-144 IRCM transmitter as follows: 0.02 A B

Inspect AN/ALQ-144 IRCM transmitter for security, scratches, cracks, and cleanness.

Check power cables for chafing against APU access door.

Inspect shock mounts and bonding straps, mounts, and fairing for cracks and missing attachment screws.

6.27 Inspect APU AC generator as follows: 0.02 A

Inspect APU AC generator for security of mounting, security of electrical connections, and dirt or excessive oilaccumulation.

Inspect generator casing for cracks.

Check generator air inlet and exhaust area for foreign object accumulation.

6.28 Inspect APU assembly as follows: 0.01 A

0007 00-15

TM 1-1520-237-PMS 0007 00


15TA B

Check APU exhaust for security and damage.

Inspect accessory drive and reduction drive mating surfaces for oil leaks.

Remove fuel control pan cover.

Check fuel lines and fuel control enclosure for fuel leaks.

Check lines for cracks and kinks.

Inspect fuel tube bundle for chafing.

Install fuel control pan cover.

Inspect APU support mounts and attaching hardware for damage and security.

6.29 Inspect engine/APU fire extinguisher as follows: 0.01 A B

Inspect engine/APU fire extinguisher containers for proper pressure reading on gages versus temperature.

Check lines for cracks and security.

Check for loose lines and fittings.

0007 00-16

TM 1-1520-237-PMS0007 00


15TA B

Manually check directional control valve flapper for freedom of movement. When tab is released, it should springback to its original position.

Check wiring at fire extinguisher container electrical connectors for damage.

6.30 0.01 AInspect APU directional valve for freedom of movement. Position cockpit switches as follows:

Fire Extinguisher: OFF.

Battery: ON.

Pull APU T-handle. Valve should rotate.

Push APU T-handle back in. Valve should rotate back.

Battery: OFF

6.31 Inspect main rotor pylon as follows: 0.01 A B

Open engine cowlings.

Inspect starter for proper oil level and leakage. Oil must be between overflow and machined step in fill port.

Inspect engine cowlings for cracks and missing fasteners.

Secure engine cowlings.

0007 00-17

TM 1-1520-237-PMS 0007 00


15TA B

Check engine cowling latches for cracks, positive latching, and secure closure.

Check engine air inlets for damage, missing fasteners, and foreign objects.

Inspect elastomeric gimbal for separation and bolt breakage.

6.32 Elastomeric Gimbal, 70361-08001-101.

Inspect elastomeric gimbal for separation and bolt breakage.

Check eight Allen-head bolts for tightness using finger pressure only.

If 1 to 4 bolts are loose, inspect for bond separation using a 0.005-inch feeler gage.

If more than 4 bolts are loose, replace gimbal.

Inspect input module seal for evidence of oil leakage.

Inspect upper and rear main rotor pylon fairings for cracks and missing fasteners.

6.33 Inspect HIRSS > as follows: < 0.09 A B

Inspect rear fairing and panel for cracks, dents, and security of attachment hardware.

0007 00-18

TM 1-1520-237-PMS 0007 00


15TA B

Inspect nacelle for cracks, dents, and security of attachment hardware.

Inspect exhaust extender for cracks, dents, and security of attachment hardware.

Visually inspect core and baffle for warpage and condition of emissive coating.

Inspect deswirl duct for security and damage.

Inspect firewall support angle, lower support fitting, and fail-safe plate for condition and security.

6.34 If standard engine exhaust modules are installed, inspect as follows: 0.09 A B

Inspect exhaust fairings for cracks and missing fasteners.

Inspect exhaust ejector for damage and foreign objects.

6.35 Close and secure all access panels, doors, cowlings, and covers. 0.01 A B



END OFWORK PACKAGE

0007 00-19/20 blank

TM 1-1520-237-PMS0008 00



UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L

POWER ON

INITIAL SETUP:


Materials/PartsBrush, Cleaning, Item 59 WP 1803 00Hydraulic Fluid, Fire Resistant, Item 144, WP 1803 00Lubricating Oil, General Purpose, Item 185, WP 1803 00Towel, Machinery Wiping, Item 344, WP 1803 00


ReferencesTM 1-1520-237-23WP 1803 00

SeqNo. Item and Procedure MH MOS

15T

A BPOWER ON

7.1 0.03 A B

NOTESequence Number 7.1 applies only to helicopters equipped with stabilator system test panel.

Perform actuators position comparator check part of stabilator system operational check UH-60A, UH-60L, HH-60A,HH-60L > (TM 11-1520-237-23) or EH-60 > < (TM 11-1520-249-23-2). <

0008 00-1

TM 1-1520-237-PMS 0008 00

SeqNo. Item and Procedure MH MOS

15T

A B7.2 0.4 A BHH-60A HH-60L > Inspect external electrical rescue hoist as follows: <

Reel out entire length of rescue hoist cable.Check cable for corrosion, kinks, separated strands, wear, and broken or frayed wires. Pay particular attention to areaaround hook.

Reel in hoist cable with gloved hand and wipe cable with clean heavy cloth.

7.3 0.01 A BCABS > Tilt back copilots seat. Apply electrical power to helicopter and check the following: <

Verify system fault indicator has no fault indication. Press PTD button and verify all LEDS illuminate and after 3 secondsgo off.


END OFWORK PACKAGE

0008 00-2

DISTRIBUTION: To be distributed in accordance with Initial Distribution Number (IDN) 314143 requirements for TM 1-1520-237-PMS.

PETER J. SCHOOMAKER General, United States Army

Chief of Staff Official:

JOYCE E. MORROW Administrative Assistant to the

Secretary of the Army0704602

By Order of the Secretary of the Army:

TM 1-1520-237-PMS

These are the instructions for sending an electronic 2028

The following format must be used if submitting an electronic 2028. The subject line must be exactly the same and all fields must be included; however only the following fields are mandatory: 1, 3, 4, 5, 6, 7, 8, 9, 10, 13, 15, 16, 17, and 27.

From: “Whomever” <[email protected]>

To: [email protected]

Subject: DA Form 2028

1. From: Joe Smith 2. Unit: home 3. Address: 4300 Park 4. City: Hometown 5. St: MO 6. Zip: 77777 7. Date Sent: 19--OCT--93 8. Pub. No.: 55--2840--229--23 9. Pub Title: TM 10. Publication Date: 04--JUL--85 11. Change Number: 7 12. Submitter Rank: MSG 13. Submitter Name: Joe 14. Submitter MName: T

15. Submitter LName: Smith 16. Submitter Phone: 123--123--1234 17. Problem: 1 18. Page: 2 19. Paragraph: 3 20. Line: 4 21. NSN: 5 22. Reference: 6 23. Figure: 7 24. Table: 8 25. Item: 9 26. Total: 123 27. Text: : This is the text for the problem below line 27.

The Metric System and Equivalents Linear Measure Liquid Measure Square Measure

1 centimeter = 10 millimeters = .39 inch 1 centileter = 1 milliliters = .34 fl. ounce 1 sq. centimeter = 100 sq. millimeters = .155 sq. inch 1 decimeter = 10 centimeters = 3.94 inches 1 deciliter = 10 centiliters = 3.38 ounces 1 sq. decimeter = 100 sq. centimeters = 15.5 sq. inches 1 meter = 10 decimeters = 39.37 inches 1 liter = 10 deciliters = 33.81 fl. ounces 1 sq. meter (centare) = 100 sq. decimeters = 10.76 sq. feet 1 dekameter = 10 meters = 32.8 feet 1 dekaliter = 10 liters = 2.64 gallons 1 sq. dekameter (are) = 100 sq. meters = 1, 076.4 feet 1 hectometer= 10 dekameters = 328.08 feet 1 hectoliter = 10 dekaliters =26.42 gallons 1 sq. hectometer (hectare) = 100 sq. dekameters = 2.47 acres 1 kilometer = 10 hectometers = 3,280.8 feet 1 kiloliter = 10 hectoliters = 264.18 gallons 1 sq. kilometer = 100 sq. hectometers = .386 sq. mile

Weights Cubic Measure 1 centigram = 10 milligrams = 1.5 grain 1 hectogram = 10 dekagrams = 3.52 ounces 1 cu. centimeter = 1000 cu. millimeters = .06 cu. inch 1 decigram = 10 centigrams = 1.54 grains 1 kilogram = 10 hectograms = 2.2 pounds 1 cu. decimeter = 1000 cu. centimeters = 61.02 cu. inches 1 gram = 10 decigrams = .035 ounce 1 quintal = 100 kilograms = 220.46 pounds 1 cu. meter = 100 cu. decimeters = 35.31 feet 1 dekagram = 10 grams = .35 ounce 1 metric ton = 10 quintals = 1.1 short tons

Approximate Conversion Factors To Change To Multiply

By inches centimeters 2. 540 feet meters . 305 yards meters . 914 miles kilometers 1.609 square inches square centimeters 6. 451 square feet square meters . 093 square yards square meters . 836 square miles square kilometers 2. 590 acres square

hectometers . 405

cubic feet cubic meters . 028 cubic yards cubic meters . 765 fluid ounces mililiters 29. 573 pints liters . 473

To Change To Multiply By

quarts liters . 946 gallons liters 3. 785 ounces grams 28. 349 pounds kilogram s . 454 short tons metric tons . 907 pound--feet newton--meters 1. 356 pound--inches newton--meters . 11296 ounce--inches newton--meters . 007062 centimeters inches . 394 meters feet 3. 280 meters yards 1.094 kilometers miles . 621 square centimeters square inches . 155 square meters square feet 10. 764

To Change To Multiply By

square meters square yards 1. 196 square kilometers square miles . 386 square hectometers

acres 2. 471

cubic meters cubic feet 35. 315 cubic meters cubic yards 1. 308 milliliters fluid ounces . 034 liters pints 2. 113 liters quarts 1. 057 liters gallons . 264 gram s ounces . 035 kilogram s pounds 2. 205 metric tons short tons 1. 102

Temperature (Exact)

F Fahrenheit 5/9 (after Celsius C temperature subtracting 32) temperature

PIN: 082273-000

Documents

TM 1-1520-237-PMS PREVENTIVE MAINTENANCE SERVICE 21-MARCH-2007