[Blank Page] - Lord Corporation (Rev 3).pdfP/N Y-27316-44-1, which may be installed on the Bell 206 tail skid as needed, to assist in the dynamic balancing of the tail rotor hub and

SM-6470 Bell Helicopter Models:

206A, 206B, 206L, 206L-1, 206L-3, 206L-4

LORD CORPORATION

2455 Robison Road West

ERIE, PENNSYLVANIA 16509-4675 USA 814: 456-8511

64-00-48 June 02/16

LB2-1010-20-1

SERVICE MANUAL FOR INSTALLATION & MAINTENANCE OF ELASTOMERIC TAIL ROTOR FLAPPING BEARING KIT

1.

2.

C

om

po

nen

t M

ain

ten

an

ce

Ma

nu

al

[Blank Page]

LORD CORPORATION

2455 Robison Road West

ERIE, PA 16509-4675 USA

64-00-48 Page T-1

Jun 02/16

SERVICE MANUAL FOR

INSTALLATION & MAINTENANCE OF

ELASTOMERIC TAIL ROTOR FLAPPING BEARING KIT

LORD PART NUMBER: LB2-1010-20-1

[Blank Page]

LORD CORPORATION SERVICE MANUAL

PART NUMBER LB2-1010-20-1

64-00-48 Page SWLA-1

Jun 22/11

SAFETY ADVISORY WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE

HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO COMPLY WITH THE MANUFACTURER'S OR SUPPLIER'S RECOMMENDATIONS CAN RESULT IN PERSONAL INJURY OR DISEASE.

This publication describes physical and chemical processes which can make it necessary to use chemicals, solvents, paints and other commercially available materials. The user of this publication must get the Material Safety Data Sheets (MSDS) (OSHA Form 20 or equivalent) from the manufacturers or suppliers of the materials to be used. The user must know the manufacturer/supplier information and keep to the procedures, recommendations, warnings and cautions set forth for the safe use, handling, storage and disposal of the materials.

---------------------------------------------------------------------------------------------------------------------

WARRANTY/LIABILITY ADVISORY WARNING: LORD CORPORATION ASSUMES NO RESPONSIBILITY FOR ANY TAIL ROTOR FLAPPING

BEARING KIT WHICH IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH THESE PUBLISHED INSTRUCTIONS AND/OR LORD CORPORATION FAA/FAR 36 REPAIR AUTHORIZATIONS. NEITHER DOES LORD CORPORATION ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND EQUIPMENT FABRICATED BY COMPANIES OTHER THAN LORD CORPORATION.

INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASE THE LIFE OF COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR EQUIPMENT CAN RESULT IN DAMAGE TO PRODUCT COMPONENTS OR GIVE UNSATISFACTORY RESULTS. EQUIPMENT OR PARTS THAT HAVE BEEN REPAIRED OR FABRICATED BY OTHER THAN LORD CORPORATION AUTHORIZED FACILITIES CAN INCREASE RISKS OF DEATH OR PERSONAL INJURY, COMPONENT FAILURES AND SECONDARY DAMAGE AND CAN VOID WARRANTIES UNDERWRITTEN BY LORD CORPORATION.

[Blank Page]



64-00-48 Page RR-1 Jun 02/16

RECORD OF REVISIONS Retain this record in the front of the manual. On receipt of revisions, insert revised pages in manual. Enter revision number, date issued, date inserted and initials.

REV NO.

DATE ISSUED

DATE INSERTED

BY REV NO

DATE ISSUED

DATE ISSUED

BY

1 April 25, 2000

2 June 22, 2011

3 June 02, 2016

[Blank Page]



64-00-48 Page SBL-1

Jun 22/11

SERVICE BULLETIN LIST

SERVICE BULLETIN NUMBER

REVISION NUMBER

DATE BULLETIN INCORPORATED INTO MANUAL

[Blank Page]



64-00-48 Page LEP-1

Jun 02/16

LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE

TITLE PAGE T-1 Jun 02/16

SAFETY ADVISORY – WARRANTY / LIABILITY ADVISORY SWLA-1 Jun 22/11

RECORD OF REVISIONS RR-1 Jun 02/16

SERVICE BULLETIN LIST SBL-1 Jun 22/11

LIST OF EFFECTIVE PAGES LEP-1 Jun 02/16

TABLE OF CONTENTS TC-1 Jun 22/11

INTRODUCTION INT-1 Jun 02/16

DESCRIPTION AND OPERATION

1 2 3 4

Jun 02/16 Jun 02/16 Jun 02/16 Jun 02/16

TESTING AND FAULT ISOLATION 101 Jun 22/11

SCHEMATICS AND WIRING DIAGRAMS

201 202 203 204

Jun 22/16 Jun 22/11 Jun 02/16 Jun 02/16

DISASSEMBLY 301 Jun 02/16

CLEANING 401 Jun 02/16

INSPECTION / CHECK

501 502 503 504 505

Jun 22/11 Jun 22/11 Jun 22/11 Jun 02/16 Jun 22/11

REPAIR 601 Jun 22/11

ASSEMBLY 701 Jun 02/16

FITS AND CLEARANCE 801 Jun 22/11

SPECIAL TOOLS, FIXTURES AND EQUIPMENT 901 Jun 22/11

ILLUSTRATED PARTS LIST

1001 1002 1003 1004 1005

Jun 22/11 Jun 22/11 Jun 02/16 Jun 02/16 Jun 02/16

SPECIAL PROCEDURES 1101 Jun 22/11

REMOVAL 1201 Jun 22/11

INSTALLATION 1301 Jun 22/11

SERVICING 1401 Jun 02/16

STORAGE 1501 Jun 02/16

REWORK 1601 Jun 22/11

[Blank Page]



64-00-48 Page TC-1 Jun 22/11

TABLE OF CONTENTS

SECTION PAGE

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

DESCRIPTION AND OPERATION .................................................................................................................... 1

TESTING AND FAULT ISOLATION .............................................................................................................. 101

SCHEMATIC AND WIRING DIAGRAM ......................................................................................................... 201

DISASSEMBLY .............................................................................................................................................. 301

CLEANING ..................................................................................................................................................... 401

INSPECTION CHECK .................................................................................................................................... 501

REPAIR .......................................................................................................................................................... 601

ASSEMBLY .................................................................................................................................................... 701

FITS AND CLEARANCE ................................................................................................................................ 801

SPECIAL TOOLS, FIXTURES AND EQUIPMENT ........................................................................................ 901

ILLUSTRATED PARTS LIST ....................................................................................................................... 1001

SPECIAL PROCEDURES ............................................................................................................................ 1101

REMOVAL .................................................................................................................................................... 1201

INSTALLATION ............................................................................................................................................ 1301

SERVICING .................................................................................................................................................. 1401

STORAGE .................................................................................................................................................... 1501

REWORK ..................................................................................................................................................... 1601

[Blank Page]



64-00-48 Jun 02/16

APPROVAL

The following section/s of this Service Manual, SM-6470, are FAA DER approved in accordance with 8110.54 for latest revision.

[Blank Page]



64-00-48 Page INT-1

Jun 02/16

INTRODUCTION

This publication contains shop maintenance instructions with Illustrated Parts List (IPL) for the LB2-1010-20-1 Tail Rotor Flapping Bearing Kit manufactured by LORD Corporation. These instructions provide information necessary to conduct maintenance functions ranging from simple checks to component bearing assembly replacement.

The instructions are divided into sections per ATA standard format and are shown in the preceding Table of Contents.

Section 1 (DESCRIPTION AND OPERATION) contains a brief overview of the bearing kit including LORD part numbers.

Sections 200 (SCHEMATICS AND WIRING DESIGN), 300 (DISASSEMBLY), 400 (CLEANING) and 500 (INSPECTION / CHECK) covers removal of bearing assemblies from the aircraft and acceptable procedures to determine serviceability of the bearing assembly.

Sections 600 (REPAIR) and 700 (ASSEMBLY) provide procedures necessary for restoring the bearing assemblies to serviceable condition, and section 1400 (SERVICING) provides information regarding, repair, remanufacturing and technical support.

Section 1000 (ILLUSTRATED PARTS LIST) provides a breakdown of assemblies, subassemblies and parts within the LB2-1010-20-1 flapping bearing kit.

Sections 1200 (REMOVAL) and 1300 (INSTALLATION) refer to the aircraft maintenance manual. Sections 100 (TESTING AND FAULT ISOLATION, 800 (FITS AND CLEARANCES), 900 (SPECIAL TOOLS, FIXTURES AND EQUIPMENT), 1100 (SPECIAL PROCEDURES) and 1600 (REWORK) are not used.

This manual should be used in conjunction with the appropriate aircraft maintenance manual.

The procedures in this manual are only to be performed by qualified shop mechanics that are familiar with this type of equipment.



[Blank Page]



64-00-48 Page 1

Jun 02/16

DESCRIPTION AND OPERATION

Description The LB2-1010-20-1 tail rotor elastomeric flapping bearing kit consists of a single elastomeric flapping bearing assembly, P/N LB2-1010-20-2, two brackets, P/N Y-27316-42-1, which are used to position and secure the flapping bearing in the tail rotor hub assembly, an identification plate, P/N Y-27316-43-1; an optional weight P/N Y-27316-44-1, which may be installed on the Bell 206 tail skid as needed, to assist in the dynamic balancing of the tail rotor hub and blade assembly, a decal P/N Y-27316-45-1 and attaching hardware.

Operation The LORD elastomeric tail rotor flapping bearing kit P/N LB2-1010-20-1 has the capability by its unique design to reduce unscheduled maintenance actions, reduce tail rotor vibration levels and improve direct operating costs. In addition to reducing maintenance man-hours, the elastomeric trunnion bearing has an indefinite life cycle based on inspections and on-condition replacement. The flapping bearing P/N LB2-1010-20-2 can be replaced while re-using the other serviceable components in the P/N LB2-1010-20-1 kit.



64-00-48 Page 2

Jun 02/16

1) Modification of Tail Rotor Hub Assemblies 206-011-810-(ALL)

A) Remove tail rotor hub and blade assembly from helicopter in accordance with the applicable Bell 206

Maintenance Manual.

B) Disassemble tail rotor hub and blade assembly in accordance with applicable Bell 206 Component Repair & Overhaul Manual.

C) Disassemble tail rotor hub assembly in accordance with applicable Bell 206 Component Repair & Overhaul Manual to remove trunnion and bearing housings

D) Trunnion and bearing housing will no longer be required and should be tagged accordingly. Retain hardware and balance weights.

E) If tail rotor hub is to be overhauled at this time, continue procedures in accordance with applicable 206 Component Repair & Overhaul Manual.

F) If no further maintenance actions are required on the tail rotor yoke, thoroughly clean to remove grease, oil and dirt and inspect for visual damage in accordance with applicable 206 Component Repair & Overhaul Manual.

G) Ensure yoke bores are free of nicks, dents and gouges per the applicable Bell 206 Component Repair & Overhaul Manual.

H) (Steps 1I – 1L Reference Figures 200-1 and 200-2)

Note: If necessary, heat may be applied to the yoke to ease installation of flapping bearing. Do not allow flapping bearing to be exposed to heat higher than 160°F. When using heat, it is recommended to use a temperature indicator stick or calibrated optical pyrometer.



64-00-48 Page 3

Jun 02/16

I) Install elastomeric flapping bearing (2) in yoke (1) and align dovetail grooves as shown in Figure 200-1, View A.

J) Position brackets (3) to dovetail grooves of bearing (2).

Note: Bolt (6) length, number of washers (5) and weights (4) will be determined during static balance in accordance with applicable Bell 206 Component Repair & Overhaul Manual and Illustrated Parts Breakdown.

K) Install bolts (6) and washers (5) with only a few threads of the bolts engaged in the yoke. Do not torque bolts; the bolts are used to keep the brackets aligned during the next step.

L) Using a 4” c-clamp or larger, as shown in Figure 200-2, slowly tighten c-clamp until brackets contact yoke.

M) Torque bolts (6) uniformly to 30 to 40 inch-pounds.

N) Install the LORD modification plate (7) on the yoke using either Magnolia Magno Bond #6398 or a similar product.

O) Re-assemble tail rotor hub and blade assembly in accordance with applicable Bell 206 Component Repair & Overhaul Manual.

P) Static balance tail rotor hub and blade assembly in accordance with Section 700-2.

2) Install Tail Skid Weight (Optional)

Note: Installation of the tail skid weight (10) is optional at the installer’s discretion. If the tail rotor can be dynamically balanced within the limits specified in the applicable Bell Maintenance Manual, then the tail skid weight is not required. If the dynamic balance limits cannot be met, then install the tail skid weight per steps A through K.

Note: As an alternate means of compliance for this Section, Bell Helicopter Textron Technical Bulletin No. 206L-00-200 may be accomplished in lieu of Steps A through K.

A) Remove the tail skid (9, Figure 200-3) from the vertical fin (8) in accordance with the appropriate 206 Series Maintenance Manual. Note which tail skid is being used.

B) Mark the location of the new holes in the tail skid, (Figure 200-4, Detail B). Note the difference in the dimensions for each skid.

C) Drill two holes of 0.176 inches diameter to align with the weight (10), (Figure 200-4, Detail B)

D) Apply a layer of sealant (Bell C-251 or MIL-PRF-81733D) on mating surface of the weight (10).

E) Install weight (10) on tail skid.

F) Apply sealant (Bell C-251 or MIL-PRF-81733D) on the bolts (11) and attach optional weight (10) to the tail skid (9) with the bolts (11), the washers (12) and nuts (13). Torque nuts 25 to 35 inch-pounds.

G) Paint weight to match aircraft.

H) Install the decal (14) on the top of the weight (10) and apply a layer of clear paint (MIL-PRF-85285D (3), clear) on the decal.

I) If a roll pin was previously used to retain the tail skid in the vertical fin, drill 0.249 – 0.255 inch dia. Hole through the vertical fin (8) and the tail skid (9).

http://specs4.ihserc.com/DocViewFrame.aspx?sess=629920940&prod=SPECS4&docid=ZLKLLCAAAAAAAAAA

http://specs4.ihserc.com/DocViewFrame.aspx?sess=629920940&prod=SPECS4&docid=ZLKLLCAAAAAAAAAA



64-00-48 Page 4

Jun 02/16

J) Apply sealant (AMS-S-8802) to the tail skid area of the mount in the vertical fin.

Note: Make sure to install the nut (17) on the tail rotor side of the vertical fin (8) (refer to Figure 200-3, Detail A).

K) Put the tail skid (9) into the mount on the vertical fin (8) and install the bolt (15), washers (16) and nut (17), torque nut 50 – 70 inch-pounds. Safety with the cotter pin (18).

L) Depending on which model 206 helicopter the tail skid weight is installed on, weight and balance will be affected as follows:

Series Longitudinal Weight Change

ARM Moment Lateral Weight Change

Skid Assembly 206-020-110-005

206 A/B

+2.1 Lbs. +369.68 776.3 in-lbs. Not affected

206L

+2.1 Lbs. +405.20 850.5 in-lbs. Not affected

Skid Assembly 206-023-110-001 (“Hooked”)

206 A/B +2.1 Lbs. +365.68 767.9 in-lbs. Not affected

206L

+2.1 Lbs. +401.20 842.5 in-lbs Not affected

M) Upon completion of this modification, make the appropriate entries in the helicopter logbook and component historical records.

[Blank Page]



64-00-48 Page 101 Jun 22/11

TESTING AND FAULT ISOLATION

[NOT APPLICABLE]



64-00-48 Page 202 Jun 22/11

[Blank Page]



64-00-48 Page 201 Jun 22/11

SCHEMATICS AND WIRING DESIGN

Figure 200-1:

Tail Rotor Hub Assembly – Disassembly / Assembly



64-00-48 Page 202 Jun 22/11

Figure 200-2:

Tail Rotor Hub Assembly – Disassembly / Assembly



64-00-48 Page 203 Jun 02/16

Figure 200-3:

Weight Installation

(OPTIONAL)



64-00-48 Page 204 Jun 02/16

DETAIL B – OPTIONAL WEIGHT INSTALLATION

Figure 200-4

Weight Installation – Optional



64-00-48 Page 301 Jun 02/16

DISASSEMBLY

Disassemble Tail Rotor Hub Assembly

Remove tail rotor hub and blade assembly from helicopter in accordance with applicable Bell 206 Maintenance Manual.

Disassemble tail rotor hub and blade assembly in accordance with applicable Bell 206 Component Repair & Overhaul Manual. (Reference Figure 200-1)

Disassemble the tail rotor hub assembly using the following procedure:

A. Cut lock wire and remove bolts (6), washers (5), weights (4) and brackets (3) from each side of yoke. Retain weights and extra washers for static balancing.

Note: If necessary, heat may be applied to the yoke to ease removal of flapping bearing. Do not allow flapping bearing to be exposed to heat higher than 160°F. When using heat, it is recommended to use a temperature indicator stick or calibrated optical pyrometer.

B. Remove flapping bearing (2) from the yoke (1).

[Blank Page]



64-00-48 Page 401 Jun 02/16

CLEANING

Cleaning

Note: The elastomeric flapping bearing should not be soaked or immersed in alcohol or come in contact with any other type of cleaning solvent.

It is recommended that the elastomeric portion of the flapping bearing be cleaned with warm soapy water (up to 140°F) to remove grease, oils and dirt. Denatured alcohol may also be used to clean the elastomer, however, should only be applied with a rag by wiping.

The brackets and the metal portion of the flapping bearing may be cleaned using aircraft cleaning solvents.

[Blank Page]



64-00-48 Page 501 Jun 22/11

INSPECTION / CHECK

1) Inspection / Check

Inspect and repair brackets in accordance with Figure 500-1.

Inspect flapping bearing for evidence of cracked shims, tears, elastomer separation, shims touching, voids in elastomer or elastomer sheeting or extrusion and those limits found in Figure 500-2.

Inspect and repair flapping bearing in accordance with Figures 500-3 and 500-4.

2) Airworthiness Limitations

There are no maximum airworthiness lives assigned to the components listed below.

Component Part Number Airworthiness Life

Flapping Bearing LB2-1010-20-2 Conditional

Bracket Y-27316-42-1 Conditional

3) Scheduled Inspections

A) 100 Hours and Annual: Visually inspect (without disassembly) tail rotor flapping bearing for evidence of cracked shims, tears, elastomer separation, shims touching, voids in elastomer or elastomer sheeting or extrusion.

B) 2,500 Hour Inspection: The flapping bearing, P/N LB2-1010-20-2, and brackets, P/N Y-27316-42-1, are to be inspected every 2,500 hours of operation in accordance with the inspection criteria found in paragraphs 1 and 3A.

4) Unscheduled Inspections

A) After Hard Landing:

If damage to fuselage structure, skid gear, or tailboom is such that a major repair, replacement or alignment is necessary, remove flapping bearing and brackets and conduct an inspection in accordance with paragraphs 1 and 3A.

B) After Sudden Stoppage / Acceleration: If sudden stoppage/acceleration has occurred as defined by the applicable Bell 206 Maintenance Manual, remove and scrap flapping bearing and brackets.

C) After Main Rotor Over Speed: If a main rotor over speed has occurred as defined by the applicable Bell 206 Maintenance Manual, remove flapping bearing and brackets and conduct an inspection in accordance with paragraphs 1 and 3.

D) After Over Torque: If an over torque has occurred, visually inspect (without disassembly) tail rotor flapping bearing for evidence of cracked shims, tears, elastomer separation, shims touching, voids in elastomer or elastomer sheeting or extrusion. Refer to paragraphs 1 and 3 for allowable limits.



64-00-48 Page 502 Jun 22/11

Type of Damage Maximum Damage or Repair Depth

Mechanical and Corrosion 0.010 inch before and after repair

Maximum Area per Full Depth Repair 0.150 square inch

Number of Repairs 2 per segment

Edge Chamfer to Remove Damage 0.010 inch x 45°

Cracks in Metal 0

Bores 0.002 inch for ¼ circumference

Blue Coat Chips or Cracks Less than 0.125” x 0.125”

Figure 500-1:

Bracket Damage Limits

1



64-00-48 Page 503 Jun 22/11

Figure 500-2:

Flapping Bearing Elastomer Inspection



64-00-48 Page 504 Jun 02/16

DESCRIPTION LOCATION

MIN. INCHES

MAX. INCHES

Trunnion Splines (Between 0.0450 Inch Diameter Pins)

ID 0.9546 0.9520

Bearing Outer Member OD 1.3730 1.3745

Overall Length 3.54 3.652

Note: Use pins with one side ground flat to provide clearance between pins and root of spine teeth.

Figure 500-3:

Flapping Bearing Wear Limits

1

3

2

1

3



64-00-48 Page 505 Jun 22/11

TYPE OF DAMAGE MAXIMUM DAMAGE OR REPAIR DEPTH

Mechanical and Corrosion

0.005 inch before and after repair 0.010 inch before and after repair

Maximum Area per Full Depth Repair

0.050 sq. inch 0.150 sq. inch

Number of Repairs One Two per segment

Edge Chamfer to Remove Damage

0.010 inch Two per segment

Cracks None allowed None allowed

Blue Coat N/A Less than 0.125” x 0.125”

Figure 500-4:

Flapping Bearing Damage Limits

[Blank Page]



64-00-48 Page 601 Jun 22/11

REPAIR

Procedures in the REPAIR section contain criteria necessary for restoring the Isolator Assembly to serviceable condition. Repair procedures shall be limited to correction of minor defects or damage. Refer to Section 500 (INSPECTION / CHECK) to determine reparability.

Bearings that exceed criteria noted in Section 500 (INSPECTION / CHECK) are to be returned to LORD Corporation.

WARNNING: DO NOT CHANGE SURFACE FINISH, PART SHAPE OR EXCEED WEAR LIMITS.

FAILURE TO COMPLY CAN RESULT IN PREMATURE FAILURE OF PART.

[Blank Page]



64-00-48 Page 701 Jun 02/16

ASSEMBLY

1) Tail Rotor Hub Assembly (Reference Figures 200-1 and 200-2)

Assemble the tail rotor hub assembly using the following procedure.

Note: If necessary, heat may be applied to the yoke to ease installation of flapping bearing. Do not allow flapping bearing to be exposed to heat higher than 160°F. When using heat, it is recommended to use a temperature indicator stick or calibrated optical pyrometer.

A) Install flapping bearing (2) in yoke (1) and align dovetail grooves as shown in Figure 200-1, View A.

B) Position brackets (3) in dovetail grooves of flapping bearing (2).

Note: Bolt (6) length, amount of washers (5) and weights (4) will be determined during static balance in accordance with applicable Bell 206 Component Repair & Overhaul Manual and Illustrated Parts Breakdown.

C) Install bolts (6) and washers (5) with only a few threads of the bolts engaged in the yoke. Do not torque bolts at this point. The bolts are used to keep the brackets aligned during the next step.

D) Using a 4” c-clamp or larger as shown in Figure 200-2, slowly tighten c-clamp until brackets contact yoke.

E) Torque bolts (6) 30 to 40 inch-pounds.

F) Install tail rotor blades in accordance with applicable 206 Component Repair & Overhaul Manual.

G) Perform static balance of the tail rotor hub and blade assembly (reference paragraph 2).

2) Static Balance

Static balance of the tail rotor hub and blade assembly will be performed in accordance with the applicable Bell 206 Component Repair & Overhaul Manual; however, the following exceptions will apply during chord wise balance.

A) When adding additional washers or weights to the bracket bolts, it will be necessary to loosen and add washers or weights to only one bolt at a time. Once the proper amount of weight has been determined, both bolts may be removed and the washers or weights can be distributed equally.

B) Once the proper amount of balance weights has been installed under the bolts, torque bolts 30 – 40 inch-pounds and lock wire.

Tail rotor hub and blade assembly is now ready for installation. The requirements for installation and dynamic balancing of the tail rotor with the elastomeric flapping bearing are the same as for a conventional bearing.

[Blank Page]



64-00-48 Page 801 Jun 22/11

FITS AND CLEARANCES

[NOT APPLICABLE]

[Blank Page]



64-00-48 Page 901 Jun 22/11

SPECIAL TOOLS, FIXTURES AND EQUIPMENT

[NOT APPLICABLE]

[Blank Page]



64-00-48 Page 1001

Jun 22/11


1. General Information

A. The Illustrated Parts List (IPL) provides a breakdown of assemblies, subassemblies and detail parts of the isolator assemblies. All parts are listed, except for parts that lose their identities by being permanently fastened to other parts or are part of an assembly not subject to disassembly.

B. Bulk materials such as safety or electrical wire and tape, and consumable materials such as adhesives, sealants, lubricants, solder, paint, and primer are not included in the Detailed Parts Lists. These materials are identified in the materials list at the beginning of each section.

C. To find a part number when the part number is unknown, locate the part on the illustration and note the item number. Locate the item number on the Detailed Parts List. The part number will be shown on the same line. In some instances there are gaps in item number sequence and the item numbers are not continuously sequential.

2. Explanation of Columns, Terms and Symbols in the Illustrated Parts List (IPL)

A. ITEM NO.

The item numbers key the Details Parts List to the applicable illustration. The item number corresponds to an item number on the illustration.

(1) An item number not on the illustration is identified by a dash (-) preceding the item number. This can indicate the following:

(a) When two or more visually alike parts are listed in sequence, only the first part is illustrated. The illustration, however, is applicable to both parts.

(b) When detail parts of an assembly or installation are separately illustrated, the resulting assembly may be illustrated as an assembly by bracketing the detail parts and identifying the bracket as the assembly. If brackets are not used, the detail parts are illustrated, but the assembly is not.

(2) An item number followed by an alphabetical character such as A, B, C, etc. indicates the part listed is similar to the same item number without the alphabetical character. The difference could be each part is used for a different next higher assembly (NHA) or is an equivalent part. This will be noted in the NOMENCLATURE or EFF CODE columns.

B. LORD PART NUMBER

This column contains the original manufacturer’s part number of the assembly, subassembly or detail part listed. Part numbers in the IPL are those of LORD Corporation, Erie, PA (76005) or are standard parts unless a Commercial and Government Entity (CAGE) code appears in the NOMENCLATURE column. Refer to paragraph 4 for details. The following phrases may be used in this column:

(1) “ORDER NHA” is used when no part number exists for the part listed or when it is preferable to order an assembly rather than detail parts. “ORDER NHA” items that have no part numbers are not procurable and should not be ordered. The next higher assembly, however, is procurable and may be ordered.

(2) ”NONPROC” followed by an assigned number (for example NONPROC123) is used when no part number exists for the assembly. NONPROC assemblies are not procurable



64-00-48 Page 1002

Jun 22/11

and may not be ordered. However, the detail parts of the assembly are procurable and may be ordered, unless otherwise specified.

(3) “REF” followed by an assigned number (for example REF001) is used when the part number of the part is more than fifteen digits. The original part number with more than fifteen digits is listed in the NOMENCLATURE column and is the part number to be used when ordering the part.

C. BELL PART NUMBER:

This column is reserved for BELL part numbers and accommodates eleven numbers.

D. NOMENCLATURE:

This column identifies the parts being listed by noun name followed by modifiers when applicable. This column also provides the following information.

(1) The relationship of each listed item to its next higher assembly (NHA) is shown by an indenture code. Each listed item is placed in the NOMENCLATURE column one indenture (one dot) to the right of the assembly to which it belongs. Items at equal indentures are all components of a single assembly or subassembly. An example of the indenture code system is shown below.

1 2 3 4 5 6 7 Assembly or Installation Descriptive Title ● Assembly ● Attaching Parts for Assembly ● ● Detail Parts for Assembly ● ● ● Subassembly ● ● ● Attaching Parts for Subassembly ● ● ● ● Detail Parts for Subassembly ● ● ● ● ● Sub-Subassembly ● ● ● ● ● Attaching Parts for Sub-Subassembly ● ● ● ● ● ● Detail Parts for Sub-Subassembly

(2) Symbols used, with the exception of effectivity and CAGE codes, are as follows:

(ATTACHING PARTS) Designates start of each group of attaching parts.

-----*----- Designates end of each group of attaching parts.

(3) The following phrases may be used in this column:

(a) “DELETED” identifies a part no longer used.

(b) “SUPERSEDED” identifies a part no longer authorized for use.

(c) “REPLACES” OR “REPLACES ITEM XXX” identifies this part is newer and therefore more desirable than the “REPLACED” part. However, either may be used.

(d) “REPLACED” or “REPL BY ITEM XXX” identifies this part is older and therefore less desirable than the “REPLACES” part. However, either may be used.



64-00-48 Page 1003 Jun 02/16

(e) “ALTN PART FOR ITEM XXX” identifies this part as an alternative. However, either part may be used and neither is more desirable than the other.

(f) “TPN” precedes a True Part Number with all dashes, slashes, spaces and/or symbols assigned by the original manufacturer of the part. This is the part number to be used when ordering the part.

E. EFF CODE:

This column establishes part relationship with assemblies that are essentially the same, but have minor variations. These assemblies are the end items on the Detailed Parts List and are assigned reference letters such as A, B, C, D, etc. Subassemblies or detail parts that are not common to all configurations, but are associated with one or more of the coded end items, carry the letters assigned to the end item(s) with which they are associated. If a part is common to all end items, the EFF CODE column is blank.

F. UNITS PER ASSY:

This column shows the quantity of each item required for the next higher subassembly, assembly or installation outline. Quantities shown for attaching parts are the number required for the related part, subassembly or assembly and, therefore, may not be the total quantity used for the end item of the Detail Parts List. The following letters may be used in this column.

(1) “AR” indicates, “as required” and refers to variable quantity items such as shims, spacers or similar items.

(2) “RF” indicates “reference” and refers to items and their quantities which are listed elsewhere and are provided here as a reference only.

3. Abbreviations

Standard abbreviations used in the IPL agree with ASME Y14.38

4. Commercial and Government Entity (CAGE) Codes

A. CAGE codes, preceded by the capital letter “V” (V12345), are used to identify the original manufacturer of non LORD Corporation (V76005) components. CAGE codes are listed in the NOMENCLATURE column, except for the government codes below which are not listed.

V96906 Military Standard (prefix MS) V88044 Army/Navy Standard (prefix AN) V80205 National Aircraft Standard (prefix NAS)

B. The following CAGE codes are listed in this IPL.

LORD 76005

5. Reference Designator Index (RDI)

Not Applicable

6. Numeric Index (NI)

Not Applicable

7. Overhauled Parts

Return parts to LORD for overhaul.



64-00-48 Page 1004 Jun 02/16


ITEM NO.

LORD PART NUMBER

BELL PART

NUMBER

NOMENCLATURE

1 2 3 4 5 6 7

EFF CODE

QTY/ ASSY

1000-1 LB2-1010-20-1 TAIL ROTOR FLAPPING BEARING KIT 1

5 LB2-1010-20-2 BONDED MOUNTING 1

10 Y-27316-42-1 BRACKET 2

15 Y-27316-43-1 IDENTIFICATION PLATE 1

Figure 1000-1

LB2-1010-20-1 Exploded View



64-00-48 Page 1005 Jun 02/16


ITEM NO.

LORD PART NUMBER

BELL PART

NUMBER

NOMENCLATURE

1 2 3 4 5 6 7

EFF CODE

QTY/ ASSY

1000-1 LB2-1010-20-1 TAIL ROTOR FLAPPING BEARING KIT

20 Y-27316-44-1 WEIGHT (Optional) 1

25 MS27039-0833 BOLT (Optional) 2

30 NAS1149DN832J WASHER (Optional) 4

35 MS21042L08 NUT (Optional) 2

40 Y-27316-45-1 DECAL 1

45 NAS6604D20 BOLT 1

50 NAS1149DO432K WASHER 2

55 MS14145L5 NUT 1

60 MS24665-151 COTTER PIN 1

Figure 1000-2

LB2-1010-20-1 Exploded View

[Blank Page]



64-00-48 Page 1101

Jun 22/11

SPECIAL PROCEDURES

[NOT APPLICABLE]

[Blank Page]



64-00-48 Page 1201

Jun 22/11

REMOVAL

[SEE AIRCRAFT MAINTENANCE MANUAL]

[Blank Page]



64-00-48 Page 1301

Jun 22/11

INSTALLATION

[SEE AIRCRAFT MAINTENANCE MANUAL]

[Blank Page]



64-00-48 Page 1401 Jun 02/16

SERVICING

1) SPARE PARTS / SUPPORT

Spare Parts, Repair and Remanufacturing

The following parts may be purchased directly from LORD Corporation. The LB2-1010-20-2 flapping bearing is available as a replacement part on an exchange basis.

Component Part Number

Tail Rotor Flapping Bearing Kit

LB2-1010-20-1

Flapping Bearing LB2-1010-20-2

Bracket Y-27316-42-1

MOD Plate Y-27316-43-1

Weight (Optional) Y-27316-44-1

Decal Y-27316-45-1

If spare parts, repair or manufacturing services are required, contact the following:

LORD Corporation LORD Aerospace MRO Services 2455 Robison Road West Erie, PA 16509-4675

Phone: 814-868-3180 E-mail: [email protected]

2) Technical Support Questions regarding the installation, use or maintenance of this kit should be directed to: LORD Corporation Customer Service 2455 Robison Road West Erie, PA 16509-4675

Phone: 814-868-3180 E-mail: [email protected]

[Blank Page]



64-00-48 Page 1501 Jun 02/16

STORAGE

1. Packaging and Storage Conditions

A. Packaging

Parts to be stored in original sealed packaging or in opaque, environmentally sealed packaging with desiccant. Parts should be packaged and stored in a relaxed position.

B. Temperature

Parts should be stored at room temperature defined as 72°F ± 9°F (22°C ± 5°C). Parts should not be stored at a temperature below 32°F (0°C) or above 100°F (38°C).

C. Humidity

Parts to be stored at minimum possible relative humidity and away from all sources of moisture.

D. Light

Parts to be stored away from light sources, such as sunlight and artificial light with high levels of ultra-violet content.

E. Environment

Parts to be stored away from degrading environments such as ozone and ozone generating equipment, fluids and fluid vapors deleterious to elastomerics such as solvents, oils, and greases, and harmful solids such as copper and manganese. Parts should also be stored away from sources of ionizing radiation.

2. Preservatives

Do not apply preservatives or solvents to any part of the Isolator Assembly as it may adversely affect the function and/or life of the part.

[Blank Page]

64-00-48 Page 1601

Jun 22/11

REWORK (SERVICE BULLETINS)

[NOT APPLICABLE]

64-00-48 Page 1601

Jun 22/11

[Blank Page]

Documents

[Blank Page] - Lord Corporation (Rev 3).pdfP/N Y-27316-44-1, which may be installed on the Bell 206 tail skid as needed, to assist in the dynamic balancing of the tail rotor hub and