Commercial 

Airplanes 777

Service Bulletin

Number: 777-32-0085

Original Issue: April 14, 2011

ATA System: 3200

SUBJECT: LANDING GEAR - Main Landing Gear - Center Axle and Pivot Joint Configuration

Change

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

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Copyright © 2011 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

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BOEING SERVICE BULLETIN 777-32-0085

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 22

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 1: CENTER AXLE CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

FIGURE 2: INNER CYLINDER CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

APPENDIX A: PART MARKING REIDENTIFICATION TABLE . . . . . . . . . . . . . . . . . . . . . . . . 30

APPENDIX B: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY INTERCHANGEABILITY

BASED ON AIRPLANE MINOR MODEL . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

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BOEING SERVICE BULLETIN 777-32-0085
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BOEING SERVICE BULLETIN 777-32-0085

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-32-0085

Original Issue: April 14, 2011

ATA System: 3200

SUBJECT: LANDING GEAR - Main Landing Gear - Center Axle and Pivot Joint Configuration

Change

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

Accomplishment of this service bulletin will change the configuration of the main landing gear (MLG) pivot joint

to reduce the amount of heat generated in the center axle and the shock strut inner cylinder lugs during takeoff

and landing. High levels of heat in the pivot joint can result in damage to the center axle and inner cylinder lugs

which could result in significant manpower and airplane downtime to repair.

During MLG overhaul, 39 center axles have been found with cracks or heat damage at the inner cylinder/truck

beam pivot joint location. There have been no reports of a center axle fracture. There have been no reports of

heat damage in the inner cylinder pivot bores. Heat damage and cracks were found at the pivot joint location

which is caused by the truck pitching motion during normal airplane operations. Cracks were found in areas

common to the inner cylinder pivot bushings where heat damage had occurred.

This service bulletin provides the instructions to change the configuration of the center axle assemblies and

shock strut inner cylinder assemblies of the MLGs to reduce friction in the pivot joint. Reduced friction in the

pivot joint will lead to a lower amount of heat in the pivot joint which will extend the service life of the parts.

Incorporation of the changes in accordance with this service bulletin and a final, one-time inspection of the pivot

joint in accordance with Boeing Service Bulletin (SB) 777-32A0082, Part 2 is terminating action to the repeat

inspections of SB 777-32A0082, Part 2.

Incorporation of the changes in accordance with this service bulletin and incorporation of the lubrication

requirements in accordance with 777 MPD Section 9, 32-CMR-01 is terminating action to the repeat lubrications

of SB 777-32A0082, Part 1.

Boeing Service Related Problem (SRP) 777-SRP-32-0159 is related to this service bulletin.

Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin.

ACTION (PRR 62777-70S)

Get access to the left and right MLG wheel wells. Remove the landing gear center axles of both MLGs. Replace

the center axles or change the center axles by polishing to the new configuration. Remove the inner cylinder

bushings and install new inner cylinder bushings. Part mark the MLG components and assemblies. Lubricate

the pivot joint with new grease.

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Update maintenance program in accordance with 777 MPD Section 9, 32-CMR-01 to do periodic lubrications

of the MLG pivot joint.

EFFECTIVITY

777-200, -300, -200LR, -300ER and 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected

airplane(s).

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks given in this service bulletin mandatory.

No compliance time is given.

Boeing recommends this service bulletin be done to introduce improvements.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 777-32-0085

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Number: 777-32-0085

Original Issue: April 14, 2011

ATA System: 3200

SUBJECT: LANDING GEAR - Main Landing Gear - Center Axle and Pivot Joint Configuration

Change

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 62777-70S for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 777-200LR, -300ER and 777F Airplanes with line number 423- 914.

2 - 777-200 and -300 Airplanes with line number 1- 868.

Airplane Models:

777-200, 777-200LR, 777-300, 777-300ER, 777F

Variable Number Group

WA001 - WA017 2

WA076 - WA080 2

WA086 - WA093 2

WA101 - WA104 2

WA116 - WA119 2

WA131 - WA137 2

WA171 - WA175 2

WA196 - WA198 2

WA206 - WA212 2

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Variable Number Group

WA221 - WA223 2

WA231 - WA232 2

WA241 - WA250 2

WA261 - WA266 2

WA281 - WA283 2

WA301 - WA304 2

WB001 - WB021 2

WB031 - WB046 2

WB051 - WB088 2

WB101 - WB106 2

WB121 - WB125 2

WB131 - WB148 2

WB151 - WB155 2

WB161 - WB177 2

WB181 - WB194 2

WB201 - WB215 2

WB231 - WB247 2

WB271 - WB273 2

WB276 - WB286 2

WB291 - WB302 2

WB306 - WB307 2

WB311 - WB337 2

WB341 - WB342 2

WB366 - WB368 2

WB371 - WB388 2

WB406 2

WB411 - WB413 2

WB416 - WB439 2

WB446 - WB453 2

WB476 2

WB481 - WB484 2

WB501 - WB512 2

WB531 - WB537 2

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BOEING SERVICE BULLETIN 777-32-0085
Variable Number Group

WB551 - WB554 2

WB591 - WB597 2

WB601 - WB606 2

WB611 - WB622 2

WB631 - WB638 2

WB646 - WB649 2

WC051 - WC073 2

WC101 - WC104 2

WC111 - WC120 2

WC221 - WC224 2

WC241 - WC243 2

WC281 - WC290 2

WC301 - WC308 2

WC361 - WC364 2

WC371 - WC374 2

WC381 - WC395 2

WC441 2

WC446 - WC449 2

WC456 - WC459 2

WC486 - WC493 2

WC506 - WC508 2

WC521 - WC522 2

WC531 - WC536 2

WC546 - WC548 2

WC556 2

WC566 - WC567 2

WC571 - WC574 2

WC581 2

WD001 - WD002 1

WD011 - WD018 1

WD031 - WD036 1

WD046 - WD055 1

WD066 - WD075 1

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BOEING SERVICE BULLETIN 777-32-0085
Variable Number Group

WD081 - WD088 1

WD091 1

WD096 1

WD101 - WD103 1

WD501 - WD513 1

WD521 - WD541 1

WD546 - WD554 1

WD561 - WD573 1

WD581 - WD599 1

WD606 - WD609 1

WD621 - WD632 1

WD651 - WD665 1

WD671 - WD676 1

WD691 - WD709 1

WD741 - WD752 1

WD761 - WD771 1

WD786 - WD788 1

WD796 - WD813 1

WD826 - WD837 1

WD846 - WD861 1

WD871 - WD883 1

WD911 - WD914 1

WD921 - WD922 1

WD936 - WD939 1

WD946 - WD951 1

WD966 - WD970 1

WD981 - WD982 1

WD986 - WD987 1

WD996 1

WE001 - WE004 1

WE011 - WE012 1

WE021 - WE024 1

WE031 1

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BOEING SERVICE BULLETIN 777-32-0085
Variable Number Group

WE051 - WE052 1

WE071 1

WE081 - WE082 1

WE126 - WE131 1

WF001 - WF004 1

WF016 - WF020 1

WF031 - WF032 1

WF046 - WF053 1

WF076 - WF077 1

WF081 - WF088 1

WF096 - WF099 1

WF106 - WF107 1

WF111 - WF112 1

WF121 1

2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for

the recommended use.

B. Concurrent Requirements

The service bulletin listed below must be done at the same time as this service bulletin:

Company Service Bulletin Description

A final one-time inspection of the pivot joint

in accordance with Part 2 - MLG Pivot Joint

Inspection is required for terminating action

of the repeat inspections.

The Boeing Company 777-32A0082 Original Issue

C. Reason

Accomplishment of this service bulletin will change the configuration of the main landing gear (MLG)

pivot joint to reduce the amount of heat generated in the center axle and the shock strut inner cylinder

lugs during takeoff and landing. High levels of heat in the pivot joint can result in damage to the center

axle and inner cylinder lugs which could result in significant manpower and airplane downtime to repair.

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BOEING SERVICE BULLETIN 777-32-0085
During MLG overhaul, 39 center axles have been found with cracks or heat damage at the inner

cylinder/truck beam pivot joint location. There have been no reports of a center axle fracture. There

have been no reports of heat damage in the inner cylinder pivot bores. Heat damage and cracks were

found at the pivot joint location which is caused by the truck pitching motion during normal airplane

operations. Cracks were found in areas common to the inner cylinder pivot bushings where heat damage

had occurred.

This service bulletin provides the instructions to change the configuration of the center axle assemblies

and shock strut inner cylinder assemblies of the MLGs to reduce friction in the pivot joint. Reduced

friction in the pivot joint will lead to a lower amount of heat in the pivot joint which will extend the service

life of the parts.

Incorporation of the changes in accordance with this service bulletin and a final, one-time inspection

of the pivot joint in accordance with Boeing Service Bulletin (SB) 777-32A0082, Part 2 is terminating

action to the repeat inspections of SB 777-32A0082, Part 2.

Incorporation of the changes in accordance with this service bulletin and incorporation of the lubrication

requirements in accordance with 777 MPD Section 9, 32-CMR-01 is terminating action to the repeat

lubrications of SB 777-32A0082, Part 1.

Boeing Service Related Problem (SRP) 777-SRP-32-0159 is related to this service bulletin.

Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin.

D. Description

Get access to the left and right MLG wheel wells. Remove the landing gear center axles of both MLGs.

Replace the center axles or change the center axles by polishing to the new configuration. Remove

the inner cylinder bushings and install new inner cylinder bushings. Part mark the MLG components

and assemblies. Lubricate the pivot joint with new grease.

Update maintenance program in accordance with 777 MPD Section 9, 32-CMR-01 to do periodic

lubrications of the MLG pivot joint.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300ER, 777F 731, 741

Group 2:

Affected Maintenance Zones

Model Zone

777-200, 777-300 731, 741

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BOEING SERVICE BULLETIN 777-32-0085
E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks given in this service

bulletin mandatory.

No compliance time is given.

Boeing recommends this service bulletin be done to introduce improvements.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this change for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Open Access 5 13.00 2.60

Part 1: Figure 1 (a) 4 36.00 9.00

Part 2: Figure 2 4 16.00 4.00

Close Access 5 13.00 2.60

TOTAL FOR EACH AIRPLANE 78.00 18.20

(a) Polish task is variable in nature and is not included in estimate.

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BOEING SERVICE BULLETIN 777-32-0085
H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All Airplanes + 2.4 + 3254.5

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Engineering Change Memo PRR 62777-70S

b. Boeing Service Bulletin 777-32A0082

c. Boeing Service Letter 777-SL-32-001, 777-SL-32-059

d. Boeing Service Related Problem (SRP) 777-SRP-32-0159

e. Component Maintenance Manual (CMM) 32-11-03, 32-11-07, 32-11-64, 32-11-65

f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-42-03, 20-42-10, 20-50-10,

20-60-02

g. 777 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-30, 32-11-26

h. 777 Maintenance Planning Data (MPD) Section 9, 32-CMR-01

2. Data supplied with this Service Bulletin

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

Misc Tool Replacement and Honing Kit In- 1 B -

ner Cyl Ctr Axle

MIT161W1122

2 - -

3 - -

3. Installation Drawings Used in the Preparation of this Service Bulletin

Drawing Number Title

161W0000 Installation - Main Landing Gear

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

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BOEING SERVICE BULLETIN 777-32-0085
K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Aircraft Maintenance Manual 12-21, 32-11

777 Illustrated Parts Catalog 32-11

Component Maintenance Manual 32-11

777 Maintenance Planning Data Document Section 9, ATA 32

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

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BOEING SERVICE BULLETIN 777-32-0085
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BOEING SERVICE BULLETIN 777-32-0085

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The parts are subject to the terms and conditions of the Boeing standard purchase order

acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

Group 1:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Part Number Name

161W1122-4 (a) Bushing - Inner Cylinder, Main Landing Gear 160 $5,166.00

161W1122-5 (b) Bushing - Inner Cylinder, Main Landing Gear 160 $4,685.00

161W1163-21 Axle Assembly - Center, Main Landing Gear 608 $59,569.00

(a) This part can be fabricated. Refer to CMM 32-11-65 as an accepted procedure.

(b) This is an oversized part.

Group 2:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Part Number Name

161W1122-4 (a) Bushing - Inner Cylinder, Main Landing Gear 160 $5,166.00

161W1122-5 (b) Bushing - Inner Cylinder, Main Landing Gear 160 $4,685.00

161W1163-19 Axle Assembly - Center, Main Landing Gear 608 $56,569.00

(a) This part can be fabricated. Refer to CMM 32-11-03 as an accepted procedure.

(b) This is an oversized part.

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BOEING SERVICE BULLETIN 777-32-0085
B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

Group 1:

Part Number QTY Name Notes

Bushing - Inner Cylinder, Main (a)

Landing Gear

161W1122-4 4

Bushing - Inner Cylinder, Main (b)

Landing Gear

161W1122-5 4

Axle Assembly - Center, Main

Landing Gear

161W1163-21 2

(a) This part can be fabricated. Refer to CMM 32-11-65 as an accepted procedure.

(b) This is an oversized part.

Group 2:

Part Number QTY Name Notes

Bushing - Inner Cylinder, Main (a)

Landing Gear

161W1122-4 4

Bushing - Inner Cylinder, Main (b)

Landing Gear

161W1122-5 4

Axle Assembly - Center, Main

Landing Gear

161W1163-19 2

(a) This part can be fabricated. Refer to CMM 32-11-03 as an accepted procedure.

(b) This is an oversized part.

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

MIL-PRF-32014 - Grease

BMS 5-95 - Sealant (a)

BMS 10-60, Type - Enamel (a)

II

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BOEING SERVICE BULLETIN 777-32-0085
Part Number / QTY Name Notes

Specification

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

3. Parts Modified and Reidentified

Refer to APPENDIX A for Part Marking and Reidentification.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service

Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the

date the tools will be used.

Purchase Data:

Tool Kit Number Name Unit Price

Contact Boeing

Spares for Current

Pricing Information

Misc Tool - Bushing Replacement and Honing Kit - Inner Cyl

Ctr Axle

MIT161W1122

The kits are subject to the terms and conditions of the Boeing standard purchase order

acknowledgement. After the Price date, new price data is applicable. Prices are in United States dollars.

Terms: Net 30 days.

Reference this service bulletin number and submit purchase order by one of the methods that follow:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

(Service Bulletin 777-32-0085)

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BOEING SERVICE BULLETIN 777-32-0085
F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

necessary. Examine operator tool supply to make sure all necessary tools are available.

Tool Kit Number Name

Misc Tool - Bushing Replacement and Honing Kit - Inner Cyl

Ctr Axle

MIT161W1122

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BOEING SERVICE BULLETIN 777-32-0085
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

5. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

6. Refer to APPENDIX A for Part Marking Reidentification.

B. WORK INSTRUCTIONS

Airplane Work

1. Install the main landing gear (MLG) and nose landing gear (NLG) downlock pins. Refer to 777

AMM 32-00-30 as an accepted procedure.

2. Install the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

3. Remove the left and right MLG center axles. Refer to 777 AMM 32-11-26 as an accepted procedure.

4. Change both the left and right MLG center axles in accordance with Part 1 - Center Axle Change.

5. Change both the left and right MLG inner cylinder assemblies in accordance with Part 2 - Inner

Cylinder Change.

6. Install the left and right MLG changed center axles. Refer to 777 AMM 32-11-26 as an accepted

procedure.

7. Lubricate the MLG pivot joint using MIL-PRF-32014 grease. Refer 777 AMM 12-21-14 as an

accepted procedure.

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BOEING SERVICE BULLETIN 777-32-0085
8. Apply new part mark to the left and right MLG component and buildup assemblies. Refer to SOPM

20-50-10 as an accepted procedure. Refer to APPENDIX A for new part numbers.

9. Remove the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

10. Remove the MLG and NLG downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure.

11. Put the airplane back into serviceable condition.

12. Update maintenance program in accordance with 777 MPD Section 9, 32-CMR-01 to do periodic

lubrications of the MLG pivot joint. Use MIL-PRF-32014 grease only. Refer to 777 AMM 12-21-14

as an accepted procedure.

PART 1 - CENTER AXLE CHANGE

1. Option 1: Replace existing center axle assembly with new, overhauled or serviceable center axle

assembly, as applicable. Refer to APPENDIX B for part number applicability.

2. Option 2: Change the existing center axle assembly in accordance with FIGURE 1.

PART 2 - INNER CYLINDER CHANGE

1. Option 1: Replace existing inner cylinder assembly with new, overhauled or serviceable inner

cylinder assembly, as applicable. Refer to APPENDIX B for part number applicability.

2. Option 2: Change existing inner cylinder assembly in accordance with FIGURE 2.

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BOEING SERVICE BULLETIN 777-32-0085
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Polish, lap or redress the chrome

plate on the center

journal outside diameter to a surface

roughness of 8 Ra

or better. Refer to

SOPM 20-42-03 as

an accepted procedure. Grinding of the

chrome plate is not

allowed. Operations

which produce

sparks are not allowed. (a)

1 Polish Center Axle - 1

to center axle and

center axle assembly. Refer to CMM

32-11-07, Repair 7-

2 or CMM 32-11-64,

Repair 5-2 as an accepted procedure,

as applicable. Refer

to APPENDIX A for

new part numbers

and part marking

methods.

2 Apply Part Mark - -

FIGURE 1: CENTER AXLE CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-32-0085
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Restore any damaged finishes. Refer

to CMM 32-11-07,

Repair 7-2 or CMM

32-11-64, Repair 5-

2 as an accepted

procedure, as applicable.

3 Apply Finishes - -

(a) If using cooling fluid during polishing, remove wheel sleeves prior to polishing. Reinstall wheel sleeves

after polishing. Refer to CMM 32-11-07, Repair 7-1 or CMM 32-11-64, Repair 5-1 as an accepted procedure,

as applicable.

FIGURE 1: CENTER AXLE CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0085
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to tool

MIT161W1122 instructions.

161W1122-2 2

(161W1122-1 or

161W1122-3 optional)

1 Remove Bushing, Inner Cylinder

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Bore and - -

Faces

2 Clean

FIGURE 2: INNER CYLINDER CHANGE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-32-0085
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Restore any cadmium plating and any

primer that is missing. Refer to CMM

32-11-03, Repair 4-

2 or CMM 32-11-65,

Repair 5-2, as applicable, and SOPM

20-42-10 as accepted procedures.

3 Apply Finishes - -

Refer to CMM 32-

11-03, Repair 4-1 or

CMM 32-11-65, Repair 5-1 as an accepted procedure,

as applicable. Refer

to tool

MIT161W1122 instructions.

161W1122-4 2

(161W1122-5 optional)

4 Install (New) Bushing, Inner Cylinder

at the lubrication fittings until grease

appears in bushing

inner diameter at all

through-wall hole locations. Temporary

plugging of individual bushing holes is

allowed to make

sure grease gets to

all through-wall hole

locations. Refer to

CMM 32-11-03, Repair 4-1 or CMM 32-

11-65, Repair 5-1 as

an accepted procedure, as applicable.

5 Apply Grease MIL-PRF-32014 -

FIGURE 2: INNER CYLINDER CHANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-32-0085
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Lug - 4

Faces

6 Clean

Fillet seal bushing

flange and shank

end. Refer to CMM

32-11-03, Repair 4-

1 or CMM 32-11-65,

Repair 5-1 as an accepted procedure,

as applicable.

Apply Sealant BMS 5-95 -

Refer to SOPM 20-

60-02 as an accepted procedure. Use

color 707 Gray.

Apply Enamel BMS 10-60 TYPE II -

as necessary to

meet the dimensional requirements. Refer to CMM 32-11-

03, Repair 4-1 or

CMM 32-11-65, Repair 5-1 as an accepted procedure,

as applicable. Refer

to tool

MIT161W1122 instructions. (a) (b)

161W1122-4 2

(161W1122-5 optional)

7 Hone Bushing, Inner Cylinder

to inner cylinder assembly. Refer to

SOPM 20-50-10,

code RH as an accepted procedure.

Refer to APPENDIX

A for new part numbers and part marking methods. Remove existing part

markings.

8 Apply Part Mark - -

(a) Bushing bores must be concentric within 0.0005 inches.

(b) Final bushing bore diameters must be within 0.0015 inches of each other.

FIGURE 2: INNER CYLINDER CHANGE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-32-0085
Group 1:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Center Axle Component and Assembly

Rubber Stamp, Code (a) (b)

RH (e)

161W1163-9 Center Axle Assembly 161W1163-9

Electrochemical Etch or (a) (b)

Vibro-engrave (e)

161W1163-10 . Center Axle 161W1163-10

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1163-15 Center Axle Assembly 161W1163-21

(a) (c)

(d)

Electrochemical Etch or

Vibro-engrave (e)

161W1163-16 . Center Axle 161W1163-22

Inner Cylinder Assembly

Rubber Stamp, Code (a) (b)

RH (e)

Inner Cylinder Assem- 161W2120-1

bly

161W2120-1

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

Inner Cylinder Assem- 161W2120-5

bly

161W2120-3

MLG Component Assembly

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W2100-1

sembly

161W2100-1

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W2100-2

sembly

161W2100-2

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W2100-7

sembly

161W2100-3

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W2100-8

sembly

161W2100-4

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W2100-9

sembly

161W2100-5

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W2100-10

sembly

161W2100-6

MLG Buildup Assembly

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-43 MLG Buildup Assembly 161W1000-43

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-44 MLG Buildup Assembly 161W1000-44

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-45 MLG Buildup Assembly 161W1000-45

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-46 MLG Buildup Assembly 161W1000-46

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 1 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Group 1:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-55 MLG Buildup Assembly 161W1000-55

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-56 MLG Buildup Assembly 161W1000-56

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-57 MLG Buildup Assembly 161W1000-57

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-58 MLG Buildup Assembly 161W1000-58

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-59 MLG Buildup Assembly 161W1000-83

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-60 MLG Buildup Assembly 161W1000-84

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-67 MLG Buildup Assembly 161W1000-67

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-68 MLG Buildup Assembly 161W1000-68

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-69 MLG Buildup Assembly 161W1000-69

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-70 MLG Buildup Assembly 161W1000-70

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-71 MLG Buildup Assembly 161W1000-81

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-72 MLG Buildup Assembly 161W1000-82

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-73 MLG Buildup Assembly 161W1000-73

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-74 MLG Buildup Assembly 161W1000-74

(a) Make the change in accordance with this service bulletin.

(b) There is no equivalent Boeing part number for the changed part. Identify on the part that the change

done in accordance with this service bulletin was made.

(c) This is the part number after the change is done in accordance with this service bulletin.

(d) This part is used in production.

(e) Refer to SOPM 20-50-10 as an accepted procedure.

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 2 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Group 2:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Center Axle Component and Assembly

Rubber Stamp, Code (a) (b)

RH (e)

161W1163-1 Center Axle Assembly 161W1163-1

Electrochemical Etch or (a) (b)

Vibro-engrave (e)

161W1163-2 . Center Axle 161W1163-2

Rubber Stamp, Code (a) (b)

RH (e)

161W1163-3 Center Axle Assembly 161W1163-3

Electrochemical Etch or (a) (b)

Vibro-engrave (e)

161W1163-4 . Center Axle 161W1163-4

Rubber Stamp, Code (a) (b)

RH (e)

161W1163-5 Center Axle Assembly 161W1163-5

Electrochemical Etch or (a) (b)

Vibro-engrave (e)

161W1163-6 . Center Axle 161W1163-6

Rubber Stamp, Code (a) (b)

RH (e)

161W1163-7 Center Axle Assembly 161W1163-7

Electrochemical Etch or (a) (b)

Vibro-engrave (e)

161W1163-8 . Center Axle 161W1163-8

Rubber Stamp, Code (a) (b)

RH (e)

161W1163-9 Center Axle Assembly 161W1163-9

Electrochemical Etch or (a) (b)

Vibro-engrave (e)

161W1163-10 . Center Axle 161W1163-10

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1163-11 Center Axle Assembly 161W1163-17

(a) (c)

(d)

Electrochemical Etch or

Vibro-engrave (e)

161W1163-12 . Center Axle 161W1163-18

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1163-13 Center Axle Assembly 161W1163-19

(a) (c)

(d)

Electrochemical Etch or

Vibro-engrave (e)

161W1163-14 . Center Axle 161W1163-20

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1163-15 Center Axle Assembly 161W1163-21

(a) (c)

(d)

Electrochemical Etch or

Vibro-engrave (e)

161W1163-16 . Center Axle 161W1163-22

Inner Cylinder Assembly

Rubber Stamp, Code (a) (b)

RH (e)

Inner Cylinder Assem- 161W1120-3

bly

161W1120-3

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 3 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Group 2:

Existing Part Number Component Name New Part Number Part Marking Method Notes

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

Inner Cylinder Assem- 161W1120-7

bly

161W1120-5

Rubber Stamp, Code (a) (b)

RH (e)

Inner Cylinder Assem- 161W1255-1

bly

161W1255-1

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

Inner Cylinder Assem- 161W1255-9

bly

161W1255-5

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

Inner Cylinder Assem- 161W1255-10

bly

161W1255-7

MLG Component Assembly

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-1

sembly

161W1100-1

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-2

sembly

161W1100-2

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-3

sembly

161W1100-3

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-4

sembly

161W1100-4

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-5

sembly

161W1100-5

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-6

sembly

161W1100-6

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-7

sembly

161W1100-7

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-8

sembly

161W1100-8

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-9

sembly

161W1100-9

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-10

sembly

161W1100-10

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-11

sembly

161W1100-11

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-12

sembly

161W1100-12

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-15

sembly

161W1100-15

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 4 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Group 2:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-16

sembly

161W1100-16

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-17

sembly

161W1100-17

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-18

sembly

161W1100-18

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-19

sembly

161W1100-19

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-20

sembly

161W1100-20

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-21

sembly

161W1100-21

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-22

sembly

161W1100-22

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-23

sembly

161W1100-23

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-24

sembly

161W1100-24

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W1100-33

sembly

161W1100-25

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W1100-34

sembly

161W1100-26

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W1100-35

sembly

161W1100-27

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W1100-36

sembly

161W1100-28

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W1100-37

sembly

161W1100-29

(a) (c)

(d)

Name Plate Vibro-engrave (e)MLG Component As- 161W1100-38

sembly

161W1100-30

Name Plate Vibro-en- (a) (b)

grave (e)

MLG Component As- 161W1100-31

sembly

161W1100-31

MLG Buildup Assembly

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-3 MLG Buildup Assembly 161W1000-3

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 5 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Group 2:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-4 MLG Buildup Assembly 161W1000-4

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-5 MLG Buildup Assembly 161W1000-5

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-6 MLG Buildup Assembly 161W1000-6

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-7 MLG Buildup Assembly 161W1000-7

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-8 MLG Buildup Assembly 161W1000-8

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-9 MLG Buildup Assembly 161W1000-9

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-10 MLG Buildup Assembly 161W1000-10

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-11 MLG Buildup Assembly 161W1000-11

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-12 MLG Buildup Assembly 161W1000-12

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-13 MLG Buildup Assembly 161W1000-13

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-14 MLG Buildup Assembly 161W1000-14

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-15 MLG Buildup Assembly 161W1000-15

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-16 MLG Buildup Assembly 161W1000-16

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-17 MLG Buildup Assembly 161W1000-17

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-18 MLG Buildup Assembly 161W1000-18

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-19 MLG Buildup Assembly 161W1000-19

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-20 MLG Buildup Assembly 161W1000-20

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-21 MLG Buildup Assembly 161W1000-21

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 6 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Group 2:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-22 MLG Buildup Assembly 161W1000-22

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-23 MLG Buildup Assembly 161W1000-23

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-24 MLG Buildup Assembly 161W1000-24

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-25 MLG Buildup Assembly 161W1000-25

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-26 MLG Buildup Assembly 161W1000-26

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-27 MLG Buildup Assembly 161W1000-27

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-28 MLG Buildup Assembly 161W1000-28

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-35 MLG Buildup Assembly 161W1000-35

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-36 MLG Buildup Assembly 161W1000-36

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-37 MLG Buildup Assembly 161W1000-37

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-38 MLG Buildup Assembly 161W1000-38

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-39 MLG Buildup Assembly 161W1000-39

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-40 MLG Buildup Assembly 161W1000-40

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-41 MLG Buildup Assembly 161W1000-41

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-42 MLG Buildup Assembly 161W1000-42

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-47 MLG Buildup Assembly 161W1000-47

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-48 MLG Buildup Assembly 161W1000-48

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-49 MLG Buildup Assembly 161W1000-49

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 7 OF 8)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: April 14, 2011

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BOEING SERVICE BULLETIN 777-32-0085
Group 2:

Existing Part Number Component Name New Part Number Part Marking Method Notes

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-50 MLG Buildup Assembly 161W1000-50

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-51 MLG Buildup Assembly 161W1000-51

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-52 MLG Buildup Assembly 161W1000-52

Rubber Stamp, Code (a) (b)

RH (e)

161W1000-53 MLG Buildup Assembly 161W1000-53

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-61 MLG Buildup Assembly 161W1000-75

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-62 MLG Buildup Assembly 161W1000-76

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-63 MLG Buildup Assembly 161W1000-77

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-64 MLG Buildup Assembly 161W1000-78

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-65 MLG Buildup Assembly 161W1000-79

(a) (c)

(d)

Rubber Stamp, Code

RH (e)

161W1000-66 MLG Buildup Assembly 161W1000-80

(a) Make the change in accordance with this service bulletin.

(b) There is no equivalent Boeing part number for the changed part. Identify on the part that the change

done in accordance with this service bulletin was made.

(c) This is the part number after the change is done in accordance with this service bulletin.

(d) This part is used in production.

(e) Refer to SOPM 20-50-10 as an accepted procedure.

APPENDIX A: PART MARKING REIDENTIFICATION TABLE

(SHEET 8 OF 8)

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BOEING SERVICE BULLETIN 777-32-0085
Applicable Inner Cylinder

Assemblies (a)

Applicable Center Axle

Assemblies (a)

Maximum Taxi Gross

Weight

Airplane Model

161W1163-1, -3, -5, -7, -9, 161W1120-3, -7 (b)

-17, -19, -21 (b)

777-200 547,000 lbs

161W1255-1, -9, -10 (b)

161W1163-1, -3, -5, -7, -9, 161W1255-1, -9, -10 (b)

-17, -19, -21 (b)

777-200ER 652,000 lbs

161W1163-3, -7, -9, -19, - 161W1255-10 (b)

21 (b)

777-200ER/IGW 658,000 lbs

161W1163-3, -7, -9, -19, - 161W1255-10 (b)

21 (b)

777-300 662,000 lbs

777-200LR 768,800 lbs 161W1163-9, -21 (b) 161W2120-1, -5 (b)

777-300ER 777,000 lbs 161W1163-9, -21 (b) 161W2120-1, -5 (b)

777F 768,800 lbs 161W1163-9, -21 (b) 161W2120-1, -5 (b)

(a) Refer to 777-SL-32-001 for additional interchangeability information.

(b) Make sure every part used has been changed in accordance with this service bulletin.

APPENDIX B: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY INTERCHANGEABILITY

BASED ON AIRPLANE MINOR MODEL

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-32-0085