Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0080

Original Issue: July 10, 2008

Revision 1: April 16, 2009

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder

Pivot Joint - Lubrication and Inspection

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

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2008 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Unpublished Work - All Rights Reserved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.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all

trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document

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3.0
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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ..................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 32

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 34

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 35

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 1: LEFT MLG CENTER AXLE INSPECTION [Group 1, Configuration 2-5] . . . . . . . . . . 41

FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION [Group 1, Configuration 2-5] . . . . . . . . . . 43

FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION [Group 1, Configuration 2-5] . . . 45

FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION [Group 1, Configuration 2-5] . . 47

FIGURE 5: LEFT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION [Group

1, Configuration 2-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

FIGURE 6: RIGHT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION [Group

1, Configuration 2-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE INSPECTION [Group 1, Configuration 2-5] . . 55

FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION [Group 1, Configuration 2-5] . 58

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BOEING SERVICE BULLETIN 777-32-0080
FIGURE 9: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT [Group

1, Configuration 2-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

FIGURE 10: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT [Group

1, Configuration 2-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT

INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL . . . . . . . . . . . . . 71

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BOEING SERVICE BULLETIN 777-32-0080
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Revision Transmittal Sheet Number: 777-32-0080

Original Issue: July 10, 2008

Revision 1: April 16, 2009

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder

Pivot Joint - Lubrication and Inspection

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

777F Airplanes were added to Group 1 of this service bulletin effectivity.

No more work is necessary on airplanes inspected or changed in accordance with the original issue of this

service bulletin but continued lubrication, inspection and repair is necessary for airplanes that operate at SWR

Level 2 runways.

REASON FOR REVISION

This revision is sent to revise the Accomplishment Instructions to provide more detailed inspections and repairs.

This revision is also sent to revise the Compliance Tables to allow for more time before inspections on airplanes

with low DME SWR Level 2 runway visits.

These sections were changed:

1. In Paragraph 1.A., Effectivity, added information about the PRR created for the new tool designed for

Revision 1 of this service bulletin.

2. In Paragraph 1.C., Reason, added references to Boeing Service Letters (SL) that are related to this service

bulletin.

3. In Paragraph 1.C., Reason, added references to a Boeing Fleet Team Digest article (FTD) that is related

to this service bulletin.

4. In Paragraph 1.D., Description, added text describing inspections of the inner cylinder bushings.

5. In Paragraph 1.E., Compliance, revised the title and compliance information of Table 2.

6. In Paragraph 1.E., Compliance, revised the title and compliance information of Table 3.

7. In Paragraph 1.E., Compliance, added Table 4 and Table 5.

8. In Paragraph 1.G., Manpower, revised the task Part 2.

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9. In Paragraph 1.G., Manpower, added the task Part 3, Part 4, Part 5 and Part 6.

10. In Paragraph 1.K., Publications Affected, added information about Damage Tolerance Based Structural

Inspections.

11. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added Corrosion Inhibiting Compound.

12. In Paragraph 2.E., Special Tooling - Price and Availability, added information about new tool MIT161W1122.

13. In Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin, added information about new tool

MIT161W1122.

14. In Paragraph 3.A., General Information, added a note referencing Appendix A.

15. In Paragraph 3.B., Accomplishment Instructions, revised Part 2.

16. In Paragraph 3.B., Accomplishment Instructions, added new Part 3, Part 4, Part 5 and Part 6 to add new

inspection procedures.

17. In Paragraph 3.B., Figure 1 and Figure 2, added a step to clean the center axle and footnotes a., b., c., and

d. and removed inspections for inner cylinder lug bores.

18. In Paragraph 3.B., Figures 3, 4, 5, 6, 7, 8, 9 and 10 were added to provide more detailed inspections and

repairs.

19. In Appendix A, added interchangeability data for 777F.

20. In Appendix A, updated center axle interchangeability.

The data given in Information Notice 777-32-0080 IN 01 is included in this revision.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: July 10, 2008

Revision 1: April 16, 2009

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BOEING SERVICE BULLETIN 777-32-0080
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Summary Number: 777-32-0080

Original Issue: July 10, 2008

Revision 1: April 16, 2009

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder

Pivot Joint - Lubrication and Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of this service bulletin will detect and prevent heat damage and possible cracks in the main

landing gear (MLG) center axle and shock strut inner cylinder lugs (pivot joint) on airplanes that visit Short

Wavelength Roughness (SWR) Level 2 runways. Airplanes that visit SWR Level 2 runways are subject to

increased heat buildup in the MLG pivot joint which can cause cracks in the pivot joint components. The cracks

could lead to fracture of the center axle or inner cylinder lugs. Fracture of the center axle or inner cylinder lugs

can result in the partial collapse of a MLG and loss of control during ground operations.

The type of runway surface roughness that causes damage to the MLG pivot joint is described by a factor called

SWR. SWR Level 1 airports are airports outside of the Commonwealth of Independent States (CIS) and specified

airports within the CIS for which data is available. SWR Level 2 airports are all other airports within the CIS that

are not identified as SWR Level 1. CIS means the following countries: Armenia, Azerbaijan, Belarus, Georgia,

Kazakhstan, Kyrgyzstan, Moldova, Russia, Tajikistan, Turkmenistan, Ukraine, and Uzbekistan. Refer to Boeing

Service Letter 777-SL-32-058 for an active list of SWR Level 1 and SWR Level 2 runways.

SWR Level 2 runways have caused fractures of MLG pivot joint components of 757 and 767 airplanes. One 757

airplane experienced fractures in both MLG truck beams at the same landing. That airplane had accumulated

4,952 flight hours and 1,055 flight cycles. One 767 MLG truck beam fracture occurred as the airplane was making

a U-turn at the end of the runway, before takeoff. All three truck beams fractured at the pivot joint, which caused

the inner cylinder to contact the ground.

This service bulletin provides the instructions for increased lubrication, inspection and repair of the MLG pivot

joint components on airplanes that visit SWR Level 2 runways. Increased lubrication of the MLG pivot joint

components will prevent heat damage which can lead to cracks and/or fracture of the pivot joint components.

Boeing Service Related Problem (SRP) 777-SRP-32-0145 is related to this service bulletin.

Boeing Service Letter 777-SL-32-058 is related to this service bulletin.

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

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Boeing Fleet Team Digest (FTD) Article 777 FTD 32-06006 is related to this service bulletin.

ACTION (PRR 62269-R)

Group 1, Configuration 1:

No action required by this service bulletin.

Group 1, Configuration 2-5:

Get access to the left and right MLG wheel wells. Lubricate the pivot joint of both MLGs and repeat the lubrication.

Remove the landing gear trucks and center axles of both MLGs. Do a detailed, magnetic particle and nital etch

inspection of the MLG pivot joints, including the center axle, inner cylinder bushings and inner cylinder lug bores.

If no damage is found, repeat the inspection. If damage is found, repair or replace the damaged parts and repeat

the inspection.

EFFECTIVITY

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

list of affected airplanes.

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service

bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BOEING SERVICE BULLETIN 777-32-0080
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BOEING SERVICE BULLETIN 777-32-0080
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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0080

Original Issue: July 10, 2008

Revision 1: April 16, 2009

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder

Pivot Joint - Lubrication and Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

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 airplanes shown below. Refer to PRR 62269-R for data about this

change.

NOTE: This Service Bulletin is for the airplanes identified below. The Effectivity list shown below

is complete for airplanes through line number 839. Airplanes after line number 839 are

also affected by this service bulletin, and are in Group(s): 1

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GROUP CONFIGURATION DESCRIPTION

1 - All 777-200, 777-200LR, 777-300, 777-300ER and 777F Airplanes.

1 Airplanes that have never visited an SWR Level 2 airport.

Airplanes with 50 visits or less to the SWR Level 2 runway at DME

that do pivot joint lubrication before and after every visit.

2

Airplanes with 50 visits or less to the SWR Level 2 runway at DME

that do not do pivot joint lubrication before and after every visit.

3

Airplanes with more than 50 visits to the SWR Level 2 runway at

DME and airplanes that visit any other SWR Level 2 runway that do

not do pivot joint lubrication before and after every visit

4

Airplanes with more than 50 visits to the SWR Level 2 runway at

DME and airplanes that visit any other SWR Level 2 runway that do

pivot joint lubrication before and after every visit.

5

Airplane Models:

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

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA101 - WA104 1

WA116 - WA119 1

WA131 - WA137 1

WA171 - WA175 1

WA196 - WA198 1

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 - WA283 1

WA301 - WA304 1

WB001 - WB021 1

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BOEING SERVICE BULLETIN 777-32-0080
Variable Number Group

WB031 - WB046 1

WB051 - WB088 1

WB101 - WB106 1

WB121 - WB125 1

WB131 - WB148 1

WB151 - WB155 1

WB161 - WB177 1

WB181 - WB194 1

WB201 - WB215 1

WB231 - WB247 1

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB337 1

WB341 - WB342 1

WB366 - WB368 1

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB416 - WB439 1

WB446 - WB453 1

WB476 1

WB481 - WB484 1

WB501 - WB512 1

WB531 - WB537 1

WB551 - WB554 1

WB591 - WB597 1

WB601 - WB606 1

WB611 - WB622 1

WB631 - WB638 1

WB646 - WB649 1

WC051 - WC073 1

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BOEING SERVICE BULLETIN 777-32-0080
Variable Number Group

WC101 - WC104 1

WC111 - WC120 1

WC221 - WC222 1

WC241 - WC243 1

WC281 - WC290 1

WC301 - WC308 1

WC361 - WC364 1

WC371 - WC374 1

WC381 - WC395 1

WC441 1

WC446 - WC449 1

WC456 - WC459 1

WC486 - WC493 1

WC506 - WC508 1

WC521 - WC522 1

WC531 - WC536 1

WC546 - WC548 1

WC556 1

WC566 - WC567 1

WC571 - WC574 1

WD001 - WD002 1

WD011 - WD018 1

WD031 - WD036 1

WD046 - WD055 1

WD066 - WD073 1

WD081 - WD085 1

WD501 - WD513 1

WD521 - WD541 1

WD546 - WD554 1

WD561 - WD573 1

WD581 - WD599 1

WD606 - WD609 1

WD621 - WD632 1

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BOEING SERVICE BULLETIN 777-32-0080
Variable Number Group

WD651 - WD664 1

WD671 - WD676 1

WD691 - WD709 1

WD741 - WD752 1

WD761 - WD771 1

WD786 - WD788 1

WD796 - WD809 1

WD826 - WD834 1

WD846 - WD860 1

WD871 - WD878 1

WD911 - WD914 1

WD936 - WD939 1

WD946 - WD948 1

WD966 - WD969 1

WD981 - WD982 1

WD986 1

WE001 1

WF001 - WF004 1

WF016 - WF019 1

WF031 - WF032 1

WF046 - WF048 1

WF076 - WF077 1

WF081 - WF083 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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BOEING SERVICE BULLETIN 777-32-0080
C. Reason

Accomplishment of this service bulletin will detect and prevent heat damage and possible cracks in

the main landing gear (MLG) center axle and shock strut inner cylinder lugs (pivot joint) on airplanes

that visit Short Wavelength Roughness (SWR) Level 2 runways. Airplanes that visit SWR Level 2

runways are subject to increased heat buildup in the MLG pivot joint which can cause cracks in the

pivot joint components. The cracks could lead to fracture of the center axle or inner cylinder lugs.

Fracture of the center axle or inner cylinder lugs can result in the partial collapse of a MLG and loss of

control during ground operations.

The type of runway surface roughness that causes damage to the MLG pivot joint is described by a

factor called SWR. SWR Level 1 airports are airports outside of the Commonwealth of Independent

States (CIS) and specified airports within the CIS for which data is available. SWR Level 2 airports are

all other airports within the CIS that are not identified as SWR Level 1. CIS means the following countries:

Armenia, Azerbaijan, Belarus, Georgia, Kazakhstan, Kyrgyzstan, Moldova, Russia, Tajikistan,

Turkmenistan, Ukraine, and Uzbekistan. Refer to Boeing Service Letter 777-SL-32-058 for an active

list of SWR Level 1 and SWR Level 2 runways.

SWR Level 2 runways have caused fractures of MLG pivot joint components of 757 and 767 airplanes.

One 757 airplane experienced fractures in both MLG truck beams at the same landing. That airplane

had accumulated 4,952 flight hours and 1,055 flight cycles. One 767 MLG truck beam fracture occurred

as the airplane was making a U-turn at the end of the runway, before takeoff. All three truck beams

fractured at the pivot joint, which caused the inner cylinder to contact the ground.

This service bulletin provides the instructions for increased lubrication, inspection and repair of the

MLG pivot joint components on airplanes that visit SWR Level 2 runways. Increased lubrication of the

MLG pivot joint components will prevent heat damage which can lead to cracks and/or fracture of the

pivot joint components.

Boeing Service Related Problem (SRP) 777-SRP-32-0145 is related to this service bulletin.

Boeing Service Letter 777-SL-32-058 is related to this service bulletin.

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

Boeing Fleet Team Digest (FTD) Article 777 FTD 32-06006 is related to this service bulletin.

This revision is sent to provide the following additional detail:

1. In Paragraph 1.A., Effectivity, added information about the PRR created for the new tool designed

for Revision 1 of this service bulletin.

2. In Paragraph 1.C., Reason, added references to Boeing Service Letters (SL) that are related to

this service bulletin.

3. In Paragraph 1.C., Reason, added references to a Boeing Fleet Team Digest article (FTD) that is

related to this service bulletin.

4. In Paragraph 1.D., Description, added text describing inspections of the inner cylinder bushings.

5. In Paragraph 1.E., Compliance, revised the title and compliance information of Table 2.

6. In Paragraph 1.E., Compliance, revised the title and compliance information of Table 3.

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Revision 1: April 16, 2009 777-32-0080

16 of 71

BOEING SERVICE BULLETIN 777-32-0080
7. In Paragraph 1.E., Compliance, added Table 4 and Table 5.

8. In Paragraph 1.G., Manpower, revised the task Part 2.

9. In Paragraph 1.G., Manpower, added the task Part 3, Part 4, Part 5 and Part 6.

10. In Paragraph 1.K., Publications Affected, added information about Damage Tolerance Based

Structural Inspections.

11. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added Corrosion Inhibiting

Compound.

12. In Paragraph 2.E., Special Tooling - Price and Availability, added information about new tool

MIT161W1122.

13. In Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin, added information about

new tool MIT161W1122.

14. In Paragraph 3.A., General Information, added a note referencing Appendix A.

15. In Paragraph 3.B., Accomplishment Instructions, revised Part 2.

16. In Paragraph 3.B., Accomplishment Instructions, added new Part 3, Part 4, Part 5 and Part 6 to

add new inspection procedures.

17. In Paragraph 3.B., Figure 1 and Figure 2, added a step to clean the center axle and footnotes a.,

b., c., and d. and removed inspections for inner cylinder lug bores.

18. In Paragraph 3.B., Figures 3, 4, 5, 6, 7, 8, 9 and 10 were added to provide more detailed inspections

and repairs.

19. In Appendix A, added interchangeability data for 777F.

20. In Appendix A, updated center axle interchangeability.

The data given in Information Notice 777-32-0080 IN 01 is included in this revision.

D. Description

Group 1, Configuration 1:

No action required by this service bulletin.

Group 1, Configuration 2-5:

Get access to the left and right MLG wheel wells. Lubricate the pivot joint of both MLGs and repeat the

lubrication. Remove the landing gear trucks and center axles of both MLGs. Do a detailed, magnetic

particle and nital etch inspection of the MLG pivot joints, including the center axle, inner cylinder bushings

and inner cylinder lug bores. If no damage is found, repeat the inspection. If damage is found, repair

or replace the damaged parts and repeat the inspection.

No more work is necessary on airplanes inspected or changed in accordance with the original issue

of this service bulletin but continued lubrication, inspection and repair is necessary for airplanes that

operate at SWR Level 2 runways.

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Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

17 of 71

BOEING SERVICE BULLETIN 777-32-0080
The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

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

777-300ER, 777F

E. Compliance

Accomplish Part 1 and Part 2 as required in Table 2, Table 3, Table 4 and Table 5 below in accordance

with Paragraph 3., Accomplishment Instructions.

Evaluate the following conditions and actions based on each independent MLG individually.

NOTE: For the following tables, a SWR Level 2 runway visit is defined as one landing at an SWR

Level 2 runway followed by one takeoff from an SWR Level 2 runway.

Group 1, Configuration 1:

Table 1: Airplanes That Have Never Visited a SWR Level 2 Runway

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

No action required by this - -

service bulletin.

All Airplanes

Group 1, Configuration 2:

Table 2: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Immediately before

and after each

SWR Level 2 Runway Visit. (b)

Within 30 Days

After the Date of

the Original Issue of this Service Bulletin.

Immediately before first SWR

Level 2 Runway

visit.

Do Part 1 - MLG Pivot

Joint Lubrication.

All Airplanes (a)

-ANDEvery 800 SWR

Level 2 Runway

Visits

Within 24

Months After the

Date of the

Original Issue of

this Service Bulletin.

Before 48

Months after the

First SWR Level

2 Runway Visit.

Do Part 2 - MLG Pivot

Joint Inspection.

-ORWithin 48 Months

after next SWR

Level 2 Runway

Visit, whichever is

first. (a)

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Revision 1: April 16, 2009 777-32-0080

18 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 2:

Table 2: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

Condition 1: No crack, no

chicken wire cracks, no

corrosion and no chrome

plate distress found.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 2, Option 1.

Condition 2: Chicken wire

cracks found, or corrosion

is found, or chrome plate

distress is found with no

other crack found.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 2, Option 2.

-ANDBefore further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 3, Option 1.

Condition 3: Any crack

found, excluding chicken

wire cracks.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 3, Option 2.

-ANDBefore further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

No further action is re- - - -

quired for this inner cylinder location.

Condition 4: Bushings are

within wear limits, no crack

found, no bushing distress

is found, no smearing of

the material into the lubrication grooves is found and

the grease flow is not restricted.

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Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

19 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 2:

Table 2: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 5: Bushings are

not within wear limits or

any crack is found or

bushing distress is found

or smearing of material into

the lubrication grooves is

found or the grease flow is

restricted

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 6: No sign of

bushing rotation or migration is found.

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 7: Cracked paint

is found but cracked

sealant is not found.

Before further - -

flight.

Restore fillet seal in accordance with Part 5, Condition 8.Condition 8: Cracked

sealant is found that is not

cracked to the lug face.

100 Days until

bushing is replaced.

Before further -

flight.

Apply corrosion inhibiting

compound in accordance

with Part 5, Condition 9.

Condition 9: Cracked

sealant is found that is

cracked to the lug face and

no corrosion is found.

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 10: Cracked

sealant is found that is

cracked to the lug face and

corrosion is found.

Before further - -

flight.

Refinish the lug bore and

faces and install new

bushings in accordance

with Part 6, Condition 11.

Condition 11: No crack is

found, no corrosion is

found and no bronze

transfer is found.

Before further - -

flight.

Repair the inner cylinder

in accordance with Part

6, Condition 12, Option 1.

Condition 12: Any crack is

found, any corrosion is

found or any bronze transfer is found. -ORRepair the inner cylinder

in accordance with Part

6, Condition 12, Option 2.

-ORReplace inner cylinder

with a new, overhauled or

serviceable inner cylinder

in accordance with Part

6, Condition 12, Option 3.

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Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

20 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 2:

Table 2: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(a) If no visits to an SWR Level 2 runway have taken place since the last inspection as given in this service

bulletin, or since last MLG overhaul, then no action is required until the next SWR Level 2 runway visit

occurs.

(b) Refer to 777 MPD Item 12-081-00 for additional routine lubrication requirements.

Group 1, Configuration 3:

Table 3: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Not Do Pivot Joint

Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Every 20 flight cycles. (b)Within 30 Days

after the Date of

the Original Issue of this Service Bulletin.

Before 30 Days

after the First

SWR Level 2

Runway Visit.

Do Part 1 - MLG Pivot

Joint Lubrication.

All Airplanes (a)

-ANDEvery 500 SWR

Level 2 Runway

Visits

Within 24

Months after the

Date of the

Original Issue of

this Service Bulletin.

Before 36

Months after the

First SWR Level

2 Runway Visit.

Do Part 2 - MLG Pivot

Joint Inspection.

-ORWithin 18 Months

after next SWR

Level 2 Runway

Visit, whichever is

first. (a)

Before further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

Condition 1: No crack, no

chicken wire cracks, no

corrosion and no chrome

plate distress found.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

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Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

21 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 3:

Table 3: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Not Do Pivot Joint

Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 2, Option 1.

Condition 2: Chicken wire

cracks found, or corrosion

is found, or chrome plate

distress is found with no

other crack found.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 2, Option 2.

-ANDBefore further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 3, Option 1.

Condition 3: Any crack

found, excluding chicken

wire cracks.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 3, Option 2.

-ANDBefore further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

No further action is re- - - -

quired for this inner cylinder location.

Condition 4: Bushings are

within wear limits, no crack

found, no bushing distress

is found, no smearing of

the material into the lubrication grooves is found and

the grease flow is not restricted.

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Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

22 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 3:

Table 3: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Not Do Pivot Joint

Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 5: Bushings are

not within wear limits or

any crack is found or

bushing distress is found

or smearing of material into

the lubrication grooves is

found or the grease flow is

restricted

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 6: No sign of

bushing rotation or migration is found.

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 7: Cracked paint

is found but cracked

sealant is not found.

Before further - -

flight.

Restore fillet seal in accordance with Part 5, Condition 8.Condition 8: Cracked

sealant is found that is not

cracked to the lug face.

100 Days until

bushing is replaced.

Before further -

flight.

Apply corrosion inhibiting

compound in accordance

with Part 5, Condition 9.

Condition 9: Cracked

sealant is found that is

cracked to the lug face and

no corrosion is found.

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 10: Cracked

sealant is found that is

cracked to the lug face and

corrosion is found.

Before further - -

flight.

Refinish the lug bore and

faces and install new

bushings in accordance

with Part 6, Condition 11.

Condition 11: No crack is

found, no corrosion is

found and no bronze

transfer is found.

Before further - -

flight.

Repair the inner cylinder

in accordance with Part

6, Condition 12, Option 1.

Condition 12: Any crack is

found, any corrosion is

found or any bronze transfer is found. -ORRepair the inner cylinder

in accordance with Part

6, Condition 12, Option 2.

-ORReplace inner cylinder

with a new, overhauled or

serviceable inner cylinder

in accordance with Part

6, Condition 12, Option 3.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

23 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 3:

Table 3: Airplanes with 50 Visits or Less to the SWR Level 2 Runway at DME that Do Not Do Pivot Joint

Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(a) If no visits to an SWR Level 2 runway have taken place since the last inspection as given in this service

bulletin, or since last MLG overhaul, then no action is required until the first SWR Level 2 runway visit

occurs.

(b) This repeat interval satisfies 777 MPD Item 12-081-00 routine lubrication requirements for the pivot joint.

Group 1, Configuration 4:

Table 4: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Not Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Every 20 flight cycles. (b)Within 30 Days

after the Date of

the Original Issue of this Service Bulletin.

Before 30 Days

after the First

SWR Level 2

Runway Visit.

Do Part 1 - MLG Pivot

Joint Lubrication.

All Airplanes (a)

-ANDEvery 500 SWR

Level 2 Runway

Visits

Within 12

Months after the

Date of the

Original Issue of

this Service Bulletin.

Before 500 Total SWR Runway Level 2 Visits.

-ORWithin 18

Months after the

First SWR Level

2 Runway Visit,

whichever is

first.

Do Part 2 - MLG Pivot

Joint Inspection.

-ORWithin 18 Months

after next SWR

Level 2 Runway

Visit, whichever is

first. (a)

Before further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

Condition 1: No crack, no

chicken wire cracks, no

corrosion and no chrome

plate distress found.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

24 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 4:

Table 4: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Not Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 2, Option 1.

Condition 2: Chicken wire

cracks found, or corrosion

is found, or chrome plate

distress is found with no

other crack found.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 2, Option 2.

-ANDBefore further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 3, Option 1.

Condition 3: Any crack

found, excluding chicken

wire cracks.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 3, Option 2.

-ANDBefore further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

No further action is re- - - -

quired for this inner cylinder location.

Condition 4: Bushings are

within wear limits, no crack

found, no bushing distress

is found, no smearing of

the material into the lubrication grooves is found and

the grease flow is not restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

25 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 4:

Table 4: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Not Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 5: Bushings are

not within wear limits or

any crack is found or

bushing distress is found

or smearing of material into

the lubrication grooves is

found or the grease flow is

restricted

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 6: No sign of

bushing rotation or migration is found.

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 7: Cracked paint

is found but cracked

sealant is not found.

Before further - -

flight.

Restore fillet seal in accordance with Part 5, Condition 8.Condition 8: Cracked

sealant is found that is not

cracked to the lug face.

100 Days until

bushing is replaced.

Before further -

flight.

Apply corrosion inhibiting

compound in accordance

with Part 5, Condition 9.

Condition 9: Cracked

sealant is found that is

cracked to the lug face and

no corrosion is found.

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 10: Cracked

sealant is found that is

cracked to the lug face and

corrosion is found.

Before further - -

flight.

Refinish the lug bore and

faces and install new

bushings in accordance

with Part 6, Condition 11.

Condition 11: No crack is

found, no corrosion is

found and no bronze

transfer is found.

Before further - -

flight.

Repair the inner cylinder

in accordance with Part

6, Condition 12, Option 1.

Condition 12: Any crack is

found, any corrosion is

found or any bronze transfer is found. -ORRepair the inner cylinder

in accordance with Part

6, Condition 12, Option 2.

-ORReplace inner cylinder

with a new, overhauled or

serviceable inner cylinder

in accordance with Part

6, Condition 12, Option 3.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

26 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 4:

Table 4: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Not Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(a) If no visits to an SWR Level 2 runway have taken place since the last inspection as given in this service

bulletin, or since last MLG overhaul, then no action is required until the first SWR Level 2 runway visit

occurs.

(b) This repeat interval satisfies 777 MPD Item 12-081-00 routine lubrication requirements for the pivot joint.

Group 1, Configuration 5:

Table 5: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Immediately before

and after each

SWR Level 2 Runway Visit. (b)

Within 30 Days

after the Date of

the Original Issue of this Service Bulletin.

Immediately before first SWR

Level 2 Runway

visit.

Do Part 1 - MLG Pivot

Joint Lubrication.

All Airplanes (a)

-ANDEvery 800 SWR

Level 2 Runway

Visits

Within 12

Months after the

Date of the

Original Issue of

this Service Bulletin.

Before 800 Total SWR Runway Level 2 Visits.

-ORWithin 48

Months after the

First SWR Level

2 Runway Visit,

whichever is

first.

Do Part 2 - MLG Pivot

Joint Inspection.

-ORWithin 48 Months

after next SWR

Level 2 Runway

Visit, whichever is

first. (a)

Before further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

Condition 1: No crack, no

chicken wire cracks, no

corrosion and no chrome

plate distress found.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

27 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 5:

Table 5: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 2, Option 1.

Condition 2: Chicken wire

cracks found, or corrosion

is found, or chrome plate

distress is found with no

other crack found.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 2, Option 2.

-ANDBefore further - -

flight.

Do Part 4 - Inner Cylinder

Bushing Inspection.

-ANDDo Part 5 - Inner Cylinder

Bushing Migration and

Rotation Inspection.

Before further - -

flight.

Repair the center axle in

accordance with Part 3,

Condition 3, Option 1.

Condition 3: Any crack

found, excluding chicken

wire cracks.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 3, Option 2.

-ANDBefore further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

No further action is re- - - -

quired for this inner cylinder location.

Condition 4: Bushings are

within wear limits, no crack

found, no bushing distress

is found, no smearing of

the material into the lubrication grooves is found and

the grease flow is not restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

28 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 5:

Table 5: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 5: Bushings are

not within wear limits or

any crack is found or

bushing distress is found

or smearing of material into

the lubrication grooves is

found or the grease flow is

restricted

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 6: No sign of

bushing rotation or migration is found.

No further action is re- - - -

quired for this inner cylinder bushing location.

Condition 7: Cracked paint

is found but cracked

sealant is not found.

Before further - -

flight.

Restore fillet seal in accordance with Part 5, Condition 8.Condition 8: Cracked

sealant is found that is not

cracked to the lug face.

100 Days until

bushing is replaced.

Before further -

flight.

Apply corrosion inhibiting

compound in accordance

with Part 5, Condition 9.

Condition 9: Cracked

sealant is found that is

cracked to the lug face and

no corrosion is found.

Before further - -

flight.

Do Part 6 - Inner Cylinder

Lug Bore Inspection.

Condition 10: Cracked

sealant is found that is

cracked to the lug face and

corrosion is found.

Before further - -

flight.

Refinish the lug bore and

faces and install new

bushings in accordance

with Part 6, Condition 11.

Condition 11: No crack is

found, no corrosion is

found and no bronze

transfer is found.

Before further - -

flight.

Repair the inner cylinder

in accordance with Part

6, Condition 12, Option 1.

Condition 12: Any crack is

found, any corrosion is

found or any bronze transfer is found. -ORRepair the inner cylinder

in accordance with Part

6, Condition 12, Option 2.

-ORReplace inner cylinder

with a new, overhauled or

serviceable inner cylinder

in accordance with Part

6, Condition 12, Option 3.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1: April 16, 2009 777-32-0080

29 of 71

BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 5:

Table 5: Airplanes with More than 50 Visits to the SWR Level 2 Runway at DME and Airplanes that Visit

Any Other SWR Level 2 Runway that Do Pivot Joint Lubrication Before and After Every Visit

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(a) If no visits to an SWR Level 2 runway have taken place since the last inspection as given in this service

bulletin, or since last MLG overhaul, then no action is required until the first SWR Level 2 runway visit

occurs.

(b) Refer to 777 MPD Item 12-081-00 for additional routine lubrication requirements.

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 inspection 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.

Number of Per- Task Hours Elapsed Hours

sons

Task

Part 1 2 4.00 2.00

Part 2 6 54.00 9.00

Part 3: Figure 1 1 5.00 5.00

Part 3: Figure 2 1 5.00 5.00

Part 4: Figure 3 1 2.25 2.25

Part 4: Figure 4 1 2.25 2.25

Part 5: Figure 5 1 0.50 (a) 0.50 (a)

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BOEING SERVICE BULLETIN 777-32-0080
Number of Per- Task Hours Elapsed Hours

sons

Task

Part 5: Figure 6 1 0.50 (a) 0.50 (a)

Part 6: Figure 7 2 9.00 (b) 4.50 (b)

Part 6: Figure 8 2 9.00 (b) 4.50 (b)

Part 6: Figure 9 (c) (c)

Part 6: Figure 10 (c) (c)

TOTAL FOR EACH AIRPLANE 91.50 35.50

(a) Estimate assumes no evidence of migration or rotation is found. If evidence

of migration or rotation is found, more time will be necessary.

(b) Estimate assumes Condition 11 is found. If Condition 12 is found, more time

will be necessary.

(c) Estimate assumes Condition 11 is found. If Condition 12 is found, work in

FIGURE 9 and FIGURE 10 will require additional time.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Engineering Change Memo PRR 62269-R

b. Boeing Service Letter 777-SL-12-006, 777-SL-32-058, 777-SL-32-059

c. Boeing Service Related Problem (SRP) 777-SRP-32-0145

d. Component Maintenance Manual (CMM) 32-00-07, 32-11-03, 32-11-07, 32-11-64, 32-11-65

e. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-20-01, 20-20-02,

20-30-02, 20-30-03, 20-42-10

f. 777 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-30, 32-11-04, 32-11-18,

32-11-26

g. 777 Fleet Team Digest (FTD) 32-06006

h. 777 Maintenance Planning Data (MPD) Item 12-081-00

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BOEING SERVICE BULLETIN 777-32-0080
2. Data supplied with this Service Bulletin

None.

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.

K. Publications Affected

1. Publications:

Publication Chapter-Section

Component Maintenance Manual 32-11

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

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN 777-32-0080
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

below. Parts availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date

Boeing gets the purchase order.

Unit Price thru December 31, 2009ROLT

(Weeks)

Part Number Name

161W1163-13 Center Axle Assy 94 $54,030.00

161W1163-15 Center Axle Assy 99 $54,030.00

161W1255-7 Inner Cylinder Assy 232 $225,407.00

161W2120-3 Inner Cylinder Assy 192 $254,847.00

161W1122-2 Bushing, Inner Cylinder 48 $2,928.00

161W1122-3 Bushing, Inner Cylinder 50 $3,526.00

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

acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United

States dollars. Terms: Net 30 days.

Reference this service bulletin and submit your 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

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes inspection, and/or repair

procedures given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

None.

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BOEING SERVICE BULLETIN 777-32-0080
2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

Royco 11MS - Grease

BMS 5-95 - Sealant

BMS 10-79, Type - Primer

III

BMS 3-23, Type II, - Corrosion Inhibiting Compound

Class I

BMS 3-32 - Shock Strut Fluid

Refer to APPENDIX A for

part number applicability.

161W1163-1, -3, - 2 Center Axle Assy

5, -7, -11, -13, or15

Refer to APPENDIX A for

part number applicability.

161W1120-3, -5 2 Inner Cylinder Assy

Refer to APPENDIX A for

part number applicability.

161W1255-1, -5, - 2 Inner Cylinder Assy

7

Refer to APPENDIX A for

part number applicability.

161W2120-1, -3 2 Inner Cylinder Assy

161W1122-2 4 Bushing, Inner Cylinder (a)

161W1122-3 4 Bushing, Inner Cylinder Oversized part. (a) (b)

(a) This part can be fabricated as given in CMM 32-11-03 or CMM 32-11-65, as applicable.

(b) The 161W1122-3 bushing is preferred over the 161W1122-2 bushing due to larger lube

passages.

3. Parts Modified and Reidentified

None.

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.

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BOEING SERVICE BULLETIN 777-32-0080
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 777-32-0080 R01)

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 777-32-0080
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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
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. Use the approved fastener and process material substitutions in accordance with

777 SRM, Chapter 51. Alternate fasteners are listed in 777 SRM Chapter 51 and

Boeing Drawing 012W6100.

5. A Detailed Inspection is defined as: An intensive examination of a specific item,

installation, or assembly to detect damage, failure, or irregularity. Available lighting

is normally supplemented with a direct source of good lighting at an intensity deemed

appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be

necessary. Surface cleaning and elaborate procedures may be required.

6. 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.

7. Refer to Appendix A for Part Interchangeability Based on Airplane Model.

B. WORK INSTRUCTIONS

Group 1, Configuration 1:

1. No action required by this service bulletin.

Group 1, Configuration 2-5:

PART 1 - MAIN LANDING GEAR PIVOT JOINT LUBRICATION

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. Lubricate the MLG pivot joints. Refer to 777 AMM 12-21-14 as an accepted procedure. Refer to

777-SL-12-006 for cold weather lubrication.

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BOEING SERVICE BULLETIN 777-32-0080
4. Remove the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

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

6. Put the airplane back into serviceable condition.

Group 1, Configuration 2-5:

PART 2 - MLG PIVOT JOINT INSPECTION

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 trucks. Refer to 777 AMM 32-11-18 as an accepted procedure.

4. Do Part 3 - Center Axle Inspection.

5. Install the left and right MLG trucks. Refer to 777 AMM 32-11-18 as an accepted procedure.

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

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

8. Put the airplane back into serviceable condition.

Group 1, Configuration 2-5:

PART 3 - CENTER AXLE INSPECTION

1. Inspect the center axle of the left MLG in accordance with FIGURE 1 and the right MLG in

accordance with FIGURE 2.

a. Condition 1: No crack, no chicken wire cracks, no corrosion and no chrome plate distress

found.

(1) Do Part 4 - Inner Cylinder Bushing Inspection.

(2) Do Part 5 - Inner Cylinder Bushing Migration and Rotation Inspection.

b. Condition 2: Chicken wire cracks found, or corrosion is found, or chrome plate distress is

found with no other crack found.

(1) Option 1: Repair the center axle in accordance with CMM 32-11-07 Repair 7-2.

(2) Option 2: Replace the center axle with a new, overhauled or serviceable center axle.

Refer to 777 AMM 32-11-26 as an accepted procedure. Refer to APPENDIX A for center

axle assembly interchangeability based on airplane type.

(3) Do Part 4 - Inner Cylinder Bushing Inspection.

(4) Do Part 5 - Inner Cylinder Bushing Migration and Rotation Inspection.

c. Condition 3: Any crack found, excluding chicken wire cracks.

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BOEING SERVICE BULLETIN 777-32-0080
(1) Option 1: Repair the center axle in accordance with CMM 32-11-07 Repair 7-2.

(2) Option 2: Replace the center axle with a new, overhauled or serviceable center axle.

Refer to 777 AMM 32-11-26 as an accepted procedure. Refer to APPENDIX A for center

axle assembly interchangeability based on airplane type.

(3) Do Part 6 - Inner Cylinder Lug Bore Inspection.

Group 1, Configuration 2-5:

PART 4 - INNER CYLINDER BUSHING INSPECTION

1. Inspect the inner cylinder bushings of the left MLG in accordance with FIGURE 3 and the right

MLG in accordance with FIGURE 4.

a. Condition 4: Bushings are within wear limits, no crack found, no bushing distress is found, no

smearing of the material into the lubrication grooves is found and the grease flow is not

restricted.

(1) No further action is required for this inner cylinder location.

b. Condition 5: Bushings are not within wear limits or any crack is found or bushing distress is

found or smearing of material into the lubrication grooves is found or the grease flow is

restricted.

(1) Do Part 6 - Inner Cylinder Lug Bore Inspection.

Group 1, Configuration 2-5:

PART 5 - INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

1. Inspect the MLG inner cylinder bushings for signs of rotation and migration of the left MLG in

accordance with FIGURE 5 and of the right MLG in accordance with FIGURE 6.

a. Condition 6: No sign of bushing rotation or migration is found.

(1) No further action is required for this inner cylinder bushing location.

b. Condition 7: Cracked paint is found but cracked sealant is not found.

(1) No further action is required for this inner cylinder bushing location.

c. Condition 8: Cracked sealant is found that is not cracked to the lug face.

(1) Restore fillet seal of the left MLG in accordance with FIGURE 5 or of the right MLG in

accordance with FIGURE 6, as applicable.

d. Condition 9: Cracked sealant is found that is cracked to the lug face and no corrosion is found.

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(1) Apply corrosion inhibiting compound to the left MLG in accordance with FIGURE 5 or to

the right MLG in accordance with FIGURE 6, as applicable.

(2) Repeat application of corrosion inhibiting compound to the left MLG in accordance with

FIGURE 5 or to the right MLG in accordance with FIGURE 6, as applicable, at the intervals

in accordance with Paragraph 1.E., Compliance.

e. Condition 10: Cracked sealant is found that is cracked to the lug face and corrosion is found.

(1) Do Part 6 - Inner Cylinder Lug Bore Inspection.

Group 1, Configuration 2-5:

PART 6 - INNER CYLINDER LUG BORE INSPECTION

1. Inspect the inner cylinder lug bores of the left MLG in accordance with FIGURE 7 or of the right

MLG in accordance with FIGURE 8, as applicable.

a. Condition 11: No crack is found, no corrosion is found, no heat damage is found and no bronze

transfer is found in the inner cylinder lug bore.

(1) Refinish the lug bore and faces in accordance with CMM 32-11-03 Repair 4-2 or CMM

32-11-65 Repair 5-2, as applicable.

(2) Install new bushings in accordance with CMM 32-11-03 Repair 4-1 or CMM 32-11-65

Repair 5-1, as applicable.

b. Condition 12: Any crack is found, any corrosion is found, any heat damage is found or any

bronze transfer is found in the inner cylinder lug bore.

(1) Option 1: Repair the inner cylinder of the left MLG in accordance with FIGURE 9 or of

the right MLG in accordance with FIGURE 10, as applicable.

(2) Option 2: Repair the inner cylinder in accordance with CMM 32-11-03 Repair 4-2 or CMM

32-11-65 Repair 5-2, as applicable.

(3) Option 3: Replace inner cylinder with a new, overhauled or serviceable inner cylinder.

Refer to 777 AMM 32-11-04 as an accepted procedure. Refer to APPENDIX A for inner

cylinder assembly interchangeability based on airplane type.

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BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-

30-03 as an accepted procedure.

1 Clean Center Axle - 1

Do a Detailed Inspection of the outer diameter for chicken

wire cracks, corrosion and chrome

plate distress. (a) (b)

(c) (d)

2 Inspect Center Axle - 1

Do a Magnetic Particle Inspection of the

outer diameter for

cracks in accordance with SOPM

20-20-01.

3 Inspect Center Axle - 1

(a) Signs of chrome plate distress includes ladder cracks, material or bronze transfer, darkened streaks,

plating which is smeared, chipped, cracked, flaked, a different color, or gone. Visually examine the plated

surface with light at an angle, but do not use magnification. Look at the surfaces from different angles.

FIGURE 1: LEFT MLG CENTER AXLE INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

The sharp point of a dental explorer can be used to find cracks in the chrome plating. Refer to CMM 32-

00-07 for information about chrome plate distress identification.

(b) Chicken Wire Cracks are defined as cracks that occur when stresses created in the chrome deposit during

plating are relieved. The cracks are evident in the deposited chrome when viewed from a perpendicular

plane as a pattern similar to chicken wire. Crack size can vary with plating conditions.

(c) Color changes and darkened streaks that can be removed with Scotchbrite and/or hand tools within a

maximum blend depth of 0.001 inch are acceptable and not considered signs of chrome plate distress.

(d) A Fluorescent Penetrant Inspection in accordance with SOPM 20-20-02 can be used to supplement the

detailed inspection of large areas for chrome plate distress.

FIGURE 1: LEFT MLG CENTER AXLE INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-

30-03 as an accepted procedure.

1 Clean Center Axle - 1

Do a Detailed Inspection of the outer diameter for chicken

wire cracks, corrosion and chrome

plate distress. (a) (b)

(c) (d)

2 Inspect Center Axle - 1

Do a Magnetic Particle Inspection of the

outer diameter for

cracks in accordance with SOPM

20-20-01.

3 Inspect Center Axle - 1

FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(a) Signs of chrome plate distress includes ladder cracks, material or bronze transfer, darkened streaks,

plating which is smeared, chipped, cracked, flaked, a different color, or gone. Visually examine the plated

surface with light at an angle, but do not use magnification. Look at the surfaces from different angles.

The sharp point of a dental explorer can be used to find cracks in the chrome plating. Refer to CMM 32-

00-07 for information about chrome plate distress identification.

(b) Chicken Wire Cracks are defined as cracks that occur when stresses created in the chrome deposit during

plating are relieved. The cracks are evident in the deposited chrome when viewed from a perpendicular

plane as a pattern similar to chicken wire. Crack size can vary with plating conditions.

(c) Color changes and darkened streaks that can be removed with Scotchbrite and/or hand tools within a

maximum blend depth of 0.001 inch are acceptable and not considered signs of chrome plate distress.

(d) A Fluorescent Penetrant Inspection in accordance with SOPM 20-20-02 can be used to supplement the

detailed inspection of large areas for chrome plate distress.

FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean inner diameter, grease grooves

and around flange

area. Refer to

SOPM 20-30-03 as

an accepted procedure.

1 Clean Inner Cylinder Bushings - 2

Do a Detailed Inspection of the bushing

inner diameter and

flanges for cracks,

smearing of material

into the lubrication

grooves and bushing

distress. (a) (b)

2 Inspect Inner Cylinder Bushings - 2

For wear limits in

accordance with

CMM 32-11-07 or

CMM 32-11-64, as

applicable.

3 Inspect Inner Cylinder Bushings - 2

Through the lube fittings to make sure

the grease flow is

not restricted.

Grease should appear at all four

grease holes in the

bushing. (c) (d)

4 Apply Grease ROYCO 11MS -

(a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.

(b) Darkened areas, heat discoloration and burnishing that can be removed with Scotchbrite and/or hand

tools within a maximum blend depth of 0.001 inch are acceptable and are not considered signs of bushing

distress.

(c) Clean lube passages if grease flow is restricted. A room temperature or heated shock strut fluid such as

BMS 3-32 can be applied through the lube fitting and passage to remove dried grease as an accepted

procedure. Repeat application of grease and cleaning of lube passages until grease flow is not restricted.

(d) Temporary plugging of individual bushing through-wall holes is recommended to redirect grease to all

through-wall holes.

FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION

(SHEET 1 OF 2)

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47 of 71

BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean inner diameter, grease grooves

and around flange

area. Refer to

SOPM 20-30-03 as

an accepted procedure.

1 Clean Inner Cylinder Bushings - 2

Do a Detailed Inspection of the bushing

inner diameter and

flanges for cracks,

smearing of material

into the lubrication

grooves and bushing

distress. (a) (b)

2 Inspect Inner Cylinder Bushings - 2

For wear limits in

accordance with

CMM 32-11-07 or

CMM 32-11-64, as

applicable.

3 Inspect Inner Cylinder Bushings - 2

Through the lube fittings to make sure

the grease flow is

not restricted.

Grease should appear at all four

grease holes in the

bushing. (c) (d)

4 Apply Grease ROYCO 11MS -

(a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.

(b) Darkened areas, heat discoloration and burnishing that can be removed with Scotchbrite and/or hand

tools within a maximum blend depth of 0.001 inch are acceptable and are not considered signs of bushing

distress.

(c) Clean lube passages if grease flow is restricted. A room temperature or heated shock strut fluid such as

BMS 3-32 can be applied through the lube fitting and passage to remove dried grease as an accepted

procedure. Repeat application of grease and cleaning of lube passages until grease flow is not restricted.

(d) Temporary plugging of individual bushing through-wall holes is recommended to redirect grease to all

through-wall holes.

FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 5: LEFT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the bushing

flange for signs of

migration or rotation.

(a)

1 Inspect Inner Cylinder Bushings - 2

If any cracked

sealant is found. Locally remove

cracked sealant and

determine if the

sealant is cracked to

the lug face.

2 Remove Sealant - -

If sealant is not

found to be cracked

to the lug face, clean

lug face in area

where sealant was

removed. Refer to

SOPM 20-30-03 as

an accepted procedure.

Inner Cylinder Lug - -

Face

3 Clean

Apply Sealant BMS 5-95 - To restore fillet seal.

If sealant is found to

be cracked to the lug

face, clean lug face

in area where

sealant was removed. Refer to

SOPM 20-30-03 as

an accepted procedure.

Inner Cylinder Lug - -

Face

4 Clean

Do a detailed inspection for corrosion in

the area where the

sealant was removed.

Inner Cylinder Lug - -

Face

Inspect

FIGURE 5: LEFT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

(SHEET 2 OF 3)

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Revision 1 April 16, 2009 777-32-0080

50 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

If no corrosion is

found, remove 0.10

- 0.20 inch length of

fillet seal at two or

more locations to allow moisture to escape when the corrosion inhibiting compound is applied.

5 Remove Sealant - -

generously to gaps

where sealant was

removed. Direct

spray between the

bushing flange and

the lug face.

BMS 3-23, TYPE II, -

CLASS 1

Corrosion Inhibiting

Compound

Apply

(a) Cracked sealant is a sign of bushing migration or rotation. Cracked paint only is not a sign of bushing

migration or rotation.

FIGURE 5: LEFT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

(SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

51 of 71

BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 6: RIGHT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

(SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

52 of 71

BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the bushing

flange for signs of

migration or rotation.

(a)

1 Inspect Inner Cylinder Bushings - 2

If any cracked

sealant is found. Locally remove

cracked sealant and

determine if the

sealant is cracked to

the lug face.

2 Remove Sealant - -

If sealant is not

found to be cracked

to the lug face, clean

lug face in area

where sealant was

removed. Refer to

SOPM 20-30-03 as

an accepted procedure.

Inner Cylinder Lug - -

Face

3 Clean

Apply Sealant BMS 5-95 - To restore fillet seal.

If sealant is found to

be cracked to the lug

face, clean lug face

in area where

sealant was removed. Refer to

SOPM 20-30-03 as

an accepted procedure.

Inner Cylinder Lug - -

Face

4 Clean

Do a detailed inspection for corrosion in

the area where the

sealant was removed.

Inner Cylinder Lug - -

Face

Inspect

FIGURE 6: RIGHT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

(SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

53 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

If no corrosion is

found, remove 0.10

- 0.20 inch length of

fillet seal at two or

more locations to allow moisture to escape when the corrosion inhibiting compound is applied.

5 Remove Sealant - -

generously to gaps

where sealant was

removed. Direct

spray between the

bushing flange and

the lug face.

BMS 3-23, TYPE II, -

CLASS 1

Corrosion Inhibiting

Compound

Apply

(a) Cracked sealant is a sign of bushing migration or rotation. Cracked paint only is not a sign of bushing

migration or rotation.

FIGURE 6: RIGHT MLG INNER CYLINDER BUSHING MIGRATION AND ROTATION INSPECTION

(SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

54 of 71

BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE INSPECTION

(SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

55 of 71

BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to tool

MIT161W1122 instructions. (a)

1 Remove Inner Cylinder Bushings - 2

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Bore and - 2

Face

2 Clean

from lug bore and

faces. Refer to

SOPM 20-30-02 as

an accepted procedure.

3 Remove Primer BMS 10-79, TYPE III -

Do a Detailed Inspection of the lug bore

inner diameter for

cracks, corrosion or

bronze transfer and

the lug bore faces

for cracks or corrosion.

Inner Cylinder Bore and - 2

Face

4 Inspect

Do a Penetrant Inspection in accordance with SOPM

20-20-02 for corrosion.

Inner Cylinder Bore and - 2

Face

5 Inspect

Do a Magnetic Particle Inspection in accordance with

SOPM 20-20-01 for

cracks.

Inner Cylinder Bore and - -

Face

6 Inspect

FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(b) From the area in

the lug bore and

faces where corrosion or bronze transfer was found. Remove the cadmium

plate by manual application of ammonium nitrate solution.

Make sure adjacent

areas are protected

where cadmium

plating removal is

not required. Refer

to SOPM 20-30-02

as an accepted procedure.

7 Remove Cadmium Plating - -

(b) Do a Local Etch

of Large Parts Inspection of the base

metal where the

cadmium plating

was removed to detect heat damage in

accordance with

SOPM 20-10-02.

Make sure adjacent

areas are protected

where the nital etch

inspection is not required. Ammonium

Persulfate method is

not allowed.

8 Inspect Inner Cylinder Lug Bore - 2

(a) Bushing removal is only required at the location where bushing damage was found. If lug bore damage

is found at the location where the bushing was removed, then it is recommended that both bushings be

removed to ensure correct lug bore and bushing alignment during subsequent repair procedures.

(b) This step is only required if a crack, corrosion or bronze transfer is found on the inner cylinder lug bore

or if a crack is found on the center axle.

FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE INSPECTION

(SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

57 of 71

BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION

(SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

58 of 71

BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to tool

MIT161W1122 instructions. (a)

1 Remove Inner Cylinder Bushings - 2

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Bore and - 2

Face

2 Clean

from lug bore and

faces. Refer to

SOPM 20-30-02 as

an accepted procedure.

3 Remove Primer BMS 10-79, TYPE III -

Do a Detailed Inspection of the lug bore

inner diameter for

cracks, corrosion or

bronze transfer and

the lug bore faces

for cracks or corrosion.

Inner Cylinder Bore and - 2

Face

4 Inspect

Do a Penetrant Inspection in accordance with SOPM

20-20-02 for corrosion.

Inner Cylinder Bore and - 2

Face

5 Inspect

Do a Magnetic Particle Inspection in accordance with

SOPM 20-20-01 for

cracks.

Inner Cylinder Bore and - -

Face

6 Inspect

FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION

(SHEET 2 OF 3)

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Revision 1 April 16, 2009 777-32-0080

59 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(b) From the area in

the lug bore and

faces where corrosion or bronze transfer was found. Remove the cadmium

plate by manual application of ammonium nitrate solution.

Make sure adjacent

areas are protected

where cadmium

plating removal is

not required. Refer

to SOPM 20-30-02

as an accepted procedure.

7 Remove Cadmium Plating - -

(b) Do a Local Etch

of Large Parts Inspection of the base

metal where the

cadmium plating

was removed to detect heat damage in

accordance with

SOPM 20-10-02.

Make sure adjacent

areas are protected

where the nital etch

inspection is not required. Ammonium

Persulfate method is

not allowed.

8 Inspect Inner Cylinder Lug Bore - 2

(a) Bushing removal is only required at the location where bushing damage was found. If lug bore damage

is found at the location where the bushing was removed, then it is recommended that both bushings be

removed to ensure correct lug bore and bushing alignment during subsequent repair procedures.

(b) This step is only required if a crack, corrosion or bronze transfer is found on the inner cylinder lug bore

or if a crack is found on the center axle.

FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION

(SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

60 of 71

BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 9: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 1 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

61 of 71

BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

As necessary to remove any corrosion,

heat damage, cracks

or bronze transfer.

Maximum 0.020 inch

increase in the diameter with a maximum

lug bore diameter of

7.1015 inches. Refer

to tool

MIT161W1122 instructions. Refer to

SOPM 20-10-02 as

an accepted procedure. (a)

1 Hone Inner Cylinder Lug Bore - -

As necessary to remove any cracks or

corrosion. Blend out

shallow surface irregularities and or shallow discrete pits less

than 0.005 inch in

depth. Refer to

SOPM 20-10-02 as

an accepted procedure.

Inner Cylinder Lug - -

Face

2 Repair

Do a detailed inspection using 10 power

magnification to ensure all corrosion

and bronze transfer

has been removed.

Inner Cylinder Bore and - -

Face

3 Inspect

FIGURE 9: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 2 OF 5)

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Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

62 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a penetrant inspection of the repaired areas, except

chemical etch of the

surface to remove

smeared metal is not

allowed. Refer to

SOPM 20-20-02 as

an accepted procedure.

Inner Cylinder Bore and - -

Face

4 Inspect

Do a Magnetic Particle inspection of the

repaired areas in accordance with

SOPM 20-20-01.

Inner Cylinder Bore and - -

Face

5 Inspect

Do a Local Etch of

Large Parts Inspection of the repaired

areas to detect heat

damage in accordance with SOPM

20-10-02. Make sure

adjacent areas are

protected where the

nital etch inspection

is not required.

Inner Cylinder Bore and - -

Face

6 Inspect

Flapper peen the repaired areas. Refer

to SOPM 20-10-03

as an accepted procedure.

Inner Cylinder Bore and - -

Face

7 Shot Peen

Record the before

plating dimensions

to help size new

bushings.

Inner Cylinder Bore and - -

Face

8 Measure

Apply low hydrogen

embrittlement stylus

cadmium plating to

machined areas in

accordance with

SOPM 20-42-10, except 72 square inch

limit can be exceeded for the post bake

requirement.

Low Hydrogen Embrit- - -

tlement Cadmium Plate

9 Apply

FIGURE 9: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 3 OF 5)

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Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

63 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

to the entire bore

and in other areas

where primer was

removed. Refer to

CMM 32-11-03 Repair 4-2 or CMM 32-

11-65 Repair 5-2 as

an accepted procedure, as applicable.

10 Apply Primer BMS 10-79, TYPE III -

at the lubrication fittings until grease

appears in the

bores. If necessary,

clean the lubrication

passages. Remove

any excess grease.

11 Apply Grease ROYCO 11MS -

In accordance with

CMM 32-11-03 Repair 4-2 or CMM 32-

11-65 Repair 5-2, as

applicable.

12 Make Inner Cylinder Bushing 161W1122-3 -

Apply a thin layer to

the bores, chamfers

and faces of the inner cylinder that will

contact the bushings.

13 Apply Sealant BMS 5-95 -

In accordance with

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

11-65 Repair 5-1, as

applicable. Refer to

tool MIT161W1122

instructions.

14 Install (New) Inner Cylinder Bushings - -

as necessary to

meet the dimensional requirements in

accordance with

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

11-65 Repair 5-1, as

applicable. Refer to

tool MIT161W1122

instructions. (b) (c)

15 Hone Inner Cylinder Bushings - -

FIGURE 9: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 4 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

64 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

at the lubrication fittings until grease

appears in the bores

at all four grease

holes in accordance

with CMM 32-11-03

Repair 4-1 or CMM

32-11-65 Repair 5-1,

as applicable. (d)

16 Apply Grease ROYCO 11MS -

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Lug - -

Face

17 Clean

Fillet seal bushing

flange in accordance

with CMM 32-11-03

Repair 4-1 or CMM

32-11-65 Repair 5-1,

as applicable.

Apply Sealant BMS 5-95 -

(a) Lug bores must be concentric within 0.0015 inches.

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

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

(d) Temporary plugging of individual through-wall holes is recommended to redirect grease to all throughwall holes.

FIGURE 9: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 5 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

65 of 71

BOEING SERVICE BULLETIN 777-32-0080
This Figure applies only to: Group 1, Configuration 2-5.

FIGURE 10: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 1 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

66 of 71

BOEING SERVICE BULLETIN 777-32-0080
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each MLG.

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

As necessary to remove any corrosion,

heat damage, cracks

or bronze transfer.

Maximum 0.020 inch

increase in the diameter with a maximum

lug bore diameter of

7.1015 inches. Refer

to tool

MIT161W1122 instructions. Refer to

SOPM 20-10-02 as

an accepted procedure. (a)

1 Hone Inner Cylinder Lug Bore - -

As necessary to remove any cracks or

corrosion. Blend out

shallow surface irregularities and or shallow discrete pits less

than 0.005 inch in

depth. Refer to

SOPM 20-10-02 as

an accepted procedure.

Inner Cylinder Lug - -

Face

2 Repair

Do a detailed inspection using 10 power

magnification to ensure all corrosion

and bronze transfer

has been removed.

Inner Cylinder Bore and - -

Face

3 Inspect

FIGURE 10: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 2 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

67 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a penetrant inspection of the repaired areas, except

chemical etch of the

surface to remove

smeared metal is not

allowed. Refer to

SOPM 20-20-02 as

an accepted procedure.

Inner Cylinder Bore and - -

Face

4 Inspect

Do a Magnetic Particle inspection of the

repaired areas in accordance with

SOPM 20-20-01.

Inner Cylinder Bore and - -

Face

5 Inspect

Do a Local Etch of

Large Parts Inspection of the repaired

areas to detect heat

damage in accordance with SOPM

20-10-02. Make sure

adjacent areas are

protected where the

nital etch inspection

is not required.

Inner Cylinder Bore and - -

Face

6 Inspect

Flapper peen the repaired areas. Refer

to SOPM 20-10-03

as an accepted procedure.

Inner Cylinder Bore and - -

Face

7 Shot Peen

Record the before

plating dimensions

to help size new

bushings.

Inner Cylinder Bore and - -

Face

8 Measure

Apply low hydrogen

embrittlement stylus

cadmium plating to

machined areas in

accordance with

SOPM 20-42-10, except 72 square inch

limit can be exceeded for the post bake

requirement.

Low Hydrogen Embrit- - -

tlement Cadmium Plate

9 Apply

FIGURE 10: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 3 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

68 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

to the entire bore

and in other areas

where primer was

removed. Refer to

CMM 32-11-03 Repair 4-2 or CMM 32-

11-65 Repair 5-2 as

an accepted procedure, as applicable.

10 Apply Primer BMS 10-79, TYPE III -

at the lubrication fittings until grease

appears in the

bores. If necessary,

clean the lubrication

passages. Remove

any excess grease.

11 Apply Grease ROYCO 11MS -

In accordance with

CMM 32-11-03 Repair 4-2 or CMM 32-

11-65 Repair 5-2, as

applicable.

12 Make Inner Cylinder Bushing 161W1122-3 -

Apply a thin layer to

the bores, chamfers

and faces of the inner cylinder that will

contact the bushings.

13 Apply Sealant BMS 5-95 -

In accordance with

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

11-65 Repair 5-1, as

applicable. Refer to

tool MIT161W1122

instructions.

14 Install (New) Inner Cylinder Bushings - -

as necessary to

meet the dimensional requirements in

accordance with

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

11-65 Repair 5-1, as

applicable. Refer to

tool MIT161W1122

instructions. (b) (c)

15 Hone Inner Cylinder Bushings - -

FIGURE 10: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 4 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

69 of 71

BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

at the lubrication fittings until grease

appears in the bores

at all four grease

holes in accordance

with CMM 32-11-03

Repair 4-1 or CMM

32-11-65 Repair 5-1,

as applicable. (d)

16 Apply Grease ROYCO 11MS -

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Lug - -

Face

17 Clean

Fillet seal bushing

flange in accordance

with CMM 32-11-03

Repair 4-1 or CMM

32-11-65 Repair 5-1,

as applicable.

Apply Sealant BMS 5-95 -

(a) Lug bores must be concentric within 0.0015 inches.

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

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

(d) Temporary plugging of individual through-wall holes is recommended to redirect grease to all throughwall holes.

FIGURE 10: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT

(SHEET 5 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 10, 2008

Revision 1 April 16, 2009 777-32-0080

70 of 71

BOEING SERVICE BULLETIN 777-32-0080
Applicable Inner Cylinder

Assemblies

Applicable Center Axle

Assemblies

Maximum Taxi Gross

Weight

Airplane Model

161W1163-1, -3, -5, -7, -9, 161W1120-3, -5

-11, -13, -15

777-200 547,000 lbs

161W1255-1, -5, -7

161W1163-1, -3, -5, -7, -9, 161W1255-1, -5, -7

-11, -13, -15

777-200ER 652,000 lbs

161W1163-3, -7, -9, -13, - 161W1255-7

15

777-200ER/IGW 658,000 lbs

161W1163-3, -7, -9, -13, - 161W1255-7

15

777-300 662,000 lbs

777-200LR 768,800 lbs 161W1163-9, -15 161W2120-1, -3

777-300ER 777,000 lbs 161W1163-9, -15 161W2120-1, -3

777F 768,800 lbs 161W1163-9, -15 161W2120-1, -3

APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT

INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL

(SHEET 1 OF 1)

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Revision 1 April 16, 2009 777-32-0080

71 of 71

BOEING SERVICE BULLETIN 777-32-0080