### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 1 of 71 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 2 of 71 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 3 of 71 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 4 of 71 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 5 of 719. 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** July 10, 2008 Original Issue: April 16, 2009 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 6 of 71 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 7 of 71Boeing 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 8 of 71 **BOEING SERVICE BULLETIN 777-32-0080**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 9 of 71 **BOEING SERVICE BULLETIN 777-32-0080**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 10 of 71 **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. **NO TE:**  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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 11 of 71**DESCRIPTION CONFIGURATION**  **GROUP** All 777-200, 777-200LR, 777-300, 777-300ER and 777F Airplanes.

- 1 Airplanes that have never visited an SWR Level 2 airport. 1 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 **Group Variable Number**  1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 12 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 13 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 14 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group**  **Variable Number** 1 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 2. Spares Affected
None. **B. Concurrent Requirements**
None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 15 of 71 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 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 Zone**  **Model** 731, 741 777-200, 777-200LR, 777-300, 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. **NO TE:**  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: T** 

**ab le 1:**  **Airplanes That Ha**  **ve Ne ver**  **Visited a SWR Le vel 2 Runwa** **y Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- - No action required by this service bulletin. All Airplanes

**Group 1, Configuration 2: T** 

**ab le 2:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Piv** **ot Joint Lubri cation Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** Immediately before and after eachSWR Level 2 Runway Visit. (b) Within 30 Days After the Date ofthe 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 ofthis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 18 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 2:**  **T**

**ab le 2:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Piv** **ot Joint Lubri cation Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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.-AND- - Before 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.-AND- - Before 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 ofthe material into the lubrication grooves is found andthe grease flow is not restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 19 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 2:**  **T**

**ab le 2:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Piv** **ot Joint Lubri cation Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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 ofbushing 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 untilbushing 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 isfound 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 777-32-0080 Revision 1: April 16, 2009 20 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 2:**  **T**

**ab le 2:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Piv** **ot Joint Lubri cation Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** (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: T** 

**ab le 3:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Not Do Piv** **ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** Every 20 flight cycles. (b) Within 30 Days after the Date ofthe 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 ofthis 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 21 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 3:**  **T**

**ab le 3:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Not Do Piv** **ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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.-AND- - Before 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.-AND- - Before 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 ofthe material into the lubrication grooves is found andthe grease flow is not restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 22 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 3:**  **T**

**ab le 3:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Not Do Piv** **ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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 ofbushing 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 untilbushing 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 isfound 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 777-32-0080 Revision 1: April 16, 2009 23 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 3:**  **T**

**ab le 3:**  **Airplanes with 50 Visits or Less to the SWR Le** **vel 2 Runwa y at DME that Do Not Do Piv** **ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** (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: T** 

**ab le 4:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Not Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** Every 20 flight cycles. (b) Within 30 Days after the Date ofthe 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 ofthis 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 777-32-0080 Revision 1: April 16, 2009 24 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 4:**  **T**

**ab le 4:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Not Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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.-AND- - Before 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.-AND- - Before 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 ofthe material into the lubrication grooves is found andthe grease flow is not restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 25 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 4:**  **T**

**ab le 4:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Not Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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 ofbushing 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 untilbushing 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 isfound 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 777-32-0080 Revision 1: April 16, 2009 26 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 4:**  **T**

**ab le 4:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Not Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** (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: T** 

**ab le 5:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** Immediately before and after eachSWR Level 2 Runway Visit. (b) Within 30 Days after the Date ofthe 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 ofthis 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 777-32-0080 Revision 1: April 16, 2009 27 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 5:**  **T**

**ab le 5:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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.-AND- - Before 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.-AND- - Before 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 ofthe material into the lubrication grooves is found andthe grease flow is not restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 28 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 5:**  **T**

**ab le 5:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- - 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 ofbushing 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 untilbushing 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 isfound 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 777-32-0080 Revision 1: April 16, 2009 29 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Group 1, Configuration 5:**  **T**

**ab le 5:**  **Airplanes with More than 50 Visits to the SWR Le** **vel 2 Runwa y at DME and Airplanes that**  **Visit An**  **y Other SWR Le vel 2 Runwa** **y that Do Piv ot Joint Lubrication Bef**  **ore and After Ever y**  **Visit Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** (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. **Elapsed Hours Task Hours**  **Number of Per- sons**  **Task**

2.00 4.00 2 Part 1 9.00 54.00 6 Part 2 5.00 5.00 1 Part 3: Figure 1 5.00 5.00 1 Part 3: Figure 2 2.25 2.25 1 Part 4: Figure 3 2.25 2.25 1 Part 4: Figure 4 0.50 (a) 0.50 (a) 1 Part 5: Figure 5

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 30 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Elapsed Hours**  **Task Hours Number of Per-**  **sons Task**  0.50 (a) 0.50 (a) 1 Part 5: Figure 6 4.50 (b) 9.00 (b) 2 Part 6: Figure 7 4.50 (b) 9.00 (b) 2 Part 6: Figure 8 (c) (c) Part 6: Figure 9 (c) (c) Part 6: Figure 10 35.50 91.50 TOTAL FOR EACH AIRPLANE (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 31 of 71 **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
**Title Drawing Number**  Installation - Main Landing Gear 161W0000 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: **Chapter-Section**

**Publication** 32-11 Component Maintenance Manual 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 32 of 71 **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 De cember 31, 2009**  **ROLT (Weeks)**  **Name Part Number**  $54,030.00 94 Center Axle Assy 161W1163-13 $54,030.00 99 Center Axle Assy 161W1163-15 $225,407.00 232 Inner Cylinder Assy 161W1255-7 $254,847.00 192 Inner Cylinder Assy 161W2120-3 $2,928.00 48 Bushing, Inner Cylinder 161W1122-2 $3,526.00 50 Bushing, Inner Cylinder 161W1122-3 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 33 of 71 **BOEING SERVICE BULLETIN 777-32-0080**2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** Grease

- Royco 11MS Sealant

- BMS 5-95 Primer

- BMS 10-79, Type III Corrosion Inhibiting Compound

- BMS 3-23, Type II, Class I Shock Strut Fluid

- BMS 3-32 Refer to APPENDIX A for part number applicability. Center Axle Assy 2 161W1163-1, -3, -5, -7, -11, -13, or15 Refer to APPENDIX A for part number applicability. Inner Cylinder Assy 2 161W1120-3, -5

Refer to APPENDIX A for part number applicability. Inner Cylinder Assy 2 161W1255-1, -5, - 7 Refer to APPENDIX A for part number applicability. Inner Cylinder Assy 2 161W2120-1, -3 (a) Bushing, Inner Cylinder 4 161W1122-2 Oversized part. (a) (b) Bushing, Inner Cylinder 4 161W1122-3 (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 34 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Pur**  **c hase Data:** 
**Unit Price Name**  **Tool Kit Number** Contact Boeing Spares for Current Pricing InformationMisc 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.
**Name Tool Kit Number**  Misc Tool - Bushing Replacement and Honing Kit - Inner Cyl Ctr Axle MIT161W1122

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 35 of 71 **BOEING SERVICE BULLETIN 777-32-0080**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 36 of 71 **BOEING SERVICE BULLETIN 777-32-0080**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CA UTION:**  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. **NO TE:**  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: P** 

**AR T 1 - MAIN LANDING GEAR PIV** **O T JOINT LUBRICA**  **TION** 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 37 of 71 **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: P** 

**AR T 2 - MLG PIV** **O T 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: P** 

**AR T 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 38 of 71 **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: P** 

**AR T 4 - INNER CYLINDER B**  **USHING 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: P** 

**AR T 5 - INNER CYLINDER B**  **USHING MIGRA TION AND R**  **O T**  **A**

**TION 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 39 of 71 **BOEING SERVICE BULLETIN 777-32-0080**(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: P** 

**AR T 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1: April 16, 2009 40 of 71 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Refer to SOPM 20-30-03 as an accepted procedure. 1

- Center Axle Clean 1

Do a Detailed Inspection of the outer diameter for chickenwire cracks, corrosion and chrome plate distress. (a) (b) (c) (d) 1

- Center Axle Inspect 2

Do a Magnetic Particle Inspection of the outer diameter forcracks in accordance with SOPM 20-20-01. 1

- Center Axle Inspect 3

(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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 41 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 42 of 71 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Refer to SOPM 20-30-03 as an accepted procedure. 1

- Center Axle Clean 1

Do a Detailed Inspection of the outer diameter for chickenwire cracks, corrosion and chrome plate distress. (a) (b) (c) (d) 1

- Center Axle Inspect 2

Do a Magnetic Particle Inspection of the outer diameter forcracks in accordance with SOPM 20-20-01. 1

- Center Axle Inspect 3

**FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 43 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 44 of 71 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 45 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Clean inner diameter, grease grooves and around flange area. Refer to SOPM 20-30-03 asan accepted procedure. 2

- Inner Cylinder Bushings Clean 1

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

- Inner Cylinder Bushings Inspect 2

For wear limits in accordance with CMM 32-11-07 or CMM 32-11-64, as applicable. 2

- Inner Cylinder Bushings Inspect 3

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) - ROYCO 11MS Grease Apply 4

(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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 46 of 71 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Clean inner diameter, grease grooves and around flange area. Refer to SOPM 20-30-03 asan accepted procedure. 2

- Inner Cylinder Bushings Clean 1

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

- Inner Cylinder Bushings Inspect 2

For wear limits in accordance with CMM 32-11-07 or CMM 32-11-64, as applicable. 2

- Inner Cylinder Bushings Inspect 3

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) - ROYCO 11MS Grease Apply 4

(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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 48 of 71 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 49 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Do a Detailed Inspection of the bushing flange for signs of migration or rotation. (a) 2

- Inner Cylinder Bushings Inspect 1

If any crackedsealant is found. Locally remove cracked sealant and determine if the sealant is cracked to the lug face. - - Sealant Remove 2

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 asan accepted procedure. - - Inner Cylinder Lug Face Clean 3

To restore fillet seal.

- BMS 5-95 Sealant Apply If sealant is found to be cracked to the lug face, clean lug face in area wheresealant was removed. Refer to SOPM 20-30-03 asan accepted procedure. - - Inner Cylinder Lug Face Clean 4

Do a detailed inspection for corrosion in the area where thesealant was removed. - - Inner Cylinder Lug Face Inspect

**FIGURE 5: LEFT 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 777-32-0080 Revision 1 April 16, 2009 50 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** If no corrosion is found, remove 0.10 - 0.20 inch length of fillet seal at two ormore locations to allow moisture to escape when the corrosion inhibiting compound is applied. - - Sealant Remove 5

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 777-32-0080 Revision 1 April 16, 2009 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 777-32-0080 Revision 1 April 16, 2009 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Do a Detailed Inspection of the bushing flange for signs of migration or rotation. (a) 2

- Inner Cylinder Bushings Inspect 1

If any crackedsealant is found. Locally remove cracked sealant and determine if the sealant is cracked to the lug face. - - Sealant Remove 2

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 asan accepted procedure. - - Inner Cylinder Lug Face Clean 3

To restore fillet seal.

- BMS 5-95 Sealant Apply If sealant is found to be cracked to the lug face, clean lug face in area wheresealant was removed. Refer to SOPM 20-30-03 asan accepted procedure. - - Inner Cylinder Lug Face Clean 4

Do a detailed inspection for corrosion in the area where thesealant 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 777-32-0080 Revision 1 April 16, 2009 53 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** If no corrosion is found, remove 0.10 - 0.20 inch length of fillet seal at two ormore locations to allow moisture to escape when the corrosion inhibiting compound is applied. - - Sealant Remove 5

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 777-32-0080 Revision 1 April 16, 2009 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 777-32-0080 Revision 1 April 16, 2009 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. **NO TE:**  Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator equivalent tools can be used.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Refer to toolMIT161W1122 instructions. (a) 2

- Inner Cylinder Bushings Remove 1

Refer to SOPM 20-30-03 as an accepted procedure. 2

- Inner Cylinder Bore and Face Clean 2

from lug bore and faces. Refer to SOPM 20-30-02 asan accepted procedure. - BMS 10-79, TYPE III Primer Remove 3

Do a Detailed Inspection of the lug bore inner diameter for cracks, corrosion or bronze transfer and the lug bore facesfor cracks or corrosion. 2

- Inner Cylinder Bore and Face Inspect 4

Do a Penetrant Inspection in accordance with SOPM20-20-02 for corrosion. 2

- Inner Cylinder Bore and Face Inspect 5

Do a Magnetic Particle Inspection in accordance with SOPM 20-20-01 for cracks. - - Inner Cylinder Bore and Face Inspect 6

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 56 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) From the area in the lug bore andfaces where corrosion or bronze transfer was found. Remove the cadmiumplate by manual application of ammonium nitrate solution. Make sure adjacent areas are protected where cadmium plating removal is not required. Refer to SOPM 20-30-02as an accepted procedure. - - Cadmium Plating Remove 7

(b) Do a Local Etchof Large Parts Inspection of the base metal where the cadmium platingwas removed to detect heat damage in accordance with SOPM 20-10-02. Make sure adjacent areas are protected where the nital etchinspection is not required. Ammonium Persulfate method is not allowed. 2

- Inner Cylinder Lug Bore Inspect 8

(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 777-32-0080 Revision 1 April 16, 2009 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 777-32-0080 Revision 1 April 16, 2009 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. **NO TE:**  Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator equivalent tools can be used.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Refer to toolMIT161W1122 instructions. (a) 2

- Inner Cylinder Bushings Remove 1

Refer to SOPM 20-30-03 as an accepted procedure. 2

- Inner Cylinder Bore and Face Clean 2

from lug bore and faces. Refer to SOPM 20-30-02 asan accepted procedure. - BMS 10-79, TYPE III Primer Remove 3

Do a Detailed Inspection of the lug bore inner diameter for cracks, corrosion or bronze transfer and the lug bore facesfor cracks or corrosion. 2

- Inner Cylinder Bore and Face Inspect 4

Do a Penetrant Inspection in accordance with SOPM20-20-02 for corrosion. 2

- Inner Cylinder Bore and Face Inspect 5

Do a Magnetic Particle Inspection in accordance with SOPM 20-20-01 for cracks. - - Inner Cylinder Bore and Face Inspect 6

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 59 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) From the area in the lug bore andfaces where corrosion or bronze transfer was found. Remove the cadmiumplate by manual application of ammonium nitrate solution. Make sure adjacent areas are protected where cadmium plating removal is not required. Refer to SOPM 20-30-02as an accepted procedure. - - Cadmium Plating Remove 7

(b) Do a Local Etchof Large Parts Inspection of the base metal where the cadmium platingwas removed to detect heat damage in accordance with SOPM 20-10-02. Make sure adjacent areas are protected where the nital etchinspection is not required. Ammonium Persulfate method is not allowed. 2

- Inner Cylinder Lug Bore Inspect 8

(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 777-32-0080 Revision 1 April 16, 2009 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 777-32-0080 Revision 1 April 16, 2009 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. **NO TE:**  Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator equivalent tools can be used.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  As necessary to remove any corrosion, heat damage, cracks or bronze transfer. Maximum 0.020 inchincrease in the diameter with a maximum lug bore diameter of 7.1015 inches. Refer to toolMIT161W1122 instructions. Refer to SOPM 20-10-02 asan accepted procedure. (a) - - Inner Cylinder Lug Bore Hone 1

As necessary to remove any cracks or corrosion. Blend outshallow surface irregularities and or shallow discrete pits less than 0.005 inch in depth. Refer to SOPM 20-10-02 asan accepted procedure. - - Inner Cylinder Lug Face Repair 2

Do a detailed inspection using 10 powermagnification to ensure all corrosion and bronze transfer has been removed. - - Inner Cylinder Bore and Face Inspect 3

**FIGURE 9: LEFT 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 777-32-0080 Revision 1 April 16, 2009 62 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 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 asan accepted procedure. - - Inner Cylinder Bore and Face Inspect 4

Do a Magnetic Particle inspection of therepaired areas in accordance with SOPM 20-20-01. - - Inner Cylinder Bore and Face Inspect 5

Do a Local Etch ofLarge Parts Inspection of the repaired areas to detect heatdamage 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 Inspect 6

Flapper peen the repaired areas. Refer to SOPM 20-10-03as an accepted procedure. - - Inner Cylinder Bore and Face Shot Peen 7

Record the before plating dimensions to help size new bushings. - - Inner Cylinder Bore and Face Measure 8

Apply low hydrogen embrittlement stylus cadmium plating to machined areas in accordance withSOPM 20-42-10, except 72 square inchlimit can be exceeded for the post bake requirement. - - Low Hydrogen Embrit- tlement Cadmium Plate Apply 9

**FIGURE 9: LEFT 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 777-32-0080 Revision 1 April 16, 2009 63 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to the entire bore and in other areas where primer was removed. Refer toCMM 32-11-03 Repair 4-2 or CMM 32- 11-65 Repair 5-2 asan accepted procedure, as applicable. - BMS 10-79, TYPE III Primer Apply 10

at the lubrication fittings until grease appears in the bores. If necessary, clean the lubrication passages. Remove any excess grease. - ROYCO 11MS Grease Apply 11

In accordance withCMM 32-11-03 Repair 4-2 or CMM 32- 11-65 Repair 5-2, as applicable. - 161W1122-3 Inner Cylinder Bushing Make 12

Apply a thin layer to the bores, chamfersand faces of the inner cylinder that willcontact the bushings. - BMS 5-95 Sealant Apply 13

In accordance withCMM 32-11-03 Repair 4-1 or CMM 32- 11-65 Repair 5-1, as applicable. Refer to tool MIT161W1122 instructions. - - Inner Cylinder Bushings Install (New) 14

as necessary tomeet the dimensional requirements in accordance withCMM 32-11-03 Repair 4-1 or CMM 32- 11-65 Repair 5-1, as applicable. Refer to tool MIT161W1122 instructions. (b) (c) - - Inner Cylinder Bushings Hone 15

**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 777-32-0080 Revision 1 April 16, 2009 64 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 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) - ROYCO 11MS Grease Apply 16

Refer to SOPM 20-30-03 as an accepted procedure. - - Inner Cylinder Lug Face Clean 17

Fillet seal bushing flange in accordance with CMM 32-11-03 Repair 4-1 or CMM 32-11-65 Repair 5-1, as applicable. - BMS 5-95 Sealant Apply

(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 777-32-0080 Revision 1 April 16, 2009 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 777-32-0080 Revision 1 April 16, 2009 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. **NO TE:**  Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator equivalent tools can be used.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  As necessary to remove any corrosion, heat damage, cracks or bronze transfer. Maximum 0.020 inchincrease in the diameter with a maximum lug bore diameter of 7.1015 inches. Refer to toolMIT161W1122 instructions. Refer to SOPM 20-10-02 asan accepted procedure. (a) - - Inner Cylinder Lug Bore Hone 1

As necessary to remove any cracks or corrosion. Blend outshallow surface irregularities and or shallow discrete pits less than 0.005 inch in depth. Refer to SOPM 20-10-02 asan accepted procedure. - - Inner Cylinder Lug Face Repair 2

Do a detailed inspection using 10 powermagnification to ensure all corrosion and bronze transfer has been removed. - - Inner Cylinder Bore and Face Inspect 3

**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 777-32-0080 Revision 1 April 16, 2009 67 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 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 asan accepted procedure. - - Inner Cylinder Bore and Face Inspect 4

Do a Magnetic Particle inspection of therepaired areas in accordance with SOPM 20-20-01. - - Inner Cylinder Bore and Face Inspect 5

Do a Local Etch ofLarge Parts Inspection of the repaired areas to detect heatdamage 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 Inspect 6

Flapper peen the repaired areas. Refer to SOPM 20-10-03as an accepted procedure. - - Inner Cylinder Bore and Face Shot Peen 7

Record the before plating dimensions to help size new bushings. - - Inner Cylinder Bore and Face Measure 8

Apply low hydrogen embrittlement stylus cadmium plating to machined areas in accordance withSOPM 20-42-10, except 72 square inchlimit can be exceeded for the post bake requirement. - - Low Hydrogen Embrit- tlement Cadmium Plate Apply 9

**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 777-32-0080 Revision 1 April 16, 2009 68 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to the entire bore and in other areas where primer was removed. Refer toCMM 32-11-03 Repair 4-2 or CMM 32- 11-65 Repair 5-2 asan accepted procedure, as applicable. - BMS 10-79, TYPE III Primer Apply 10

at the lubrication fittings until grease appears in the bores. If necessary, clean the lubrication passages. Remove any excess grease. - ROYCO 11MS Grease Apply 11

In accordance withCMM 32-11-03 Repair 4-2 or CMM 32- 11-65 Repair 5-2, as applicable. - 161W1122-3 Inner Cylinder Bushing Make 12

Apply a thin layer to the bores, chamfersand faces of the inner cylinder that willcontact the bushings. - BMS 5-95 Sealant Apply 13

In accordance withCMM 32-11-03 Repair 4-1 or CMM 32- 11-65 Repair 5-1, as applicable. Refer to tool MIT161W1122 instructions. - - Inner Cylinder Bushings Install (New) 14

as necessary tomeet the dimensional requirements in accordance withCMM 32-11-03 Repair 4-1 or CMM 32- 11-65 Repair 5-1, as applicable. Refer to tool MIT161W1122 instructions. (b) (c) - - Inner Cylinder Bushings Hone 15

**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 777-32-0080 Revision 1 April 16, 2009 69 of 71 **BOEING SERVICE BULLETIN 777-32-0080 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 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) - ROYCO 11MS Grease Apply 16

Refer to SOPM 20-30-03 as an accepted procedure. - - Inner Cylinder Lug Face Clean 17

Fillet seal bushing flange in accordance with CMM 32-11-03 Repair 4-1 or CMM 32-11-65 Repair 5-1, as applicable. - BMS 5-95 Sealant Apply

(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 777-32-0080 Revision 1 April 16, 2009 70 of 71 **BOEING SERVICE BULLETIN 777-32-0080 Applicable Inner Cylinder**  **Assemblies Applicable Center Axle**  **Assemblies Maximum Taxi Gross**  **Weight Airplane Model** 
161W1120-3, -5 161W1163-1, -3, -5, -7, -9, -11, -13, -15 547,000 lbs 777-200 161W1255-1, -5, -7 161W1255-1, -5, -7 161W1163-1, -3, -5, -7, -9, -11, -13, -15 652,000 lbs 777-200ER

161W1255-7 161W1163-3, -7, -9, -13, - 15 658,000 lbs 777-200ER/IGW

161W1255-7 161W1163-3, -7, -9, -13, - 15 662,000 lbs 777-300
161W2120-1, -3 161W1163-9, -15 768,800 lbs 777-200LR 161W2120-1, -3 161W1163-9, -15 777,000 lbs 777-300ER 161W2120-1, -3 161W1163-9, -15 768,800 lbs 777F

**APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 10, 2008 777-32-0080 Revision 1 April 16, 2009 71 of 71 **BOEING SERVICE BULLETIN 777-32-0080**