Service Bulletin - 777-32-0085

Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 3 of 38 BOEING SERVICE BULLETIN 777-32-0085 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 4 of 38 BOEING SERVICE BULLETIN 777-32-0085 BLANK PAGE Commercial Airplanes 777 Service Bulletin SummaryNumber: 777-32-0085 Original Issue: April 14, 2011 ATA System: 3200 SUBJECT: LANDING GEAR - Main Landing Gear - Center Axle and Pivot Joint Configuration Change CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements. BACKGROUND Accomplishment of this service bulletin will change the configuration of the main landing gear (MLG) pivot joint to reduce the amount of heat generated in the center axle and the shock strut inner cylinder lugs during takeoff and landing. High levels of heat in the pivot joint can result in damage to the center axle and inner cylinder lugs which could result in significant manpower and airplane downtime to repair. During MLG overhaul, 39 center axles have been found with cracks or heat damage at the inner cylinder/truck beam pivot joint location. There have been no reports of a center axle fracture. There have been no reports of heat damage in the inner cylinder pivot bores. Heat damage and cracks were found at the pivot joint location which is caused by the truck pitching motion during normal airplane operations. Cracks were found in areas common to the inner cylinder pivot bushings where heat damage had occurred. This service bulletin provides the instructions to change the configuration of the center axle assemblies and shock strut inner cylinder assemblies of the MLGs to reduce friction in the pivot joint. Reduced friction in the pivot joint will lead to a lower amount of heat in the pivot joint which will extend the service life of the parts. Incorporation of the changes in accordance with this service bulletin and a final, one-time inspection of the pivot joint in accordance with Boeing Service Bulletin (SB) 777-32A0082, Part 2 is terminating action to the repeat inspections of SB 777-32A0082, Part 2. Incorporation of the changes in accordance with this service bulletin and incorporation of the lubrication requirements in accordance with 777 MPD Section 9, 32-CMR-01 is terminating action to the repeat lubrications of SB 777-32A0082, Part 1. Boeing Service Related Problem (SRP) 777-SRP-32-0159 is related to this service bulletin. Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin. ACTION (PRR 62777-70S) Get access to the left and right MLG wheel wells. Remove the landing gear center axles of both MLGs. Replace the center axles or change the center axles by polishing to the new configuration. Remove the inner cylinder bushings and install new inner cylinder bushings. Part mark the MLG components and assemblies. Lubricate the pivot joint with new grease. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 5 of 38 Update maintenance program in accordance with 777 MPD Section 9, 32-CMR-01 to do periodic lubrications of the MLG pivot joint. EFFECTIVITY 777-200, -300, -200LR, -300ER and 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks given in this service bulletin mandatory. No compliance time is given. Boeing recommends this service bulletin be done to introduce improvements. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 6 of 38 BOEING SERVICE BULLETIN 777-32-0085 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 7 of 38 BOEING SERVICE BULLETIN 777-32-0085 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 8 of 38 BOEING SERVICE BULLETIN 777-32-0085 BLANK PAGE Commercial Airplanes 777 Service Bulletin Number: 777-32-0085 Original Issue: April 14, 2011 ATA System: 3200 SUBJECT: LANDING GEAR - Main Landing Gear - Center Axle and Pivot Joint Configuration Change 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 62777-70S for data about this change. DESCRIPTION CONFIGURATION GROUP 777-200LR, -300ER and 777F Airplanes with line number 423- 914. - 1 777-200 and -300 Airplanes with line number 1- 868. - 2 Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER, 777F Group Variable Number 2 WA001 - WA017 2 WA076 - WA080 2 WA086 - WA093 2 WA101 - WA104 2 WA116 - WA119 2 WA131 - WA137 2 WA171 - WA175 2 WA196 - WA198 2 WA206 - WA212 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 9 of 38 Group Variable Number 2 WA221 - WA223 2 WA231 - WA232 2 WA241 - WA250 2 WA261 - WA266 2 WA281 - WA283 2 WA301 - WA304 2 WB001 - WB021 2 WB031 - WB046 2 WB051 - WB088 2 WB101 - WB106 2 WB121 - WB125 2 WB131 - WB148 2 WB151 - WB155 2 WB161 - WB177 2 WB181 - WB194 2 WB201 - WB215 2 WB231 - WB247 2 WB271 - WB273 2 WB276 - WB286 2 WB291 - WB302 2 WB306 - WB307 2 WB311 - WB337 2 WB341 - WB342 2 WB366 - WB368 2 WB371 - WB388 2 WB406 2 WB411 - WB413 2 WB416 - WB439 2 WB446 - WB453 2 WB476 2 WB481 - WB484 2 WB501 - WB512 2 WB531 - WB537 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 10 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group Variable Number 2 WB551 - WB554 2 WB591 - WB597 2 WB601 - WB606 2 WB611 - WB622 2 WB631 - WB638 2 WB646 - WB649 2 WC051 - WC073 2 WC101 - WC104 2 WC111 - WC120 2 WC221 - WC224 2 WC241 - WC243 2 WC281 - WC290 2 WC301 - WC308 2 WC361 - WC364 2 WC371 - WC374 2 WC381 - WC395 2 WC441 2 WC446 - WC449 2 WC456 - WC459 2 WC486 - WC493 2 WC506 - WC508 2 WC521 - WC522 2 WC531 - WC536 2 WC546 - WC548 2 WC556 2 WC566 - WC567 2 WC571 - WC574 2 WC581 1 WD001 - WD002 1 WD011 - WD018 1 WD031 - WD036 1 WD046 - WD055 1 WD066 - WD075 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 11 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group Variable Number 1 WD081 - WD088 1 WD091 1 WD096 1 WD101 - WD103 1 WD501 - WD513 1 WD521 - WD541 1 WD546 - WD554 1 WD561 - WD573 1 WD581 - WD599 1 WD606 - WD609 1 WD621 - WD632 1 WD651 - WD665 1 WD671 - WD676 1 WD691 - WD709 1 WD741 - WD752 1 WD761 - WD771 1 WD786 - WD788 1 WD796 - WD813 1 WD826 - WD837 1 WD846 - WD861 1 WD871 - WD883 1 WD911 - WD914 1 WD921 - WD922 1 WD936 - WD939 1 WD946 - WD951 1 WD966 - WD970 1 WD981 - WD982 1 WD986 - WD987 1 WD996 1 WE001 - WE004 1 WE011 - WE012 1 WE021 - WE024 1 WE031 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 12 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group Variable Number 1 WE051 - WE052 1 WE071 1 WE081 - WE082 1 WE126 - WE131 1 WF001 - WF004 1 WF016 - WF020 1 WF031 - WF032 1 WF046 - WF053 1 WF076 - WF077 1 WF081 - WF088 1 WF096 - WF099 1 WF106 - WF107 1 WF111 - WF112 1 WF121 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. B. Concurrent Requirements The service bulletin listed below must be done at the same time as this service bulletin: Description Service Bulletin Company A final one-time inspection of the pivot joint in accordance with Part 2 - MLG Pivot Joint Inspection is required for terminating action of the repeat inspections. 777-32A0082 Original Issue The Boeing Company C. Reason Accomplishment of this service bulletin will change the configuration of the main landing gear (MLG) pivot joint to reduce the amount of heat generated in the center axle and the shock strut inner cylinder lugs during takeoff and landing. High levels of heat in the pivot joint can result in damage to the center axle and inner cylinder lugs which could result in significant manpower and airplane downtime to repair. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 13 of 38 BOEING SERVICE BULLETIN 777-32-0085 During MLG overhaul, 39 center axles have been found with cracks or heat damage at the inner cylinder/truck beam pivot joint location. There have been no reports of a center axle fracture. There have been no reports of heat damage in the inner cylinder pivot bores. Heat damage and cracks were found at the pivot joint location which is caused by the truck pitching motion during normal airplane operations. Cracks were found in areas common to the inner cylinder pivot bushings where heat damage had occurred. This service bulletin provides the instructions to change the configuration of the center axle assemblies and shock strut inner cylinder assemblies of the MLGs to reduce friction in the pivot joint. Reduced friction in the pivot joint will lead to a lower amount of heat in the pivot joint which will extend the service life of the parts. Incorporation of the changes in accordance with this service bulletin and a final, one-time inspection of the pivot joint in accordance with Boeing Service Bulletin (SB) 777-32A0082, Part 2 is terminating action to the repeat inspections of SB 777-32A0082, Part 2. Incorporation of the changes in accordance with this service bulletin and incorporation of the lubrication requirements in accordance with 777 MPD Section 9, 32-CMR-01 is terminating action to the repeat lubrications of SB 777-32A0082, Part 1. Boeing Service Related Problem (SRP) 777-SRP-32-0159 is related to this service bulletin. Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin. D. Description Get access to the left and right MLG wheel wells. Remove the landing gear center axles of both MLGs. Replace the center axles or change the center axles by polishing to the new configuration. Remove the inner cylinder bushings and install new inner cylinder bushings. Part mark the MLG components and assemblies. Lubricate the pivot joint with new grease. Update maintenance program in accordance with 777 MPD Section 9, 32-CMR-01 to do periodic lubrications of the MLG pivot joint. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones Zone Model 731, 741 777-200LR, 777-300ER, 777F Group 2: Affected Maintenance Zones Zone Model 731, 741 777-200, 777-300 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 14 of 38 BOEING SERVICE BULLETIN 777-32-0085 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks given in this service bulletin mandatory. No compliance time is given. Boeing recommends this service bulletin be done to introduce improvements. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Elapsed Hours Task Hours Number of Persons Task 2.60 13.00 5 Open Access 9.00 36.00 4 Part 1: Figure 1 (a) 4.00 16.00 4 Part 2: Figure 2 2.60 13.00 5 Close Access 18.20 78.00 TOTAL FOR EACH AIRPLANE (a) Polish task is variable in nature and is not included in estimate. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 15 of 38 BOEING SERVICE BULLETIN 777-32-0085 H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane + 3254.5 + 2.4 All Airplanes I. Electrical Load Data Not changed. J. References 1. Existing Data a. Engineering Change Memo PRR 62777-70S b. Boeing Service Bulletin 777-32A0082 c. Boeing Service Letter 777-SL-32-001, 777-SL-32-059 d. Boeing Service Related Problem (SRP) 777-SRP-32-0159 e. Component Maintenance Manual (CMM) 32-11-03, 32-11-07, 32-11-64, 32-11-65 f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-42-03, 20-42-10, 20-50-10, 20-60-02 g. 777 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-30, 32-11-26 h. 777 Maintenance Planning Data (MPD) Section 9, 32-CMR-01 2. Data supplied with this Service Bulletin a. Drawings: ADCN DCN/REV Sheet Title Drawing No - B 1 Misc Tool Replacement and Honing Kit In- ner Cyl Ctr Axle MIT161W1122 - - 2 - - 3 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 16 of 38 BOEING SERVICE BULLETIN 777-32-0085 K. Publications Affected 1. Publications: Chapter-Section Publication 12-21, 32-11 777 Aircraft Maintenance Manual 32-11 777 Illustrated Parts Catalog 32-11 Component Maintenance Manual Section 9, ATA 32 777 Maintenance Planning Data Document 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 17 of 38 BOEING SERVICE BULLETIN 777-32-0085 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 18 of 38 BOEING SERVICE BULLETIN 777-32-0085 BLANK PAGE 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 Group 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) Name Part Number $5,166.00 160 Bushing - Inner Cylinder, Main Landing Gear 161W1122-4 (a) $4,685.00 160 Bushing - Inner Cylinder, Main Landing Gear 161W1122-5 (b) $59,569.00 608 Axle Assembly - Center, Main Landing Gear 161W1163-21 (a) This part can be fabricated. Refer to CMM 32-11-65 as an accepted procedure. (b) This is an oversized part. Group 2: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) Name Part Number $5,166.00 160 Bushing - Inner Cylinder, Main Landing Gear 161W1122-4 (a) $4,685.00 160 Bushing - Inner Cylinder, Main Landing Gear 161W1122-5 (b) $56,569.00 608 Axle Assembly - Center, Main Landing Gear 161W1163-19 (a) This part can be fabricated. Refer to CMM 32-11-03 as an accepted procedure. (b) This is an oversized part. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 19 of 38 BOEING SERVICE BULLETIN 777-32-0085 B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. Group 1: Notes Name QTY Part Number (a) Bushing - Inner Cylinder, Main Landing Gear 4 161W1122-4 (b) Bushing - Inner Cylinder, Main Landing Gear 4 161W1122-5 Axle Assembly - Center, Main Landing Gear 2 161W1163-21 (a) This part can be fabricated. Refer to CMM 32-11-65 as an accepted procedure. (b) This is an oversized part. Group 2: Notes Name QTY Part Number (a) Bushing - Inner Cylinder, Main Landing Gear 4 161W1122-4 (b) Bushing - Inner Cylinder, Main Landing Gear 4 161W1122-5 Axle Assembly - Center, Main Landing Gear 2 161W1163-19 (a) This part can be fabricated. Refer to CMM 32-11-03 as an accepted procedure. (b) This is an oversized part. 2. Parts and Materials Supplied by the Operator Notes Name QTY Part Number / Specification Grease - MIL-PRF-32014 (a) Sealant - BMS 5-95 (a) Enamel - BMS 10-60, Type II BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 20 of 38 BOEING SERVICE BULLETIN 777-32-0085 Notes Name QTY Part Number / Specification (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. 3. Parts Modified and Reidentified Refer to APPENDIX A for Part Marking and Reidentification. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the date the tools will be used. Purchase Data: Unit Price Name Tool Kit Number Contact Boeing Spares for Current Pricing Information Misc Tool - Bushing Replace- ment and Honing Kit - Inner Cyl Ctr Axle MIT161W1122 The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. After the Price date, new price data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin number and submit purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Mail to: Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA (Service Bulletin 777-32-0085) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 21 of 38 BOEING SERVICE BULLETIN 777-32-0085 F. Special Tooling Necessary to do this Service Bulletin To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available. Name Tool Kit Number Misc Tool - Bushing Replace- ment and Honing Kit - Inner Cyl Ctr Axle MIT161W1122 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 22 of 38 BOEING SERVICE BULLETIN 777-32-0085 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 5. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 6. Refer to APPENDIX A for Part Marking Reidentification. B. WORK INSTRUCTIONS Airplane Work 1. Install the main landing gear (MLG) and nose landing gear (NLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure. 2. Install the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure. 3. Remove the left and right MLG center axles. Refer to 777 AMM 32-11-26 as an accepted procedure. 4. Change both the left and right MLG center axles in accordance with Part 1 - Center Axle Change. 5. Change both the left and right MLG inner cylinder assemblies in accordance with Part 2 - Inner Cylinder Change. 6. Install the left and right MLG changed center axles. Refer to 777 AMM 32-11-26 as an accepted procedure. 7. Lubricate the MLG pivot joint using MIL-PRF-32014 grease. Refer 777 AMM 12-21-14 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 23 of 38 BOEING SERVICE BULLETIN 777-32-0085 8. Apply new part mark to the left and right MLG component and buildup assemblies. Refer to SOPM 20-50-10 as an accepted procedure. Refer to APPENDIX A for new part numbers. 9. Remove the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure. 10. Remove the MLG and NLG downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure. 11. Put the airplane back into serviceable condition. 12. Update maintenance program in accordance with 777 MPD Section 9, 32-CMR-01 to do periodic lubrications of the MLG pivot joint. Use MIL-PRF-32014 grease only. Refer to 777 AMM 12-21-14 as an accepted procedure. PART 1 - CENTER AXLE CHANGE 1. Option 1: Replace existing center axle assembly with new, overhauled or serviceable center axle assembly, as applicable. Refer to APPENDIX B for part number applicability. 2. Option 2: Change the existing center axle assembly in accordance with FIGURE 1. PART 2 - INNER CYLINDER CHANGE 1. Option 1: Replace existing inner cylinder assembly with new, overhauled or serviceable inner cylinder assembly, as applicable. Refer to APPENDIX B for part number applicability. 2. Option 2: Change existing inner cylinder assembly in accordance with FIGURE 2. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 24 of 38 BOEING SERVICE BULLETIN 777-32-0085 MORE DATA QTY IDENTIFICATION NAME TASK STEP Polish, lap or re- dress the chrome plate on the center journal outside diam- eter to a surface roughness of 8 Ra or better. Refer to SOPM 20-42-03 as an accepted proce- dure. Grinding of the chrome plate is not allowed. Operations which produce sparks are not al- lowed. (a) 1 - Center Axle Polish 1 to center axle and center axle assem- bly. Refer to CMM 32-11-07, Repair 7- 2 or CMM 32-11-64, Repair 5-2 as an ac- cepted procedure, as applicable. Refer to APPENDIX A for new part numbers and part marking methods. - - Part Mark Apply 2 FIGURE 1: CENTER AXLE CHANGE (SHEET 1 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 25 of 38 BOEING SERVICE BULLETIN 777-32-0085 MORE DATA QTY IDENTIFICATION NAME TASK STEP Restore any dam- aged finishes. Refer to CMM 32-11-07, Repair 7-2 or CMM 32-11-64, Repair 5- 2 as an accepted procedure, as appli- cable. - - Finishes Apply 3 (a) If using cooling fluid during polishing, remove wheel sleeves prior to polishing. Reinstall wheel sleeves after polishing. Refer to CMM 32-11-07, Repair 7-1 or CMM 32-11-64, Repair 5-1 as an accepted procedure, as applicable. FIGURE 1: CENTER AXLE CHANGE (SHEET 2 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 26 of 38 BOEING SERVICE BULLETIN 777-32-0085 MORE DATA QTY IDENTIFICATION NAME TASK STEP Refer to tool MIT161W1122 in- structions. 2 161W1122-2 (161W1122-1 or 161W1122-3 optional) Bushing, Inner Cylinder Remove 1 Refer to SOPM 20- 30-03 as an accept- ed procedure. - - Inner Cylinder Bore and Faces Clean 2 FIGURE 2: INNER CYLINDER CHANGE (SHEET 1 OF 3) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 27 of 38 BOEING SERVICE BULLETIN 777-32-0085 MORE DATA QTY IDENTIFICATION NAME TASK STEP Restore any cadmi- um plating and any primer that is miss- ing. Refer to CMM 32-11-03, Repair 4- 2 or CMM 32-11-65, Repair 5-2, as appli- cable, and SOPM 20-42-10 as accept- ed procedures. - - Finishes Apply 3 Refer to CMM 32- 11-03, Repair 4-1 or CMM 32-11-65, Re- pair 5-1 as an ac- cepted procedure, as applicable. Refer to tool MIT161W1122 in- structions. 2 161W1122-4 (161W1122-5 optional) Bushing, Inner Cylinder Install (New) 4 at the lubrication fit- tings until grease appears in bushing inner diameter at all through-wall hole lo- cations. Temporary plugging of individu- al bushing holes is allowed to make sure grease gets to all through-wall hole locations. Refer to CMM 32-11-03, Re- pair 4-1 or CMM 32- 11-65, Repair 5-1 as an accepted proce- dure, as applicable. - MIL-PRF-32014 Grease Apply 5 FIGURE 2: INNER CYLINDER CHANGE (SHEET 2 OF 3) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 28 of 38 BOEING SERVICE BULLETIN 777-32-0085 MORE DATA QTY IDENTIFICATION NAME TASK STEP Refer to SOPM 20- 30-03 as an accept- ed procedure. 4 - Inner Cylinder Lug Faces Clean 6 Fillet seal bushing flange and shank end. Refer to CMM 32-11-03, Repair 4- 1 or CMM 32-11-65, Repair 5-1 as an ac- cepted procedure, as applicable. - BMS 5-95 Sealant Apply Refer to SOPM 20- 60-02 as an accept- ed procedure. Use color 707 Gray. - BMS 10-60 TYPE II Enamel Apply as necessary to meet the dimension- al requirements. Re- fer to CMM 32-11- 03, Repair 4-1 or CMM 32-11-65, Re- pair 5-1 as an ac- cepted procedure, as applicable. Refer to tool MIT161W1122 in- structions. (a) (b) 2 161W1122-4 (161W1122-5 optional) Bushing, Inner Cylinder Hone 7 to inner cylinder as- sembly. Refer to SOPM 20-50-10, code RH as an ac- cepted procedure. Refer to APPENDIX A for new part num- bers and part mark- ing methods. Re- move existing part markings. - - Part Mark Apply 8 (a) Bushing bores must be concentric within 0.0005 inches. (b) Final bushing bore diameters must be within 0.0015 inches of each other. FIGURE 2: INNER CYLINDER CHANGE (SHEET 3 OF 3) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 29 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 1: Notes Part Marking Method New Part Number Component Name Existing Part Number Center Axle Component and Assembly (a) (b) Rubber Stamp, Code RH (e) 161W1163-9 Center Axle Assembly 161W1163-9 (a) (b) Electrochemical Etch or Vibro-engrave (e) 161W1163-10 . Center Axle 161W1163-10 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1163-21 Center Axle Assembly 161W1163-15 (a) (c) (d) Electrochemical Etch or Vibro-engrave (e) 161W1163-22 . Center Axle 161W1163-16 Inner Cylinder Assembly (a) (b) Rubber Stamp, Code RH (e) 161W2120-1 Inner Cylinder Assem- bly 161W2120-1 (a) (c) (d) Rubber Stamp, Code RH (e) 161W2120-5 Inner Cylinder Assem- bly 161W2120-3 MLG Component Assembly (a) (b) Name Plate Vibro-en- grave (e) 161W2100-1 MLG Component As- sembly 161W2100-1 (a) (b) Name Plate Vibro-en- grave (e) 161W2100-2 MLG Component As- sembly 161W2100-2 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W2100-7 MLG Component As- sembly 161W2100-3 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W2100-8 MLG Component As- sembly 161W2100-4 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W2100-9 MLG Component As- sembly 161W2100-5 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W2100-10 MLG Component As- sembly 161W2100-6 MLG Buildup Assembly (a) (b) Rubber Stamp, Code RH (e) 161W1000-43 MLG Buildup Assembly 161W1000-43 (a) (b) Rubber Stamp, Code RH (e) 161W1000-44 MLG Buildup Assembly 161W1000-44 (a) (b) Rubber Stamp, Code RH (e) 161W1000-45 MLG Buildup Assembly 161W1000-45 (a) (b) Rubber Stamp, Code RH (e) 161W1000-46 MLG Buildup Assembly 161W1000-46 APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 1 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 30 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 1: Notes Part Marking Method New Part Number Component Name Existing Part Number (a) (b) Rubber Stamp, Code RH (e) 161W1000-55 MLG Buildup Assembly 161W1000-55 (a) (b) Rubber Stamp, Code RH (e) 161W1000-56 MLG Buildup Assembly 161W1000-56 (a) (b) Rubber Stamp, Code RH (e) 161W1000-57 MLG Buildup Assembly 161W1000-57 (a) (b) Rubber Stamp, Code RH (e) 161W1000-58 MLG Buildup Assembly 161W1000-58 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-83 MLG Buildup Assembly 161W1000-59 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-84 MLG Buildup Assembly 161W1000-60 (a) (b) Rubber Stamp, Code RH (e) 161W1000-67 MLG Buildup Assembly 161W1000-67 (a) (b) Rubber Stamp, Code RH (e) 161W1000-68 MLG Buildup Assembly 161W1000-68 (a) (b) Rubber Stamp, Code RH (e) 161W1000-69 MLG Buildup Assembly 161W1000-69 (a) (b) Rubber Stamp, Code RH (e) 161W1000-70 MLG Buildup Assembly 161W1000-70 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-81 MLG Buildup Assembly 161W1000-71 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-82 MLG Buildup Assembly 161W1000-72 (a) (b) Rubber Stamp, Code RH (e) 161W1000-73 MLG Buildup Assembly 161W1000-73 (a) (b) Rubber Stamp, Code RH (e) 161W1000-74 MLG Buildup Assembly 161W1000-74 (a) Make the change in accordance with this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the change done in accordance with this service bulletin was made. (c) This is the part number after the change is done in accordance with this service bulletin. (d) This part is used in production. (e) Refer to SOPM 20-50-10 as an accepted procedure. APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 2 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 31 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 2: Notes Part Marking Method New Part Number Component Name Existing Part Number Center Axle Component and Assembly (a) (b) Rubber Stamp, Code RH (e) 161W1163-1 Center Axle Assembly 161W1163-1 (a) (b) Electrochemical Etch or Vibro-engrave (e) 161W1163-2 . Center Axle 161W1163-2 (a) (b) Rubber Stamp, Code RH (e) 161W1163-3 Center Axle Assembly 161W1163-3 (a) (b) Electrochemical Etch or Vibro-engrave (e) 161W1163-4 . Center Axle 161W1163-4 (a) (b) Rubber Stamp, Code RH (e) 161W1163-5 Center Axle Assembly 161W1163-5 (a) (b) Electrochemical Etch or Vibro-engrave (e) 161W1163-6 . Center Axle 161W1163-6 (a) (b) Rubber Stamp, Code RH (e) 161W1163-7 Center Axle Assembly 161W1163-7 (a) (b) Electrochemical Etch or Vibro-engrave (e) 161W1163-8 . Center Axle 161W1163-8 (a) (b) Rubber Stamp, Code RH (e) 161W1163-9 Center Axle Assembly 161W1163-9 (a) (b) Electrochemical Etch or Vibro-engrave (e) 161W1163-10 . Center Axle 161W1163-10 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1163-17 Center Axle Assembly 161W1163-11 (a) (c) (d) Electrochemical Etch or Vibro-engrave (e) 161W1163-18 . Center Axle 161W1163-12 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1163-19 Center Axle Assembly 161W1163-13 (a) (c) (d) Electrochemical Etch or Vibro-engrave (e) 161W1163-20 . Center Axle 161W1163-14 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1163-21 Center Axle Assembly 161W1163-15 (a) (c) (d) Electrochemical Etch or Vibro-engrave (e) 161W1163-22 . Center Axle 161W1163-16 Inner Cylinder Assembly (a) (b) Rubber Stamp, Code RH (e) 161W1120-3 Inner Cylinder Assem- bly 161W1120-3 APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 3 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 32 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 2: Notes Part Marking Method New Part Number Component Name Existing Part Number (a) (c) (d) Rubber Stamp, Code RH (e) 161W1120-7 Inner Cylinder Assem- bly 161W1120-5 (a) (b) Rubber Stamp, Code RH (e) 161W1255-1 Inner Cylinder Assem- bly 161W1255-1 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1255-9 Inner Cylinder Assem- bly 161W1255-5 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1255-10 Inner Cylinder Assem- bly 161W1255-7 MLG Component Assembly (a) (b) Name Plate Vibro-en- grave (e) 161W1100-1 MLG Component As- sembly 161W1100-1 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-2 MLG Component As- sembly 161W1100-2 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-3 MLG Component As- sembly 161W1100-3 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-4 MLG Component As- sembly 161W1100-4 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-5 MLG Component As- sembly 161W1100-5 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-6 MLG Component As- sembly 161W1100-6 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-7 MLG Component As- sembly 161W1100-7 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-8 MLG Component As- sembly 161W1100-8 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-9 MLG Component As- sembly 161W1100-9 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-10 MLG Component As- sembly 161W1100-10 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-11 MLG Component As- sembly 161W1100-11 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-12 MLG Component As- sembly 161W1100-12 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-15 MLG Component As- sembly 161W1100-15 APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 4 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 33 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 2: Notes Part Marking Method New Part Number Component Name Existing Part Number (a) (b) Name Plate Vibro-en- grave (e) 161W1100-16 MLG Component As- sembly 161W1100-16 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-17 MLG Component As- sembly 161W1100-17 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-18 MLG Component As- sembly 161W1100-18 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-19 MLG Component As- sembly 161W1100-19 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-20 MLG Component As- sembly 161W1100-20 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-21 MLG Component As- sembly 161W1100-21 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-22 MLG Component As- sembly 161W1100-22 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-23 MLG Component As- sembly 161W1100-23 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-24 MLG Component As- sembly 161W1100-24 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W1100-33 MLG Component As- sembly 161W1100-25 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W1100-34 MLG Component As- sembly 161W1100-26 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W1100-35 MLG Component As- sembly 161W1100-27 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W1100-36 MLG Component As- sembly 161W1100-28 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W1100-37 MLG Component As- sembly 161W1100-29 (a) (c) (d) Name Plate Vibro-en- grave (e) 161W1100-38 MLG Component As- sembly 161W1100-30 (a) (b) Name Plate Vibro-en- grave (e) 161W1100-31 MLG Component As- sembly 161W1100-31 MLG Buildup Assembly (a) (b) Rubber Stamp, Code RH (e) 161W1000-3 MLG Buildup Assembly 161W1000-3 APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 5 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 34 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 2: Notes Part Marking Method New Part Number Component Name Existing Part Number (a) (b) Rubber Stamp, Code RH (e) 161W1000-4 MLG Buildup Assembly 161W1000-4 (a) (b) Rubber Stamp, Code RH (e) 161W1000-5 MLG Buildup Assembly 161W1000-5 (a) (b) Rubber Stamp, Code RH (e) 161W1000-6 MLG Buildup Assembly 161W1000-6 (a) (b) Rubber Stamp, Code RH (e) 161W1000-7 MLG Buildup Assembly 161W1000-7 (a) (b) Rubber Stamp, Code RH (e) 161W1000-8 MLG Buildup Assembly 161W1000-8 (a) (b) Rubber Stamp, Code RH (e) 161W1000-9 MLG Buildup Assembly 161W1000-9 (a) (b) Rubber Stamp, Code RH (e) 161W1000-10 MLG Buildup Assembly 161W1000-10 (a) (b) Rubber Stamp, Code RH (e) 161W1000-11 MLG Buildup Assembly 161W1000-11 (a) (b) Rubber Stamp, Code RH (e) 161W1000-12 MLG Buildup Assembly 161W1000-12 (a) (b) Rubber Stamp, Code RH (e) 161W1000-13 MLG Buildup Assembly 161W1000-13 (a) (b) Rubber Stamp, Code RH (e) 161W1000-14 MLG Buildup Assembly 161W1000-14 (a) (b) Rubber Stamp, Code RH (e) 161W1000-15 MLG Buildup Assembly 161W1000-15 (a) (b) Rubber Stamp, Code RH (e) 161W1000-16 MLG Buildup Assembly 161W1000-16 (a) (b) Rubber Stamp, Code RH (e) 161W1000-17 MLG Buildup Assembly 161W1000-17 (a) (b) Rubber Stamp, Code RH (e) 161W1000-18 MLG Buildup Assembly 161W1000-18 (a) (b) Rubber Stamp, Code RH (e) 161W1000-19 MLG Buildup Assembly 161W1000-19 (a) (b) Rubber Stamp, Code RH (e) 161W1000-20 MLG Buildup Assembly 161W1000-20 (a) (b) Rubber Stamp, Code RH (e) 161W1000-21 MLG Buildup Assembly 161W1000-21 APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 6 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 35 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 2: Notes Part Marking Method New Part Number Component Name Existing Part Number (a) (b) Rubber Stamp, Code RH (e) 161W1000-22 MLG Buildup Assembly 161W1000-22 (a) (b) Rubber Stamp, Code RH (e) 161W1000-23 MLG Buildup Assembly 161W1000-23 (a) (b) Rubber Stamp, Code RH (e) 161W1000-24 MLG Buildup Assembly 161W1000-24 (a) (b) Rubber Stamp, Code RH (e) 161W1000-25 MLG Buildup Assembly 161W1000-25 (a) (b) Rubber Stamp, Code RH (e) 161W1000-26 MLG Buildup Assembly 161W1000-26 (a) (b) Rubber Stamp, Code RH (e) 161W1000-27 MLG Buildup Assembly 161W1000-27 (a) (b) Rubber Stamp, Code RH (e) 161W1000-28 MLG Buildup Assembly 161W1000-28 (a) (b) Rubber Stamp, Code RH (e) 161W1000-35 MLG Buildup Assembly 161W1000-35 (a) (b) Rubber Stamp, Code RH (e) 161W1000-36 MLG Buildup Assembly 161W1000-36 (a) (b) Rubber Stamp, Code RH (e) 161W1000-37 MLG Buildup Assembly 161W1000-37 (a) (b) Rubber Stamp, Code RH (e) 161W1000-38 MLG Buildup Assembly 161W1000-38 (a) (b) Rubber Stamp, Code RH (e) 161W1000-39 MLG Buildup Assembly 161W1000-39 (a) (b) Rubber Stamp, Code RH (e) 161W1000-40 MLG Buildup Assembly 161W1000-40 (a) (b) Rubber Stamp, Code RH (e) 161W1000-41 MLG Buildup Assembly 161W1000-41 (a) (b) Rubber Stamp, Code RH (e) 161W1000-42 MLG Buildup Assembly 161W1000-42 (a) (b) Rubber Stamp, Code RH (e) 161W1000-47 MLG Buildup Assembly 161W1000-47 (a) (b) Rubber Stamp, Code RH (e) 161W1000-48 MLG Buildup Assembly 161W1000-48 (a) (b) Rubber Stamp, Code RH (e) 161W1000-49 MLG Buildup Assembly 161W1000-49 APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 7 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 36 of 38 BOEING SERVICE BULLETIN 777-32-0085 Group 2: Notes Part Marking Method New Part Number Component Name Existing Part Number (a) (b) Rubber Stamp, Code RH (e) 161W1000-50 MLG Buildup Assembly 161W1000-50 (a) (b) Rubber Stamp, Code RH (e) 161W1000-51 MLG Buildup Assembly 161W1000-51 (a) (b) Rubber Stamp, Code RH (e) 161W1000-52 MLG Buildup Assembly 161W1000-52 (a) (b) Rubber Stamp, Code RH (e) 161W1000-53 MLG Buildup Assembly 161W1000-53 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-75 MLG Buildup Assembly 161W1000-61 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-76 MLG Buildup Assembly 161W1000-62 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-77 MLG Buildup Assembly 161W1000-63 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-78 MLG Buildup Assembly 161W1000-64 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-79 MLG Buildup Assembly 161W1000-65 (a) (c) (d) Rubber Stamp, Code RH (e) 161W1000-80 MLG Buildup Assembly 161W1000-66 (a) Make the change in accordance with this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the change done in accordance with this service bulletin was made. (c) This is the part number after the change is done in accordance with this service bulletin. (d) This part is used in production. (e) Refer to SOPM 20-50-10 as an accepted procedure. APPENDIX A: PART MARKING REIDENTIFICATION TABLE (SHEET 8 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 37 of 38 BOEING SERVICE BULLETIN 777-32-0085 Applicable Inner Cylinder Assemblies (a) Applicable Center Axle Assemblies (a) Maximum Taxi Gross Weight Airplane Model 161W1120-3, -7 (b) 161W1163-1, -3, -5, -7, -9, -17, -19, -21 (b) 547,000 lbs 777-200 161W1255-1, -9, -10 (b) 161W1255-1, -9, -10 (b) 161W1163-1, -3, -5, -7, -9, -17, -19, -21 (b) 652,000 lbs 777-200ER 161W1255-10 (b) 161W1163-3, -7, -9, -19, - 21 (b) 658,000 lbs 777-200ER/IGW 161W1255-10 (b) 161W1163-3, -7, -9, -19, - 21 (b) 662,000 lbs 777-300 161W2120-1, -5 (b) 161W1163-9, -21 (b) 768,800 lbs 777-200LR 161W2120-1, -5 (b) 161W1163-9, -21 (b) 777,000 lbs 777-300ER 161W2120-1, -5 (b) 161W1163-9, -21 (b) 768,800 lbs 777F (a) Refer to 777-SL-32-001 for additional interchangeability information. (b) Make sure every part used has been changed in accordance with this service bulletin. APPENDIX B: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL (SHEET 1 OF 1) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 14, 2011 777-32-0085 38 of 38 BOEING SERVICE BULLETIN 777-32-0085