### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-32A0082**  Original Issue: December 09, 2010 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, KC-10, KDC-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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 1 of 61 5.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 2 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 23 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 24 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 25 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 27 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 FIGURE 1: LEFT MLG CENTER AXLE INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . . 33 FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION. . . . . . . . . . . . . . . . . . 37 FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION. . . . . . . . . . . . . . . . . . 40 FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION. . . . . . . . . . . . . . . . . . 43 FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION. . . . . . . . . . . . . . . . . 46 FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT . . 49 FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT . 55 APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL. . . . . . . . . . . . . 61

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 3 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 4 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Summary**  **Number: 777-32A0082** Original Issue: December 09, 2010 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder Pivot Joint Lubrication and Inspection THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **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 777 airplanes. The airplanes 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 collapse of a MLG. During MLG overhaul, 28 center axles have been found with cracks at the inner cylinder/truck beam pivot joint location. There have been no reports of a center axle fracture. 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 for increased lubrication, inspection and repair of the MLG pivot joint components. 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-32-0159 is related to this service bulletin. Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin. The Work Instructions of this service bulletin are equivalent to the Work Instructions of Boeing Service Bulletin (SB) 777-32-0080, which is related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 5 of 61**ACTION** 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 center axles of both MLGs. Do a detailed, magnetic particle and, if necessary, 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** 777-200, -300, -200LR, -300ER and 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **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 and times given in this service bulletin mandatory. 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. Boeing is offering an MLG center axle exchange program for those Customers who would like to purchase an exchange axle to facilitate their inspection/overhaul program. Please contact Boeing for availability and detailed terms and conditions. **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: December 09, 2010 777-32A0082 6 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 7 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 8 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-32A0082**  Original Issue: December 09, 2010 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder Pivot Joint Lubrication and Inspection THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **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.
**DESCRIPTION CONFIGURATION**  **GROUP** 777-200, -300 Airplanes line numbers 1 through 914.

- 1 Airplanes that have not done pivot joint lubrication every 50 flight cycles or 25 days, whichever occurs later, since main landing gear was new, last overhauled, last Part 2 Inspection of this service bulletin or last Part 2 Inspection of SB 777-32-0080. 1

Airplanes that have done pivot joint lubrication every 50 flight cycles or 25 days, whichever occurs later, since main landing gear was new, last overhauled, last Part 2 Inspection of this service bulletin or last Part 2 Inspection of SB 777-32-0080. 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 9 of 61**DESCRIPTION CONFIGURATION**  **GROUP** 777-200LR, -300ER and 777F Airplanes line numbers 1 through 914.

- 2 Airplanes that have not done pivot joint lubrication every 50 flight cycles or 25 days, whichever occurs later, since main landing gear was new, last overhauled, last Part 2 Inspection of this service bulletin or last Part 2 Inspection of SB 777-32-0080. 1

Airplanes that have done pivot joint lubrication every 50 flight cycles or 25 days, whichever occurs later, since main landing gear was new, last overhauled, last Part 2 Inspection of this service bulletin or last Part 2 Inspection of SB 777-32-0080. 2

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 1 WB031 - WB046 1 WB051 - WB088 1 WB101 - WB106 1 WB121 - WB125

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 10 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group**  **Variable Number** 1 WB131 - WB148 1 WB151 - WB155 1 WB161 - WB177 1 WB181 - WB194 1 WB201 - WB215 1 WB231 - WB247 1 WB271 - WB273 1 WB276 - WB286 1 WB291 - WB302 1 WB306 - WB307 1 WB311 - WB337 1 WB341 - WB342 1 WB366 - WB368 1 WB371 - WB388 1 WB406 1 WB411 - WB413 1 WB416 - WB439 1 WB446 - WB453 1 WB476 1 WB481 - WB484 1 WB501 - WB512 1 WB531 - WB537 1 WB551 - WB554 1 WB591 - WB597 1 WB601 - WB606 1 WB611 - WB622 1 WB631 - WB638 1 WB646 - WB649 1 WC051 - WC073 1 WC101 - WC104 1 WC111 - WC120 1 WC221 - WC224 1 WC241 - WC243

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 11 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group**  **Variable Number** 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 WC581 2 WD001 - WD002 2 WD011 - WD018 2 WD031 - WD036 2 WD046 - WD055 2 WD066 - WD075 2 WD081 - WD088 2 WD091 2 WD096 2 WD101 - WD103 2 WD501 - WD513 2 WD521 - WD541 2 WD546 - WD554 2 WD561 - WD573 2 WD581 - WD599 2 WD606 - WD609 2 WD621 - WD632

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 12 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group**  **Variable Number** 2 WD651 - WD665 2 WD671 - WD676 2 WD691 - WD709 2 WD741 - WD752 2 WD761 - WD771 2 WD786 - WD788 2 WD796 - WD813 2 WD826 - WD837 2 WD846 - WD861 2 WD871 - WD883 2 WD911 - WD914 2 WD921 - WD922 2 WD936 - WD939 2 WD946 - WD951 2 WD966 - WD970 2 WD981 - WD982 2 WD986 - WD987 2 WD996 2 WE001 - WE004 2 WE011 - WE012 2 WE021 - WE024 2 WE031 2 WE051 - WE052 2 WE071 2 WE081 - WE082 2 WE126 - WE131 2 WF001 - WF004 2 WF016 - WF020 2 WF031 - WF032 2 WF046 - WF053 2 WF076 - WF077 2 WF081 - WF088 2 WF096 - WF099

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 13 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group**  **Variable Number** 2 WF106 - WF107 2 WF111 - WF112 2 WF121 2. Spares Affected None. **B. Concurrent Requirements** None. **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 777 airplanes. The airplanes 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 collapse of a MLG. During MLG overhaul, 28 center axles have been found with cracks at the inner cylinder/truck beam pivot joint location. There have been no reports of a center axle fracture. 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 for increased lubrication, inspection and repair of the MLG pivot joint components. 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-32-0159 is related to this service bulletin. Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin. The Work Instructions of this service bulletin are equivalent to the Work Instructions of Boeing Service Bulletin (SB) 777-32-0080, which is related to this service bulletin. **D. Description** 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 center axles of both MLGs. Do a detailed, magnetic particle and, if necessary, 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. The work in this service bulletin is done in the maintenance zone(s) given below.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 14 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group 1:** 
**Affected Maintenance Zones Zone**  **Model** 731, 741 777-200, 777-300 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 731, 741 777-200LR, 777-300ER, 777F **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 and times given in this service bulletin mandatory. Accomplish Part 1 and Part 2 as required in Table 1, Table 2, Table 3, Table 4, Table 5 and Table 6 below in accordance with Paragraph 3., Accomplishment Instructions. Evaluate the following conditions and actions based on each independent MLG individually. **Table 1: MLG Pivot Joint Lubrication Compliance Data Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  50 flight cycles or 25 days, whichever occurs later. (a) Within 120 Days After the Original Issue Date of this Service Bulletin. Do Part 1 - MLG Pivot Joint Lubrication. (a) All Airplanes

(a) Refer to 777 MPD Section 1 Item 12-081-00 and 777 MRB Section 1 Item 12-081-00.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 15 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group 1, Configuration 1:**  **Table 2: MLG Pivot Joint Inspection for 777-200 and -300 Airplanes That Do Not Do Pivot Joint Lubrication Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear was New, Last**  **Overhauled, Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB 777-32-0080. Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** 3,750 Days Within 1,125 Days After the Original IssueDate of this Service Bulletin. Before 1) or 2): 1) MLG has notbeen overhauled: 2,250 Days After TheDate of Issuance of theOriginal Certificate of Airworthiness or the Original Export Certificate of Airworthiness. Do Part 2 - MLG Pivot Joint Inspection. (a) (b)See Table 6 for disposition of conditions found. All Airplanes

2) MLG hasbeen overhauled: 2,250 Days Since Last MLG Overhaul. (a) Overhaul of the MLG satisfies the intent of Part 2. (b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 16 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group 1, Configuration 2:**  **Table 3: MLG Pivot Joint Inspection for 777-200 and -300 Airplanes That Do Pivot Joint Lubrication Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear was New, Last Overhauled,**  **Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB 777-32-0080. Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** 3,750 Days Within 375 DaysAfter the Original Issue Date of this Service Bulletin. Before 1) or 2): 1) MLG has notbeen overhauled: 3,750 Days After TheDate of Issuance of theOriginal Certificate of Airworthiness or the Original Export Certificate of Airworthiness. Do Part 2 - MLG Pivot Joint Inspection. (a) (b)See Table 6 for disposition of conditions found. All Airplanes

2) MLG hasbeen overhauled: 3,750 Days Since Last MLG Overhaul. (a) Overhaul of the MLG satisfies the intent of Part 2. (b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 17 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group 2, Configuration 1:**  **Table 4: MLG Pivot Joint Inspection for 777-200LR, -300ER and 777F Airplanes That Do Not Do Pivot Joint Lubrication Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear**  **was New, Last Overhauled, Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB 777-32-0080.**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  3,000 Days Within 1,125 Days After the Original IssueDate of this Service Bulletin. Before 1) or 2): 1) MLG has notbeen overhauled: 1,825 Days After TheDate of Issuance of theOriginal Certificate of Airworthiness or the Original Export Certificate of Airworthiness. Do Part 2 - MLG Pivot Joint Inspection. (a) (b)See Table 6 for disposition of conditions found. All Airplanes

2) MLG hasbeen overhauled: 1,825 Days Since Last MLG Overhaul. (a) Overhaul of the MLG satisfies the intent of Part 2. (b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 18 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Group 2, Configuration 2:** **Table 5: MLG Pivot Joint Inspection for 777-200LR, -300ER and 777F Airplanes That Do Pivot Joint Lu brication Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear was**  **New, Last Overhauled, Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB 777-32-0080.**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  3,000 Days Within 300 DaysAfter the Original Issue Date of this Service Bulletin. Before 1) or 2): 1) MLG has notbeen overhauled: 3,000 Days After TheDate of Issuance of theOriginal Certificate of Airworthiness or the Original Export Certificate of Airworthiness. Do Part 2 - MLG Pivot Joint Inspection. (a) (b)See Table 6 for disposition of conditions found. All Airplanes

2) MLG hasbeen overhauled: 3,000 Days Since Last MLG Overhaul. (a) Overhaul of the MLG satisfies the intent of Part 2. (b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2. **Table 6: Parts 2-5 Inspection Findings and Disposition Repeat Interval**  **(Not to Exceed) Compliance Time**  **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 19 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Table 6: Parts 2-5 Inspection Findings and Disposition**  **Repeat Interval (Not to Exceed)**  **Compliance Time 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.

- - 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 5 - 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, no corrosion is found and thegrease flow is not restricted.

- - Before further flight. Do Part 5 - 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 corrosion is foundor the grease flow is restricted.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 20 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Table 6: Parts 2-5 Inspection Findings and Disposition**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- - Before further flight. Refinish the lug bore and faces and install new bushings in accordance with Part 5, Condition 6. Condition 6: No crack is found, no corrosion is found, no heat damage is found and no bronze transfer is found.

- - Before further flight. Repair the inner cylinder in accordance with Part 5, Condition 7, Option 1. Condition 7: Any crack is found, any corrosion is found, any heat damage isfound or any bronze transfer is found in the inner cylinder bore. -ORRepair the inner cylinder in accordance with Part 5, Condition 7, Option 2.-ORReplace inner cylinder with a new, overhauled or serviceable inner cylinder in accordance with Part 5, Condition 7, Option 3. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 21 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Elapsed Hours**  **Task Hours Number of Per-**  **sons Task** 

2.00 4.00 2 Part 1 (a) 2.00 4.00 TOTAL FOR EACH AIRPLANE(a) Additional time may be required for cold weather lubrication. Refer to 777-SL12-006 for cold weather lubrication recommendations when temperatures are below 0 degrees Celsius. **Elapsed Hours Task Hours**  **Number of Per- sons**  **Task**

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 4.50 (a) 9.00 (a) 2 Part 5: Figure 5 4.50 (a) 9.00 (a) 2 Part 5: Figure 6 (b) (b) Part 5: Figure 7 (b) (b) Part 5: Figure 8 34.50 90.50 TOTAL FOR EACH AIRPLANE (a) Estimate assumes Condition 6 is found. If Condition 7 is found, more time will be necessary. (b) Estimate assumes Condition 6 is found. If Condition 7 is found, work in FIGURE 7 and FIGURE 8 will require additional time. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Boeing Service Bulletin 777-32-0080 b. Boeing Service Letter 777-SL-12-006, 777-SL-32-001, 777-SL-32-059, 777-SL-32-061 c. Boeing Service Related Problem (SRP) 777-SRP-32-0159

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 22 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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 Maintenance Planning Data (MPD) Section 1Item 12-081-00 h. 777 Maintenance Review Board Report (MRB) 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. **K. Publications Affected** 1. Publications: **Chapter-Section**

**Publication** 32-11 Component Maintenance Manual Section 2, ATA 12 777 Maintenance Review Board Report Section 1, ATA 12 777 Maintenance Planning Data Document 32-11 777 Maintenance Manual 32-11 777 Illustrated Parts Catalog 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 23 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT 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: December 09, 2010 777-32A0082 24 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT 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
**Unit Price as of the original issue date** **of this Service Bul letin (US Dollars)**  **ROLT as of the original**  **issue date of this Service** **Bulletin (Cal endar Days)**  **Name Part Number** 

$54,030.00 623 Center Axle Assy 161W1163-13 $54,030.00 623 Center Axle Assy 161W1163-15 $242,622.00 1624 Inner Cylinder Assy 161W1255-7 $254,847.00 1344 Inner Cylinder Assy 161W2120-3 $2,928.00 301 Bushing, Inner Cylinder 161W1122-2 $3,526.00 301 Bushing, Inner Cylinder 161W1122-3 **B. Industry Support Information** Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. Boeing is offering an MLG center axle exchange program for those Customers who would like to purchase an exchange axle to facilitate their inspection/overhaul program. Please contact Boeing for availability and detailed terms and conditions. **C. Parts Necessary For Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** Grease

- Royco 11MS

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 25 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Notes**  **Name QTY**  **Part Number / Specification**  (c) Sealant

- BMS 5-95 (c) Primer

- BMS 10-79, Type III (c) Corrosion Inhibiting Compound

- BMS 3-23, Type II, Class 1 (c) Optional. Corrosion Inhibiting Compound

- BMS 3-26, Type I (c) 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. Refer to CMM 32-11-03 or CMM 32-11-65 as an accepted procedure, as applicable. (b) The 161W1122-3 bushing is preferred over the 161W1122-2 bushing due to larger lube passages. (c) See the Qualified Parts List at the end of the Boeing Material Specification (BMS) for supplier data.
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: December 09, 2010 777-32A0082 26 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Purchase 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: December 09, 2010 777-32A0082 27 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 28 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. Use the approved fastener and process material substitutions in accordance with 777 SRM, Chapter 51. Alternate fasteners are listed in 777 SRM Chapter 51 and Boeing Drawing 012W6100. 5. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 7. Refer to Appendix A for Part Interchangeability Based on Airplane Model. **B. WORK INSTRUCTIONS PART 1 - MAIN LANDING GEAR PIVOT JOINT LUBRICATION**  1. Install the main landing gear (MLG) and nose landing gear (NLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure. 2. Install the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure. 3. Lubricate the MLG pivot joints. Refer to 777 AMM 12-21-14 as an accepted procedure. Refer to 777-SL-12-006 for cold weather lubrication.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 29 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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. **PART 2 - MLG PIVOT JOINT INSPECTION** 1. Install the main landing gear (MLG) and nose landing gear (NLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure. 2. Install the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure. 3. Remove the left and right MLG center axles. Refer to 777 AMM 32-11-26 as an accepted procedure. 4. Do Part 3 - Center Axle Inspection. 5. Install the left and right MLG center axles. Refer to 777 AMM 32-11-26 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. **PART 3 - CENTER AXLE INSPECTION** 1. Inspect the center axles in accordance with the figures below:
**RIGHT MLG LEFT MLG**  FIGURE 2 FIGURE 1 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. 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. Refer to CMM 32-11-07 Repair 7-2 or CMM 32-11-64 Repair 5-2 as an accepted procedure, as applicable. (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. c. Condition 3: Any crack found, excluding chicken wire cracks.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 30 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**(1) Option 1: Repair the center axle. Refer to CMM 32-11-07 Repair 7-2 or CMM 32-11-64 Repair 5-2 as an accepted procedure, as applicable. (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 5 - Inner Cylinder Lug Bore Inspection. **PART 4 - INNER CYLINDER BUSHING INSPECTION** 1. Inspect the inner cylinder bushings and lug faces in accordance with the figures below:
**RIGHT MLG LEFT MLG**  FIGURE 4 FIGURE 3 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, no corrosion 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 corrosion is found or the grease flow is restricted. (1) Do Part 5 - Inner Cylinder Lug Bore Inspection. **PART 5 - INNER CYLINDER LUG BORE INSPECTION** 1. Inspect the inner cylinder lug bores in accordance with the figures below, as applicable:
**RIGHT MLG LEFT MLG**  FIGURE 6 FIGURE 5 a. Condition 6: 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 or face. (1) Refinish the lug bore and faces. Refer to SOPM 20-42-10 and CMM 32-11-03 Repair 4-2 or CMM 32-11-65 Repair 5-2 as accepted procedures, as applicable. (2) Install new bushings. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65 Repair 5-1 as accepted procedures, as applicable. b. Condition 7: 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 or face. (1) Option 1: Repair the inner cylinder in accordance with the figures below, as applicable:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 31 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT RIGHT MLG**  **LEFT MLG** FIGURE 8 FIGURE 7 (2) Option 2: Repair the inner cylinder. Refer to CMM 32-11-03 Repair 4-2 or CMM 32-11-65 Repair 5-2 as accepted procedures, 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: December 09, 2010 777-32A0082 32 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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 chrome for chicken wire cracks, corrosion andchrome plate distress. (a) (b) (c) (d) 1

- Center Axle Inspect 2

Do a Magnetic Particle Inspection of the outer diameter chrome for cracks in the area common to the inner cylinderbushings plus a minimum of 2 inches on both sides. Refer to SOPM 20-20-01 asan accepted procedure. 1

- Center Axle Inspect 3

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 33 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT 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, darkened streaks or bronze transfer deposits which are removed by hand sanding with a non-metallic fine abrasive material is acceptable. (d) A Fluorescent Penetrant Inspection can be used to supplement the detailed inspection of large areas for chrome plate distress. Refer to SOPM 20-20-02 as an accepted procedure.

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 34 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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 chrome for chicken wire cracks, corrosion andchrome plate distress. (a) (b) (c) (d) 1

- Center Axle Inspect 2

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 35 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Do a Magnetic Particle Inspection of the outer diameter chrome for cracks in the area common to the inner cylinderbushings plus a minimum of 2 inches on both sides. Refer to SOPM 20-20-01 asan accepted procedure. 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. 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, darkened streaks or bronze transfer deposits which are removed by hand sanding with a non-metallic fine abrasive material is acceptable. (d) A Fluorescent Penetrant Inspection can be used to supplement the detailed inspection of large areas for chrome plate distress. Refer to SOPM 20-20-02 as an accepted procedure.

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 36 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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.

**FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 37 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean inner diameters, 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 diameters and flanges for cracks, smearing of material into the lubrication grooves and bushing distress. (a) (b) (e) (f) 2

- Inner Cylinder Bushings Inspect 2

For wear limits. Refer to CMM 32-11-07 or CMM 32-11-64 asan accepted procedure, as applicable. 2

- Inner Cylinder Bushings Inspect 3

Through the lube fittings to make sure the grease flow is not restricted.Grease should appear through at least two grease holes in the bushing. (c) (d) (g) - ROYCO 11MS Grease Apply 4

Do a Detailed Inspection for corrosion. (h) 4

- Inner Cylinder Lug Face Inspect 5 (a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.(b) Darkened areas, heat discoloration and burnishing which are removed by hand sanding with a nonmetallic fine abrasive material is acceptable. (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 bushing through-wall holes is allowed to redirect grease to other through-wall holes. (e) Bushing distress and smearing of material into the lubrication grooves that has been removed by honingthe bushing up to a diameter of 6.7545 inches is acceptable. Refer to tool MIT161W1122 for honing instructions. Final bushing bore diameters must be within 0.0015 inches of each other.

**FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 38 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (f) For improved access to bushing flanges, it is acceptable to remove the truck beam. Refer to 777 AMM 32-11-18 as an accepted procedure. (g) If the bushing has one grease hole, make sure grease appears through that hole. (h) 777-SL-32-061 has information about corrosion prevention.

**FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 39 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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.

**FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 40 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean inner diameters, 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 diameters and flanges for cracks, smearing of material into the lubrication grooves and bushing distress. (a) (b) (e) (f) 2

- Inner Cylinder Bushings Inspect 2

For wear limits. Refer to CMM 32-11-07 or CMM 32-11-64 asan accepted procedure, as applicable. 2

- Inner Cylinder Bushings Inspect 3

Through the lube fittings to make sure the grease flow is not restricted.Grease should appear through at least two grease holes in the bushing. (c) (d) (g) - ROYCO 11MS Grease Apply 4

Do a Detailed Inspection for corrosion. (h) 4

- Inner Cylinder Lug Face Inspect 5 (a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.(b) Darkened areas, heat discoloration and burnishing which are removed by hand sanding with a nonmetallic fine abrasive material is acceptable. (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 bushing through-wall holes is allowed to redirect grease to other through-wall holes. (e) Bushing distress and smearing of material into the lubrication grooves that has been removed by honingthe bushing up to a diameter of 6.7545 inches is acceptable. Refer to tool MIT161W1122 for honing instructions. Final bushing bore diameters must be within 0.0015 inches of each other.

**FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 41 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (f) For improved access to bushing flanges, it is acceptable to remove the truck beam. Refer to 777 AMM 32-11-18 as an accepted procedure. (g) If the bushing has one grease hole, make sure grease appears through that hole. (h) 777-SL-32-061 has information about corrosion prevention.

**FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 42 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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.

**FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 43 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT NOTE:**  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 bores and faces common to thebushing flange (unpainted surface). Make sure primer has been completely removed. Refer to SOPM 20-30-02 asan accepted procedure. - - Primer Remove 3

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

- Inner Cylinder Bore and Face Inspect 4

Do a Penetrant Inspection for corrosion. Refer to SOPM20-20-02 as an accepted procedure. (c) (d) 2

- Inner Cylinder Bore and Face Inspect 5

Do a Magnetic Particle Inspection for cracks. Refer to SOPM 20-20-01 asan accepted procedure. (d) 2

- Inner Cylinder Bore and Face Inspect 6

**FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 44 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) From the lug bores and faces.Remove the cadmium plate by manualapplication of ammonium nitrate solution. Refer to SOPM 20-30-02 as an accepted procedure. Make sure adjacent areas are protected wherecadmium plating removal is not required. (d) - - 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. Refer to SOPM 20-10-02 as an accepted procedure. Make sure adjacent areas are protected wherethe nital etch inspection is not required.Ammonium Persulfate method is not allowed. (d) 2

- Inner Cylinder Lug Bore Inspect 8

(a) Bushing removal is only required at the location where corrosion, bushing damage, bushing beyond wear limit or axle crack was found. (b) This step is only required if a crack or bronze transfer is found on the inner cylinder lug bore or if a crack is found on the center axle.(c) Bushing removal can result in smeared cadmium in the lug bore. Smeared cadmium can give false indications of corrosion. Remove cadmium and reinspect to make sure any corrosion indications resulting from smeared cadmium are removed.(d) This step is not necessary if the only bushing condition resulting in bushing removal was grease flow restriction unless damage was found during the Detailed Inspection.

**FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 45 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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.

**FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 46 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT NOTE:**  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 bores and faces common tobushing flange (unpainted surface). Make sure primer has been completely removed. Refer to SOPM 20-30-02 asan accepted procedure. - - Primer Remove 3

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

- Inner Cylinder Bore and Face Inspect 4

Do a Penetrant Inspection for corrosion. Refer to SOPM20-20-02 as an accepted procedure. (c) (d) 2

- Inner Cylinder Bore and Face Inspect 5

Do a Magnetic Particle Inspection for cracks. Refer to SOPM 20-20-01 asan accepted procedure. (d) 2

- Inner Cylinder Bore and Face Inspect 6

**FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 47 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) From the lug bores and faces.Remove the cadmium plate by manualapplication of ammonium nitrate solution. Refer to SOPM 20-30-02 as an accepted procedure. Make sure adjacent areas are protected wherecadmium plating removal is not required. (d) - - 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. Refer to SOPM 20-10-02 as an accepted procedure. Make sure adjacent areas are protected wherethe nital etch inspection is not required.Ammonium Persulfate method is not allowed. (d) 2

- Inner Cylinder Lug Bore Inspect 8

(a) Bushing removal is only required at the location where corrosion, bushing damage, bushing beyond wear limit or axle crack was found. (b) This step is only required if a crack or bronze transfer is found on the inner cylinder lug bore or if a crack is found on the center axle.(c) Bushing removal can result in smeared cadmium in the lug bore. Smeared cadmium can give false indications of corrosion. Remove cadmium and reinspect to make sure any corrosion indications resulting from smeared cadmium are removed.(d) This step is not necessary if the only bushing condition resulting in bushing removal was grease flow restriction unless damage was found during the Detailed Inspection.

**FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 48 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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.

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 1 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 49 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT NOTE:**  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 of the repaired area for corrosion and bronze transfer using 10 powermagnification. Repeat repair procedure beginning at Step 1 if corrosion or bronze transfer is found. - - Inner Cylinder Bore and Face Inspect 3

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 2 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 50 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Do a penetrant inspection of the repaired areas forcracks and corrosion. Refer to SOPM20-20-02 as an accepted procedure.Repeat repair procedure beginning at Step 1 if crack or corrosion is found. - - Inner Cylinder Bore and Face Inspect 4

Do a Magnetic Particle inspection of the repaired areas for cracks. Refer to SOPM 20-20-01 asan accepted procedure. Repeat repair procedure beginning at Step 1 if crack is found. - - Inner Cylinder Bore and Face Inspect 5

Do a Local Etch ofLarge Parts Inspection of the repaired areas to detect heat damage. Refer to SOPM 20-10-02 asan accepted procedure. Make sure adjacent areas are protected where the nital etch inspectionis not required. Repeat repair procedure beginning atStep 1 if heat damage is found. - - 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

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 3 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 51 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Apply low hydrogen embrittlement stylus cadmium plating toareas where cadmium plating was removed, except 72 square inch limit can be exceeded for thepost bake requirement. Refer to SOPM 20-42-10 asan accepted procedure. - - Low Hydrogen Embrit- tlement Cadmium Plate Apply 9

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

Refer to CMM 32- 11-03 Repair 4-2 orCMM 32-11-65 Repair 5-2 as an accepted procedure, 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

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 52 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to CMM 32- 11-03 Repair 4-1 orCMM 32-11-65 Repair 5-1 as an accepted procedure, as applicable. Refer to toolMIT161W1122 instructions. - - Inner Cylinder Bushings Install (New) 14

at the lubrication fittings until grease appears in the bores. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65Repair 5-1 as an accepted procedure, as applicable. (d) - ROYCO 11MS Grease Apply 15

Refer to SOPM 20-30-03 as an accepted procedure. - - Inner Cylinder Lug Face Clean 16

Fillet seal bushing flange and shank end. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65Repair 5-1 as an accepted procedure, as applicable. - BMS 5-95 Sealant Apply

as necessary tomeet the dimensional requirements. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65 Repair 5-1,as an accepted procedure as applicable. Refer to toolMIT161W1122 instructions. (b) (c) - - Inner Cylinder Bushings Hone 17

(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.

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 5 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 53 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (d) Temporary plugging of through-wall holes is allowed to redirect grease to other through-wall holes.

**FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 6 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 54 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**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.

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 1 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 55 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT NOTE:**  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 of the repaired area for corrosion and bronze transfer using 10 powermagnification. Repeat repair procedure beginning at Step 1 if corrosion or bronze transfer is found. - - Inner Cylinder Bore and Face Inspect 3

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 2 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 56 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Do a penetrant inspection of the repaired areas forcracks and corrosion. Refer to SOPM20-20-02 as an accepted procedure.Repeat repair procedure beginning at Step 1 if crack or corrosion is found. - - Inner Cylinder Bore and Face Inspect 4

Do a Magnetic Particle inspection of the repaired areas for cracks. Refer to SOPM 20-20-01 asan accepted procedure. Repeat repair procedure beginning at Step 1 if crack is found. - - Inner Cylinder Bore and Face Inspect 5

Do a Local Etch ofLarge Parts Inspection of the repaired areas to detect heat damage. Refer to SOPM 20-10-02 asan accepted procedure. Make sure adjacent areas are protected where the nital etch inspectionis not required. Repeat repair procedure beginning atStep 1 if heat damage is found. - - 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

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 3 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 57 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Apply low hydrogen embrittlement stylus cadmium plating toareas where cadmium plating was removed, except 72 square inch limit can be exceeded for thepost bake requirement. Refer to SOPM 20-42-10 asan accepted procedure. - - Low Hydrogen Embrit- tlement Cadmium Plate Apply 9

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

Refer to CMM 32- 11-03 Repair 4-2 orCMM 32-11-65 Repair 5-2 as an accepted procedure, 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

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 58 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to CMM 32- 11-03 Repair 4-1 orCMM 32-11-65 Repair 5-1 as an accepted procedure, as applicable. Refer to toolMIT161W1122 instructions. - - Inner Cylinder Bushings Install (New) 14

at the lubrication fittings until grease appears in the bores. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65Repair 5-1 as an accepted procedure, as applicable. (d) - ROYCO 11MS Grease Apply 15

Refer to SOPM 20-30-03 as an accepted procedure. - - Inner Cylinder Lug Face Clean 16

Fillet seal bushing flange and shank end. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65Repair 5-1 as an accepted procedure, as applicable. - BMS 5-95 Sealant Apply

as necessary tomeet the dimensional requirements. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65 Repair 5-1as an accepted procedure, as applicable. Refer to toolMIT161W1122 instructions. (b) (c) - - Inner Cylinder Bushings Hone 17

(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.

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 5 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 59 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (d) Temporary plugging of through-wall holes is allowed to redirect grease to other through-wall holes.

**FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT (SHEET 6 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2010 777-32A0082 60 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT Applicable Inner Cylinder**  **Assemblies (a) Applicable Center Axle**  **Assemblies (a) 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 (a) Refer to 777-SL-32-001 for additional interchangeability information.

**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: December 09, 2010 777-32A0082 61 of 61 **BOEING SERVICE BULLETIN 777-32A0082 ALERT**  **ALERT**