### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-24A0119**  Original Issue: November 11, 2011 ATA System: 2421 5383 **SUBJECT:** ELECTRICAL POWER - Power and Regulation - Inspection and if Necessary, Repair of Clamps, Power Feeder Cable, Insulation Blanket and Aft Pressure Bulkhead 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. 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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 1 of 41 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 2 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 17 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 20 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 20 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 FIGURE 1: ACCESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 2: INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 3: REPLACEMENT AND REPAIR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 APPENDIX A: CONDUCTIVITY TEST EXAMPLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 APPENDIX B: INDIRECT CONDUCTIVITY EDDY CURRENT INSPECTION. . . . . . . . . . . . . . . . 39

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 3 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 4 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Summary**  **Number: 777-24A0119** Original Issue: November 11, 2011 ATA System: 2421 5383 **SUBJECT:** ELECTRICAL POWER - Power and Regulation - Inspection and if Necessary, Repair of Clamps, Power Feeder Cable, Insulation Blanket and Aft Pressure Bulkhead 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 prevent failure of the clamp at station 2150 between stringer 3R and 4R, and within the section 48 flammable fluid leakage zone. If not incorporated, a failed clamp can result in wire chafing and potential electrical arcing which might cause a fire in section 48 which is identified as flammable fluid leakage zone, or heat damage to the Auxiliary Power Unit (APU) power feeder cable, insulation blankets and/or pressure bulkhead at station 2150. An operator has reported failure of the clamp at station 2150 and between stringer 3R and 4R in the forward section of the aft pressure bulkhead. The chafing caused by the failed clamp resulted in heat damage to the APU power feeder cables, insulation blankets, and the pressure bulkhead adjacent to the clamp. This service bulletin gives the instructions to do a Detailed Inspection of the clamps at station 2150 and in the 48 section aft of the pressure bulkhead. If non-TA clamps, or damage to the cable, blankets and the pressure bulkhead are found, this service bulletin gives procedures to replace the existing non-TA clamps with the TA clamps, and to repair the cable, the blanket and the pressure bulkhead if required. Boeing Service Related Problem (SRP) 777-SRP-24-0139 is related to this service bulletin. This SRP is described in Fleet Team Digest Article 777 FTD 24-10003. **ACTION (PRR 62777-84S)** Gain access to the APU power feeder cable between stringer 3R and 4R at station 2150. Gain access to the APU power feeder cable in the 48 section. Do a Detailed Inspection of the clamps on the APU power feeder cable. Replace the existing non-TA clamps with the TA clamps.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 5 of 41Do a General Visual Inspection of the APU power feeder cable for cable damage. Repair damaged cable if found. Do a General Visual Inspection of the insulation blanket adjacent to the clamp at station 2150 and between stringer 3R and 4R. Repair damaged insulation blanket if found. Do a test to determine damage to the aft pressure bulkhead and structure. Contact Boeing for repair instructions if damage is found. Close access. **EFFECTIVITY** 777-200, 777-200LR, 777-300, 777-300ER, and 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** 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. Boeing recommends that the change given in this service bulletin be done within 48 months of the original issue of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of July 22, 2010. Please refer to Paragraph 2.B., Industry Support Information. **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: November 11, 2011 777-24A0119 6 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 7 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 8 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-24A0119**  Original Issue: November 11, 2011 ATA System: 2421 5383 **SUBJECT:** ELECTRICAL POWER - Power and Regulation - Inspection and if Necessary, Repair of Clamps, Power Feeder Cable, Insulation Blanket and Aft Pressure Bulkhead 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 D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 62777-84S for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** Freighter Airplanes

- 1 Passenger Airplanes

- 2

Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER, 777F **Group Variable Number**  2 WA001 - WA017 2 WA076 - WA079 2 WA086 - WA093 2 WA101 - WA104 2 WA116 - WA119

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 9 of 41**Group Variable Number**  2 WA131 - WA137 2 WA171 - WA175 2 WA196 - WA198 2 WA206 - WA212 2 WA221 - WA223 2 WA231 - WA232 2 WA241 - WA250 2 WA261 - WA266 2 WA281 - WA283 2 WA301 - WA304 2 WB001 - WB021 2 WB031 - WB042 2 WB044 - 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 10 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT Group**  **Variable Number** 2 WB446 - WB453 2 WB476 2 WB481 - WB484 2 WB501 - WB512 2 WB531 - WB537 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 11 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT Group**  **Variable Number** 2 WD001 - WD002 2 WD011 - WD018 2 WD031 - WD036 2 WD046 - WD055 2 WD066 - WD075 2 WD081 - WD088 2 WD091 2 WD096 2 WD101 - WD105 2 WD111 2 WD501 - WD513 2 WD521 - WD541 2 WD546 - WD554 2 WD561 - WD573 2 WD581 - WD599 2 WD606 - WD609 2 WD621 - WD632 2 WD651 - WD665 2 WD671 - WD677 2 WD691 - WD709 2 WD741 - WD752 2 WD761 - WD771 2 WD786 - WD788 2 WD796 - WD817 2 WD826 - WD837 2 WD846 - WD863 2 WD871 - WD885 2 WD911 - WD915 2 WD921 - WD922 2 WD936 - WD939 2 WD946 - WD953 2 WD966 - WD970 2 WD981 - WD982

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 12 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT Group**  **Variable Number** 2 WD986 - WD987 2 WD996 2 WE001 - WE004 2 WE011 - WE012 2 WE021 - WE026 2 WE031 - WE034 2 WE051 - WE053 2 WE071 2 WE081 - WE082 2 WE126 - WE135 2 WE151 2 WE176 - WE177 2 WE186 1 WF001 - WF004 1 WF016 - WF020 1 WF031 - WF032 1 WF046 - WF055 1 WF076 - WF077 1 WF081 - WF088 1 WF096 - WF100 1 WF106 - WF107 1 WF111 - WF112 1 WF121 - WF122 1 WF131 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 13 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT C. Reason**  Accomplishment of this service bulletin will prevent failure of the clamp at station 2150 between stringer 3R and 4R, and within the section 48 flammable fluid leakage zone. If not incorporated, a failed clamp can result in wire chafing and potential electrical arcing which might cause a fire in section 48 which is identified as flammable fluid leakage zone, or heat damage to the Auxiliary Power Unit (APU) power feeder cable, insulation blankets and/or pressure bulkhead at station 2150. An operator has reported failure of the clamp at station 2150 and between stringer 3R and 4R in the forward section of the aft pressure bulkhead. The chafing caused by the failed clamp resulted in heat damage to the APU power feeder cables, insulation blankets, and the pressure bulkhead adjacent to the clamp. This service bulletin gives the instructions to do a Detailed Inspection of the clamps at station 2150 and in the 48 section aft of the pressure bulkhead. If non-TA clamps, or damage to the cable, blankets and the pressure bulkhead are found, this service bulletin gives procedures to replace the existing non-TA clamps with the TA clamps, and to repair the cable, the blanket and the pressure bulkhead if required. Boeing Service Related Problem (SRP) 777-SRP-24-0139 is related to this service bulletin. This SRP is described in Fleet Team Digest Article 777 FTD 24-10003. **D. Description** Gain access to the APU power feeder cable between stringer 3R and 4R at station 2150. Gain access to the APU power feeder cable in the 48 section. Do a Detailed Inspection of the clamps on the APU power feeder cable. Replace the existing non-TA clamps with the TA clamps. Do a General Visual Inspection of the APU power feeder cable for cable damage. Repair damaged cable if found. Do a General Visual Inspection of the insulation blanket adjacent to the clamp at station 2150 and between stringer 3R and 4R. Repair damaged insulation blanket if found. Do a test to determine damage to the aft pressure bulkhead and structure. Contact Boeing for repair instructions if damage is found. Close access. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 312, 314 777F

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 14 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT Group 2:** 
**Affected Maintenance Zones Zone**  **Model** 312, 314 777-200, 777-200LR, 777-300, 777-300ER **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. Boeing recommends that the change given in this service bulletin be done within 48 months of the original issue of this service bulletin. **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. **Group 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 0.50 0.50 1 Figure 1 3.25 3.25 1 Figure 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 15 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT Group 1:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.50(a) 2.50(a) 1 Figure 3 (b) (b) Test (If required) 1.00 1.00 1 Close Access 7.75 7.75 TOTAL FOR EACH AIRPLANE (a) Estimate assumes no repair is required to APU power feeder cable or insulation blankets. If repair is required more time may be required (b) Estimate assumes no test time is required. If testing is required more time will be required. **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 0.25 0.25 1 Figure 1 3.25 3.25 1 Figure 2 2.50(a) 2.50(a) 1 Figure 3 (b) (b) Test (If required) 0.75 0.75 1 Close Access 7.25 7.25 TOTAL FOR EACH AIRPLANE (a) Estimate assumes no repair is required to APU power feeder cable or insulation blankets. If repair is required more time may be required. (b) Estimate assumes no test time is required. If testing is required more time will be required. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 62777-84S b. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 16 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**c. 777 Aircraft Maintenance Manual (AMM) 20-10-22, 24-22-00, 25-21-06, 25-21-07, 25-59-01, 25-80-00, 52-48-05, 52-48-06 d. 777 Fleet Team Digest (FTD) 24-10003 e. 777 Non-Destructive Testing (NDT) Manual Part 6, 51-00-08 f. Service Related Problem (SRP) 777-SRP-24-0139 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  WIRE BUNDLE INSTL - R.S. UPR SWL W/AFT PRESS BLKHD (STA 2150 - 2414) & FW BLKHD (FWD) 288W4800

These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: None. 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 affects FCS but no new DTIs are necessary.
**L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 17 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 18 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits 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 kits 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 1-2: 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)**  **QTY Date**  **Name Kit Number** 

$500.00 149 10 July 01, 2011 APU Power Feeder Clamp Replacement 005W3505-1 $500.00 149 10 August 01, 2011 APU Power Feeder Clamp Replacement 005W3505-1 $500.00 149 10 August 29, 2011 APU Power Feeder Clamp Replacement 005W3505-1 $500.00 149 10 September 27, 2011 APU Power Feeder Clamp Replacement 005W3505-1 $500.00 149 9 October 25, 2011 APU Power Feeder Clamp Replacement 005W3505-1

**B. Industry Support Information** Boeing warranty remedies are available for 777 airplanes in warranty as of July 22, 2010. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane number in your purchase order. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 19 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT NOTE:**  One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. **Group 1-2:**
**Kit 005W3505 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -1**  TOPKIT - APU Power FeederClamp Replacement - 005W3505-1

(a) CLAMP 25 TA027063-22P (a) CLAMP 25 TA027063-24P (a) There are more parts than are necessary 2. Parts and Materials Supplied by the Operator None. 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** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 20 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT 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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. The work instructions are divided into work packages. Task Hours and Elapsed Hours for each package are given in Paragraph 1.G., Manpower. You can do each work package independently. 4. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. 7. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 8. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 21 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**9. A Special Detailed Inspection is defined as: An intensive examination of a specific item,installation, or assembly to detect damage, failure, or irregularity. The examination is likely to make extensive use of specialized Inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. 10. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 11. 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. 12. Refer to Appendix A for heat damage inspection referencing example. 13. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 14. 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. 15. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 16. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. **B. WORK INSTRUCTIONS** 1. Remove electrical power from the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure. 2. **Group 1:** Gain access to the APU power feeder cable at station 2150 and between stringer 3R and 4R in accordance with Figure 1. Open the access door in the aft bulkhead cargo center panel. Refer to 777 AMM 25-59-01 as an accepted procedure. **Group 2:** Gain access to the APU power feeder cable at station 2150 and between stringer 3R and 4R in accordance with Figure 1. Open the ceiling panel of the aft A2 and A3 galley. Refer to 777 AMM 25-21-06 and 777 AMM 25-21-07 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 22 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT Group 1-2:**  Gain access to the APU power feeder cable in the 48 section in accordance with Figure 1. Open the access door 311BL and 313AL. Refer to 777 AMM 52-48-05 and 777 AMM 52-48-06 as an accepted procedure. 3. Do a Detailed Inspection of the clamps on the APU power feeder cable at station 2150, and in the 48 section in accordance with Figure 2. a. If TA027063 clamps are used, do steps 10, 11 and 12. b. If non-TA027063 clamps are used, proceed to step 4. 4. Do a General Visual Inspection of the APU power feeder cables in accordance with Figure 2. a. If no damage to the cable is found, do steps 8, 10, 11 and 12. b. If damage to the cable is found, proceed to step 5. 5. Do a General Visual Inspection of the insulation blanket adjacent to the clamp at station 2150 and between stringer 3R and 4R for possible heat damages in accordance with Figure 2. a. If no heat damage to the insulation blanket is found, do steps 7, 8, 10, 11 and 12. b. If heat damage to the insulation blanket is found, proceed to step 6. 6. Do a heat damage inspection on the pressure bulkhead and structure in accordance with the instructions below. a. Perform a detailed inspection of the Section 47 and 48 fuselage structure within 42 inches of the APU feeder clamp. This includes the skin, stringers, and end fittings on either side of station 2150, the aft pressure dome web, radial stiffeners, intermediate stiffeners, the station 2150 inner chord, outer chord, failsafe chord (Y-chord), doublers, triplers, circumferential tear straps and web. Inspect for the following indications of heat damage: (1) Primer discoloration (2) Structural deterioration b. If visual indications of heat damage are found, do steps 6.c through 6.f. c. Remove loose paint, dirt and sealant from the surface of the inspection area. Refer to 777 AMM 20-10-22 as an accepted procedure. **NOTE:** 1. Do not remove the finishes to perform conductivity. 2. Do not use abrasive materials to remove paint, dirt and sealant. d. With a felt tipped marker, create a 1.00 inch by 1.00 inch grid across the skin locations thought to be heat damaged and number the grid. For all other structure mark the part into 1.00 inch sections. Refer to Appendix A, Grid Creation Example, as an accepted procedure. e. Do a Special Detailed Inspection of the aluminum part for heat damage.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 23 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**(1) If space is not restrictive, do the Inspection for Heat Damage to Aluminum Structure, refer to 777 NDT Part 6, 51-00-08 as an accepted procedure and proceed to step 6.f. (2) If space is restrictive, standard conductivity probes may not fit in the tight areas, such as the failsafe chord (Y-chord). If the manufacturer of the conductivity test equipment cannot provide a probe to fit into the area of interest, refer to Appendix B, Indirect Conductivity Eddy Current Inspection, as an accepted procedure. **NOTE:** 1. Conductivity is very sensitive on materials with a clad layer. Do not remove the primer on any parts. Measure the conductivity of all parts through the primer. 2. Because the stringer end fittings common to station 2150 are small, measure a similar end fitting away from the damage that is similar in size and gage. Be sure to measure the conductivity of the fitting in three locations, near the tension bolts, at the neck of the fitting and near the stringer attachment fasteners. 3. The baseline conductivity values should be measured away from the area thought to be heat damaged. These values should be measured on the same part and gage. 4. Measure the undamaged area at two to three locations and take average value as the baseline conductivity. 5. Record conductivity of each box in the grid created in a spreadsheet. Refer to Appendix A, Conductivity Table for Skin and Other Structure Example as an accepted procedure. f. Do analysis of the inspection results. (1) If any areas deviate greater than 1% International Annealed Copper Standard (IACS) from the baseline conductivity reading (for example: the baseline percent IACS is 34, IACS measurement less than 33 or more than 35 is deviation), do steps 6.f.(1).(a), 6.f.(1).(b), 6.f.(1).(c), 7, 8, 9, 10, 11 and 12. (a) Contact Boeing for repair instruction (b) Provide the following to Boeing: 1) Measured conductivity values for all structure listed in 6.a that is within 21 inches of the areas showing evidence of discoloration or deterioration due to the fire. 2) Detailed digital photos of the structure marked with the grid. 3) Dimensions of the heat damage and distances to surrounding structure, such as radial stiffeners, intermediate stiffeners, circumferential tear straps, doublers, triplers and the station 2150 failsafe chord (Y-Chord). (c) Do the repair in accordance to the instruction from Boeing. (2) If no damage to the pressure bulkhead is determined, do steps 7, 8, 9, 10, 11 and 12. 7. Do the repair for APU power feeder cable in accordance with Figure 3.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 24 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**8. Do the replacement of the existing non-TA027063 clamps with TA027063 clamps in accordance with Figure 3. 9. Do the repair for insulation blanket in accordance with Figure 3. 10. **Group 1:** Close access. Refer to 777 AMM 25-59-01, Main Deck Cargo Compartment Lining Panels, as an accepted procedure. **Group 2:** Close access. Refer to 777 AMM 25-21-06, Main Ceiling Panel and 777 AMM 25-21-07, Lowered Ceiling Panel, as an accepted procedure. **Group 1-2:** Close access. Refer to 777 AMM 52-48-05, Service Access Door and 777 AMM 52-48-06, Controls Bay Access Door, as an accepted procedure. 11. Restore the electrical power to the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure. 12. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 25 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 1: ACCESS**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 26 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step**

- - Access Panel Locate 1

- - Access Door Locate 2

**FIGURE 1: ACCESS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 27 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 2: INSPECTION**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 28 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 2: INSPECTION**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 29 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 2: INSPECTION**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 30 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 2: INSPECTION**  **(SHEET 4 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 31 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** Do a Detailed Inspection of the clamps. - - CLAMPS Inspect 1 Note: The color of the clamp cushion material for TA027063 is brown, any other color isconsidered nonTA027063 clamps. If non-TA027063 clamps are used, doa General Visual Inspection of the APU power feeder cable for damage. 1 W7850 APU Power Feeder Cable Inspect 2

If APU power feeder cable is damaged, do a General VisualInspection of the insulation blanket for heat damage. - - Insulation Blanket Inspect 3

**FIGURE 2: INSPECTION (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 32 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 3: REPLACEMENT AND REPAIR**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 33 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 3: REPLACEMENT AND REPAIR**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 34 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 3: REPLACEMENT AND REPAIR**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 35 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT FIGURE 3: REPLACEMENT AND REPAIR**  **(SHEET 4 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 36 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** If non-TA027063 clamps are found, refer to SWPM 20-10-12 as an accepted procedure. See the extra parts table for different clamp size, if necessary. 23 TA027063-22P CLAMP Install (New) 1

If damage is found, refer to SWPM 20-10-13 as an accepted procedure. 1 W7850 APU Power Feeder Cable Repair 2

If damage is found, refer to 777 AMM25-80-00 as an accepted procedure. 1

- Insulation Blanket Repair 3

The parts shown in the table below are provided as extra parts for this figure.
**More Data Qty**  **Identification Name**  2 TA027063-22P CLAMP Use TA027063-24P clamps if required. 25 TA027063-24P CLAMP

**FIGURE 3: REPLACEMENT AND REPAIR (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 37 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT APPENDIX A: CONDUCTIVITY TEST EXAMPLES**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 38 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**1. Purpose Use this indirect conductivity eddy current procedure to evaluate aluminum structure for heat damage when a standard probe of conductivity instrument will not fit into the an area with limited clearance. This eddy current procedure uses an impedance plane display instrument. It is not considered as accurate as a standard conductivity instrument. 2. Equipment a. Instrument Use an impedance plane display eddy current instrument that operates at a frequency range of 100 kHz to 500 kHz. A Hocking Phasec 2200 eddy current instrument was used to help prepare this procedure. b. Probes Use a shielded differential type probe with outer diameter of approximately 0.125 inch (3.2mm) that operates from 100 to 500 kHz. An NDT Engineering Inc (Olympus) MP-30 probe is an example of a suitable probe. **NOTE:** Use a probe that is not sensitive to hand pressure. c. Reference Standard Use two certified conductivity standards with values as follows: (1) One standard should have a conductivity value between 34 - 43% IACS (34 - 36 preferred). (2) One standard with a conductivity value between 26 - 29.5% IACS. 3. Preparation for Inspection a. Get access to the areas in step 6 of Work Instructions, paragraph 3.B where visual inspections indicated potential heat damage. b. Remove all dirt and grease from the inspection areas that the probe will touch. 4. Instrument Calibration a. Connect the probe to the instrument. b. Set the instrument frequency to 150 kHz. c. Put the probe on the conductivity reference standard with the highest conductivity. d. Balance the instrument as specified by the manufacturer's instructions.

**APPENDIX B: INDIRECT CONDUCTIVITY EDDY CURRENT INSPECTION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 39 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**e. Set the balance point at approximately 20% of full screen height and 60% full screen width. Refer to Appendix B, Calibration Screen Display Example, Point 1, as an accepted procedure. f. Set the lift-off (phase) so that the signal moves horizontally from right to left when the probe is lifted off the reference standard. Refer to Appendix B, Calibration Screen Display Example, as an accepted procedure. g. Put the probe on the conductivity reference standard with the lowest conductivity. h. Adjust the instrument gain to set the signal at 80%FSH (60% full screen height separation between the two signals). Refer to Appendix B, Calibration Screen Display Example, Point 2, as an accepted procedure. i. Do steps 4.c through 4.h in Appendix B again to make sure that there is a 60% full screen height separation between the two signals. **NOTE:** Change probes or increase the instrument frequency if you can not get the 60% full screen height separation between the two signals. j. The conductivity of the part can be estimated by extrapolating the vertical position of the signal as compared to the two known conductivity standards. 5. Inspection Procedure a. Put the probe on the high conductivity standard and balance the instrument again. b. Put the probe on the suspect structure (e.g. failsafe chord (Y-chord)) at a location away from the possible damage and quickly read the vertical height of the signal. Record this instrument reading. c. Move the probe towards the damage to see if there is a change in signal height. Heat damage will cause the signal to decrease in height (indicating increased conductivity). If there are no changes to the signal height, there is no heat damage to the Y-chord. d. If there is a change in the signal height, take careful readings to estimate the conductivity values. Before each reading, put the probe on the high conductivity standard and balance the instrument before putting the probe back on to the part. The conductivity of the part can be estimated by extrapolating the vertical position of the signal as compared to the two known conductivity standards. **NOTE:** It is very important to have the conductivity standards the same temperature as the part to be examined. Put the standards near the inspection part before starting the calibration to make sure they are the same temperature. Holding the probe on the standard or part for too long can cause the probe tip to get warm and the reading to change. Make sure that the instrument reads the correct value on the test standard before taking a reading on the part. Balance the instrument often on the high conductivity standard and take the readings quickly. e. Record conductivity of each box in the grid created in a spreadsheet. Refer to Appendix A, Conductivity Table for Skin and Other Structure Example, as an accepted procedure. 6. Inspection Results

**APPENDIX B: INDIRECT CONDUCTIVITY EDDY CURRENT INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 40 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**Proceed to step 6.f of Work Instruction, paragraph 3.B.

**APPENDIX B: INDIRECT CONDUCTIVITY EDDY CURRENT INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 11, 2011 777-24A0119 41 of 41 **BOEING SERVICE BULLETIN 777-24A0119 ALERT**  **ALERT**