# Boeing Alert Service Bulletin 757-28A0073: Revision 2 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-0496; AD 2016-11-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 757-28A0073](https://openairdocs.org/service-documents/boeing/757-28a0073.md) - Title as filed: U.S. DOT/FAA - SB-757-28A0073-02 - Pages: 69 - PDF: https://openairdocs.org/files/sha256/cc/24/cc24ae94132a3113e560dc93d4434651b1aebd0e85ea00de2ae53afebd7c3555 - Page: https://openairdocs.org/service-documents/boeing/757-28a0073/file/cc24ae94132a ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-28A0073 Original Issue: November 20, 2003 Revision 2: June 04, 2009 ATA System: 2822 SUBJECT: FUEL - Fuel Shutoff Valve Wire Inspection and Reroute in Nacelles/Pylons, Engine to Wing Aft Fairings - Rolls Royce Powered Airplanes 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all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2003 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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 20, 2003 757-28A0073Revision 2: June 04, 2009 1 of 69 8.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 2 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 Summary ..................................................... 7 1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1 1. Airplanes ............................................ 1 1 2. Spares Affected ........................................ 1 4 B. Concurrent Requirements ...................................... 1 4 C. Reason ................................................ 1 4 D. Description .............................................. 1 6 E. Compliance .............................................. 1 7 F . Approval ............................................... 1 7 G. Manpower .............................................. 1 7 H. Weight and Balance Changes .................................... 1 8 I. Electrical Load Data ......................................... 1 8 J. References .............................................. 1 8 1. Existing Data: .......................................... 1 8 2. Data supplied with this Service Bulletin: ........................... 1 9 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9 K. Publications Affected ......................................... 1 9 L. Interchangeability and Intermixability of Parts ........................... 1 9 2. MATERIAL INFORMATION ........................................ 2 1 A. Material - Price and Availability ................................... 2 1 B. Industry Support Information .................................... 2 1 C. Parts Necessary For Each Airplane ................................. 2 1 1. Kits/Parts: ............................................ 2 1 2. Parts and Materials Supplied by the Operator: ........................ 2 4 3. Parts Modified and Reidentified: ................................ 2 5 4. Parts Removed and Not Replaced: .............................. 2 5 D. Parts Necessary to Change Spares ................................. 2 5 E. Special Tooling - Price and Availability ............................... 2 5 F . Special Tooling Necessary to do this Service Bulletin ....................... 2 5 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7 A. GENERAL INFORMATION ..................................... 2 7 B. WORK INSTRUCTIONS ....................................... 2 7 FIGURE 1: PREPARE FOR INSPECTION OF WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES [Group 1, Configuration 1] ................................... 3 9 FIGURE 2: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - GROUP 1 CONFIGURATION 1 AIRPLANES [Group 1, Configuration 1] ............................ 4 1 FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES [Group 1, Configuration 1] ................................... 4 5 FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES [Group 1, Configuration 1] ................................... 5 2 FIGURE 5: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - FOR GROUP 1 CONFIGURATION 1 AIRPLANES [Group 1, Configuration 1] ........................... 6 0 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 3 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 4 FIGURE 6: RIGHT HAND STRUT - INSTALL BACK-TO-BACK CLAMPS AT THE AFT END OF THE STRUT - GROUP 1 CONFIGURATION 2, AND GROUP 2 AIRPLANES [Group 1, Configuration 2; Group 2 ] ................................................ 6 4 FIGURE 7: LEFT HAND STRUT - INSTALL THE TFE SPIRAL CABLE WRAP ON WIRE BUNDLE W5100 AT THE AFT END OF THE STRUT - GROUP 1 CONFIGURATION 2 AND 3, AND GROUP 2 AIRPLANES [Group 1, Configuration 2-3; Group 2] ..................... 6 6 FIGURE 8: RIGHT HAND STRUT - INSTALL SPIRAL CABLE WRAP ON WIRE BUNDLE W5200 AT THE AFT END OF THE STRUT - GROUP 1 CONFIGURATION 2 AND 3, AND GROUP 2 AIRPLANES [Group 1, Configuration 2-3; Group 2] ............................. 6 8 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 4 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 5 Commercial Airplanes 757 Service Bulletin ALERT Revision Transmittal SheetNumber: 757-28A0073Original Issue: November 20, 2003 Revision 2: June 04, 2009 ATA System: 2822 SUBJECT: FUEL - Fuel Shutoff Valve Wire Inspection and Reroute in Nacelles/Pylons, Engine to Wing Aft Fairings - Rolls Royce Powered Airplanes This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive 2005-18-18 dated October 14, 2005, is related to this service bulletin. More work is necessary on airplanes changed as shown in the original issue of this service bulletin dated November 20, 2003 or Revision 1 of this service bulletin dated February 24, 2005. REASON FOR REVISION This revision is sent to tell the operators that Boeing received messages from some operators regarding the interference between the Fuel Shutoff Valve wires and the adjacent fairing at the aft end of the right engine strut. To prevent possible damage of the Fuel Shutoff Valve wires, Boeing decided to add additional protection to the Fuel Shutoff Valve wires that do not have a Teflon sleeve already installed during production. A new TFE (Tetrafluoroethylene) Spiral Cable Wrap is added to the Fuel Shutoff Valve wires at the aft end of the strut, for both, the left and right engine strut. The Spiral Cable Wrap will improve the Fuel Shutoff Valve wires protection. NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production. The Teflon Sleeve installed during production starts at the lower part of Nacelle STA 278 and ends in the wing area. It is not necessary to install the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. These sections were changed: 1. In Summary, Paragraph Action - Added new action requirement to protect the aft end of the Fuel Shutoff valve wires with a Spiral Cable Wrap, on both Left and Right Engine. Added clarification note. 2. In Summary - Added additional data to Summary, Paragraph Action, and to the Summary illustration. 3. In Planning Information, paragraph 1.A. Effectivity - Added Configuration 3 to Group 1 airplanes in the Group Configuration Table. 4. In Planning Information, paragraph 1.C. Reason - Added the list of all changes included in Revision 2 of this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 5 of 69 ### Page 6 5. In Planning Information, paragraph 1.D. Description - Added new action requirement to protect the aft end of the Fuel Shutoff Valve wires with a Spiral Cable Wrap, on both, Left and Right Engine. Added a clarification note. 6. In Planning Information, paragraph 1.E., Compliance - Added data related to the Airworthiness Directive (AD). 7. In Planning Information, paragraph 1.F ., Approval - Changed the existing approval statement with the new approval statement and added data related to the Airworthiness Directive (AD). 8. In Planning Information, paragraph 1.G., Manpower - Added the manpower for the new figures and changed the manpower for some existing figures. 9. In Material Section, paragraph 2.C.2., Parts and Materials Supplied by Operators - Added the Spiral Cable Wrap. 10. In Material Section, paragraph 2.C4., Parts Removed and Not Replaced - Added to the table two screws and two washers that are removed and not replaced. 11. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Part I - Changed format and added instructions to install the Spiral Cable Wrap on Fuel Shutoff Valve wires, at the aft end of the strut, for both, Left and Right Engine. 12. In Accomplishment Instructions, paragraph 3.B. Work Instructions - Added a new Part III that provides instructions to install the Spiral Cable Wrap on Fuel Shutoff Valve wires, at the aft end of the strut, for both, Left and Right Engine, for airplanes that already incorporated Revision 1 of the service bulletin. 13. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Part V - Changed the word "Left" with "Right" in step instruction 1.i. 14. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Figure 1- Added two notes. 15. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Figure 3, Figure 4 - Added the Spiral Cable Wrap and did some minor graphical changes to figures. 16. In Accomplishment Instructions, paragraph 3.B. Work Instructions - Added Figure 7 and Figure 8, for airplanes that incorporated Revision 1 of the service bulletin that have to add the Spiral Cable Wrap on Fuel Shutoff Valve wires, at the aft end of the strut, for both, Left and Right Engine. The data given in Information Notice 757-28A0073 IN 01 is included in this revision. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. REVISION HISTORY November 20, 2003Original Issue: February 24, 2005Revision 1: June 04, 2009Revision 2: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 6 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 7 Commercial Airplanes 757 Service Bulletin ALERT SummaryNumber: 757-28A0073Original Issue: November 20, 2003 Revision 2: June 04, 2009 ATA System: 2822 SUBJECT: FUEL - Fuel Shutoff Valve Wire Inspection and Reroute in Nacelles/Pylons, Engine to Wing Aft Fairings - Rolls Royce Powered Airplanes 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 The related 757-300 bulletin is 757-28A0074. This service bulletin provides instructions to do an inspection of wires in the left and right engine to wing aft fairings, repair as necessary and reroute. One operator reported tripping of the spar fuel shutoff valve circuit breaker due to a chafed wire shorted against structure in the aft fairing flammable leakage zone.The airplane had 10900 hours and 6225 cycles.The operator examined other airplanes in their fleet and found chafed wires in some of the airplanes. The cause of the chafe condition was missing or incorrectly installed wire sleeving, incorrect chafe grommet installation and incorrect wire bundle clamp installation. Shorting and the creation of arcs and sparks in a flammable leakage zone could cause a fire in flight or on the ground. Boeing Service Related Problem (SRP) 757-SRP-28-0090 is related to this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 7 of 69 ### Page 8 ACTION Inspect the Fuel Shutoff Valve wires from Power Plant Station (PP STA) 278, aft, to the rear spar of the wing in the left and right engine to wing aft fairings. Inspect the Fuel Shutoff Valve wires for chafe sleeves and wire damage at PP STA's 278, 290 and 301. Repair the Fuel Shutoff Valve wires found with damage as required. If no chafe sleeve is installed on the Fuel Shutoff Valve wires, add wrap-on sleeve. Inspect the PP STA 278 and PP STA 301 bulkheads to make sure the installation of the caterpillar grommet is correct. Add a new wire bundle support bracket at PP STA 301 bulkheads. Add also a TFE Spiral Cable Wrap on the Fuel Shutoff Valve wires at the aft end of the right and left strut, if no chafe sleeve was installed during production. Add back-to-back P-clamps between wire and hydraulic supply tube at the aft end of the right hand strut only. Re-route the wire bundles. NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production. The Teflon Sleeve installed during production starts at the lower part of Nacelle STA 278 and ends in the wing area. It is not necessary to install the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. EFFECTIVITY 757-200, 757-200CB and 757-200PF airplanes powered by Rolls Royce engines. Refer to service bulletin Paragraph 1.A.1 for effectivity. COMPLIANCE Boeing recommends that operators inspect and make the change given in this service bulletin within 5 years from the date of this service bulletin revision. Federal Aviation Administration (FAA) Airworthiness Directive 2005-18-18 dated October 14, 2005, is related to this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for airplanes in warranty as of November 8, 2002. Please refer to Paragraph 2.B., Industry Support Information. MANPOWER The total Task Hours time and Elapsed Hours time depend of the airplane configuration and necessary rework figures. Please 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 20, 2003 757-28A0073Revision 2: June 04, 2009 8 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 9 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 9 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 10 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT BLANK PAGE ### Page 11 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-28A0073 Original Issue: November 20, 2003 Revision 2: June 04, 2009 ATA System: 2822 SUBJECT: FUEL - Fuel Shutoff Valve Wire Inspection and Reroute in Nacelles/Pylons, Engine to Wing Aft Fairings - Rolls Royce Powered Airplanes 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 D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. DESCRIPTIONCONFIGURATIONGROUP Airplanes with wire bundles which are not correctly installed and are in a location where damage to wires can occur. -1 Airplanes that did not incorporate the intent of the initial release of this service bulletin. 1 Airplanes that have incorporated the intent of the initial release of this bulletin. 2 Airplanes that have incorporated the intent of revision 1 of this service bulletin. 3 Airplanes that incorporated the intent of the initial release of this service bulletin during production. -2 Airplane Models: 757-200, 757-200CB, 757-200PF BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 11 of 69 ### Page 12 GroupVariable Number 1NA001 - NA028 1NA191 - NA199 1NA201 - NA239 1NA301 - NA305 1NA341 - NA352 1NA391 - NA399 1NA401 - NA408 1NA441 - NA447 1NB021 - NB023 1NB036 - NB041 1NB051 - NB053 1NB061 - NB073 1NB079 1NB131 - NB148 1NB161 - NB162 1NB201 - NB204 1NB221 - NB228 1NB230 1NB236 1NB239 1NB261 - NB267 1NB291 - NB299 1NB301 - NB302 1NB311 - NB312 1NB321 - NB331 1NB421 - NB438 1NB446 1NB451 - NB454 1NB501 - NB523 1NB561 1NB571 1NB581 - NB583 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 12 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 13 GroupVariable Number 1NC058 - NC062 1NC936 - NC950 1NC971 - NC974 1ND001 - ND007 1ND011 - ND059 1ND111 - ND113 1ND161 - ND199 1ND201 - ND203 1ND221 - ND225 1ND241 - ND248 1ND301 - ND322 1ND401 1ND891 1ND895 2NJ001 - NJ004 2NJ031 - NJ032 1NN001 - NN002 1NN051 - NN052 1NS601 - NS616 1NT001 - NT009 1NT201 - NT202 1NT231 - NT234 1NT237 - NT240 1NT242 1NT245 - NT248 1NT281 - NT289 1NT381 - NT386 1NT401 - NT409 1NT411 - NT412 1NT426 - NT427 1NT431 - NT432 1NT436 - NT438 1NT446 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 13 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 14 GroupVariable Number 1NT731 - NT769 1NT861 - NT862 1NT901 - NT916 1NT971 - NT985 2. Spares Affected None. B. Concurrent Requirements None. C. Reason The related 757-300 bulletin is 757-28A0074. This service bulletin provides instructions to do an inspection of wires in the left and right engine to wing aft fairings, repair as necessary and reroute. One operator reported tripping of the spar fuel shutoff valve circuit breaker due to a chafed wire shorted against structure in the aft fairing flammable leakage zone. The airplane had 10900 hours and 6225 cycles. The operator examined other airplanes in their fleet and found chafed wires in some of the airplanes. The cause of the chafe condition was missing or incorrectly installed wire sleeving, incorrect chafe grommet installation and incorrect wire bundle clamp installation. Shorting and the creation of arcs and sparks in a flammable leakage zone could cause a fire in flight or on the ground. Revision 1 is sent to include the following changes: — In Summary, Paragraph Manpower, removed table and reference to Manpower paragraph. — In Planning Information, Paragraph 1.A., Effectivity, added the table with the airplanes groups and configurations. — In Planning Information, Paragraph 1.D., Description, added the back-to-back p-clamps installation. — In Planning Information, Paragraph 1.G., Manpower, changed Table. — In Planning Information, Paragraph 1.H., Weight and Balance Change, changed Table. — In Planning Information, Paragraph 1.J.3., Installation Drawings Used in the Preparation of this Service Bulletin, added four drawings. — In Material Information, Paragraph 2.A. Material-Price and Availability, added Note. — In Material Information, Paragraph 2.A. Material-Price and Availability, replaced the top kit 012N1023-1 with the new top kit 012N1023-8 and added top kit 012N1023-6. — In Material Information, Paragraph 2.C.1. Kits/Parts, replaced the top kit 012N1023-1 with top kit 012N1023-8, and added top kit 012N1023-6. Added the parts for each kit. — In Material Information, Paragraph 2.C.2. Parts and Materials Supplied by Operator, added an optional adhesive and more parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 14 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 15 — In Accomplishment Instructions, Paragraph 3.B., Work Instructions, added Part I for Group 1 Configuration 1 airplanes, and changed the instructions to re-route wire bundle W5100 for the Left Engine Strut and wire bundle W5200 for the Right Engine Strut. Added also new instructions to install back-to-back p-clamps at the aft end of the Right Engine Strut. — In Accomplishment Instructions, Paragraph 3.B. Work Instructions added Part II for Group 1 Configuration 2 and Group 2 airplanes for installation of the back-to-back p-clamps at the aft end of the Right Engine Strut. — In Accomplishment Instructions, Paragraph 3.B. Work Instructions added Part III. Moved the instructions to test the Left Engine Fuel Shut-off Wire Bundle W5100 to Part III. — In Accomplishment Instructions, Paragraph 3.B. Work Instructions added Part IV. Moved the instructions to test the Right Engine Fuel Shut-off Wire Bundle W5200 to Part IV. — In Accomplishment Instructions, Paragraph 3.B Work Instructions, changed Figure 2 and Figure 3. — In Accomplishment Instructions, Paragraph 3.B. Work Instructions, added Figure 4, Figure 5, and Figure 6. Revision 2 is sent to include the following changes: 1. In Summary, Paragraph Action - Added new action requirement to protect the aft end of the Fuel Shutoff valve wires with a Spiral Cable Wrap, on both Left and Right Engine. Added clarification note. 2. In Summary - Added additional data to Summary, Paragraph Action, and to the Summary illustration. 3. In Planning Information, paragraph 1.A. Effectivity - Added Configuration 3 to Group 1 airplanes in the Group Configuration Table. 4. In Planning Information, paragraph 1.C. Reason - Added the list of all changes included in Revision 2 of this service bulletin. 5. In Planning Information, paragraph 1.D. Description - Added new action requirement to protect the aft end of the Fuel Shutoff Valve wires with a Spiral Cable Wrap, on both, Left and Right Engine. Added a clarification note. 6. In Planning Information, paragraph 1.E., Compliance - Added data related to the Airworthiness Directive (AD). 7. In Planning Information, paragraph 1.F ., Approval - Changed the existing approval statement with the new approval statement and added data related to the Airworthiness Directive (AD). 8. In Planning Information, paragraph 1.G., Manpower - Added the manpower for the new figures and changed the manpower for some existing figures. 9. In Material Section, paragraph 2.C.2., Parts and Materials Supplied by Operators - Added the Spiral Cable Wrap. 10. In Material Section, paragraph 2.C4., Parts Removed and Not Replaced - Added to the table two screws and two washers that are removed and not replaced. 11. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Part I - Changed format and added instructions to install the Spiral Cable Wrap on Fuel Shutoff Valve wires, at the aft end of the strut, for both, Left and Right Engine. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 15 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 16 12. In Accomplishment Instructions, paragraph 3.B. Work Instructions - Added a new Part III that provides instructions to install the Spiral Cable Wrap on Fuel Shutoff Valve wires, at the aft end of the strut, for both, Left and Right Engine, for airplanes that already incorporated Revision 1 of the service bulletin. 13. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Part V - Changed the word "Left" with "Right" in step instruction 1.i. 14. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Figure 1- Added two notes. 15. In Accomplishment Instructions, paragraph 3.B. Work Instructions, Figure 3, Figure 4 - Added the Spiral Cable Wrap and did some minor graphical changes to figures. 16. In Accomplishment Instructions, paragraph 3.B. Work Instructions - Added Figure 7 and Figure 8, for airplanes that incorporated Revision 1 of the service bulletin that have to add the Spiral Cable Wrap on Fuel Shutoff Valve wires, at the aft end of the strut, for both, Left and Right Engine. D. Description Inspect the Fuel Shutoff Valve wires from Power Plant Station (PP STA) 278, aft, to the rear spar of the wing in the left and right engine to wing aft fairings. Inspect the Fuel Shutoff Valve wires for chafe sleeves and wire damage at PP STA's 278, 290 and 301. Repair the Fuel Shutoff Valve wires found with damage as required. If no chafe sleeve is installed during production, add wrap-on sleeve. Inspect the PP STA 278 and PP STA 301 bulkheads to make sure the installation of the caterpillar grommet is correct. Add a new wire bundle support bracket at PP STA 301 bulkheads. Add also a TFE Spiral Cable Wrap on the Fuel Shutoff Valve wires at the aft end of the right and left strut, if no chafe sleeve was installed during production. Add back-to-back P-clamps between wire and hydraulic supply tube at the aft end of the right hand strut only. Re-route the wire bundles. NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production. The Teflon Sleeve installed during production starts at the lower part of Nacelle STA 278 and ends in the wing area. It is not necessary to install the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 433, 434757-200, 757-200CB, 757- 200PF Group 2: Affected Maintenance Zones ZoneModel 433, 434757-200 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 16 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 17 E. Compliance Boeing recommends THAT OPERATORS INSPECT AND MAKE THE CHANGE GIVEN IN THIS SERVICE BULLETIN within 5 years from the date of this service bulletin revision. Federal Aviation Administration (FAA) Airworthiness Directive 2005-18-18 effective from October 14, 2005 is related to 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. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (f)(1) and (f)(2) of AD 2005-18-18. All provisions of AD 2005-18-18 that are not specifically referenced in the above statement remain fully applicable and must be complied with. 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/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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. Elapsed Hours Task-HoursNumber of Persons Task 1.02.02Open Access 1.02.02Figure 1 2.04.02Figure 2 2.7511.04Figure 3 3.012.04Figure 4 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 17 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 18 Elapsed Hours Task-HoursNumber of Persons Task 2.04.02Figure 5 1.0 (a)1.0 (a)1Figure 6 0.750.751Figure 7 1.251.251Figure 8 4.0 (b)8.0 (b)2Test 1.02.02Close Access Variable (c)Variable (c)TOTAL FOR EACH AIRPLANE (a) For Right Hand Strut Only. (b) For aircraft test, additional time required for repairs. (c) Total Task-Hours time and Elapsed hours time depend of the airplane configuration and necessary rework fig- ures. H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane NegligibleNegligibleAll I. Electrical Load Data Not changed. J. References 1. Existing Data: a. 757 WDM 28-22-11 b. Service Related Problem (SRP) 757-SRP-28-0090 c. Boeing Service Bulletin 757-54-0013 R04 d. Boeing Service Bulletin 757-28A0074 e. Boeing Drawing 65-88700. f. Standard Wiring Practices Manual (SWPM) 20-00-14, 20-10-11, 20-10-12, 20-10-13, 20-10-14, 20-10-15, 20-10-19, 20-30-11, 20-30-12, 20-61-11 g. 757 Aircraft Maintenance Manual (AMM) 06-43-00, 06-44-00, 24-22-00 h. 757 Structural Repair Manual (SRM) 51-40-02 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 18 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 19 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number LOWER PANEL INSTL. OUTBD WING112N4001 BRACKET INSTL. - HYDRAULIC, LOWER SURFACE WING AND REAR SPAR SECT 271N6171 WIRE BUNDLE INSTL - L FILLET AREA & REAR SPAR IRSS 150 - 325288N1315 WIRE BUNDLE INSTL - R FILLET AREA & REAR SPAR IRSS 150 - 325288N1316 WIRE BUNDLE INSTL - LEFT REAR SPAR IRSS 325.0 - W.S. 836.55288N1317 WIRE BUNDLE INSTL - RIGHT REAR SPAR IRSS 325.0 - W.S. 836.55288N1318 TUBING INSTL LEFT AFT STRUT FAIRING208N3121 ELECT. CABLE INSTL LEFT AFT STRUT FAIRING PP3 208-53-PPS 278288N3121 WIRE BUNDLE INSTL - RIGHT AFT STRUT FAIRING PPS 208.53 - PPS 278288N3122 TRAILING EDGE INSTL - AFT FAIRING, STRUT313N5023 BULKHEAD INSTL - AFT FAIRING, STRUT313N5033 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 None. 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 20, 2003 757-28A0073Revision 2: June 04, 2009 19 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 20 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 20 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT BLANK PAGE ### Page 21 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. Kits availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. NOTE: Operators that did not incorporate the initial release of this service bulletin need to order top kit 012N1023-8 given in the table below. Operators that incorporated the intent of the initial release of this service bulletin need to order only 012N1023-6 top kit. Unit Price thru Dec. 31 2008 ROLT (Weeks) NameKit Number $1,491.0047STRUT WIRE BUNDLE ROUT - ING REVISION - TOP KIT 012N1023-8 $3.1045RH STRUT WIRE BUNDLE ROUTING REVISION - TOP KIT 012N1023-6 The Kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Term: 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P .O. Box 3707 Seattle, Washington 98124-2207 USA B. Industry Support Information Boeing warranty remedies are available for 757 airplanes in warranty as of November 8, 2002. For man-hour and material reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. 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 20, 2003 757-28A0073Revision 2: June 04, 2009 21 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 22 NOTE: The top kit 012N1023-8 and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for Group 1 Configuration 1 airplanes (airplanes that do not have the intent of the initial release of this service bulletin incorporated). The kit 012N1023-6 and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for Group 1 Configuration 2 airplanes (airplanes that incorporated the intent of the initial release of this service bulletin) and Group 2 airplanes. For Group 1 Configuration 3 airplanes, operators should use the the Spiral Cable Wrap and Lacing Tape provided in Paragraph 2.C.2., Parts and Materials Supplied by the Operator table. Kit 012N1023 NotesExisting Part Number NameQTYNew Part Number -8-7-6-5-2-1 (h)STRUT WIRE BUNDLE ROUT - ING REVISION- TOP KIT 1....-012N1023-1 STRUT WIRE BUNDLE ROUT - ING REVISION- STRUT KIT ....-2012N1023-2 (h)STRUT WIRE BUNDLE ROUT - ING REVISION- TOP KIT 1..-..012N1023-5 (i)RH STRUT WIRE BUNDLE ROUT - ING REVISION- TOP KIT ..-1..012N1023-6 STRUT WIRE BUNDLE ROUT - ING REVISION- STRUT KIT .-.2..012N1023-7 (h)STRUT WIRE BUNDLE ROUT - ING REVISION- TOP KIT -.....012N1023-8 (e)TFE-2X SLEEVING....1.012N1023-3 (f)LOCKSTITCH LACING TAPE ....1.012N1023-4 (b)BRACKET ASSY....1.313N5033-134 (a) (d)BOLT, PROTRUD- ING HD ....2.BACB30NX6K3X (a)CLAMP , LOOP..1...BACC10DK20 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 22 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 23 Kit 012N1023 NotesExisting Part Number NameQTYNew Part Number -8-7-6-5-2-1 (a)CLAMP , WIRE BUNDLE ..1.2.BACC10GU101 (a)COLLAR....2.BACC30M6 (b)GROMMET....1.BACG20Z- E001275 (b) (g)NUTPLATE.1....BACN10JA3 (a)NUT..1...BACN10YR3CD (b) (d) (g) RIVET.2....BACR15DR3AC5 (a) (d)BOLT..1...BACS12HN3-10 (a)WASHER..1.1.NAS1149D0332J (b)SCREW....1.NAS1801-3-8 (b) (c) (g) NUT SPACER.2....NAS463YDD10H (b)CLAMP....2.TA025041-02 (a) This part is not used in production. (b) This part is used in production. (c) Y ou can use the existing part to replace the new part. (d) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 and Boeing Drawing 65-88700 (757) are used to determine the part numbers used as substitutes. (e) 18 inches long, light blue, Zeus #7 unperforated thin wall. (f) 120 inches long, BMS 13-54, Class 1, Grade D, Type 3, Color - White, Finish C, aramid fabric. (g) Discard the existing part. (h) Top Kit 012N1023-8 replaces Top Kit 012N1023-1 on airplanes that have not accomplished the initial release of this Service Bulletin. Note: Operators that have already received Top Kit 012N1023-1 but have not ac- complished the initial release of this Service Bulletin (Group 1, Configuration 1) require Top Kit 012N1023- 5 to achieve the improvements detailed in this service bulletin. (i) Top Kit 012N1023-6 is required on airplanes that have accomplished the initial release of this Service Bulletin (Group 1, Configuration 2) and on airplanes that incorporated the intent of the initial release of this Service Bulletin during production (Group 2). BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 23 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 24 Kit 012N1023 NotesExisting Part Number NameQTYNew Part Number -6 RH STRUT WIRE BUNDLE ROUTING REVISION-TOP KIT -012N1023-6 (a)CLAMP , LOOP1BACC10DK20 (a)CLAMP , WIRE BUNDLE 1BACC10GU101 (a)NUT1BACN10YR3CD (a) (b)BOLT1BACS12HN3-10 (a) (b)WASHER1NAS1149D0332J (a) This part is not used in production. (b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substi- tute fasteners may be supplied in kits. Boeing Document D-590 and Boeing Drawing 65-88700 (757) are used to determine the part numbers used as substitutes. 2. Parts and Materials Supplied by the Operator: NotesNameQTYPart Number / Specification Type II, Class 1, Grade B (a) (b)Adhesive: Epoxy Polyamide, 2 Compo- nent 2 oz.BMS 5-126 Type V or Type VI (a)(b)Adhesive, Urethane2 oz.BMS 5-105 Type 5, Class 1. Cut the length as necessary at assembly. (a) Wire5 Ft.BMS 13-60, 18 AWG Type 1, Class 1. Cut the length as necessary at assembly. (a) Pigtail Wire10 InchBMS 13-16, 18 AWG Refer to SWPM 20-30-12 as an accepted procedure. Splice Kit1D-150-0169 Refer to SWPM 20-30-11 as an accepted procedure. Terminal, Lug1BACT12AC3 Refer to SWPM 20-61-11 as an accepted procedure. Socket Contact1BACC47CP2T Refer to SWPM 20-10-15 as an accepted procedure. (c) Inner Ferrule1BACS13S149BNP Refer to SWPM 20-10-15 BSW- PM 20-10-15. (d) Outer Ferrule1BACS13S225CNP BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 24 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 25 NotesNameQTYPart Number / Specification (e)Heat Shrinkable Sleeve1TFE-4X, 1/4 DIA Type III, Class 1, Grade D, Finish C. Length as necessary. (a) Lacing Tape10 Ft.BMS 13-54 M.M. Newman TFE Spiral Wrap 0.125 Inch OD, 0.065 ID (f) Spiral, Cable Wrap4.0 Ft.HT1-8T1 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Y ou can use BMS 5-126 or BMS 5-105, whichever is available. However, if a faster cure time is needed, use BMS 5-105 adhesive. (c) Measure the OD of the wire. The applicable inner ferrule has an ID that is a small amount larger than the OD of the wire. If necessary use a smaller or larger size inner ferrule. Refer to SWPM 20-10-15, Table VII. (d) More than one outer ferrule can be specified for one inner ferrule. Refer to SWPM 20-10-15, Table VII. (e) Refer to SWPM 20-10-14 for other heat shrinkable sleeve sizes and for alternative materials. (f) Operators can order this material from Boeing. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: NotesQTYNameExisting Part Number 2ClampBACC10GU101 2WasherAN960PD10L 2ScrewNAS1801-3-( ) 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 20, 2003 757-28A0073Revision 2: June 04, 2009 25 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 26 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 26 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT BLANK PAGE ### Page 27 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. 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 — Hole dimensions for standard solid rivets are given in 757 Structural Repair Manual, Chapter 51 — Torque limits to tighten nuts and bolts are given in 757 Structural Repair Manual, Chapter 51. 4. For approved fastener and process material substitutions, refer to 757 Structural Repair Manual, Chapter 51, Alternate fasteners are given in 757 Structural Repair Manual Chapter 51 and Boeing Drawing 65-88700. 5. If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. 6. Refer to the Standard Wiring Practices Manuals SWPM 20-00-14 for replacement of wires. 7. Refer to the Standard Wiring Practices Manuals SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures. 8. Refer to the Standard Wiring Practices Manuals SWPM 20-10-13 for repair of electrical wires and cables. B. WORK INSTRUCTIONS Group 1, Configuration 1: PART I - Reroute of Fuel Shut-off Valve wires W5100 (L/H) and W5200 (R/H) 1. For Left Engine Strut Reroute of Wire Bundle W5100 as follows: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 27 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 28 a. Gain access to the left aft fairing. Open panel 434AL and remove panels 434DR and 434CL as given in 757 AMM 06-43-00, or operators approved equivalent procedure. b. Inspect wire W5100 routing from Power Plant Station 278 to the aft end of the strut fairing. (1) If wire W5100 is installed as shown in FIGURE 1: (a) Remove the support clamps as shown in FIGURE 1. (b) Inspect wire bundle for damage, repair damage if found. Refer to FIGURE 2. (c) Add support bracket to PP STA 301 Bulkhead as shown in FIGURE 2. (d) Add protective sleeve and TFE spiral cable wrap if no chafe sleeve was installed during production, and add the support clamps and change the wire routing as shown in FIGURE 3. If there is not enough wire slack to re-route the wire: NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production.The Teflon Sleeve installed during production starts at the lower part of the Aft Strut fairing, at STA 278, and ends in the wing area. It is not necessary to install the protective sleeves and the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. 1) Gain access to the left wing trailing edge. Open panel 551EBX and 551BB as given in 757 AMM 06-44-00, or approved equivalent procedure. 2) Loosen all clamps from Fuel shut-off valve IRSS 270 to IRSS 353 as shown in FIGURE 3. 3) Pull enough wire back into the strut fairing, and attach wire to the loop clamp as shown in FIGURE 3. NOTE: Excess wire may be available in an existing loop made during production between IRSS 270 and IRSS 353. If no wire slack is found make a wire splice at the location shown in Figure 3. Remove the end of the wire W5100 from the splice location to connector D02142 (at Fuel Shut-off Valve) and ground GD2319-ST and discard. Splice a new wire, long enough to provide enough slack for re-routing the wire in the engine strut, that matches the discarded wire except for length added at the splice location. Make sure that the splice does not touch any clamp or structure. NOTE: Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that wire bundle clearance to surrounding structure or tubing, anywhere along the wire bundle routing, is as given in SWPM 20-10-11, Table IX. 4) Tighten all clamps from IRSS 270 to IRSS 353 and tie wire W5100 with lacing tape to the bundle as initially found. (2) If wire W5100 is installed as shown in FIGURE 5: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 28 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 29 (a) Inspect wire bundle for damage, repair damage if found. Refer to FIGURE 5. (b) Add support bracket to PP STA 301 Bulkhead as shown in FIGURE 5. (c) Add protective sleeve and TFE spiral cable wrap if no chafe sleeve was installed during production, and change wire W5100 routing as shown in FIGURE 3. If there is not enough wire slack to re-route the wire: NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production.The Teflon Sleeve installed during production starts at the lower part of the Aft Strut Fairing, at STA 278, and ends in the wing area. It is not necessary to install the protective sleeves and the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. 1) Gain access to the left wing trailing edge. Open panel 551EBX and 551BB as given in 757 AMM 06-44-00, or approved equivalent procedure. 2) Loosen all clamps from Fuel shut-off valve IRSS 270 to IRSS 353 as shown in FIGURE 3. 3) Pull enough wire back into the strut fairing, and attach wire to the loop clamp as shown in FIGURE 3. NOTE: Excess wire may be available in an existing loop made during production between IRSS 270 and IRSS 353. If no wire slack is found make a wire splice at the location shown in Figure 3. Remove the end of the wire W5100 from the splice location to connector D02142 (at Fuel Shut-off Valve) and ground GD2319-ST and discard. Splice a new wire, long enough to provide enough slack for re-routing the wire in the engine strut, that matches the discarded wire except for length added at the splice location. Make sure that the splice does not touch any clamp or structure. NOTE: Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that wire bundle clearance to surrounding structure or tubing, anywhere along the wire bundle routing, is as given in SWPM 20-10-11, Table IX. 4) Tighten all clamps from IRSS 270 to IRSS 353 and tie wire W5100 with lacing tape to the bundle as initially found. c. If wire damage was repaired or wire was spliced, test the Fuel Shut-Off valve wire W5100 as given in PART IV. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 29 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 30 d. Close panel 434AL and install panels 434DR and 434CL as given in 757 AMM 06-43-00, or operators approved equivalent procedure. e. Close panels 551EBX and 551BB as given in 757 AMM 06-43-00, or operators approved equivalent procedure. f. Put the airplane back to a serviceable condition. 2. For Right Engine Strut re-route the wire bundle W5200 as follows: a. Gain access to the right aft fairing. Open panel 444AL and remove panels 444DR and 444CL as given in 757 AMM 06-43-00, or operators approved equivalent procedure b. Inspect wire W5200 routing from Power Plant Station 278 to the aft end of the strut fairing. (1) If wire W5200 is installed as shown in FIGURE 1: (a) Remove the support clamps as shown in FIGURE 1. (b) Inspect wire bundle for damage, repair damage if found. Refer to FIGURE 2. (c) Add support bracket to PP STA 301 Bulkhead as shown in FIGURE 2. (d) Add support clamps and change wire routing as shown in FIGURE 4. (e) Add protective sleeve and TFE spiral cable wrap if no chafe sleeve was installed during production, and add back-to-back P-clamps on the hydraulic supply tube at the aft end of the Fairing strut as shown in FIGURE 4, and attach the wire to the loop clamps. If there is no slack to attach the wire: NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production.The Teflon Sleeve installed during production starts at the lower part of the Aft Strut Fairing, at STA 278, and ends in the wing area. It is not necessary to install the protective sleeves and the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. 1) Gain access to the right wing trailing edge. Open panel 651EBX and 651BB as given in 757 AMM 06-44-00, or operators approved equivalent procedure. 2) Loosen all clamps from Fuel shut-off valve IRSS 270 to IRSS 353 as shown in FIGURE 4. 3) Pull enough wire back into the strut fairing, and attach wire to the loop clamps as shown in FIGURE 4. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 30 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 31 NOTE: Excess wire may be available in an existing loop made during production between IRSS 270 and IRSS 353. If no wire slack is found make a wire splice at the location shown in Figure 4. Remove the end of the wire W5200 from the splice location to connector D02022 (at Fuel Shut-off Valve) and ground GD2419-ST and discard. Splice a new wire, long enough to provide enough slack for re-routing the wire in the engine strut, that matches the discarded wire except for length added at the splice location. Make sure that the splice does not touch any clamp or structure. NOTE: Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that wire bundle clearance to surrounding structure or tubing, anywhere along the wire bundle routing, is as given in SWPM 20-10-11, Table IX. 4) Tighten all clamps from IRSS 270 to IRSS 353 and tie wire W5200 with lacing tape to the bundle as initially found. (2) If wire W5200 is installed as shown in FIGURE 5: (a) Inspect wire bundle for damage, repair damage if found. Refer to FIGURE 5. (b) Add support bracket to PP STA 301 Bulkhead as shown in FIGURE 5. (c) Add protective sleeve and TFE spiral cable wrap if no chafe sleeve was installed during production, and add back-to-back P-clamps on the hydraulic supply tube at the aft end of the Fairing strut as shown in FIGURE 4, and attach wire to the loop clamp. If there is no slack to attach the wire: NOTE: Some airplanes have a Teflon Sleeve installed on the Fuel Shutoff Valve wires during production.The Teflon Sleeve installed during production starts at the lower part of the Aft Strut Fairing, at STA 278, and ends in the wing area. It is not necessary to install the protective sleeves and the Spiral Cable Wrap at the locations given in the bulletin, if the Fuel Shutoff Valve wires already have a Teflon sleeve installed at those locations. 1) Gain access to the right wing trailing edge. Open panel 651EBX and 651BB as given in 757 AMM 06-44-00, or operators approved equivalent procedure. 2) Loosen all clamps from Fuel shut-off valve IRSS 270 to IRSS 353 as shown in FIGURE 4. 3) Pull enough wire back into the strut fairing, and attach wire to the loop clamp as shown in FIGURE 4. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 31 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 32 NOTE: Excess wire may be available in an existing loop made during production between IRSS 270 and IRSS 353. If no wire slack is found make a wire splice at the location shown in Figure 4. Remove the end of the wire W5200 from the splice location to connector D02022 (at Fuel Shut-off Valve) and ground GD2419-ST and discard. Splice a new wire, long enough to provide enough slack for re-routing the wire in the engine strut, that matches the discarded wire except for length added at the splice location. Make sure that the splice does not touch any clamp or structure. NOTE: Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that wire bundle clearance to surrounding structure or tubing, anywhere along the wire bundle routing, is as given in SWPM 20-10-11, Table IX. 4) Tighten all clamps from IRSS 270 to IRSS 353 and tie wire W5200 with lacing tape to the bundle as initially found. c. If wire damage was repaired or wire was spliced test the Fuel Shut-Off valve as given in PART V. d. Close panel 444AL and install panels 444DR and 444CL as given in 757 AMM 06-43-00, or operators approved equivalent procedure. e. Close panels 651EBX and 651BB as given in 757 AMM 06-44-00, or operators approved equivalent procedure. f. Put the airplane back to a serviceable condition. Group 1, Configuration 2; Group 2: PART II - Installation of the Back-to Back clamps on the Right Engine Strut only 1. Gain access to the right aft fairing. Open panel 444AL and remove panels 444DR and 444CL as given in 757 AMM 06-43-00, or operators approved equivalent procedure. 2. Inspect wire bundle for damage, repair damage if found. Refer to FIGURE 6. 3. Add back-to-back p-clamps on the hydraulic supply tube at the aft end of the Fairing strut as shown in Figure 6, and attach wire to the loop clamp. NOTE: Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that wire bundle clearance to surrounding structure or tubing, anywhere along the wire bundle routing, is as given in SWPM 20-10-11, Table IX. 4. If wire damage was repaired test the Fuel Shut-Off Valve wire W5200 as given in PART V. 5. Close panel 444AL and install panels 444DR and 444CL as given in 757 AMM 06-43-00, or operators approved equivalent procedure. 6. Put the airplane back to a serviceable condition. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 32 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 33 Group 1, Configuration 2-3; Group 2: PART III - Installation of the TFE Spiral Cable Wrap on the Fuel Shutoff Valve wires at the aft end of Left and Right Engine Strut 1. Gain access: a. For the Left Engine Strut open panel 434AL and remove panels 434DR and 434CL. Refer to 757 AMM 06-43-00 as an accepted procedure. b. For the Right Engine Strut open panel 444AL and remove panels 444DR and 444CL. Refer to 757 AMM 06-43-00 as an accepted procedure. 2. Remove the wire bundle support clamps at the aft end of the Left and Right Engine Strut: a. For the Left Engine Strut as given in FIGURE 7. b. For the Right Engine Strut as given in FIGURE 8. 3. Inspect wire bundles W5100 (Left Engine Strut) and W5200 (Right Engine Strut) for damage. If damage is found: a. For the Left Engine Strut repair wire W5100 as given in FIGURE 7, and in SWPM 20-00-14 and SWPM 20-10-13. b. For the Right Engine Strut repair wire W5200 as given in FIGURE 8, and SWPM 20-00-14 and SWPM 20-10-13. 4. Add the TFE Spiral Cable Wrap if no Teflon sleeve was installed during production, and install the support clamps: a. For the Left Engine Strut as given in FIGURE 7. b. For the Right Engine Strut as given in FIGURE 8. NOTE: Do not install the TFE Spiral Cable Wrap if Teflon sleeve was installed during production at this location. Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that wire bundle clearance to surrounding structure or tubing, anywhere along the wire bundle routing, is as given in BSWPM 20-10-11, Table IX. 5. If wire damage was repaired test the Fuel Shut-Off Valve wires as follows: a. For the Left Engine Strut, wire bundle W5100, do "Part IV - Test for Left Engine Strut Fuel Shut-Off Valve wire W5100". b. For the Right Engine Strut, wire bundle W5200, do "Part V - Test for Right Engine Strut Fuel Shut-Off Valve wire W5200". 6. Close panels: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 33 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 34 a. For the left strut close panel 434AL and install panels 434DR and 434CL. Refer to 757 AMM 06-43-00 as an accepted procedure. b. For the right strut close panel 444AL and install panels 444DR and 444CL. Refer to 757 AMM 06-43-00 as an accepted procedure. 7. Put the airplane back to a serviceable condition. Group 1-2: PART IV- Test for Left Engine Strut Fuel Shut-Off Valve wire W5100 WARNING: OBEY THE APPLICABLE SHOP PROCEDURES FOR MAINTENANCE ON ENERGIZED ELECTRICAL SYSTEMS. SHORT CIRCUIT AND ELECTRICAL SHOCK TO PERSONS CAN OCCUR. 1. Do a check of each of the two redundant wires that supply power to close the left engine fuel spar valve a. Gain access to left engine fuel shut-off valve. Remove access panel 551BB as given in 757 AMM 06-44-00 b. Open these circuit breakers on the P6 panel and attach DO-NOT -CLOSE tags: (1) 6E1, FUEL VALVES L SPAR (2) 6H1, FIRE EXTINGUISHING ENG L BTL 1 (3) 6H2, FIRE EXTINGUISHING ENG L BTL 2 c. PUT THE LEFT ENGINE FUEL CONTROL SWITCH, FOUND ON THE P10 QUADRANT PANEL, TO THE "CUTOFF" POSITION d. Put the left engine fire switch, found on the P8 quadrant panel, to the NORMAL position e. Disconnect the connector for the left spar valve actuator, D2142 f. Remove the DO-NOT -CLOSE tag and close circuit breaker; 6E1, FUEL VALVES L SPAR on the Main Power Distribution Panel, P6 g. For the left spar valve, do a check for 28 VDC power (21.0 VDC minimum, 34.0 VDC maximum) between these pins on connector D2142 CONNECTOR D2142 TOFROM pin 4pin 5 pin 4pin 6 h. Open circuit breaker; 6E1, FUEL VALVES L SPAR and attach A DO-NOT -CLOSE tag on the Main Power Distribution Panel, P6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 34 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 35 i. For the left spar valve, re-connect the connector for the left spar valve actuator, D2142 j. For the left actuator, remove the DO-NOT -CLOSE tag and close these circuit breakers on the P6 panel (1) 6E1, FUEL VALVES L SPAR (2) 6H1, FIRE EXTINGUISHING ENG L BTL 1 (3) 6H2, FIRE EXTINGUISHING ENG L BTL 2 k. Supply electrical power as given in 757 AMM 24-22-00 2. Perform a functional test of the left engine fuel shutoff valve a. Make sure to close circuit breaker; 6E1, FUEL VALVES L SPAR on the P6 panel b. Make sure to close circuit breaker; 11D33, FUEL DISAGREE ENABLE LEFT on the P11 panel c. Put the FUEL CONTROL switch for the left engine on the P10 stand to the RICH-RUN position d. Get access to the actuator on the left engine fuel shutoff valve through the access door 551BB as given in 757 AMM 06-44-00 e. Make sure the manual override handle on the left engine fuel shutoff valve moves to the open position f. Make sure the SPAR VALVE disagreement light comes on while the left engine fuel shutoff valve moves to the open position g. Open these circuit breakers on the P6 panel and attach the DO-NOT -CLOSE tags. (1) 6H1, FIRE EXTINGUISHING ENG L BTL 1 (2) 6H2, FIRE EXTINGUISHING ENG L BTL 2 h. Pull the FIRE HANDLE for the left engine i. Make sure the manual override handle on the left engine fuel shutoff valve moves to the closed position j. Make sure the SPAR VALVE disagreement light comes on while the left engine fuel shutoff valve moves to the closed position k. Put the FIRE HANDLE for the left engine to the NORMAL position l. Make sure the manual override handle on the left engine fuel shutoff valve moves to the OPEN position m. Remove the DO-NOT -CLOSE tags and close these circuit breakers on the P6 panel. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 35 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 36 (1) 6H1, FIRE EXTINGUISHING ENG L BTL 1 (2) 6H2, FIRE EXTINGUISHING ENG L BTL 2 n. Open circuit breaker; 11D33, FUEL DISAGREE ENABLE LEFT, on the P11 panel o. Make sure the EICAS message, L FUEL SPAR VAL, shows on the top display p. Close circuit breaker; 11D33, FUEL DISAGREE ENABLE LEFT, on the P11 panel q. Make sure that the EICAS message, L FUEL SPAR VAL, does not show on the top display r. Put the FUEL CONTROL switch for the left engine on the P10 panel to the CUTOFF position s. Make sure the manual override handle on the left engine fuel shutoff valve moves to the closed position t. Close access to left engine fuel shutoff valve. Install access panel 551BB as given in 757 AMM 06-44-00 Group 1-2: PART V- Test for Right Engine Strut Fuel Shut-Off Valve wire W5200 WARNING: OBEY THE APPLICABLE SHOP PROCEDURES FOR MAINTENANCE ON ENERGIZED ELECTRICAL SYSTEMS. SHORT CIRCUIT AND ELECTRICAL SHOCK TO PERSONS CAN OCCUR. 1. Do a check of each of the two redundant wires that supply power to close the right engine fuel spar valve a. Gain access to right engine fuel shutoff valve. Remove access panel 651BB as given in 757 AMM 06-44-00, if not already removed. b. Open these circuit breakers on the P6 panel and attach DO-NOT -CLOSE tags: (1) 6E2, FUEL VALVES R SPAR (2) 6H3, FIRE EXTINGUISHING ENG R BTL 1 (3) 6H4, FIRE EXTINGUISHING ENG R BTL 2 c. PUT THE RIGHT ENGINE FUEL CONTROL SWITCH, FOUND ON THE P10 QUADRANT PANEL, TO THE "CUTOFF" POSITION d. Put the right engine fire switch, found on the P8 quadrant panel, to the NORMAL position e. Disconnect the connector for the right spar valve actuator, D2022 f. Remove the DO-NOT -CLOSE tag and close circuit breaker; 6E2, FUEL VALVES R SPAR on the Main Power Distribution Panel, P6 g. For the right spar valve, do a check for 28 VDC power (21.0 VDC minimum, 34.0 VDC maximum) between these pins on connector D2022 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 36 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 37 CONNECTOR D2022 TOFROM pin 4pin 5 pin 4pin 6 h. Open circuit breaker; 6E2, FUEL VALVES R SPAR and attach a DO-NOT -CLOSE tag on the Main Power Distribution Panel, P6 i. For the right spar valve, re-connect the connector for the right spar valve actuator, D2022 j. For the right actuator, remove the DO-NOT -CLOSE tag and close these circuit breakers on the P6 panel (1) 6E2, FUEL VALVES R SPAR (2) 6H3, FIRE EXTINGUISHING ENG R BTL 1 (3) 6H4, FIRE EXTINGUISHING ENG R BTL 2 k. Supply electrical power as given in 757 AMM 24-22-00 2. Perform a functional test of the Engine Fuel Shutoff Valves a. Make sure to close circuit breaker; 6E2, FUEL VALVES R SPAR on the P6 panel b. Make sure to close circuit breaker; 11D34, FUEL DISAGREE ENABLE RIGHT on the P11 panel c. Put the FUEL CONTROL switch for the right engine on the P10 stand to the RICH-RUN position d. Get access to the actuator on the right engine fuel shutoff valve through the access door 651BB as given in 757 AMM 06-44-00 e. Make sure the manual override handle on the right engine fuel shutoff valve moves to the open position f. Make sure the SPAR VALVE disagreement light comes on while the right engine fuel shutoff valve moves to the open position g. Open these circuit breakers on the P6 panel and attach the DO-NOT -CLOSE tags. (1) 6H3, FIRE EXTINGUISHING ENG R BTL 1 (2) 6H4, FIRE EXTINGUISHING ENG R BTL 2 h. Pull the FIRE HANDLE for the right engine i. Make sure the manual override handle on the right engine fuel shutoff valve moves to the closed position BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 37 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 38 j. Make sure the SPAR VALVE disagreement light comes on while the right engine fuel shutoff valve moves to the closed position k. Put the FIRE HANDLE for the right engine to the NORMAL position l. Make sure the manual override handle on the right engine fuel shutoff valve moves to the OPEN position m. Remove the DO-NOT -CLOSE tags and close these circuit breakers on the P6 panel. (1) 6H3, FIRE EXTINGUISHING ENG R BTL 1 (2) 6H4, FIRE EXTINGUISHING ENG R BTL 2 n. Open circuit breaker; 11D34, FUEL DISAGREE ENABLE RIGHT, on the P11 panel o. Make sure the EICAS message, R FUEL SPAR VAL, shows on the top display p. Close circuit breaker; 11D34, FUEL DISAGREE ENABLE RIGHT, on the P11 panel q. Make sure that the EICAS message, R FUEL SPAR VAL, does not show on the top display r. Put the FUEL CONTROL switch for the right engine to the CUTOFF position s. Make sure the manual override handle on the right engine fuel shutoff valve moves to the closed position t. Close access to right engine fuel shutoff valve. Install access panel 651BB as given in 757 AMM 06-44-00 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2: June 04, 2009 38 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 39 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. PP STA 276.93 PP STA 301 AFT FAIRING ACCESS PP DOOR AND ACCESS PANEL STA 290 PP STA 278 FWD< W49907 FIGURE 1: PREPARE FOR INSPECTION OF WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 1 OF 2) Original Issue: November 20, 2003 Revision 2 June 04, 2009 BOEING PROPRIETARY - 757-28A0073 Copyright © Unpublished Work - See page 1 for details. 39 of 69 ### Page 40 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 one side of the airplane. NOTE: Access to the area between the bulkhead at PP STA 278 and the bulkhead at PP STA 301 is through the lightening holes in the bulkheads. NOTESQTYPART NUMBERNAMETASKSTEP 1NAS1801-3-()ScrewRemove/Keep1 1AN960PD10LWasher 1BACN10JC3Nut (a)1-ClampRemove2 (a) (b)3NAS1801-3-()ScrewRemove/Keep3 3AN960PD10LWasher 3-Clamp 1NAS1801-3-()ScrewRemove/Keep4 1-Washer 1-Nut 1NAS1801-3-()ScrewRemove/Keep5 1AN960PD10LWasher 1BACN10JC3Nut (a)1-ClampRemove6 (a) Discard these clamps. New clamps are provided in the kit. (b) One screw and one washer removed in this step are not going to be replaced. FIGURE 1: PREPARE FOR INSPECTION OF WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 2 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 40 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 41 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. PP STA 276.93 PP STA 301 AFT FAIRING ACCESS PP DOOR AND ACCESS PANEL STA 290 PP STA 278 SEE 3(45 FWD W49908 FIGURE 2: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 1 OF 4) Original Issue: November 20, 2003 Revision 2 June 04, 2009 BOEING PROPRIETARY - 757-28A0073 Copyright © Unpublished Work - See page 1 for details. 41 of 69 ### Page 42 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT PP STA 301 FWDO PP STA 301 1.00 MINIMUM 6 /13) 61 & 1112 GROMMET 10)11 FWD W49913 A-A FIGURE 2: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 2 OF 4) Original Issue: November 20, 2003 Revision 2 June 04, 2009 BOEING PROPRIETARY - 757-28A0073 Copyright © Unpublished Work - See page 1 for details. 42 of 69 ### Page 43 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 one engine. NOTESQTYPART NUMBERNAMETASKSTEP from PP STA 278 to the aft end of strut fairing for damage. 1W5100 left engineWire BundleInspect1 W5200 right engine If damage is found, repair as given in SWPM 20-00-14 and SWPM 20- 10-13, and check as given in the WORK INSTRUCTIONS. 1W5100 left engineWire BundleRepair2 W5200 right engine If installed, go to step 6. If missing, go to step 4. 2BACG20Z-ECaterpillar GrommetInspect3 1313N5033-()BulkheadClean4 1 oz.-Isopropyl/Denatured Alcohol 6 Inch Grommet at each location to extend a minimum of 1 inch below wire bundle. (a) (b) 2BACG20Z-ECaterpillar GrommetInstall5 Type II, Class 1, Epibond 1534 A/B.1 oz.BMS 5-126 orAdhesive Type V or Type VI as given in BAC 5010 Type 82. (c) 1 oz.BMS 5-105 As given in 757 SRM 51-40-02.2-RivetRemove6 2-Spacer 1-Nut Plate As given in 757 SRM 51-40-02.2-RivetsRemove7 over 2 attach holes.1313N5033-134Bracket AssyPut/Hold8 0.200-0.203 inch diameter as given in 757 SRM 51-40-02. 2-HolesDrill9 1313N5033-134Bracket AssyRemove10 in bracket and bulkhead.2-HolesDeburr11 As given in 757 SRM 51-40-02.1313N5033-134Bracket AssyInstall12 2BACB30NX6K3XBolt 2BACC30M6Collar As given in 757 SRM 51-40-02.2BACR15DR3AC5RivetInstall13 2NAS463YDD10HSpacer 1BACN10JA3Nut Plate FIGURE 2: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 3 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 43 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 44 NOTESQTYPART NUMBERNAMETASKSTEP (a) Remove the legs from the forward side of the grommet installed on STA 278 Bulkhead. (b) Remove the legs from the forward side of the grommet installed on STA 301 Bulkhead. If necessary, remove legs from the aft side of the grommet installed at STA 301, only at the location adjacent to the existing bracket, to provide clearance. (c) Use this adhesive when a faster cure time is needed. FIGURE 2: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 4 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 44 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 45 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. PP STA (6 13) 276.93 PP STA 301 AFT FAIRING ACCESS PP DOOR AND ACCESS PANEL STA 290 1.5 INCH . MINIMUM FROM CLAMP 2.5 INCH MINIMUM (10 FROM CLAMP SEE PP STA 278 FWD W49915 FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 1 OF 7) Original Issue: November 20, 2003 Revision 2 June 04, 2009 757-28A0073 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 69 ### Page 46 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT PP STA 301 PP STA 290 FWDO W49916 FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 2 OF 7) Original Issue: November 20, 2003 Revision 2 June 04, 2009 BOEING PROPRIETARY - 757-28A0073 Copyright © Unpublished Work - See page 1 for details. 46 of 69 ### Page 47 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT W5100 5613) WS 350 IRSS 346.54 FWDE LEFT REAR SPAR D35542 FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 3 OF 7) Original Issue: November 20, 2003 Revision 2 June 04, 2009 757-28A0073 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 69 ### Page 48 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT W5100 5)6 13) SPLICE AREA IRSS 250 FUEL IRSS SHUT-OFF 270 VALVE IRSS 290 IRSS 310 IRSS AINBD 330 →EWD D35575 FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 4 OF 7) Original Issue: November 20, 2003 Revision 2 June 04, 2009 757-28A0073 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 69 ### Page 49 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 one engine strut. NOTE: Access to the area between the bulkhead at PP STA 278 and the bulkhead at PP STA 301 is through the lightening holes in the bulkheads. NOTESQTYPART NUMBERNAMETASKSTEP If sleeve is installed go to step 2.1 Cut sleeve along length and wrap around wire bundle. 4-5 inch long TFE-2XSleeveInstall Each lacing tape is 12.0 inch long. Refer to SWPM 20-10-11 as an accepted pro- cedure. 3BMS 13-54Lacing Tape Make sure all wire slack is evenly dis- tributed.(a) 1BACC10GU101ClampInstall2 1AN960PD10LWasherInstall/Kept 1NAS1801-3-()Screw 1BACN10JC3Nut If sleeve is installed go to step 4.3 Cut sleeve along length and wrap around wire bundle. 4-5 inch long TFE-2XSleeveInstall Each lacing tape is 12.0 inch long. Refer to SWPM 20-10-11 as an accepted pro- cedure. 3BMS 13-54Lacing Tape If more wire is necessary to re-route the wire do steps 4, 5, and 6, or 7. If no more wire is necessary go to step 7. 4 from IRSS 270 to IRSS 347.-ClampsLoosen that hold wire W5100 from IRSS 270 to IRSS 347. Lacing tapeCut5 FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 5 OF 7) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 49 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 50 NOTESQTYPART NUMBERNAMETASKSTEP to the aft end of the strut fairing. If no slack is found splice wire.(b) W5100WirePull6 at the location shown using the splice kit and route wire to the fuel shut-off valve connector. Refer to SWPM 20-30-12 and SWPM 20-10-11 as accepted proce- dures. (c) -BMS 13-60, Type 5, Class 1, AWG 18 WireSplice Cut length as necessary, 6.0 inches maximum permitted. Install the shield ground wire as given in SWPM 20-10-15. -BMS 13-16, Type 1, Class 1, AWG 18 Pigtail Wire Refer to SWPM 20-30-12 as an accepted procedure.. 1D-150-0169Splice Kit Refer to SWPM 20-61-11 as an accepted procedure. (d) (e) 1BACC47CP2TSocket Contact Refer to SWPM 20-10-15 as an accepted procedure. (f) 1BACS13S149BNPInner Ferrule Refer to SWPM 20-10-15 as an accepted procedure. (g) 1BACS13S225CNPOuter Ferrule Refer to SWPM 20-10-14 as an accepted procedure. 1TFE 4X, 1/4 DIAHeat Shrinkable Sleeve Refer to SWPM 20-30-11 as an accepted procedure. 1BACT12AC3Terminal Lug Tie wire to the bundle. Refer to SWPM 20-10-11 as an accepted procedure. -BMS13-54, Type III, Class 1 Lacing tape Make sure all wire slack is evenly dis- tributed. (a) 1TA025041-02ClampInstall7 1-WasherInstall/Kept 1NAS1801-3-()Screw 1-Nut If sleeve is installed go to step 9.8 Cut sleeve along length and wrap around wire bundle. 4-5 inch long TFE-2XSleeveInstall Each lacing tape is 12.0 inch long. Refer to SWPM 20-10-11 as an accepted pro- cedure. 3BMS 13-54Lacing Tape Make sure all wire slack is evenly dis- tributed. Refer to SWPM 20-10-12 as an accepted procedure.(a) 1TA025041-02ClampInstall9 1NAS1149D0332JWasher 1NAS1801-3-8Screw FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 6 OF 7) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 50 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 51 NOTESQTYPART NUMBERNAMETASKSTEP the TFE Spiral Cable Wrap on the wire bundle. Extend the Spiral Cable Wrap on both sides of the clamp. Apply 3 layers of Permacel tape at each end of the TFE Spiral Cable Wrap. Secure (tie) the Per- macel tape with Lacing Tape. Refer to SWPM 20-10-11 as an accepted proce- dure. 2 Ft.HT1-8T1TFE Spiral Ca- ble Wrap Install10 As req.P-421Permacel Tape As Req. BMS13-54, Type III, Class 1 Lacing tape With lobe containing wire bundle aft and fastener head inboard . Refer toSWPM 20-10-12as an accepted procedure.(a) 1BACC10GU101ClampInstall11 1AN960PD10LWasherInstall/Kept 1NAS1801-3-()Screw 1BACN10JC3Nut that have been loosen in step 4, from loop clamp to the fuel shut-off valve locat- ed at IRSS 270. Refer to SWPM 20-10- 12 as an accepted procedure.(a) -ClampsTighten12 from the aft end of strut fairing to the fuel shut-off valve. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted proce- dures. (a) (h) -BMS13-54, Type III, Class 1 Lacing tapeInstall13 (a) Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that the wire bundle clearance to the surrounding structure or tubing, anywhere along the wire routing, is as given in SWPM 20-10-11, Table IX. (b) Make sure that you do not damage wire W5100 or any other wire common to the bundle to which W5100 is attached. (c) Remove the socket contact from the connector. Pull wire to the aft end of the strut to obtain the necessary slack. Cut the wire so that the splice will be located at the location shown. Splice the new wire and route it to the fuel shutoff valve connector the same as the initial wire. (d) Use care to remove the initial contact, with their wire connected. Use isopropyl alcohol, as given in SWPM 20-61-11, to make it easier to remove contacts. (e) Insert the new contact at the same position as the removed socket contact was found. (f) Measure the OD of the wire. The applicable inner ferrule has an ID that is a small amount larger than the OD of the wire. If necessary use a smaller or larger size inner ferrule. (g) More than one outer ferrule can be specified for one inner ferrule. Refer to SWPM 20-10-15 Table VII. (h) Make a drip loop at IRSS 270 as initially found. Refer to SWPM 20-10-11 as an accepted procedure. FIGURE 3: LEFT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 7 OF 7) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 51 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 52 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. PP STA 5x6 14 276.93 PP STA 301 AFT FAIRING ACCESS PP DOOR AND ACCESS PANEL STA 290 SEE PP STA 278 → SEE A PP STA 278 D30639 FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 1 OF 8) Original Issue: November 20, 2003 Revision 2 June 04, 2009 757-28A0073 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 69 ### Page 53 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT PP STA 301 PP STA 290 1.5 INCH MINIMUM FROM CLAMP FWD ' 1.5 INCH MINIMUM FROM CLAMP D31527 FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 2 OF 8) Original Issue: November 20, 2003 Revision 2 June 04, 2009 BOEING PROPRIETARY - 757-28A0073 Copyright © Unpublished Work - See page 1 for details. 53 of 69 ### Page 54 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT W5200 5)(6) 14 WS 350 IRSS 346.54 SFWD RIGHT REAR SPAR D35583 FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 3 OF 8) Original Issue: November 20, 2003 Revision 2 June 04, 2009 757-28A0073 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 69 ### Page 55 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT FUEL SHUT-OFF VALVE W5200 5 6 14 SPLICE AREA IRSS 250 IRSS to a 270 IRSS 290 IRSS 310 INBD < IRSS FWD 330 D35609 FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 4 OF 8) Original Issue: November 20, 2003 Revision 2 June 04, 2009 BOEING PROPRIETARY - 757-28A0073 Copyright © Unpublished Work - See page 1 for details. 55 of 69 ### Page 56 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 one engine strut. NOTE: Access to the area between the bulkhead at PP STA 278 and the bulkhead at PP STA 301 is through the lightening holes in the bulkheads. NOTESQTYPART NUMBERNAMETASKSTEP If sleeve is installed go to step 2.1 Cut sleeve along length and wrap around wire bundle. 4-5 inch long TFE-2XSleeveInstall Each lacing tape is 12.0 inch long. Refer to SWPM 20-10-11 as an accepted pro- cedure. 3BMS 13-54Lacing Tape Make sure all wire slack is evenly dis- tributed. Refer to SWPM 20-10-12 as an accepted procedure. (a) 1BACC10GU101ClampInstall2 1AN960PD10LWasherInstall/Kept 1NAS1801-3-()Screw 1BACN10JC3Nut If sleeve is installed go to step 4.3 Cut sleeve along length and wrap around wire bundle. 4-5 inch long TFE-2XSleeveInstall Each lacing tape is 12.0 inch long. Refer to SWPM 20-10-11 as an accepted pro- cedure. 3BMS 13-54Lacing Tape If more wire is necessary to re-route the wire do steps 4, 5, and 6. If no more wire is necessary go to step 7. 4 from IRSS 270 to IRSS 347.-ClampsLoosen that hold wire W5200 from IRSS 270 to IRSS 347. Lacing tapeCut5 FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 5 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 56 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 57 NOTESQTYPART NUMBERNAMETASKSTEP to the aft end of the strut fairing. If no slack is found splice wire. (b) W5200WirePull6 at the location shown using the splice kit and route wire to the fuel shut-off valve connector. Refer SWPM 20-30-12 and SWPM 20-10-11 as accepted proce- dures. (c) -BMS 13-60, Type 5, Class 1, AWG 18 WireSplice Cut length as necessary, 8.0 inches maximum permitted. Install the shield ground wire as given in SWPM 20-10-15. -BMS 13-16, Type 1, Class 1, AWG 18 Pigtail Wire Refer to SWPM 20-30-12 as an accepted procedure. 1D-150-0169Splice Kit Refer to SWPM 20-61-11 as an accepted procedure. (d) (e) 1BACC47CP2TSocket Contact Refer to SWPM 20-10-15 as an accepted procedure. (f) 1BACS13S149BNPInner Ferrule Refer to SWPM 20-10-15 as an accepted procedure.(g) 1BACS13S225CNPOuter Ferrule Refer to SWPM 20-10-14 as an accepted procedure. 1TFE 4X, 1/4 DIAHeat Shrinkable Sleeve Refer to SWPM 20-30-11 as an accepted procedure. 1BACT12AC3Terminal Lug Tie wire to the bundle. Refer to SWPM 20-10-11 as an accepted procedure. -BMS13-54, Type III, Class 1 Lacing tape Make sure all wire slack is evenly dis- tributed. (a) 1TA025041-02ClampInstall7 1-WasherInstall/Kept 1NAS1801-3-()Screw 1-Nut If sleeve is installed go to step 6.8 Cut sleeve along length and wrap around wire bundle. 4-5 inch long TFE-2XSleeveInstall Each lacing tape is 12.0 inch long. Refer to SWPM 20-10-11 as an accepted pro- cedure. 3BMS 13-54Lacing Tape Make sure all wire slack is evenly dis- tributed. Refer to SWPM 20-10-12 as an accepted procedure. (a) 1TA025041-02ClampInstall9 1NAS1149D0332JWasher 1NAS1801-3-8Screw FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 6 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 57 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 58 NOTESQTYPART NUMBERNAMETASKSTEP the TFE Spiral Cable Wrap on the wire bundle. Extend the Spiral Cable Wrap away from each clamp as shown. Apply 3 layers of Permacel tape at each end of the TFE Spiral Cable Wrap. Secure (tie) the Permacel tape with Lacing Tape. Refer to SWPM 20-10-11 as an accepted procedure. 2 Ft.HT1-8T1TFE Spiral Ca- ble Wrap Install10 -P-421 (Permacel)Permacel Tape As Req. BMS13-54, Type III, Class 1 Lacing tape With lobe containing wire bundle aft and fastener head outboard. Refer to SWPM 20-10-12 as an accepted procedure. (a) 1BACC10GU101ClampInstall11 1AN960PD10LWasherInstall/Kept 1NAS1801-3-()Screw 1BACN10JC3Nut on the hydraulic supply tube. (a) (h)1BACC10DK20ClampInstall12 1BACC10GU101Clamp 1BACS12HN3-10Screw 1NAS1149D0332JWasher 1BACN10YR3CDNut that have been loosen in step 4, from loop clamp to the fuel shut-off valve locat- ed at IRSS 270. (a) -ClampsTighten13 from the aft end of strut fairing to the fuel shut-off valve. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted proce- dures. (a) (i) -BMS13-54, Type III, Class 1 Lacing tapeInstall14 (a) Make sure that wire bundle is correctly installed and does not touch the hydraulic tubes, strut fairing panel, or surrounding structure. Inspect that the wire bundle clearance to the surrounding structure or tubing, anywhere along the wire routing, is as given in SWPM 20-10-11, Table IX. (b) Make sure that you do not damage wire W5200 or any other wire common to the bundle to which W5200 is attached. (c) Remove the socket contact from the connector. Pull wire to the aft end of the strut to obtain the necessary slack. Cut the wire so that the splice will be located at the location shown. Splice the new wire and route it to the fuel shutoff valve connector the same as the initial wire. (d) Use care to remove the initial contact, with their wire connected. Use isopropyl alcohol, as given in SWPM 20-61-11, to make it easier to remove contacts. (e) Insert the new contact at the same position as the removed socket contact was found. (f) Measure the OD of the wire. The applicable inner ferrule has an ID that is a small amount larger than the OD of the wire. If necessary use a smaller or larger size inner ferrule. FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 7 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 58 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 59 NOTESQTYPART NUMBERNAMETASKSTEP (g) More than one outer ferrule can be specified for one inner ferrule. Refer to SWPM 20-10-15, Table VII as an accepted procedure. (h) Locate Clamps approximately 5.0 Inch aft of hydraulic clamp block. (i) Make a drip loop at IRSS 270 as initially found. Refer to SWPM 20-10-11 as an accepted procedure. FIGURE 4: RIGHT HAND STRUT - REROUTE WIRE BUNDLE - GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 8 OF 8) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 20, 2003 757-28A0073Revision 2 June 04, 2009 59 of 69 BOEING SERVICE BULLETIN 757-28A0073 ALERTALERT ### Page 60 (OCR) BOEING SERVICE BULLETIN 757-28A0073 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. PP STA 276.93 PP STA 301 AFT FAIRING ACCESS PP DOOR AND ACCESS PANEL STA 290 PP STA 278 SEE A PP STA 278 780 FWD D30899 FIGURE 5: INSPECT WIRE BUNDLE AND ADD SUPPORT BRACKET - FOR GROUP 1 CONFIGURATION 1 AIRPLANES (SHEET 1 OF 4) Original Issue: November 20, 2003 Revision 2 June 04, 2009 757-28A0073 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 69 The text continues at https://openairdocs.org/service-documents/boeing/757-28a0073/file/cc24ae94132a.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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