# Boeing Service Bulletin MD11-28-126: Boeing - Service Bulletin - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-0210; AD 2014-03-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Service Bulletin MD11-28-126](https://openairdocs.org/service-documents/boeing/md11-28-126.md) - Title as filed: Boeing - Service Bulletin - Pages: 244 - PDF: https://openairdocs.org/files/sha256/9b/89/9b8903cd73039fa2d4bd00ba12d437152654b64d839781a19ddaf788934d8909 - Page: https://openairdocs.org/service-documents/boeing/md11-28-126/file/9b8903cd7303 ## 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 MD11 Service Bulletin Number: MD11-28-126 Original Issue: March 03, 2009 Revision 4: November 29, 2011 ATA System: 2811 SUBJECT: FUEL - Integral Fuel Tanks - Inspection and Sleeving Installation of Wire Assemblies Routed Above the Center Upper Auxiliary Fuel Tank 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all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 1 of 244 2.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 2 of 244 BOEING SERVICE BULLETIN MD11-28-126 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 3 B. Concurrent Requirements ...................................... 1 3 C. Reason ................................................ 1 3 D. Description .............................................. 1 4 E. Compliance .............................................. 1 5 F. Approval ............................................... 1 6 G. Manpower .............................................. 1 6 H. Weight and Balance Changes .................................... 1 8 I. Electrical Load Data ......................................... 1 9 J. References .............................................. 1 9 1. Existing Data: ......................................... 1 9 2. Data supplied with this Service Bulletin: ........................... 2 0 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 0 K. Publications Affected ........................................ 2 0 L. Interchangeability and Intermixability of Parts ........................... 2 0 2. MATERIAL INFORMATION ........................................ 2 1 A. Material - Price and Availability ................................... 2 1 B. Industry Support Information .................................... 2 2 C. Parts Necessary For Each Airplane ................................. 2 2 1. Kits/Parts: ........................................... 2 2 2. Parts and Materials Supplied by the Operator: ........................ 3 2 3. Parts Modified and Reidentified: ............................... 3 3 4. Parts Removed and Not Replaced: .............................. 3 3 D. Parts Necessary to Change Spares ................................. 3 3 E. Special Tooling - Price and Availability ............................... 3 3 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 3 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5 A. GENERAL INFORMATION ..................................... 3 5 B. WORK INSTRUCTIONS ....................................... 3 8 FIGURE 1: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL [Group 1, Configuration 1] .... 5 1 FIGURE 2: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION [Group 1, Configuration 1] . 56 FIGURE 3: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION [Group 1, Configuration 1 ] ................................................ 6 0 FIGURE 4: CLAMPS AT FLOOR BEAMS, RIGHT SIDE - REMOVAL [Group 1, Configuration 1; Group 3] .................................................. 6 7 FIGURE 5: BARRIER/SHIELD SLEEVING, RIGHT SIDE - INSTALLATION [Group 1, Configuration 1; Group 3 ] ................................................ 7 2 FIGURE 6: CLAMPS AND EXTRUDED CHANNEL, RIGHT SIDE - INSTALLATION [Group 1, Configuration 1; Group 3] ........................................... 7 5 FIGURE 7: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL [Group 2, Configuration 1] .... 8 1 FIGURE 8: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION [Group 2, Configuration 1] . 86 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 3 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 4 FIGURE 9: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION [Group 2, Configuration 1 ] ................................................ 8 9 FIGURE 10: CLAMPS AT FLOOR BEAMS, RIGHT SIDE - REMOVAL [Group 2, Configuration 1; Group 4] .................................................. 9 6 FIGURE 11: BARRIER/SHIELD SLEEVING, RIGHT SIDE - INSTALLATION [Group 2, Configuration 1; Group 4 ] ................................................ 1 0 1 FIGURE 12: CLAMPS AND EXTRUDED CHANNEL, RIGHT SIDE - INSTALLATION [Group 2, Configuration 1; Group 4] .......................................... 1 0 4 FIGURE 13: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL [Group 3] ............ 1 1 0 FIGURE 14: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION [Group 3] ......... 1 1 8 FIGURE 15: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION [Group 3] .... 1 2 3 FIGURE 16: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL [Group 4] ............ 1 3 2 FIGURE 17: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION [Group 4] ......... 1 3 9 FIGURE 18: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION [Group 4] .... 1 4 4 FIGURE 19: LEFT AND RIGHT SIDE WIRE BUNDLE - INSPECTION [Group 1, Configuration 2] . . . 153 FIGURE 20: LEFT AND RIGHT SIDE WIRE BUNDLE - INSPECTION [Group 2, Configuration 2] . . . 158 FIGURE 21: BARRIER/SHIELD SLEEVING AND CLAMPING INSTALLATION - LEFT AND RIGHT SIDE [Group 1, Configuration 2] .................................. 1 6 3 FIGURE 22: BARRIER/SHIELD SLEEVING AND CLAMPING INSTALLATION - LEFT AND RIGHT SIDE [Group 2, Configuration 2] .................................. 1 6 9 FIGURE 23: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL [Group 5, Configuration 1] . . . 176 FIGURE 24: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION [Group 5, Configuration 1] . 181 FIGURE 25: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION [Group 5, Configuration 1 ] ................................................ 1 8 5 FIGURE 26: CLAMPS AT FLOOR BEAMS, RIGHT SIDE - REMOVAL [Group 5, Configuration 1] . . 192 FIGURE 27: BARRIER/SHIELD SLEEVING, RIGHT SIDE - INSTALLATION [Group 5, Configuration 1] . 197 FIGURE 28: CLAMPS AND EXTRUDED CHANNEL, RIGHT SIDE - INSTALLATION [Group 5, Configuration 1 ] ................................................ 2 0 0 FIGURE 29: WIRE BUNDLE - INSPECTION [Group 5, Configuration 2] ................. 2 0 7 FIGURE 30: BARRIERSHIELD SLEEVEING, RIGHT SIDE - INSTALLATION [Group 5, Configuration 2] . 209 FIGURE 31: CLAMPS AND EXTRUDED CHANNEL, RIGHT SIDE - INSTALLATION [Group 5, Configuration 2 ] ................................................ 2 1 2 FIGURE 32: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL [Group 6] ............ 2 1 6 FIGURE 33: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION [Group 6] ......... 2 2 1 FIGURE 34: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION [Group 6] .... 2 2 4 FIGURE 35: CLAMPS AT FLOOR BEAMS, RIGHT SIDE - REMOVAL [Group 6] ............ 2 3 1 FIGURE 36: BARRIER/SHIELD SLEEVING, RIGHT SIDE - INSTALLATION [Group 6] ........ 2 3 6 FIGURE 37: CLAMPS AND EXTRUDED CHANNEL, RIGHT SIDE - INSTALLATION [Group 6] .... 2 3 9 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 4 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 5 Commercial Airplanes MD11 Service Bulletin Revision Transmittal SheetNumber: MD11-28-126Original Issue: March 03, 2009 Revision 4: November 29, 2011 ATA System: 2811 SUBJECT: FUEL - Integral Fuel Tanks - Inspection and Sleeving Installation of Wire Assemblies Routed Above the Center Upper Auxiliary Fuel Tank This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16 is related to this service bulletin. No More work is necessary on airplane(s) changed in accordance with Revision 3 of this service bulletin. REASON FOR REVISION This revision is sent to incorporate engineering released subsequent to Revision 3 of this service bulletin, which adds sleeving clamping and extruded channel requirements to formerly Group 2 airplanes with wire assembly run AES9501 - ENL and AES9601 - ENR. These sections were changed: 1. In Paragraph 1.D., Description, added Group 6 description and maintenance zone data. 2. In Paragraph 1.G., Manpower, added Group 6 manpower data. 3. In Paragraph 1.H., Weight and Balance Changes, added Group 6 weight and balance data. 4. In Paragraph 1.J.3., Installation Drawings Used in the Preparation of this Service Bulletin, changed drawing revision level. 5. In Paragraph 2.A., Material - Price and Availability, added kits. 6. In Paragraph 2.C.1., Kits/Parts, added kits. 7. In Paragraph 3.A., General Information, removed former note number 8 and renumbered all subsequent. 8. In Paragraph 3.B., Work Instructions, added Group 6 data. 9. Corrected typographical error in Figure 18. 10. Added Figures 32 through 37. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 5 of 244 ### Page 6 Pages with no vertical lines have no important changes. REVISION HISTORY March 03, 2009Original Issue: June 18, 2009Revision 1: November 18, 2010Revision 2: June 03, 2011Revision 3: November 29, 2011Revision 4: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 6 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 7 Commercial Airplanes MD11 Service Bulletin SummaryNumber: MD11-28-126Original Issue: March 03, 2009 Revision 4: November 29, 2011 ATA System: 2811 SUBJECT: FUEL - Integral Fuel Tanks - Inspection and Sleeving Installation of Wire Assemblies Routed Above the Center Upper Auxiliary Fuel Tank CONCURRENT REQUIREMENTS None. BACKGROUND Boeing Special Federal Aviation Regulation (SFAR) 88 engineering investigations have determined that wires routed above the center upper auxiliary fuel tank are in close proximity to the upper surface of the tank. In addition some wire harness mounts may have loosened, allowing the wires to contact the tank. This condition may cause wire damage or chafing that can lead to possible arcing and sparking on the fuel tank upper surface. Inspecting the wires will determine the condition of the wires. Installation of nonmetallic barrier/shield sleeving, new clamps, and new extruded channels for wiring support will minimize the possibility of wires contacting the fuel tank upper surface. If not corrected, wires contacting the center upper auxiliary fuel tank surface may become damaged, and the possibility of arcing and sparking may lead to burn-through of the upper surface of the fuel tank. Burn-through on the upper surface of the fuel tank could potentially result in a tank explosion. This service bulletin resulted from the safety assessments conducted by Boeing under Special Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements. ACTION Refer to Paragraph 1.D., Description. EFFECTIVITY MD-11 and MD-11F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16 is related to this service bulletin. Boeing recommends that the inspection/change given in this service bulletin be done within 60 months after the effective date of Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the changes and/or repair procedures given in this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 7 of 244 ### Page 8 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: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 8 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 9 (OCR) BOEING SERVICE BULLETIN MD11-28-126 INSPECTION AND SLEEVING INSTALLATION OF WIRE ASSEMBLIES ROUTED ABOVE THE CENTER UPPER AUXILIARY FUEL TANK 2022707 Original Issue: March 03, 2009 Revision 4: November 29, 2011 BOEING PROPRIETARY - MD11-28-126 Copyright © Unpublished Work - See page 1 for details. 9 of 244 ### Page 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 10 of 244 BOEING SERVICE BULLETIN MD11-28-126 BLANK PAGE ### Page 11 Commercial Airplanes MD11 Service Bulletin Number: MD11-28-126 Original Issue: March 03, 2009 Revision 4: November 29, 2011 ATA System: 2811 SUBJECT: FUEL - Integral Fuel Tanks - Inspection and Sleeving Installation of Wire Assemblies Routed Above the Center Upper Auxiliary Fuel Tank 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below. When a Group 3 or Group 4 airplane shown below is modified to a freighter configuration by Boeing Passenger to Freighter (P to F) engineering, it will become a Group 1 or Group 2 airplane respectively. DESCRIPTIONCONFIGURATIONGROUP Applicable to MD-11/MD-11F airplanes with Wire Support Brackets P/N AAP8000-559 and AAP8000-1527 and without Forward Auxiliary Fuel Tank. -1 Applicable to MD-11/MD-11F operators who have not accomplished prior issues of this service bulletin. 1 Applicable to MD-11/MD-11F operators who have accomplished prior issues of this service bulletin. 2 Applicable to MD-11/MD-11F airplanes without Wire Support Brackets P/N AAP8000-559 and AAP8000-1527 and without Forward Auxiliary Fuel Tank. -2 Applicable to MD-11/MD-11F operators who have not accomplished prior issues of this service bulletin. 1 Applicable to MD-11 operators who have accomplished prior issues of this service bulletin. 2 Applicable to MD-11/MD-11F airplanes with Wire Support Brackets P/N AAP8000-559 and AAP8000-1527 and with Forward Auxiliary Fuel Tank. -3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 11 of 244 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP Applicable to MD-11 airplanes without Wire Support Brackets P/N AAP8000-559 and AAP8000-1527 and with Forward Auxiliary Fuel Tank. -4 Applicable to MD-11/MD-11F airplanes with Wire Support Brackets P/N AAP8000-559 and AAP8000-1527 and without Forward Auxiliary Fuel Tank. -5 Applicable to MD-11/MD-11F operators who have not accomplished prior issues of this service bulletin. 1 Applicable to MD-11/MD-11F operators who have accomplished prior issues of this service bulletin. 2 Applicable to MD-11F airplanes without Wire Support Brackets P/N AAP8000-559 and AAP8000-1527 and without Forward Auxiliary Fuel Tank. -6 Airplane Models: MD-11, MD-11F GroupFuselage Num- ber 2447 - 449 2451 - 464 2466 - 487 6488 2489 6491 2492 - 517 2519 - 531 4532 2533 - 543 4544 2545 - 552 2554 - 564 6565 2566 6567 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 12 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 13 GroupFuselage Num- ber 2568 - 578 2580 - 587 1588 - 589 3590 1591 - 596 3597 1598 - 607 3608 5609 1610 - 615 5616 - 618 1619 - 624 5625 - 629 1630 - 636 5637 1638 5639 - 646 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Boeing Special Federal Aviation Regulation (SFAR) 88 engineering investigations have determined that wires routed above the center upper auxiliary fuel tank are in close proximity to the upper surface of the tank. In addition some wire harness mounts may have loosened, allowing the wires to contact the tank. This condition may cause wire damage or chafing that can lead to possible arcing and sparking on the fuel tank upper surface. Inspecting the wires will determine the condition of the wires. Installing nonmetallic barrier/shield sleeving, new clamps, and new extruded channels for wiring support, will minimize the possibility of wires contacting the fuel tank upper surface. If not corrected, wires contacting the center upper auxiliary fuel tank surface may become damaged, the possibility of arcing and sparking may lead to burn-through of the upper surface of the fuel tank. Burn-through on the upper surface of the fuel tank could potentially result in a tank explosion. This service bulletin resulted from the safety assessments conducted by Boeing under Special Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 13 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 14 Revision 1 was sent to add parts that were omitted, correct part quantities of some parts and to change airplane groupings. This revision corrects the no-work condition given in Information Notice MD11-28-126 IN 01. Revision 2 was sent to incorporate engineering released subsequent to revision 1 of this service bulletin, which adds a passenger configuration previously omitted and clarifies nonmetallic barrier/shield sleeving and extruded channel requirements not accounted for in the previous release. Revision 2 incorporates the changes given in Information Notice MD11-28-126 IN 02, MD11-28-126 IN 03 and MD11-28-126 IN 04 and corrects the no-work condition given in Information Notice MD11-28-126 IN 05 and MD11-28-126 IN 06 and are included in this revision. Revision 3 was sent to incorporate engineering released subsequent to Revision 2 of this service bulletin, which adds sleeving and extruded channel requirements to formerly Group 1 airplanes with wire assembly run AES9601 - ENR. Revision 4 is sent to incorporate engineering released subsequent to Revision 3 of this service bulletin, which adds sleeving clamping and extruded channel requirements to formerly Group 2 airplanes with wire assembly run AES9501 - ENL and AES9601 - ENR. D. Description Group 1-2, Configuration 1; Group 3-4; Group 5, Configuration 1; Group 6: This service bulletin gives instructions to do as follows: 1. Does a General Visual Inspection of the wires bundles to determine if wires touch the upper surface of the center upper auxiliary fuel tank and marking locations as necessary. 2. Does a Detailed Inspection of the wires routed above the center upper auxiliary fuel tank for splices and damage (such as chafing, arcing and broken insulation) to wire bundles and does corrective action if necessary. 3. Does a Detailed Inspection of the upper surface of the center upper auxiliary fuel tank for damage to the fuel barrier seal and damage to the fuel tank and does corrective action as necessary. 4. Installs a nonmetallic barrier/shield sleeving to the wire harnesses, new clamps, new attaching hardware, and a new extruded channel, to raise the wire harnesses off the upper surface of the center upper auxiliary fuel tank. Group 1, Configuration 2: This service bulletin gives instructions to do as follows: 1. A Detailed Inspection (DI) of wire bundles for splices, damage and fuel tank fuel barrier seal damage on the center upper auxiliary fuel tank and corrects as necessary. Also installs nonmetallic barrier/shield sleeving, extruded channels and replaces clamps in the locations that follow: a. Passenger Configuration - From Y=1238.950 to 1256.000, Between X=81.00 to X=106.00 b. Passenger Configuration - From Y=1238.950 to 1256.800, Between X= -81.00 to X= -106.00 c. Passenger or Freighter - From Y=1238.950 to 1381.000, Between X=60.00 to X=70.00. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 14 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 15 Group 2, Configuration 2: This service bulletin gives instructions to do as follows: 1. A Detailed Inspection (DI) of wire bundles for splices, damage and fuel tank fuel barrier seal damage on the center upper auxiliary fuel tank and corrects as necessary. Also installs nonmetallic barrier/shield sleeving, extruded channels and replaces clamps in the locations that follow: a. Passenger Configuration - From Y=1238.950 to 1275.250, Between X=81.00 to X=106.00 b. Passenger Configuration - From Y=1238.950 to 1275.250, Between X= -81.00 to X= -106.00. Group 5, Configuration 2: This service bulletin gives instructions to do as follows: 1. A Detailed Inspection (DI) of wire assembly run AES9601 - ENR for splices, damage and fuel tank fuel barrier seal damage on the center upper auxiliary fuel tank and corrects as necessary. Also installs nonmetallic barrier/shield sleeving, extruded channels and replaces clamps. Revision 4 - No More work is necessary on airplane(s) changed in accordance with Revision 3 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1-3: Affected Maintenance Zones ZoneModel 131, 141, 142MD-11, MD-11F Group 4: Affected Maintenance Zones ZoneModel 131, 141, 142MD-11 Group 5-6: Affected Maintenance Zones ZoneModel 131, 141, 142MD-11F E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16 is related to this service bulletin. Boeing recommends that the inspection/change given in this service bulletin be done within 60 months after the effective date of Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 15 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 16 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. In addition, the Manager of the FAA Los Angeles 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 (g), (g1), (g2), (g3), (g4), (g5) and (h) of Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16. All provisions of Federal Aviation Administration (FAA) Airworthiness Directive 2009-26-16 that are not specifically referenced in the above statement remain fully applicable and must be complied with. 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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. This service bulletin assumes that the area above the center upper auxiliary fuel tank is open and access is available to all the floor beams for maintenance. Group 1, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask 17.034.02Figures 1 and 4 8.517.02Inspect 21.063.03Figures 2 and 5 20.561.53Figures 3 and 6 67.0175.5TOTAL FOR EACH AIRPLANE BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 16 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 17 Group 1, Configuration 2: Elapsed HoursTask HoursNumber of PersonsTask 2.02.01Figure 19 7.07.01Figure 21 9.09.0TOTAL FOR EACH AIRPLANE Group 2, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask 16.533.02Figures 7 and 10 8.517.02Inspect 21.063.03Figures 8 and 11 20.561.53Figures 9 and 12 66.5174.5TOTAL FOR EACH AIRPLANE Group 2, Configuration 2: Elapsed HoursTask HoursNumber of PersonsTask 1.51.51Figure 20 4.54.51Figure 22 6.06.0TOTAL FOR EACH AIRPLANE Group 3: Elapsed HoursTask HoursNumber of PersonsTask 17.034.02Figures 4 and 13 8.517.02Inspect 24.072.03Figures 5 and 14 24.072.03Figures 6 and 15 73.5195.0TOTAL FOR EACH AIRPLANE Group 4: Elapsed HoursTask HoursNumber of PersonsTask 16.533.02Figures 10 and 16 8.517.02Inspect 24.072.03Figures 11 and 17 24.072.03Figures 12 and 18 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 17 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 18 Group 4: Elapsed HoursTask HoursNumber of PersonsTask 73.0194.0TOTAL FOR EACH AIRPLANE Group 5, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask 18.036.02Figures 23 and 26 10.521.02Inspect 24.072.03Figures 24 and 27 23.570.53Figures 25 and 28 76.0175.5TOTAL FOR EACH AIRPLANE Group 5, Configuration 2: Elapsed HoursTask HoursNumber of PersonsTask 1.01.01Figure 29 4.04.01Figure 30 4.04.01Figure 31 9.09.0TOTAL FOR EACH AIRPLANE Group 6: Elapsed HoursTask HoursNumber of PersonsTask 17.535.02Figures 32 and 35 9.018.02Inspect 22.066.03Figures 33 and 36 21.564.53Figures 34 and 37 70.0183.5TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Group 1: Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Sta- tion (Inches) Airplane + 40899.3+ 34.3+ 1192.4MD-11 and MD-11F BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 18 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 19 Group 2: Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Sta- tion (Inches) Airplane + 39571.8+ 30.3+ 1306.0MD-11 and MD-11F Group 3: Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Sta- tion (Inches) Airplane + 42362.2+ 32.5+ 1303.7MD-11 and MD-11F Group 4: Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Sta- tion (Inches) Airplane + 39994.1+ 33.6+ 1190.3MD-11 Group 5: Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Sta- tion (Inches) Airplane + 42148.0+ 35.3+ 1296.9MD-11 and MD-11F Group 6: Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Sta- tion (Inches) Airplane + 40756.6+ 31.2+ 1306.3MD-11F I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Structural Repair Manual (SRM) 51. b. MD-11-1F Structural Repair Manual (SRM) 51-42-03. c. MD-11-1P Structural Repair Manual (SRM) 51-42-03. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 19 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 20 d. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-06, 20-00-13, 20-10-01, 20-10-02, 20-10-03, and 20-10-10. e. MD-11 Special Compliance Item (SCI), Critical Design Configuration Control Limitation (CDCCL), 20-1, 20-5, 20-6, and 20-13. f. FAA Airworthiness Directive (AD) 2009-26-16. 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: ChangeTitleDocument Number MWire Protection - Above Upper and Forward Auxiliary Fuel Tank SR11280054 AEO NWire Protection - Above Upper and Forward Auxiliary Fuel Tank SR11280054 This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: 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 does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 20 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### 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. 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 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 Revi- sion 4 date of this Service Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bulletin (Calendar Days) NameKit Number $18,139.00120Service KitSB11280126-11 12,268.00120Service KitSB11280126-13 18,426.00120Service KitSB11280126-7 12,544.00120Service KitSB11280126-9 1,835.00120Supplemental KitSB11280126-17 1,622.00120Supplemental KitSB11280126-21 10,501.00120Service KitSB11280126-23 1,059.00120Supplemental KitSB11280126-25 17,327.00120Service KitSB11280126-27 NotesUnit Price as of the Revi- sion 4 date of this Service Bulletin (US Dollars ROLT as of the Revision 4 date of this Service Bul- letin (Calendar Days) NameKit Number (a)$1,964.00120Supplemental KitSB11280126-15 (b)1,114.00120Supplemental KitSB11280126-19 (c)1,902.00120Supplemental KitSB11280126-29 (a) Applicable to Group 1 operators who have SB11280126-3 Service Kit(s) in stock and have not accomplished the prior issue service bulletin. (b) Applicable to Group 2 operators who have SB11280126-5 Service Kit(s) in stock and have not accomplished the prior issue service bulletin. (c) Applicable to Group 6 operators who have SB11280126-13 Service Kit(s) in stock and have not accom- plished the prior issue service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 21 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 22 B. Industry Support Information Boeing warranty remedies are not available for the configuration changes and/or repair procedures given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: One Service kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Service Kit is divided into Figure Kits for each installation figure shown in the table below. Figure Kit 986532Top Kit --1111SB11280126-11 11----SB11280126-13 ------SB11280126-23 ------SB11280126-27 --11--SB11280126-7 ------SB11280126-9 Figure Kit 181715141211Top Kit ------SB11280126-11 ----11SB11280126-13 ------SB11280126-23 ------SB11280126-27 --11--SB11280126-7 11--11SB11280126-9 Figure Kit 343328272524Top Kit ------SB11280126-11 ------SB11280126-13 --1111SB11280126-23 11----SB11280126-27 ------SB11280126-7 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 22 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 23 Figure Kit 343328272524Top Kit ------SB11280126-9 Figure Kit 3736Top Kit --SB11280126-11 --SB11280126-13 --SB11280126-23 11SB11280126-27 --SB11280126-7 --SB11280126-9 Group 1, Configuration 1: KIT SB11280126-11 NOTES Existing Part NumberName Figure New Part Number 6532 QTY (a)SCREW6143D0005-3-10 (a)SCREW3193D0005-3-12 (a)SCREW223D0005-3-16 (a)STA-STRAP2322799D0254-1-1-9 NUT1135MS21042L3 WASHER2984NAS1252-10L EXTRUDED CHANNEL 816NMC05118 (a)CLAMP8S7934111-10SA (a)CLAMP12S7934111-1SA (a)CLAMP46S7934111-3SA (a)CLAMP8S7934111-4SA (a)CLAMP138S7934111-5SA (a)CLAMP7S7934111-6SA (a)CLAMP8S7934111-8SA SLEEVE2SR11280054-11 SLEEVE3SR11280054-13 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 23 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 24 Group 1, Configuration 1: KIT SB11280126-11 NOTES Existing Part NumberName Figure New Part Number 6532 QTY SLEEVE1SR11280054-15 SLEEVE11SR11280054-19 SLEEVE11SR11280054-21 SLEEVE12SR11280054-29 SLEEVE48SR11280054-3 SLEEVE23SR11280054-37 SLEEVE411SR11280054-7 SLEEVE47SR11280054-9 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. Group 1, Configuration 2: KIT SB11280126-17 NotesNameQTYNew Part Number (a)SCREW23D0005-3-16 (a)STA-STRAP169D0254-1-1-9 NUT2MS21042L3 WASHER8NAS1252-10L (a)CLAMP6S7934111-3SA SLEEVE5SR11280054-37 SLEEVE1SR11280054-7 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. Group 2, Configuration 1: KIT SB11280126-13 NOTES Existing Part NumberName Figure New Part Number 121198 QTY (a)SCREW33303D0005-3-10 (a)SCREW19363D0005-3-12 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 24 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 25 Group 2, Configuration 1: KIT SB11280126-13 NOTES Existing Part NumberName Figure New Part Number 121198 QTY (a)SCREW113D0005-3-16 (a)STA-STRAP67809D0254-1-1-9 NUT5367MS21042L3 WASHER127172NAS1252-10L EXTRUDED CHANNEL 916NMC05118 (a)CLAMP816S7934111-10SA (a)CLAMP88S7934111-12SA (a)CLAMP168S7934111-18SA (a)CLAMP15S7934111-1SA (a)CLAMP53S7934111-3SA (a)CLAMP24S7934111-4SA (a)CLAMP138S7934111-5SA (a)CLAMP1623S7934111-6SA (a)CLAMP8S7934111-7SA SLEEVE1SR11280054-13 SLEEVE11SR11280054-15 SLEEVE11SR11280054-19 SLEEVE11SR11280054-21 SLEEVE12SR11280054-29 SLEEVE2SR11280054-3 SLEEVE3SR11280054-35 SLEEVE2SR11280054-37 SLEEVE11SR11280054-5 SLEEVE43SR11280054-7 SLEEVE3SR11280054-9 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 25 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 26 Group 2, Configuration 2: KIT SB11280126-21 NotesNameQTYNew Part Number (a)SCREW23D0005-3-16 (a)STA-STRAP149D0254-1-1-9 NUT2MS21042L3 WASHER8NAS1252-10L EXTRUDED CHANNEL1NMC05118 (a)CLAMP3S7934111-1SA (a)CLAMP3S7934111-3SA SLEEVE3SR11280054-35 SLEEVE2SR11280054-37 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. Group 3: KIT SB11280126-7 NOTES Existing Part NumberName Figure New Part Number 151465 QTY (a)SCREW53D0005-08-12 (a)SCREW53D0005-08-14 (a)SCREW1463D0005-3-10 (a)SCREW1933D0005-3-12 (a)SCREW223D0005-3-16 (a)STA-STRAP2792329D0254-1-1-9 NUT3511MS21042L3 WASHER8429NAS1252-10L WASHER10NAS1252-8L EXTRUDED CHANNEL 168NMC05118 (a)CLAMP8S7934111-10SA (a)CLAMP12S7934111-1SA (a)CLAMP5S7934111-2SA (a)CLAMP64S7934111-3SA BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 26 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 27 Group 3: KIT SB11280126-7 NOTES Existing Part NumberName Figure New Part Number 151465 QTY (a)CLAMP8S7934111-4SA (a)CLAMP1313S7934111-5SA (a)CLAMP7S7934111-6SA (a)CLAMP8S7934111-8SA SLEEVE2SR11280054-11 SLEEVE3SR11280054-13 SLEEVE1SR11280054-15 SLEEVE11SR11280054-19 SLEEVE11SR11280054-21 SLEEVE1SR11280054-25 SLEEVE31SR11280054-29 SLEEVE84SR11280054-3 SLEEVE32SR11280054-37 SLEEVE114SR11280054-7 SLEEVE74SR11280054-9 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. Group 4: KIT SB11280126-9 NOTES Existing Part NumberName Figure New Part Number 18171211 QTY (a)SCREW53D0005-08-12 (a)SCREW53D0005-08-14 (a)SCREW30333D0005-3-10 (a)SCREW36193D0005-3-12 (a)SCREW113D0005-3-16 (a)STA-STRAP80679D0254-1-1-9 NUT6753MS21042L3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 27 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 28 Group 4: KIT SB11280126-9 NOTES Existing Part NumberName Figure New Part Number 18171211 QTY WASHER172127NAS1252-10L WASHER10NAS1252-8L EXTRUDED CHANNEL 169NMC05118 (a)CLAMP168S7934111-10SA (a)CLAMP88S7934111-12SA (a)CLAMP816S7934111-18SA (a)CLAMP15S7934111-1SA (a)CLAMP5S7934111-2SA (a)CLAMP35S7934111-3SA (a)CLAMP24S7934111-4SA (a)CLAMP1313S7934111-5SA (a)CLAMP2316S7934111-6SA (a)CLAMP8S7934111-7SA SLEEVE1SR11280054-13 SLEEVE11SR11280054-15 SLEEVE11SR11280054-19 SLEEVE11SR11280054-21 SLEEVE1SR11280054-25 SLEEVE31SR11280054-29 SLEEVE2SR11280054-3 SLEEVE3SR11280054-35 SLEEVE2SR11280054-37 SLEEVE11SR11280054-5 SLEEVE34SR11280054-7 SLEEVE3SR11280054-9 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 28 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 29 Group 5, Configuration 1: KIT SB11280126-23 NOTES Existing Part NumberName Figure New Part Number 28272524 QTY (a)SCREW6143D0005-3-10 (a)SCREW11193D0005-3-12 (a)SCREW223D0005-3-16 (a)STA-STRAP2402799D0254-1-1-9 NUT1935MS21042L3 WASHER5384NAS1252-10L EXTRUDED CHANNEL 916NMC05118 (a)CLAMP8S7934111-10SA (a)CLAMP12S7934111-1SA (a)CLAMP3S7934111-3SA (a)CLAMP8S7934111-4SA (a)CLAMP218S7934111-5SA (a)CLAMP7S7934111-6SA (a)CLAMP8S7934111-8SA SLEEVE2SR11280054-11 SLEEVE3SR11280054-13 SLEEVE1SR11280054-15 SLEEVE11SR11280054-19 SLEEVE11SR11280054-21 SLEEVE2SR11280054-29 SLEEVE48SR11280054-3 SLEEVE511SR11280054-7 SLEEVE47SR11280054-9 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 29 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 30 Group 5, Configuration 2: KIT SB11280126-25 NotesNameQTYNew Part Number (a)SCREW83D0005-3-12 (a)STA-STRAP89D0254-1-1-9 NUT8MS21042L3 WASHER24NAS1252-10L EXTRUDED CHANNEL1NMC05118 (a)CLAMP8S7934111-5SA SLEEVE1SR11280054-7 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. Group 6: KIT SB11280126-27 NOTES Existing Part NumberName Figure New Part Number 37363433 QTY (a)SCREW25223D0005-3-10 (a)SCREW27443D0005-3-12 (a)STA-STRAP72889D0254-1-1-9 NUT5266MS21042L3 WASHER131176NAS1252-10L EXTRUDED CHANNEL 916NMC05118 (a)CLAMP816S7934111-10SA (a)CLAMP88S7934111-12SA (a)CLAMP168S7934111-18SA (a)CLAMP12S7934111-1SA (a)CLAMP23S7934111-3SA (a)CLAMP24S7934111-4SA (a)CLAMP2116S7934111-5SA (a)CLAMP1623S7934111-6SA (a)CLAMP8S7934111-7SA SLEEVE1SR11280054-13 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 30 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 31 Group 6: KIT SB11280126-27 NOTES Existing Part NumberName Figure New Part Number 37363433 QTY SLEEVE11SR11280054-15 SLEEVE11SR11280054-19 SLEEVE11SR11280054-21 SLEEVE12SR11280054-29 SLEEVE2SR11280054-3 SLEEVE11SR11280054-5 SLEEVE54SR11280054-7 SLEEVE3SR11280054-9 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. NOTE: The kit that follows is applicable to Group 1 operators who have SB11280126-3 Service Kit(s) in stock and have not accomplished the prior issue service bulletin. Kit SB11280126-15 NotesNameQTYNew Part Number SLEEVE4SR11280054-3 SLEEVE4SR11280054-7 SLEEVE3SR11280054-9 WASHER51NAS1252-10L (a)CLAMP6S7934111-3SA (a)CLAMP3S7934111-5SA (a)SCREW23D0005-3-10 (a)STA STRAP299D0254-1-1-9 (a)SCREW43D0005-3-16 NUT46MS21042L3 SLEEVE5SR11280054-37 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 31 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 32 NOTE: The kit that follows is applicable to Group 2 operators who have SB11280126-5 Service Kit(s) in stock and have not accomplished the prior issue service bulletin. Kit SB11280126-19 NotesNameQTYNew Part Number WASHER127NAS1252-10L EXTRUDED CHANNEL1NMC05118 (a)CLAMP3S7934111-1SA (a)CLAMP3S7934111-3SA (a)CLAMP1S7934111-5SA (a)SCREW13D0005-3-12 (a)SCREW23D0005-3-16 NUT120MS21042L3 SLEEVE3SR11280054-35 SLEEVE2SR11280054-37 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. NOTE: The kit that follows is applicable to Group 6 operators who have SB11280126-13 Service Kit(s) in stock and have not accomplished the prior issue service bulletin. KIT SB11280126-29 NotesNameQTYNew Part Number (a)SCREW163D0005-3-12 (a)STA-STRAP139D0254-1-1-9 WASHER8NAS1252-10L (a)CLAMP16S7934111-5SA SLEEVE2SR11280054-7 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. 2. Parts and Materials Supplied by the Operator: NotesNameQTYPart Number / Specification (a) Only required, if use as optional part for SR11280054-23. Strap, Tiedown, Electrical Components - Self-locking, Plastic -9D0254-1-1-9 (b) 250 yard roll.Tape1SR11280054-23 (DMS 2089) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 32 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 33 NotesNameQTYPart Number / Specification (b) 72 yards.(0.030 x 1.0 Inch) Elastomer Tape1SR11280054-27 (DMS 2186-2) (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. (b) Or approved Equivalent. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: NotesQTYNameExisting Part Number 5CLAMPMS21919WDG1 (a) Keep the part if there are other uses for it. 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: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 33 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 34 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 34 of 244 BOEING SERVICE BULLETIN MD11-28-126 BLANK PAGE ### Page 35 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. 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. CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. For equivalent parts, refer to AEPL, Drawing 7595071. 3. For approved fastener and process material substitutions, refer to MD-11 Structural Repair Manual, Chapter 51. 4. If the length of any fastener specified in this service bulletin does not meet installation standards given in Structural Repair Manual (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. 5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the maximum thickness which may be used under fastener head or nut to counteract accumulation of tolerances. EXCEPTION: When the available fastener length increments are greater than 1/16-inch, a 3/16-inch thick stack of the same type washers may be used. 6. 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 – Torque limits to tighten nuts and bolts are in SRM Chapter 51. 7. This service bulletin assumes that the area above the center upper auxiliary fuel tank is open and access is available to all the floor beams for maintenance. 8. Obey all of the warnings and cautions given in the specified manual sections. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 35 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 36 9. Power Feeder cable splices and all other wire splices located over the center auxiliary fuel tanks between Stations 1218.950 and 1381.000 must be relocated and repaired in accordance with the Work Instructions below. 10. Installation of Barrier/Shield Sleeving will start 2 inches (+/- 1 Inch) away from Station 1218.950 aft side and will end 2 inches (+/- 1 Inch) away from Station 1381.000 forward side. 11. 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. 12. Maximum electrical components and wire assemblies are shown. All electrical components and wire assemblies are not required for all airplanes. 13. Install clamps to ensure a friction fit on wire bundles to prevent movement within the clamp when moderate pressure is applied. It is permissible to use smaller or larger size clamps of the same type in order to meet this requirement. Refer to SWPM 20-10-01 as an accepted procedure. 14. Rotate clamps if necessary to eliminate preloading of support brackets. 15. If a power feeder cable or wire splice is located within the area of the sleeving/tape installations, the following instructions must be applied.  Remove any existing protective covering (sleeving, tape or tubing) from affected wire bundles.  Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure.  Inspect and verify location of any wire splices within affected wire bundles.  Existing and/or new wire splices shall be relocated/located as follows: Wire splices located in an area where protective covering (sleeving, tubing, or tape) is to be installed. (a) Relocate splice at least 6.0 inches beyond end(s) of where pro- tective covering is to be installed. Select wire code 801 (DMS 2426, copper wires) or wire code 98 (DMS 2339, aluminum wires) with appropriate length. Refer to SWPM 20-00-13 as an accepted procedure. Cut and identify new cable. Refer to SWPM 20-00-03 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 36 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 37 Wire splices installed above fuel tank.(b) Relocate spices involving 10 gauge and larger (10, 8, 6, or 4 wire gauges) to locations at least 3 feet or 2 wire supports (whichever is further) from the fuel tank boundaries. Select wire code 801 (DMS 2426, copper wires) or wire code 98 (DMS 2339, aluminum wires) with appropriate length. Refer to SWPM 20-00-13 as an accepted procedure. Cut and identify new cable. Refer to SWPM 20-00-03 as an accepted procedure. 16. Replacement or repair of wiring within 6.0 inches of fuel tanks and fuel pipes must use existing or new wire routing and clipping established in accordance with this service bulletin. 17. Do not use the "Boeing installed wire types" as replacement or repair wiring inside or within 6.0 inches of the fuel tanks or fuel pipes. Use the "Boeing replacement wire types" as replacement or repair wiring inside fuel tanks or within 6.0 inches of fuel pipes. Refer to SWPM 20-00-13 as an accepted procedure. 18. Replacement or repair of wiring used within 6.0 inches of fuel tanks and fuel pipes must use the exact same wire gauge as the type design. 19. Do an electrical continuity test as required after the repair or replacement of wires and replacement of wire splices. 20. 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. 21. 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 access procedures may be required. 22. 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. 23. 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. The removed part can be discarded if a new or serviceable part is installed. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 37 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 38 24. Refer to these SWPM chapters as accepted procedures for applicable operations: SubjectChapter Identification of Electrical Wire - CommercialSWPM 20-00-03 Inspection Instructions for Standard Wiring InstallationsSWPM 20-00-06 Electrical Wire CodesSWPM 20-00-13 Wiring Installation - Maintenance PracticesSWPM 20-10-01 Shielding - Maintenance PracticesSWPM 20-10-02 Wire Splicing - Maintenance PracticesSWPM 20-10-03 Wire Harness and Component - CleaningSWPM 20-10-10 25. It is permissible to select a smaller or larger diameter sleeving of the same type. 26. Installed clamp part numbers may be different than the part numbers listed in the removal Figure(s). 27. 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. 28. 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. 29. 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. B. WORK INSTRUCTIONS Group 1, Configuration 1: 1. Do a General Visual Inspection of wire bundles routed above the center upper auxiliary fuel tank between floor beams at Stations 1238.950 to 1361.000 to determine if wires touch the upper surface of the center upper auxiliary fuel tank. Mark the location(s) where the wire bundle(s) contacts the upper surface of the center upper auxiliary fuel tank as applicable. 2. Remove all wire harness clamps from overwing floor beams and remove all TC92 wire harness mounts from wire bundles in accordance with the Figures listed in the table that follows: FigureArea 1Left Side 4Right Side 3. Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 38 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 39 4. Do a Detailed Inspection of all wire bundles above the center upper auxiliary fuel tank between Stations 1218.950 and 1381.000 for the presence of wire splices and damage (such as chafing, arcing and broken insulation), and do a Detailed Inspection for damage (burn marks) on the upper surface of the center upper auxiliary fuel tank/fuel vapor barrier seal. NOTE: Pay special attention to areas where wires were in contact with the upper surface of the center upper auxiliary fuel tank (marked in Step 1) Condition 1 - No Damage and No Splices Found Proceed to Step 5. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank/Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Replace/repair damaged wire(s). Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 5. Install barrier/shield sleeving P/N SR11280054-(), in accordance with the Figures listed in the table that follows: FigureArea 2Left Side 5Right Side 6. Install new clamps, new attaching hardware and extruded channel in accordance with the Figures listed in the table that follows: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 39 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 40 FigureArea 3Left Side 6Right Side 7. Put the airplane back to a serviceable condition. Group 1, Configuration 2: 1. Gain access to wire bundles routed above the center auxiliary fuel tank. Refer to the table that follows for approximate affected area: Freighter ConfigurationPassenger Configuration From Y=1238.950 to Y=1381.000, Between X=60.00 to X=70.00 From Y=1238.950 to Y=1381.000, Between X=60.00 to X=70.00 From Y=1238.950 to Y=1256.000, Between X=81.00 to X=106.00 From Y=1238.950 to Y=1256.800, Between X= - 81.00 to X= - 106.00 2. Do a Detailed Inspection of wire bundles above the center upper auxiliary fuel tank in accordance with FIGURE 19. Based on inspection findings, do as follows: Condition 1 - No Damage and No Splices Found Proceed to Step 3. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank / Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 40 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 41 a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Repair/replace wire(s) causing damage. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 3. Install barrier/shield sleeving and clamping in accordance with FIGURE 21. 4. Close access. 5. Put the airplane back to a serviceable condition. Group 2, Configuration 1: 1. Do a General Visual Inspection of wire bundles routed above the center upper auxiliary fuel tank between floor beams at Stations 1238.950 to 1361.000 to determine if wires touch the upper surface of the center upper auxiliary fuel tank. Mark the location(s) where the wire bundle(s) contacts the upper surface of the center upper auxiliary fuel tank as applicable. 2. Remove all wire harness clamps from overwing floor beams and remove all TC92 wire harness mounts from wire bundles in accordance with the Figures listed in the table that follows: FigureArea 7Left Side 10Right Side 3. Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure. 4. Do a Detailed Inspection of all wire bundles above the center upper auxiliary fuel tank between Stations 1218.950 and 1381.000 for the presence of wire splices and damage (such as chafing, arcing and broken insulation), and do a Detailed Inspection for damage (burn marks) on the upper surface of the center upper auxiliary fuel tank/fuel vapor barrier seal. NOTE: Pay special attention to areas where wires were in contact with the upper surface of the center upper auxiliary fuel tank (marked in Step 1). Condition 1 - No Damage and No Splices Found Proceed to Step 5. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank/Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 41 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 42 a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Replace/repair damaged wire(s). Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 5. Install barrier/shield sleeving P/N SR11280054-(), in accordance with the Figures listed in the table that follows: FigureArea 8Left Side 11Right Side 6. Install new clamps, new attaching hardware and extruded channel in accordance with the Figures listed in the table that follows: FigureArea 9Left Side 12Right Side 7. Put the airplane back to a serviceable condition. Group 2, Configuration 2: Passenger Configuration "Only" 1. Gain access to wire bundles routed above the center auxiliary fuel tank. Refer to the table that follows for approximate affected area: Passenger Configuration "Only" From Y=1238.950 to Y=1275.250, Between X=81.00 to X=106.00 From Y=1238.950 to Y=1275.250, Between X= -70.00 to X= -106.00 2. Do a Detailed Inspection of wire bundles above the center upper auxiliary fuel tank in accordance with FIGURE 20. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 42 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 43 Based on inspection findings, do as follows: Condition 1 - No Damage and No Splices Found Proceed to Step 3. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank / Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Repair/replace wire(s) causing damage. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 3. Install barrier/shield sleeving and clamping in accordance with FIGURE 22. 4. Close access. 5. Put the airplane back to a serviceable condition. Group 3: 1. Do a General Visual Inspection of wire bundles routed above the center upper auxiliary fuel tank between floor beams at Stations 1039.000 to 1361.000 to determine if wires touch the upper surface of the center upper auxiliary fuel tank. Mark the location(s) where the wire bundle(s) contacts the upper surface of the center upper auxiliary fuel tank as applicable. 2. Remove wire harness clamps from overwing floor beams and remove all TC92 wire harness mounts from wire bundles in accordance with the Figures listed in the table that follows: FigureArea 13Left Side BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 43 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 44 FigureArea 4Right Side 3. Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure. 4. Do a Detailed Inspection of all wire bundles above the center upper auxiliary fuel tank between Stations 1039.000 and 1361.000 for the presence of wire splices and damage (such as chafing, arcing and broken insulation), and do a Detailed Inspection for damage (burn marks) on the upper surface of the center upper auxiliary fuel tank/fuel vapor barrier seal. NOTE: Pay special attention to areas where wires were in contact with the upper surface of the center upper auxiliary fuel tank (marked in Step 1) Condition 1 - No Damage and No Splices Found Proceed to Step 5. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank/Fuel Vapor Barrier Seal. Replace/repair damaged wire(s). Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Replace/repair damaged wire(s). Refer to SWPM 20-10-01and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 5. Install barrier/shield sleeving P/N SR11280054-(), in accordance with the Figures listed in the table that follows: FigureArea 14Left Side BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 44 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 45 FigureArea 5Right Side 6. Install new clamps, new attaching hardware and extruded channel, in accordance with the Figures listed in the table that follows: FigureArea 15Left Side 6Right Side 7. Put the airplane back to a serviceable condition. Group 4: 1. Do a General Visual Inspection of wire bundles routed above the center upper auxiliary fuel tank between floor beams at Stations 1039.000 to 1361.000 to determine if wires touch the upper surface of the center upper auxiliary fuel tank. Mark the location(s) where the wire bundle(s) contacts the upper surface of the center upper auxiliary fuel tank as applicable. 2. Remove all wire harness clamps from overwing floor beams and remove all TC92 wire harness mounts from wire bundles in accordance with the Figures in the table that follows: FigureArea 16Left Side 10Right Side 3. Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure. 4. Do a Detailed Inspection of all wire bundles above the center upper auxiliary fuel tank between Stations 1039.000 and 1361.000 for the presence of wire splices and damage (such as chafing, arcing and broken insulation), and do a Detailed Inspection for damage (burn marks) on the upper surface of the center upper auxiliary fuel tank/fuel vapor barrier seal. NOTE: Pay special attention to areas where wires were in contact with the upper surface of the center upper auxiliary fuel tank (marked in Step 1) Condition 1 - No Damage and No Splices Found Proceed to Step 5. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank/Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 45 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 46 a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Replace/repair damaged wire(s). Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 5. Install barrier/shield sleeving P/N SR11280054-(), in accordance with the Figures listed in the table that follows: FigureArea 17Left Side 11Right Side 6. Install new clamps, new attaching hardware and extruded channel, in accordance with the Figures listed in the table that follows: FigureArea 18Left Side 12Right Side 7. Put the airplane back to a serviceable condition. Group 5, Configuration 1: 1. Do a General Visual Inspection of wire bundles routed above the center upper auxiliary fuel tank between floor beams at Stations 1238.950 to 1361.000 to determine if wires touch the upper surface of the center upper auxiliary fuel tank. Mark the location(s) where the wire bundle(s) contacts the upper surface of the center upper auxiliary fuel tank as applicable. 2. Remove all wire harness clamps from overwing floor beams and remove all TC92 wire harness mounts from wire bundles in accordance with the Figures listed in the table that follows: FigureArea 23Left Side BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 46 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 47 FigureArea 26Right Side 3. Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure. 4. Do a Detailed Inspection of all wire bundles above the center upper auxiliary fuel tank between Stations 1218.950 and 1381.000 for the presence of wire splices and damage (such as chafing, arcing and broken insulation), and do a Detailed Inspection for damage (burn marks) on the upper surface of the center upper auxiliary fuel tank/fuel vapor barrier seal. NOTE: Pay special attention to areas where wires were in contact with the upper surface of the center upper auxiliary fuel tank (marked in Step 1) Condition 1 - No Damage and No Splices Found Proceed to Step 5. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank/Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Replace/repair damaged wire(s). Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 5. Install barrier/shield sleeving P/N SR11280054-(), in accordance with the Figures listed in the table that follows: FigureArea 24Left Side BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 47 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 48 FigureArea 27Right Side 6. Install new clamps, new attaching hardware and extruded channel in accordance with the Figures listed in the table that follows: FigureArea 25Left Side 28Right Side 7. Put the airplane back to a serviceable condition. Group 5, Configuration 2: 1. Gain access to wire bundle AES9601 run letter ENR routed above the center auxiliary fuel tank from station Y=1238.950 to Y=1381.000 approximately X= -46.50. 2. Do a Detailed Inspection of wire bundle AES9601 run ENR above the center upper auxiliary fuel tank in accordance with FIGURE 29. Based on inspection findings, do as follows: Condition 1 - No Damage and No Splices Found Proceed to Step 3. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank / Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03 or MD-11-1P SRM 51-42-03. b. Repair/replace wire(s) causing damage. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 48 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 49 Contact Boeing for repair instructions and do the repair. 3. Install barrier/shield sleeving, clamping and extruded channels in accordance with FIGURE 30 and FIGURE 31. 4. Close access. 5. Put the airplane back to a serviceable condition. Group 6: 1. Do a General Visual Inspection of wire bundles routed above the center upper auxiliary fuel tank between floor beams at Stations 1238.950 to 1361.000 to determine if wires touch the upper surface of the center upper auxiliary fuel tank. Mark the location(s) where the wire bundle(s) contacts the upper surface of the center upper auxiliary fuel tank as applicable. 2. Remove all wire harness clamps from overwing floor beams and remove all TC92 wire harness mounts from wire bundles in accordance with the Figures listed in the table that follows: FigureArea 32Left Side 35Right Side 3. Clean all affected wire bundles. Refer to SWPM 20-10-10 as an accepted procedure. 4. Do a Detailed Inspection of all wire bundles above the center upper auxiliary fuel tank between Stations 1218.950 and 1381.000 for the presence of wire splices and damage (such as chafing, arcing and broken insulation), and do a Detailed Inspection for damage (burn marks) on the upper surface of the center upper auxiliary fuel tank/fuel vapor barrier seal. NOTE: Pay special attention to areas where wires were in contact with the upper surface of the center upper auxiliary fuel tank (marked in Step 1). Condition 1 - No Damage and No Splices Found Proceed to Step 5. Condition 2 - Damage Found on Wire Bundles, No Damage to Upper Surface of Auxiliary Fuel Tank/Fuel Vapor Barrier Seal. Replace/repair damaged wires. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 3 - Splices Found on Power Feeder Wires or Non-Power Feeder Wires a. Remove and relocate each splice to a location at least 3 feet or 2 wire supports, whichever is further, away from fuel tank boundaries. Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. b. Identify new wire. Refer to SWPM 20-00-03 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 49 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 50 Condition 4 - Damage Found on Wire Bundles and Damage Found on Fuel Vapor Barrier Seal of Auxiliary Fuel Tank a. Repair Fuel Vapor Barrier Seal in accordance with MD-11-1F SRM 51-42-03. b. Replace/repair damaged wire(s). Refer to SWPM 20-10-01 and SWPM 20-10-03 as accepted procedures. Condition 5 - Damage Found on Upper Surface of Auxiliary Fuel Tank Contact Boeing for repair instructions and do the repair. 5. Install barrier/shield sleeving P/N SR11280054-(), in accordance with the Figures listed in the table that follows: FigureArea 33Left Side 36Right Side 6. Install new clamps, new attaching hardware and extruded channel in accordance with the Figures listed in the table that follows: FigureArea 34Left Side 37Right Side 7. Put the airplane back to a serviceable condition. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 50 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 51 (OCR) BOEING SERVICE BULLETIN MD11-28-126 This Figure applies only to: Group 1, Configuration 1. STA 1381.000 STA 1361.000 STA 1341.000 STA STA 1305.250 1321.000 STA 1293.750 STA 1275.250 STA B 1256.000 STA B 1238.950 X=17.000* H PASSENGER CONFIGURATION X=81.000 ONLY FIGURE 1: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL (SHEET 1 OF 5) Original Issue: March 03, 2009 Revision 4 November 29, 2011 MD11-28-126 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 244 ### Page 52 (OCR) BOEING SERVICE BULLETIN MD11-28-126 X=75.250 X=30.000 X=17.000 Z=-19.000 - B-B (7 PLACES) C X=75.250 X=60.500 X=30.000 X=17.000 E Z=-19.000 - (16 D-D FIGURE 1: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL (SHEET 2 OF 5) Original Issue: March 03, 2009 Revision 4 November 29, 2011 MD11-28-126 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 244 ### Page 53 (OCR) BOEING SERVICE BULLETIN MD11-28-126 20) E-E (3 PLACES) G-G (24 PASSENGER CONFIGURATION ONLY STA 1256.750 - G (22) 22 STA 1239.000 X=81.000 F-F LOOKING DOWN STA 1361.000_ FIGURE 1: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL (SHEET 3 OF 5) Original Issue: March 03, 2009 Revision 4 November 29, 2011 BOEING PROPRIETARY - MD11-28-126 Copyright © Unpublished Work - See page 1 for details. 53 of 244 ### Page 54 (OCR) BOEING SERVICE BULLETIN MD11-28-126 STA 1381.000 STA 1361.000 1341.000 STA STA 1305.250 1321.000 STA 1293.750 STA 1275.250 STA 1256.000 STA 1238.950 X=17.000 • PASSENGER CONFIGURATION X=81.000 ONLY - MOUNT TYPICAL 2013837 FIGURE 1: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL (SHEET 4 OF 5) Original Issue: March 03, 2009 Revision 4 November 29, 2011 BOEING PROPRIETARY - MD11-28-126 Copyright © Unpublished Work - See page 1 for details. 54 of 244 ### Page 55 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 this figure. More DataQtyIdentificationNameTaskStep EDE - (AGS9201)-S7934111-()CLAMPRemove1 EDC - (AES9103), (ACS9009)-S7934111-()CLAMPRemove2 EDC - (AES9111)-S7934111-()CLAMPRemove3 EBE - (AGS9201)-S7934111-()CLAMPRemove4 EBC - (AES9102), (AES9109)-S7934111-()CLAMPRemove5 EBC - (AES9111)-S7934111-()CLAMPRemove6 EBJ - (AES9111)-S7934111-()CLAMPRemove EBJ - (AES9105)-S7934111-()CLAMPRemove7 EDJ - (AES9111)-S7934111-()CLAMPRemove8 EDJ - (AES9106)-S7934111-()CLAMPRemove9 EAN - (AES9111)-S7934111-()CLAMPRemove10 EAN - (AES9115)-S7934111-()CLAMPRemove11 EAJ - (AES9104)-S7934111-()CLAMPRemove12 EAC - (AES9101)-S7934111-()CLAMPRemove13 EAC - (AES9108), (AES9111)-S7934111-()CLAMPRemove14 EAE - (AGS9201)-S7934111-()CLAMPRemove15 NLL (AGS9121)8MS21919WDG3CLAMPRemove16 NLM (AGS9119)8MS21919WDG6CLAMPRemove17 ENL (AES9501)8NMC1001-2CLAMPRemove18 HEE (AGS9124)8MS25281R4CLAMPRemove19 EDC (AES9110)7MS25281R6CLAMPRemove20 EBC (AES9109)7MS25281R1CLAMPRemove21 EAC (AES9108)3MS25281R2CLAMPRemove22 EDC (AES9103)5MS25281R1CLAMPRemove23 EKW (AES9110)1MS25281R2CLAMPRemove24 EPA (AES9109)1MS25281R2CLAMPRemove25 EGY (AES9108)1MS25281R2CLAMPRemove26 -TC92MountRemove27 FIGURE 1: CLAMPS AT FLOOR BEAMS, LEFT SIDE - REMOVAL (SHEET 5 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4 November 29, 2011 55 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 56 (OCR) BOEING SERVICE BULLETIN MD11-28-126 This Figure applies only to: Group 1, Configuration 1. D STA 1381.000 STA 1361.000 STA 1341.000 STA STA 1305.250 1321.000 STA 1293.750 STA 1275.250 STA 1256.000 STA 1238.950 X=17.000 (23 PASSENGER CONFIGURATION ONLY END SLEEVING 2.0/3.0 INCHES PAST CLAMP 2013839 FIGURE 2: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION (SHEET 1 OF 4) Original Issue: March 03, 2009 Revision 4 November 29, 2011 MD11-28-126 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 244 ### Page 57 (OCR) BOEING SERVICE BULLETIN MD11-28-126 TIE TAPE (27- 0.50 (MAX.) 6.00 (MAX.) TYPICAL SLEEVING INSTALLATION 29) TIE TAPE TIE TAPE (27) 0.50 28) TAPE (MAX.) 6.00 (MAX.) C 2013840 FIGURE 2: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION (SHEET 2 OF 4) Original Issue: March 03, 2009 Revision 4 November 29, 2011 MD11-28-126 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 244 ### Page 58 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 this figure. More DataQtyIdentificationNameTaskStep (a) EDE - (AGS9201)1SR11280054-9SLEEVEInstall (New)1 (a) EDC - (AES9110, AES9103) 1SR11280054-15SLEEVEInstall (New)2 (a) EDC - (AES9111)1SR11280054-7SLEEVEInstall (New)3 (a) EBE - (AGS9201)1SR11280054-3SLEEVEInstall (New)4 (a) EBC - (AES9102, AES9109) 1SR11280054-7SLEEVEInstall (New)5 (a) EBC - (AES9111)1SR11280054-7SLEEVEInstall (New)6 (a) EBJ - (AES9111)1SR11280054-7SLEEVEInstall (New) (a) EBJ - (AES9105)1SR11280054-9SLEEVEInstall (New)7 (a) EDJ - (AES9111)1SR11280054-7SLEEVEInstall (New)8 (a) EDJ - (AES9106)1SR11280054-3SLEEVEInstall (New)9 (a) EAN - (AES9111)1SR11280054-3SLEEVEInstall (New)10 (a) EAN - (AES9115)1SR11280054-11SLEEVEInstall (New)11 (a) EAJ - (AES9104)1SR11280054-9SLEEVEInstall (New)12 (a) EAC - (AES9101)1SR11280054-3SLEEVEInstall (New)13 (a) EAC - (AES9108, AES9111) 1SR11280054-7SLEEVEInstall (New)14 (a) EAE - (AGS9201)1SR11280054-7SLEEVEInstall (New)15 (a) NLL - (AGS9121)1SR11280054-9SLEEVEInstall (New)16 (a) NLM - (AGS9119)1SR11280054-7SLEEVEInstall (New)17 (a) ENL - (AES9501)1SR11280054-7SLEEVEInstall (New)18 (a) HEE - (AGS9124)1SR11280054-7SLEEVEInstall (New)19 EDC - (AES9110)1SR11280054-19SLEEVEInstall (New)20 EBC - (AES9109)1SR11280054-29SLEEVEInstall (New)21 EAC - (AES9108)1SR11280054-21SLEEVEInstall (New)22 EDC - (AES9103)1SR11280054-29SLEEVEInstall (New)23 EKW - (AES9110)1SR11280054-37SLEEVEInstall (New)24 EPA - (AES9109)1SR11280054-37SLEEVEInstall (New)25 EGY - (AES9108)1SR11280054-37SLEEVEInstall (New)26 FIGURE 2: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION (SHEET 3 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4 November 29, 2011 58 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 59 More DataQtyIdentificationNameTaskStep Part number 9D0254-1-1-9 optional. -SR11280054-23TIE TAPEInstall (New)27 -SR11280054-27TAPEInstall (New)28 Part number 9D0254-1-1-9 optional. -SR11280054-23TIE TAPEInstall (New)29 (a) It is permissible to select smaller or larger sized sleeving of the same type. Refer to extra parts table below for additional sleeving availability. More DataQtyIdentificationName 1SR11280054-11SLEEVE 4SR11280054-3SLEEVE 1SR11280054-7SLEEVE 3SR11280054-9SLEEVE FIGURE 2: BARRIER/SHIELD SLEEVING, LEFT SIDE - INSTALLATION (SHEET 4 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2009 MD11-28-126Revision 4 November 29, 2011 59 of 244 BOEING SERVICE BULLETIN MD11-28-126 ### Page 60 (OCR) BOEING SERVICE BULLETIN MD11-28-126 This Figure applies only to: Group 1, Configuration 1. STA 1381.000 STA 1361.000 STA 1341.000 STA STA 1305.250 1321.000 STA 1293.750 STA 1275.250 STA 1256.000 STA 1238.950 X=17.000 H • PASSENGER CONFIGURATION ONLY X=81.000 2013995 FIGURE 3: CLAMPS AND EXTRUDED CHANNEL, LEFT SIDE - INSTALLATION (SHEET 1 OF 7) Original Issue: March 03, 2009 Revision 4 November 29, 2011 MD11-28-126 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 244 The text continues at https://openairdocs.org/service-documents/boeing/md11-28-126/file/9b8903cd7303.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. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.