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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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.
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Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 1 of 244
2.0
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BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary7
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
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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
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Original Issue: March 03, 2009 MD11-28-126Revision 4: November 29, 2011 4 of 244 BOEING SERVICE BULLETIN MD11-28-126
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.
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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:
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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.
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MANPOWER Refer to Paragraph 1.G., Manpower .
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability .
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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
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BLANK PAGE
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
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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 Number 2447 - 449 2451 - 464 2466 - 487 6488 2489 6491 2492 - 517 2519 - 531 4532 2533 - 543 4544 2545 - 552 2554 - 564 6565 2566 6567
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