### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Number: MD11-28A124**  Original Issue: June 17, 2009 Revision 1: August 24, 2010 ATA System: 2820 **SUBJECT:** FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly Installation Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 1 of 36 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 2 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 18 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 21 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 26 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION AND WIRE SUPPORT - INSPECTION/CHANGE [Group 1, Configuration 2]. . . . . . . . 33 FIGURE 2: WIRE SUPPORT - CHANGE [Group 2, Configuration 2]. . . . . . . . . . . . . . . . . . . 35

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 3 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 4 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Revision Transmittal Sheet**  **Number: MD11-28A124** Original Issue: June 17, 2009 Revision 1: August 24, 2010 ATA System: 2820 **SUBJECT:** FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly Installation This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2009-NM-252-AD, is related to this service bulletin. More work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The more work does a General Visual Inspection (GVI) of the self-adhering, high-temperature electrical insulation tape for correct installation and changes wire supports. **REASON FOR REVISION** This revision is sent to incorporate engineering released subsequent to the original issue of this service bulletin which clarifies the work instructions, does a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation and changes wire supports. This revision incorporates the changes given in Information Notice MD11-28A124 IN 01 and corrects the no-work condition given in Information Notice MD11-28A124 IN 02 and is included in this revision. An additional 3.3 task hours for Group 1 Configuration 2 and 3.0 task hours for Group 2 Configuration 2 are required. These sections were changed: 1. In Paragraph 1.D., Description, added Group/Configuration data. 2. In Paragraph 1.E., Compliance, added NPRM information. 3. In Paragraph 1.G., Manpower, added Group/Configuration data. 4. In Paragraph 1.H., Weight and Balance Changes, changed information. 5. In Paragraph 1.J.1.e., Existing Data, added NPRM information. 6. In Paragraph 1.J.2.a., Drawings, changed drawing revision level.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 5 of 367. In Paragraph 2.A., Materials - Price and Availability, changed kits information. 8. In Paragraph 2.B., Industry Support Information, changed information. 9. In Paragraph 2.C.1., Kits/Parts, changed kits information and added Group/Configuration data. 10. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added Group/Configuration data. 11. In Paragraph 3.A., General Information, changed notes. 12. In Paragraph 3.B., Work Instructions, added Group/Configurations data. 13. Added Figures 1 and 2. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. **REVISION HISTORY** June 17, 2009 Original Issue: August 24, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 6 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**

### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Summary**  **Number: MD11-28A124** Original Issue: June 17, 2009 Revision 1: August 24, 2010 ATA System: 2820 **SUBJECT:** FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** An investigation by Boeing has determined that tail tank fuel system wire assemblies routed together and in close proximity to the upper surface of the tail tank are a potential ignition source should wire damage occur. Also, during normal maintenance, wire damage may be caused when maintenance personnel working in the tail tank area inadvertently step on the wire assemblies causing contact with the tail tank upper surface and/or where the wire assemblies transition down the front spar horizontal stabilizer. Inspecting the tail tank wiring for damage and repair/replacing if required and providing protection of the wires, will minimize the possibility of wire damage in the tail tank area. If not corrected, in a case of wire damage, there is a possibility of burn-through on the upper surface of the tail tank that could potentially result in an explosion. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". Airworthiness Limitation Instruction (ALI) 20-2 from Report MDC-02K1003 affects airplane maintenance documents. **ACTION** Refer to Paragraph 1.D., Description. **EFFECTIVITY** MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 7 of 36**COMPLIANCE** Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2009-NM-252-AD, is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the inspection/change given in this service bulletin be done within 5 years after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection, configuration changes and/or repair procedures given in this service bulletin. **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: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 8 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 9 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 10 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Number: MD11-28A124**  Original Issue: June 17, 2009 Revision 1: August 24, 2010 ATA System: 2820 **SUBJECT:** FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below.
**DESCRIPTION CONFIGURATION**  **GROUP** Applicable to airplanes that require additional wire separation and is affected by Service Rework Drawing/Configuration SR11280052-7001. - 1

Applicable to operators who have not accomplished the original issue service bulletin. 1
Applicable to operators who have accomplished the original issue service bulletin and have more work. 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 11 of 36**DESCRIPTION CONFIGURATION**  **GROUP** Applicable to airplanes that do not require additional wire separation and is affected by Service Rework Drawing/Configuration SR11280052-7003. - 2

Applicable to operators who have not accomplished the original issue service bulletin. 1
Applicable to operators who have accomplished the original issue service bulletin and have more work. 2

Airplane Models: MD-11, MD-11F **Group Fuselage Num-**  **ber** 2 447 - 449 2 451 - 460 1 461 - 464 1 466 - 489 1 491 - 517 1 519 - 552 1 554 - 646 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** An investigation by Boeing has determined that tail tank fuel system wire assemblies routed together and in close proximity to the upper surface of the tail tank are a potential ignition source should wire damage occur. Also, during normal maintenance, wire damage may be caused when maintenance personnel working in the tail tank area inadvertently step on the wire assemblies causing contact with the tail tank upper surface and/or where the wire assemblies transition down the front spar horizontal stabilizer. Inspecting the tail tank wiring for damage and repair/replacing if required and providing protection of the wires, will minimize the possibility of wire damage in the tail tank area. If not corrected, in a case of wire damage, there is a possibility of burn-through on the upper surface of the tail tank that could potentially result in an explosion.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 12 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". Airworthiness Limitation Instruction (ALI) 20-2 from Report MDC-02K1003 affects airplane maintenance documents. Revision 1 is sent to incorporate engineering released subsequent to the original issue of this service bulletin which clarifies the work instructions, does a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation and changes wire supports. Revision 1 incorporates the changes given in Information Notice MD11-28A124 IN 01 and corrects the no-work condition given in Information Notice MD11-28A124 IN 02 and is included in this revision. An additional 3.3 task hours for Group 1 Configuration 2 and 3.0 task hours for Group 2 Configuration 2 are required. **D. Description Group 1, Configuration 1:**  1. This service bulletin does a General Visual Inspection (GVI) of the tail tank fuel system wire assembly installation for damage and does as follows:
Condition 1: No Wire Damage Found
a. Separates wire assemblies and individually wraps each with self-adhering, high-temperature electrical insulation tape. b. Installs wire assembly support brackets/routes wire assemblies. c. Installs a wire protection bracket.
Condition 2: Wire Damage Found
a. Repairs or replaces wires. b. Separates wire assemblies and individually wraps each with self-adhering, high-temperature electrical insulation tape. c. Installs wire assembly support brackets/routes wire assemblies. d. Installs a wire protection bracket. 2. Puts the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 13 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 2, Configuration 1:**  1. This service bulletin does a GVI of the tail tank fuel system wire assembly installation for damage and does as follows:
Condition 1: No Wire Damage Found
a. Installs wire assembly support brackets/routes wire assemblies. b. Installs a wire protection bracket.
Condition 2: Wire Damage Found a. Repairs or replaces wires. b. Installs wire assembly support brackets/routes wire assemblies. c. Installs a wire protection bracket. 2. Puts the airplane back to a serviceable condition.
**Group 1, Configuration 2:** 1. Does a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation, and changes wire supports. 2. Puts the airplane back to a serviceable condition.
**Group 2, Configuration 2:** 1. Changes wire supports. 2. Puts the airplane back to a serviceable condition.
Revision 1 - More work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The more work does a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation and changes wire supports. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 311 MD-11, MD-11F

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 14 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT E. Compliance**  Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2009-NM-252-AD, is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the inspection/change given in this service bulletin be done within 5 years after the original issue date of this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. **Group 1, Configuration 1: Elapsed Hours**  **Task Hours Number of**  **Persons Task**  **Condition 2 Condition 1**  **Condition 2 Condition 1**  0.5 0.5 1.0 1.0 2 Open Access 2.0 2.0 2.0 2.0 1 Removal 0.5 0.5 0.5 0.5 1 Inspection 6.0 6.0 1 Repair 8.0 8.0 16.0 16.0 2 Change

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 15 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1, Configuration 1:**  **Elapsed Hours Task Hours**  **Number of Persons**  **Task Condition 2**  **Condition 1 Condition 2**  **Condition 1** 0.5 0.5 1.0 1.0 2 Close Access 17.5 11.5 28.0 20.5 TOTAL FOR EACH AIRPLANE
**NOTE: Group 1, Configuration 2:**  **Elapsed Hours**  **Task Hours Number of**  **Persons Task** 

0.5 1.0 2 Open Access 0.3 0.3 1 Inspect 1.0 1.0 1 Figure 1 0.5 1.0 2 Close Access 2.3 3.3 TOTAL FOR EACH AIRPLANE
**NOTE:** Maximum total task hours and elapsed hours are given per airplane. Actual task hours and elapsed hours are contingent upon inspection findings and are to be estimated by the operator. **Group 2, Configuration 1: Elapsed Hours**  **Task Hours Number of**  **Persons Task**  **Condition 2 Condition 1**  **Condition 2 Condition 1**  0.5 0.5 1.0 1.0 2 Open Access 2.0 2.0 2.0 2.0 1 Removal 0.5 0.5 0.5 0.5 1 Inspection 6.0 6.0 1 Repair 8.0 5.0 16.0 10.0 2 Change 0.5 0.5 1.0 1.0 2 Close Access 16.0 8.5 22.0 14.5 TOTAL FOR EACH AIRPLANE **Group 2, Configuration 2: Elapsed**  **Hours Task Hours**  **Number of Persons**  **Task**

0.5 1.0 2 Open Access 1.0 1.0 1 Figure 2 0.5 1.0 2 Close Access

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 16 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 2, Configuration 2:**  **Elapsed Hours**  **Task Hours Number of**  **Persons Task** 

2.0 3.0 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1:**  **Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Increase Approximate Station**  **(Inches) Airplane** 

MD-11 and MD-11F +19,328.4 +9.0 2147.6 Condition 1 +29,725.2 +13.8 2154.0 Condition 2 **Group 2: Moment Change**  **(MEW) IN.-LBS Mfr's Empty**  **Weight (MEW) LBS Increase** **Approximate Sta tion (Inches)**  **Airplane**

MD-11 and MD-11F +18,250.4 +8.5 2147.1 Condition 1 +28,432.8 +13.2 2154.0 Condition 2
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Boeing Service Bulletin MD11-28-102. b. MD-11 Structural Repair Manual (SRM) 51. c. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-10-01, 20-10-10, 20-10-17, and 20-50-01. d. MD-11 Aircraft Maintenance Manual (AMM) 06-33-00, 24-40-00, 27-40-00, and 29-00-00. e. FAA Notice of Proposed Rule Making (NPRM) 2009-NM-252-AD.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 17 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**2. Data supplied with this Service Bulletin: No data is supplied with this service bulletin. To obtain the data necessary to support this service bulletin submit a data request to: Data and Services Management MS D800-0019 3855 Lakewood Boulevard Long Beach, California 90846 Phone: (562) 593-6996 Fax: (562) 593-2001 E-mail: dse.boecom@boeing.com a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- H DWG Alert - Tail Fuel Tank Wire Installation SR11280052 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  55-11 Illustrated Parts Catalog MDC-02K1003 (ALI 20-2) Special Compliance Item Report

2. Damage Tolerance Based Structural Inspections: Boeing has evaluated 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** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 18 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT 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 Revision 01** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 01 date**

**of this Service Bulletin (Calendar**  **Days) Name**  **Kit Number**

$11,829.00 90 Service Kit SA11280124-7 9.00 30 Supplemental Kit SA11280124-9 **B. Industry Support Information** Boeing warranty remedies are not available for the inspection, 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 top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. **Group 1-2, Configuration 1:**
**Kit SA11280124 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -7**  (a) SCREW 1 3D0005-3-12 (a) SCREW 1 3D0005-3-22 (a) SCREW 1 3D0005-3-30

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 19 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1-2, Configuration 1:** 
**Kit SA11280124 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -7**  (a) SCREW 9 3D0005-3-8 (a) NUT-CLIP 9 3D0039-14 (a) NUT-CLIP 3 3D0039-16 BRACKET 6 9D0230-3L080824 BRACKET 3 9D0230-3L080832 (a) STRAP 21 9D0254-1-1-9 BRACKET 1 AAP8000-539 (b) ALN8600-551 BRACKET 1 AAP8004-1103 PIN 2 HL326-5-4 NUT 2 MS21042L08 NUT 3 MS21042L3 CLAMP 1 MS21919WDG10 SCREW 1 NAS1096-3-12 SCREW 6 NAS1096-3-10 SCREW 1 NAS1096-3-8 WASHER 27 NAS1252-10L WASHER 2 NAS1252-416H WASHER 2 NAS1252-8L SCREW 2 NAS1801-4-11 (a) SPACER 1 NAS43DD3-16FC (a) SPACER 1 NAS43DD3-48FC (a) SPACER 1 NAS43DD3-72FC (a) CLAMP 6 S7934111-10SA (a) CLAMP 5 S7934111-14SA (a) CLAMP 1 S7934111-24SA (a) CLAMP 3 S7934111-4SA (a) CLAMP 7 S7934111-6SA (a) CLAMP 1 S7934111-7SA BRACKET 1 SR11280052-13

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 20 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1-2, Configuration 1:** 
**Kit SA11280124 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -7**  EXTRUDED CHANNEL 8 SR11280052-17
BRACKET 1 SR11280052-29 BRACKET 1 SR11280052-31 BRACKET 1 SR11280052-33 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. (b) Discard the existing part. **Group 1-2, Configuration 2: Supplemental Kit SA11280124**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-9** (a) CLAMP 2 S7934111-4SA SCREW 2 NAS1801-4-11 (a) Or approved Equivalent. Refer to AEPL, Drawing 7595071. 2. Parts and Materials Supplied by the Operator: **Group 1, Configuration 1: Condition 1: No Wire Damage Found** 
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) (e) TAPE (ELASTOMER) 80 FT x 1.0 Inch Width SR11280052-11 (DMS 2186 Type 2) or T2/600T Series (b) (e) COATING CHEMICAL FILM, LIQUID As Required Alodine 1500 (DPM 5089-1) (c) PRIMER, FR 4 Oz. 515X347 Base with 910X527 Catalyst (DMS 1786) or Equivalent

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 21 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1, Configuration 1:**  **Condition 1: No Wire Damage Found**
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (d) ENAMEL, HIGH SOLIDS EPOXY TOP- COAT, GLOSS WHITE 1 Oz. 446-21-7507 BaseDN7507 White with X530 Activator (DMS 2433-2C) or Equivalent (a) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear, Delaware 19701, CAGE 52869(b) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, California 95037, CAGE 1KQX9 (c) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street, Mojave, California 93501-7048, CAGE 85570 (d) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor City, California 90710-2102, CAGE 1KSU0 (e) Or approved Equivalent. **Group 1, Configuration 1: Condition 2: Wire Damage Found** 
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) (i) TAPE (ELASTOMER) 80 FT x 1.0 Inch Width SR11280052-11 (DMS 2186 Type 2) or T2/600T Series (b) SLEEVE (BRAIDED, EXPANDABLEARAMID FIBER/PPS, MONOFILAMENT, PREFORMED WRAPAROUND) 10 FT x 1.187 I.D. SR11280052-21 (DMS 2379 Type 5, Class 4) or 5678103007S (a) (i) TAPE (ELASTOMER) 36 YARDS x 1.0 Inch Width SR11280052-23 (DMS 2186 Type 1) or T3/SA Series (c) TAPE (POLYURETHANE NUMBER 8672, TRANSPARENT) 36 YARDS x 1.0 Inch Width SR11280052-25 (DPM 5777-6) (d) (i) COATING CHEMICAL FILM, LIQUID As Required Alodine 1500 (DPM 5089-1)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 22 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1, Configuration 1:**  **Condition 2: Wire Damage Found**
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (g) PRIMER, FR 4 Oz. 515X347 Base with 910X527 Catalyst (DMS 1786) or Equivalent (h) ENAMEL, HIGH SOLIDS EPOXY TOP- COAT, GLOSS WHITE 1 Oz. 446-21-7507 BaseDN7507 White with X530 Activator (DMS 2433-2C) or Equivalent (e) SPLIT FERRULE 5 M85049/93-10 (f) CLAMP, LOOP 10 9D0180-1 or A10086 (a) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear, Delaware 19701, CAGE 52869 (b) Can be purchased from: Federal Mogul Corporation, 1277 Joe Battle Boulevard, El Paso, Texas 79936-0966, CAGE 81851 (c) Can be purchased from: 3M Company, 3M Center, Saint Paul, Minnesota 55144-1000, CAGE 0KHE3 (d) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, California 95037, CAGE 1KQX9 (e) Can be purchased from: Glenair, Incorporated, 1211 Air Way, Glendale, California 91201- 2405, CAGE 06324 (f) Can be purchased from: Band-It-Idex, Incorporated, 4799 Dahlia Street, Denver, Colorado 80216-3222, CAGE 3BBM2(g) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street, Mojave, California 93501-7048, CAGE 85570 (h) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor City, California 90710-2102, CAGE 1KSU0 (i) Or approved Equivalent.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 23 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 2, Configuration 1:**  **Condition 1: No Wire Damage Found**
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) (d) COATING CHEMICAL FILM, LIQUID As Required Alodine 1500 (DPM 5089-1) (b) PRIMER, FR 4 Oz. 515X347 Base with 910X527 Catalyst (DMS 1786) or Equivalent (c) ENAMEL, HIGH SOLIDS EPOXY TOP- COAT, GLOSS WHITE 1 Oz. 446-21-7507 BaseDN7507 White with X530 Activator (DMS 2433-2C) or Equivalent(a) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, California 95037, CAGE 1KQX9 (b) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street, Mojave, California 93501-7048, CAGE 85570 (c) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor City, California 90710-2102, CAGE 1KSU0 (d) Or approved Equivalent. **Group 2, Configuration 1: Condition 2: Wire Damage Found** 
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) SLEEVE (BRAIDED, EXPANDABLEARAMID FIBER/PPS, MONOFILAMENT, PREFORMED WRAPAROUND) 10 FT x 1.187 I.D. SR11280052-21 (DMS 2379 Type 5, Class 4) or 5678103007S (b) (i) TAPE (ELASTOMER) 36 YARDS x 1.0 Inch Width SR11280052-23 (DMS 2186 Type 1) or T3/SA Series (c) TAPE (POLYURETHANE NUMBER 8672, TRANSPARENT) 36 YARDS x 1.0 Inch Width SR11280052-25 (DPM 5777-6) (d) (i) COATING CHEMICAL FILM, LIQUID As Required Alodine 1500 (DPM 5089-1)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 24 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 2, Configuration 1:**  **Condition 2: Wire Damage Found**
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (g) PRIMER, FR 4 Oz. 515X347 Base with 910X527 Catalyst (DMS 1786) or Equivalent (h) ENAMEL, HIGH SOLIDS EPOXY TOP- COAT, GLOSS WHITE 1 Oz. 446-21-7507 BaseDN7507 White with X530 Activator (DMS 2433-2C) or Equivalent (e) SPLIT FERRULE 5 M85049/93-10 (f) CLAMP, LOOP 10 9D0180-1 or A10086 (a) Can be purchased from: Federal Mogul Corporation, 1277 Joe Battle Boulevard, El Paso, Texas 79936-0966, CAGE 81851 (b) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear, Delaware 19701, CAGE 52869 (c) Can be purchased from: 3M Company, 3M Center, Saint Paul, Minnesota 55144-1000, CAGE 0KHE3(d) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, California 95037, CAGE 1KQX9 (e) Can be purchased from: Glenair, Incorporated, 1211 Air Way, Glendale, California 91201- 2405, CAGE 06324 (f) Can be purchased from: Band-It-Idex, Incorporated, 4799 Dahlia Street, Denver, Colorado 80216-3222, CAGE 3BBM2 (g) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street, Mojave, California 93501-7048, CAGE 85570 (h) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor City, California 90710-2102, CAGE 1KSU0 (i) Or approved Equivalent.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 25 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1, Configuration 2:** 
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) (b) (c) TAPE (ELASTOMER) 5 FT x 1.0 Inch Width SR11280052-11 (DMS 2186 Type 2) or T2/600T Series (a) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear, Delaware 19701, CAGE 52869 (b) As required based on inspection findings. (c) Or approved Equivalent. **Group 2, Configuration 2:** None. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 26 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT 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. The instructions identified in Paragraph 3.B., Work Instructions give the recommended sequences of steps. The sequences of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. For equivalent parts, refer to AEPL, Drawing 7595071. 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. Locate/position clamps as required to clear airplane structure/components. 6. 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. 7. Refer to these Standard Wiring Practices Manual (SWPM) Chapters for applicable operations as accepted procedures:
Identification of Electrical Wire - Commercial SWPM 20-00-03 General Maintenance Practices - Electrical SWPM 20-00-09 Electrical Wire Codes SWPM 20-00-13 Wiring Installation - Maintenance Practices SWPM 20-10-01

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 27 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**Wire Harness and Component Cleaning SWPM 20-10-10 Braided Electrical Wire Bundles SWPM 20-10-17 Electrical Bonding - Maintenance Practices SWPM 20-50-01
8. Obey all of the warnings and cautions given in the specified manual sections. 9. A General Visual Inspection (GVI) 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 ensure visual access to all surfaces in the inspection area. This level of inspection is made under normal 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. 10. These work instructions refer to procedures included on 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. 11. Review and understand all general notes of Service Rework Drawing SR11280052, Sheets 3 through 3.18 before starting modification. 12. 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. 13. 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. **B. WORK INSTRUCTIONS Group 1, Configuration 1:**  1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure. 3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted procedure. 5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that follow:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 28 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Refer to:**  **Location Access Door**  MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 6. Remove clamps and keep attaching hardware from wire assemblies in accordance with Service Rework Drawing SR11280052, Sheets 6 and 6.1. 7. Separate AJS9013 and AJS9014 wire assemblies in accordance with Service Rework Drawing SR11280052, Sheet 6. 8. Do a GVI of the AJS9013, AJS9014, AJS9015, and AGS9124 wire assemblies in accordance with Service Rework Drawing SR11280052, Sheet 3.4 and do as follows: Condition 1: No Wire Assembly Damage Found a. Continue at Step 9. Condition 2: Wire Assembly Damage Found a. Repair or replace wire assemblies in accordance with Service Rework Drawing SR11280052, Sheets 3.4 through 3.17. b. Continue at Step 9. 9. Apply self-adhering, high-temperature electrical insulation tape on AJS9013 and AJS9014 wire assemblies in accordance with Service Rework Drawing SR11280052, Sheets 6 and 6.1. 10. Install wire assembly support brackets and route wire assemblies AJS9013 and AJS9014 in accordance with Service Rework Drawing SR11280052, Sheets 6.0, 6.1, 6.2, 7.1, and 7.3. 11. Install extruded channel wire supports in accordance with Service Rework Drawing SR11280052, Sheet 6. 12. Install bracket in accordance with Service Rework Drawing SR11280052, Sheet 7. 13. Close access to the tail tank fuel system wire assembly installation by closing the following access panels:
**Refer to: Location**  **Access Door** MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 14. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 29 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Group 1, Configuration 2:**  1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure. 3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted procedure. 5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that follow:
**Refer to: Location**  **Access Door** MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 6. Do a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation and change wire supports in accordance with Figure 1. 7. Close access to the tail tank fuel system wire assembly installation by closing the following access panels:
**Refer to: Location**  **Access Door** MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 8. Put the airplane back to a serviceable condition. **Group 2, Configuration 1:** 1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure. 3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted procedure. 5. Gain access to the tail tank fuel system wire assembly installation by opening the following access panels:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 30 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT Refer to:**  **Location Access Door**  MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 6. Remove clamps and keep attaching hardware from wire assemblies in accordance with Service Rework Drawing SR11280052, Sheets 6.3 and 6.4. 7. Do a GVI of the AJS9013, AJS9014, AJS9015, and AGS9124 wire assemblies in accordance with Service Rework Drawing SR11280052, Sheet 3.4 and do as follows: Condition 1: No Wire Assembly Damage Found a. Continue at Step 8. Condition 2: Wire Assembly Damage Found a. Repair or replace wire assemblies in accordance with Service Rework Drawing SR11280052, Sheets 3.4 through 3.17. b. Continue at Step 8. 8. Install wire assembly support brackets and route wire assemblies AJS9013 and AJS9014 in accordance with Service Rework Drawing SR11280052, Sheets 6.2, 6.3, 6.4, 7.1, and 7.3. 9. Install extruded channel wire supports in accordance with Service Rework Drawing SR11280052, Sheet 6.3. 10. Install bracket in accordance with Service Rework Drawing SR11280052, Sheet 7. 11. Close access to the tail tank fuel system wire assembly installation by closing the following access panels:
**Refer to: Location**  **Access Door** MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 12. Put the airplane back to a serviceable condition. **Group 2, Configuration 2:** 1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure. 3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure. 4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 31 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that follow:
**Refer to: Location**  **Access Door** MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 6. Change wire supports in accordance with Figure 2. 7. Close access to the tail tank fuel system wire assembly installation by closing the following access panels:
**Refer to: Location**  **Access Door** MD-11 AMM 06-33-00. Lower Aft Fuselage 311AB 316AB 8. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1: August 24, 2010 32 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT This Figure applies only to: Group 1, Configuration 2.** 

**FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION AND WIRE SUPPORT - INSPECTION/CHANGE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1 August 24, 2010 33 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a)

- SR11280052-11 Tape Inspect 1

- - Nut Remove/Keep 2

- - Washer

- - Screw 1

- Clamp Remove 1 S7934111-4SA Clamp Install (New) 3

- - Washer Install (Kept)

- - Screw

- - Nut

- - Screw Remove/Keep 4

- - Washer 1

- Clamp Remove 1 S7934111-4SA Clamp Install (New) 5

- - Washer Install (Kept)

- - Screw Barrel facing aft. 1 S7934111-4SA Clamp Change 6 2 3D0005-4-6 Screw Remove 7 2 NAS1252-416H Washer Remove/Keep 2 NAS1252-416H Washer Install/Kept 8 2 NAS1801-4-11 Screw Install (New) (a) Adjust tape installation as necessary to achieve noted dimensions.

**FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION AND WIRE SUPPORT - INSPECTION/CHANGE**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1 August 24, 2010 34 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT This Figure applies only to: Group 2, Configuration 2.** 

**FIGURE 2: WIRE SUPPORT - CHANGE (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1 August 24, 2010 35 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP**

- - Nut Remove/Keep 1

- - Washer

- - Screw 1

- Clamp Remove 1 S7934111-4SA Clamp Install (New) 2

- - Screw Install (Kept)

- - Washer

- - Nut

- - Screw Remove/Keep 3

- - Washer 1

- Clamp Remove 1 S7934111-4SA Clamp Install (New) 4

- - Washer Install (Kept)

- - Screw Barrel facing aft. 1 S7934111-4SA Clamp Change 5 2 3D0005-4-6 Screw Remove 6 2 NAS1252-416H Washer Remove/Keep 2 NAS1252-416H Washer Install/Kept 7 2 NAS1801-4-11 Screw Install (New) (a) Adjust tape installation as necessary to achieve noted dimensions.

**FIGURE 2: WIRE SUPPORT - CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 17, 2009 MD11-28A124 Revision 1 August 24, 2010 36 of 36 **BOEING SERVICE BULLETIN MD11-28A124 ALERT**  **ALERT**