**McDonnell Douglas** 

### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Number: MD11-28A143**  Original Issue: December 02, 2009 ATA System: 2822 **SUBJECT:**FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and Fuel Boost/Transfer Pump - Inspection/Replacement 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 1 of 44 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 2 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 7 A. Effectivity................................................ 7 1. Airplanes............................................. 7 2. Spares Affected......................................... 8 B. Concurrent Requirements....................................... 8 C. Reason................................................. 8 D. Description............................................... 8 E. Compliance.............................................. 9 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 14 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 21 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 23 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 . . 35 APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N 60-84351. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 . . . 40 APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER 60-84355-1 INSPECTION LOGIC DIAGRAM. . . . . . . . . . . . . . . . . . . . . . . . . 43 APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER 60-84351 INSPECTION LOGIC DIAGRAM. . . . . . . . . . . . . . . . . . . . . . . . . . 44

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 3 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 4 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**

BLANK PAGE**McDonnell Douglas** 

### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Summary**  **Number: MD11-28A143** Original Issue: December 02, 2009 ATA System: 2822 **SUBJECT:**FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and Fuel Boost/Transfer Pump - Inspection/Replacement 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** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly, part number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector assembly, fuel boost/transfer pump, and replacing any non-serviceable part with a serviceable part as required based on inspection results, will minimize the possibility of a potential ignition source in the fuel tanks and potential fuel tank explosion. If not corrected, insulation resistance degradation and/or arcing in the potted backside of the fuel boost/transfer pump housing electrical connector assembly could compromise the performance of the fuel boost/transfer pump housing electrical connector assembly and result in a failure that can introduce an ignition source into the fuel tank and potential fuel tank explosion. **ACTION** This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector assembly and fuel boost/transfer pump. **EFFECTIVITY** MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes and repair procedures given in this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 5 of 44**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: December 02, 2009 MD11-28A143 6 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT McDonnell Douglas**  

### Commercial **Airplanes** 

# MD11 Service Bulletin **ALERT Number: MD11-28A143**  Original Issue: December 02, 2009 ATA System: 2822 **SUBJECT:**FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and Fuel Boost/Transfer Pump - Inspection/Replacement 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 **NOTE:**The fuel pump housing electrical connector replacement with part number 60-84351 was done on fuselage number 466 prior to the original issue of this service bulletin in accordance with Drawing SP11280022 and FAA Alternative Method of Compliance (AMOC) approval letter with referenced Boeing letter CP-L4L-09-00243. This service bulletin is applicable to airplanes that have installed fuel pump housing electrical connector assembly part number 60-84355-1 in accordance with Service Bulletin MD11-28A138.
**DESCRIPTION CONFIGURATION**  **GROUP** Applicable to airplanes without ER3060 gallon forward auxiliary.

- 1 Applicable to airplanes with ER3060 gallon forward auxiliary fuel tanks. - 2

Airplane Models: MD-11, MD-11F **Group Fuselage Num-**  **ber** 1 447 - 589 2 590

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 7 of 44**Group Fuselage Num-**  **ber** 1 591 - 596 2 597 1 598 - 607 2 608 1 609 - 612 2 613 1 614 2 615 1 616 - 646 2. Spares Affected Examine your spares supply for the parts or components identified in below. For the recommended use Paragraph 2.D., Parts Necessary to Change Spares. If any parts or components are found.
**Name Part Number**  Pump Housing 60-843-3 Pump Housing 60-845-3 Connector 60-84355-1 **B. Concurrent Requirements** None. **C. Reason** MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly, part number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector assembly, fuel boost/transfer pump, and replacing any non-serviceable part with a serviceable part as required based on inspection results, will minimize the possibility of a potential ignition source in the fuel tanks and potential fuel tank explosion. If not corrected, insulation resistance degradation and/or arcing in the potted backside of the fuel boost/transfer pump housing electrical connector assembly could compromise the performance of the fuel boost/transfer pump housing electrical connector assembly and result in a failure that can introduce an ignition source into the fuel tank and potential fuel tank explosion. **D. Description** This service bulletin provides instructions to inspect/replace fuel pump housing electrical connector assembly and fuel boost/transfer pump. The work in this service bulletin is done in the maintenance zone(s) given below.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 8 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Group 1:** 
**Affected Maintenance Zones Zone**  **Model** 141, 142, 311, 515, 517, 531, 532, 533, 541, 615, 617, 632, 633, 641 MD-11, MD-11F
**Group 2:**
**Affected Maintenance Zones Zone**  **Model** 141, 142, 143, 311, 515, 517, 531, 532, 533, 541, 615, 617, 632, 633, 641 MD-11, MD-11F
**E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Airworthiness Directive No. FAA AD 2007-15-05 is related to this service bulletin. Refer to Appendix D and E for a logic diagram of the work instructions. **TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition** (a) Within 10 months af- ter the original issue date on this service bulletin. Replace fuel pump electrical connector assemblies with P/N60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part 5. All Airplanes.

OR Within 10 months after the original issue date on this service bulletin. Do continuity, resistance and insulation resistance inspectionin accordance with Accomplishment Instructions 3.B. Part 3. AND Replace fuel pump electrical connector assemblies with P/N60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part 5. (a) Within 12 months af- ter inspection.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 9 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL**  **BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  Before further flight. Do restoration in accordancewith Accomplishment Instructions 3.B. Part 5.(Serviceable Fuel pump and housing electrical connector assembly)Fuel pump housing electrical connector assembly wiring resistance reading is less than or equal to 2.5 ohms and terminal E is open. AND Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is open. ANDFuel pump housing electrical connector assembly wiring insulation resistance reading is greater than or equal to 10 gigaohm. Before further flight. Replace fuel boost/transfer pump and restore in accordancewith Accomplishment Instructions 3.B. Part 3 and Part 5. (Defective Fuel boost/transfer pump) Fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open and fuel pumphousing electrical connector assembly wiring resistance reading is lessthan or equal to 2.5 ohms and terminal E is open and fuel pumphousing electrical connector assembly wiring insulation resistance reading is greater than or equal to 10 gigaohm. (a) Before further flight. Replace fuel pump electrical connector assemblies with P/N60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part 5. (Defective Fuel pump housing electrical connector assembly)Fuel pump housing electrical connector assembly wiring resistance reading is greater than 2.5 ohms or terminal E is not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is open. ORFuel pump housing electrical connector assembly wiring insulation resistance reading is less than 10 gigaohm. (a) REFER TO TABLE 2 AFTER REPLACEMENT OF FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 WITH P/N 60-84351.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 10 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL**  **BOOST/TRANSFER PUMP - INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 
18 Months Within 18 months af-ter P/N 60-84351 installation. Do continuity, resistance and insulation resistance inspectionin accordance with Accomplishment Instructions 3.B. Part 4. All Airplanes

Before further flight. Do restoration in accordancewith Accomplishment Instructions 3.B. Part 5.(Serviceable Fuel pump and housing electrical connector assembly)Fuel pump housing electrical connector assembly wiring resistance reading is less than or equal to 2.5 ohms and terminal E is open. AND Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is open. ANDFuel pump housing electrical connector assembly wiring insulation resistance reading is greater than or equal to 10 megaohm. Before further flight. Replace fuel boost/transfer pump and restore in accordancewith Accomplishment Instructions 3.B. Part 4 and Part 5. (Defective Fuel boost/transfer pump) Fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open and fuel pumphousing electrical connector assembly wiring resistance reading is lessthan or equal to 2.5 ohms and terminal E is open and fuel pumphousing electrical connector assembly wiring insulation resistance reading is greater than or equal to 10 megaohm.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 11 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL**  **BOOST/TRANSFER PUMP - INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  Before further flight. Replace fuel pump electrical connector assemblies with P/N60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 4 and Part 5. (Defective Fuel pump housing electrical connector assembly)Fuel pump housing electrical connector assembly wiring resistance reading is greater than 2.5 ohms or terminal E is not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is open. ORFuel pump housing electrical connector assembly wiring insulation resistance reading is less than 10 megaohm.
**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 Angles 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 (l) of FAA AD 2007-15-05. All provisions of FAA AD 2007-15-05 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 inspection for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 12 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**• Time to cure the materials • Time to make the parts • Time to find the tools. **Group 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 8.0 8.0 1 Open Access 15.0 30.0 2 Inspect *0.1 - 43.0 *0.2 - 86.0 2 Change 8.0 8.0 1 Close Access 1.0 2.0 2 Test *32.1 - 75.0 *48.2 -134.0 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 9.0 9.0 1 Open Access 17.0 34.0 2 Inspect *0.1 - 48.0 *0.2 - 96.0 2 Change 9.0 9.0 1 Close Access 1.0 2.0 2 Test *36.1 - 84.0 *54.2 - 150.0 TOTAL FOR EACH AIRPLANE *A range of total task hours and elapsed hours and given for inspection per airplane. Actual task hours and elapsed hours for the change are contingent upon inspection findings and are to be estimated by the operator. **H. Weight and Balance Changes** Weight and balance changes affected by incorporation of this service bulletin are contingent upon the changes to each particular airplane. Weight data is to be computed by the operator by weighing parts removed and parts installed during this change. Necessary revisions should be made to the appropriate airplane weight and balance report. **I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 13 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT J. References**  1. Existing Data a. Boeing Service Bulletin MD11-28A138. b. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01, 20-20-01, 20-20-02, 20-20-03, 20-31-00, and 20-50-01. c. MD11 Aircraft Maintenance Manual (AMM) 12-11-03, 28-00-00, 28-22-01, 28-22-02 and 28-22-10. d. MD11 Structural Repair Manual (SRM) 51. e. FAA Airworthiness Directive (FAA) 2007-15-05. f. Wiring Diagram Manual (WDM) 28-22-01, 28-22-02, 28-22-03, 28-22-04 and 28-22-05. g. Crane Hydro-Aire Service Information Letters 60-847-3-1 and 60-843-845-3-28-2. h. FAA Alternative Method of Compliance (AMOC) approval letter with referenced Boeing letter CP-L4L-09-00243. 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**

- E DWG ELEC INSTL - FUEL PUMP ELECTRICAL CONNECTOR SR11280084
3. Installation Drawings Used in the Preparation of this Service Bulletin: None. **K. Publications Affected** 1. Publications:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 14 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Chapter-Section**  **Publication** 28-14 and 28-22 Fault Isolation Manual 28-13 and 28-22 Illustrated Parts Catalog 28-22 Aircraft Maintenance Manual 28 Maintenance Planning Data 28-22 Wiring Diagram Manual Equipment List 28-22 Wiring Diagram Manual 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: December 02, 2009 MD11-28A143 15 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 16 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. If there is a limit to the quantity of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
**Unit Price thru November 30,**  **2010 ROLT (Weeks)**  **Name Part Number** 

$267.00 13 SERVICE KIT SR11280084-3 41.00 13 SERVICE KIT SR11280084-5 9.00 13 SERVICE KIT SR11280084-7 155.00 13 SERVICE KIT SR11280084-9 526.00 13 SERVICE KIT SR11280084-11 526.00 13 SERVICE KIT SR11280084-13 The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Mail to: Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes and 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 17 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Group 1:** 
**Notes Name**  **QTY New Part Number**  (a) KIT 4 SR11280084-3 (a) KIT 8 SR11280084-5 (a) KIT 2 SR11280084-7 (a) KIT 3 SR11280084-9 (a) Total quantity required per airplane. **Group 1:**
**SR11280084 Notes**  **Name QTY**  **New Part Number -9**  **-7 -5**  **-3** SLEEVE

. 1

. . 10-35916-16 GROMMET

. 1

. . 10-60766-8 NUT GROMMET ASSY 1

. 1

. 10-74916-8 COMB

. . . 1 2768771-1 (a) SCREW 1 1 1 1 3D0005-3-12 (a) TERMINAL LUG 765 5 3 3 3 5D0086-25 (a) TERMINAL LUG 766

. 2 2 2 5D0086-26 CLAMP 1

. . . 687-118NF08 FERRULE

. . . 1 7D0294-1 (a) FERRULE ASSY 1

. . . 9D0067-4 (a) BAND,RETAINING 1

. . . 9D0180-2 (a) PIN

. . . 2 9D0196-1 (a) BUSHING

. . . 1 9D0197-1 GLAND NUT

. . . 1 M8700-7/3 WASHER 3 3 3 3 MS35338-137 LOCKWASHER 1 1 1 1 MS35338-43 NUT 3 3 3 3 MS35649-284 WASHER 3 3 3 3 NAS1149CN832R WASHER 1 1 1 1 NAS1149F0332P OVERBRAID 2 FT NEQL48830 (b) TUBING 2 FT SR11280084-15 (a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 18 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Group 1:** 
**SR11280084 Notes**  **Name QTY**  **New Part Number -9**  **-7 -5**  **-3** (b) Material specification DMS 2380 Class 1 or approved Equivalent. **Group 2:**
**SR11280084 Notes**  **Name QTY**  **New Part Number** (a) KIT 1 SR11280084-11 (a) KIT 1 SR11280084-13 (a) KIT 4 SR11280084-3 (a) KIT 8 SR11280084-5 (a) KIT 2 SR11280084-7 (a) KIT 3 SR11280084-9 (a) Total quantity required per airplane. **Group 2:**
**SR11280084 Notes**  **Name QTY**  **New Part Number -13**  **-11 -9**  **-7 -5**  **-3** SLEEVE

. . . 1

. . 10-35916-16 GROMMET

. . . 1

. . 10-60766-8 NUT GROMMET ASSY

. . 1

. 1

. 10-74916-8 COMB

. . . . . 1 2768771-1 (a) SCREW 1 1 1 1 1 1 3D0005-3-12 (a) TERMINAL LUG 765

. . 5 3 3 3 5D0086-25 (a) TERMINAL LUG 766

. . . 2 2 2 5D0086-26 CLAMP

. . 1

. . . 687-118NF08 FERRULE

. . . . . 1 7D0294-1 (a) FERRULE ASSY

. . 1

. . . 9D0067-4 (a) BAND,RETAINING

. . 1

. . . 9D0180-2 (a) PIN

. . . . . 2 9D0196-1 (a) BUSHING

. . . . . 1 9D0197-1

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 19 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Group 2:** 
**SR11280084 Notes**  **Name QTY**  **New Part Number -13**  **-11 -9**  **-7 -5**  **-3** PIN T/C 1127 5 5

. . . . DC64-16P GLAND NUT

. . . . . 1 M8700-7/3 (a) CONNECTOR 1

. . . . . MS3450L16-8P (a) CONNECTOR

. 1

. . . . MS3450L16-8PX WASHER

. . 3 3 3 3 MS35338-137 LOCKWASHER 1 1 1 1 1 1 MS35338-43 NUT

. . 3 3 3 3 MS35649-284 WASHER

. . 3 3 3 3 NAS1149CN832R WASHER 1 1 1 1 1 1 NAS1149F0332P OVERBRAID 2 FT NEQL48830 (c) TUBING 2 FT SR11280084-15 (b) WIRE KIT

. 1

. . . . SR11280084-101 (b) WIRE KIT 1

. . . . . SR11280084-102 (b) WIRE KIT

. 1

. . . . SR11280084-103 (b) WIRE KIT 1

. . . . . SR11280084-104 (a) Or approved Equivalent, refer to AEPL, Drawing 7595071. (b) Refer to Wire Kit Components Table. (c) Material specification DMS 2380 Class 1 or approved Equivalent. **Group 2: Wire Kit SR11280084**  **Notes Name**  **QTY New Part Number**  **-104 -103**  **-102 -101**  (a) TERMINAL LUG T/C 766 1 1 5D0086-26 (a) WIRE CODE 801 7 FT 7 FT 2 FT 2 FT D2426-1C-16NM PLUG 1 DC62L16SJ8SN PLUG 1 DC62L16SJ8SX PIN T/C 1127 1 1 DC64-16P SKT T/C 1125 5 5 1 1 DC65-16SS (a) Or approved Equivalent.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 20 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**2. Parts and Materials Supplied by the Operator **NOTE:**The items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, show the total quantity necessary for each airplane unless noted otherwise. **Group 1:**
**Notes Name**  **QTY New Part Number / Specifica-**  **tion** (a) CONNECTOR ASSY 17 60-84351 (a) (c) PUMP ASSY 17 60-847-X (a) PACKING 17 M25988/1-019 (a) SCREW 68 LL500D4-6 Or ES500D4-6 (b) TAPE 1 Inch x .030 Inch x 12 Feet SR11280084-17 (DMS 2186 Type 2) Or AR 386 Or Equivalent CAGE Hydro-Aire, Incorporated (a) Can be purchased from: 81982 3000 Winona Avenue Burbank, California 91504-2540 USA 02988 Freudenberg-NOK (b) Can be purchased from: 65 Spruce Street Tillsonburg, Ontario N4G 4H3 Canada (c) Refer to Illustrated Parts Catalog (IPC) for applicable fuel boost/transfer pump configuration. **Group 2:**
**Notes Name**  **QTY New Part Number / Specifica-**  **tion** (a) CONNECTOR ASSY 19 60-84351 (a) (c) PUMP ASSY 19 60-847-X (a) PACKING 19 M25988/1-019 (a) SCREW 76 LL500D4-6 Or ES500D4-6 (b) TAPE 1 Inch x .030 Inch x 12 Feet SR11280084-17 (DMS 2186 Type 2) Or AR 386 Or Equivalent

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 21 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Group 2:** 
**Notes Name**  **QTY New Part Number / Specifica-**  **tion** CAGE Hydro-Aire, Incorporated (a) Can be purchased from: 81982 3000 Winona Avenue Burbank, California 91504-2540 USA 02988 Freudenberg-NOK (b) Can be purchased from: 65 Spruce Street Tillsonburg, Ontario N4G 4H3 Canada (c) Refer to IPC for applicable fuel boost/transfer pump configuration.

3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** To get parts shown below, contact the Crane Spares Department at (818) -526-2500 or FAX to (818)-526-2658.
**Notes Name**  **New Part Number / Specifica- tion**  (a) (d) CONNECTOR ASSY 60-84351 (a) (d) PACKING M25988/1-019 (a) (d) SCREW LL500D4-6 Or ES500D4-6 (b) (c) TAPE SR11280084-17 (DMS 2186 Type 2) Or AR 386 Or Equivalent CAGE Hydro-Aire, Incorporated (a) Can be purchased from: 81982 3000 Winona Avenue Burbank, California 91504-2540 USA02988 Freudenberg-NOK (b) Can be purchased from: 65 Spruce Street Tillsonburg, Ontario N4G 4H3 Canada (c) Stock size 1 inch x .030 inch x 12 feet.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 22 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Notes**  **Name New Part Number / Specifica-**  **tion** (d) Use applicable quantities to revise spare 60-843-3 and 60-845-3 fuel pump housing assemblies. Replace spare 60-84355-1 with 60-84351 as needed.

**E. Special Tooling - Price and Availability** The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Tool price and supply data are not given. **F. Special Tooling Necessary to do this Service Bulletin** To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available.
**CAGE Supplier**  **Name Tool / Kit Number**  0HYG7 Fluke Corporation Model 10 Multimeter 1420 75TH Street Southwest Or Everett, Washington 98206 Equivalent 0PK96 Quadtech, Incorporated Model 1864 Megohm meter 5 Clock Tower Place, Suite 210 Or Maynard, Massachusetts 01754 Equivalent * An Equivalent Megohm meter must be able to apply voltage at 100+/-10 Volts DC and be current limited to 5 Milliamps. A T67291 or T67291-1 test tool/alternate tool is required to accomplish this inspection. Refer to Crane Hydro-Aire Service Information Letter 60-847-3-1.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 23 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 24 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**

BLANK PAGE**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. **WARNING:**WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS CAN OCCUR. **CAUTION:**ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. **CAUTION:**KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:**1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Equivalent parts are listed in the AEPL, Drawing 7595071. 3. Use the approved fastener and process material substitutions, in accordance with MD11 SRM, Chapter 51. 4. If the length of any fastener specified in this service bulletin does not meet the installation standards in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in SRM Chapter 51 may be used. Not applicable to Crane Hydro-Aire fuel pump or fuel pump housing or attaching parts. 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. – Torque limits to tighten nuts and bolts are in SRM, Chapter 51. 7. Refer to these SWPM chapters for applicable operations, as accepted procedures:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 25 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**– **TITLE CHAPTER**  IDENTIFICATION OF ELECTRICAL WIRE - COMMERCIAL SWPM 20-00-03 GENERAL MAINTENANCE PRACTICES - ELECTRICAL SWPM 20-00-09 ELECTRICAL WIRE CODES SWPM 20-00-13 ELECTRICAL WIRE END TERMINATION CODES AND TOOL CODES SWPM 20-00-16 FABRICATING AND INSTALLING WIRE HARNESSES - COMMERCIAL SWPM 20-10-01 TERMINALS - MAINTENANCE PRACTICES SWPM 20-20-01 TERMINAL BLOCKS - MAINTENANCE PRACTICES SWPM 20-20-02 GENERAL INSTALLATIONS HARDWARE - MAINTENANCE PRACTICES SWPM 20-20-03 ELECTRICAL CONNECTORS - MAINTENANCE PRACTICES SWPM 20-31-00 ELECTRICAL BONDING - MAINTENANCE PRACTICES SWPM 20-50-01
8. Refer to Wiring Diagram Manual (WDM) for applicable wiring diagrams as follows:

– **WIRING DIAGRAM LOCATION**  28-22-01 Tank 1 28-22-02 Tank 2 28-22-03 Tank 3 28-22-04 Aux Tank * 28-22-05 Tail Tank * Including Fwd Aux Tanks (If Installed).
9. Obey all of the warnings and cautions given in the specified manual sections. 10. Review and understand all general notes of Service Rework Drawing SR11280084 sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.7.1, 3.8, 3.9, 3.10 and 7 before start of modification. 11. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 12. Any protrusion of threads is acceptable provided that the threads do not rub or ride against nearby wire assemblies or components.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 26 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**13. Access panel numbers and locations may vary. 14. Identify and note location of wires prior to removal from terminal strip and/or ground stud. 15. The inspection order of operation procedures outlined in Parts 3 and 4 of Paragraph 3.B., Work Instructions must be followed. The instructions identified in Paragraph 3.B., Work Instructions give the recommended sequence of steps for which pump location to inspect. The sequence of steps to inspect the pump locations can be changed. **B. WORK INSTRUCTIONS PART 1 (ACCESS/PREPARATION)**  **WARNING:**FUEL TANKS MUST BE FILLED TO SPECIFIED LEVEL OR DRAINED, PURGED, AND SAFE FOR MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. 1. Make sure fuel tanks are filled to specified level or defuel, purge, and make fuel system safe for maintenance. Refer to MD11 AMM 12-11-03 and MD11 AMM 28-00-00 as accepted procedures.
**Minimum Fuel Level Tank**  **Kilogram Pounds**  9070 20000 1* 10430 23000 2 9070 20000 3* 4980 11000 Upper Aux 2040 4500 Lower Aux 3170 7000 Tail * Tanks 1 and 3 aft fuel boost/transfer pumps and conduits are located in tank 2. Tank 2 must be filled to specified level when accomplishing this inspection for tanks 1 and 3 aft fuel boost/transfer pumps. **Group 2:**
**Minimum Fuel Level Tank**  **Kilogram Pounds**  2040 4500 Fwd Aux 2. Place Fuel System Controller (FSC) in manual mode and make sure all pumps are off. Refer to MD11 AMM 28-00-00 as an accepted procedure. 3. Gain access to inspection areas. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. 4. Open/verify circuit breakers as follows:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 27 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**a. Open fuel boost/transfer pump power circuit breakers. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. b. Make sure Remote Control Circuit Breaker (RCCB) indicators are green/open.
**Location Circuit Breaker**  **RCCB** EPC Bay 2 Tank 1 Trans B1-672 EPC Bay 3 Tank 1 Aft B1-673 ADG Equipment Panel Tank 1 Aft B1-190* EPC Bay 1 Tank 1 Fwd B1-674 EPC Bay 1 Tank 2 R Aft B1-675 EPC Bay 1 Tank 2 Fwd B1-676 EPC Bay 3 Tank 3 Fwd B1-677 EPC Bay 1 Tank 3 Trans B1-678 EPC Bay 3 Tank 2 Trans B1-682 EPC Bay 2 Tank 3 Aft B1-679 ADG Equipment Panel Tank 3 Aft B1-191* EPC Bay 1 R Upper Aux Tank B1-1258 EPC Bay 3 R Lower Aux Tank B1-1259 EPC Bay 2 L Upper Aux Tank B1-1260 EPC Bay 2 L Lower Aux Tank B1-1261 Electrical Power Panel Tank 2 L Aft B1-1572 EPC Bay 1 Tail Tank L Trans B1-1573 EPC Bay 2 Tail Tank R Trans B1-1575 Electrical Power Panel Tail Tank Altn B1-1577 *If installed **Group 2:**
**Location Circuit Breaker**  **RCCB** EPC Bay 1 Fwd Aux L B1-391 EPC Bay 3 Fwd Aux R B1-392**PART 2 (FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY - REPLACEMENT)** 1. Replace existing 60-84355-1 fuel pump housing electrical connector assembly in accordance with Appendix B. 2. Proceed to Part 5 (Restoration).

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 28 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT PART 3 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR**  **ASSEMBLY PART NUMBER 60-84355-1 INSPECTION)** 1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through fuel boost/transfer pump as follows: a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect connectors) and check disconnected wires terminal to terminal in accordance with Appendix A, Tables below and refer to MD11 AMM 28-22-10 as an accepted procedure: **NOTE:**Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms. **NOTE:**Terminal E should read open during multimeter check. **Wiring Resistance Check Results**  **Check Results**  **Check** 2-3 1-2 2-E 1-3 3-E 1-E **Group 2: Wiring Resistance Check**  **Results Check**  **Results Check**  B-C A-B B-E A-C C-E A-E b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open, remove fuel boost/transfer pump, refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an acceptable procedure and check pin-to-pin as follows: **NOTE:**Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms. **NOTE:**Pin E should read open during multimeter check. **Fuel Boost/Transfer Pump Resistance Check Results**  **Check Results**  **Check** B-C A-B B-E A-C

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 29 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Fuel Boost/Transfer Pump Resistance Check**  **Results Check**  **Results Check**  C-E A-E 2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with pin E open, replace existing fuel pump housing electrical connector assembly in accordance with Appendix B. 3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. 4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly insulation resistance check as follows: a. Install T67291 or T6729-1 test tool/alternate tool. b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation resistance by applying test voltage terminal-to-terminal in accordance with Appendix A, and Tables below: **NOTE:**Insulation resistance should be greater or equal to 10 gigaohm.
**Insulation Resistance Check Results**  **Check Results**  **Check** 2-3 1-2 2-E 1-3 3-E 1-E **Group 2:**
**Insulation Resistance Check Results**  **Check Results**  **Check** B-C A-B B-E A-C C-E A-E c. Remove test pump/alternate tool. 5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 30 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**a. Replace fuel boost/transfer pump. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. b. Proceed to Part 5 (Restoration). 6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than 10 gigaohm. a. Replace existing fuel pump housing electrical connector assembly in accordance with Appendix B. b. Proceed to Part 5 (Restoration). 7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are as follows: a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and terminal E is open. b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is open. c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than or equal to 10 gigaohm. **PART 4 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY PART NUMBER 60-84351 INSPECTION)**  1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through fuel boost/transfer pump as follows: a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect connectors) and check disconnected wires terminal to terminal in accordance with Appendix C, Tables below and refer to MD11 AMM 28-22-10 as an accepted procedure: **NOTE:**Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms. **NOTE:**Terminal E should read open during multimeter check. **Wiring Resistance Check Results**  **Check Results**  **Check** 2-D 1-2 2-E 1-3 3-D 1-D 3-E 1-E D-E 2-3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 31 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Group 2:**  **Wiring Resistance Check Results**  **Check Results**  **Check** B-D A-B B-E A-C C-D A-D C-E A-E D-E B-C b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open, remove fuel boost/transfer pump, refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an acceptable procedure and check pin-to-pin as follow: **NOTE:**Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms. **NOTE:**Pin E should read open during multimeter check. **Fuel Boost/Transfer Pump Resistance Check Results**  **Check Results**  **Check** B-D A-B B-E A-C C-D A-D C-E A-E D-E B-C 2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with pin E open, replace the affected fuel pump housing electrical connector assembly. Refer to MD11 AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin MD11-28A113" as an accepted procedure. 3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. 4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly insulation resistance check as follows: a. Install T67291 or T6729-1 test tool/alternate tool. b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation resistance by applying test voltage terminal-to-terminal in accordance with Appendix C, and Tables below: **NOTE:**Insulation resistance should be greater or equal to 10 megaohm.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 32 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT Insulation Resistance Check**  **Results Check**  **Results Check**  2-D 1-2 2-E 1-3 3-D 1-D 3-E 1-E D-E 2-3 **Group 2:**
**Insulation Resistance Check Results**  **Check Results**  **Check** B-D A-B B-E A-C C-D A-D C-E A-E D-E B-C c. Remove test pump/alternate tool. 5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open. a. Replace fuel boost/transfer pump. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. b. Proceed to Part 5 (Restoration). 6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than 10 megaohm. a. Replace the affected fuel pump housing electrical connector assembly. Refer to MD11 AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin MD11-28A113" as an accepted procedure. b. Proceed to Part 5 (Restoration). 7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are as follows:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 33 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and terminal E is open. b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is open. c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than or equal to 10 megaohm. **PART 5 (RESTORATION)** 1. If not already accomplished, connect fuel pump housing electrical connector assemblies to terminal strip and ground studs. Refer to MD11 AMM 28-22-10 and Appendix A (part number 60-84355-1), or Appendix C (part number 60-84351) as an accepted procedure. 2. Install fuel boost/transfer pumps if not previously installed refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. 3. Do operational test of fuel boost/transfer pumps and using a digital multimeter check that voltage between applicable terminal strip post and ground is 104 to 122VAC. Refer to MD11 AMM 28-22-01, MD11 AMM 28-22-02 and Appendix A (part number 60-84355-1), or Appendix C (part number 60-84351) as an accepted procedure. 4. Close access. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure. 5. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 34 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT ALL GROUPS:** 

**Ground Stud Terminal Strip**  **Connector Tank/Pump**  **Post Number**  **Socket Number** 

- 1 S3-368 A R5-1102 1/Forward - 2 B

- 3 C 5022A E*

- 1 S3-370 A R5-1100 1/Transfer - 2 B

- 3 C 4726A E*

- 1 S3-369 A R5-1101 1/Aft - 2 B

- 3 C 4727A E*

- 1 S3-371 A R5-1105 2/Forward - 2 B

- 3 C 5009A E*

- 1 S3-372 A R5-1104 2/Left Aft - 2 B

- 3 C 4728A E*

- 1 S3-374 A R5-1099 2/Transfer - 2 B

- 3 C 6078A E*

- 1 S3-373 A R5-1103 2/Right Aft - 2 B

- 3 C 4821A E*

- 1 S3-377 A R5-1106 3/Forward - 2 B

- 3 C 6022A E*

- 1 S3-376 A R5-1107 3/Transfer - 2 B

- 3 C 4823A E*

**APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 35 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT ALL GROUPS:** 

**Ground Stud Terminal Strip**  **Connector Tank/Pump**  **Post Number**  **Socket Number** 

- 1 S3-375 A R5-1108 3/Right Aft - 2 B

- 3 C 4822A E*

- 1 S3-803 A R5-1934 Center Aux/Left Upper - 2 B

- 3 C 4729A E*

- 1 S3-802 A R5-1933 Center Aux/Right Upper - 2 B

- 3 C 4824A E*

- 1 S3-805 A R5-1936 Center Aux/Left Lower - 2 B

- 3 C 4895A E*

- 1 S3-804 A R5-1935 Center Aux/Right Lower - 2 B

- 3 C 4894A E*

- 1 S3-764 A R5-2802 Tail/Left Transfer - 2 B

- 3 C 7043A 5 E*

- 1 S3-765 A R5-2800Tail/Right Transfer - 2 B

- 3 C 7043A 5 E*

- 1 S3-755 A R5-2801 Tail/Altn - 2 B

- 3 C 7043A 5 E* * E should read open during multimeter check.

**APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 36 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT GROUP 2:** 

**Ground Stud Connector**  **Connector (Pump) Tank/Pump**  **Socket Number**  **Socket Number** 

- A R5-9668 A R5-1347 Forward Aux Right - B B

- C C 9079A E* E*

- A R5-9669 A R5-1348 Forward Aux Left - B B

- C C 9078A E* E* * E should read open during multimeter check.
**GROUP 2:**
**Terminal Relay**  **Location Tank/Pump**  A1 R2-110 Right Forward Aux B1 C1 A1 R2-109 Left Forward Aux B1 C1

**APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 37 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**1. Put the Fuel System Controller (FSC) in manual mode and make sure all pumps are off. Refer to MD11 AMM 28-00-00 as an accepted procedure. 2. Replace the affected fuel pump housing electrical connector assembly in accordance with Table below and refer to MD11 AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin MD11-28A113" as an accepted procedure. **ALL GROUPS: Drawing**  **SR11280084 Connector Identifi**  **cation Fuel Pump Identifi**  **cation Location**  **Tank** Sheets 3, 3.1, 3.3, 3.4, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9, 9.6, 10 and 21 R5-1102 M1-1102 Forward 1

Sheets 3, 3.1, 3.3, 3.5, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9, 9.6, 10 and 19. R5-1100 M1-1100 Transfer 1 R5-1101 M1-1101 Left Aft 1
Sheets 3, 3.1, 3.3, 3.4, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.1, 9.6, 10 and 20. R5-1105 M1-1105 Forward 2

Sheets 3, 3.1, 3.3, 3.5, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.1, 9.6, 10 and 19. R5-1104 M1-1104 Left Aft 2

Sheets 3, 3.1, 3.3, 3.4, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.1, 9.6, 10 and 17. R5-1099 M1-1099 Transfer 2

Sheets 3, 3.1, 3.3, 3.5, 3.8, 3.9, 3.10, 4, 4.1, 5., 5.1, 6, 6.1, 7, 9.1, 9.7, 10 and 16. R5-1103 M1-1103 Right Aft 2

Sheets 3, 3.1, 3.3, 3.4, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.2, 9.7, 10 and 18. R5-1106 M1-1106 Forward 3

**APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N 60-84351**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 38 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT ALL GROUPS:**  **Drawing SR11280084** **Connector Identifi cation** **Fuel Pump Identifi cation**  **Location Tank**  Sheets 3, 3.1, 3.3, 3.5, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6. 6.1, 7, 9.2, 9.7, 10 and 16. R5-1107 M1-1107 Transfer 3 R5-1108 M1-1108 Right Aft 3
Sheets 3, 3.1, 3.3, 3.5, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.3, 9.7, 10 and 13. R5-1934 M1-1934 Left Center Aux/Upper R5-1933 M1-1933 Right Center Aux/Upper
Sheets 3, 3.1, 3.2, 3.3, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.3, 9.8, 10, 14 and 15. R5-1936 M1-1936 Left Center Aux/Lower R5-1935 M1-1935 Right Center Aux/Lower

Sheets 3, 3.1, 3.3, 3.7, 3.7.1, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.5, 9.8, 10 and 11. R5-2802 M1-2802 Left Transfer Tail

Sheets 3, 3.1, 3.3, 3.7, 3.7.1, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.5, 9.8, 10 and 11. R5-2800 M1-2800 Right Transfer Tail

Sheets 3, 3.1, 3.3, 3.7, 3.7.1, 3.8, 3.9, 3.10, 4, 4.1, 5, 5.1, 6, 6.1, 7, 9.5, 9.9, 10 and 11. R5-2801 M1-2801 Alt Feed Tail

**GROUP 2: Drawing**  **SR11280084 Connector Identifi**  **cation Fuel Pump Identifi**  **cation Location**  **Tank** Sheets 3, 3.1, 3.3, 3.6, 3.9, 3.10, 4.1, 5.1, 6.1, 7, 8, 8.1, 8.2, 8.3, 9.4, 9.8, 10 and 12. R5-1347 M1-1347 Right Forward Aux R5-1348 M1-1348 Left Forward Aux

**APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N 60-84351**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 39 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT ALL GROUPS:** 

**Ground Stud Terminal Strip**  **Connector Tank/Pump**  **Post Number**  **Socket Number** 

- 1 S3-368 A R5-1102 1/Forward - 2 B

- 3 C 5022A D 5022A E*

- 1 S3-370 A R5-1100 1/Transfer - 2 B

- 3 C 4726A D 4726A E*

- 1 S3-369 A R5-1101 1/Aft - 2 B

- 3 C 4727A D 4727A E*

- 1 S3-371 A R5-1105 2/Forward - 2 B

- 3 C 5009A D 5009A E*

- 1 S3-372 A R5-1104 2/Left Aft - 2 B

- 3 C 4728A D 4728A E*

- 1 S3-374 A R5-1099 2/Transfer - 2 B

- 3 C 6078A D 6078A E*

- 1 S3-373 A R5-1103 2/Right Aft - 2 B

- 3 C 4821A D 4821A E*

**APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 40 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT ALL GROUPS:** 

**Ground Stud Terminal Strip**  **Connector Tank/Pump**  **Post Number**  **Socket Number** 

- 1 S3-377 A R5-1106 3/Forward - 2 B

- 3 C 6022A D 6022A E*

- 1 S3-376 A R5-1107 3/Transfer - 2 B

- 3 C 4823A D 4823A E*

- 1 S3-375 A R5-1108 3/Right Aft - 2 B

- 3 C 4822A D 4822A E*

- 1 S3-803 A R5-1934 Center Aux/Left Upper - 2 B

- 3 C 4729A D 4729A E*

- 1 S3-802 A R5-1933 Center Aux/Right Upper - 2 B

- 3 C 4824A D 4824A E*

- 1 S3-805 A R5-1936 Center Aux/Left Lower - 2 B

- 3 C 4895A D 4895A E*

- 1 S3-804 A R5-1935 Center Aux/Right Lower - 2 B

- 3 C 4894A D 4894A E*

- 1 S3-764 A R5-2802 Tail/Left Transfer - 2 B

- 3 C 7043A 5 D 7043A 5 E*

**APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 41 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT ALL GROUPS:** 

**Ground Stud Terminal Strip**  **Connector Tank/Pump**  **Post Number**  **Socket Number** 

- 1 S3-765 A R5-2800Tail/Right Transfer - 2 B

- 3 C 7043A 5 D 7043A 5 E*

- 1 S3-755 A R5-2801 Tail/Altn - 2 B

- 3 C 7043A 5 D 7043A 5 E* * E should read open during multimeter check.
**GROUP 2:**

**Ground Stud Connector**  **Connector (Pump) Tank/Pump**  **Socket Number**  **Socket Number** 

- A R5-9668 A R5-1347 Forward Aux Right - B B

- C C 9079A D D 9079A E* E*

- A R5-9669 A R5-1348 Forward Aux Left - B B

- C C 9078A D D 9078A E* E* * E should read open during multimeter check.
**GROUP 2:**
**Terminal Relay**  **Location Tank/Pump**  A1 R2-110 Right Forward Aux B1 C1 A1 R2-109 Left Forward Aux B1 C1

**APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 42 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER**  **60-84355-1 INSPECTION LOGIC DIAGRAM (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 43 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER**  **60-84351 INSPECTION LOGIC DIAGRAM (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 02, 2009 MD11-28A143 44 of 44 **BOEING SERVICE BULLETIN MD11-28A143 ALERT**  **ALERT**