### Commercial **Airplanes** 

# MD11 Service Bulletin
**Number: MD11-28-137** Original Issue: June 24, 2014 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Change Fuel Pump Control and Indication System Wiring Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). 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 © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. 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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries 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.

Original Issue: June 24, 2014 MD11-28-137 1 of 69 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 2 of 69 **BOEING SERVICE BULLETIN MD11-28-137**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 20 4. Process Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 21 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 29 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 29 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 APPENDIX B: INPUT SURVEY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 3 of 69 **BOEING SERVICE BULLETIN MD11-28-137**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 4 of 69 **BOEING SERVICE BULLETIN MD11-28-137**

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### Commercial **Airplanes** 

# MD11 Service Bulletin **Summary Number: MD11-28-137**  Original Issue: June 24, 2014 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Change Fuel Pump Control and Indication System Wiring **CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** Frictional heating or sparking resulting from fuel pump failure, wear of fuel pump rotating components, or ingestion of debris by the fuel pump may result in development of a fuel tank ignition source. Frictional heating or sparking in fuel pump inlets or priming system outlets exposed (i.e. not covered by fuel) to the tank ullage in combination with the ullage being flammable, may result in a fuel tank ignition event. Center wing auxiliary, tail, and fuselage auxiliary fuel tanks may be subject to this condition since they are normally pumped dry over the course of a mission. A fuel tank ignition event could develop with a fuel pump running in an empty tank if the normal shutoff command is delayed or as a result of control system failures that keep the fuel pump in a latent uncommanded running condition. To ensure a timely fuel pump shutoff command revise flight crew shutoff procedures for center wing auxiliary, tail, and fuselage auxiliary fuel pumps. To address the latent fuel pump uncommanded running condition change center wing auxiliary, tail, and fuselage auxiliary fuel pump control and indication system wiring to detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel pump running in an empty fuel tank may result in a fuel tank ignition event. 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. Boeing Fleet Team Digest (FTD) MD-11 FTD 28-03006 and MD-11 FTD 28-13001 are related to this service bulletin. **ACTION** This service bulletin changes fuel pump control and indication system wiring to detect and indicate fuel pump uncommanded running conditions. **EFFECTIVITY** MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-08-23 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 60 months after the effective date of AD 2013-08-23.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 5 of 69**INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes 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. Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 6 of 69 **BOEING SERVICE BULLETIN MD11-28-137**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 7 of 69 **BOEING SERVICE BULLETIN MD11-28-137**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 8 of 69 **BOEING SERVICE BULLETIN MD11-28-137**

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### Commercial **Airplanes** 

# MD11 Service Bulletin
**Number: MD11-28-137** Original Issue: June 24, 2014 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Change Fuel Pump Control and Indication System Wiring
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below.
**DESCRIPTION CONFIGURATION**  **GROUP** MD-11 and MD-11F Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR11280077-7001, -7002 and SR11280083-7001 drawing configurations. - 1

MD-11 Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR11280077-7003, -7004 and SR11280083-7003 drawing configurations. - 2

MD-11 and MD-11F Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR11280077-7005, -7006 and SR11280083-7005 drawing configurations. - 3

Airplane Models: MD-11, MD-11F **Group Fuselage Num-**  **ber** 1 447 - 449 1 451 - 459 1 460 - 464 1 466 - 469 1 470 - 479

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 9 of 69**Group Fuselage Num-**  **ber** 1 480 - 489 1 491 - 499 1 500 - 509 1 510 - 517 1 519 1 520 - 529 1 530 - 531 2 532 1 533 - 539 1 540 - 543 2 544 1 545 - 549 1 550 - 552 1 554 - 559 1 560 - 569 1 570 - 579 1 580 - 589 1 590 - 596 3 597 - 599 3 600 - 609 3 610 - 619 3 620 - 629 3 630 - 639 3 640 - 646 2. Spares Affected None. **B. Concurrent Requirements** The service bulletin listed below must be done before or at the same time as this service bulletin:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 10 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Description**  **Service Bulletin Company**  Replace Fuel Pump Control Relays with Fault Current Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination MD11-28A133 Original Issue The Boeing Company

**C. Reason** Frictional heating or sparking resulting from fuel pump failure, wear of fuel pump rotating components, or ingestion of debris by the fuel pump may result in development of a fuel tank ignition source. Frictional heating or sparking in fuel pump inlets or priming system outlets exposed (i.e. not covered by fuel) to the tank ullage in combination with the ullage being flammable, may result in a fuel tank ignition event. Center wing auxiliary, tail, and fuselage auxiliary fuel tanks may be subject to this condition since they are normally pumped dry over the course of a mission. A fuel tank ignition event could develop with a fuel pump running in an empty tank if the normal shutoff command is delayed or as a result of control system failures that keep the fuel pump in a latent uncommanded running condition. To ensure a timely fuel pump shutoff command revise flight crew shutoff procedures for center wing auxiliary, tail, and fuselage auxiliary fuel pumps. To address the latent fuel pump uncommanded running condition change center wing auxiliary, tail, and fuselage auxiliary fuel pump control and indication system wiring to detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel pump running in an empty fuel tank may result in a fuel tank ignition event. 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. Boeing Fleet Team Digest (FTD) MD-11 FTD 28-03006 and MD-11 FTD 28-13001 are related to this service bulletin. **D. Description** This service bulletin changes fuel pump control and indication system wiring to detect and indicate fuel pump uncommanded running conditions. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1, 3:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 MD-11, MD-11F

**Group 2:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 MD-11

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 11 of 69 **BOEING SERVICE BULLETIN MD11-28-137 E. Compliance**  Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-08-23 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 60 months after the effective date of AD 2013-08-23. **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. In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an Alternative Method of Compliance (AMOC) to the requirements of paragraph (g)(2) and (g)(4) of AD 2013-08-23. All provisions of AD 2013-08-23 that are not specifically referenced in the above statement remain fully applicable and must be complied with. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this 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 inspect the work • 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** 3.0 6.0 2 Open Access 0.6 1.2 2 Install Hardware 42.4 84.8 2 Route and Terminate Wiring 3.0 6.0 2 Close Access

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 12 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Group 1:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  0.5 1.0 2 Test 49.5 99.0 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 1.3 2.6 2 Install Hardware 73.3 146.6 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 81.1 162.2 TOTAL FOR EACH AIRPLANE **Group 3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 0.6 1.2 2 Install Hardware 42.0 84.0 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 49.1 98.2 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1:**  **Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW) LBS**  **Approximate Station (Inches)**  **Airplane**

+3928.9 +6.6 595.3 MD-11, MD-11F **Group 2: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 

+6473.5 +11.0 588.5 MD-11

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 13 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Group 3:**  **Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW) LBS**  **Approximate Station (Inches)**  **Airplane**

+3498.9 +5.6 624.8 MD-11, MD-11F
**I. Electrical Load Data** 1. Direct Current DC Load Changes: No DC loads added or deleted. 2. Alternating Current (AC) Load Changes: a. Add AC loads by amounts shown below:

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-2**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1209)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **LWR AUX TK L PUMP SLAVE RELAY**  **5D0123-1 ITEM**  **500X R2-**  **5875A CHAP**  **280 BUS**  **2B**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-2**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1207)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **UPR AUX TK L PUMP SLAVE RELAY**  **5D0123-1 ITEM**  **500X R2-**  **5880A CHAP**  **280 BUS**  **2B**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 14 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UNITS**  **%OPR 1**  **100 E/NE**  **PHASE E**  **C VAC**  **PF 115**  **VAC-2 1**  **UNIT LOAD**  **(W) 5**  **NOTES (B1-**  **1207) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER UPR AUX TK L PUMP**  **SLAVE RELAY 5D0123-1**  **ITEM 500X**  **R2- 5880A**  **CHAP 280**  **BUS 2B** 

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0.5 0.5 5 10 10 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E A**  **VAC PF**  **115 VAC-1**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1-497) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER L TAIL TANK PUMP**  **SLAVE RELAY 5D0123-1**  **ITEM 500X**  **R2- 5888A**  **CHAP 280**  **BUS 1A** 

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 0 0 0 0 0 TAKEOFF & CLIMB 2.5 2.5 5 50 50 CRUISE COLD 2.5 2.5 5 50 50 CRUISE HOT 2.5 2.5 5 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 15 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UNITS**  **%OPR 1**  **100 E/NE**  **PHASE E**  **A VAC**  **PF 115**  **VAC Emer**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1577)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **TAIL ALT PUMP SLAVE RELAY**  **5D0123-1 ITEM**  **500X R2-**  **7000 CHAP**  **280 BUS**  **3A**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 0 0 0 0 0 TAKEOFF & CLIMB 0.25 0 5 5 0 CRUISE COLD 0.25 0 5 5 0 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-1**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1206)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **UPR AUX TK R PUMP SLAVE RELAY**  **5D0123-1 ITEM**  **500X R2-**  **5878A CHAP**  **280 BUS**  **1A**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0.5 0.5 5 10 10 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 16 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UNITS**  **%OPR 1**  **100 E/NE**  **PHASE E**  **C VAC**  **PF 115**  **VAC-3 1**  **UNIT LOAD**  **(W) 5**  **NOTES (B1-**  **1208) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER LWR AUX TK R PUMP**  **SLAVE RELAY 5D0123-1**  **ITEM 500X**  **R2- 5884A**  **CHAP 280**  **BUS 3C** 

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E A**  **VAC PF**  **115 VAC-2**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1-496) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER R TAIL TANK PUMP**  **SLAVE RELAY 5D0123-1**  **ITEM 500X**  **R2- 5889A**  **CHAP 280**  **BUS 2B** 

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 0 0 0 0 0 TAKEOFF & CLIMB 2.5 2.5 5 50 50 CRUISE COLD 2.5 2.5 5 50 50 CRUISE HOT 2.5 2.5 5 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 17 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Group 2:** 

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-1**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1645)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **FWD AUX-1 L PUMP SLAVE RELAY**  **5D0123-1 ITEM**  **500X R2-**  **7001 CHAP**  **280 BUS**  **1A**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE **Group 2:**

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-1**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1-542) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER FWD AUX-2 L PUMP**  **SLAVE RELAY 5D0123-1**  **ITEM 500X**  **R2- 7002**  **CHAP 280**  **BUS 1A** 

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 18 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Group 2:** 

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-3**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1644)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **FWD AUX-1 R PUMP SLAVE RELAY**  **5D0123-1 ITEM**  **500X R2-**  **7003 CHAP**  **280 BUS**  **3C**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE **Group 2:**

**UNITS %OPR**  **1 100**  **E/NE PHASE**  **E C**  **VAC PF**  **115 VAC-3**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1-543) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER FWD AUX-2 R PUMP**  **SLAVE RELAY 5D0123-1**  **ITEM 5002**  **R2- 7004**  **CHAP 280**  **BUS 3C** 

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5 5 5 100 100 TAKEOFF & CLIMB 5 5 5 100 100 CRUISE COLD 5 5 5 100 100 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 19 of 69 **BOEING SERVICE BULLETIN MD11-28-137**b. Delete AC loads by amounts shown below: No AC loads deleted. **J. References** 1. Existing Data: a. Boeing Service Bulletin MD11-28A133. b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-08-23. c. Standard Overhaul Practices Manual (SOPM) 20-50-01. d. Standard Wiring Practices Manual (SWPM) 20-00-09, 20-00-13, 20-00-16, 20-10-04, 20-20-02, 20-20-03, 20-31-00, 20-40-01 and 20-50-01. e. MD11 Aircraft Maintenance Manual (AMM) 06-31-00, 06-31-06, 06-31-08, 24-40-00, 28-22-01 and 52-31-00. f. MD-11 Fleet Team Digest (FTD) 28-03006 and 28-13001. g. MD-11 Structural Repair Manual (SRM) 51. 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 Mail Code: 110-SE20 (bldg 80) 2201 Seal Beach Blvd. Seal Beach, California 90740 USA Phone: (562) 797-1717 Fax: (562) 797-3783 E-mail: lbd.dataservicesmanagement@boeing.com a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- B DWG ELEC INSTL - FUEL PUMP UNCOMMAND- ED SIGNAL SR11280077

- A DWG WIRE INSTL - FUEL PUMP UNCOMMAND- ED SIGNAL SR11280083

3. Installation Drawings Used in the Preparation of this Service Bulletin: None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 20 of 69 **BOEING SERVICE BULLETIN MD11-28-137**4. Process Data: Douglas Process Specifications referred to on the drawings are not given in this service bulletin since these procedures are frequently used as standard shop practices. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  28-22 Aircraft Maintenance Manual Section 1 and 3 FAA Approved Flight Manual 28-02, 28-14, 28-22 Fault Isolation Manual Volumes I, II & III Flight Crew Operations Manual MDC-02K1003 (ALI 28-4) Special Compliance Item Report 28-21, 28-22, 28-44 Wiring Diagram Manual 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. **M. Software Accomplishment Summary** Not affected.

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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. 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 RESPON DER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFOR**  **MATION Unit Price as of the original is**  **sue date of this Service Bulletin (US Dollars)**  **ROLT as of the original issue date of this Service Bulletin**  **(Calendar Days) Name**  **Kit Number**

$14,149.00 120 Service Kit SB11280137-3 $17,765.00 120 Service Kit SB11280137-5 $14,856.00 120 Service Kit SB11280137-7 Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes 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:**
**SB11280137-3 Notes**  **Name QTY**  **Part Number** (a) SCREW 14 3D0005-04-9 (a) SCREW 6 3D0005-08-11

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**SB11280137-3 Notes**  **Name QTY**  **Part Number** (a) CLIPNUT 14 3D0191-04 (a) TERM BLOCK 5 5D0010-15 (a) SOCKET 7 5D0021-2 (a) TERM BLOCK 1 5D0107-1 (a) RELAY 7 5D0123-1 LOCKWASHER 6 MS35338-42 WASHER 14 NAS1252-4L WASHER 6 NAS1252-8L RIVNUT 6 NAS1329S08K75 (b) WIRE KIT 1 SR11280077-101 (b) WIRE KIT 1 SR11280077-104 (b) WIRE KIT 1 SR11280077-108 (b) WIRE KIT 1 SR11280077-112 (b) WIRE KIT 1 SR11280077-114 (b) WIRE KIT 1 SR11280077-116 (b) WIRE KIT 1 SR11280077-117 (b) WIRE KIT 1 SR11280077-119 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to Wire Kit Table below for Wire Kit Contents. **Group 1:**
**Wire Kit Table -119**  **-117 -116**  **-114 -112**  **-108 -104**  **-101 SR11280077**  **Notes Name**  **QTY Part Number**  (a) TERMINAL LUG 764 2 5D0086-24 (a) TERMINAL LUG 766 1 5D0086-26 (a) TERMINAL LUG 878 3 5D0086-3 (a) TERMINAL LUG 761 2 6 4 5D0086-5 (a) TERMINAL LUG 762 1 3 2 4 5D0086-6 (b) WIRE CODE 801 32 FT. 24 FT. D2426-1C-16NM

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**Wire Kit Table -119**  **-117 -116**  **-114 -112**  **-108 -104**  **-101 SR11280077**  **Notes Name**  **QTY Part Number**  (b) WIRE CODE 801 100 FT. 11 FT. 29 FT. 20 FT. 250 FT. 250 FT. 255 FT. 50 FT. D2426-1C-20NM (b) WIRE CODE 801 52 FT. D2426-1C-22NM (b) WIRE CODE 801 20 FT. D2426-1C-24NM
PIN, T/C 1131 2 4 DC38-16P PIN, T/C 1126 3 1 3 2 4 33 DC38-20P SKT T/C 1123 2 28 1 DC39-16S SKT T/C 1124 7 6 6 DC39-20S (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. **Group 2:**
**SB11280137-5 Notes**  **Name QTY**  **Part Number** (a) SCREW 22 3D0005-04-9 (a) SCREW 16 3D0005-08-11 (a) SCREW 2 3D0005-3-11 (a) CLIPNUT 22 3D0191-04 (a) TERM BLOCK 1 5D0010-13 (a) TERM BLOCK 8 5D0010-15 (a) SOCKET 11 5D0021-2 (a) TERM BLOCK 1 5D0107-1 (a) RELAY 11 5D0123-1 LOCKWASHER 16 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 2 NAS1252-10L WASHER 22 NAS1252-4L WASHER 16 NAS1252-8L RIVNUT 7 NAS1329S08K75

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**SB11280137-5 Notes**  **Name QTY**  **Part Number** (b) WIRE KIT 1 SR11280077-102 (b) WIRE KIT 1 SR11280077-105 (b) WIRE KIT 1 SR11280077-107 (b) WIRE KIT 1 SR11280077-109 (b) WIRE KIT 1 SR11280077-111 (b) WIRE KIT 1 SR11280077-113 (b) WIRE KIT 1 SR11280077-115 (b) WIRE KIT 1 SR11280077-116 (b) WIRE KIT 1 SR11280077-118 (b) WIRE KIT 1 SR11280077-120 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to Wire Kit Table below for Wire Kit Contents. **Group 2:**
**Wire Kit Table -120**  **-118 -116**  **-115 -113**  **-111 -109**  **-107 -105**  **-102 SR11280077**  **Notes Name**  **QTY Part Number**  (a) DIODE 2 5D0013-2A (a) TERMINAL LUG 764 2 5D0086-24 (a) TERMINAL LUG 766 1 5D0086-26 (a) TERMINAL LUG 878 3 5D0086-3 (a) TERMINAL LUG 761 6 6 8 5D0086-5 (a) TERMINAL LUG 762 3 3 4 6 2 5D0086-6 (b) WIRE CODE 801 32 FT. 24 FT.D2426-1C16NM (b) WIRE CODE 801 150 FT. 33 FT. 29 FT. 39 FT. 334 FT. 84 FT. 334 FT. 85 FT. 349 FT. 236 FT.D2426-1C20NM (b) WIRE CODE 801 108 FT. 42 FT.D2426-1C22NM

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**Wire Kit Table -120**  **-118 -116**  **-115 -113**  **-111 -109**  **-107 -105**  **-102 SR11280077**  **Notes Name**  **QTY Part Number**  (b) WIRE CODE 801 20 FT.D2426-1C24NM PIN, T/C 1131 3 1 4 DC38-16P PIN, T/C 1126 6 2 3 3 6 1 1 55 7 DC38-20P SKT T/C 1123 1 2 1 36 9 DC39-16S SKT T/C 1124 10 1 1 8 13 DC39-20S (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. **Group 3:**
**SB11280137-7 Notes**  **Name QTY**  **Part Number** (a) SCREW 2 3D0005-08-10 (a) SCREW 6 3D0005-08-11 (a) NUT-CLIP 2 3D0039-8 (a) RELAY 7 5D0123-1 RELAY SOCKET 7 65009-020-513 RELAY SOCKET 1 65009-021-513 (a) BRACKET 2 9D0062-3-08-08 PIN T/C 1145 1 M39029/1-102 RIVET 4 MS20470AD4-3D LOCKWASHER 6 MS35338-42 WASHER 6 NAS1252-8L RIVNUT 6 NAS1329S08K75 CLAMP 2 NMC1001-2 (b) WIRE KIT 1 SR11280077-103 (b) WIRE KIT 1 SR11280077-106 (b) WIRE KIT 1 SR11280077-110 (b) WIRE KIT 1 SR11280077-112 (b) WIRE KIT 1 SR11280077-114

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**SB11280137-7 Notes**  **Name QTY**  **Part Number** (b) WIRE KIT 1 SR11280077-116 (b) WIRE KIT 1 SR11280077-117 (b) WIRE KIT 1 SR11280077-119 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to Wire Kit Table below for Wire Kit Contents. **Group 3:**
**Wire Kit Table -119**  **-117 -116**  **-114 -112**  **-110 -106**  **-103 SR11280077**  **Notes Name**  **QTY Part Number**  (a) TERMINAL LUG 764 2 5D0086-24 (a) TERMINAL LUG 766 1 5D0086-26 (a) TERMINAL LUG 761 2 6 4 5D0086-5 (a) TERMINAL LUG 762 1 3 2 5D0086-6 (a) PIN T/C 1005 14 5D0187-2222P PIN T/C 579 8 617240 SOCKET T/C 578 3 4 617340 (b) WIRE CODE 801 25 FT. 24 FT. D2426-1C-16NM (b) WIRE CODE 801 100 FT. 11 FT. 29 FT. 20 FT. 250 FT. 250 FT. 188 FT. 50 FT. D2426-1C-20NM (b) WIRE CODE 801 126 FT. D2426-1C-24NM
PIN, T/C 1131 2 DC38-16P PIN, T/C 1126 3 1 3 2 4 DC38-20P SKT T/C 1123 2 DC39-16S SKT T/C 1124 7 3 3 DC39-20S PIN T/C 1147 34 M39029/1-101 PIN T/C 1145 2 M39029/1-102 CONTACT 28 M39029/22-193 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13.

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**Notes Name**  **QTY Part Number / Specification**  (a) TIE TAPE As Required DMS 2089 (18XTZ), (23XTZ) or Equivalent (a) Can be purchased from: Gudenbrod, Incorporated, 274 Shoemaker Road, Pottstown, Pennsylvania, 19464, CAGE 82110
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.

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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. **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **CAUTION:** ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Equivalent parts are listed in the AEPL, Drawing 7595071. 3. Use the approved fastener and process material substitutions, in accordance with MD-11 SRM 51. 4. If the length of any fastener specified in this service bulletin does not meet installation standards given 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. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the maximum thickness which may be used under fastener head or nut to counteract accumulation of tolerances. EXCEPTION: When the available fastener length increments are greater than 1/16-inch, a 3/16-inch thick stack of the same type washers may be used. 6. Unless shown differently, these dimensions and tolerances are used: • Linear dimensions are in inches. • Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. • Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch. • Angular tolerance is plus or minus 2 degrees. • Hole dimensions for standard solid rivets are in MD-11 SRM 51. • Torque limits to tighten nuts and bolts are in MD-11 SRM 51. 7. Refer to these SWPM chapters for applicable operations, as accepted procedures:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 31 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Title**  **Chapter** 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

COIL AND STOW - MAINTENANCE PRACTICES SWPM 20-10-04 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 POWER DISTRIBUTION BUS - MAINTENANCE PRACTICES SWPM 20-40-01 ELECTRICAL BONDING - MAINTENANCE PRACTICES SWPM 20-50-01

8. Obey all of the warnings and cautions given in the specified manual sections. 9. 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. 10. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data. 11. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 12. 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. 13. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 14. Review and understand all general notes of Service Rework Drawings that follow: **Sheets Service Rework Drawing**  3, 3.1, 3.2, 3.3, 3.4 SR11280077 1 SR11280083

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 32 of 69 **BOEING SERVICE BULLETIN MD11-28-137 B. WORK INSTRUCTIONS**  1. Gain access: a. Open access doors in the table as follow: **Location/Description Reference**  **Access Door** Avionics Equipment Compartment MD11 AMM 06-31-00 112AB Left-side Air-conditioning Compartment 113AL 113DL Right-side Air-conditioning Compartment 114AR Center Accessory Compartment 131AB b. Open forward cargo compartment door. Refer to MD11 AMM 52-31-00 as an accepted procedure. c. Remove/Keep forward cargo compartment ceiling panels and attaching hardware right and left sides between stations Y=595.000 and Y=673.500. Refer to MD11 AMM 06-31-06 and MD11 AMM 06-31-08. 2. Install relays and hardware in accordance with the table(s) as follow: **Group 1:**
**Sheets Drawing**  13, 14, 22, 24, 25 SR11280077-7001 **Group 2:**
**Sheets Drawing**  15, 16, 18, 20, 21, 22, 23, 24, 25, 26, 27 SR11280077-7003 **Group 3:**
**Sheets Drawing**  17, 18, 19, 22, 24, 25 SR11280077-7005 3. Route wiring in accordance with the table(s) as follow: **Group 1:**
**Additional Data Sheet(s)**  **Drawing** 1, 4.1, 5, 6, 7, 8, 9, 10 SR11280083 Views C, B-B, FORWARD EQUIPMENT RACK 2 SR11280083

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**Additional Data Sheet(s)**  **Drawing** Views N, F-F, G-G, D 3 SR11280083 Views AL-AL, AM for -7001, AN, AP 11 SR11280083 **Group 2:**
**Additional Data Sheet(s)**  **Drawing** 1, 2, 4.1, 5, 6, 7, 8, 9, 10 SR11280083 Views N, F-F, G-G, D 3 SR11280083 Views AL-AL, AM for -7003, AN, AP 11 SR11280083 **Group 3:**
**Additional Data Sheet(s)**  **Drawing** 1, 3, 4, 5, 6, 7, 8, 9, 10 SR11280083 Views C, B-B, FORWARD EQUIPMENT RACK 2 SR11280083 Views AL-AL, AM for -7005, AN, AP 11 SR11280083 4. Change wiring in accordance with the table(s) as follow: **Group 1:**
**Sheets Drawing**  6.8, 6.9, 6.10, 6.11, 6.12, 8, 101.201, 104.201, 104.202, 108.201, 112.201, 114.201, 116.201, 117.201, 119.201, 302.201 SR11280077-7001

**Group 2:**
**Sheets Drawing**  6.13, 6.14, 6.15, 6.16, 6.17, 6.18, 6.19, 6.20, 8, 102.201, 105.201, 105.202, 107.201, 109.201, 111.201, 113.201, 115.201, 116.201, 118.201, 120.201, 301.201, 303.201, 305.201 SR11280077-7003

**Group 3:**
**Sheets Drawing**  6.21, 6.22, 6.23, 6.24, 6.25, 6.26, 103.201, 106.201, 106.202, 110.201, 112.201, 114.201, 116.201, 117.201, 119.201, 304.201 SR11280077-7005

5. Test fuel pumps uncommanded on detection circuits as follow:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 34 of 69 **BOEING SERVICE BULLETIN MD11-28-137 Group 1, 3:**  Perform Functional Test of the Fuel Pumps Uncommanded On Detection Circuit in accordance with MD-11 AMM 28-22-01. **Group 2:** Perform Functional Test of the Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX A. 6. Close access: a. Install/Kept forward cargo compartment ceiling panels and attaching hardware right and left sides between stations Y=595.000 and Y=673.500. Refer to MD11 AMM 06-31-06 and MD11 AMM 06-31-08. b. Close forward cargo compartment door. Refer to MD11 AMM 52-31-00 as an accepted procedure. c. Close access doors in the table as follow:**Location/Description Reference**  **Access Door** Avionics Equipment Compartment MD11 AMM 06-31-00 112AB Left-side Air-conditioning Compartment 113AL 113DL Right-side Air-conditioning Compartment 114AR Center Accessory Compartment 131AB 7. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 35 of 69 **BOEING SERVICE BULLETIN MD11-28-137**1. Test equipment required: a. Electrical jumper wire, 22 gauge, two feet in length with alligator clips at both ends large enough to grasp Fault Current Detector (FCD) terminal posts. b. Multimeter, with alligator clips at end of wire leads large enough to grasp FCD terminal posts. 2. Test set up: a. Apply electrical power to the aircraft. Refer to MD-11 AMM 24-40-00 as an accepted procedure. b. On the Systems Control Panel do as follows: (1) Turn the six BRT knobs (15) to the middle position. (2) Push the FUEL switchlight (16). c. Adjust the applicable fuel quantities as follows: (1) Total aux fuel quantity is less than 600 lb (272 kg). (2) Forward aux tank (if installed) fuel quantity must be less than 200 lb (91 kg). (3) Tail tank fuel quantity must be less than 300 lb (136 kg). d. On the Fuel System Control Panel (FSCP) set the SYSTEM switchlight (17) to MANUAL and after 10 seconds verify the following on the FUEL synoptic page: (1) All main tank forward and aft boost pumps (total of 7) are shown as ON (green or amber circle and pump vanes). (2) Upper Aux Left Pump is shown as ON (green or amber circle and pump vanes). (3) Upper Aux Right Pump is shown as ON (green or amber circle and pump vanes). (4) Lower Aux Left Pump is shown as ON (green or amber circle and pump vanes). (5) Lower Aux Right Pump is shown as ON (green or amber circle and pump vanes). (6) Tail Tank Left Pump is shown as ON (green or amber circle and pump vanes). (7) Tail Tank Right Pump is shown as ON (green or amber circle and pump vanes). e. On the FSCP push the 1 PUMPS, 2 PUMPS, 3 PUMPS, AUX TANKS L TRANS, AUX TANKS R TRANS and TAIL TANK TRANS switches and verify the following on the FUEL synoptic page: (1) All main tank forward and aft boost pumps (total of 7) are shown as OFF (white empty circle). (2) Upper Aux Left Pump is shown as OFF (white empty circle).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 1 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 36 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(3) Upper Aux Right Pump is shown as OFF (white empty circle). (4) Lower Aux Left Pump is shown as OFF (white empty circle). (5) Lower Aux Right Pump is shown as OFF (white empty circle). (6) Tail Tank Left Pump is shown as OFF (white empty circle). (7) Tail Tank Right Pump is shown as OFF (white empty circle). **NOTE:** If other fuel pumps are shown as ON, push the applicable pump switch on the FSCP until all fuel pumps are shown as OFF. f. On the FWD AUX FUEL TANK switch panel, verify that the L TRANS and R TRANS switches are OFF. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. g. Open circuit breakers and install safety tags as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER TAIL TANK L XFR B1-1578 20 B FUEL PUMP POWER AUX TANK 1 L FWD B1-394 21 B FUEL PUMP POWER AUX TANK 2 L FWD B1-1647 22 B FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP POWER TANK 1 FWD B1-614 24 B FUEL PUMP POWER TANK 2 FWD B1-608 25 B FUEL PUMP POWER TANK 3 XFR B1-618 26 B FUEL PUMP CONTROL TAIL TANK L XFR B1-497 20 E FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E FUEL PUMP CONTROL TANK 1 FWD B1-615 24 E FUEL PUMP CONTROL TANK 2 FWD B1-609 25 E FUEL PUMP CONTROL TANK 3 XFR B1-619 26 E

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 2 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 37 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 2** **Name Number**  **Column Row**  FUEL PUMP POWER TAIL TANK R XFR B1-1576 20 C FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP POWER TANK 1 XFR B1-610 24 C FUEL PUMP POWER TANK 2 R AFT B1-596 25 C FUEL PUMP POWER TANK 3 AFT B1-620 26 C FUEL PUMP CONTROL TAIL TANK R XFR B1-496 21 F FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F FUEL PUMP CONTROL TANK 1 XFR B1-611 24 F FUEL PUMP CONTROL TANK 2 R AFT B1-603 25 F FUEL PUMP CONTROL TANK 3 AFT B1-621 26 F
**UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK 1 R FWD B1-393 21 D FUEL PUMP POWER AUX TANK 2 R FWD B1-1646 22 D FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D FUEL PUMP POWER TANK 1 AFT B1-612 24 D FUEL PUMP POWER TANK 2 XFR B1-756 25 D FUEL PUMP POWER TANK 3 FWD B1-616 26 D FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G FUEL PUMP CONTROL TANK 1 AFT B1-613 24 G FUEL PUMP CONTROL TANK 2 XFR B1-757 25 G FUEL PUMP CONTROL TANK 3 FWD B1-617 26 G 3. Test procedure - Fuel Pumps Uncommanded On Detection Circuit Functional Test: a. Upper Aux Left Pump (M1-1934) Test:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 3 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 38 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove the terminal shield of FCD U1-702 (1) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-702 (1). (3) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F (4) On the FUEL synoptic page, verify the Upper Aux Left Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Upper Aux Left Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (5) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F (6) On the FUEL synoptic page verify the Upper Aux Left Pump is shown in as OFF (white empty circle). (7) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-702 (1). (8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-702 (1) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 4 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 39 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 2** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F (10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-702 (1) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-702 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (11) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-702 (1) reads less than 10 volts. (b) On the FUEL synoptic page the Upper Aux Left Pump is shown as ON (amber circle and pump vanes). (12) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-702 (1) reads more than 110 volts. (b) On the FUEL synoptic page the Upper Aux Left Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (13) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F (14) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-702 (1) reads less than 10 volts. (15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-702 (1). (16) At the CAC EPC Bay-2 install the terminal shield (14) on FCD U1-702 (1) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 5 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 40 of 69 **BOEING SERVICE BULLETIN MD11-28-137**b. Upper Aux Right Pump (M1-1933) Test: (1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-1, remove the terminal shield of FCD U1-701 (2) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (2) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-701 (2). (3) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E (4) On the FUEL synoptic page, verify the Upper Aux Right Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Upper Aux Right Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (5) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E (6) On the FUEL synoptic page verify the Upper Aux Right Pump is shown in as OFF (white empty circle). (7) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-701 (2). (8) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-701 (2) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 6 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 41 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E (10) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-701 (2) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-701 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (11) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-701 (2) reads less than 10 volts. (b) On the FUEL synoptic page the Upper Aux Right Pump is shown as ON (amber circle and pump vanes). (12) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-701 (2) reads more than 110 volts. (b) On the FUEL synoptic page the Upper Aux Right Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (13) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E (14) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-701 (2) reads less than 10 volts. (15) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-701 (2). (16) At the CAC EPC Bay-1 install the terminal shield (14) on FCD U1-701 (2) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 7 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 42 of 69 **BOEING SERVICE BULLETIN MD11-28-137**c. Lower Aux Left Pump (M1-1936) Test: (1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove the terminal shield of FCD U1-704 (3) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-704 (3). (3) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F (4) On the FUEL synoptic page, verify the Lower Aux Left Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Lower Aux Left Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (5) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F (6) On the FUEL synoptic page verify the Lower Aux Left Pump is shown in as OFF (white empty circle). (7) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-704 (3). (8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-704 (3) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 8 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 43 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 2** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F (10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-704 (3) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-704 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (11) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-704 (3) reads less than 10 volts. (b) On the FUEL synoptic page the Lower Aux Left Pump is shown as ON (amber circle and pump vanes). (12) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-704 (3) reads more than 110 volts. (b) On the FUEL synoptic page the Lower Aux Left Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (13) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F (14) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-704 (3) reads less than 10 volts. (15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-704 (3). (16) At the CAC EPC Bay-2 install the terminal shield (14) on FCD U1-704 (3) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 9 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 44 of 69 **BOEING SERVICE BULLETIN MD11-28-137**d. Lower Aux Right Pump (M1-1935) Test: (1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-3, remove the terminal shield of FCD U1-703 (4) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (2) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-703 (4). (3) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 B (4) On the FUEL synoptic page, verify the Lower Aux Right Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Lower Aux Right Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (5) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 B (6) On the FUEL synoptic page verify the Lower Aux Right Pump is shown in as OFF (white empty circle). (7) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-703 (4). (8) At the CAC EPC Bay-3 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-703 (4) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 10 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 45 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 B (10) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-703 (4) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-703 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (11) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-703 (4) reads less than 10 volts. (b) On the FUEL synoptic page the Lower Aux Right Pump is shown as ON (amber circle and pump vanes). (12) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-703 (4) reads more than 110 volts. (b) On the FUEL synoptic page the Lower Aux Right Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (13) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 B (14) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-703 (4) reads less than 10 volts. (15) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-703 (4). (16) At the CAC EPC Bay-3 install the terminal shield (14) on FCD U1-703 (4) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 11 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 46 of 69 **BOEING SERVICE BULLETIN MD11-28-137**e. Tail Tank Left Pump (M1-2802) Test: (1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-1, remove the terminal shield of FCD U1-851 (5) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (2) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-851 (5). (3) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL TAIL TANK L XFR B1-497 20 E (4) On the FUEL synoptic page, verify the Tail Tank Left Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Tail Tank Left Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (5) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL TAIL TANK L XFR B1-497 20 E (6) On the FUEL synoptic page verify the Tail Tank Left Pump is shown in as OFF (white empty circle). (7) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-851 (5). (8) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-851 (5) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 12 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 47 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL TAIL TANK L XFR B1-497 20 E (10) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-851 (5) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-851 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (11) On the FSCP, push the TAIL TANK TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-851 (5) reads less than 10 volts. (b) On the FUEL synoptic page the Tail Tank Left Pump is shown as ON (amber circle and pump vanes). (12) On the FSCP, push the TAIL TANK TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-851 (5) reads more than 110 volts. (b) On the FUEL synoptic page the Tail Tank Left Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (13) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL TAIL TANK L XFR B1-497 20 E (14) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-851 (5) reads less than 10 volts. (15) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-851 (5). (16) At the CAC EPC Bay-1 install the terminal shield (14) on FCD U1-851 (5) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 13 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 48 of 69 **BOEING SERVICE BULLETIN MD11-28-137**f. Tail Tank Right Pump (M1-2800) Test: (1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove the terminal shield of FCD U1-852 (6) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-852 (6). (3) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL TAIL TANK R XFR B1-496 21 F (4) On the FUEL synoptic page, verify the Tail Tank Right Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Tail Tank Right Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (5) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL TAIL TANK R XFR B1-496 21 F (6) On the FUEL synoptic page verify the Tail Tank Right Pump is shown as OFF (white empty circle). (7) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-852 (6). (8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-852 (6) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 14 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 49 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 2** **Name Number**  **Column Row**  FUEL PUMP CONTROL TAIL TANK R XFR B1-496 21 F (10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-852 (6) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-852 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (11) On the FSCP, push the TAIL TANK TRANS switch and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-852 (6) reads less than 10 volts. (b) On the FUEL synoptic page the Tail Tank Right Pump is shown as ON (amber circle and pump vanes). (12) On the FSCP, push the TAIL TANK TRANS switch and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-852 (6) reads more than 110 volts. (b) On the FUEL synoptic page the Tail Tank Right Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (13) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL TAIL TANK R XFR B1-496 21 F (14) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-852 (6) reads less than 10 volts. (15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-852 (6). (16) At the CAC EPC Bay-2 install the terminal shield (14) on FCD U1-852 (6) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 15 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 50 of 69 **BOEING SERVICE BULLETIN MD11-28-137**g. Tail Altn Pump (M1-2801) Test: (1) On the FUEL synoptic page, verify the Tail Altn Pump is shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (2) Open and tag circuit breakers as follow: **OVERHEAD, RIGHT EMER AC BUS Name**  **Number Column**  **Row** FUEL PUMP TANK 2 L AFT B1-680 17 G FUEL PUMP TAIL TANK ALTN B1-1574 18 G (3) At the Avionics Compartment Forward Equipment Panel remove the terminal shield of FCD U1-850 (7) as follows: (a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14). (b) Remove the terminal shield (14). (4) At the Avionics Compartment Forward Equipment Panel connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-850 (7). (5) Close circuit breaker as follows: **OVERHEAD, RIGHT EMER AC BUS Name**  **Number Column**  **Row** FUEL PUMP TAIL TANK ALTN B1-1574 18 G (6) On the FUEL synoptic page, verify the Tail Tank Altn Pump is shown as ON (amber circle and pump vanes). **NOTE:** If the Tail Tank Altn Pump is not shown as ON, this indicates that there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (7) Open circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 16 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 51 of 69 **BOEING SERVICE BULLETIN MD11-28-137 OVERHEAD, RIGHT EMER AC BUS**  **Name Number**  **Column Row**  FUEL PUMP TAIL TANK ALTN B1-1574 18 G (8) On the FUEL synoptic page verify the Tail Tank Altn Pump is shown as OFF (white empty circle). (9) At the Avionics Compartment Forward Equipment Panel remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-850 (7). (10) At the Avionics Compartment Forward Equipment Panel attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-850 (7) and verify that it reads less than 10 volts. **WARNING:** THE NEXT STEPS WILL CAUSE TERMINALS 12, A2, B2, C2, A1, B1, C1, AND X1 OF FCD U1-850 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE AVIONICS COMPARTMENT SHOULD REMAIN CLEAR OF THESE EXPOSED TERMINALS UNTIL POWER IS REMOVED OR INJURY COULD RESULT. (11) Close circuit breaker as follows: **OVERHEAD, RIGHT EMER AC BUS Name**  **Number Column**  **Row** FUEL PUMP TAIL TANK ALTN B1-1574 18 G (12) At the Avionics Compartment Forward Equipment Panel verify the multimeter attached to terminal stud 12 of FCD U1-850 (7) reads more than 110 volts. (13) On the FSCP, push the TAIL TANK ALT PUMP switch and verify as follows: (a) At the Avionics Compartment Forward Equipment Panel the multimeter attached to terminal stud 12 of FCD U1-850 (7) reads less than 10 volts. (14) On the FSCP, push the TAIL TANK ALT PUMP switch and verify as follows: (a) At the Avionics Compartment Forward Equipment Panel the multimeter attached to terminal stud 12 of FCD U1-850 (7) reads more than 110 volts. (b) On the FUEL synoptic page the Tail Tank Altn Pump is shown as OFF (white empty circle). **WARNING:** TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (15) Open circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 17 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 52 of 69 **BOEING SERVICE BULLETIN MD11-28-137 OVERHEAD, RIGHT EMER AC BUS**  **Name Number**  **Column Row**  FUEL PUMP TAIL TANK ALTN B1-1574 18 G (16) At the Avionics Compartment Forward Equipment Panel verify the multimeter attached to terminal stud 12 of FCD U1-850 (7) reads less than 10 volts. (17) At the Avionics Compartment Forward Equipment Panel remove the multimeter lead from terminal stud 12 of FCD U1-850 (7). (18) At the Avionics Compartment Forward Equipment Panel install the terminal shield (14) on FCD U1-850 (7) as follows: (a) Install the terminal shield (14) with two screws (12) and two lockwashers (13). (19) Close circuit breakers as follow: **OVERHEAD, RIGHT EMER AC BUS Name**  **Number Column**  **Row** FUEL PUMP TANK 2 L AFT B1-680 17 G FUEL PUMP TAIL TANK ALTN B1-1574 18 G h. Forward Aux Tank Left Pumps (M1-1492 and M1-1494) Test: **WARNING:** TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (1) Verify circuit breakers are open and tagged as follow: **OVERHEAD, RIGHT EMER AC BUS Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E (2) At the CAC EPC Bay-1 remove the terminal shields of FCDs U1-709 (8) and U1-790 (9) as follow: (a) Remove the two screws (12) and lockwashers (13) from each FCD terminal shield (14). (b) Remove the terminal shields (14). (3) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-709 (8).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 18 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 53 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(4) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E (5) On the FUEL synoptic page, verify the two Fwd Aux Left Pumps are shown as ON (amber circle and pump vanes). (6) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS switch is illuminated. **NOTE:** If the ON annunciator light in the L TRANS switch is not illuminated or the Fwd Aux Left Pumps are not shown as ON, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (7) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E (8) On the FUEL synoptic page verify both Fwd Aux Left Pumps are shown as OFF (white empty circle). (9) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS switch is not illuminated. (10) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-709 (8). (11) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-709 (8) and verify that it reads less than 10 volts. (12) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 19 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 54 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(13) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-709 (8) reads more than 110 volts. **WARNING:**THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-709 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (14) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-709 (8) reads less than 10 volts. (b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as ON (amber circle and pump vanes). (c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts. **NOTE:** If the voltage does not increase to more than 110 volts and remain there, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. 1) Monitor the voltage for an additional minute and verify that the voltage does not drop back below 10 volts at any time. (15) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-709 (8) reads more than 110 volts. (b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (16) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E (17) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-709 (8) reads less than 10 volts. (18) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-709 (8).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 20 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 55 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(19) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-790 (9). (20) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E (21) On the FUEL synoptic page, verify the two Fwd Aux Left Pumps are shown as ON (amber circle and pump vanes). (22) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS switch is illuminated. **NOTE:** If the ON annunciator light in the L TRANS switch is not illuminated or the Left Forward Aux Pumps are not shown as ON, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (23) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E (24) On the FUEL synoptic page verify both Fwd Aux Left Pumps are shown as OFF (white empty circle). (25) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS switch is not illuminated. (26) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-790 (9). (27) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-790 (9) and verify that it reads less than 10 volts. (28) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 21 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 56 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E (29) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-790 (9) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-790 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (30) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-790 (9) reads less than 10 volts. (b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as ON (amber circle and pump vanes). (c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts. **NOTE:** If the voltage does not increase to more than 110 volts and remain there, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. 1) Monitor the voltage for an additional minute and verify that the voltage does not drop back below 10 volts at any time. (31) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-790 (9) reads more than 110 volts. (b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (32) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 22 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 57 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(33) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-790 (9) reads less than 10 volts. (34) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-790 (9). (35) At the CAC EPC Bay-1 install the terminal shields (14) on FCDs U1-709 (8) and U1-790 (9) as follow: (a) Install the terminal shields (14) with two screws (12) each and two lockwashers (13) each. (36) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows: (a) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as ON (amber circle and pump vanes). (b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the L TRANS switch is illuminated. **NOTE:** If the ON annunciator light in the L TRANS switch is not illuminated or the Fwd Aux Left Pumps are not shown as ON, verify that diode R7-361 is installed correctly. (37) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows: (a) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as OFF (white empty circle). (b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the L TRANS switch is not illuminated. i. Forward Aux Tank Right Pumps (M1-1491 and M1-1493) Test: **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (1) Verify circuit breakers are open and tagged as follow: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G (2) At the CAC EPC Bay-3 remove the terminal shields of the FCDs U1-710 (10) and U1-789 (11) as follow: (a) Remove the two screws (12) and lockwashers (13) from each FCD terminal shield (14).

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 23 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 58 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(b) Remove the terminal shields (14). (3) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-710 (10). (4) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G (5) On the FUEL synoptic page, verify the two Fwd Aux Right Pumps are shown as ON (amber circle and pump vanes). (6) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS switch is illuminated. **NOTE:** If the ON annunciator light in the R TRANS switch is not illuminated or the Forward Aux Right Pumps are not shown as ON, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (7) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G (8) On the FUEL synoptic page verify both Fwd Aux Right Pumps are shown as OFF (white empty circle). (9) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS switch is not illuminated. (10) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-710 (10). (11) At the CAC EPC Bay-3 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-710 (10) and verify that it reads less than 10 volts. (12) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 24 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 59 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G (13) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-710 (10) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-710 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (14) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-710 (10) reads less than 10 volts. (b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as ON (amber circle and pump vanes). (c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts. **NOTE:** If the voltage does not increase to more than 110 volts and remain there, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. 1) Monitor the voltage for an additional minute and verify that the voltage does not drop back below 10 volts at any time. (15) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-710 (10) reads more than 110 volts. (b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (16) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 25 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 60 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(17) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-710 (10) reads less than 10 volts. (18) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-710 (10). (19) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-789 (11). (20) Close circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G (21) On the FUEL synoptic page, verify the two Fwd Aux Right Pumps are shown as ON (amber circle and pump vanes). (22) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS switch is illuminated. **NOTE:** If the ON annunciator light in the R TRANS switch is not illuminated or the Fwd Aux Right Pumps are not shown as ON, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (23) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G (24) On the FUEL synoptic page verify both Fwd Aux Right Pumps are shown as OFF (white empty circle). (25) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS switch is not illuminated. (26) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-789 (11). (27) At the CAC EPC Bay-3 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-789 (11) and verify that it reads less than 10 volts. (28) Close circuit breaker as follows:

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 26 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 61 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G (29) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-789 (11) reads more than 110 volts. **WARNING:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-789 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY COULD RESULT. (30) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-789 (11) reads less than 10 volts. (b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as ON (amber circle and pump vanes). (c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts. **NOTE:** If the voltage does not increase to more than 110 volts and remain there, then there is a possible wiring or component failure of the uncommanded on detection circuitry and troubleshooting is necessary. 1) Monitor the voltage for an additional minute and verify that the voltage does not drop back below 10 volts at any time. (31) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-789 (11) reads more than 110 volts. (b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as OFF (white empty circle). **WARNING:**TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (32) Open circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 27 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 62 of 69 **BOEING SERVICE BULLETIN MD11-28-137**(33) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-789 (11) reads less than 10 volts. (34) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-789 (11). (35) At the CAC EPC Bay-3 install the terminal shields (14) on FCDs U1-710 (10) and U1-789 (11) as follow: (a) Install the terminal shields (14) with two screws (12) each and two lockwashers (13) each. (36) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows: (a) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as ON (amber circle and pump vanes). (b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the R TRANS switch is illuminated. **NOTE:** If the ON annunciator light in the R TRANS switch is not illuminated or the Fwd Aux Right Pumps are not shown as ON, verify that diode R7-362 is installed correctly. (37) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows: (a) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as OFF (white empty circle). (b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the R TRANS switch is not illuminated. 4. Test close up: a. Remove safety tags and close circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER TAIL TANK L XFR B1-1578 20 B FUEL PUMP POWER AUX TANK 1 L FWD B1-394 21 B FUEL PUMP POWER AUX TANK 2 L FWD B1-1647 22 B FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP POWER TANK 1 FWD B1-614 24 B FUEL PUMP POWER TANK 2 FWD B1-608 25 B FUEL PUMP POWER TANK 3 XFR B1-618 26 B FUEL PUMP CONTROL TAIL TANK L XFR B1-497 20 E

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 28 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 63 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK 1 L FWD B1-1645 21 E FUEL PUMP CONTROL AUX TANK 2 L FWD B1-542 22 E FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E FUEL PUMP CONTROL TANK 1 FWD B1-615 24 E FUEL PUMP CONTROL TANK 2 FWD B1-609 25 E FUEL PUMP CONTROL TANK 3 XFR B1-619 26 E
**UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER TAIL TANK R XFR B1-1576 20 C FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP POWER TANK 1 XFR B1-610 24 C FUEL PUMP POWER TANK 2 R AFT B1-596 25 C FUEL PUMP POWER TANK 3 AFT B1-620 26 C FUEL PUMP CONTROL TAIL TANK R XFR B1-496 21 F FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F FUEL PUMP CONTROL TANK 1 XFR B1-611 24 F FUEL PUMP CONTROL TANK 2 R AFT B1-603 25 F FUEL PUMP CONTROL TANK 3 AFT B1-621 26 F
**UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK 1 R FWD B1-393 21 D FUEL PUMP POWER AUX TANK 2 R FWD B1-1646 22 D FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D FUEL PUMP POWER TANK 1 AFT B1-612 24 D FUEL PUMP POWER TANK 2 XFR B1-756 25 D FUEL PUMP POWER TANK 3 FWD B1-616 26 D FUEL PUMP CONTROL AUX TANK 1 R FWD B1-1644 21 G

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 29 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 64 of 69 **BOEING SERVICE BULLETIN MD11-28-137 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK 2 R FWD B1-543 22 G FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G FUEL PUMP CONTROL TANK 1 AFT B1-613 24 G FUEL PUMP CONTROL TANK 2 XFR B1-757 25 G FUEL PUMP CONTROL TANK 3 FWD B1-617 26 G b. On the Fuel System Control Panel (FSCP) set the SYSTEM switchlight (17) to AUTO and verify on the FUEL synoptic page that all Aux and Tail pumps remain OFF.

**APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT (SHEET 30 OF 33)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 65 of 69 **BOEING SERVICE BULLETIN MD11-28-137 APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT**  **(SHEET 31 OF 33)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 66 of 69 **BOEING SERVICE BULLETIN MD11-28-137 APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT**  **(SHEET 32 OF 33)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 67 of 69 **BOEING SERVICE BULLETIN MD11-28-137 APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT**  **(SHEET 33 OF 33)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 68 of 69 **BOEING SERVICE BULLETIN MD11-28-137 APPENDIX B: INPUT SURVEY**  **(SHEET 1 OF 1)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 MD11-28-137 69 of 69 **BOEING SERVICE BULLETIN MD11-28-137**