### Commercial **Airplanes** 

# DC10 Service Bulletin **Number: DC10-28-256** Original Issue: June 24, 2014 ATA System: 2800 **SUBJECT:** FUEL - Fuel Systems - 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 Unpublished Work.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Original Issue: June 24, 2014 DC10-28-256 1 of 99 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 2 of 99 **BOEING SERVICE BULLETIN DC10-28-256**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 25 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 26 4. Process Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 26 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 39 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 40 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE [Group 1, 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE [Group 2-3, 5-6]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE [Group 9] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES [Group 8] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 APPENDIX E: INPUT SURVEY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 3 of 99 **BOEING SERVICE BULLETIN DC10-28-256**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 4 of 99 **BOEING SERVICE BULLETIN DC10-28-256**

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### Commercial **Airplanes** 

# DC10 Service Bulletin **Summary Number: DC10-28-256**  Original Issue: June 24, 2014 ATA System: 2800 **SUBJECT:** FUEL - Fuel Systems - 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, fuselage auxiliary, and wing tip compartment (KC-10 only) 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, fuselage auxiliary, and wing tip compartment (KC-10 only) fuel tanks. To address the latent fuel pump uncommanded running condition change center wing auxiliary, fuselage auxiliary, and wing tip compartment (KC-10 only) fuel pump control and indication system wiring to detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel tank 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) DC-10, MD-10 FTD 28-13001 and DC-10, MD-10 FTD 28-13003 are related to this service bulletin. **ACTION** This service bulletin changes fuel pump control and indication system wiring. **EFFECTIVITY** DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F(KC-10A), DC-10-30F(KDC-10), DC-10-40, DC-10-40F and MD-10-30F 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 DC10-28-256 5 of 99**INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Group(s)**  18.4 36.8 1 31.4 62.8 2-3, 9 25.6 51.2 4 10.1 20.2 5 31.6 63.2 6 41.5 83.0 7 48.6 97.2 8
**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 E 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 DC10-28-256 6 of 99 **BOEING SERVICE BULLETIN DC10-28-256**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 7 of 99 **BOEING SERVICE BULLETIN DC10-28-256**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 8 of 99 **BOEING SERVICE BULLETIN DC10-28-256**

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### Commercial **Airplanes** 

# DC10 Service Bulletin **Number: DC10-28-256** Original Issue: June 24, 2014 ATA System: 2800 **SUBJECT:** FUEL - Fuel Systems - 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** DC-10-10 and DC-10-15 Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7001, -7002 and SR10280073-7001 drawing configurations. - 1

DC-10-30, DC-10-30F and DC-10-30F (KDC-10) Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7003, -7004 and SR10280073-7003 drawing configurations. - 2

DC-10-30, DC-10-30F, DC-10-40 and DC-10-40F Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7005, -7006 and SR10280073-7005 drawing configurations. - 3

DC-10-10F Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7007, -7008 and SR10280073-7007 drawing configurations. - 4

DC-10-30F Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7009, -7010 and SR10280073-7009 drawing configurations. - 5

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 9 of 99**DESCRIPTION CONFIGURATION**  **GROUP** DC-10-30 Airplanes that change fuel pump control and indication system wiring to detect and display uncommanded fuel pump running conditions in accordance with SR10280072-7011, -7012 and SR10280073-7011 drawing configurations. - 6

DC-10-30F (KC-10A) Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7013, -7014 and SR10280073-7013 drawing configurations. - 7

DC-10-30F and MD-10-30F Airplanes that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280069-7001, -7002 and SR10280070-7001 drawing configurations. - 8

DC-10-30 Airplanes with AFT AUX tank that change fuel pump control and indication system wiring to detect and indicate uncommanded fuel pump running conditions in accordance with SR10280072-7005, -7006 and SR10280073-7005 drawing configurations. - 9

Airplane Models: DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F (KDC-10), DC-10-40, DC-10-40F, MD-10-30F**Group Fuselage Num-**  **ber** 1 2 3 60 1 65 3 71 1 72 4 83 3 90 8 96 3 99 3 100 8 103 2 106 8 110 3 114 - 115

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 10 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group**  **Fuselage Num- ber**  3 117 3 122 - 123 2 127 3 129 3 131 - 135 3 137 3 146 - 147 3 150 3 152 3 156 - 158 3 160 2 165 3 166 3 170 - 171 3 174 3 178 - 179 3 183 - 184 3 187 - 189 3 190 3 192 3 195 - 196 3 199 3 201 3 204 3 206 3 211 - 216 8 219 3 220 - 221 3 223 - 227 3 229 3 230 3 232

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 11 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group**  **Fuselage Num- ber**  3 234 2 235 3 236 3 239 3 240 3 242 3 244 - 246 2 248 1 251 - 252 2 253 3 254 2 255 3 256 8 257 3 261 - 263 2 264 3 265 - 266 2 267 3 268 3 274 - 275 8 277 3 281 8 282 1 285 3 286 3 289 3 290 - 291 9 292 3 299 3 300 - 301 5 302 - 303 3 304 - 306

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 12 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group**  **Fuselage Num- ber**  3 308 3 310 7 311 5 312 3 313 2 314 6 315 3 316 8 317 1 318 3 324 6 325 8 326 3 327 3 329 8 330 3 332 7 333 3 334 - 338 3 340 9 341 3 342 - 343 9 345 1 346 3 349 3 355 - 356 7 359 7 360 - 361 7 363 3 366 - 367 1 372 7 373

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 13 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group**  **Fuselage Num- ber**  7 375 - 378 7 380 3 381 7 383 - 389 7 390 - 399 7 400 - 408 8 409 7 410 - 411 8 412 7 413 - 415 8 416 7 417 - 418 8 419 7 420 - 421 8 422 7 423 - 429 7 430 - 432 8 433 9 434 - 438 7 439 8 440 7 441 8 442 - 444 3 445 - 446 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 DC10-28-256 14 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Description**  **Service Bulletin Company**  Replace Fuel Pump Control Relays with Fault Current Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination DC10-28A253 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, fuselage auxiliary, and wing tip compartment (KC-10 only) 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, fuselage auxiliary, and wing tip compartment (KC-10 only) fuel tanks. To address the latent fuel pump uncommanded running condition change center wing auxiliary, fuselage auxiliary, and wing tip compartment (KC-10 only) fuel pump control and indication system wiring to detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel tank 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) DC-10, MD-10 FTD 28-13001 and DC-10, MD-10 FTD 28-13003 are related to this service bulletin. **D. Description** This service bulletin changes fuel pump control and indication system wiring. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-10, DC-10-15

**Group 2:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-30, DC-10-30F, DC-10- 30F (KDC-10)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 15 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 3:** 
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-30, DC-10-30F, DC-10- 40, DC-10-40F **Group 4:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-10F

**Group 5:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-30F

**Group 6, 9:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-30

**Group 7:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-30F (KC-10A)

**Group 8:**
**Affected Maintenance Zones Zone**  **Model** 112, 113, 114, 121, 122, 123, 125, 126, 127, 131, 132 DC-10-30F, MD-10-30F

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 16 of 99 **BOEING SERVICE BULLETIN DC10-28-256 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** 1. DC-10 Airplanes: 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 a Alternative Method of Compliance (AMOC) to the requirements of paragraph (g)(3) 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. 2. MD-10 Airplanes: 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. 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 a 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 17 of 99 **BOEING SERVICE BULLETIN DC10-28-256**• 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 0.3 0.6 2 Install Hardware 11.6 23.2 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 18.4 36.8 TOTAL FOR EACH AIRPLANE **Group 2-3, 9: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 0.8 1.6 2 Install Hardware 24.1 48.2 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 31.4 62.8 TOTAL FOR EACH AIRPLANE **Group 4: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 19.1 38.2 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 25.6 51.2 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 18 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 5:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  3.0 6.0 2 Open Access 0.8 1.6 2 Install Hardware 2.8 5.6 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 10.1 20.2 TOTAL FOR EACH AIRPLANE **Group 6: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 0.8 1.6 2 Install Hardware 24.3 48.6 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 31.6 63.2 TOTAL FOR EACH AIRPLANE **Group 7: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 0.3 0.6 2 Install Hardware 34.7 69.4 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 41.5 83.0 TOTAL FOR EACH AIRPLANE **Group 8: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.0 6.0 2 Open Access 0.5 1.0 2 Install Hardware

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 19 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 8:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  41.6 83.2 2 Route and Terminate Wiring 3.0 6.0 2 Close Access 0.5 1.0 2 Test 48.6 97.2 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**
+1,216.1 +1.5 810.7 DC-10-10, DC-10-15 **Group 2: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+3,841.0 +4.6 835.0 DC-10-30, DC-10-30F, DC-10-30F (KDC-10) **Group 3: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+3,831.8 +4.6 833.0 DC-10-30, DC-10-30F, DC-10-40, DC-10-40F **Group 4: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+1,841.6 +2.3 800.7 DC-10-10F **Group 5: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+3,833.2 +4.6 833.3 DC-10-30F

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 20 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 6:**  **Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW) LBS**  **Approximate Station (Inches)**  **Airplane**
+3,853.9 +4.6 837.8 DC-10-30 **Group 7: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+3,646.4 +4.3 848.0 DC-10-30F (KC-10A) **Group 8: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+4,366.1 +7.3 598.1 DC-10-30F, MD-10-30F **Group 9: Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane** 
+3,831.8 +4.6 833.0 DC-10-30

**I. Electrical Load Data** 1. Direct Current (DC) Load Changes a. Add DC loads by amounts shown below: **Group 8:**

**UNITS %OPR**  **1 100**  **E/NE E**  **VDC 28**  **VDC UNIT**  **LOAD (A)**  **0.11 NOTES**  **(B1-475) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER Lwr Aux L Fuel Pump**  **Manual Slave Relay 5D0122-1**  **ITEM 500X**  **R2- 8980A**  **CHAP 280**  **BUS DB** 

**AVERAGE AMPS % 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 21 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 8:** 

**UNITS %OPR**  **1 100**  **E/NE E**  **VDC 28**  **VDC UNIT**  **LOAD (A)**  **0.11 NOTES**  **(B1-475) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER Lwr Aux L Fuel Pump**  **Manual Slave Relay 5D0122-1**  **ITEM 500X**  **R2- 8980A**  **CHAP 280**  **BUS DB** 

**AVERAGE AMPS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0.0033 0.0011 0.11 3 1 CRUISE COLD 0.0033 0.0011 0.11 3 1 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE **Group 8:**

**UNITS %OPR**  **1 100**  **E/NE E**  **VDC 28**  **VDC UNIT**  **LOAD (A)**  **0.11 NOTES**  **(B1-475) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER Lwr Aux R Fuel Pump**  **Manual Slave Relay 5D0122-1**  **ITEM 500X**  **R2- 8981A**  **CHAP 280**  **BUS DB** 

**AVERAGE AMPS % 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 0.0033 0.0011 0.11 3 1 CRUISE COLD 0.0033 0.0011 0.11 3 1 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 DC10-28-256 22 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 2-3, 5-6, 9:** 

**UNITS %OPR**  **1 100**  **E/NE E**  **VDC 28**  **VDC UNIT**  **LOAD (A)**  **0.25 NOTES**  **(B1-475) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER R Lower Aux Pump Con**  **trol Relay 5D0397-1**  **ITEM 50X**  **R2-703 CHAP**  **280 BUS**  **DB**

**AVERAGE AMPS % 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 0.0075 0.0025 0.25 3 1 CRUISE COLD 0.0075 0.0025 0.25 3 1 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE **Group 2-3, 5-6, 9:**

**UNITS %OPR**  **1 100**  **E/NE E**  **VDC 28**  **VDC UNIT**  **LOAD (A)**  **0.25 NOTES**  **(B1-475) SUPPLIER**  **DACO EQUIPMENT NAME**  **PART NUMBER L Lower Aux Pump Con**  **trol Relay 5D0397-1**  **ITEM 50X**  **R2-704 CHAP**  **280 BUS**  **DB**

**AVERAGE AMPS % 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 0.0075 0.0025 0.25 3 1 CRUISE COLD 0.0075 0.0025 0.25 3 1 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 DC10-28-256 23 of 99 **BOEING SERVICE BULLETIN DC10-28-256**2. Alternating Current (AC) Load Changes a. Add AC loads by amounts shown below: **Group 8:**

**UNITS %OPR**  **1 100**  **E/NE/M PHASE**  **E C**  **VAC PF**  **115 VAC-1**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1206)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **R Upper Aux Pump Cont. Relay**  **5D0123-1 ITEM**  **500X R2-**  **5891 CHAP**  **280 BUS**  **11**

**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 0.15 0.2 5 3 4 CRUISE COLD 0.15 0.2 5 3 4 CRUISE HOT 0 0 0 0 0 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE **Group 8:**

**UNITS %OPR**  **1 100**  **E/NE/M PHASE**  **E C**  **VAC PF**  **115 VAC-2**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1207)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **L Upper Aux Pump Cont. Relay**  **5D0123-1 ITEM**  **500X R2-**  **5892 CHAP**  **280 BUS**  **21**

**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 0.15 0.2 5 3 4 CRUISE COLD 0.15 0.2 5 3 4 CRUISE HOT 0 0 0 0 0 DESCENT & LAND

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 24 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 8:** 

**UNITS %OPR**  **1 100**  **E/NE/M PHASE**  **E C**  **VAC PF**  **115 VAC-2**  **1 UNIT**  **LOAD (W)**  **5 NOTES**  **(B1- 1207)**  **SUPPLIER DACO**  **EQUIPMENT NAME PART NUMBER**  **L Upper Aux Pump Cont. Relay**  **5D0123-1 ITEM**  **500X R2-**  **5892 CHAP**  **280 BUS**  **21**

**AVERAGE WATTS % TIME OPR**  **15/30 M 2/5 M**  **5 S 15/30 M**  **2/5 M CONDITION**  0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE
**J. References** 1. Existing Data: a. Boeing Service Bulletin DC10-28A253. b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-08-23. c. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 06-31-00, 06-32-03 and 52-31-00. d. DC-10 Aircraft Maintenance Manual (AMM) 24-40-00 and 28-22-00. e. MD-10 Aircraft Maintenance Manual (AMM) 06-36-00, 12-11-04, 24-40-00 and 32-00-00. f. DC-10, MD-10 Fleet Team Digest (FTD) 28-13001 and DC-10, MD-10 FTD 28-13003. g. DC-10, MD-10 Structural Repair Manual (SRM) 51. h. Standard Overhaul Practices Manual (SOPM) 20-50-01. i. Standard Wiring Practices Manual (SWPM) 20-00-09, 20-00-13, 20-00-16, 20-10-01, 20-20-03, 20-31-00 and 20-50-01. 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 25 of 99 **BOEING SERVICE BULLETIN DC10-28-256 ADCN**  **DCN/REV Sheet**  **Title Drawing No**  C

- AEO ELEC INSTL - FUEL PUMP UNCOMMAND- ED SIGNAL SR10280069 D

- AEO

- B DWG

- A DWG WIRE INSTL - FUEL PUMP UNCOMMAND- ED SIGNAL SR10280070

D

- AEO ELEC INSTL - FUEL PUMP UNCOMMAND- ED SIGNAL SR10280072

- C DWG

- B DWG WIRE INSTL - FUEL PUMP UNCOMMAND- ED SIGNAL SR10280073

3. Installation Drawings Used in the Preparation of this Service Bulletin: None. 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 Fault Isolation Manual Volumes I, II & III Flight Crew Operations Manual MDC-02K1003 (ALI 20-4) 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 26 of 99 **BOEING SERVICE BULLETIN DC10-28-256 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 **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** 

$1,213.00 120 Service Kit SB10280256-3 $3,133.00 120 Service Kit SB10280256-5 $3,621.00 120 Service Kit SB10280256-7 $997.00 120 Service Kit SB10280256-9 $3,642.00 120 Service Kit SB10280256-11 $3,705.00 120 Service Kit SB10280256-13 $5,164.00 120 Service Kit SB10280256-15 $3,042.00 120 Service Kit SB10280256-17 Operators are encouraged to complete the survey provided in APPENDIX E 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 27 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 1:** 
**Kit SB10280256-3 Notes**  **Name QTY**  **Part Number** (a) SCREW 4 3D0005-08-8 (a) TERM BLOCK 4 5D0010-15 (a) END CLAMP 4 5D0101-2 (a) TRACK, TERMINAL 2 9D0090-2U PIN, T/C 1126 2 DC38-20P NUT 4 MS21042L08 WASHER 4 NAS1252-8L (b) WIRE KIT 1 SR10280072-102 (b) WIRE KIT 1 SR10280072-108 (b) WIRE KIT 1 SR10280072-112 (b) WIRE KIT 1 SR10280072-117 (b) WIRE KIT 1 SR10280072-119 (b) WIRE KIT 1 SR10280072-125 (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 -125**  **-119 -117**  **-112 -108**  **-102 SR10280072**  **Notes Name**  **QTY New Part Number**  (a) TERMINAL LUG 761 2 2 5D0086-5 (b) WIRE CODE 801 70 FT. 8 FT. 10 FT. 74 FT. 82 FT. 40 FT. D2426-1C-20NM (b) WIRE CODE 801 10 FT. D2426-1C-24NM
PIN, T/C 1126 4 DC38-20P (a) PIN T/C 601/701 1 2 2 1 2 S00023-20P (a) SKT T/C 602/702 7 1 2 S00023-20S PIN T/C 613 2 YHMM20-1F50 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 28 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 2:** 
**Kit SB10280256-5 Notes**  **Name QTY**  **Part Number** (a) SCREW 2 3D0005-08-11 (a) SCREW 4 3D0005-08-12 (a) SCREW 4 3D0005-08-8 (a) TERM BLOCK 4 5D0010-15 (a) END CLAMP 4 5D0101-2 (a) RELAY 2 5D0397-1 (a) TRACK, TERMINAL 2 9D0090-2U PIN, T/C 1126 4 DC38-20P RIVET 8 MS20470AD3-3D NUT 4 MS21042L08 LOCKWASHER 6 MS35338-42 WASHER 10 NAS1252-8L RIVNUT 2 NAS1329S08K75 NUTPLATE 4 NAS1474A08 (b) WIRE KIT 1 SR10280072-103 (b) WIRE KIT 1 SR10280072-109 (b) WIRE KIT 1 SR10280072-113 (b) WIRE KIT 1 SR10280072-117 (b) WIRE KIT 1 SR10280072-120 (b) WIRE KIT 1 SR10280072-123 (b) WIRE KIT 1 SR10280072-126 TERM BLOCK 3 YHLZ44 (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 -126**  **-123 -120**  **-117 -113**  **-109 -103**  **SR10280072 Notes**  **Name QTY**  **Number** (a) DIODE 2 5D0013-2A (a) TERMINAL LUG 761 4 6 2 5D0086-5

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 29 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 2:** 
**Wire Kit Table -126**  **-123 -120**  **-117 -113**  **-109 -103**  **SR10280072 Notes**  **Name QTY**  **Number** (a) TERMINAL LUG 762 1 1 5D0086-6 (b) WIRE CODE 801 5 FT. D2426-1C-16NM (b) WIRE CODE 801 130 FT. 31 FT. 34 FT. 10 FT. 147 FT. 164 FT. 80 FT. D2426-1C-20NM (b) WIRE CODE 801 15 FT. 5 FT. D2426-1C-24NM
PIN, T/C 1126 4 3 1 DC38-20P PIN T/C 1003 1 LRM16W-2DE5 (a) PIN T/C 601/701 2 2 4 2 2 4 S00023-20P (a) SKT T/C 602/702 10 5 1 4 S00023-20S PIN T/C 612 1 4 YHMM16-3F50 PIN T/C 613 1 1 4 YHMM20-1F50 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. **Group 3, 9:**
**Kit SB10280256-7 Notes**  **Name QTY**  **Part Number** (a) SCREW 2 3D0005-08-11 (a) SCREW 4 3D0005-08-12 (a) SCREW 4 3D0005-08-8 (a) TERM BLOCK 4 5D0010-15 (a) END CLAMP 4 5D0101-2 (a) RELAY 2 5D0397-1 (a) TRACK, TERMINAL 2 9D0090-2U PIN, T/C 1126 4 DC38-20P RIVET 8 MS20470AD3-3D NUT 4 MS21042L08 LOCKWASHER 6 MS35338-42 WASHER 10 NAS1252-8L RIVNUT 2 NAS1329S08K75

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**Kit SB10280256-7 Notes**  **Name QTY**  **Part Number** NUTPLATE 4 NAS1474A08 (a) WIRE KIT 1 SR10280072-103 (b) WIRE KIT 1 SR10280072-110 (b) WIRE KIT 1 SR10280072-114 (b) WIRE KIT 1 SR10280072-117 (b) WIRE KIT 1 SR10280072-120 (b) WIRE KIT 1 SR10280072-123 (b) WIRE KIT 1 SR10280072-127 TERM BLOCK 3 YHLZ44 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to wire kit table below for wire kit contents. **Group 3, 9:**
**Wire Kit Table -127**  **-123 -120**  **-117 -114**  **-110 -103**  **SR10280072 Notes**  **Name QTY**  **New Part Number** (a) DIODE 2 5D0013-2A (a) TERMINAL LUG 761 4 6 2 5D0086-5 (a) TERMINAL LUG 762 1 1 5D0086-6 (b) WIRE CODE 801 5 FT. D2426-1C-16NM (b) WIRE CODE 801 130 FT. 31 FT. 34 FT. 10 FT. 147 FT. 164 FT. 80 FT. D2426-1C-20NM (b) WIRE CODE 801 10 FT. 10 FT. D2426-1C-24NM
PIN, T/C 1126 6 2 DC38-20P PIN T/C 1003 1 LRM16W-2DE5 (a) PIN T/C 601/701 2 2 4 2 2 4 S00023-20P (a) SKT T/C 602/702 12 4 4 S00023-20S PIN T/C 612 1 4 YHMM16-3F50 PIN T/C 613 1 1 4 YHMM20-1F50 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 31 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 4:** 
**Kit SB10280256-9 Notes**  **Name QTY**  **Part Number** (a) TERM BLOCK 3 5D0010-15 PIN, T/C 1126 4 DC38-20P (b) WIRE KIT 1 SR10280072-104 (b) WIRE KIT 1 SR10280072-111 (b) WIRE KIT 1 SR10280072-115 (b) WIRE KIT 1 SR10280072-117 (b) WIRE KIT 1 SR10280072-119 (b) WIRE KIT 1 SR10280072-128 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to wire kit table below for wire kit contents. **Group 4:**
**Wire Kit Table -128**  **-119 -117**  **-115 -111**  **-104 SR10280072**  **Notes Name**  **QTY New Part Number**  (a) TERMINAL LUG 761 2 2 5D0086-5 (b) WIRE CODE 801 70 FT. 8 FT 10 FT. 147 FT. 164 FT. 84 FT. D2426-1C-20NM (b) WIRE CODE 801 10 FT. D2426-1C-24NM
PIN, T/C 1126 8 DC38-20P SOCKET T/C 706 2 LRC16M-32DJ5 (a) PIN T/C 601/701 2 2 2 2 4 S00023-20P (a) SKT T/C 602/702 6 2 4 S00023-20S PIN T/C 611 2 YHMM22-2DB8 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. **Group 5:**
**Kit SB10280256-11 Notes**  **Name QTY**  **Part Number** (a) SCREW 2 3D0005-08-11

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**Kit SB10280256-11 Notes**  **Name QTY**  **Part Number** (a) SCREW 4 3D0005-08-12 (a) SCREW 4 3D0005-08-8 (a) TERM BLOCK 4 5D0010-15 (a) END CLAMP 4 5D0101-2 (a) RELAY 2 5D0397-1 (a) TRACK, TERMINAL 2 9D0090-2U PIN, T/C 1126 4 DC38-20P RIVET 8 MS20470AD3-3D NUT 4 MS21042L08 LOCKWASHER 6 MS35338-42 WASHER 10 NAS1252-8L RIVNUT 2 NAS1329S08K75 NUTPLATE 4 NAS1474A08 (b) WIRE KIT 1 SR10280072-105 (b) WIRE KIT 1 SR10280072-110 (b) WIRE KIT 1 SR10280072-114 (b) WIRE KIT 1 SR10280072-117 (b) WIRE KIT 1 SR10280072-120 (b) WIRE KIT 1 SR10280072-123 (b) WIRE KIT 1 SR10280072-127 TERM BLOCK 3 YHLZ44 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to wire kit table below for wire kit contents. **Group 5:**
**Wire Kit Table -127**  **-123 -120**  **-117 -114**  **-110 -105**  **SR10280072 Notes**  **Name QTY**  **New Part Number** (a) DIODE 2 5D0013-2A (a) TERMINAL LUG 761 4 6 2 5D0086-5 (a) TERMINAL LUG 762 1 1 5D0086-6

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 33 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 5:** 
**Wire Kit Table -127**  **-123 -120**  **-117 -114**  **-110 -105**  **SR10280072 Notes**  **Name QTY**  **New Part Number** (b) WIRE CODE 801 5 FT. D2426-1C-16NM (b) WIRE CODE 801 130 FT. 31 FT. 34 FT. 10 FT. 147 FT. 164 FT. 80 FT. D2426-1C-20NM (b) WIRE CODE 801 10 FT. 10 FT. D2426-1C-24NM
PIN, T/C 1126 6 2 DC38-20P PIN T/C 1003 1 LRM16W-2DE5 (a) PIN T/C 601/701 2 2 4 2 2 4 S00023-20P (a) SKT T/C 602/702 12 4 4 S00023-20S PIN T/C 612 1 4 YHMM16-3F50 PIN T/C 613 1 1 4 YHMM20-1F50 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. **Group 6:**
**Kit SB10280256-13 Notes**  **Name QTY**  **New Part Number** (a) SCREW 2 3D0005-08-11 (a) SCREW 4 3D0005-08-12 (a) SCREW 4 3D0005-08-8 (a) TERM BLOCK 6 5D0010-15 (a) END CLAMP 4 5D0101-2 (a) RELAY 2 5D0397-1 (a) TRACK, TERMINAL 2 9D0090-2U PIN, T/C 1126 12 DC38-20P RIVET 8 MS20470AD3-3D NUT 4 MS21042L08 LOCKWASHER 6 MS35338-42 WASHER 10 NAS1252-8L RIVNUT 2 NAS1329S08K75 NUTPLATE 4 NAS1474A08

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**Kit SB10280256-13 Notes**  **Name QTY**  **New Part Number** (b) WIRE KIT 1 SR10280072-106 (b) WIRE KIT 1 SR10280072-110 (b) WIRE KIT 1 SR10280072-114 (b) WIRE KIT 1 SR10280072-117 (b) WIRE KIT 1 SR10280072-120 (b) WIRE KIT 1 SR10280072-123 (b) WIRE KIT 1 SR10280072-127 TERM BLOCK 3 YHLZ44 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to wire kit table(s) below for wire kit contents. **Group 6:**
**Wire Kit Table -127**  **-123 -120**  **-117 -114**  **-110 -106**  **SR10280072 Notes**  **Name QTY**  **New Part Number** (a) DIODE 2 5D0013-2A (a) TERMINAL LUG 761 4 6 2 5D0086-5 (a) TERMINAL LUG 762 1 1 5D0086-6 (b) WIRE CODE 801 5 FT. D2426-1C-16NM (b) WIRE CODE 801 130 FT. 31 FT. 34 FT. 10 FT. 147 FT. 164 FT. 80 FT. D2426-1C-20NM (b) WIRE CODE 801 10 FT. 10 FT. D2426-1C-24NM
PIN, T/C 1126 6 2 4 DC38-20P PIN T/C 1003 1 LRM16W-2DE5 (a) PIN T/C 601/701 2 2 4 2 2 4 S00023-20P (a) SKT T/C 602/702 12 4 4 S00023-20S PIN T/C 612 1 4 YHMM16-3F50 PIN T/C 613 1 1 YHMM20-1F50 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13.

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**Kit SB10280256-15 Notes**  **Name QTY**  **New Part Number** (a) SCREW 4 3D0005-08-8 (a) TERM BLOCK 6 5D0010-15 (a) END CLAMP 4 5D0101-2 (a) TRACK, TERMINAL 2 9D0090-2U PIN, T/C 1126 11 DC38-20P NUT 4 MS21042L08 WASHER 8 NAS1252-8L (b) WIRE KIT 1 SR10280072-101 (b) WIRE KIT 1 SR10280072-107 (b) WIRE KIT 1 SR10280072-110 (b) WIRE KIT 1 SR10280072-116 (b) WIRE KIT 1 SR10280072-118 (b) WIRE KIT 1 SR10280072-121 (b) WIRE KIT 1 SR10280072-124 (b) WIRE KIT 1 SR10280072-129 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to wire kit table below for wire kit contents. **Group 7:**
**Wire Kit Table -129**  **-124 -121**  **-118 -116**  **-110 -107**  **-101 SR10280072**  **Notes Name**  **QTY New Part Number**  (a) TERMINAL LUG 761 2 4 4 2 5D0086-5 (a) TERMINAL LUG 762 1 5D0086-6 (a) PIN T/C 1005 2 5D0187-2222P (b) WIRE CODE 801 175 FT. 14 FT. 16 FT. 20 FT. 334 FT. 164 FT. 120 FT. 14 FT. D2426-1C-20NM (b) WIRE CODE 801 10 FT. D2426-1C-22NM (b) WIRE CODE 801 10 FT. 15 FT. D2426-1C-24NM
PIN, T/C 1126 7 3 6 DC38-20P

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 36 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 7:** 
**Wire Kit Table -129**  **-124 -121**  **-118 -116**  **-110 -107**  **-101 SR10280072**  **Notes Name**  **QTY New Part Number**  (a) PIN T/C 601/701 4 2 4 4 4 4 2 S00023-20P (a) SKT T/C 602/702 15 8 6 S00023-20S PIN T/C 613 2 YHMM20-1F50 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. **Group 8:**
**Kit SB10280256-17 Notes**  **Name QTY**  **New Part Number** (a) SCREW 4 3D0005-04-9 (a) SCREW 2 3D0005-08-11 (a) SCREW 2 3D0005-3-11 (a) CLIPNUT 4 3D0191-04 (a) TERM BLOCK 2 5D0107-1 (a) RELAY 2 5D0122-1 (a) RELAY 2 5D0123-1 (a) TERMINAL 1 5D0518-4 PIN, T/C 1131 4 DC38-16P PIN, T/C 1147 4 M39029/1-101 LOCKWASHER 2 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 2 NAS1252-10L WASHER 4 NAS1252-4L WASHER 2 NAS1252-8L RIVNUT 2 NAS1329S08K75 (b) WIRE KIT 1 SR10280069-101 (b) WIRE KIT 1 SR10280069-102 (b) WIRE KIT 1 SR10280069-103 (b) WIRE KIT 1 SR10280069-104 (b) WIRE KIT 1 SR10280069-105

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 37 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 8:** 
**Kit SB10280256-17 Notes**  **Name QTY**  **New Part Number** (b) WIRE KIT 1 SR10280069-106 (b) WIRE KIT 1 SR10280069-107 (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Refer to wire kit table below for wire kit contents. **Group 8:**
**Wire Kit Table -107**  **-106 -105**  **-104 -103**  **-102 -101**  **Kit SR10280069 Notes**  **Name QTY**  **New Part Number** (a) DIODE 2 5D0013-2A (a) TERMINAL LUG 764 2 5D0086-24 (a) TERMINAL LUG 766 4 5D0086-26 (a) TERMINAL LUG 761 2 2 5D0086-5 (a) TERMINAL LUG 762 1 1 5D0086-6 (a) PIN T/C 1005 4 5D0187-2222P SOCKET T/C 487 2 617220 PIN T/C 579 5 617240 SOCKET T/C 486 1 1 617320 SOCKET T/C 578 5 617340 RELAY SOCKET 2 65009-020-513 RECEPTACLE 2 CL3-1007-162 (b) WIRE CODE 801 44 FT. 2 FT. 84 FT. 217 FT. 332 FT. D2426-1C-16NM (b) WIRE CODE 801 38 FT. 7 FT. 7 FT. 84 FT. 109 FT. 109 FT. 21 FT. D2426-1C-20NM (b) WIRE CODE 801 34 FT. D2426-1C-24NM
PIN, T/C 1131 7 DC38-16P SOCKET T/C 706 13 LRC16M-32DJ5 PIN T/C 705 2 2 LRM16M-32DJ5 CONN SKT T/C 1004 3 1 2 LRC16W2 PIN T/C 1003 3 2 LRM16W-2DE5

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 38 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 8:** 
**Wire Kit Table -107**  **-106 -105**  **-104 -103**  **-102 -101**  **Kit SR10280069 Notes**  **Name QTY**  **New Part Number** PIN T/C 1147 19 M39029/1-101 CONTACT T/C 542/546 8 M39029/22-193 (a) PIN T/C 601/701 2 1 1 S00023-20P (a) SKT T/C 602/702 2 1 1 S00023-20S (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Or approved alternate. Refer to SWPM 20-00-13. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) TIE TAPE As Required DMS 2089 (18XTZ), (23XTZ) or Equivalent (b) Coating, Chemical Conversion As Required Alodine 1200S (DPM 1453-5) or Equivalent (a) Primer, Fluid Resistant As Required DMS 1786 (Koropon 515-700 with Catalyst910- 704) or Equivalent(a) Can be purchased from: Gudebrod, Incorporated, 274 Shoemaker Road, Pottstown, Pennsylvania, 19464, CAGE 82110 (b) Can be purchased from: Henkel Corporation, 32100 Stephenson Highway, Madison Heights, Michigan, 48071, CAGE 1N6B3

3. Parts Modified and Reidentified None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 39 of 99 **BOEING SERVICE BULLETIN DC10-28-256**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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 40 of 99 **BOEING SERVICE BULLETIN DC10-28-256 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 DC-10, MD-10 SRM 51. 4. If the length of any fastener specified in this service bulletin does not meet the installation standards in Structural Repair Manual (SRM) Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards 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 DC-10, MD-10 SRM 51. • Torque limits to tighten nuts and bolts are in DC-10, MD-10 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 DC10-28-256 41 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Title**  **Chapter** GENERAL MAINTENANCE PRACTICES - ELECTRICAL SWPM 20-00-09ELECTRICAL WIRE CODES SWPM 20-00-13ELECTRICAL WIRE END TERMINATION CODES AND TOOL CODES SWPM 20-00-16

WIRING INSTALLATION - MAINTENANCE PRACTICES SWPM 20-10-01GENERAL INSTALLATIONS HARDWARE - MAINTENANCE PRACTICES SWPM 20-20-03

ELECTRICAL CONNECTORS - MAINTENANCE PRACTICES SWPM 20-31-00ELECTRICAL 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. **Group 1-7, 9:** Review and understand all general notes of Service Rework Drawings SR10280072 sheets 3, 3.1, 3.2, 3.3 and SR10280073 sheet 1. **Group 8:** Review and understand all general notes of Service Rework Drawings SR10280069 sheets 3, 3.1, 3.2, 3.3, 3.4 and SR10280070 sheet 1. **B. WORK INSTRUCTIONS** 1. Gain access:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 42 of 99 **BOEING SERVICE BULLETIN DC10-28-256**a. Open access doors in the table as follow:
**Reference Location/Description**  **Access Door** DC-10, MD-10 AMM 06-31-00 Avionics Equipment Compartment 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 DC-10, MD-10 AMM 52-31-00 as an accepted procedure. c. Remove/Keep forward cargo compartment ceiling panels and attaching hardware, left and right sides between stations Y=595.000 and Y=1099.000. Refer to DC-10, MD-10 AMM 06-32-03. 2. Install electrical equipment in accordance with the table(s) as follow: **Group 1, 7:**
**Sheets Drawing**  12-13 SR10280072 **Group 2-3, 5-6, 9:**
**Sheets Drawing**  12-15 SR10280072 **Group 4:** None. **Group 8:**
**Sheets Drawing**  8, 12-15 SR10280069 3. Route wiring in accordance with the table(s) as follow: **Group 1, 4:**
**Additional Data Sheet(s)**  **Drawing** 1-9, 11 SR10280073 Views G, AN, AU 10 SR10280073

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 43 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 2, 5-6:** 
**Additional Data Sheet(s)**  **Drawing** 1-9, 11 SR10280073 Views AM, AN, AP, AR AU, AZ 10 SR10280073 **Group 3, 9:**
**Additional Data Sheet(s)**  **Drawing** 1-9, 11 SR10280073 Views AM, AN, AP, AS, AV, AZ 10 SR10280073 **Group 7:**
**Additional Data Sheet(s)**  **Drawing** 1-9, 11 SR10280073 Views G, AM, AN, AP, AT, AY 10 SR10280073 **Group 8:**
**Additional Data Sheet(s)**  **Drawing** 1-11 SR10280070 4. Terminate wiring in accordance with the table(s) as follow: **Group 1:**
**Sheet Drawing**  6.10, 102.201, 108.201, 112.201, 117.201, 119.201, 125.201, 306.201, 310.201 SR10280072

**Group 2:**
**Sheets Drawing**  6.9, 6.11, 6.12, 103.201, 109.201, 113.201, 117.201, 120.201, 123.201, 126.201, 307.201, 311.201, 315.201, 316.201 SR10280072

**Group 3, 9:**
**Sheets Drawing**  6.9, 6.13, 6.14, 103.201, 110.201, 114.201, 117.201, 120.201, 123.201, 127.201, 308.201, 312.201, 315.201, 316.201 SR10280072

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 44 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Group 4:** 
**Sheet Drawing**  6.15, 104.201, 111.201, 115.201, 117.201, 119.201, 128.201, 303.201, 317.201 SR10280072

**Group 5:**
**Sheets Drawing**  6.9, 6.16, 6.17, 105.201, 110.201, 114.201, 117.201, 120.201, 123.201, 127.201, 309.201, 313.201, 315.201-316.201 SR10280072

**Group 6:**
**Sheets Drawing**  6.9, 6.18, 6.19, 106.201, 110.201, 114.201, 117.201, 120.201, 123.201, 127.201, 301.201, 304.201, 309.201, 313.201, 315.201- 316.201 SR10280072

**Group 7:**
**Sheets Drawing**  6.20, 6.21, 6.22, 101.201, 107.201, 110.201, 116.201, 118.201, 121.201, 124.201, 129.201, 302.201, 305.201, 307.201, 314.201 SR10280072

**Group 8:**
**Sheets Drawing**  6.1 - 6.4, 101.201-107.201, 301.201, 303.201-307.201 SR10280069
5. Test: **Group 1, 4:** Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX A. **Group 2-3, 5-6:** Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX B. **Group 7:** Test Fuel Pumps Uncommanded On Detection Circuit in accordance with DC-10 AMM 28-22-00. **Group 8:** Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX D. **Group 9:** Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX C.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 45 of 99 **BOEING SERVICE BULLETIN DC10-28-256**6. Close access: a. Install/Kept forward cargo compartment ceiling panels and attaching hardware, left and right sides between stations Y=595.000 and Y=1099.000. Refer to DC-10, MD-10 AMM 06-32-03. b. Close forward cargo compartment door. Refer to DC-10, MD-10 AMM 52-31-00 as an accepted procedure. c. Close access doors in the table as follow:
**Reference Location/Description**  **Access Door** DC-10, MD-10 AMM 06-31-00 Avionics Equipment Compartment 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 DC10-28-256 46 of 99 **BOEING SERVICE BULLETIN DC10-28-256 This Appendix applies only to: Group 1, 4.**  **WARNING:**THIS TEST PROCEDURE DEALS WITH HIGH VOLTAGE AC POWER. USE OF EXTREME CAUTION IS ADVISED OR INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. 1. Test Equipment: a. An electrical wire jumper, two feet long, with each end soldered to 0.062 +/- .001 DIA pin. 2. Test Procedure for DC-10-10, DC-10-10F, and DC-10-15 Airplanes with Aux Tank: a. Test Setup: (1) Energize aircraft electrical busses with external electrical power. Refer to DC-10 AMM 24-40-00 as an accepted procedure. (2) On the Upper Main Circuit Breaker Panel open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R B1-1250 23 B FUEL PUMP CONTROL AUX TANK R B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L B1-1248 23 C FUEL PUMP CONTROL AUX TANK L B1-1207 23 F b. Right Aux Tank Pump M1-91 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the RIGHT FUEL PUMP AUX TANK switch (S1-838) to OFF position. (2) In the Avionics Compartment at the AFT RELAY PANEL Z112FZ remove the R AUX PUMP SLAVE CONTROL RELAY (R2-5219) from its receptacle (R5-5219). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

**APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 1 OF 6)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 47 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R B1-1206 23 E (5) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R B1-1206 23 E (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO" light is OFF. (8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 1 Name**  **Number Column**  **Row** R AUX PUMP PRESS LOW LT B1-1246 25 H (9) Remove the jumper from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 1 Name**  **Number Column**  **Row** R AUX PUMP PRESS LOW LT B1-1246 25 H (12) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "TANK PUMP PRESS LO" light is illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 1 Name**  **Number Column**  **Row** R AUX PUMP PRESS LOW LT B1-1246 25 H

**APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 2 OF 6)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 48 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO" light is OFF. (15) Remove the jumper from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (16) At the AFT RELAY PANEL Z112FZ install the R AUX PUMP SLAVE CONTROL RELAY (R2-5219) to its receptacle (R5-5219). (17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 1 Name**  **Number Column**  **Row** R AUX PUMP PRESS LOW LT B1-1246 25 H (18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R B1-1206 23 E (19) Onthe Flight Engineer's Fuel Panel set the RIGHT FUEL PUMP CONTROL AUX TANK switch (S1-838) to ON position. (20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO" light is illuminated. (21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R B1-1206 23 E (22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO" light is OFF. (23) On the Flight Engineer's Fuel Panel set the RIGHT FUEL PUMP AUX TANK switch (S1-838) to OFF position. c. Left Aux Tank Pump M1-92 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the LEFT FUEL PUMP AUX TANK switch (S1-839) to OFF position.

**APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 3 OF 6)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 49 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(2) At the AFT RELAY PANEL Z112FZ remove the L AUX PUMP SLAVE CONTROL RELAY (R2-5220) from its receptacle (R5-5220). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L B1-1207 23 F (5) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L B1-1207 23 F (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO" light is OFF. (8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 2 Name**  **Number Column**  **Row** L AUX PUMP PRESS LOW LT B1-1247 25 J (9) Remove the jumper from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 2 Name**  **Number Column**  **Row** L AUX PUMP PRESS LOW LT B1-1247 25 J

**APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 4 OF 6)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 50 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(12) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO" light is illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 2 Name**  **Number Column**  **Row** L AUX PUMP PRESS LOW LT B1-1247 25 J (14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO" light is OFF. (15) Remove the jumper from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (16) At the AFT RELAY PANEL Z112FZ install the L AUX PUMP SLAVE CONTROL RELAY (R2-5220) to its receptacle (R5-5220). (17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL DC BUS 2 Name**  **Number Column**  **Row** L AUX PUMP PRESS LOW LT B1-1247 25 J (18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L B1-1207 23 F (19) On the Flight Engineer's Fuel Panel set the LEFT FUEL PUMP CONTROL AUX TANK switch (S1-839) to ON position. (20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO" light is illuminated. (21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L B1-1207 23 F

**APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 5 OF 6)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 51 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO" light is OFF. (23) On the Flight Engineer's Fuel Panel set the LEFT FUEL PUMPS AUX TANKS switch (S1-839) to OFF position. d. Test Closeout: (1) On the Upper Main Circuit Breaker Panel close circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R B1-1250 23 B FUEL PUMP CONTROL AUX TANK R B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L B1-1248 23 C FUEL PUMP CONTROL AUX TANK L B1-1207 23 F

**APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 6 OF 6)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 52 of 99 **BOEING SERVICE BULLETIN DC10-28-256 This Appendix applies only to: Group 2-3, 5-6.**  **WARNING:**THIS TEST PROCEDURE DEALS WITH HIGH VOLTAGE AC POWER. USE OF EXTREME CAUTION IS ADVISED OR INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. 1. Test Equipment: a. An electrical wire jumper, two feet long, with each end soldered to 0.062 +/- .001 DIA pin. 2. Test Procedure for DC-10-30, DC-10-30F, DC-10-30F (KDC-10), DC-10-40, and DC-10-40F Airplanes: a. Test Setup: (1) Energize aircraft electrical busses with external electrical power. Refer to DC-10 AMM 24-40-00 as an accepted procedure. (2) On the Upper Main Circuit Breaker Panel open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G b. Right Upper Aux Tank Pump M1-91 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to OFF position.

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 1 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 53 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(2) In the Avionics Compartment at the AFT RELAY PANEL Z112FZ remove the UPPER R AUX PUMP SLAVE CONTROL RELAY (R2-5219) from its receptacle (R5-5219). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is OFF. (8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, DC BUS 1 Name**  **Number Column**  **Row** R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H (9) Remove the jumper from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, DC BUS 1 Name**  **Number Column**  **Row** R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 2 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 54 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(12) Onthe Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS LO" light is illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, DC BUS 1 Name**  **Number Column**  **Row** R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H (14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is OFF. (15) Remove the jumper from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (16) At the AFT RELAY PANEL Z112FZ install the UPPER R AUX PUMP SLAVE CONTROL RELAY (R2-5219) to its receptacle (R5-5219). (17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, DC BUS 1 Name**  **Number Column**  **Row** R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H (18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (19) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to UPR position. (20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is illuminated. (21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 3 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 55 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is OFF. (23) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to OFF position. c. Left Upper Aux Tank Pump M1-92 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to OFF position. (2) At the AFT RELAY PANEL Z112FZ remove the UPPER L AUX PUMP SLAVE CONTROL RELAY (R2-5220) from its receptacle (R5-5220). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Left "UPR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is OFF. (8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, DC BUS 2 Name**  **Number Column**  **Row** L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (9) Remove the jumper from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ.

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 4 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 56 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, DC BUS 2 Name**  **Number Column**  **Row** L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (12) Onthe Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS LO" light is illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, DC BUS 2 Name**  **Number Column**  **Row** L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is OFF. (15) Remove the jumper from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (16) At the AFT RELAY PANEL Z112FZ install the UPPER L AUX PUMP SLAVE CONTROL RELAY (R2-5220) to its receptacle (R5-5220). (17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, DC BUS 2 Name**  **Number Column**  **Row** L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (19) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to UPR position.

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 5 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 57 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is illuminated. (21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is OFF. (23) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to OFF position. d. Right Lower Aux Tank Pump M1-93 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to OFF position. (2) At the AFT RELAY PANEL Z112FZ remove the LOWER R AUX PUMP SLAVE CONTROL RELAY (R2-5221) from its receptacle (R5-5221). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5221 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "LWR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" light is OFF.

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 6 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 58 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(8) Remove the jumper from pin A1 to pin A2 of the R5-5221 receptacle located in the AFT RELAY PANEL Z112FZ. (9) At the AFT RELAY PANEL Z112FZ install the LOWER R AUX PUMP SLAVE CONTROL RELAY (R2-5221) to its receptacle (R5-5221). (10) At the Upper Main Circuit Breaker Panel close 5A circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (11) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to ALL position. (12) Onthe Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights are illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (14) Onthe Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights remain illuminated. (15) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to OFF position. (16) Onthe Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights are OFF. (17) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 7 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 59 of 99 **BOEING SERVICE BULLETIN DC10-28-256**e. Left Lower Aux Tank Pump M1-94 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to OFF position. (2) At the AFT RELAY PANEL Z112FZ remove the LOWER L AUX PUMP SLAVE CONTROL RELAY (R2-5222) from its receptacle (R5-5222). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5222 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A 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 (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Left "LWR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A 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 (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" light is OFF. (8) Remove the jumper from pin A1 to pin A2 of the R5-5222 receptacle located in the AFT RELAY PANEL Z112FZ. (9) At the AFT RELAY PANEL Z112FZ install the LOWER L AUX PUMP SLAVE CONTROL RELAY (R2-5222) to its receptacle (R5-5222). (10) At the Upper Main Circuit Breaker Panel close 5A circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 8 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 60 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 2** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F (11) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to ALL position. (12) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" and Aux Tank Left "UPR TANK PUMP PRESS LO" lights are illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A 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) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" and Aux Tank Left "UPR TANK PUMP PRESS LO" lights remain illuminated. (15) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to OFF position. (16) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" and Aux Tank Left "UPR TANK PUMP PRESS LO" lights are OFF. (17) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F
f. Test Closeout: (1) On the Upper Main Circuit Breaker Panel close circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 9 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 61 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 2** **Name Number**  **Column Row**  FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G

**APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 10 OF 10)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 62 of 99 **BOEING SERVICE BULLETIN DC10-28-256 This Appendix applies only to: Group 9.**  **WARNING:**THIS TEST PROCEDURE DEALS WITH HIGH VOLTAGE AC POWER. USE OF EXTREME CAUTION IS ADVISED OR INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. 1. Test Equipment: a. An electrical wire jumper, two feet long, with each end soldered to 0.062 +/- .001 DIA pin. 2. Test Procedure for DC-10-30 Airplanes with Aft Aux Tank: a. Test Setup: (1) Energize aircraft electrical busses with external electrical power. Refer to DC-10 AMM 24-40-00 as an accepted procedure. (2) On the Upper Main Circuit Breaker Panel open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L AFT B1-1647 22 B FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP CONTROL AUX TANK L AFT B1-1645 22 E FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R AFT B1-1646 22 D FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D FUEL PUMP CONTROL AUX TANK R AFT B1-1644 22 G FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 1 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 63 of 99 **BOEING SERVICE BULLETIN DC10-28-256**b. Right Upper Aux Tank Pump M1-91 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to OFF position. (2) In the Avionics Compartment at the AFT RELAY PANEL Z112FZ remove the UPPER R AUX PUMP SLAVE CONTROL RELAY (R2-5219) from its receptacle (R5-5219). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is OFF. (8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
**Name Number**  **Column Row**  R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H (9) Remove the jumper from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
**Name Number**  **Column Row**  R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 2 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 64 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(12) Onthe Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS LO" light is illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
**Name Number**  **Column Row**  R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H (14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is OFF. (15) Remove the jumper from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY PANEL Z112FZ. (16) At the AFT RELAY PANEL Z112FZ install the UPPER R AUX PUMP SLAVE CONTROL RELAY (R2-5219) to its receptacle (R5-5219). (17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
**Name Number**  **Column Row**  R AUX UPR & LWR PRESS LOW LTS B1-1246 25 H (18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (19) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to UPR position. (20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is illuminated. (21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E (22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS LO" light is OFF.

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 3 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 65 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(23) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to OFF position. c. Left Upper Aux Tank Pump M1-92 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP L switch (S1-720) to OFF position. (2) At the AFT RELAY PANEL Z112FZ remove the UPPER L AUX PUMP SLAVE CONTROL RELAY (R2-5220) from its receptacle (R5-5220). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Left "UPR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is OFF. (8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
**Name Number**  **Column Row**  L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (9) Remove the jumper from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 4 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 66 of 99 **BOEING SERVICE BULLETIN DC10-28-256 Name**  **Number Column**  **Row** L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (12) Onthe Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS LO" light is illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
**Name Number**  **Column Row**  L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is OFF. (15) Remove the jumper from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY PANEL Z112FZ. (16) At the AFT RELAY PANEL Z112FZ install the UPPER L AUX PUMP SLAVE CONTROL RELAY (R2-5220) to its receptacle (R5-5220). (17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
**Name Number**  **Column Row**  L AUX UPR & LWR PRESS LOW LTS B1-1247 25 J (18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F (19) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP L switch (S1-720) to UPR position. (20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is illuminated. (21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 5 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 67 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS LO" light is OFF. (23) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP L switch (S1-720) to OFF position. d. Right Lower Aux Tank Pump M1-93 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to OFF position. (2) At the AFT RELAY PANEL Z112FZ remove the LOWER R AUX PUMP SLAVE CONTROL RELAY (R2-5221) from its receptacle (R5-5221). (3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5221 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "LWR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" light is OFF. (8) Remove the jumper from pin A1 to pin A2 of the R5-5221 receptacle located in the AFT RELAY PANEL Z112FZ. (9) At the AFT RELAY PANEL Z112FZ install the LOWER R AUX PUMP SLAVE CONTROL RELAY (R2-5221) to its receptacle (R5-5221). (10) At the Upper Main Circuit Breaker Panel close 5A circuit breakers as follow:

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 6 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 68 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (11) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to BOTH position. (12) Onthe Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights are illuminated. (13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G (14) Onthe Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights remain illuminated. (15) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to OFF position. (16) Onthe Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights are OFF. (17) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E e. Left Lower Aux Tank Pump M1-94 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP L switch (S1-720) to OFF position. (2) At the AFT RELAY PANEL Z112FZ remove the LOWER L AUX PUMP SLAVE CONTROL RELAY (R2-5222) from its receptacle (R5-5222).

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 7 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 69 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5222 receptacle located in the AFT RELAY PANEL Z112FZ. (4) At the Upper Main Circuit Breaker Panel close 5A 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 (5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Left "LWR TANK PUMP PRESS LO" light is illuminated. (6) At the Upper Main Circuit Breaker Panel open 5A 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 (7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" light is OFF. (8) Remove the jumper from pin A1 to pin A2 of the R5-5222 receptacle located in the AFT RELAY PANEL Z112FZ. (9) At the AFT RELAY PANEL Z112FZ install the LOWER L AUX PUMP SLAVE CONTROL RELAY (R2-5222) to its receptacle (R5-5222). (10) At the Upper Main Circuit Breaker Panel close 5A circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F (11) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP L switch (S1-720) to BOTH position. (12) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" and Left "UPR TANK PUMP PRESS LO" lights are illuminated.

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 8 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 70 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(13) At the Upper Main Circuit Breaker Panel open 5A 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) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" and Aux Tank Left "UPR TANK PUMP PRESS LO" lights remain illuminated. (15) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP L switch (S1-720) to OFF position. (16) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS LO" and Aux Tank Left "UPR TANK PUMP PRESS LO" lights are OFF. (17) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F f. Right Aft Aux Tank Pump M1-168 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the AFT TANK PUMP R switch (S1-682) to OFF position. (2) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R AFT B1-1644 22 G (3) On the Flight Engineer's Fuel Panel set the AFT TANK PUMP R switch (S1-682) to OVRD position. (4) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "AFT TANK PUMP PRESS LO" light is illuminated. (5) On the Flight Engineer's Fuel Panel set the AFT TANK PUMP R switch (S1-682) to OFF position. (6) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "AFT TANK PUMP PRESS LO" light is OFF. (7) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 9 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 71 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R AFT B1-1644 22 G g. Left Aft Aux Tank Pump M1-169 Uncommanded On Detection Circuit Test Procedure: (1) On the Flight Engineer's Fuel Panel set the AFT TANK PUMP L switch (S1-966) to OFF position. (2) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L AFT B1-1645 22 E (3) On the Flight Engineer's Fuel Panel set the AFT TANK PUMP L switch (S1-966) to OVRD position. (4) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "AFT TANK PUMP PRESS LO" light is illuminated. (5) On the Flight Engineer's Fuel Panel set the AFT TANK PUMP L switch (S1-966) to OFF position. (6) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "AFT TANK PUMP PRESS LO" light is OFF. (7) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L AFT B1-1645 22 E
h. Test Closeout: (1) On the Upper Main Circuit Breaker Panel close circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L AFT B1-1647 22 B FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP CONTROL AUX TANK L AFT B1-1645 22 E

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 10 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 72 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 1**  **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R UPR & LWR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP CONTROL AUX TANK L UPR & LWR B1-1207 22 F FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R AFT B1-1646 22 D FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D FUEL PUMP CONTROL AUX TANK R AFT B1-1644 22 G FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G

**APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE (SHEET 11 OF 11)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 73 of 99 **BOEING SERVICE BULLETIN DC10-28-256 This Appendix applies only to: Group 8.**  1. TEST EQUIPMENT: 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. AUX PUMPS TESTS: a. Test Setup: (1) Make sure that the landing gear is safe for maintenance. Refer to MD-10 AMM 32-00-00 as an accepted procedure. (1) Energize aircraft electrical power system. Refer to MD-10 AMM 24-40-00 as an accepted procedure. (2) Make sure auxiliary fuel tanks quantity is less than 500 LBS. Refer to MD-10 AMM 12-11-04 as an accepted procedure. (3) On the Systems Control Panel (SCP), turn the six BRT knobs (23) to the middle position. (4) Push the FUEL (22) switchlight on the SCP. Make sure that the FUEL synoptic page is shown on the Systems Display. (5) On the Fuel System Control Panel (FSCP) , set the SYSTEM (7) switchlight to MANUAL mode. After ten seconds, on the FUEL synoptic page verify as follow: (a) All main tank forward and aft boost pumps (total of 7) are shown as ON (green or amber circle and pump vanes). (b) Upper Aux Left Pump is shown as ON (green or amber circle and pump vanes). (c) Upper Aux Right Pump is shown as ON (green or amber circle and pump vanes). (d) Lower Aux Left Pump is shown as ON (green or amber circle and pump vanes). (e) Lower Aux Right Pump is shown as ON (green or amber circle and pump vanes). (6) On the FSCP push the 1 PUMPS (1), 2 PUMPS (2), 3 PUMPS (3), AUX TANKS L TRANS (8) and AUX TANKS R TRANS (9) switchlights and verify the following on the FUEL synoptic page: (a) All main tank forward and aft boost pumps (total of 7) are shown as OFF (white empty circle). (b) Upper Aux Left Pump is shown as OFF (white empty circle).

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 1 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 74 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(c) Upper Aux Right Pump is shown as OFF (white empty circle). (d) Lower Aux Left Pump is shown as OFF (white empty circle). (e) Lower Aux 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. **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 breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** 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 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 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 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

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 2 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 75 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  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 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. Upper Auxiliary Tank Left Fuel Pump (M1-92) Test: (1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove the terminal shield of FCD U1-702 (15) as follows: (a) Remove the two screws (16) and lockwashers (17) from the FCD terminal shield (18). (b) Remove the terminal shield (18). (2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-702 (15). (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. (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

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 3 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 76 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(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 (15). (8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-702 (15) and verify that it reads less than 10 volts. (9) 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 (10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-702 (15) reads more than 110 volts. **CAUTION:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-702 (15) 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 (8) switchlight and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-702 (15) 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 (8) switchlight and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-702 (15) reads more than 110 volts. (b) On the FUEL synoptic page the Upper Aux Left Pump is shown as OFF (white empty circle). (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 (15) reads less than 10 volts.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 4 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 77 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-702 (15). (16) At the CAC EPC Bay-2 install the terminal shield (18) on FCD U1-702 (15) as follows: (a) Install the terminal shield (18) with two screws (16) and two lockwashers (17). c. Upper Auxiliary Tank Right Fuel Pump (M1-91) Test: (1) At the CAC EPC Bay-1, remove the terminal shield of FCD U1-701 (11) as follows: (a) Remove the two screws (16) and lockwashers (17) from the FCD terminal shield (18). (b) Remove the terminal shield (18). (2) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-701 (11). (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. (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 (11). (8) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal stud 12 of FCD U1-701 (11) and verify that it reads less than 10 volts. (9) Close circuit breaker as follows:

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 5 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 78 of 99 **BOEING SERVICE BULLETIN DC10-28-256 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 (11) reads more than 110 volts. **CAUTION:** THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-701 (11) 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 (9) switchlight and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-701 (11) 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 (9) switchlight and verify as follows: (a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-701 (11) reads more than 110 volts. (b) On the FUEL synoptic page the Upper Aux Right Pump is shown as OFF (white empty circle). (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 (11) reads less than 10 volts. (15) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-701 (11). (16) At the CAC EPC Bay-1 install the terminal shield (18) on FCD U1-701 (11) as follows: (a) Install the terminal shield (18) with two screws (16) and two lockwashers (17). d. Lower Auxiliary Tank Left Fuel Pump (M1-94) Test: (1) Open circuit breakers as follow:

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 6 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 79 of 99 **BOEING SERVICE BULLETIN DC10-28-256 OVERHEAD, BATTERY BUS**  **Name Number**  **Column Row**  FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B **OVERHEAD, BATTERY DIRECT BUS Name**  **Number Column**  **Row** GROUND REFUEL POWER B1-475 29 A (2) At the CAC EPC Bay-2, remove the terminal shield of FCD U1-704 (10) as follows: (a) Remove the two screws (16) and lockwashers (17) from the FCD terminal shield (18). (b) Remove the terminal shield (14). (3) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-704 (10). (4) Close circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (5) 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. (6) Open circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (7) On the FUEL synoptic page verify the Lower Aux Left Pump is shown in as OFF (white empty circle). (8) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-704 (10).

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 7 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 80 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(9) At the CAC EPC Bay-2 attach the multimeter lead, set to measure DC voltage, to terminal stud 12 of FCD U1-704 (10) and verify that it reads less than 5 volts. (10) Close circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (11) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-704 (10) reads more than 24 volts. (12) 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
**CAUTION:** 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. (13) On the FSCP, push the AUX TANKS L TRANS (8) switchlight and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-704 (10) reads less than 5 volts. (b) On the FUEL synoptic page the Lower Aux Left Pump is shown as ON (amber circle and pump vanes). (14) On the FSCP, push the AUX TANKS L TRANS (8) switchlight and verify as follows: (a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-704 (10) reads more than 24 volts. (b) On the FUEL synoptic page the Lower Aux Left Pump is shown as OFF (white empty circle). (15) Open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK L LWR B1-1209 23 F

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 8 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 81 of 99 **BOEING SERVICE BULLETIN DC10-28-256 OVERHEAD, BATTERY BUS**  **Name Number**  **Column Row**  FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (16) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-704 (10) reads less than 5 volts. (17) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-704 (10). (18) At the CAC EPC Bay-2 install the terminal shield (18) on FCD U1-704 (10) as follows: (a) Install the terminal shield (18) with two screws (16) and two lockwashers (17). (19) Close circuit breakers as follow: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B **OVERHEAD, BATTERY DIRECT BUS Name**  **Number Column**  **Row** GROUND REFUEL POWER B1-475 29 A e. Lower Auxiliary Tank Right Fuel Pump (M1-93) Test: (1) Open circuit breakers as follow: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B **OVERHEAD, BATTERY DIRECT BUS Name**  **Number Column**  **Row** GROUND REFUEL POWER B1-475 29 A (2) At the CAC EPC Bay-3, remove the terminal shield of FCD U1-703 (12) as follows: (a) Remove the two screws (16) and lockwashers (17) from the FCD terminal shield (18). (b) Remove the terminal shield (18).

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 9 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 82 of 99 **BOEING SERVICE BULLETIN DC10-28-256**(3) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-703 (12). (4) Close circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (5) 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. (6) Open circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (7) On the FUEL synoptic page verify the Lower Aux Right Pump is shown in as OFF (white empty circle). (8) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of FCD U1-703 (12). (9) At the CAC EPC Bay-3 attach the multimeter lead, set to measure DC voltage, to terminal stud 12 of FCD U1-703 (12) and verify that it reads less than 5 volts. (10) Close circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (11) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-703 (12) reads more than 24 volts. (12) Close circuit breaker as follows:

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 10 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 83 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G
**CAUTION:** 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. (13) On the FSCP, push the AUX TANKS R TRANS (9) switchlight and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-703 (12) reads less than 5 volts. (b) On the FUEL synoptic page the Lower Aux Right Pump is shown as ON (amber circle and pump vanes). (14) On the FSCP, push the AUX TANKS R TRANS (9) switchlight and verify as follows: (a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-703 (12) reads more than 24 volts. (b) On the FUEL synoptic page the Lower Aux Right Pump is shown as OFF (white empty circle). (15) Open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP CONTROL AUX TANK R LWR B1-1208 23 G **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B (16) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-703 (12) reads less than 5 volts. (17) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-703 (12). (18) At the CAC EPC Bay-3 install the terminal shield (18) on FCD U1-703 (4) as follows: (a) Install the terminal shield (18) with two screws (16) and two lockwashers (17). (19) Close circuit breakers as follow:

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 11 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 84 of 99 **BOEING SERVICE BULLETIN DC10-28-256 OVERHEAD, BATTERY BUS**  **Name Number**  **Column Row**  FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B **OVERHEAD, BATTERY DIRECT BUS Name**  **Number Column**  **Row** GROUND REFUEL POWER B1-475 29 A f. Aux Pumps Test Closeout: (1) Close circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** 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 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 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 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

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 12 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 85 of 99 **BOEING SERVICE BULLETIN DC10-28-256 UPPER MAIN, FUEL AC BUS 3** **Name Number**  **Column Row**  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 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 (2) On the FSCP set the SYSTEM (7) switchlight to AUTO mode. After thirty seconds, verify the following on the FUEL synoptic page: (a) Upper Aux Left Pump is shown as OFF (white empty circle). (b) Upper Aux Right Pump is shown as OFF (white empty circle). (c) Lower Aux Left Pump is shown as OFF (white empty circle). (d) Lower Aux Right Pump is shown as OFF (white empty circle). 3. UPPER AUXILIARY FILL VALVE CONTROL TEST: a. Make sure Fuel Tank 2 quantity is a minimum of 8500 LBS. Refer to MD-10 AMM 12-11-04 as an accepted procedure. b. On the FSCP set the SYSTEM (7) switchlight to AUTO mode. c. On MCDU-3 push the MENU (19) key and verify the MENU page is shown. d. On MCDU-3 push the Line Select Key (LSK) (20) adjacent to CFDS and verify the CFDS INITIAL MENU is shown. e. On MCDU-3 push the LSK (20) adjacent to LRU MAINTENANCE and verify the CFDS LRU MAINTENANCE screen is shown. f. On MCDU-3 push the PAGE (21) key until FSC is shown. g. On MCDU-3 push the LSK (20) adjacent to FSC and verify the FSC MAINTENANCE screen is shown. h. On MCDU-3 push the LSK (20) adjacent to Return-to-Service Test and verify the Return-to-Service screen is shown.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 13 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 86 of 99 **BOEING SERVICE BULLETIN DC10-28-256**i. On MCDU-3 push the LSK (20) adjacent to CONTINUE. j. On MCDU-3 push the LSK (20) adjacent to SELECT PUMPS. k. On MCDU-3 push the Page (21) key and verify the SYSTEM LRUS-PUMPS 2/3 page is shown. l. Wait 5 seconds until the < symbols are displayed and then push the LSK (20) adjacent to 2 XFER-OFF to turn on Tank 2 XFER pump. Verify the 2 XFER-OFF changes to 2 XFER-ON for this pump. m. On the FUEL synoptic page verify the Tank 2 transfer pump is ON (green circle and pump vanes). n. On MCDU-3 push the LSK (20) adjacent to VALVES. o. On MCDU-3 push the Page (21) key to get the SYSTEM LRUS-VALVES 2/3 page. p. Wait 5 seconds until the < symbols are displayed and then press the LSK (20) adjacent to AUX FILL ISOL-OFF to open the Aux Fill Isolation valve. Verify the AUX FILL ISOL-OFF changes to AUX FILL ISOL-ON for this valve. q. On the FUEL synoptic page verify the Aux Fill Isolation Valve is OPEN (Valve is green and aligned with flow line). r. On MCDU-3 push the LSK (20) adjacent to FILL LWR AUX-OFF. Verify the FILL LWR AUX-OFF changes to FILL LWR AUX-ARM for this valve. s. On the FUEL synoptic page verify that the lower aux fill valve opens (green spigot valve displayed at the side of the aux tank) and Aux Tank Fuel Quantity increases. t. When Aux Tank Fuel Quantity has increased by 4000 lbs +/- 300 lbs of fuel, on MCDU-3 push the LSK (20) adjacent to FILL LWR AUX-ARM. Verify the FILL LWR AUX-ARM changes to FILL LWR AUX-OFF for this valve. u. On the FUEL synoptic page verify the lower aux fill valve is no longer displayed and after approximately one minute the Aux Tank Fuel Quantity stops increasing. v. On MCDU-3 push the LSK (20) adjacent to FILL UPR AUX-OFF. Verify the FILL UPR AUX-OFF changes to FILL UPR AUX-ARM for this valve. w. On the FUEL synoptic page verify the upper aux fill valve opens (green spigot valve at the top of the aux tank) and Aux Tank Fuel Quantity increases. **NOTE:** NOTE: If upper aux fill valve does not open, troubleshoot wiring changes to B964-292-20 and B964-296-22 wires in this Service Bulletin (Ref. Dwg. SR10280069 Sheets 6.1, 8 and 303.201). x. When Aux Tank Fuel Quantity has increased by an additional 800 lbs +/- 200 lbs of fuel, push the LSK (20) adjacent to FILL UPR AUX-ARM and verify the FILL UPR AUX-ARM changes to FILL UPR AUX-OFF for this valve.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 14 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 87 of 99 **BOEING SERVICE BULLETIN DC10-28-256**y. On the FUEL synoptic page verify the upper aux fill valve closes (spigot valve removed from display) and after approximately one minute the Aux Tank Fuel Quantity stops increasing. z. On MCDU-3 push the LSK (20) adjacent to AUX FILL ISOL-ON and verify the AUX FILL ISOL-ON changes to AUX FILL ISOL-OFF for this valve. aa. After approximately 10 seconds on the FUEL synoptic page verify the Aux Fill Isolation Valve is closed (Valve is white). ab. On MCDU-3 push the LSK (20) adjacent to PUMPS OFF. ac. After approximately 5 seconds verify on the FUEL synoptic page that tank 2 transfer pump is OFF (white empty circle). ad. On the FSCP set the SYSTEM (7) switchlight to MANUAL mode. ae. After 5 seconds, on the FSCP, push the 1 PUMPS (1), 2 PUMPS (2), 3 PUMPS (3), AUX TANKS L TRANS (8) and AUX TANKS R TRANS (9) switchlights and verify the switchlights go off. On the FUEL synoptic page verify as follow: (1) All main tank forward and aft boost pumps (total of 7) are OFF (white empty circle). (2) Upper Aux Left Pump is OFF (white empty circle). (3) Upper Aux Right Pump is OFF (white empty circle). (4) Lower Aux Left Pump is OFF (white empty circle). (5) Lower Aux Right Pump is OFF (white empty circle). **NOTE:** If any other fuel pumps are ON, push the appropriate pump switch on the FSCP so that all fuel pumps are OFF. af. Open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F ag. Open access panel 619CB. Refer to MD-10 AMM 06-36-00.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 15 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 88 of 99 **BOEING SERVICE BULLETIN DC10-28-256**ah. At the right wing refueling control panel verify that all tanks fill valve switches are set to the CLOSE position. ai. On the FSCP push the AUX TANKS L TRANS (8) switchlight. aj. On the FUEL synoptic page verify the left lower aux fuel pump is ON and high pressure (green circle and pump vanes). ak. Within approximately 20 seconds verify that the upper aux fill valve opens (green spigot valve at the top of the aux tank) and flow line between lower aux left pump and upper aux fill valve turns green. **NOTE:** If the upper aux fill valve does not open, Service Bulletin rewiring is not correct and troubleshooting is required. al. At the right wing refueling control panel momentarily place the POWER (24) switch in the ARM position and then release. Verify that the power indicating light is illuminated. am. Within approximately 10 seconds, on the FUEL synoptic page verify that the upper aux fill valve is no longer displayed. **NOTE:** If the upper aux fill valve remains open, Service Bulletin rewiring is not correct and troubleshooting is required. an. At the right wing refueling control panel momentarily place the POWER (24) switch in the DISARM position and then release. Verify that the power indicating light is not illuminated. ao. Within approximately 20 seconds, on the FUEL synoptic page verify that the upper aux fill valve is open (green spigot valve at the top of the aux tank) and flow line between lower aux left pump and upper aux fill valve turns green. ap. Open circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B aq. Within approximately 10 seconds, on the FUEL synoptic page verify that the upper aux fill valve is no longer displayed. **NOTE:** If the upper aux fill valve remains open, Service Bulletin rewiring is not correct and troubleshooting is required. ar. Close circuit breaker as follows:

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 16 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 89 of 99 **BOEING SERVICE BULLETIN DC10-28-256 OVERHEAD, BATTERY BUS**  **Name Number**  **Column Row**  FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B as. Within approximately 20 seconds on the FUEL synoptic page verify that the upper aux fill valve is open (green spigot valve at the top of the aux tank) and flow line between lower aux left pump and upper aux fill valve turns green. at. On the FSCP push the AUX TANKS L TRANS (8) switchlight. au. On the FUEL synoptic page verify the left lower aux fuel pump is OFF (white empty circle) and upper aux fill valve is not displayed. av. On the FSCP push the AUX TANKS R TRANS (9) switchlight. aw. On the FUEL synoptic page verify the right lower aux fuel pump is ON and high pressure (green circle and pump vanes). ax. Within approximately 20 seconds verify that the upper aux fill valve is open (green spigot valve at the top of the aux tank) and flow line between lower aux right pump and upper aux fill valve turns green. **NOTE:** If the upper aux fill valve does not open, Service Bulletin rewiring is not correct and troubleshooting is required. ay. At the right wing refueling control panel momentarily place the POWER (24) switch in the ARM position and then release. Verify that the power indicating light is illuminated. az. Within approximately 10 seconds on the FUEL synoptic page verify that the upper aux fill valve is no longer displayed. **NOTE:** If the upper aux fill valve remains open, Service Bulletin rewiring is not correct and troubleshooting is required. ba. At the right wing refueling control panel momentarily place the POWER (24) switch in the DISARM position and then release. Verify that the power indicating light is not illuminated. bb. Within approximately 20 seconds on the FUEL synoptic page verify that the upper aux fill valve is open (green spigot valve at the top of the aux tank) and flow line between lower aux right pump and upper aux fill valve turns green. bc. Open circuit breaker follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 17 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 90 of 99 **BOEING SERVICE BULLETIN DC10-28-256**bd. Within approximately 10 seconds on the FUEL synoptic page verify that the upper aux fill valve is no longer displayed. **NOTE:** If the upper aux fill valve remains open, Service Bulletin rewiring is not correct and troubleshooting is required. be. Close circuit breaker as follows: **OVERHEAD, BATTERY BUS Name**  **Number Column**  **Row** FUEL TANK FILL VALVE & BAT BUS SENSING B1-474 29 B bf. Within approximately 20 seconds on the FUEL synoptic page verify that the upper aux fill valve is open (green spigot valve at the top of the aux tank) and flow line between lower aux right pump and upper aux fill valve turns green. bg. On the FSCP push the AUX TANKS R TRANS (9) switchlight. bh. On the FUEL synoptic page verify that the right lower aux fuel pump is OFF (white empty circle) and upper aux fill valve is not displayed. bi. Close access panel 619CB. Refer to MD-10 AMM 06-36-00. bj. Open circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D bk. On the FSCP push the AUX TANKS L TRANS (8) and AUX TANKS R TRANS (9) switchlights. bl. On the FUEL synoptic page verify that the left and right lower aux fuel pumps are commanded ON (amber circle and pump vanes). bm. On the FSCP push the AUX TANKS L TRANS (8) switchlight. bn. On the FUEL synoptic page verify that the left lower aux fuel pump is OFF (white empty circle). **NOTE:** If the left lower aux fuel pump does not go OFF, Service Bulletin rewiring is not correct and troubleshooting of the diode R7-910 installation is required.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 18 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 91 of 99 **BOEING SERVICE BULLETIN DC10-28-256**bo. On the FSCP push the AUX TANKS L TRANS (8) switchlight. bp. On the FUEL synoptic page verify that the left and right lower aux fuel pumps are commanded ON (amber circle and pump vanes). bq. On the FSCP push the AUX TANKS R TRANS (9) switchlight. br. On the FUEL synoptic page verify that the right lower aux fuel pump is OFF (white empty circle). **NOTE:** If the right lower aux fuel pump does not go OFF, Service Bulletin rewiring is not correct and troubleshooting of the diode R7-911 installation is required. bs. On the FSCP push the AUX TANKS L TRANS (8) switchlight. bt. On the FUEL synoptic page verify the left lower aux fuel pump is OFF (white empty circle). bu. Close circuit breakers as follow: **UPPER MAIN, FUEL AC BUS 1 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R UPR B1-1250 23 B FUEL PUMP CONTROL AUX TANK R UPR B1-1206 23 E **UPPER MAIN, FUEL AC BUS 2 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK L UPR B1-1248 22 C FUEL PUMP POWER AUX TANK L LWR B1-1249 23 C FUEL PUMP CONTROL AUX TANK L UPR B1-1207 22 F **UPPER MAIN, FUEL AC BUS 3 Name**  **Number Column**  **Row** FUEL PUMP POWER AUX TANK R LWR B1-1251 23 D bv. On the FSCP push the AUX TANKS L TRANS (8) and AUX TANKS R TRANS (9) switchlights. bw. On the FUEL synoptic page verify the left and right upper and lower aux fuel pumps are ON (green circle and pump vanes) and fuel is transferring from lower to upper aux tank. bx. On the FSCP push the Tank 2 Fill Valve switchlight and verify that the ARM light stays illuminated after the switch is released. by. On the FUEL synoptic page verify that the Tank 2 Fill Valve is open and fuel is being transferred back into Tank 2 from the Aux tanks.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 19 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 92 of 99 **BOEING SERVICE BULLETIN DC10-28-256**bz. When Aux tank quantity is less than 500 lbs, on the FSCP push the AUX TANKS L TRANS (8) and AUX TANKS R TRANS (9) switches. ca. On the FUEL synoptic page verify that the left and right upper and lower aux fuel pumps are OFF (white empty circle). cb. On the FSCP set the SYSTEM (7) switchlight to AUTO mode. 4. END OF TEST.

**APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES (SHEET 20 OF 25)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 93 of 99 **BOEING SERVICE BULLETIN DC10-28-256 APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES**  **(SHEET 21 OF 25)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 94 of 99 **BOEING SERVICE BULLETIN DC10-28-256 APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES**  **(SHEET 22 OF 25)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 95 of 99 **BOEING SERVICE BULLETIN DC10-28-256 APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES**  **(SHEET 23 OF 25)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 96 of 99 **BOEING SERVICE BULLETIN DC10-28-256 APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES**  **(SHEET 24 OF 25)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 97 of 99 **BOEING SERVICE BULLETIN DC10-28-256 APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES**  **(SHEET 25 OF 25)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 24, 2014 DC10-28-256 98 of 99 **BOEING SERVICE BULLETIN DC10-28-256 APPENDIX E: 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 DC10-28-256 99 of 99 **BOEING SERVICE BULLETIN DC10-28-256**