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.

ECCN: 9E991

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Unpublished Work.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

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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

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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.

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INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Group(s) Total Task Hours Elapsed Hours

1 36.8 18.4

2-3, 9 62.8 31.4

4 51.2 25.6

5 20.2 10.1

6 63.2 31.6

7 83.0 41.5

8 97.2 48.6

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.

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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.

GROUP CONFIGURATION DESCRIPTION

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 -

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GROUP CONFIGURATION DESCRIPTION

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

Fuselage Num- Group

ber

2 1

60 3

65 1

71 3

72 1

83 4

90 3

96 8

99 3

100 3

103 8

106 2

110 8

114 - 115 3

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Fuselage Num- Group

ber

117 3

122 - 123 3

127 2

129 3

131 - 135 3

137 3

146 - 147 3

150 3

152 3

156 - 158 3

160 3

165 2

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 3

219 8

220 - 221 3

223 - 227 3

229 3

230 3

232 3

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Fuselage Num- Group

ber

234 3

235 2

236 3

239 3

240 3

242 3

244 - 246 3

248 2

251 - 252 1

253 2

254 3

255 2

256 3

257 8

261 - 263 3

264 2

265 - 266 3

267 2

268 3

274 - 275 3

277 8

281 3

282 8

285 1

286 3

289 3

290 - 291 3

292 9

299 3

300 - 301 3

302 - 303 5

304 - 306 3

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Fuselage Num- Group

ber

308 3

310 3

311 7

312 5

313 3

314 2

315 6

316 3

317 8

318 1

324 3

325 6

326 8

327 3

329 3

330 8

332 3

333 7

334 - 338 3

340 3

341 9

342 - 343 3

345 9

346 1

349 3

355 - 356 3

359 7

360 - 361 7

363 7

366 - 367 3

372 1

373 7

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Fuselage Num- Group

ber

375 - 378 7

380 7

381 3

383 - 389 7

390 - 399 7

400 - 408 7

409 8

410 - 411 7

412 8

413 - 415 7

416 8

417 - 418 7

419 8

420 - 421 7

422 8

423 - 429 7

430 - 432 7

433 8

434 - 438 9

439 7

440 8

441 7

442 - 444 8

445 - 446 3

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:

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Company Service Bulletin Description

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

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-10, DC-10-15

Group 2:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-30, DC-10-30F, DC-10-

30F (KDC-10)

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Group 3:

Affected Maintenance Zones

Model Zone

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

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-10F

Group 5:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-30F

Group 6, 9:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-30

Group 7:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-30F (KC-10A)

Group 8:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

DC-10-30F, MD-10-30F

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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:

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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:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 0.6 0.3

Route and Terminate 2 23.2 11.6

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 36.8 18.4

Group 2-3, 9:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 1.6 0.8

Route and Terminate 2 48.2 24.1

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 62.8 31.4

Group 4:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Route and Terminate 2 38.2 19.1

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 51.2 25.6

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Group 5:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 1.6 0.8

Route and Terminate 2 5.6 2.8

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 20.2 10.1

Group 6:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 1.6 0.8

Route and Terminate 2 48.6 24.3

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 63.2 31.6

Group 7:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 0.6 0.3

Route and Terminate 2 69.4 34.7

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 83.0 41.5

Group 8:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 1.0 0.5

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BOEING SERVICE BULLETIN DC10-28-256
Group 8:

Task Number of Persons Task Hours Elapsed Hours

Route and Terminate 2 83.2 41.6

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 97.2 48.6

H. Weight and Balance Changes

Group 1:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-10, DC-10-15 810.7 +1.5 +1,216.1

Group 2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30, DC-10-30F, 835.0 +4.6 +3,841.0

DC-10-30F (KDC-10)

Group 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30, DC-10-30F, 833.0 +4.6 +3,831.8

DC-10-40, DC-10-40F

Group 4:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-10F 800.7 +2.3 +1,841.6

Group 5:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30F 833.3 +4.6 +3,833.2

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BOEING SERVICE BULLETIN DC10-28-256
Group 6:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30 837.8 +4.6 +3,853.9

Group 7:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30F (KC-10A) 848.0 +4.3 +3,646.4

Group 8:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30F, MD-10-30F 598.1 +7.3 +4,366.1

Group 9:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

DC-10-30 833.0 +4.6 +3,831.8

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

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 0 0 0 0 0

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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

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

CRUISE COLD 1 3 0.11 0.0011 0.0033

CRUISE HOT 1 3 0.11 0.0011 0.0033

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 0 0 0 0 0

CRUISE COLD 1 3 0.11 0.0011 0.0033

CRUISE HOT 1 3 0.11 0.0011 0.0033

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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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 Control Relay

5D0397-1

ITEM

50X

R2-703

CHAP

280

BUS

DB

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 0 0 0 0 0

CRUISE COLD 1 3 0.25 0.0025 0.0075

CRUISE HOT 1 3 0.25 0.0025 0.0075

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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 Control Relay

5D0397-1

ITEM

50X

R2-704

CHAP

280

BUS

DB

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 0 0 0 0 0

CRUISE COLD 1 3 0.25 0.0025 0.0075

CRUISE HOT 1 3 0.25 0.0025 0.0075

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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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

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 0 0 0 0 0

CRUISE COLD 4 3 5 0.2 0.15

CRUISE HOT 4 3 5 0.2 0.15

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 0 0 0 0 0

CRUISE COLD 4 3 5 0.2 0.15

CRUISE HOT 4 3 5 0.2 0.15

DESCENT & LAND 0 0 0 0 0

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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

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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

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BOEING SERVICE BULLETIN DC10-28-256
Drawing No Title Sheet DCN/REV ADCN

ELEC INSTL - FUEL PUMP UNCOMMAND- AEO - C

ED SIGNAL

SR10280069

AEO - D

DWG B -

WIRE INSTL - FUEL PUMP UNCOMMAND- DWG A -

ED SIGNAL

SR10280070

ELEC INSTL - FUEL PUMP UNCOMMAND- AEO - D

ED SIGNAL

SR10280072

DWG C -

WIRE INSTL - FUEL PUMP UNCOMMAND- DWG B -

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:

Publication Chapter-Section

Aircraft Maintenance Manual 28-22

FAA Approved Flight Manual Section 1 and 3

Fault Isolation Manual 28-02

Flight Crew Operations Manual Volumes I, II & III

Special Compliance Item Report MDC-02K1003 (ALI 20-4)

Wiring Diagram Manual 28-21, 28-22, 28-44

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for

changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This

service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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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 issue date of this Service Bulletin

(US Dollars)

ROLT as of the original issue

date of this Service Bulletin

(Calendar Days)

Kit Number Name

SB10280256-3 Service Kit 120 $1,213.00

SB10280256-5 Service Kit 120 $3,133.00

SB10280256-7 Service Kit 120 $3,621.00

SB10280256-9 Service Kit 120 $997.00

SB10280256-11 Service Kit 120 $3,642.00

SB10280256-13 Service Kit 120 $3,705.00

SB10280256-15 Service Kit 120 $5,164.00

SB10280256-17 Service Kit 120 $3,042.00

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.

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BOEING SERVICE BULLETIN DC10-28-256
Group 1:

Kit SB10280256-3

Part Number QTY Name Notes

3D0005-08-8 4 SCREW (a)

5D0010-15 4 TERM BLOCK (a)

5D0101-2 4 END CLAMP (a)

9D0090-2U 2 TRACK, TERMINAL (a)

DC38-20P 2 PIN, T/C 1126

MS21042L08 4 NUT

NAS1252-8L 4 WASHER

SR10280072-102 1 WIRE KIT (b)

SR10280072-108 1 WIRE KIT (b)

SR10280072-112 1 WIRE KIT (b)

SR10280072-117 1 WIRE KIT (b)

SR10280072-119 1 WIRE KIT (b)

SR10280072-125 1 WIRE KIT (b)

(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

SR10280072 -102 -108 -112 -117 -119 -125

New Part Number QTY Name Notes

5D0086-5 2 2 TERMINAL LUG 761 (a)

70 WIRE CODE 801 (b)

FT.

10 8 FT.

FT.

74

FT.

82

FT.

40

FT.

D2426-1C-20NM

10 WIRE CODE 801 (b)

FT.

D2426-1C-24NM

DC38-20P 4 PIN, T/C 1126

S00023-20P 2 1 2 2 1 PIN T/C 601/701 (a)

S00023-20S 2 1 7 SKT T/C 602/702 (a)

YHMM20-1F50 2 PIN T/C 613

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Or approved alternate. Refer to SWPM 20-00-13.

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BOEING SERVICE BULLETIN DC10-28-256
Group 2:

Kit SB10280256-5

Part Number QTY Name Notes

3D0005-08-11 2 SCREW (a)

3D0005-08-12 4 SCREW (a)

3D0005-08-8 4 SCREW (a)

5D0010-15 4 TERM BLOCK (a)

5D0101-2 4 END CLAMP (a)

5D0397-1 2 RELAY (a)

9D0090-2U 2 TRACK, TERMINAL (a)

DC38-20P 4 PIN, T/C 1126

MS20470AD3-3D 8 RIVET

MS21042L08 4 NUT

MS35338-42 6 LOCKWASHER

NAS1252-8L 10 WASHER

NAS1329S08K75 2 RIVNUT

NAS1474A08 4 NUTPLATE

SR10280072-103 1 WIRE KIT (b)

SR10280072-109 1 WIRE KIT (b)

SR10280072-113 1 WIRE KIT (b)

SR10280072-117 1 WIRE KIT (b)

SR10280072-120 1 WIRE KIT (b)

SR10280072-123 1 WIRE KIT (b)

SR10280072-126 1 WIRE KIT (b)

YHLZ44 3 TERM BLOCK

(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

SR10280072 -103 -109 -113 -117 -120 -123 -126

Number QTY Name Notes

5D0013-2A 2 DIODE (a)

5D0086-5 2 6 4 TERMINAL LUG 761 (a)

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Group 2:

Wire Kit Table

SR10280072 -103 -109 -113 -117 -120 -123 -126

Number QTY Name Notes

5D0086-6 1 1 TERMINAL LUG 762 (a)

D2426-1C-16NM 5 FT. WIRE CODE 801 (b)

130 WIRE CODE 801 (b)

FT.

31

FT.

34

FT.

10

FT.

147

FT.

164

FT.

80

FT.

D2426-1C-20NM

15 WIRE CODE 801 (b)

FT.

D2426-1C-24NM 5 FT.

DC38-20P 1 3 4 PIN, T/C 1126

LRM16W-2DE5 1 PIN T/C 1003

S00023-20P 4 2 2 4 2 2 PIN T/C 601/701 (a)

S00023-20S 4 1 5 10 SKT T/C 602/702 (a)

YHMM16-3F50 4 1 PIN T/C 612

YHMM20-1F50 4 1 1 PIN T/C 613

(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

Part Number QTY Name Notes

3D0005-08-11 2 SCREW (a)

3D0005-08-12 4 SCREW (a)

3D0005-08-8 4 SCREW (a)

5D0010-15 4 TERM BLOCK (a)

5D0101-2 4 END CLAMP (a)

5D0397-1 2 RELAY (a)

9D0090-2U 2 TRACK, TERMINAL (a)

DC38-20P 4 PIN, T/C 1126

MS20470AD3-3D 8 RIVET

MS21042L08 4 NUT

MS35338-42 6 LOCKWASHER

NAS1252-8L 10 WASHER

NAS1329S08K75 2 RIVNUT

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Group 3, 9:

Kit SB10280256-7

Part Number QTY Name Notes

NAS1474A08 4 NUTPLATE

SR10280072-103 1 WIRE KIT (a)

SR10280072-110 1 WIRE KIT (b)

SR10280072-114 1 WIRE KIT (b)

SR10280072-117 1 WIRE KIT (b)

SR10280072-120 1 WIRE KIT (b)

SR10280072-123 1 WIRE KIT (b)

SR10280072-127 1 WIRE KIT (b)

YHLZ44 3 TERM BLOCK

(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

SR10280072 -103 -110 -114 -117 -120 -123 -127

New Part Number QTY Name Notes

5D0013-2A 2 DIODE (a)

5D0086-5 2 6 4 TERMINAL LUG 761 (a)

5D0086-6 1 1 TERMINAL LUG 762 (a)

D2426-1C-16NM 5 FT. WIRE CODE 801 (b)

130 WIRE CODE 801 (b)

FT.

31

FT.

34

FT.

10

FT.

147

FT.

164

FT.

80

FT.

D2426-1C-20NM

10 WIRE CODE 801 (b)

FT.

10

FT.

D2426-1C-24NM

DC38-20P 2 6 PIN, T/C 1126

LRM16W-2DE5 1 PIN T/C 1003

S00023-20P 4 2 2 4 2 2 PIN T/C 601/701 (a)

S00023-20S 4 4 12 SKT T/C 602/702 (a)

YHMM16-3F50 4 1 PIN T/C 612

YHMM20-1F50 4 1 1 PIN T/C 613

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Or approved alternate. Refer to SWPM 20-00-13.

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Group 4:

Kit SB10280256-9

Part Number QTY Name Notes

5D0010-15 3 TERM BLOCK (a)

DC38-20P 4 PIN, T/C 1126

SR10280072-104 1 WIRE KIT (b)

SR10280072-111 1 WIRE KIT (b)

SR10280072-115 1 WIRE KIT (b)

SR10280072-117 1 WIRE KIT (b)

SR10280072-119 1 WIRE KIT (b)

SR10280072-128 1 WIRE KIT (b)

(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

SR10280072 -104 -111 -115 -117 -119 -128

New Part Number QTY Name Notes

5D0086-5 2 2 TERMINAL LUG 761 (a)

70 WIRE CODE 801 (b)

FT.

10 8 FT

FT.

147

FT.

164

FT.

84

FT.

D2426-1C-20NM

10 WIRE CODE 801 (b)

FT.

D2426-1C-24NM

DC38-20P 8 PIN, T/C 1126

LRC16M-32DJ5 2 SOCKET T/C 706

S00023-20P 4 2 2 2 2 PIN T/C 601/701 (a)

S00023-20S 4 2 6 SKT T/C 602/702 (a)

YHMM22-2DB8 2 PIN T/C 611

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Or approved alternate. Refer to SWPM 20-00-13.

Group 5:

Kit SB10280256-11

Part Number QTY Name Notes

3D0005-08-11 2 SCREW (a)

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Group 5:

Kit SB10280256-11

Part Number QTY Name Notes

3D0005-08-12 4 SCREW (a)

3D0005-08-8 4 SCREW (a)

5D0010-15 4 TERM BLOCK (a)

5D0101-2 4 END CLAMP (a)

5D0397-1 2 RELAY (a)

9D0090-2U 2 TRACK, TERMINAL (a)

DC38-20P 4 PIN, T/C 1126

MS20470AD3-3D 8 RIVET

MS21042L08 4 NUT

MS35338-42 6 LOCKWASHER

NAS1252-8L 10 WASHER

NAS1329S08K75 2 RIVNUT

NAS1474A08 4 NUTPLATE

SR10280072-105 1 WIRE KIT (b)

SR10280072-110 1 WIRE KIT (b)

SR10280072-114 1 WIRE KIT (b)

SR10280072-117 1 WIRE KIT (b)

SR10280072-120 1 WIRE KIT (b)

SR10280072-123 1 WIRE KIT (b)

SR10280072-127 1 WIRE KIT (b)

YHLZ44 3 TERM BLOCK

(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

SR10280072 -105 -110 -114 -117 -120 -123 -127

New Part Number QTY Name Notes

5D0013-2A 2 DIODE (a)

5D0086-5 2 6 4 TERMINAL LUG 761 (a)

5D0086-6 1 1 TERMINAL LUG 762 (a)

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Group 5:

Wire Kit Table

SR10280072 -105 -110 -114 -117 -120 -123 -127

New Part Number QTY Name Notes

D2426-1C-16NM 5 FT. WIRE CODE 801 (b)

130 WIRE CODE 801 (b)

FT.

31

FT.

34

FT.

10

FT.

147

FT.

164

FT.

80

FT.

D2426-1C-20NM

10 WIRE CODE 801 (b)

FT.

10

FT.

D2426-1C-24NM

DC38-20P 2 6 PIN, T/C 1126

LRM16W-2DE5 1 PIN T/C 1003

S00023-20P 4 2 2 4 2 2 PIN T/C 601/701 (a)

S00023-20S 4 4 12 SKT T/C 602/702 (a)

YHMM16-3F50 4 1 PIN T/C 612

YHMM20-1F50 4 1 1 PIN T/C 613

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Or approved alternate. Refer to SWPM 20-00-13.

Group 6:

Kit SB10280256-13

New Part Number QTY Name Notes

3D0005-08-11 2 SCREW (a)

3D0005-08-12 4 SCREW (a)

3D0005-08-8 4 SCREW (a)

5D0010-15 6 TERM BLOCK (a)

5D0101-2 4 END CLAMP (a)

5D0397-1 2 RELAY (a)

9D0090-2U 2 TRACK, TERMINAL (a)

DC38-20P 12 PIN, T/C 1126

MS20470AD3-3D 8 RIVET

MS21042L08 4 NUT

MS35338-42 6 LOCKWASHER

NAS1252-8L 10 WASHER

NAS1329S08K75 2 RIVNUT

NAS1474A08 4 NUTPLATE

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Group 6:

Kit SB10280256-13

New Part Number QTY Name Notes

SR10280072-106 1 WIRE KIT (b)

SR10280072-110 1 WIRE KIT (b)

SR10280072-114 1 WIRE KIT (b)

SR10280072-117 1 WIRE KIT (b)

SR10280072-120 1 WIRE KIT (b)

SR10280072-123 1 WIRE KIT (b)

SR10280072-127 1 WIRE KIT (b)

YHLZ44 3 TERM BLOCK

(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

SR10280072 -106 -110 -114 -117 -120 -123 -127

New Part Number QTY Name Notes

5D0013-2A 2 DIODE (a)

5D0086-5 2 6 4 TERMINAL LUG 761 (a)

5D0086-6 1 1 TERMINAL LUG 762 (a)

D2426-1C-16NM 5 FT. WIRE CODE 801 (b)

130 WIRE CODE 801 (b)

FT.

31

FT.

34

FT.

10

FT.

147

FT.

164

FT.

80

FT.

D2426-1C-20NM

10 WIRE CODE 801 (b)

FT.

10

FT.

D2426-1C-24NM

DC38-20P 4 2 6 PIN, T/C 1126

LRM16W-2DE5 1 PIN T/C 1003

S00023-20P 4 2 2 4 2 2 PIN T/C 601/701 (a)

S00023-20S 4 4 12 SKT T/C 602/702 (a)

YHMM16-3F50 4 1 PIN T/C 612

YHMM20-1F50 1 1 PIN T/C 613

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Or approved alternate. Refer to SWPM 20-00-13.

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Group 7:

Kit SB10280256-15

New Part Number QTY Name Notes

3D0005-08-8 4 SCREW (a)

5D0010-15 6 TERM BLOCK (a)

5D0101-2 4 END CLAMP (a)

9D0090-2U 2 TRACK, TERMINAL (a)

DC38-20P 11 PIN, T/C 1126

MS21042L08 4 NUT

NAS1252-8L 8 WASHER

SR10280072-101 1 WIRE KIT (b)

SR10280072-107 1 WIRE KIT (b)

SR10280072-110 1 WIRE KIT (b)

SR10280072-116 1 WIRE KIT (b)

SR10280072-118 1 WIRE KIT (b)

SR10280072-121 1 WIRE KIT (b)

SR10280072-124 1 WIRE KIT (b)

SR10280072-129 1 WIRE KIT (b)

(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

SR10280072 -101 -107 -110 -116 -118 -121 -124 -129

New Part Number QTY Name Notes

5D0086-5 2 4 4 2 TERMINAL LUG 761 (a)

5D0086-6 1 TERMINAL LUG 762 (a)

5D0187-2222P 2 PIN T/C 1005 (a)

175 WIRE CODE 801 (b)

FT.

14

FT.

16

FT.

20

FT.

334

FT.

164

FT.

120

FT.

14

FT.

D2426-1C-20NM

10 WIRE CODE 801 (b)

FT.

D2426-1C-22NM

10 WIRE CODE 801 (b)

FT.

15

FT.

D2426-1C-24NM

DC38-20P 6 3 7 PIN, T/C 1126

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Group 7:

Wire Kit Table

SR10280072 -101 -107 -110 -116 -118 -121 -124 -129

New Part Number QTY Name Notes

S00023-20P 2 4 4 4 4 2 4 PIN T/C 601/701 (a)

S00023-20S 6 8 15 SKT T/C 602/702 (a)

YHMM20-1F50 2 PIN T/C 613

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Or approved alternate. Refer to SWPM 20-00-13.

Group 8:

Kit SB10280256-17

New Part Number QTY Name Notes

3D0005-04-9 4 SCREW (a)

3D0005-08-11 2 SCREW (a)

3D0005-3-11 2 SCREW (a)

3D0191-04 4 CLIPNUT (a)

5D0107-1 2 TERM BLOCK (a)

5D0122-1 2 RELAY (a)

5D0123-1 2 RELAY (a)

5D0518-4 1 TERMINAL (a)

DC38-16P 4 PIN, T/C 1131

M39029/1-101 4 PIN, T/C 1147

MS35338-42 2 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10L 2 WASHER

NAS1252-4L 4 WASHER

NAS1252-8L 2 WASHER

NAS1329S08K75 2 RIVNUT

SR10280069-101 1 WIRE KIT (b)

SR10280069-102 1 WIRE KIT (b)

SR10280069-103 1 WIRE KIT (b)

SR10280069-104 1 WIRE KIT (b)

SR10280069-105 1 WIRE KIT (b)

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Group 8:

Kit SB10280256-17

New Part Number QTY Name Notes

SR10280069-106 1 WIRE KIT (b)

SR10280069-107 1 WIRE KIT (b)

(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

Kit SR10280069 -101 -102 -103 -104 -105 -106 -107

New Part Number QTY Name Notes

5D0013-2A 2 DIODE (a)

5D0086-24 2 TERMINAL LUG 764 (a)

5D0086-26 4 TERMINAL LUG 766 (a)

5D0086-5 2 2 TERMINAL LUG 761 (a)

5D0086-6 1 1 TERMINAL LUG 762 (a)

5D0187-2222P 4 PIN T/C 1005 (a)

617220 2 SOCKET T/C 487

617240 5 PIN T/C 579

617320 1 1 SOCKET T/C 486

617340 5 SOCKET T/C 578

65009-020-513 2 RELAY SOCKET

CL3-1007-162 2 RECEPTACLE

44 WIRE CODE 801 (b)

FT.

84 2 FT.

FT.

217

FT.

332

FT.

D2426-1C-16NM

38 WIRE CODE 801 (b)

FT.

84 7 FT. 7 FT.

FT.

109

FT.

109

FT.

21

FT.

D2426-1C-20NM

34 WIRE CODE 801 (b)

FT.

D2426-1C-24NM

DC38-16P 7 PIN, T/C 1131

LRC16M-32DJ5 13 SOCKET T/C 706

LRM16M-32DJ5 2 2 PIN T/C 705

LRC16W2 2 1 3 CONN SKT T/C 1004

LRM16W-2DE5 2 3 PIN T/C 1003

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Group 8:

Wire Kit Table

Kit SR10280069 -101 -102 -103 -104 -105 -106 -107

New Part Number QTY Name Notes

M39029/1-101 19 PIN T/C 1147

M39029/22-193 8 CONTACT T/C 542/546

S00023-20P 1 1 2 PIN T/C 601/701 (a)

S00023-20S 1 1 2 SKT T/C 602/702 (a)

(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

Part Number / QTY Name Notes

Specification

DMS 2089 As Required TIE TAPE (a)

(18XTZ), (23XTZ)

or

Equivalent

Alodine 1200S As Required Coating, Chemical Conversion (b)

(DPM 1453-5)

or

Equivalent

DMS 1786 As Required Primer, Fluid Resistant (a)

(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.

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4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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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:

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Chapter Title

SWPM 20-00-09 GENERAL MAINTENANCE PRACTICES - ELECTRICAL

SWPM 20-00-13 ELECTRICAL WIRE CODES

ELECTRICAL WIRE END TERMINATION CODES AND TOOL

CODES

SWPM 20-00-16

SWPM 20-10-01 WIRING INSTALLATION - MAINTENANCE PRACTICES

GENERAL INSTALLATIONS HARDWARE - MAINTENANCE

PRACTICES

SWPM 20-20-03

SWPM 20-31-00 ELECTRICAL CONNECTORS - MAINTENANCE PRACTICES

SWPM 20-50-01 ELECTRICAL BONDING - MAINTENANCE PRACTICES

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:

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a. Open access doors in the table as follow:

Access Door Location/Description Reference

112AB Avionics Equipment Compartment DC-10, MD-10 AMM 06-31-00

113AL Left-side Air Conditioning Compartment

113DL

114AR Right-side Air Conditioning Compartment

131AB Center Accessory Compartment

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:

Drawing Sheets

SR10280072 12-13

Group 2-3, 5-6, 9:

Drawing Sheets

SR10280072 12-15

Group 4:

None.

Group 8:

Drawing Sheets

SR10280069 8, 12-15

3. Route wiring in accordance with the table(s) as follow:

Group 1, 4:

Drawing Sheet(s) Additional Data

SR10280073 1-9, 11

SR10280073 10 Views G, AN, AU

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Group 2, 5-6:

Drawing Sheet(s) Additional Data

SR10280073 1-9, 11

SR10280073 10 Views AM, AN, AP, AR AU, AZ

Group 3, 9:

Drawing Sheet(s) Additional Data

SR10280073 1-9, 11

SR10280073 10 Views AM, AN, AP, AS, AV, AZ

Group 7:

Drawing Sheet(s) Additional Data

SR10280073 1-9, 11

SR10280073 10 Views G, AM, AN, AP, AT, AY

Group 8:

Drawing Sheet(s) Additional Data

SR10280070 1-11

4. Terminate wiring in accordance with the table(s) as follow:

Group 1:

Drawing Sheet

6.10, 102.201, 108.201, 112.201, 117.201, 119.201, 125.201,

306.201, 310.201

SR10280072

Group 2:

Drawing Sheets

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:

Drawing Sheets

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

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Group 4:

Drawing Sheet

6.15, 104.201, 111.201, 115.201, 117.201, 119.201, 128.201,

303.201, 317.201

SR10280072

Group 5:

Drawing Sheets

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:

Drawing Sheets

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:

Drawing Sheets

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:

Drawing Sheets

SR10280069 6.1 - 6.4, 101.201-107.201, 301.201, 303.201-307.201

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.

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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:

Access Door Location/Description Reference

112AB Avionics Equipment Compartment DC-10, MD-10 AMM 06-31-00

113AL Left-side Air Conditioning Compartment

113DL

114AR Right-side Air Conditioning Compartment

131AB Center Accessory Compartment

7. Put the airplane back to a serviceable condition.

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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

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 23 B1-1248 FUEL PUMP POWER AUX TANK L

F 23 B1-1207 FUEL PUMP CONTROL AUX TANK L

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)

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UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R

(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

Row Column Number Name

H 25 B1-1246 R AUX PUMP PRESS LOW LT

(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

Row Column Number Name

H 25 B1-1246 R AUX PUMP PRESS LOW LT

(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

Row Column Number Name

H 25 B1-1246 R AUX PUMP PRESS LOW LT

APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(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

Row Column Number Name

H 25 B1-1246 R AUX PUMP PRESS LOW LT

(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R

(19) On the 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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R

(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

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(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

Row Column Number Name

F 23 B1-1207 FUEL PUMP CONTROL AUX TANK L

(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

Row Column Number Name

F 23 B1-1207 FUEL PUMP CONTROL AUX TANK L

(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

Row Column Number Name

J 25 B1-1247 L AUX PUMP PRESS LOW LT

(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

Row Column Number Name

J 25 B1-1247 L AUX PUMP PRESS LOW LT

APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(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

Row Column Number Name

J 25 B1-1247 L AUX PUMP PRESS LOW LT

(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

Row Column Number Name

J 25 B1-1247 L AUX PUMP PRESS LOW LT

(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1207 FUEL PUMP CONTROL AUX TANK L

(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

Row Column Number Name

F 23 B1-1207 FUEL PUMP CONTROL AUX TANK L

APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(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

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 23 B1-1248 FUEL PUMP POWER AUX TANK L

F 23 B1-1207 FUEL PUMP CONTROL AUX TANK L

APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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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

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

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

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(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

(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

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(12) On the 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

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

(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

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(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

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(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

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(12) On the 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

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(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

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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

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(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(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

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(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(11) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to

ALL position.

(12) On the 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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(14) On the 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) On the 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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

f. Test Closeout:

(1) On the Upper Main Circuit Breaker Panel close circuit breakers as follow:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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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

Row Column Number Name

B 22 B1-1647 FUEL PUMP POWER AUX TANK L AFT

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

E 22 B1-1645 FUEL PUMP CONTROL AUX TANK L AFT

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 22 B1-1646 FUEL PUMP POWER AUX TANK R AFT

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

G 22 B1-1644 FUEL PUMP CONTROL AUX TANK R AFT

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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:

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

(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:

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(12) On the 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:

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

(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:

Row Column Number Name

H 25 B1-1246 R AUX UPR & LWR PRESS LOW LTS

(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

(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

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(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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:

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(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

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Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(12) On the 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:

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(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:

Row Column Number Name

J 25 B1-1247 L AUX UPR & LWR PRESS LOW LTS

(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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(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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(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

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UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(11) On the Flight Engineer's Fuel Panel set the UPR & LWR TANK PUMP R switch (S1-719) to

BOTH position.

(12) On the 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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(14) On the 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) On the 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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

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

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(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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

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(13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

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

Row Column Number Name

G 22 B1-1644 FUEL PUMP CONTROL AUX TANK R AFT

(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

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 22 B1-1644 FUEL PUMP CONTROL AUX TANK R AFT

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

Row Column Number Name

E 22 B1-1645 FUEL PUMP CONTROL AUX TANK L AFT

(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

Row Column Number Name

E 22 B1-1645 FUEL PUMP CONTROL AUX TANK L AFT

h. Test Closeout:

(1) On the Upper Main Circuit Breaker Panel close circuit breakers as follow:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

B 22 B1-1647 FUEL PUMP POWER AUX TANK L AFT

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

E 22 B1-1645 FUEL PUMP CONTROL AUX TANK L AFT

APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR & LWR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR & LWR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 22 B1-1646 FUEL PUMP POWER AUX TANK R AFT

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

G 22 B1-1644 FUEL PUMP CONTROL AUX TANK R AFT

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE

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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

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(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

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

B 24 B1-614 FUEL PUMP POWER TANK 1 FWD

B 25 B1-608 FUEL PUMP POWER TANK 2 FWD

B 26 B1-618 FUEL PUMP POWER TANK 3 XFR

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

E 24 B1-615 FUEL PUMP CONTROL TANK 1 FWD

E 25 B1-609 FUEL PUMP CONTROL TANK 2 FWD

E 26 B1-619 FUEL PUMP CONTROL TANK 3 XFR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

C 24 B1-610 FUEL PUMP POWER TANK 1 XFR

C 25 B1-596 FUEL PUMP POWER TANK 2 R AFT

C 26 B1-620 FUEL PUMP POWER TANK 3 AFT

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

F 24 B1-611 FUEL PUMP CONTROL TANK 1 XFR

F 25 B1-603 FUEL PUMP CONTROL TANK 2 R AFT

F 26 B1-621 FUEL PUMP CONTROL TANK 3 AFT

APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

D 24 B1-612 FUEL PUMP POWER TANK 1 AFT

D 25 B1-756 FUEL PUMP POWER TANK 2 XFR

D 26 B1-616 FUEL PUMP POWER TANK 3 FWD

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

G 24 B1-613 FUEL PUMP CONTROL TANK 1 AFT

G 25 B1-757 FUEL PUMP CONTROL TANK 2 XFR

G 26 B1-617 FUEL PUMP CONTROL TANK 3 FWD

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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(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

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(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

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(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(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

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UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(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

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(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

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OVERHEAD, BATTERY BUS

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

OVERHEAD, BATTERY DIRECT BUS

Row Column Number Name

A 29 B1-475 GROUND REFUEL POWER

(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

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(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

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

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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OVERHEAD, BATTERY BUS

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

OVERHEAD, BATTERY DIRECT BUS

Row Column Number Name

A 29 B1-475 GROUND REFUEL POWER

e. Lower Auxiliary Tank Right Fuel Pump (M1-93) Test:

(1) Open circuit breakers as follow:

OVERHEAD, BATTERY BUS

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

OVERHEAD, BATTERY DIRECT BUS

Row Column Number Name

A 29 B1-475 GROUND REFUEL POWER

(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

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(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

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

Row Column Number Name

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

OVERHEAD, BATTERY BUS

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

(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

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OVERHEAD, BATTERY BUS

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

OVERHEAD, BATTERY DIRECT BUS

Row Column Number Name

A 29 B1-475 GROUND REFUEL POWER

f. Aux Pumps Test Closeout:

(1) Close circuit breakers as follow:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

B 24 B1-614 FUEL PUMP POWER TANK 1 FWD

B 25 B1-608 FUEL PUMP POWER TANK 2 FWD

B 26 B1-618 FUEL PUMP POWER TANK 3 XFR

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

E 24 B1-615 FUEL PUMP CONTROL TANK 1 FWD

E 25 B1-609 FUEL PUMP CONTROL TANK 2 FWD

E 26 B1-619 FUEL PUMP CONTROL TANK 3 XFR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

C 24 B1-610 FUEL PUMP POWER TANK 1 XFR

C 25 B1-596 FUEL PUMP POWER TANK 2 R AFT

C 26 B1-620 FUEL PUMP POWER TANK 3 AFT

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

F 24 B1-611 FUEL PUMP CONTROL TANK 1 XFR

F 25 B1-603 FUEL PUMP CONTROL TANK 2 R AFT

F 26 B1-621 FUEL PUMP CONTROL TANK 3 AFT

APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

D 24 B1-612 FUEL PUMP POWER TANK 1 AFT

D 25 B1-756 FUEL PUMP POWER TANK 2 XFR

D 26 B1-616 FUEL PUMP POWER TANK 3 FWD

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

G 24 B1-613 FUEL PUMP CONTROL TANK 1 AFT

G 25 B1-757 FUEL PUMP CONTROL TANK 2 XFR

G 26 B1-617 FUEL PUMP CONTROL TANK 3 FWD

(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

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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

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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

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

ag. Open access panel 619CB. Refer to MD-10 AMM 06-36-00.

APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

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

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OVERHEAD, BATTERY BUS

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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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

Row Column Number Name

B 29 B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

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

Row Column Number Name

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

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

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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

Row Column Number Name

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

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

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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

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APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES

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APPENDIX E: INPUT SURVEY

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