Commercial 

Airplanes DC10

Service Bulletin

ALERT

Number: DC10-28A253

Original Issue: June 05, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination

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Unpublished Work.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

Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in

connection with this document unless provided in writing by Boeing.

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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 35

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 56

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 57

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

APPENDIX A: INPUT SURVEY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83

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BLANK PAGE
Commercial 

Airplanes DC10

Service Bulletin

ALERT

Summary Number: DC10-28A253

Original Issue: June 05, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

DC-10 and MD-10 fuel boost/transfer pumps failures have occurred due to electrical ground or phase to phase

fault within the fuel pump electrical interface connector shell, pump motor windings and pump motor assembly

lead wires. These failures have caused arcing damage to the interface connector shell or fuel pump explosion

proof compartment. Investigation by Boeing has determined that during an electrical arcing event the affected

Remote Control Circuit Breaker (RCCB) may not react to the thermal rise from an electrical fault fast enough to

prevent arcing damage. Replacing the fuel boost/transfer pump control relays with Fault Current Detectors (FCD)

will minimize arcing events at the fuel pump electrical interface connector, pump motor windings and pump

motor assembly lead wires that could breach the explosion proof compartment. If not corrected, failure of the

connector or fuel pump motor could result in a breach of the fuel boost/transfer pump interface connector shell

or the fuel pump housing assembly and potentially become a fuel tank ignition source.

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 28-03003, DC-10, MD-10 FTD 28-12001, 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 provides instructions to do as follows:

1. Replaces fuel boost/transfer pump control relays in the Center Accessory Compartment (CAC), Electrical

Power Center (EPC) and Avionics Compartment (AC) forward equipment panel with fuel boost/transfer

pump FCDs.

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2. Group 6, Configuration 1:

Changes lower auxiliary fuel boost/transfer pump terminal board and associated wiring located in the

Main Landing Gear (MLG) right-side wheel-well.

3. Group 4, 8, Configuration 1:

Changes upper auxiliary fuel boost/transfer pump terminal board and associated wiring located in the

MLG left and right-side wheel well.

4. Group 1-8, Configuration 1:

Changes fuel tank boost/transfer pump ground wire termination.

5. Group 7:

Removes the Aux tank pump relays and associated wiring.

NOTE: The FCD is intended for use with ONLY airplane Original Equipment Manufacturer (OEM) certified fuel

pumps and fuel pump housings, including OEM pump/housing spare parts and parts repaired per OEM

approved repair instructions.

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, MD-10-10F, and MD-10-30F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected

airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directives AD 2013-08-23, AD 2002-13-10 and AD

2011-11-05 are 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.

INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing

predict the quantity and timing of the Boeing Supplied Kits/Parts.

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BLANK PAGE
Commercial 

Airplanes DC10

Service Bulletin

ALERT

Number: DC10-28A253

Original Issue: June 05, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

Applicable to DC-10-10, DC-10-10F and DC-10-15 airplanes with

fuel tanks 1, 2, 3, and upper auxiliary which are affected by Service

Rework Drawings SR10280053-7001, -7002 and SR10280071-7001,

-7002.

1 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

Applicable to DC-10-30, DC-10-30F, DC-10-40 and DC-10-40F

airplanes with fuel tanks 1, 2, 3, upper, and lower auxiliary which are

affected by Service Rework Drawings SR10280053-7003, -7004 and

SR10280071-7003, -7004.

2 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

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GROUP CONFIGURATION DESCRIPTION

Applicable to DC-10-30 airplanes with fuel tanks 1, 2, 3, upper, lower

and aft auxiliary which are affected by Service Rework Drawings

SR10280053-7005, -7006 and SR10280071-7005, -7006.

3 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

Applicable to DC-10-30F (KC-10A) airplanes with fuel tanks 1, 2, 3,

upper, lower, forward and aft auxiliary and wing tip 1 and 3 which are

affected by Service Rework Drawings SR10280053-7007, -7008 and

SR10280071-7007, -7008.

4 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

Applicable to DC-10-10, DC-10-10F and DC-10-15 airplanes with

fuel tanks 1, 2, and 3 which are affected by Service Rework Drawings

SR10280053-7009, -7010 and SR10280071-7009, -7010.

5 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

Applicable to MD-10-30F airplanes with fuel tanks 1, 2, 3, upper and

lower auxiliary which are affected by Service Rework Drawings

SR10280053-7011, -7012 and SR10280068-7001, -7002.

6 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

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GROUP CONFIGURATION DESCRIPTION

Applicable to MD-10-10F airplanes with fuel tanks 1, 2, and 3 which

are affected by Service Rework Drawings SR10280053-7013, -7014

and SR10280068-7003, -7004.

7 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

Applicable to DC-10-30F (KDC-10) airplanes with fuel tanks 1, 2, 3,

upper and lower auxiliary which are affected by Service Rework

Drawings SR10280053-7015, -7016 and SR10280071-7003, -7004.

8 -

Applicable to operators that have Not accomplished Service bulletin

DC10-28-264.

1

Applicable to operators that have accomplished Service bulletin

DC10-28-264.

2

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

Fuselage Num- Group

ber

2 1

6 7

8 7

15 7

17 7

25 7

26 7

27 7

32 7

33 5

34 5

35 7

39 7

40 5

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Fuselage Num- Group

ber

41 5

42 7

43 5

55 7

59 7

60 2

61 5

62 7

65 1

70 7

71 2

72 1

76 7

78 7

83 1

86 7

89 7

90 2

96 6

99 2

100 2

103 6

106 2

110 6

112 7

114 - 115 2

117 2

119 7

122 - 123 2

127 2

129 2

131 - 135 2

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Fuselage Num- Group

ber

137 2

138 - 139 7

140 7

142 7

144 - 145 7

146 - 147 2

148 7

150 2

152 2

153 - 155 7

156 - 158 2

160 2

162 5

165 - 166 2

169 7

170 - 171 2

173 7

174 2

177 7

178 - 179 2

183 - 184 2

187 - 189 2

190 2

192 2

194 7

195 - 196 2

198 7

199 2

201 2

203 7

204 2

205 7

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Fuselage Num- Group

ber

206 2

207 - 209 7

210 7

211 - 216 2

219 6

220 - 221 2

223 - 227 2

229 2

230 2

232 2

234 2

235 8

236 2

239 2

240 2

242 2

244 - 246 2

247 7

248 2

249 7

250 7

251 - 252 1

253 - 256 2

257 6

261 - 263 2

264 8

265 - 268 2

269 7

270 - 273 7

274 - 275 2

277 6

281 2

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Fuselage Num- Group

ber

282 6

285 1

286 2

289 2

290 - 291 2

292 3

294 7

296 5

297 - 298 7

299 2

300 - 306 2

307 7

308 2

309 7

310 2

311 4

312 - 316 2

317 6

318 1

319 7

321 7

323 7

324 - 325 2

326 6

327 2

329 2

330 6

332 2

333 4

334 - 338 2

340 2

341 3

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Fuselage Num- Group

ber

342 - 343 2

344 7

345 3

346 1

347 7

349 2

351 7

353 7

355 - 356 2

358 5

359 4

360 - 361 4

363 4

366 - 367 2

372 1

373 4

375 - 378 4

379 7

380 4

381 2

383 - 389 4

390 - 399 4

400 - 408 4

409 6

410 - 411 4

412 6

413 - 415 4

416 6

417 - 418 4

419 2

420 - 421 4

422 2

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Fuselage Num- Group

ber

423 - 429 4

430 - 432 4

433 6

434 - 438 3

439 4

440 6

441 4

442 - 444 6

445 - 446 2

2. Spares Affected

None.

B. Concurrent Requirements

For operators who have not accomplished Service Bulletin DC10-28A229 any revision and

DC10-28A259, there are no concurrent requirements.

For operators who have accomplished Service Bulletin DC10-28A229 any revision and DC10-28A259,

the service bulletin or special product drawing listed below must be done before or at the same time

as this service bulletin:

Group 1-8, Configuration 1:

Service Bulletin Description

or Special Product Drawing

Company

Replaces fuel pump housing electrical connector assembly part number 60-84355-1 with part number 60-84351DC10-28A261 Revision 01The Boeing Company

Replaces fuel pump housing electrical connector assembly part number 60-84355-1 with part number 60-84351.The Boeing Company SP10280068

C. Reason

DC-10 and MD-10 fuel boost/transfer pumps failures have occurred due to electrical ground or phase

to phase fault within the fuel pump electrical interface connector shell, pump motor windings and pump

motor assembly lead wires. These failures have caused arcing damage to the interface connector shell

or fuel pump explosion proof compartment. Investigation by Boeing has determined that during an

electrical arcing event the affected Remote Control Circuit Breaker (RCCB) may not react to the thermal

rise from an electrical fault fast enough to prevent arcing damage. Replacing the fuel boost/transfer

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pump control relays with Fault Current Detectors (FCD) will minimize arcing events at the fuel pump

electrical interface connector, pump motor windings and pump motor assembly lead wires that could

breach the explosion proof compartment. If not corrected, failure of the connector or fuel pump motor

could result in a breach of the fuel boost/transfer pump interface connector shell or the fuel pump

housing assembly and potentially become a fuel tank ignition source.

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 28-03003, DC-10, MD-10 FTD 28-12001, 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 provides instructions to do as follows:

1. Replaces fuel boost/transfer pump control relays in the Center Accessory Compartment (CAC),

Electrical Power Center (EPC) and Avionics Compartment (AC) forward equipment panel with fuel

boost/transfer pump FCDs.

2. Group 6, Configuration 1:

Changes lower auxiliary fuel boost/transfer pump terminal board and associated wiring located in

the Main Landing Gear (MLG) right-side wheel-well.

3. Group 4, 8, Configuration 1:

Changes upper auxiliary fuel boost/transfer pump terminal board and associated wiring located in

the MLG left and right-side wheel well.

4. Group 1-8, Configuration 1:

Changes fuel tank boost/transfer pump ground wire termination.

5. Group 7:

Removes the Aux tank pump relays and associated wiring.

NOTE: The FCD is intended for use with ONLY airplane Original Equipment Manufacturer (OEM)

certified fuel pumps and fuel pump housings, including OEM pump/housing spare parts and

parts repaired per OEM approved repair instructions.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1, 5:

Affected Maintenance Zones

Model Zone

112, 131, 132, 144, 145, 515, 518, 541, 615,

618, 641, 731, 741

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

15

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Group 2:

Affected Maintenance Zones

Model Zone

112, 131, 132, 144, 145, 515, 518, 541, 615,

618, 641, 731, 741

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

40, DC-10-40F

Group 3:

Affected Maintenance Zones

Model Zone

112, 131, 132, 144, 145, 182, 515, 518, 541,

615, 618, 641, 731, 741

DC-10-30

Group 4:

Affected Maintenance Zones

Model Zone

112, 126, 131, 132, 144, 145, 182, 515, 518,

535, 541, 615, 618, 635, 641, 731, 741

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

Group 6:

Affected Maintenance Zones

Model Zone

112, 131, 132, 144, 145, 515, 518, 541, 615,

618, 641, 731, 741

MD-10-30F

Group 7:

Affected Maintenance Zones

Model Zone

MD-10-10F 112, 131, 132, 515, 518, 541, 615, 618, 641

Group 8:

Affected Maintenance Zones

Model Zone

112, 131, 132, 144, 145, 515, 518, 541, 615,

618, 641, 731, 741

DC-10-30F (KDC-10)

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E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directives AD 2013-08-23, AD 2002-13-10 and

AD 2011-11-05 are 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. Group 1-5, 8:

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

modification defined in this service bulletin as a Alternative Method of Compliance (AMOC) to the

requirements of paragraph (g), (g)(1) and (h) of AD 2013-08-23 and to the repetitive inspection

interval requirement of paragraph (a) of AD 2002-13-10 and paragraph (j) of AD 2011-11-05 as

follows. Accomplishment of this service bulletin will allow the existing repetitive 18 month inspection

interval to be increased to no later than 24 months and no later than every 24 months thereafter.

All provisions of AD 2013-08-23, AD 2002-13-10 and AD 2011-11-05 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. Group 6-7:

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

modification defined in this service bulletin as a Alternative Method of Compliance (AMOC) to the

requirements of paragraph (g), (g)(1) and (h) of AD 2013-08-23 and to the repetitive inspection

interval requirement of paragraph (a) of AD 2002-13-10 and paragraph (j) of AD 2011-11-05 as

follows. Accomplishment of this service bulletin will allow the existing repetitive 18 month inspection

interval to be increased to no later than 24 months and no later than every 24 months thereafter.

All provisions of AD 2013-08-23, AD 2002-13-10 and AD 2011-11-05 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.

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
G. Manpower

The table below shows an estimate of the task hours necessary to do this change for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

NOTE: A range of Task Hours and Elapsed Hours are given to make the changes outlined in this

service bulletin. Actual Task Hours and Elapsed Hours is contingent upon wire kit installation.

Group 1, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 6 6

Change 1 16.0 to 68.0 16.0 to 68.0

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 34.0 to 86.0 28.0 to 80.0

Group 1, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 6 6

Change 1 14.8 to 66.8 14.8 to 66.8

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 32.8 to 84.8 26.8 to 78.8

Group 2, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 7 7

Change 1 18.0 to 45.0 18.0 to 45.0

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ALERT ALERT
Group 2, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 37.0 to 64.0 31.0 to 58.0

Group 2, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 7 7

Change 1 16.6 to 43.6 16.6 to 43.6

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 35.6 to 62.6 29.6 to 56.6

Group 3, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6 3

Replace 1 8 8

Change 1 20.0 to 47.0 20.0 to 47.0

Test 2 2 1

Close Access 2 6 3

TOTAL FOR EACH AIRPLANE 42.0 to 69.0 35.0 to 62.0

Group 3, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6 3

Replace 1 8 8

Change 1 18.4 to 45.4 18.4 to 45.4

Test 2 2 1

Close Access 2 6 3

TOTAL FOR EACH AIRPLANE 40.4 to 67.4 33.4 to 60.4

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ALERT ALERT
Group 4, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6 3

Replace 1 9 9

Change 1 26.0 to 62.0 26.0 to 62.0

Test 2 2 1

Close Access 2 6 3

TOTAL FOR EACH AIRPLANE 49.0 to 85.0 42.0 to 78.0

Group 4, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6 3

Replace 1 9 9

Change 1 24.2 to 60.2 24.2 to 60.2

Test 2 2 1

Close Access 2 6 3

TOTAL FOR EACH AIRPLANE 47.2 to 83.2 40.2 to 76.2

Group 5, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 5 5

Change 1 13.0 to 31.0 13.0 to 31.0

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 30.0 to 48.0 24.0 to 42.0

Group 5, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 5 5

Change 1 12.0 to 30.0 12.0 to 30.0

Test 2 2 1

Close Access 2 5 2.5

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ALERT ALERT
Group 5, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 29.0 to 47.0 23.0 to 41.0

Group 6, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 7 7

Change 1 20.0 to 58.0 20.0 to 58.0

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 39.0 to 77.0 33.0 to 71.0

Group 6, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 7 7

Change 1 18.6 to 56.6 18.6 to 56.6

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 37.6 to 75.6 31.6 to 69.6

Group 7, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 16 16

Change 1 13.0 to 38.0 13.0 to 38.0

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 41.0 to 66.0 35.0 to 60.0

Group 7, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

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ALERT ALERT
Group 7, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Replace 1 16 16

Change 1 12.0 to 37.0 12.0 to 37.0

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 40.0 to 65.0 34.0 to 59.0

Group 8, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 7 7

Change 1 21.0 to 48.0 21.0 to 48.0

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 40.0 to 67.0 34.0 to 61.0

Group 8, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5 2.5

Replace 1 7 7

Change 1 19.6 to 46.6 19.6 to 46.6

Test 2 2 1

Close Access 2 5 2.5

TOTAL FOR EACH AIRPLANE 38.6 to 65.6 32.6 to 59.6

H. Weight and Balance Changes

Group 1:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

1,056.5 +9.1 +9,640.4

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

DC-10-15

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ALERT ALERT
Group 2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

1,065.3 +7.9 +8,446.7

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

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

Group 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

DC-10-30 1,071.9 +8.8 +9,465.8

Group 4:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

DC-10-30F (KC-10A) 1,085.8 +10.5 +11,418.3

Group 5:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

1,044.2 +5.6 +5,869.1

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

DC-10-15

Group 6:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

DC-10-30F, MD-10-30F 1,074.7 +9.1 +9,825.8

Group 7:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-10-10F 1,021.4 +0.9 +950.6

Group 8:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

DC-10-30F (KDC-10) 1,076.7 +8.2 +8,837.5

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
I. Electrical Load Data

1. Direct Current DC Load Changes:

No DC loads added or deleted.

2. Alternating Current (AC) Load Changes:

a. Add AC loads by amounts shown below:

NOTE: Retain removed relay % TIME OPR for each BUS/CHAP/ITEM shown below (for

example BUS 12, CHAP 280, ITEM 501, U1-751 shall retain the % TIME OPR for

R2-51).

Group 1-4, 6, 8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1206)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Aux Tank Upper R Fuel

Pump Control

HDGE-X3F-001

ITEM

504

U1-

701

CHAP

280

BUS

12

Group 1-4, 6, 8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1207)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Aux Tank Upper L Fuel

Pump Control

HDGE-X3F-001

ITEM

504

U1-

702

CHAP

280

BUS

22

Group 2-4, 6, 8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1208)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Aux Tank Lower R Fuel

Pump Control

HDGE-X3F-001

ITEM

506

U1-

703

CHAP

280

BUS

32

Group 2-4, 6, 8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1209)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Aux Tank Lower L Fuel

Pump Control

HDGE-X3F-001

ITEM

507

U1-

704

CHAP

280

BUS

22

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ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-615)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 1 FWD Fuel Pump

Control

HDGE-X3F-001

ITEM

501

U1-

751

CHAP

280

BUS

12

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-613)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 1 L AFT Fuel

Pump Control

HDGE-X3F-001

ITEM

501

U1-

752

CHAP

280

BUS

32

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-611)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 1 XFR Fuel Pump

Control

HDGE-X3F-001

ITEM

503

U1-

753

CHAP

280

BUS

22

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-609)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 2 Fwd Fuel Pump

Control

HDGE-X3F-001

ITEM

502

U1-

754

CHAP

280

BUS

12

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-757)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 2 Fuel XFR Pump

Control

HDGE-X3F-001

ITEM

505

U1-

755

CHAP

280

BUS

32

Group 1-3, 5-8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-680)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 2 L AFT Fuel

Pump Cont

HDGE-X3F-001

ITEM

502

U1-

756

CHAP

280

BUS

3C

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ALERT ALERT
Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-680)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 2 L AFT Fuel

Pump Cont

HDGE-X3F-001

ITEM

502

U1-

756

CHAP

280

BUS

3E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-603)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 2 R AFT Fuel

Pump Control

HDGE-X3F-001

ITEM

502

U1-

757

CHAP

280

BUS

22

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-617)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 3 FWD Fuel Pump

Control

HDGE-X3F-001

ITEM

503

U1-

758

CHAP

280

BUS

32

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-621)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 3 R AFT Fuel

Pump Control

HDGE-X3F-001

ITEM

503

U1-

759

CHAP

280

BUS

22

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-619)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 3 XFR Pump Control

HDGE-X3F-001

ITEM

503

U1-

760

CHAP

280

BUS

12

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

NE

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1645)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

AFT Aux Tank L Fuel

Pump Control

HDGE-X3F-001

ITEM

503

U1-

790

CHAP

280

BUS

12

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ALERT ALERT
Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

NE

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1644)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

AFT Aux Tank R Fuel

Pump Control

HDGE-X3F-001

ITEM

502

U1-

789

CHAP

280

BUS

32

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1913)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

XFR Fuel Pump Control

Fwd Fus Tank

HDGE-X3F-001

ITEM

505

U1-

785

CHAP

280

BUS

12

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1915)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

XFR Fuel Pump Control

Aft Fus Tank

HDGE-X3F-001

ITEM

507

U1-

786

CHAP

280

BUS

32

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1871)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 3 TIP Fuel Pump

Control

HDGE-X3F-001

ITEM

508

U1-

787

CHAP

280

BUS

32

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1872)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tank 1 TIP Fuel Pump

Control

HDGE-X3F-001

ITEM

508

U1-

788

CHAP

280

BUS

22

b. Delete AC loads by amounts shown below:

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ALERT ALERT
Group 1-4, 6-8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1206)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Aux Tank Upper R Fuel

Pump Control Relay

5D0163-1

ITEM

504

R2-

101

CHAP

280

BUS

12

Group 1-4, 6-8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1207)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Aux Tank Upper L Fuel

Pump Control Relay

5D0163-1

ITEM

504

R2-

102

CHAP

280

BUS

22

Group 2-4, 6-8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1208)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Aux Tank Lower R Fuel

Pump Control Relay

5D0163-1

ITEM

506

R2-

103

CHAP

280

BUS

32

Group 2-4, 6-8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1209)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Aux Tank Lower L Fuel

Pump Control Relay

5D0163-1

ITEM

507

R2-

104

CHAP

280

BUS

22

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-615)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 1 FWD Fuel Pump

Control Relay

5D0163-1

ITEM

501

R2-51

CHAP

280

BUS

12

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-613)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 1 L AFT Fuel

Pump Control Relay

5D0163-1

ITEM

501

R2-52

CHAP

280

BUS

32

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ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-611)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank1 XFR Fuel Pump

Control Relay

5D0163-1

ITEM

503

R2-53

CHAP

280

BUS

22

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-609)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 2 Fwd Fuel Pump

Control Relay

5D0163-1

ITEM

502

R2-54

CHAP

280

BUS

12

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-757)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 2 Fuel XFR Pump

Control Relay

5D0163-1

ITEM

505

R2-55

CHAP

280

BUS

32

Group 1-3, 5-8:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-680)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 2 L AFT Fuel

Pump Cont Relay

5D0163-1

ITEM

502

R2-56

CHAP

280

BUS

3C

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-680)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 2 L AFT Fuel

Pump Cont Relay

5D0163-1

ITEM

502

R2-56

CHAP

280

BUS

3E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-603)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 2 R AFT Fuel

Pump Control Relay

5D0163-1

ITEM

502

R2-57

CHAP

280

BUS

22

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ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-617)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 3 FWD Fuel Pump

Control Relay

5D0163-1

ITEM

503

R2-58

CHAP

280

BUS

32

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-621)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 3 R

AFT Fuel Pump Control

Relay

5D0163-1

ITEM

503

R2-59

CHAP

280

BUS

22

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-619)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 3 XFR Pump Control Relay

5D0163-1

ITEM

503

R2-60

CHAP

280

BUS

12

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

NE

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1645)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

AFT Aux Tank L Fuel

Pump Control Relay

5D0163-1

ITEM

503

R2-90

CHAP

280

BUS

12

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

NE

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1644)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

AFT Aux Tank R Fuel

Pump Control Relay

5D0163-1

ITEM

502

R2-89

CHAP

280

BUS

32

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1913)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

XFR Fuel Pump Control

Fwd Fus Tank

5D0163-1

ITEM

505

R2-

185

CHAP

280

BUS

12

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ALERT ALERT
Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1915)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

XFR Fuel Pump Control

Aft Fus Tank

5D0163-1

ITEM

507

R2-

186

CHAP

280

BUS

32

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1871)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 3 TIP Fuel Pump

Control

5D0163-1

ITEM

508

R2-

187

CHAP

280

BUS

32

Group 4:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1872)

SUPPLIER

Hartman

(V74063)

EQUIPMENT NAME

PART NUMBER

Tank 1 TIP Fuel Pump

Control

5D0163-1

ITEM

508

R2-

188

CHAP

280

BUS

22

J. References

1. Existing Data:

a. Boeing Service Bulletin DC10-28-252 Revision 02, DC10-28A229, DC10-28A259 and

DC10-28A261 Revision 01.

b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2002-13-10, 2011-11-05

and 2013-08-23.

c. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 06-31-00, 06-32-01, 06-32-04, 06-37-00,

28-00-00, 28-22-00, 28-22-01, and 28-22-14.

d. DC-10, MD-10 Fleet Team Digest (FTD) 28-03003, 28-12001, 28-13001 and 28-13003.

e. DC-10, MD-10 Structural Repair Manual (SRM) 51.

f. Special Product Drawing SP10280068.

g. Standard Overhaul Practices Manual (SOPM) 20-50-01.

h. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01,

20-10-03, 20-20-03, 20-31-01, and 20-50-01.

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ALERT ALERT
a. Boeing Service Bulletin DC10-28-252, DC10-28A229, DC10-28A259, DC10-28A261

b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2002-13-10, 2002-13-10,

2011-11-05, 2013-08-23

c. Standard Overhaul Practices Manual (SOPM) 20-50-01

d. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-13, 20-00-16,

20-10-01, 20-10-03, 20-20-03, 20-31-01, 20-50-01

e. DC-10, MD-10 Fleet Team Digest (FTD) 28-03003, 28-12001, 28-13001, 28-13003

f. DC-10, MD-10 Structural Repair Manual (SRM) 51

g. DC-10 Aircraft Maintenance Manual (AMM) 06-31-00, 06-32-01, 06-32-04, 06-37-00, 28-00-00,

28-22-00, 28-22-01, 28-22-14

h. MD-10 Aircraft Maintenance Manual (AMM) 06-31-00, 06-32-01, 06-32-04, 06-37-00, 28-00-00,

28-22-00, 28-22-01, 28-22-14

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:

Drawing No Title Sheet DCN/REV ADCN

WIRE INSTALLATION - ELIMINATE CIR- AEO - H

CUIT GROUND FOR FUEL PUMP

SR10280053

DWG G -

ELECTRICAL INSTALLATION - FUEL AEO - F

PUMP FAULT CURRENT DETECTOR

SR10280068

DWG E -

ELECTRICAL INSTALLATION - FUEL DWG D -

PUMP FAULT CURRENT DETECTOR

SR10280071

3. Installation Drawings Used in the Preparation of this Service Bulletin:

None.

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ALERT ALERT
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

Fault Isolation Manual 28-14, 28-22, 28-23

Illustrated Parts Catalog 28-22

Schematic Manual 28-22

MDC-02K1003 (ALI 28-1, CDCCL 28-

10)

Special Compliance Item Report

Wiring Diagram Manual 28-21, 28-22, 28-43, 28-44, 28-46

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

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

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

NOTE: This service bulletin replaces existing fuel pump control relays with FCDs. After accomplishment

of this service bulletin airplanes cannot revert to the previously installed non-FCD fuel pump

control relays.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of the 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

SB10280253-3 Service Kit 150 $58,642.00

SB10280253-5 Service Kit 150 $65,249.00

SB10280253-7 Service Kit 150 $73,989.00

SB10280253-9 Service Kit 150 $88,424.00

SB10280253-11 Service Kit 150 $46,513.00

SB10280253-13 Service Kit 150 $67,541.00

SB10280253-15 Service Kit 150 $46,711.00

SB10280253-17 Service Kit 150 $69,605.00

SB10280253-19 Service Kit 150 $58,636.00

SB10280253-21 Service Kit 150 $65,243.00

SB10280253-23 Service Kit 150 $73,978.00

SB10280253-25 Service Kit 150 $84,060.00

SB10280253-27 Service Kit 150 $46,514.00

SB10280253-29 Service Kit 150 $65,537.00

SB10280253-31 Service Kit 150 $46,707.00

SB10280253-33 Service Kit 150 $65,243.00

Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to

help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

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ALERT ALERT
B. Industry Support Information

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

C. Parts Necessary for Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Group 1, Configuration 1:

Kit SB10280253-3

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 8 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 48 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

5D0086-25 12 TERMINAL LUG 765 (a)

HDGE-X3F-001 12 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 48 WASHER

NAS1252-8L 43 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 11 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-102 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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Group 1, Configuration 1:

Kit SB10280253-3

Part Number QTY Name Notes

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

(b) Refer to Wire Kit Table.

Group 1, Configuration 2:

Kit SB10280253-19

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 8 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 48 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

HDGE-X3F-001 12 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 48 WASHER

NAS1252-8L 43 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 11 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-102 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

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ALERT ALERT
Group 2, Configuration 1:

Kit SB10280253-5

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 10 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 56 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

HDGE-X3F-001 14 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 56 WASHER

NAS1252-8L 47 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 13 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 2, Configuration 2:

Kit SB10280253-21

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 10 SCREW (a)

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Group 2, Configuration 2:

Kit SB10280253-21

Part Number QTY Name Notes

3D0005-08-30 2 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 56 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

HDGE-X3F-001 14 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 56 WASHER

NAS1252-8L 47 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 13 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

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ALERT ALERT
Group 3, Configuration 1:

Kit SB10280253-7

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 11 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 64 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

CYW20 2 END CAP

HDGE-X3F-001 16 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 64 WASHER

NAS1252-8L 52 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 15 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

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ALERT ALERT
Group 3, Configuration 2:

Kit SB10280253-23

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 11 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 64 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 16 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 64 WASHER

NAS1252-8L 52 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 15 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 4, Configuration 1:

Kit SB10280253-9

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

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Group 4, Configuration 1:

Kit SB10280253-9

New Part Number QTY Name Notes

3D0005-08-32 2 SCREW (a)

3D0005-08-8 72 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 18 TERMINAL LUG 765 (a)

HDGE-X3F-001 18 FAULT CURRENT DTCTR

MS18029-6S7 2 COVER ASSY

MS20470AD3-3D 32 RIVET

MS20470AD4-4D 14 RIVET

MS27212-6-7 2 TERM BOARD ASSY

MS35338-42 14 LOCKWASHER

MS35649-282 14 NUT

NAS1149FN816P 86 WASHER

NAS1252-8L 54 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 16 SPACER

NAS620-4L 4 WASHER

NAS8200U7 4 SCREW

SR10280053-3 2 BRACKET ASSY

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

SR10280071-105 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
Group 4, Configuration 2:

Kit SB10280253-25

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 72 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 18 FAULT CURRENT DTCTR

MS20470AD3-3D 32 RIVET

NAS1149FN816P 72 WASHER

NAS1252-8L 54 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 16 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

SR10280071-105 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 5, Configuration 1:

Kit SB10280253-11

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 6 SCREW (a)

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
Group 5, Configuration 1:

Kit SB10280253-11

New Part Number QTY Name Notes

3D0005-08-30 3 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 40 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

5D0086-25 10 TERMINAL LUG 765 (a)

HDGE-X3F-001 10 FAULT CURRENT DTCTR

MS20470AD3-3D 16 RIVET

NAS1149FN816P 40 WASHER

NAS1252-8L 41 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 8 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 10 SPACER

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 5, Configuration 2:

Kit SB10280253-27

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 6 SCREW (a)

3D0005-08-30 3 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 40 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

HDGE-X3F-001 10 FAULT CURRENT DTCTR

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ALERT ALERT
Group 5, Configuration 2:

Kit SB10280253-27

New Part Number QTY Name Notes

MS20470AD3-3D 16 RIVET

NAS1149FN816P 40 WASHER

NAS1252-8L 41 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 8 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 10 SPACER

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 6, Configuration 1:

Kit SB10280253-13

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-28 10 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 58 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

ABN7377-600 1 BRACKET ASSY

HDGE-X3F-001 14 FAULT CURRENT DTCTR

MS18029-6S6 1 COVER ASSY

MS20470AD3-3D 24 RIVET

MS20470AD4-7D 7 RIVET

MS27212-6-6 1 TERMINAL BOARD

MS35338-42 8 LOCKWASHER

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ALERT ALERT
Group 6, Configuration 1:

Kit SB10280253-13

New Part Number QTY Name Notes

MS35649-282 6 NUT

NAS1149FN816P 62 WASHER

NAS1252-8L 52 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 14 SPACER

NAS620-4L 2 WASHER

NAS8200U7 2 SCREW

SR10280068-101 1 WIRE KIT (b)

SR10280068-102 1 WIRE KIT (b)

SR10280068-103 1 WIRE KIT (b)

TA4012C16 2 BRACKET

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

(b) Refer to Wire Kit Table.

Group 6, Configuration 2:

Kit SB10280253-29

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-28 10 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 58 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 14 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

MS35338-42 2 LOCKWASHER

NAS1149FN816P 56 WASHER

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ALERT ALERT
Group 6, Configuration 2:

Kit SB10280253-29

New Part Number QTY Name Notes

NAS1252-8L 52 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 14 SPACER

SR10280068-101 1 WIRE KIT (b)

SR10280068-102 1 WIRE KIT (b)

SR10280068-103 1 WIRE KIT (b)

TA4012C16 2 BRACKET

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

(b) Refer to Wire Kit Table.

Group 7, Configuration 1:

Kit SB10280253-15

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-28 8 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 42 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 10 TERMINAL LUG 765 (a)

HDGE-X3F-001 10 FAULT CURRENT DTCTR

MS20470AD3-3D 16 RIVET

MS35338-42 2 LOCKWASHER

NAS1149FN816P 40 WASHER

NAS1252-8L 48 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 8 NUTPLATE

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
Group 7, Configuration 1:

Kit SB10280253-15

Part Number QTY Name Notes

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 12 SPACER

SR10280068-102 1 WIRE KIT (b)

SR10280068-103 1 WIRE KIT (b)

TA4012C16 2 BRACKET

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

(b) Refer to Wire Kit Table.

Group 7, Configuration 2:

Kit SB10280253-31

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-28 8 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 42 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 10 FAULT CURRENT DTCTR

MS20470AD3-3D 16 RIVET

MS35338-42 2 LOCKWASHER

NAS1149FN816P 40 WASHER

NAS1252-8L 48 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 8 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 12 SPACER

SR10280068-102 1 WIRE KIT (b)

SR10280068-103 1 WIRE KIT (b)

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ALERT ALERT
Group 7, Configuration 2:

Kit SB10280253-31

Part Number QTY Name Notes

TA4012C16 2 BRACKET

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

(b) Refer to Wire Kit Table.

Group 8, Configuration 1:

Kit SB10280253-17

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 10 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 56 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

HDGE-X3F-001 14 FAULT CURRENT DTCTR

MS18029-6S7 2 COVER ASSY

MS20470AD3-3D 24 RIVET

MS20470AD4-4D 14 RIVET

MS27212-6-7 2 TERM BOARD ASSY

MS35338-42 14 LOCKWASHER

MS35649-282 14 NUT

NAS1149FN816P 70 WASHER

NAS1252-8L 47 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 13 SPACER

NAS620-4L 4 WASHER

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
Group 8, Configuration 1:

Kit SB10280253-17

New Part Number QTY Name Notes

NAS8200U7 4 SCREW

SR10280053-3 2 BRACKET ASSY

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 8, Configuration 2:

Kit SB10280253-33

New Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 7 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-28 10 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 1 SCREW (a)

3D0005-08-8 56 SCREW (a)

5D0061-2 1 TIE MOUNT (a)

HDGE-X3F-001 14 FAULT CURRENT DTCTR

MS20470AD3-3D 24 RIVET

NAS1149FN816P 56 WASHER

NAS1252-8L 47 WASHER

NAS1329S08KB75 1 RIVNUT

NAS1474A08 12 NUTPLATE

NAS43DD3-32FC 3 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 13 SPACER

SR10280071-101 1 WIRE KIT (b)

SR10280071-103 1 WIRE KIT (b)

SR10280071-104 1 WIRE KIT (b)

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BOEING SERVICE BULLETIN DC10-28A253

ALERT ALERT
Group 8, Configuration 2:

Kit SB10280253-33

New Part Number QTY Name Notes

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

(b) Refer to Wire Kit Table.

Group 1:

Wire Kit -101 -102 -103 -104

SR10280071

Part Number QTY Name Notes

D2426-1C-16NM 62 FT 175 FT 63 FT 73 FT WIRE CODE 801 (a)

D2426-1C-22NM 11 FT 143 FT - - WIRE CODE 801 (a)

D2426-1C-24NM 4 FT 4 FT 13 FT 12 FT WIRE CODE 801 (a)

5D0086-25 - 3 - - TERM LUG 765 (b)

5D0086-26 9 9 9 9 TERMINAL LUG 766 (b)

S00023-20S 1 - 1 1 SOCKET T/C 602/702 (b)

LRC22M-1DE5 - 1 - - SOCKET T/C 604

LRC16M-32DJ5 3 - 3 3 SOCKET T/C 706

5D0086-2 2 2 2 2 TERM LUG T/C 877 (b)

5D0086-3 1 1 1 1 TERM LUG T/C 878 (b)

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

(b) Or approved Equivalent. Refer to AEPL Drawing 7595071.

Group 2-3, 8:

Wire Kit -101 -103 -104

SR10280071

New Part Number QTY Name Notes

D2426-1C-16NM 62 FT 63 FT 73 FT WIRE CODE 801 (a)

D2426-1C-22NM 11 FT - - WIRE CODE 801 (a)

D2426-1C-24NM 4 FT 13 FT 12 FT WIRE CODE 801 (a)

5D0086-26 9 9 9 TERMINAL LUG 766 (b)

S00023-20S 1 1 1 SOCKET T/C 602/702 (b)

LRC16M-32DJ5 3 3 3 SOCKET T/C 706

5D0086-2 2 2 2 TERM LUG T/C 877 (b)

5D0086-3 1 1 1 TERM LUG T/C 878 (b)

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ALERT ALERT
Group 2-3, 8:

Wire Kit -101 -103 -104

SR10280071

New Part Number QTY Name Notes

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

(b) Or approved Equivalent. Refer to AEPL Drawing 7595071.

Group 4:

Wire Kit -101 -103 -104 -105

SR10280071

New Part Number QTY Name Notes

D2426-1C-16NM 62 FT 63 FT 73 FT 47 FT WIRE CODE 801 (a)

D2426-1C-22NM 11 FT - - 28 FT WIRE CODE 801 (a)

D2426-1C-24NM 4 FT 13 FT 12 FT - WIRE CODE 801 (a)

5D0086-26 9 9 9 9 TERMINAL LUG 766 (b)

S00023-20S 1 1 1 1 SOCKET T/C 602/702 (b)

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

LRC16M-32DJ5 3 3 3 - SOCKET T/C 706

5D0086-2 2 2 2 2 TERM LUG T/C 877 (b)

5D0086-3 1 1 1 4 TERM LUG T/C 878 (b)

5D0033-43 - - - 3 SPLICE T/C 1048 (b)

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

(b) Or approved Equivalent. Refer to AEPL Drawing 7595071.

Group 5:

Wire Kit -103 -104

SR10280071

New Part Number QTY Name Notes

D2426-1C-16NM 63 FT 73 FT WIRE CODE 801 (a)

D2426-1C-24NM 13 FT 12 FT WIRE CODE 801 (a)

5D0086-26 9 9 TERMINAL LUG 766 (b)

S00023-20S 1 1 SOCKET T/C 602/702 (b)

LRC16M-32DJ5 3 3 SOCKET T/C 706

5D0086-2 2 2 TERM LUG T/C 877 (b)

5D0086-3 1 1 TERM LUG T/C 878 (b)

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ALERT ALERT
Group 5:

Wire Kit -103 -104

SR10280071

New Part Number QTY Name Notes

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

(b) Or approved Equivalent. Refer to AEPL Drawing 7595071.

Group 6:

Wire Kit -101 -102 -103

SR10280068

New Part Number QTY Name Notes

D2426-1C-16NM 118 FT 93 FT 99 FT WIRE CODE 801 (a)

D2426-1C-24NM 10 FT 10 FT 27 FT WIRE CODE 801 (a)

D2426-1C-22NM 18 FT 31 FT - WIRE CODE 801 (a)

S00023-20S 1 - 1 SOCKET T/C 602/702 (b)

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

LRC16M-32DJ5 3 3 3 SOCKET T/C 706

5D0086-26 9 9 9 TERMINAL LUG 766 (b)

5D0086-3 1 1 1 TERM LUG T/C 878 (b)

5D0086-2 2 2 2 TERM LUG T/C 877 (b)

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

(b) Or approved Equivalent. Refer to AEPL Drawing 7595071.

Group 7:

Wire Kit -102 -103

SR10280068

New Part Number QTY Name Notes

D2426-1C-16NM 93 FT 99 FT WIRE CODE 801 (a)

D2426-1C-24NM 10 FT 27 FT WIRE CODE 801 (a)

D2426-1C-22NM 31 FT - WIRE CODE 801 (a)

S00023-20S - 1 SOCKET T/C 602/702 (b)

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

LRC16M-32DJ5 3 3 SOCKET T/C 706

5D0086-26 9 9 TERMINAL LUG 766 (b)

5D0086-3 1 1 TERM LUG T/C 878 (b)

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ALERT ALERT
Group 7:

Wire Kit -102 -103

SR10280068

New Part Number QTY Name Notes

5D0086-2 2 2 TERM LUG T/C 877 (b)

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

(b) Or approved Equivalent. Refer to AEPL Drawing 7595071.

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

18XTZ, 23XTZ 1 Roll STRING TIE (a)

(DMS 2089)

or

Equivalent

Alodine 1200S As Required COATING CHEMICAL FILM, LIQUID (b)

(DPM 1453-5)

or

Equivalent

515X347 Base with 4 Oz PRIMER, FR (c)

910X527 Catalyst

(DMS 1786)

or

Equivalent

ENAMEL, HIGH SOLIDS EPOXY TOPCOAT, GLOSS (d)

WHITE

446-21-Ser Base 1 Oz

with

530 Activator

(DMS 2433)

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

(c) Can be purchased from: PRC-DeSoto International Incorporated, 11601 United Street, Mojave,

California 93501, CAGE: 85570

(d) Can be purchased from: Akzo Nobel Aerospace Coatings Incorporated, 1 East Water Street

Waukegan, Illinois 60085, CAGE: 91342

3. Parts Modified and Reidentified

None.

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ALERT ALERT
4. Parts Removed and Not Replaced

Group 1-6, 8:

None.

Group 7:

Existing Part Name QTY Notes

Number

5D0163-1 Relay 4 (a) (b)

(a) Equipment Item Numbers R2-101, R2-102, R2-103, and R2-104.

(b) Keep the part if there are other uses for it.

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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ALERT ALERT
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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY

ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE

PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE

CAN OCCUR.

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 DC-10,

MD-10 SRM 51.

4. If the length of any fastener specified in this service bulletin does not meet installation

standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of

the same specification, or an approved substitute, with a length which meets the

installation standards given in SRM Chapter 51 may be used. In addition, washers

may be installed for fastener grip length in accordance with SRM Chapter 51. 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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ALERT ALERT
SWPM 20-00-03 Identification of Electrical Wire - Commercial

SWPM 20-00-09 General Maintenance Practices - Electrical

SWPM 20-00-13 Electrical Wire Codes

SWPM 20-00-16 Electrical Wire End Termination Codes and Tool Codes

SWPM 20-10-01 Wiring Installation - Maintenance Practices

SWPM 20-10-03 Wire Splicing - Maintenance Practices

SWPM 20-20-03 General Installation Hardware - Maintenance Practices

Amphenol Series 48 Electrical Connectors - Maintenance PracticesSWPM 20-31-01

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. Review and understand all general notes of Service Rework Drawing SR10280053

sheets 3, 3.1, 3.2 before start of modification.

15. Group 1-5, 8:

Review and understand all general notes of Service Rework Drawing SR10280071

sheets 3, 3.1, 3.2 and 3.3 before start of modification.

Group 6-7:

Review and understand all general notes of Service Rework Drawing SR10280068

sheets 3, 3.1, 3.2, 3.3 and 3.4 before start of modification.

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16. The FCD is intended for use with ONLY airplane Original Equipment Manufacturer

(OEM) certified fuel pumps and fuel pump housings, including OEM pump/housing

spare parts and parts repaired per OEM approved repair instructions.

B. WORK INSTRUCTIONS

Group 1, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 6.16, 6.17, 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8, 9, 13

Generator 2 EPC Equipment Panel 7, 8, 14.1, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.31, 6.34, 6.39, 6.48, 7, 8, 11, 15

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.19, 6.20, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

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6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in step 7 below.

Refer to DC-10 AMM 28-22-01 as an accepted procedure.

7. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-802, S3-803 8.4, 10, 14, 301.201

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 301.201, 301.202

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 301.201

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 301.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 301.201

8. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

9. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

10. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

11. Close access.

12. Put the airplane back to a serviceable condition.

Group 1, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11

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Location Service Rework Drawing SR10280071 Sheets

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 6.16, 6.17, 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8, 9, 13.

Generator 2 EPC Equipment Panel 7, 8, 14.1, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.31, 6.34, 6.39, 6.48, 7, 8, 11, 15

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.19, 6.20, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 2, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

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Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.1

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11.1

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.25, 6.26, 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8,

9.1, 13

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.22, 6.23, 6.31, 6.34, 6.39, 6.48, 7, 8, 11.1, 15.1

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in step 7 below.

Refer to DC-10 AMM 28-22-01 as an accepted procedure.

7. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-802, S3-803 8.4, 10, 14, 302.201

S3-804, S3-805 8.4, 10, 15, 302.201

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 302.201, 302.202

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 302.201, 302.202

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 302.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 302.201

8. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

9. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

10. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

11. Close access.

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12. Put the airplane back to a serviceable condition.

Group 2, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.1

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11.1

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.25, 6.26, 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8,

9.1, 13

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.22, 6.23, 6.31, 6.34, 6.39, 6.48, 7, 8, 11.1, 15.1

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

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7. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 3, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.2

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11.2

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.27, 6.28, 6.30, 6.33, 6.40, 6.41, 6.43, 6.48,

7, 8, 9.2, 13.1

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

6.22, 6.23, 6.31, 6.34, 6.39, 6.42, 6.48, 7, 8, 11.2,

15.2

Generator 3 EPC Equipment Panel

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Location Service Rework Drawing SR10280071 Sheets

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in step 7 below.

Refer to DC-10 AMM 28-22-01 as an accepted procedure.

7. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-802, S3-803 8.4, 10, 14, 302.201

S3-804, S3-805 8.4, 10, 15, 302.201

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 302.201, 302.202

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 302.201, 302.202

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 302.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 302.201

P1-4815, P1-4816 8.5, 10, 11, 303.201

8. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

9. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

10. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

11. Close access.

12. Put the airplane back to a serviceable condition.

Group 3, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

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Door Number Location Refer to

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.2

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11.2

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.27, 6.28, 6.30, 6.33, 6.40, 6.41, 6.43, 6.48,

7, 8, 9.2, 13.1

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

6.22, 6.23, 6.31, 6.34, 6.39, 6.42, 6.48, 7, 8, 11.2,

15.2

Generator 3 EPC Equipment Panel

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT)in accordance with DC-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 4, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

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2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

741 Main Landing Gear (MLG) door, right-side DC-10 AMM 06-37-00

731 MLG door, left-side

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.3

Upper EPC Equipment Panel 7, 8, 10.1

Generator 3 EPC Equipment Panel 7, 8, 11.3

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10.1, 22, and 23.1.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.29, 6.30, 6.33, 6.40, 6.41, 6.44, 6.48, 7, 8,

9.3, 13.2

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.3, 17, 18, 19

6.24, 6.31, 6.34, 6.39, 6.45, 6.46, 6.48, 7, 8, 11.3,

15.3

Generator 3 EPC Equipment Panel

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.47, 6.48, 7, 8, 10.1

CAC 7, 8, 20, 21

6. Gain access to boost/transfer pump terminal boards and ground studs noted in steps 7 and 8

below. Refer to DC-10 AMM 28-22-01 as an accepted procedure.

7. Change terminal board and fuel boost/transfer pump ground wire termination in accordance with

the table that follows:

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ALERT ALERT
Equipment Item Numbers Service Rework Drawing SR10280053 Sheets Note

S3-802, S3-803 8.4.1, 10, 14, 26, 27, 28, 304.201 (a)

(a) Existing airplane wiring configuration is contingent upon Service Bulletin DC10-28-252 incorporation.

8. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets Note

S3-804, S3-805 8.4, 10, 15, 304.201

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 304.201, 304.202

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 304.202

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 304.201, 304.202

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 304.201, 304.202

S3-1110 8.6, 10, 23, 304.201

S3-1109 8.6, 10, 22, 304.201

S3-1072 8.7, 10, 12, 304.201

S3-1071 8.7, 10, 13, 304.202

9. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 4, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

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Door Number Location Refer to

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

741 Main Landing Gear (MLG) door, right-side DC-10 AMM 06-37-00

731 MLG door, left-side

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.3

Upper EPC Equipment Panel 7, 8, 10.1

Generator 3 EPC Equipment Panel 7, 8, 11.3

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10.1, 22, and 23.1.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.29, 6.30, 6.33, 6.40, 6.41, 6.44, 6.48, 7, 8,

9.3, 13.2

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.3, 17, 18, 19

6.24, 6.31, 6.34, 6.39, 6.45, 6.46, 6.48, 7, 8, 11.3,

15.3

Generator 3 EPC Equipment Panel

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.47, 6.48, 7, 8, 10.1

CAC 7, 8, 20, 21

6. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT)in accordance with DC-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

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Group 5, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.4

Upper EPC Equipment Panel 7, 8, 10.2

Generator 3 EPC Equipment Panel 7, 8, 11

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10.2, 22.2, and 23.2.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8, 9.4, 13.3,

Generator 2 EPC Equipment Panel 7, 8, 14.1, 14.4, 17, 18, 19

Generator 3 EPC Equipment Panel 6.31, 6.34, 6.39, 6.48, 7, 8, 11, 15

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.32, 6.38, 6.48, 7, 8, 10.2

CAC 7, 8, 20, 21

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in step 7 below.

Refer to DC-10 AMM 28-22-01 as an accepted procedure.

7. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

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Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 305.201

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 305.201

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 305.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 305.201

8. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

9. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

10. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

11. Close access.

12. Put the airplane back to a serviceable condition.

Group 5, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.4

Upper EPC Equipment Panel 7, 8, 10.2

Generator 3 EPC Equipment Panel 7, 8, 11

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10.2, 22.2, and 23.2.

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5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8, 9.4, 13.3

Generator 2 EPC Equipment Panel 7, 8, 14.1, 14.4, 17, 18, 19

Generator 3 EPC Equipment Panel 6.31, 6.34, 6.39, 6.48, 7, 8, 11, 15

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.32, 6.38, 6.48, 7, 8, 10.2

CAC 7, 8, 20, 21

6. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 6, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD-10 AMM 06-31-00

112CZ Forward Equipment Panel MD-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) MD-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) MD-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

741 Main Landing Gear (MLG) door, right-side MD-10 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows:

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Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280068

sheets 10, 25, and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 6.7, 6.10, 6.11, 6.14, 6.19, 6.20, 6.22, 7, 8, 9, 13

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.9, 6.12, 6.15, 6.18, 6.22, 7, 8, 11, 15

AC Forward Equipment Panel 6.16, 6.22, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.8, 6.13, 6.17, 6.22, 7, 8, 10

CAC 7, 8, 20, 21, 22, 23, 24

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and

8 below. Refer to MD-10 AMM 28-22-01 as an accepted procedure.

7. Change terminal board and fuel boost/transfer pump ground wire termination in accordance with

the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets Note

S3-805 8.4.1, 10, 15, 24, 25, 306.201 (a)

(a) Existing airplane wiring configuration is contingent upon Service Bulletin DC10-28-252 incorporation.

8. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-802, S3-803 8.4, 10, 14, 306.201

S3-804 8.4, 10, 15, 306.201

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 306.201, 306.202

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 306.201, 306.202

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 306.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 306.201

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9. Close fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to MD-10 AMM 28-22-00 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with MD-10 AMM 28-22-14.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 6, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD-10 AMM 06-31-00

112CZ Forward Equipment Panel MD-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) MD-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) MD-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

741 Main Landing Gear (MLG) door, right-side MD-10 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280068

sheets 10, 25, and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 6.7, 6.10, 6.11, 6.14, 6.19, 6.20, 6.22, 7, 8, 9, 13

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

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Location Service Rework Drawing SR10280068 Sheets

Generator 3 EPC Equipment Panel 6.9, 6.12, 6.15, 6.18, 6.22, 7, 8, 11, 15

AC Forward Equipment Panel 6.16, 6.22, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.8, 6.13, 6.17, 6.22, 7, 8, 10

CAC 7, 8, 20, 21, 22, 23, 24

6. Close fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to MD-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with MD-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 7, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD-10 AMM 06-31-00

112CZ Forward Equipment Panel MD-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) MD-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) MD-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.1

Upper EPC Equipment Panel 7, 8, 10.1

Generator 3 EPC Equipment Panel 7, 8, 11.1

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280068

sheets 10.1, 25.1, and 26.1.

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5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 6.11, 6.14, 6.19, 6.20, 6.21, 6.22, 7, 8, 9.1, 13.1,

Generator 2 EPC Equipment Panel 7, 8, 14.1, 14.3, 17, 18, 19

Generator 3 EPC Equipment Panel 6.12, 6.15, 6.18, 6.21, 6.22, 7, 8, 11.1, 15.1

AC Forward Equipment Panel 6.16, 6.22, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.13, 6.17, 6.21, 6.22, 7, 8, 10.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in step 7 below.

Refer to MD-10 AMM 28-22-01 as an accepted procedure.

7. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 305.201

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 305.201

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 305.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 305.201

8. Close fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted procedure.

9. Do operational test of the fuel pumps. Refer to MD-10 AMM 28-22-00 as an accepted procedure.

10. Do FCD Functional Test (BIT) in accordance with MD-10 AMM 28-22-14.

11. Close access.

12. Put the airplane back to a serviceable condition.

Group 7, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD-10 AMM 06-31-00

112CZ Forward Equipment Panel MD-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) MD-10 AMM 06-31-00

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Door Number Location Refer to

131AZ Electrical Power Center (EPC) Components (Bay 1) MD-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.1

Upper EPC Equipment Panel 7, 8, 10.1

Generator 3 EPC Equipment Panel 7, 8, 11.1

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280068

sheets 10.1, 25.1, and 26.1.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280068 Sheets

Generator 1 EPC Equipment Panel 6.11, 6.14, 6.19, 6.20, 6.21, 6.22, 7, 8, 9.1, 13.1

Generator 2 EPC Equipment Panel 7, 8, 14.1, 14.3, 17, 18, 19

Generator 3 EPC Equipment Panel 6.12, 6.15, 6.18, 6.21, 6.22, 7, 8, 11.1, 15.1

AC Forward Equipment Panel 6.16, 6.22, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.13, 6.17, 6.21, 6.22, 7, 8, 10.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Close fuel system circuit breakers. Refer to MD-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to MD-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with MD-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 8, Configuration 1:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

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Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

741 Main Landing Gear (MLG) door, right-side DC-10 AMM 06-37-00

731 MLG door, left-side

3. Remove fuel pump control relays in accordance with the table that follows:

Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.1

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11.1

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.25, 6.26, 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8,

9.1, 13

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.22, 6.23, 6.31, 6.34, 6.39, 6.48, 7, 8, 11.1, 15.1

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and

8 below. Refer to DC-10 AMM 28-22-01 as an accepted procedure.

7. Change terminal board and fuel boost/transfer pump ground wire termination in accordance with

the table that follows:

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Equipment Item Numbers Service Rework Drawing SR10280053 Sheets Note

S3-802, S3-803 8.4.1, 10, 14, 26, 27, 28, 307.201 (a)

(a) Existing airplane wiring configuration is contingent upon Service Bulletin DC10-28-252 incorporation.

8. Change fuel boost/transfer pump ground wire termination in accordance with the table that follows:

Equipment Item Numbers Service Rework Drawing SR10280053 Sheets

S3-804, S3-805 8.4, 10, 15, 307.201

S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 307.201, 307.202

S3-374, S3-377 8.2, 8.3, 10, 17, 18, 307.201, 307.202

S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 307.201

S3-368, S3-371 8.1, 8.2, 10, 20, 21, 307.201

9. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with DC-10 AMM 28-22-14.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 8, Configuration 2:

1. Open and safety fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) DC-10 AMM 06-31-00

112CZ Forward Equipment Panel DC-10 AMM 06-32-01

131AB Center Accessory Compartment (CAC) DC-10 AMM 06-31-00

131AZ Electrical Power Center (EPC) Components (Bay 1) DC-10 AMM 06-32-04

131BZ EPC Components (Bay 2)

132AZ EPC Components (Bay 3)

741 Main Landing Gear (MLG) door, right-side DC-10 AMM 06-37-00

731 MLG door, left-side

3. Remove fuel pump control relays in accordance with the table that follows:

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Location Service Rework Drawing SR10280071 Sheets

Generator 1 EPC Equipment Panel 7, 8, 9.1

Upper EPC Equipment Panel 7, 8, 10

Generator 3 EPC Equipment Panel 7, 8, 11.1

AC Forward Equipment Panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR10280071

sheets 10, 22.1, and 23.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR10280071 Sheets

6.18, 6.25, 6.26, 6.30, 6.33, 6.40, 6.41, 6.48, 7, 8,

9.1, 13

Generator 1 EPC Equipment Panel

Generator 2 EPC Equipment Panel 7, 8, 14, 14.2, 17, 18, 19

Generator 3 EPC Equipment Panel 6.22, 6.23, 6.31, 6.34, 6.39, 6.48, 7, 8, 11.1, 15.1

AC Forward Equipment Panel 6.35, 6.36, 6.37, 6.48, 7, 8.1, 12, 16

Upper EPC Equipment Panel 6.21, 6.32, 6.38, 6.48, 7, 8, 10

CAC 7, 8, 20, 21

6. Close fuel system circuit breakers. Refer to DC-10 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to DC-10 AMM 28-22-00 as an accepted procedure.

8. Do FCD functional test (BIT) in accordance with DC-10 AMM 28-22-14.

9. Close access.

10. Put the airplane back to a serviceable condition.

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APPENDIX A: INPUT SURVEY

(SHEET 1 OF 1)

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