Commercial McDonnell Douglas

Airplanes DC10

Service Bulletin

ALERT

Number: DC10-28A261

Original Issue: December 01, 2009

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and

Fuel Boost/Transfer Pump - Inspection/Replacement

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

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Copyright © 2009 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

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3.0
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BLANK PAGE
Table of Contents

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

1. PLANNING INFORMATION ........................................ 7

A. Effectivity ................................................ 7

1. Airplanes ............................................. 7

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 21

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 31

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 . . 44

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 . . . 50

APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84355-1 INSPECTION LOGIC DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . 54

APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84351 INSPECTION LOGIC DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . 55

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BLANK PAGE
Commercial McDonnell Douglas

Airplanes DC10

Service Bulletin

ALERT

Summary Number: DC10-28A261

Original Issue: December 01, 2009

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and

Fuel Boost/Transfer Pump - Inspection/Replacement

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

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

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

THE NEW OWNER.

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly, part

number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector assembly,

fuel boost/transfer pump and replacing any non-serviceable part with a serviceable part as required based on

inspection results, will minimize the possibility of a potential ignition source in the fuel tanks and potential fuel

tank explosion. If not corrected, insulation resistance degradation and/or arcing in the potted backside of the

fuel boost/transfer pump housing electrical connector assembly could compromise the performance of the fuel

boost/transfer pump housing electrical connector assembly and result in a failure that can introduce an ignition

source into the fuel tank and potential fuel tank explosion.

ACTION

This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector assembly

and fuel boost/transfer pump.

EFFECTIVITY

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

Refer to Paragraph 1.E., Compliance.

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INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes and repair procedures 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.

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Commercial McDonnell Douglas

Airplanes DC10

Service Bulletin

ALERT

Number: DC10-28A261

Original Issue: December 01, 2009

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and

Fuel Boost/Transfer Pump - Inspection/Replacement

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

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

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

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is applicable to airplanes that have installed fuel pump housing electrical

connector assembly part number 60-84355-1 in accordance with Service Bulletin DC10-28A259.

NOTE: The fuel pump housing electrical connector replacement with part number 60-84351 was

done on airplane fuselage number 342 prior to the original issue of this service bulletin

in accordance with Drawing SP10280068 and FAA Alternative Method of Compliance

(AMOC) approval letter with referenced Boeing letter CP-L4L-09-00243.

NOTE: Group 3 airplanes with Aft Aux tank installed must inspect fuel boost/transfer pump

installation per this procedure, unless deactivated per SR10280047 "C" change (or later)

Service Rework Drawing.

NOTE: DC-10-10 Airplanes with auxiliary upper fuel tanks that are modified to MD-10-10F

configuration by Boeing Engineering will become Group 5 airplanes.

GROUP CONFIGURATION DESCRIPTION

1 - Airplanes with 1, 2, 3, and Auxiliary Upper Fuel Tanks.

2 - Airplanes with 1, 2, 3, Auxiliary Upper and Lower Fuel Tanks.

3 - Airplanes with 1, 2, 3, Auxiliary Upper, Lower, and AFT Fuel Tanks.

Airplanes with 1, 2, 3, Auxiliary Upper, Lower, FWD, AFT, and Wing

Tip Fuel Tanks.

4 -

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GROUP CONFIGURATION DESCRIPTION

5 - Airplanes with 1, 2, and 3 Fuel Tanks.

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

100 2

103 2

106 2

110 2

112 5

114 - 115 2

117 2

119 5

122 - 123 2

127 2

129 2

131 - 135 2

137 2

138 - 140 5

142 5

144 - 145 5

146 - 147 2

148 5

15 5

150 2

152 2

153 - 155 5

156 - 158 2

160 2

162 5

165 - 166 2

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Fuselage Num- Group

ber

169 5

17 5

170 - 171 2

173 5

174 2

177 5

178 - 179 2

183 - 184 2

187 - 190 2

192 2

194 5

195 - 196 2

198 5

199 2

2 1

201 2

203 5

204 2

205 5

206 2

207 - 210 5

211 - 216 2

220 - 221 2

223 - 227 2

229 - 230 2

232 2

234 - 236 2

239 - 240 2

242 2

244 - 246 2

247 5

248 2

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Fuselage Num- Group

ber

249 5

25 5

250 5

251 - 252 1

253 - 257 2

26 5

261 - 268 2

269 1

27 5

270 - 271 5

272 1

273 5

274 - 275 2

277 2

281 - 282 2

285 1

286 2

289 - 291 2

292 3

294 5

296 - 298 5

299 - 306 2

307 5

308 2

309 5

310 2

311 4

312 - 317 2

318 1

319 5

32 5

321 5

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Fuselage Num- Group

ber

323 5

324 - 327 2

329 2

33 5

330 2

332 2

333 4

334 - 338 2

34 5

340 2

341 3

342 - 343 2

344 5

345 3

346 1

347 5

349 2

35 5

351 5

353 5

355 - 356 2

358 5

359 - 361 4

363 4

366 - 367 2

372 1

373 4

375 - 378 4

379 5

380 4

381 2

383 - 389 4

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Fuselage Num- Group

ber

39 5

390 - 399 4

40 5

400 - 408 4

409 2

41 5

410 - 411 4

412 2

413 - 415 4

416 2

417 - 418 4

419 2

42 5

420 - 421 4

422 2

423 - 429 4

43 5

430 - 432 4

433 2

434 - 438 3

439 4

440 2

441 4

442 - 446 2

55 5

59 5

6 5

61 - 62 5

65 1

70 5

72 1

76 5

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Fuselage Num- Group

ber

78 5

8 5

83 1

86 5

89 5

90 2

96 2

99 2

2. Spares Affected

Examine your spares supply for the parts or components identified in below. For the recommended

use Paragraph 2.D., Parts Necessary to Change Spares. If any parts or components are found.

Part Number Name

60-843-3 Pump Housing

60-845-3 Pump Housing

60-84355-1 Connector

B. Concurrent Requirements

None.

C. Reason

MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly,

part number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector

assembly, fuel boost/transfer pump and replacing any non-serviceable part with a serviceable part as

required based on inspection results, will minimize the possibility of a potential ignition source in the

fuel tanks and potential fuel tank explosion. If not corrected, insulation resistance degradation and/or

arcing in the potted backside of the fuel boost/transfer pump housing electrical connector assembly

could compromise the performance of the fuel boost/transfer pump housing electrical connector assembly

and result in a failure that can introduce an ignition source into the fuel tank and potential fuel tank

explosion.

D. Description

This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector

assembly and fuel boost/transfer pump.

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

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Group 1:

Affected Maintenance Zones

Model Zone

DC-10-10, DC-10-10F, DC-10- 144, 145, 511, 512, 514, 541, 611, 612, 614, 641

15, MD-10-10F

Group 2:

Affected Maintenance Zones

Model Zone

DC-10-30, DC-10-30F, DC-10- 144, 145, 511, 512, 514, 541, 611, 612, 614, 641

30F (KDC-10), DC-10-40, DC10-40F, MD-10-30F

Group 3:

Affected Maintenance Zones

Model Zone

144, 145, 186, 511, 512, 514, 541, 611, 612,

614, 641

DC-10-30

Group 4:

Affected Maintenance Zones

Model Zone

144, 145, 186, 254, 511, 512, 514, 551, 611,

612, 614, 641, 651

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

Group 5:

Affected Maintenance Zones

Model Zone

DC-10-10, DC-10-10F, DC-10- 511, 512, 514, 541, 611, 612, 614, 641

15, MD-10-10F

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive FAA AD 2007-15-05 is related to this

service bulletin.

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Refer to Appendix D for a logic diagram of the work instructions.

TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL

BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 10 months af- (a)

ter the original issue

date on this service

bulletin.

Replace fuel pump electrical

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part

5.

All Airplanes.

OR

Within 10 months after the original issue

date on this service

bulletin.

Do continuity, resistance and

insulation resistance inspection

in accordance with Accomplishment Instructions 3.B. Part 3.

AND

Replace fuel pump electrical

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part

5.

Within 12 months af- (a)

ter inspection.

Do restoration in accordance Before further flight.

with Accomplishment Instructions 3.B. Part 5.

(Serviceable Fuel pump and housing electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is less than or equal to 2.5

ohms and terminal E is open.

AND

Fuel boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

AND

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is greater than

or equal to 10 gigaohm.

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TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL

BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Replace fuel boost/transfer Before further flight.

pump and restore in accordance

with Accomplishment Instructions 3.B. Part 3 and Part 5.

(Defective Fuel boost/transfer

pump)

Fuel boost/transfer pump resistance

reading is greater than 2.5 ohms or

pin E is not open and fuel pump

housing electrical connector assembly wiring resistance reading is less

than or equal to 2.5 ohms and terminal E is open and fuel pump

housing electrical connector assembly wiring insulation resistance

reading is greater than or equal to

10 gigaohm.

Replace fuel pump electrical Before further flight. (a)

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part

5.

(Defective Fuel pump housing

electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is greater than 2.5 ohms or

terminal E is not open and fuel

boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

OR

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is less than 10

gigaohm.

(a) REFER TO TABLE 2 AFTER REPLACEMENT OF FUEL PUMP HOUSING ELECTRICAL CONNECTOR

ASSEMBLY P/N 60-84355-1 WITH P/N 60-84351.

TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL

BOOST/TRANSFER PUMP - INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 18 months af- 18 Months

ter P/N 60-84351 installation.

Do continuity, resistance and

insulation resistance inspection

in accordance with Accomplishment Instructions 3.B. Part 4.

All Airplanes

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TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL

BOOST/TRANSFER PUMP - INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do restoration in accordance Before further flight.

with Accomplishment Instructions 3.B. Part 5.

(Serviceable Fuel pump and housing electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is less than or equal to 2.5

ohms and terminal E is open.

AND

Fuel boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

AND

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is greater than

or equal to 10 megaohm.

Replace fuel boost/transfer Before further flight.

pump and restore in accordance

with Accomplishment Instructions 3.B. Part 4 and Part 5.

(Defective Fuel boost/transfer

pump)

Fuel boost/transfer pump resistance

reading is greater than 2.5 ohms or

pin E is not open and fuel pump

housing electrical connector assembly wiring resistance reading is less

than or equal to 2.5 ohms and terminal E is open and fuel pump

housing electrical connector assembly wiring insulation resistance

reading is greater than or equal to

10 megaohm.

Replace fuel pump electrical Before further flight.

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 4 and Part

5.

(Defective Fuel pump housing

electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is greater than 2.5 ohms or

terminal E is not open and fuel

boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

OR

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is less than 10

megaohm.

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F. Approval

For MD-10 models:

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.

For DC-10 models:

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e.

inspection or modification) defined in this service bulletin as an alternative method of compliance to

the requirements of Paragraph (k) of FAA AD 2007-15-05. All provisions of FAA AD 2007-15-05 that

are not specifically referenced in the above statement remain fully applicable and must be complied

with.

G. Manpower

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

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

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

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 8.0 4.0

Inspect 2 24.0 12.0

Change 2 *0.1 - 24.0 *0.05 - 12.00

Close Access 2 8.0 4.0

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

Test 2 2.0 1.0

TOTAL FOR EACH AIRPLANE *42.1 - 66.0 *21.05 - 33.00

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 8.0 4.0

Inspect 2 28.0 14.0

Change 2 *0.1 - 28.0 *0.05 - 14.00

Close Access 2 8.0 4.0

Test 2 3 1.5

TOTAL FOR EACH AIRPLANE *47.1 - 75.0 *23.55 - 37.50

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 8.0 4.0

Inspect 2 30.0 15.0

Change 2 *0.1 - 30.0 *0.05 - 15.00

Close Access 2 8.0 4.0

Test 2 3 1.5

TOTAL FOR EACH AIRPLANE *49.1 - 79.0 *24.55 -.39.50

Group 4:

Task Number of Persons Task Hours Elapsed Hours

Open Access 3 12.0 4.0

Inspection 2 36.0 18.0

Change 2 *0.1 - 44.0 *0.05 - 22.00

Close Access 3 12.0 4.0

Test 2 4.0 2.0

TOTAL FOR EACH AIRPLANE *68.1 - 108.0 *30.05 - 50.00

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Group 5:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Inspect 2 20.0 10.0

Change 2 *0.1 - 20.0 *0.05 - 10.00

Close Access 2 6.0 3.0

Test 2 2.0 1.0

TOTAL FOR EACH AIRPLANE *30.1 - 54.0 *15.05 - 27.00

*A range of total task hours and elapsed hours are given for inspection per airplane. Actual task hours

and elapsed hours for the change are contingent upon inspection findings and are to be estimated by

the operator.

H. Weight and Balance Changes

Weight and balance changes affected by incorporation of this service bulletin are contingent upon the

changes to each particular airplane. Weight data is to be computed by the operator by weighing parts

removed and parts installed during this change. Necessary revisions should be made to the appropriate

airplane weight and balance report.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Boeing Service Bulletin DC10-28A229 and DC10-28A259.

b. Boeing Service Rework Drawing SR10280047.

c. Federal Aviation Administration (FAA) Airworthiness Directive 2007-15-05.

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

20-10-01,20-10-04, 20-20-01, 20-20-02, 20-20-03, 20-31-00, and 20-50-01.

e. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 12-11-03, 20-20-06, 28-00-00, 28-22-00

and 28-22-01.

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

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g. Wiring Diagram Manual (WDM) 28-22-01, 28-22-02, 28-22-03, 28-22-04 and 28-43-01.

h. Crane Hydro-Aire Service Information Letters 60-847-3-1 and 60-843-845-3-28-2.

i. FAA Alternative Method of Compliance (AMOC) approval letter with referenced Boeing letter

CP-L4L-09-00243.

2. Data supplied with this Service Bulletin

No data is supplied with this service bulletin. To obtain the data necessary to support this service

bulletin submit a data request to:

Data and Services Management

MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

ELEC INSTL - FUEL PUMP ELECTRICAL DWG C -

CONNECTOR

SR10280075

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

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

Aircraft Maintenance Manual (DC-10, KC-10,KDC-10, MD-10) 28-22

Fault Isolation Manual (FIM) (MD-10) 28-14 and 28-22

Illustrated Parts Catalog 28-13 and 28-22

On Aircraft Maintenance Planning (OAMP) (DC-10, MD-10) 28

Turn Around Fault Isolation Manual (TAFI) (DC-10, KC-10, KDC-10) 28-02

Wiring Diagram Manual Equipment List 28-22 and 28-43

Wiring Diagram Manual 28-22

2. Damage Tolerance Based Structural Inspections:

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ALERT ALERT
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.

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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 as shown

below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.

More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the

date Boeing gets the purchase order.

Part Number Name ROLT (Weeks) Unit Price thru November 30, 2010

SR10280075-3 SERVICE KIT 13 $267.00

SR10280075-5 SERVICE KIT 13 41.00

SR10280075-7 SERVICE KIT 13 9.00

SR10280075-9 SERVICE KIT 13 1,503.00

SR10280075-11 SERVICE KIT 13 1,561.00

SR10280075-13 SERVICE KIT 13 372.00

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

After the Unit Price date, new price ROLT data is applicable. Prices are in United States dollars. Terms:

Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow:

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

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes and repair procedures given

in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

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

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ALERT ALERT
Group 1:

New Part Number QTY Name Notes

SR10280075-3 4 KIT (a)

SR10280075-5 8 KIT (a)

(a) Total quantity required per airplane.

Group 1:

New Part Number QTY Name Notes

SR10280075 -3 -5

10-74916-8 . 1 NUT GROMMET ASSY

2768771-1 1 . COMB

3D0005-3-12 1 1 SCREW (a)

5D0086-25 3 3 TERMINAL LUG 765 (a)

5D0086-26 2 2 TERMINAL LUG 766 (a)

7D0294-1 1 . FERRULE (a)

9D0196-1 2 . PIN (a)

9D0197-1 1 . BUSHING (a)

M8700-7/3 1 . GLAND NUT

MS35338-137 3 3 WASHER

MS35338-43 1 1 LOCKWASHER

MS35649-284 3 3 NUT

NAS1149CN832R 3 3 WASHER

NAS1149F0332P 1 1 WASHER

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

Group 2:

New Part Number QTY Name Notes

SR10280075-3 4 KIT (a)

SR10280075-5 8 KIT (a)

SR10280075-7 2 KIT (a)

(a) Total quantity required per airplane.

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Group 2:

New Part Number QTY Name Notes

SR10280075 -3 -5 -7

10-35916-16 . . 1 SLEEVE

10-60766-8 . . 1 GROMMET

10-74916-8 . 1 . NUT GROMMET ASSY

2768771-1 1 . . COMB

3D0005-3-12 1 1 1 SCREW (a)

5D0086-25 3 3 3 TERMINAL LUG 765 (a)

5D0086-26 2 2 2 TERMINAL LUG 766 (a)

7D0294-1 1 . . FERRULE (a)

9D0196-1 2 . . PIN (a)

9D0197-1 1 . . BUSHING (a)

M8700-7/3 1 . . GLAND NUT

MS35338-137 3 3 3 WASHER

MS35338-43 1 1 1 LOCKWASHER

MS35649-284 3 3 3 NUT

NAS1149CN832R 3 3 3 WASHER

NAS1149F0332P 1 1 1 WASHER

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

Group 3:

New Part Number QTY Name Notes

SR10280075-11 1 KIT (a)

SR10280075-3 4 KIT (a)

SR10280075-5 8 KIT (a)

SR10280075-7 2 KIT (a)

SR10280075-9 1 KIT (a)

(a) Total quantity required per airplane.

Group 3:

New Part Number QTY Name Notes

SR10280075 -3 -5 -7 -9 -11

10-35916-16 . . 1 . . SLEEVE

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ALERT ALERT
Group 3:

New Part Number QTY Name Notes

SR10280075 -3 -5 -7 -9 -11

10-60766-8 . . 1 . . GROMMET

10-74916-8 . 1 . . . NUT GROMMET ASSY

2768771-1 1 . . 1 1 COMB

3D0005-3-12 1 1 1 1 1 SCREW (a)

3D0005-3-9 . . . 1 1 SCREW (a)

5D0086-25 3 3 3 . . TERMINAL LUG 765 (a)

5D0086-26 2 2 2 - - TERMINAL LUG 766 (a)

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

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

9D0197-1 1 . . 1 1 BUSHING (a)

ANP0065-513 . . . 1 1 PLUG

ANP0065-515 . . . 1 1 PLUG

DC20F14-5P - - - - 1 RECEPTACLE

DC20F14-5PW - - - 1 - RECEPTACLE

LRM16M-32DJ5 - - - 5 5 PIN T/C 705

M8700-7/3 1 . . 1 1 GLAND NUT

MS20115-3 . . . 1 1 SHACKLE

MS21042L3 . . . 1 1 NUT

MS35338-137 3 3 3 . . WASHER

MS35338-43 1 1 1 1 1 LOCKWASHER

MS35649-284 3 3 3 . . NUT

NAS1149CN832R 3 3 3 . . WASHER

NAS1149DN416H . . . 4 4 WASHER

NAS1149F0332P 1 1 1 1 1 WASHER

NAS1191-04P-6 . . . 4 4 SCREW

NAS1252-10L . . . 2 2 WASHER

SR10280075-101 . . . . 1 WIRE KIT (b)

SR10280075-102 . . . 1 . WIRE KIT (b)

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

(b) Refer to Wire Kit Components Table.

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New Part Number Wire Kit SR10280075 Name Notes

-101 -102

5D0086-26 1 1 TERMINAL LUG T/C 766 (a)

DC2426-1C-16NM 21 FT 21 FT WIRE CODE 801 (a)

KPSE6F14-5S-EL 1 - ELECT DISCONNECT

KPSE6F14-5SW-EL - 1 ELECT DISCONNECT

LRC16M-32DJ5 5 5 SOCKET T/C 706

(a) Or approved Equivalent.

Group 4:

New Part Number QTY Name Notes

SR10280075-13 2 KIT (a)

SR10280075-3 6 KIT (a)

SR10280075-5 8 KIT (a)

SR10280075-7 2 KIT (a)

(a) Total quantity required per airplane.

Group 4:

New Part Number QTY Name Notes

SR10280075 -3 -5 -7 -13

10-35916-16 . . 1 . SLEEVE

10-60766-8 . . 1 . GROMMET

10-74916-8 . 1 . . NUT GROMMET ASSY

2768771-1 1 . . 1 COMB

3D0005-3-12 1 1 1 1 SCREW (a)

5D0086-25 3 3 3 3 TERMINAL LUG 765 (a)

5D0086-26 2 2 2 2 TERMINAL LUG 766 (a)

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

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

9D0197-1 1 . . 1 BUSHING (a)

AAN7113-517 . . . 2 GLAND

M8700-7/3 1 . . 1 GLAND NUT

MS35338-137 3 3 3 3 WASHER

MS35338-43 1 1 1 1 LOCKWASHER

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ALERT ALERT
Group 4:

New Part Number QTY Name Notes

SR10280075 -3 -5 -7 -13

MS35649-284 3 3 3 3 NUT

NAS1149CN832R 3 3 3 3 WASHER

NAS1149F0332P 1 1 1 1 WASHER

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

Group 5:

New Part Number QTY Name Notes

SR10280075-3 4 KIT (a)

SR10280075-5 6 KIT (a)

(a) Total quantity required per airplane.

Group 5:

New Part Number QTY Name Notes

SR10280075 -3 -5

10-74916-8 . 1 NUT GROMMET ASSY

2768771-1 1 . COMB

3D0005-3-12 1 1 SCREW (a)

5D0086-25 3 3 TERMINAL LUG 765 (a)

5D0086-26 2 2 TERMINAL LUG 766 (a)

7D0294-1 1 . FERRULE (a)

9D0196-1 2 . PIN (a)

9D0197-1 1 . BUSHING (a)

M8700-7/3 1 . GLAND NUT

MS35338-137 3 3 WASHER

MS35338-43 1 1 LOCKWASHER

MS35649-284 3 3 NUT

NAS1149CN832R 3 3 WASHER

NAS1149F0332P 1 1 WASHER

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

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ALERT ALERT
2. Parts and Materials Supplied by the Operator

NOTE: The items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator,

show the total quantity necessary for each airplane unless noted otherwise.

Group 1:

Part Number/Specification QTY Name Notes

60-84351 12 CONNECTOR ASSY (a)

60-847-X 12 PUMP ASSY (a) (b)

LL500D4-6 48 SCREW (a)

Or

ES500D4-6

M25988/1-019 12 PACKING (a)

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540

(b) Refer to Illustrated Parts Catalog (IPC) for applicable fuel boost/transfer pump configuration.

Group 2:

Part Number/Specification QTY Name Notes

60-84351 14 CONNECTOR ASSY (a)

60-847-X 14 PUMP ASSY (a) (b)

LL500D4-6 56 SCREW (a)

Or

ES500D4-6

M25988/1-019 14 PACKING (a)

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540

(b) Refer to IPC for applicable fuel boost/transfer pump configuration.

Group 3:

Part Number/Specification QTY Name Notes

60-84351 16 CONNECTOR ASSY (a)

60-847-X 16 PUMP ASSY (a) (b)

LL500D4-6 64 SCREW (a)

Or

ES500D4-6

M25988/1-019 16 PACKING (a)

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Group 3:

Part Number/Specification QTY Name Notes

DPM684 (NASM20995N20) 3 FT LOCKWIRE

Or

DPM5865 (NASM20995C20)

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540

(b) Refer to IPC for applicable fuel boost/transfer pump configuration.

Group 4:

Part Number/Specification QTY Name Notes

60-84351 18 CONNECTOR ASSY (a)

60-847-X 18 PUMP ASSY (a) (b)

LL500D4-6 72 SCREW (a)

Or

ES500D4-6

M25988/1-019 18 PACKING (a)

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540

(b) Refer to IPC for applicable fuel boost/transfer pump configuration.

Group 5:

Part Number/Specification QTY Name Notes

60-84351 10 CONNECTOR ASSY (a)

60-847-X 10 PUMP ASSY (a) (b)

LL500D4-6 40 SCREW (a)

Or

ES500D4-6

M25988/1-019 10 PACKING (a)

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540

(b) Refer to IPC for applicable fuel boost/transfer pump configuration.

3. Parts Modified and Reidentified

None.

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ALERT ALERT
4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

To get parts shown below, contact the Crane Spares Department at (818)-526-2500 or FAX to

(818)-526-2658.

New Part Number / Specifica- Name Notes

tion

60-84351 CONNECTOR ASSY (a) (b)

M25988/1-019 PACKING (a) (b)

LL500D4-6 SCREW (a) (b)

Or

ES500D4-6

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540 USA

(b) Use applicable quantities to change spare 60-843-3 and 60-845-3 fuel pump housing

assemblies. Replace spare 60-84355-1 with 60-84351 as needed.

E. Special Tooling - Price and Availability

The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this

Service Bulletin. Tool price and supply data are not given.

F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

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

Tool / Kit Number Name Supplier CAGE

Multimeter Model 10 Fluke Corporation 0HYG7

Or 1420 75TH Street Southwest

Equivalent Everett, Washington 98206

Megohmmeter Model 1864 Quatech, Incorporated 0PK96

Or 5 Clock Tower Place, Suite 210

Equivalent Maynard, Massachusetts 01754

* An Equivalent Ohmmeter must be able to apply voltage at 100+/-10 Volts DC and be current limited to

5 Milliamps.

A T67291 or T67291-1 test tool/alternate tool is required to accomplish this inspection. Refer to Crane

Hydro-Aire Service Information Letter 60-847-3-1.

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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.

WARNING: WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY

ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH

OR INJURY TO PERSONS CAN OCCUR.

CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE

TO THE AIRPLANE OR EQUIPMENT.

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Equivalent parts are listed in the AEPL, Drawing 7595071.

3. Use the approved fastener and process material substitutions, in accordance with

DC-10, MD-10 SRM 51.

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

installation standards in SRM Chapter 51, then a fastener of the same specification,

or an approved substitute, with a length which meets the installation standards in

SRM Chapter 51 may be used. Not applicable to Crane Hydro-Aire fuel boost/transfer

pump, fuel pump housing or attaching parts.

5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is

the maximum thickness which may be used under fastener head or nut to counteract

accumulation of tolerances.

EXCEPTION: When the available fastener length increments are greater than

1/16-inch, a 3/16-inch thick stack of the same type washers may be used.

6. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch.

– Torque limits to tighten nuts and bolts are in SRM, Chapter 51.

7. Refer to these Standard Wiring Practices Manual (SWPM) chapters for applicable

operations, as accepted procedures:

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ALERT ALERT
Chapter Title

IDENTIFICATION OF ELECTRICAL WIRE - COMMERCIALSWPM 20-00-03

SWPM 20-00-09 GENERAL MAINTENANCE PRACTICES - ELECTRICAL

SWPM 20-00-13 ELECTRICAL WIRE CODES

ELECTRICAL WIRE END TERMINATION CODES AND

TOOL CODES

SWPM 20-00-16

FABRICATING AND INSTALLING WIRE HARNESSES

- COMMERCIAL

SWPM 20-10-01

SWPM 20-10-04 COIL AND STOW - MAINTENANCE PRACTICES

SWPM 20-20-01 TERMINALS - MAINTENANCE PRACTICES

SWPM 20-20-02 TERMINAL BLOCKS - MAINTENANCE PRACTICES

GENERAL INSTALLATIONS HARDWARE - MAINTENANCE PRACTICESSWPM 20-20-03

ELECTRICAL CONNECTORS - MAINTENANCE

PRACTICES

SWPM 20-31-00

SWPM 20-50-01 ELECTRICAL BONDING - MAINTENANCE PRACTICES

8. Refer to these Wiring Diagram Manuals (WDM) for applicable operations, as accepted

procedures:

Location Wiring Diagram

Tank 1 28-22-01

Tank 2 28-22-02

Tank 3 28-22-03

Aux Tank * 28-22-04

KC-10 Tip 28-43-01

* Including Fwd Fus, Aft Fus, Upper, Lower, and Aft Aux Tanks (If Installed).

9. Obey all of the warnings and cautions given in the specified manual sections.

10. Review and understand all general notes of Service Rework Drawing SR10280075

sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.7.1, 3.8, 3.9, and 7 before start of

modification.

11. Lockwire Safetying - Maintenance Practices. Refer to DC-10, MD-10 AMM 20-20-06

as an accepted procedure.

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ALERT ALERT
12. 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.

13. Any protrusion of threads is acceptable provided that the threads do not rub or ride

against nearby wire assemblies or components.

14. Access panel numbers and locations may vary.

15. Identify and note location of wires prior to removal from terminal strip and/or ground

stud.

16. The inspection order of operation procedures outlined in Parts 3 and 4 of Paragraph

3.B., Work Instructions must be followed. The instructions identified in Paragraph

3.B., Work Instructions give the recommended sequence of steps for which pump

location to inspect. The sequence of steps to inspect the pump locations can be

changed.

B. WORK INSTRUCTIONS

PART 1 (ACCESS/PREPARATION)

WARNING: FUEL TANKS MUST BE FILLED TO SPECIFIED LEVEL OR DRAINED, PURGED, AND

SAFE FOR MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND

DAMAGE TO EQUIPMENT.

1. Make sure fuel tanks are filled to specified level or defuel, purge, and make fuel system safe for

maintenance. Refer to DC-10, MD-10 AMM 12-11-03 and DC-10, MD-10 AMM 28-00-00 as

accepted procedures.

ALL GROUPS:

Tank Minimum Fuel Level

Pounds Kilogram

1* 20000 9070

2 23000 10430

3* 20000 9070

* Tanks 1 and 3 aft fuel boost/transfer pumps and conduits are located in tank 2. Tank 2 must be filled to

specified level when accomplishing this inspection for tanks 1 and 3 aft fuel boost/transfer pumps.

Group 1-4:

Tank Minimum Fuel Level

Pounds Kilogram

Upper Aux 11000 4980

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
Group 2-4:

Tank Minimum Fuel Level

Pounds Kilogram

Lower Aux 4500 2040

Group 3:

Tank Minimum Fuel Level

Pounds Kilogram

Aft Aux (1500 Gallons) 4000 1810

Aft Aux (3200/3317 Gallons) 7000 3170

Group 4:

Tank Minimum Fuel Level

Pounds Kilogram

Fwd Fuselage 7600 3440

Aft Fuselage 10600 4800

2. Make fuel boost/transfer pumps electrical system safe as follows:

a. MD-10 only - Place fuel system controller (FSC) in manual mode and verify all fuel

boost/transfer pumps are off. Refer to MD-10 AMM 28-00-00 as an accepted procedure.

b. DC-10 - Make sure all fuel boost/transfer pumps are off. Refer to DC10 AMM 28-22-01.

3. Gain access to inspection areas. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted procedure.

4. Open/verify circuit breakers as follows:

a. Open fuel boost/transfer pump power circuit breakers. Refer to DC-10, MD-10 AMM 28-22-01

as an accepted procedure.

b. Make sure Remote Control Circuit Breaker (RCCB) indicators are green/open.

ALL GROUPS:

RCCB Circuit Breaker Location

B1-672 Tank 1 Trans EPC Bay 2

B1-673 Tank 1 Aft EPC Bay 3

B1-674 Tank 1 Fwd EPC Bay 1

B1-675 Tank 2 R Aft EPC Bay 2

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
ALL GROUPS:

RCCB Circuit Breaker Location

B1-676 Tank 2 Fwd EPC Bay 1

B1-677 Tank 3 Fwd EPC Bay 3

B1-678 Tank 3 Trans EPC Bay 1

B1-682 Tank 2 Trans EPC Bay 3

B1-679 Tank 3 Aft EPC Bay 2

B1-1572 Tank 2 L Aft Electrical Power Panel

Group 1-4:

RCCB Circuit Breaker Location

B1-1258 R Upper Aux Tank EPC Bay 1

B1-1260 L Upper Aux Tank EPC Bay 2

Group 2-4:

RCCB Circuit Breaker Location

B1-1259 R Lower Aux Tank EPC Bay 3

B1-1261 L Lower Aux Tank EPC Bay 2

Group 3:

RCCB Circuit Breaker Location

B1-1648 R Aft Aux Tank EPC Bay 3

B1-1649 L Aft Aux Tank EPC Bay 1

Group 4:

RCCB Circuit Breaker Location

B1-1873 Fwd Fus EPC Bay 1

B1-1874 Aft Fus EPC Bay 3

B1-1875 Tank 3 Tip EPC Bay 3

B1-1876 Tank 1 Tip EPC Bay 2

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
PART 2 (FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY - REPLACEMENT)

1. Replace existing 60-84355-1 fuel pump housing electrical connector assembly in accordance with

Appendix B.

2. Proceed to Part 5 (Restoration).

PART 3 (FUEL BOOST/TRANSFER PUMP AND PUMP HOUSING ELECTRICAL CONNECTOR

ASSEMBLY PART NUMBER 60-84355-1 INSPECTION)

1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through

fuel boost/transfer pump as follows:

a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect

connectors) and check disconnected wires terminal to terminal in accordance with Appendix

A, Table below and refer to DC-10, MD-10 AMM 28-22-01 as an accepted procedure:

NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.

NOTE: Terminal E should read open during multimeter check.

Wiring Resistance Check

Check Results Check Results

1-2 2-3

1-3 2-E

1-E 3-E

NOTE: If Aft Aux tank is installed, Use Table below:

Wiring Resistance Check ( Aft Aux Tank )

Check Results Check Results

A-B B-C

A-C C-E

A-E B-E

b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,

remove fuel boost/transfer pump, refer to DC-10, MD-10 AMM 28-22-01 as an accepted

procedure and check pin-to-pin as follows:

NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.

NOTE: Pin E should read open during multimeter check.

Fuel Boost/Transfer Pump Resistance Check

Check Results Check Results

A-B B-C

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
Fuel Boost/Transfer Pump Resistance Check

Check Results Check Results

A-C B-E

A-E C-E

2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is

not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with

pin E open, replace existing fuel pump housing electrical connector assembly in accordance with

Appendix B.

3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to DC-10, MD-10

AMM 28-22-01 as an accepted procedure.

4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly

insulation resistance check as follows:

a. Install T67291 or T6729-1 test tool/alternate tool.

b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation

resistance by applying test voltage terminal-to-terminal in accordance with Appendix A, and

Table below:

NOTE: Insulation resistance should be greater or equal to 10 gigaohm.

Insulation Resistance Check

Check Results Check Results

1-2 2-3

1-3 2-E

1-E 3-E

NOTE: If Aft Aux tank is installed, Use Table below

Insulation Resistance Check

Check Results Check Results

A-B B-C

A-C C-E

A-E B-E

c. Remove test pump/alternate tool.

5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
a. Replace fuel boost/transfer pump. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted

procedure.

b. Proceed to Part 5 (Restoration).

6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than

10 gigaohm.

a. Replace existing fuel pump housing electrical connector assembly in accordance with Appendix

B.

b. Proceed to Part 5 (Restoration).

7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are

as follows:

a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and

terminal E is open.

b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is

open.

c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than

or equal to 10 gigaohm.

PART 4 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR

ASSEMBLY PART NUMBER 60-84351 INSPECTION)

1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through

fuel boost/transfer pump as follows:

a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect

connectors) and check disconnected wires electrical terminal to terminal in accordance with

DC-10, MD-10 AMM 28-22-01, Appendix C, and Table below:

NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.

NOTE: Terminal E should read open during multimeter check.

Wiring Resistance Check

Check Results Check Results

1-2 2-D

1-3 2-E

1-D 3-D

1-E 3-E

2-3 D-E

NOTE: If Aft Aux tank is installed, Use Table below:

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
Wiring Resistance Check

Check Results Check Results

A-B B-D

A-C B-E

A-D C-D

A-E C-E

B-C D-E

b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,

remove fuel boost/transfer pump, refer to DC-10, MD-10 AMM 28-22-01 as an accepted

procedure and check pin-to-pin as follows:

NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.

NOTE: Pin E should read open during multimeter check.

Fuel Boost/Transfer Pump Resistance Check

Check Results Check Results

A-B B-D

A-C B-E

A-D C-D

A-E C-E

B-C D-E

2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is

not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with

pin E open, replace the affected fuel pump housing electrical connector assembly. Refer to DC-10

AMM 28-22-01 Approved Repairs, Wiring Charts entitled "without Service Bulletin DC10-28A229

incorporated" or (MD-10 only) MD-10 AMM 28-22-01 Approved Repairs, "Pre Service Bulletin

DC10-28A229" as accepted procedure.

NOTE: If a spring model protective cap is not installed, fuel tank entry is required. Refer to DC-10,

MD-10 AMM 28-00-00 as an accepted procedure.

3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to DC-10, MD-10

AMM 28-22-01 as an accepted procedure.

4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly

insulation resistance check as follows:

a. Install T67291 or T6729-1 test tool/alternate tool.

b. Set ohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation resistance

by applying test voltage terminal-to-terminal, in accordance with Appendix C, and Table below:

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
NOTE: Insulation resistance should be greater or equal to 10 megaohm.

Insulation Resistance Check

Check Results Check Results

1-2 2-D

1-3 2-E

1-D 3-D

1-E 3-E

2-3 D-E

NOTE: If Aft Aux tank is installed, Use Table below:

Insulation Resistance Check

Check Results Check Results

A-B B-D

A-C B-E

A-D C-D

A-E C-E

B-C D-E

c. Remove test pump/alternate tool.

5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or terminal E is not

open.

a. Replace fuel boost/transfer pump. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted

procedure.

b. Proceed to Part 5 (Restoration).

6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than

10 megaohm.

a. Replace the affected fuel pump housing electrical connector assembly. Refer to DC-10 AMM

28-22-01 Approved Repairs, Wiring Charts entitled "without Service Bulletin DC10-28A229

incorporated" or (MD-10 only) MD-10 AMM 28-22-01 Approved Repairs, "Pre Service Bulletin

DC10-28A229" as accepted procedure.

NOTE: If a spring model protective cap is not installed, fuel tank entry is required. Refer to

DC-10, MD-10 AMM 28-00-00 as an accepted procedure.

b. Proceed to Part 5 (Restoration).

7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are

as follows:

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and

terminal E is open.

b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is

open.

c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than

or equal to 10 megaohm.

PART 5 (RESTORATION)

1. If not already accomplished, connect fuel pump housing electrical connector assemblies to terminal

strip and ground studs. Refer to DC-10, MD-10 AMM 28-22-01 and Appendix A (part number

60-84355-1), or Appendix C (part number 60-84351) as an accepted procedure.

2. Install fuel boost/transfer pumps if not previously installed. Refer to DC-10, MD-10 AMM 28-22-01

as an accepted procedure.

3. Do operational test of fuel boost/transfer pumps and using a digital multimeter check that voltage

between applicable terminal strip post and ground is 104 to 122VAC. Refer to DC-10, MD-10 AMM

28-22-00, Appendix A (part number 60-84355-1), or Appendix C (part number 60-84351) as

accepted procedures.

4. Close access. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted procedure.

5. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-368

A

1/Forward R5-1102 B 2 -

C 3 -

E* 5022A

1 -

S3-370

A

1/Transfer R5-1100 B 2 -

C 3 -

E* 4726A

1 -

S3-369

A

1/Aft R5-1101 B 2 -

C 3 -

E* 4727A

1 -

S3-371

A

2/Forward R5-1105 B 2 -

C 3 -

E* 5009A

1 -

S3-372

A

2/Left Aft R5-1104 B 2 -

C 3 -

E* 4728A

- 1

S3-374

A

2/Transfer R5-1099 - 2 B

- 3 C

E* 6078A

1 -

S3-373

A

2/Right Aft R5-1103 B 2 -

C 3 -

E* 4821A

1 -

S3-377

A

3/Forward R5-1106 B 2 -

C 3 -

E* 6022A

1 -

S3-376

A

3/Transfer R5-1107 B 2 -

C 3 -

E* 4823A

1 -

S3-375

A

3/Right Aft R5-1108 B 2 -

C 3 -

E* 4822A

* E should read open during multimeter check.

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
GROUP 1-4:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-803

A

R5-1934 Center Aux/Left

Upper

B 2 -

C 3 -

E* 4729A

1 -

S3-802

A

R5-1933 Center Aux/Right

Upper

B 2 -

C 3 -

E* 4824A

* E should read open during multimeter check.

GROUP 2-4:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-805

A

R5-1936 Center Aux/Left

Lower

B 2 -

C 3 -

E* 4895A

1 -

S3-804

A

R5-1935 Center Aux/Right

Lower

B 2 -

C 3 -

E* 4894A

* E should read open during multimeter check.

GROUP 3:

Ground Stud Connector (Pump) ConnectorTank/Pump Number Socket Number Socket

Aft Aux/R R5-1994 A R5-4816 3 -

B 2 -

C 1 -

E* 4 4866A

Aft Aux/L R5-1995 A R5-4815 3 -

B 2 -

C 1 -

E* 4 4865A

* E should read open during multimeter check.

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
GROUP 3:

Tank/Pump Relay Terminal

Aft Aux R R2-89 A1

B1

C1

Aft Aux L R2-90 A1

B1

C1

GROUP 4:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-1072

A

1/Tip R5-4936 B 2 -

C 3 -

E* 5088A

1 -

S3-1071

A

3/Tip R5-4937 B 2 -

C 3 -

E* 6088A

8 -

S3-1109

A

Fwd Fuselage R5-2666 B 9 -

C 10 -

E* 4122A

8 -

S3-1110

A

Aft Fuselage R5-2667 B 9 -

C 10 -

E* 4848A

* E should read open during multimeter check.

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
1. Replace the affected fuel pump housing electrical connector assembly in accordance with Table below,

DC-10 AMM 28-22-01 Approved Repairs, Wiring Charts entitled "without Service Bulletin DC10-28A229

incorporated" or (MD-10 only) MD-10 AMM 28-22-01 Approved Repairs, "Pre Service Bulletin DC10-28A229"

as accepted procedure.

NOTE: If a spring model protective cap is not installed, fuel tank entry is required. Refer to DC-10, MD-10

AMM 28-00-00 as an accepted procedure.

ALL GROUPS:

Drawing SR10280075 Connector

Identification

Fuel Pump

Identification Tank Location

Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,

4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,

5.4, 6, 6.2, 7, 9.0, 9.7, 10, and 19.

1 Transfer M1-7 R5-1100

Left Aft M1-6 R5-1101

Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,

4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,

5.4, 6, 6.1, 6.2, 7, 9.0, 9.7, 10, and 21.

Forward M1-5 R5-1102

Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,

4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,

5.4, 6, 6.1, 6.2, 7, 9.1, 9.8, 10, and 16.

2 Right Aft M1-11 R5-1103

Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,

4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3, 5.4, 6,

6.2, 7, 9.1, 9.7, 10, and 17.

Transfer M1-9 R5-1099

Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,

4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,

5.4, 6, 6.1, 6.2, 7, 9.1, 9.7, 10, and 19.

Left Aft M1-10 R5-1104

Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,

4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,

5.4, 6, 6.1, 6.2, 7, 9.1, 9.7, 10, and 20.

Forward M1-8 R5-1105

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
ALL GROUPS:

Drawing SR10280075 Connector

Identification

Fuel Pump

Identification Tank Location

Sheets 3, 3.1, 3.3, 3.7, 3.8, 3.9, 4, 4.1,

4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3, 5.4, 6,

6.1, 6.2, 7, 9.2, 9.8, 10, and 18.

3 Forward M1-12 R5-1106

Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,

4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,

5.4, 6, 6.1, 6.2, 7, 9.2, 9.8, 9.9, 10,

and 16.

Transfer M1-14 R5-1107

Right Aft M1-13 R5-1108

GROUP 1-4:

Drawing SR10280075 Connector

Identification

Fuel Pump

Identification Tank Location

Sheets 3, 3.1, 3.5, 3.7, 3.8, 3.9, 4, 4.1,

4.2, 4.3, 5, 5.1, 5.2, 5.3, 6, 6.1, 6.2, 7,

9.3, 9.8, 10, and 14.

Auxiliary Upper Left M1-92 R5-1934

Auxiliary Upper Right M1-91 R5-1933

GROUP 2-4:

Drawing SR10280075 Connector

Identification

Fuel Pump

Identification Tank Location

Sheets 3, 3.1, 3.3, 3.7, 3.7.1, 3.8, 3.9,

4.1, 4.2, 4.3, 5.1, 5.2, 5.3, 6, 6.1, 6.2,

7, 9.3, 9.9, 10, 15, and 15.1.

Auxiliary Lower Left M1-94 R5-1936

Auxiliary Lower Right M1-93 R5-1935

GROUP 3:

Drawing SR10280075 Connector

Identification

Fuel Pump

Identification Tank Location

Sheets 3, 3.1, 3.2, 3.3, 3.6, 3.7, 3.8,

3.9, 4.2, 5.2, 6, 6.1, 7, 8.0, 9.4, 9.9, 10,

11, 24, 25, and 26.

Left M1-169 R5-1995

Aft Tank

R5-4815

Sheets 3, 3.1, 3.2, 3.3, 3.6, 3.7, 3.8,

3.9, 4.2, 5.2, 6, 6.1, 7, 8.1, 9.4, 9.9, 10,

11, 24, 25, and 26.

Right M1-168 R5-1994

R5-4816

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
GROUP 4:

Drawing SR10280075 Connector

Identification

Fuel Pump

Identification Tank Location

Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,

4.3, 5.3, 6, 6.1, 7, 9.5, 9.9, 10, and 22.

Transfer M1-258 R5-2666 Fwd Fuse Auxiliary

Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,

4.3, 5.3, 6, 6.1, 7, 9.5, 9.9, 10, and 23.

Transfer M1-259 R5-2667 Aft Fuse Auxiliary

Sheets 3, 3.1, 3.3, 3.7, 3.8, 3.9, 4.3,

5.3, 6, 6.1, 7, 9.6, 9.10, 10, and 13.

Left M1-249 R5-4936 Wing Tip

Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,

4.3, 5.3, 6, 6.1, 7, 9.6, 9.10, 10, and

12.

Right M1-248 R5-4937

Wing Tip

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN DC10-28A261

ALERT ALERT
ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-368

A

1/Forward R5-1102

B 2 -

C 3 -

D 5022A

E* 5022A

1 -

S3-370

A

1/Transfer R5-1100

B 2 -

C 3 -

D 4726A

E* 4726A

1 -

S3-369

A

1/Aft R5-1101

B 2 -

C 3 -

D 4727A

E* 4727A

1 -

S3-371

A

2/Forward R5-1105

B 2 -

C 3 -

D 5009A

E* 5009A

1 -

S3-372

A

2/Left Aft R5-1104

B 2 -

C 3 -

D 4728A

E* 4728A

-

1

S3-374

A

2/Transfer R5-1099

-

2

B

-

3

C

D 6078A

E* 6078A

1 -

S3-373

A

2/Right Aft R5-1103

B 2 -

C 3 -

D 4821A

E* 4821A

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

(SHEET 1 OF 4)

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ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-377

A

3/Forward R5-1106

B 2 -

C 3 -

D 6022A

E* 6022A

1 -

S3-376

A

3/Transfer R5-1107

B 2 -

C 3 -

D 4823A

E* 4823A

1 -

S3-375

A

3/Right Aft R5-1108

B 2 -

C 3 -

D 4822A

E* 4822A

* E should read open during multimeter check.

GROUP 1-4:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-803

A

R5-1934 Center Aux/Left

Upper

B 2 -

C 3 -

D 4729A

E* 4729A

1 -

S3-802

A

R5-1933 Center Aux/Right

Upper

B 2 -

C 3 -

D 4824A

E* 4824A

* E should read open during multimeter check.

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

(SHEET 2 OF 4)

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ALERT ALERT
GROUP 2-4:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-805

A

R5-1936 Center Aux/Left

Lower

B 2 -

C 3 -

D 4895A

E* 4895A

1 -

S3-804

A

R5-1935 Center Aux/Right

Lower

B 2 -

C 3 -

D 4894A

E* 4894A

* E should read open during multimeter check.

GROUP 3:

Ground Stud Connector (Pump) ConnectorTank/Pump Number Socket Number Socket

Aft Aux/R R5-1994 A R5-4816 C -

B B -

C A -

D D 4866A

E* E* 4866A

Aft Aux/L R5-1995 A R5-4815 C -

B B -

C A -

D D 4865A

E* E* 4865A

* E should read open during multimeter check.

GROUP 3:

Tank/Pump Relay Terminal

Aft Aux R R2-89 A1

B1

C1

Aft Aux L R2-90 A1

B1

C1

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

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ALERT ALERT
GROUP 4:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-1072

A

1/Tip R5-4936

B 2 -

C 3 -

D 5088A

E* 5088A

1 -

S3-1071

A

3/Tip R5-4937

B 2 -

C 3 -

D 6088A

E* 6088A

8 -

S3-1109

A

Fwd Fuselage R5-2666

B 9 -

C 10 -

D 4122A

E* 4122A

8 -

S3-1110

A

Aft Fuselage R5-2667

B 9 -

C 10 -

D 4848A

E* 4848A

* E should read open during multimeter check.

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

(SHEET 4 OF 4)

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ALERT ALERT
APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84355-1 INSPECTION LOGIC DIAGRAM

(SHEET 1 OF 1)

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ALERT ALERT
APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84351 INSPECTION LOGIC DIAGRAM

(SHEET 1 OF 1)

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Original Issue: December 01, 2009

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ALERT ALERT