August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 83

Commercial McDonnell Douglas

Airplane

Group DC-10

Service Bulletin

Number: DC10-28-249

Date: August 07, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, Tank All - Install Electrical Bonding Jumper

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2007 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Unpublished Work - All Rights Reserved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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or 

its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document 

or otherwise.
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 Table of Contents

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BOEING SERVICE BULLETIN DC10-28-249

Table of Contents

Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

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: . . . . . . . . . . . . . . . . . . . . . . . . . 20

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

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

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

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

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

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

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 26

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 27

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

FIGURE 1: JUMPER INSTALLATION - TANK 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 2: JUMPER INSTALLATION - TANK 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 3: JUMPER INSTALLATION - TANK 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK . . . . . . . . . . . . . . . . . . 45

FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK . . . . . . . . . . . . . . . . . . 52

FIGURE 6: JUMPER INSTALLATION - UPPER AUXILIARY TANK . . . . . . . . . . . . . . . . . . 59

FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK . . . . . . . . . . . . . . . . . . . . 63

FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK . . . . . . . . . . . . . . . . . . . . . . . 70

FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK . . . . . . . . . . . . . . . . . . . . . . . 77
 Table of Contents

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August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 83

Commercial McDonnell Douglas

Airplane

Group DC-10

Service Bulletin

Number: DC10-28-249 Revision Transmittal Sheet

Date: August 07, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, Tank All - Install Electrical Bonding Jumper

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary as shown in the original issue of this service bulletin.

REASON FOR REVISION

This revision is sent to incorporate engineering released subsequent to the original issue of this service bulletin, 

which relocates ground brackets and jumpers due to interference with airplane components/structure. Noted 

changes are based on findings discovered as a result of service bulletin survey done at an airline facility. 

This revision removes the no-work condition given in Information Notice DC10-28-249 IN 01.

These sections were changed:

1. Paragraph 1.A., Effectivity, added service bulletin incorporation statement.

2. In Paragraph 1.F., Approval, added Revision 1.

3. In Paragraph 1.J.1.b., Existing Data, added MD-10-10 Structural Repair Manual (SRM) 51-33-01. 

4. In Paragraph 1.J.1.c., Existing Data, added MD-10 Aircraft Maintenance Manual.

5. In Paragraph 1.J.3., Installation Drawings Used in the Preparation of this Service Bulletin, changed 

Drawings SR10280058 and SR10280062 revision level.

6. In Paragraph 2.A., Material - Price and Availability, changed Unit Price and expiration date.

7. In Paragraph 2.C.1., Kits/Part, changed in all Group Tables, hardware parts and quantities (QTY).

8. In Paragraph 3.A., General Information, changed Note 1.

9. In Paragraph 3.A., General Information, changed Note 4 statement and added MD-10. 

10. In Paragraph 3.A., General Information, changed Note 10 to read "in accordance with", was "as given in".

11. In Paragraph 3.A., General Information, added Note 11. 
 

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12. In Paragraph 3.B., Work Instructions, added in Tables to Group 1, 2 and 3, MD-10 AMM 06-36-00, 

06-35-00 and 06-27-00.

13. In Paragraph 3.B., Work Instructions, Group 5, changed panel numbers to 520MB, 610GB, 620MB, and 

130AB.

14. In Figure 1, changed illustration and step table. 

15. In Figure 2, changed illustration and step table.

16. In Figure 3, changed illustration and step table.

17. In Figure 4, changed illustration and step table.

18. In Figure 5, changed illustration and step table.

19. In Figure 6, changed illustration and step table.

20. In Figure 7, changed illustration and step table.

21. In Figure 8, changed illustration and step table.

22. In Figure 9, changed illustration and step table.

Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location 

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: August 07, 2007

Revision 1: November 06, 2008
August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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Commercial McDonnell Douglas

Airplane

Group DC-10

Service Bulletin

Number: DC10-28-249 Summary

Date: August 07, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, Tank All - Install Electrical Bonding Jumper

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Boeing investigation and analysis revealed that all the fill valve controller installations had inadequate electrical 

bonding. This could allow point-of-contact arcing or filament heating damage in the fuel tanks. Installing 

electrical bonding jumpers from the fill valve controllers to airplane structure will provide a grounding path in the 

event of a fault current occurrence in the fill valve controller. If not corrected, a high current occurrence could 

result in a potential source of ignition and consequent fire or explosion. 

This service bulletin is the result of the safety assessments conducted by Boeing under Special Federal Aviation 

Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation Requirements".

ACTION

This service bulletin provides instructions to install electrical bonding jumpers from the fill valve controllers to 

the airplane structure.

EFFECTIVITY

DC-10-10, -10F, -15, -30, -30F, -30F (KC-10A), -30F (KDC-10), -40, -40F, MD-10-10F, and MD-10-30F 

Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. 

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.

Boeing recommends operators do this service bulletin within 5 years after the date on this service bulletin.

INDUSTRY SUPPORT INFORMATION

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

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MANPOWER

Refer to Paragraph 1.G., for manpower information.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

INSTALL ELECTRICAL

BONDING JUMPER

AND

1360712
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Commercial McDonnell Douglas

Airplane

Group DC-10

Service Bulletin

Number: DC10-28-249

Date: August 07, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, Tank All - Install Electrical Bonding Jumper

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

NOTE: The intent of this change was done on fuselage number 0361.

NOTE: DC-10-10 with upper auxiliary fuel tank that are modified to MD-10-10F configuration by

Boeing Engineering will become Group 1 airplanes. 

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

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND FUSELAGE NUMBER

10 TANKER AIRCARRIER (TKR)

1 162

GROUP CONFIGURATION DESCRIPTION

1 - Applicable to DC-10 and MD-10 airplanes with 

wing fuel tanks 1, 2, and 3 configuration.

2 - Applicable to DC-10 and MD-10 airplanes with 

wing fuel tanks 1, 2, 3, and upper auxiliary fuel 

tank configuration.

3 - Applicable to DC-10, MD-10 and KDC-10 

airplanes with wing fuel tanks 1, 2, 3, upper and 

lower auxiliary fuel tanks configuration.

4 - Applicable to DC-10 airplanes with wing fuel 

tanks 1, 2, 3, upper, lower, and aft auxiliary fuel 

tanks configuration.

5 - Applicable to KC-10A airplanes.
 

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AEROFLOT - CARGO (CGB)

3 262 306 349

AEROWINGS, INC. (YNF)

1 358

AFRICA UNITED HOLDING CO. (UHD)

2 346

AIR-LIB (ALB)

3 134–135 174 204 213

227 315 325

AIRCRAFT INVESTMENT (IVA)

2 251

ALG TRANSPORTATION, INC. (ALW)

3 171

ARCA AIRLINES (RCC)

1 83

ARROW AIR (ARW)

1 34

3 212 224 267 289

314 327

AVIENT LTD. (VNT)

3 157 254 266 305

BANC OF AMERICA LEASING (SBC)

3 261 303

BIMAN BANGLADESH AIRLINES (BNG)

3 263 275 300 445

4 341

CARGOITALIA (CTG)

3 335

CAS WORLD CARGO (CWC)

3 115

CENTURION AIR CARGO (CHA)

3 268 291 316

CHARLOTTE AIRCRAFT (CTE)

3 114 131

CIELOS DEL PERU (CDP)

3 127 137 147 152

248
 

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CLIPPER LEASING (CLG)

2 372

CONTINENTAL AIRLINES (CAL)

3 100 189–190 201 99

DAS AIR CARGO (DAC)

3 281

FEDEX (FED)

1 119 138–140 142 144–145

148 15 154–155 169

17 173 177 194

198 205 207–210 247

249 25 250 26–27

270–271 273 294 297–298

307 309 319 32

321 323 33 344

347 35 351 353

379 39 42 59

6 61–62 70 76

78 8 86 89

2 112 153 203 269

272 55 72

3 103 110 219 257

277 282 317 326

330 409 412 416

419 422 433 440

442–444 96

FINOVA (GRB)

3 229

GA TELESIS, LLC (GTG)

3 133 178 236 240

242

GARUDA INDONESIA (GIA)

3 246

GECAS (GEF)

3 156 195 232 334

GEMINI AIR CARGO (GMN)

3 117 122–123 129 158

166 196 245 256

337

GENERIC CUSTOMER/SUPPLIER (XXX)

3 244 286 60 71

GHANA AIRWAYS (GHN)

3 106 165 234
 

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GLOBAL AVIATION LEASING LTD (GBL)

2 252 285 318

GLOBAL SUN (GSN)

3 146 150 225 290

324

JAL INTERNATIONAL (JAL)

3 230 343

KELOWNA FLIGHTCRAFT AIRCHARTER (KEL)

3 214

LAC (CQC)

3 90

MASTER TOP AIRLINES (MTN)

3 215

MIAMI LEASING (MLS)

1 40

MTU AERO ENGINES GMBH (YDX)

3 223 226 239

OMEGA AIR, INC. (OMH)

3 274 340

OMNI AIR INTERNATIONAL (OAE)

3 160 170 299 301

342 446

4 345 434–438

PAI AVIATION, INC. (PSS)

1 41

PROJECT ORBIS INTERNATIONAL (ORS)

1 2

RAYTHEON TECHNICAL SERVICES (HAC)

2 65

REPUBLIC FINANCIAL CORPORATION (RFC)

3 132

ROYAL NETHERLANDS AIR FORCE (RNE)

3 235 253 255 264

TEN FORTY CORPORATION (TFC)

3 206 216 220 265

304 308 310 313

366–367 381
 

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TRANSPORTES AEREOS BOLIVIANOS (TPB)

1 43

UNITED AIR LINES (UAL)

3 302 312

UNIVERSAL ASSET MANAGEMENT (UAM)

1 296

US AIR FORCE (USF)

5 311 333 359–361 363

373 375–378 380 383–408

410–411 413–415 417–418 420–421

423–432 439 441

VARIG LOGISTICA S.A. (VRG)

3 179 329 332

WORLD AIRWAYS, INC. (WLD)

3 183–184 187–188 192 199

211 221 336 338

355–356

4 292

IDENTIFICATION BY FUSELAGE NUMBER

Fuselage Group

2 1

6 1

8 1

15 1

17 1

25–27 1

32–35 1

39–43 1

55 2

59 1

60 3

61–62 1

63 3

65 2

70 1

71 3

72 2

76 1

78 1
 

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83 1

86 1

89 1

90 3

96 3

99–100 3

103 3

106 3

110 3

112 2

114–115 3

117 3

119 1

122–123 3

127 3

129 3

131–135 3

137 3

138–140 1

142 1

144–145 1

146–147 3

148 1

150 3

152 3

153 2

154–155 1

156–158 3

160 3

162 1

165–166 3

169 1

170–171 3

173 1

174 3

177 1

178–179 3

183–184 3

187–190 3

Fuselage Group
 

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192 3

194 1

195–196 3

198 1

199 3

201 3

203 2

204 3

205 1

206 3

207–210 1

211–216 3

219–221 3

223–227 3

229–232 3

234–236 3

239–242 3

244–246 3

247 1

248 3

249–250 1

251–252 2

253–257 3

261–268 3

269 2

270–271 1

272 2

273 1

274–275 3

277 3

281–282 3

285 2

286 3

289–291 3

292 4

294 1

296–298 1

299–306 3

307 1

Fuselage Group
 

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308 3

309 1

310 3

311 5

312–317 3

318 2

319 1

321 1

323 1

324–327 3

329–330 3

332 3

333 5

334–340 3

341 4

342–343 3

344 1

345 4

346 2

347 1

349 3

351 1

352 4

353 1

355–356 3

358 1

359–361 5

363 5

364 4

366–367 3

370 4

372 2

373 5

375–378 5

379 1

380 5

381 3

383–408 5

409 3

Fuselage Group
 

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2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Boeing investigation and analysis revealed that all the fill valve controller installations had inadequate 

electrical bonding. This could allow point-of-contact arcing or filament heating damage in the fuel 

tanks. Installing electrical bonding jumpers from the fill valve controllers to airplane structure will 

provide a grounding path in the event of a fault current occurrence in the fill valve controller. If not 

corrected, a high current occurrence could result in a potential source of ignition and consequent fire 

or explosion. 

This service bulletin is the result of the safety assessments conducted by Boeing under Special 

Federal Aviation Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation 

Requirements".

Revision 1 is sent to incorporate engineering released subsequent to the original issue of this service 

bulletin, which relocates ground brackets and jumpers due to interference with airplane components/

structure. Noted changes are based on findings discovered as a result of service bulletin survey done 

at an airline facility.

Revision 1 removes the no-work condition given in Information Notice DC10-28-249 IN 01.

410–411 5

412 3

413–415 5

416 3

417–418 5

419 3

420–421 5

422 3

423–432 5

433 3

434–438 4

439 5

440 3

441 5

442–446 3

Fuselage Group
 

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BOEING SERVICE BULLETIN DC10-28-249

D. Description

This service bulletin provides instructions to install electrical bonding jumpers from the fill valve 

controllers to the airplane structure.

Revision 1 - No more work is necessary as shown in the original issue of this service bulletin.

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.

Boeing recommends operators do this service bulletin within 5 years after the date on this service 

bulletin.

F. Approval

The resultant modification described in Paragraph 1.D has been shown to comply with the applicable 

Federal Aviation Regulations and Revision 1 is approved by the Manager, Los Angeles Aircraft 

Certification Office, FAA Northwest Mountain Region. 

G. Manpower

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

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

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

time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to inspect the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 1: 

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 3.0 3.0

Figure 1 1 3.0 3.0

Figure 2 1 2.0 2.0

Figure 3 1 3.0 3.0

Close Access 1 3.0 3.0

TOTAL FOR EACH AIRPLANE 14.0 14.0
 

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Group 2: 

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 3.0 3.0

Figure 1 1 3.0 3.0

Figure 2 1 2.0 2.0

Figure 3 1 3.0 3.0

Figure 6 1 3.0 3.0

Close Access 1 3.0 3.0

TOTAL FOR EACH AIRPLANE 17.0 17.0

Group 3: 

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 3.0 3.0

Figure 1 1 3.0 3.0

Figure 2 1 2.0 2.0

Figure 3 1 3.0 3.0

Figure 4 1 4.0 4.0

Figure 5 1 4.0 4.0

Test 1 1.5 1.5

Close Access 1 3.0 3.0

TOTAL FOR EACH AIRPLANE 23.5 23.5

Group 4: 

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 3.0 3.0

Figure 1 1 3.0 3.0

Figure 2 1 2.0 2.0

Figure 3 1 3.0 3.0

Figure 4 1 4.0 4.0

Figure 5 1 4.0 4.0

Figure 7 1 4.0 4.0

Test 1 1.5 1.5

Close Access 1 3.0 3.0

TOTAL FOR EACH AIRPLANE 27.5 27.5
 

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H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. DC-10 Aircraft Maintenance Manual (AMM) 06-27-00, 06-31-00, 06-35-00, 06-36-00, 

06-38-01, 28-21-02 and AMM 28-22-00.

b. DC-10, MD-10-10 Structural Repair Manual (SRM) 51-31-01, 51-33-01, and 51-41-01.

c. MD-10 Aircraft Maintenance Manual (AMM) 06-27-00, 06-35-00, 06-36-00, 28-21-02, and 

28-22-00.

d. Standard Wiring Practices Manual (SWPM) 20-20-01 and 20-50-01.

2. Data supplied with this Service Bulletin:

None.

Group 5: 

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 3.0 3.0

Figure 1 1 3.0 3.0

Figure 2 1 2.0 2.0

Figure 3 1 3.0 3.0

Figure 4 1 4.0 4.0

Figure 5 1 4.0 4.0

Figure 8 1 4.0 4.0

Figure 9 1 4.0 4.0

Test 1 1.5 1.5

Close Access 1 3.0 3.0

TOTAL FOR EACH AIRPLANE 31.5 31.5
 

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

These drawings were used to prepare this service bulletin. These drawings are not necessary to 

make the specified changes, and are not supplied with this service bulletin. These drawings may 

not be applicable to all airplane configurations or operators.

K. Publications Affected

L. Interchangeability and Intermixability of Parts

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

Document Number Title Change

SR10280058 Bonding Improvement - Fill Valve 

Controller, Fuel System, DC-10 

E

SR10280062 Bonding Improvement - Fill Valve 

Controller, Fuel System, KC-10A 

D

Publication Chapter-Section

Illustrated Parts Catalog 28-21
 

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BLANK PAGE
 

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2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown 

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

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

the date Boeing gets the purchase order.

The Kits are subject to the terms and conditions of the Boeing standard purchase order 

acknowledgment. After the Unit Price date, new price and 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. 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 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. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Kit Number Name QTY

ROLT 

(Weeks)

Unit Price thru

December 31, 2008

SB10280249-3 Service Kit 1 17 $1,459.00

SB10280249-5 Service Kit 1 17 2,122.00

SB10280249-7 Service Kit 1 17 2,216.00

SB10280249-9 Service Kit 1 17 3,011.00

SB10280249-11 Service Kit 1 17 3,805.00
 

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Figure Kit

Top Kit 1 2 3 4 5 6 7 8 9

SB10280249-11 1 1 1 1 1 - - 1 1

SB10280249-3 1 1 1 - - - - - -

SB10280249-5 1 1 1 - - 1 - - -

SB10280249-7 1 1 1 1 1 ----

SB10280249-9 1 1 1 1 1 - 1 - -

Group 1: 

Kit SB10280249-3 - Group 1: 

New Part Number

Figure

Name

123

QTY

ABN7210-539 1 - 1 BRACKET ASSY

HL326-6-2 2 1 2 PIN

MS21042L3 2 1 2 NUT

MS35338-43 1 - 1 LOCKWASHER

NAS1149F0332P 3 2 3 WASHER

NAS1801-3-9 1 - 1 SCREW

RC11307-10SS4 - 1 - CABLE, JUMPER

RC11307-10SS6 1 - 1 CABLE, JUMPER

Group 2: 

Kit SB10280249-5 - Group 2: 

New Part Number

Figure

Name

1236

QTY

ABN7210-539 1 - 1 1 BRACKET ASSY

HL326-6-2 2 1 2 2 PIN

MS21042L3 2 1 2 2 NUT

MS35338-43 1 - 1 1 LOCKWASHER

NAS1149F0332P 3 2 3 3 WASHER

NAS1801-3-9 1 - 1 1 SCREW

RC11307-10SS4 - 1 - 1 CABLE, JUMPER

RC11307-10SS6 1 - 1 - CABLE, JUMPER
 

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Group 3: 

Kit SB10280249-7 - Group 3: 

New Part Number

Figure

Name

12345

QTY

ABN7210-539 1 - 1 - - BRACKET ASSY

ABN7294-793 - - - - 1 BRACKET

HL326-6-2 2 1 2 2 2 PIN

MS21042L3 2 1 2 4 3 NUT

MS35338-42 - - - - 1 LOCKWASHER

MS35338-43 1 - 1 - - LOCKWASHER

NAS1149F0332P 3 2 3 6 4 WASHER

NAS1149FN832P - - - - 1 WASHER

NAS1801-08-10 - - - - 1 SCREW

NAS1801-3-9 1 - 1 2 1 SCREW

RC11307-10SS4 - 1 - 1 1 CABLE, JUMPER

RC11307-10SS6 1 - 1 - - CABLE, JUMPER

RC11309-10SS4 - - - - 1 CABLE, JUMPER

S2891103-10SS6 - - - 1 - JUMPER

Group 4: 

Kit SB10280249-9 - Group 4: 

New Part 

Number

Figure

Name

123457

QTY

ABN7210-539 1 - 1 - - 1 BRACKET ASSY

ABN7294-793 - - - - 1 - BRACKET

HL326-6-2 2 1 2 2 2 2 PIN

MS21042L3 2 1 2 4 3 3 NUT

MS35338-42 - - - - 1 - LOCKWASHER

MS35338-43 1 - 1 - - 1 LOCKWASHER

NAS1149F0332P 3 2 3 6 4 5 WASHER

NAS1149FN832P - - - - 1 - WASHER

NAS1801-08-10 - - - - 1 - SCREW

NAS1801-3-9 1 - 1 2 1 2 SCREW

RC11307-10SS4 - 1 - 1 1 1 CABLE, JUMPER

RC11307-10SS6 1 - 1 - - - CABLE, JUMPER

RC11309-10SS4 - - - - 1 - CABLE, JUMPER

S2891103-10SS6 - - - 1 - 1 JUMPER
 

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2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

Group 5: 

Kit SB10280249-11 - Group 5: 

New Part 

Number

Figure

Name

1234589

QTY

ABN7210-539 1 - 1 - - 1 1 BRACKET ASSY

ABN7294-793 - - - - 1 - - BRACKET

HL326-6-2 2 1 2 2 2 2 2 PIN

MS21042L3 2 1 2 4 3 3 3 NUT

MS35338-42 - - - - 1 - - LOCKWASHER

MS35338-43 1 - 1 - - 1 1 LOCKWASHER

NAS1149F0332P 3 2 3 6 4 5 5 WASHER

NAS1149FN832P - - - - 1 - - WASHER

NAS1801-08-10 - - - - 1 - - SCREW

NAS1801-3-9 1 - 1 2 1 2 2 SCREW

RC11307-10SS4 - 1 - 1 1 1 1 CABLE, JUMPER

RC11307-10SS6 1 - 1 - - - - CABLE, JUMPER

RC11309-10SS4 - - - - 1 - - CABLE, JUMPER

S2891103-

10SS12 - - - - - 1 - JUMPER

S2891103-10SS6 - - - 1 - - 1 JUMPER

Part Number / 

Specification QTY Name Notes

PR-1776 B-2, 

(DMS 2427 B-2) 

or 

Equivalent

1 Tube 

6.12 Oz.

Fillet Sealing Compound, Lower 

Specific Gravity

(a)

(a) May be purchased from: PRC-DeSoto International, Incorporated CAGE

5430 San Fernando Road 83574

Glendale, California 91203
 

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D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BLANK PAGE
 

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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

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

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

AIRPLANE CAN OCCUR.

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED

MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES

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

SPARKS OR OTHER ELECTRICAL DAMAGE.

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

DAMAGE TO THE AIRPLANE OR EQUIPMENT.

NOTE:

1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give 

the recommended sequence of steps. The sequence of steps to do this service bulletin 

can be changed.

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

definition of the acronyms.

3. Refer to SWPM 20-50-01 as an accepted Electrical Bonding procedure.

4. Use the approved fastener and process material substitutions. Refer to Structural Repair 

Manual DC-10 or MD-10 SRM, Chapter 51. 

5. 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.

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

7. 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. 

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

— Linear dimensions are in inches

— Tolerance on rivet and bolt edge margin is plus or minus 0.05 Inch

— Hole dimensions for standard solid rivets are in SRM, Chapter 51

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

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

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10. These work instructions refer to procedures included on 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.

11. Cover Fill Valve Controller to protect it from any debris during shroud assembly rework. 

Fill Valve Controller may be removed and reinstalled for ease of rework at operator’s 

option.

B. WORK INSTRUCTIONS

Group 1: 

1. Gain access to area of change by opening and keeping the panel and associated hardware as 

follows:

2. Install electrical bonding jumper as follows:

3. Close access.

4. Put the airplane back in serviceable condition.

Panel Number Name/Location Refer to

526FB Left Wing Outboard Leading Edge and 

Slats 

DC-10 AMM 06-35-00 

or 

MD-10 AMM 06-35-00

615FB Right Wing Inboard Leading Edge and 

Slats 

DC-10 AMM 06-36-00 

or 

MD-10 AMM 06-36-00

626FB Right Wing Outboard Leading Edge 

and Slats 

DC-10 AMM 06-36-00 

or 

MD-10 AMM 06-36-00

Location In Accordance With Figure

Wing Fuel Tank 1 1

Wing Fuel Tank 2 2

Wing Fuel Tank 3 3
 

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Group 2: 

1. Gain access to area of change by opening and keeping the panel and associated hardware as 

follows:

2. Install electrical bonding jumper as follows:

3. Close access.

4. Put the airplane back in serviceable condition.

Panel Number Name/Location Refer to

526FB Left Wing Outboard Leading Edge 

and Slats 

DC-10 AMM 06-35-00 

or

MD-10 AMM 06-35-00

615FB Right Wing Inboard Leading Edge 

and Slats 

DC-10 AMM 06-36-00 

or 

MD-10 AMM 06-36-00

626FB Right Wing Outboard Leading 

Edge and Slats 

DC-10 AMM 06-36-00 

or

MD-10 AMM 06-36-00

 _ Main Landing Gear Doors Left 

and Right 

DC-10 AMM 06-27-00 

or

MD-10 AMM 06-27-00

Location In Accordance With Figure

Wing Fuel Tank 1 1

Wing Fuel Tank 2 2

Wing Fuel Tank 3 3

Auxiliary Fuel Tank 6
 

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Group 3: 

1. Gain access to area of change by opening and keeping the panel and associated hardware as 

follows:

2. Install electrical bonding jumper as follows:

3. If Fill Valve Controller is removed, do an Adjustment/Test Engine Fuel Supply System. Refer to 

DC-10 AMM 28-22-00 or MD-10 AMM 28-22-00 as an accepted procedure.

4. Close access.

5. Put the airplane back in serviceable condition.

Group 4: 

1. Gain access to area of change by opening and keeping the panel and associated hardware as 

follows:

Panel Number Name/Location Refer to

526FB Left Wing Outboard Leading Edge 

and Slats 

DC-10 AMM 06-35-00 

or 

MD-10 AMM 06-35-00

615FB Right Wing Inboard Leading Edge 

and Slats 

DC-10 AMM 06-36-00 

or 

MD-10 AMM 06-36-00

626FB Right Wing Outboard Leading 

Edge and Slats 

DC-10 AMM 06-36-00 

or 

MD-10 AMM 06-36-00

 _ Main Landing Gear Doors Left 

and Right 

DC-10 AMM 06-27-00 

or

MD-10 AMM 06-27-00

Location In Accordance With Figure

Wing Fuel Tank 1 1

Wing Fuel Tank 2 2

Wing Fuel Tank 3 3

Lower Auxiliary Fuel Tank 4

Upper Auxiliary Fuel Tank 5

Panel Number Name/Location Refer to

526FB Left Wing Outboard Leading Edge and Slats DC-10 AMM 06-35-00

615FB Right Wing Inboard Leading Edge and Slats DC-10 AMM 06-36-00

626FB Right Wing Outboard Leading Edge and Slats DC-10 AMM 06-36-00

 _ Main Landing Gear Doors Left and Right DC-10 AMM 06-27-00

 _ Center Cargo Door Right Side DC-10 AMM 06-38-01
 

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2. Install electrical bonding jumper as follows:

3. If Fill Valve Controller is removed, do an Adjustment/Test Engine Fuel Supply System. Refer to 

DC-10 AMM 28-22-00 as an accepted procedure.

4. Close access.

5. Put the airplane back in serviceable condition.

Group 5: 

1. Gain access to area of change by opening and keeping the panel and associated hardware as 

follows: 

2. Install electrical bonding jumper as follows:

3. If Fill Valve Controller is removed, do an Adjustment/Test Engine Fuel Supply System. Refer to 

DC-10 AMM 28-22-00 as an accepted procedure.

4. Close access.

5. Put the airplane back in serviceable condition.

Location In Accordance With Figure

Wing Fuel Tank 1 1

Wing Fuel Tank 2 2

Wing Fuel Tank 3 3

Lower Auxiliary Fuel Tank 4

Upper Auxiliary Fuel Tank 5

Aft Auxiliary Fuel Tank 7

Panel Number Name/Location Refer to

520MB Left Wing Outboard Leading Edge and Slats DC-10 AMM 06-35-00

610GB Right Wing Inboard Leading Edge and Slats DC-10 AMM 06-36-00

620MB Right Wing Outboard Leading Edge and Slats DC-10 AMM 06-36-00

 _ Main Landing Gear Doors Left and Right DC-10 AMM 06-27-00

130AB Center Accessory Floor Panel DC-10 AMM 06-31-00

Location In Accordance With Figure

Wing Fuel Tank 1 1

Wing Fuel Tank 2 2

Wing Fuel Tank 3 3

Lower Auxiliary Fuel Tank 4

Upper Auxiliary Fuel Tank 5

Fwd Body Tank 8

Aft Body Tank 9
 FIGURE 1: JUMPER INSTALLATION - TANK 1

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FIGURE 1: JUMPER INSTALLATION - TANK 1

OUTBD

UP

B B

2

A

SEE A

1

4.50

1.50

Xfs=918.00

LEFT SIDE

LOOKING AFT AT FRONT SPAR

BEFORE

1356567

(SHEET 1 OF 4)
 FIGURE 1: JUMPER INSTALLATION - TANK 1

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OUTBD

UP

OUTBD

UP

B-B

0.44

4

D D

Xfs=918.00

C C

LEFT SIDE

LOOKING AFT AT FRONT SPAR

AFTER

A

3

2 0.50

(2 LOCATIONS)

3

LOOKING UP

1356568

(SHEET 2 OF 4)
 FIGURE 1: JUMPER INSTALLATION - TANK 1

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C-C D-D

3

5

6

3

1356569

(SHEET 3 OF 4)
 FIGURE 1: JUMPER INSTALLATION - TANK 1

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET ASSY ABN7210-539 - Locate, drill and process 2 holes 

for HL326-6 pin. Refer to DC-10 

or MD-10 SRM 51-33-01 as an 

accepted procedure.

3 Apply BOND - - Faying surfaces common to 

jumper terminals, bracket to 

structure, and fill valve controller 

for current path return. Refer to 

DC-10 or MD-10 SWPM 

20-50-01 as an accepted 

procedure.

4 Install (New) BRACKET ASSY ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 or MD-10 SRM 

51-33-01 as an accepted 

procedure. Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Install (New) CABLE, JUMPER RC11307-10SS6 1 Terminal lug of cable jumper 

may be bent for ease of 

installation. Refer to DC-10 or 

MD-10 SWPM 20-20-01as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

Install (New) WASHER NAS1149F0332P 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) SCREW NAS1801-3-9 1

6 Install (New) CABLE, JUMPER RC11307-10SS6 - Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 or MD-10 

SWPM 20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving 

parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

(SHEET 4 OF 4)
 FIGURE 2: JUMPER INSTALLATION - TANK 2

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FIGURE 2: JUMPER INSTALLATION - TANK 2

INBD

UP

Xfs=-227.00

RIGHT SIDE

LOOKING AFT AT FRONT SPAR

B B

1

SEE A

1357643

(SHEET 1 OF 3)
 FIGURE 2: JUMPER INSTALLATION - TANK 2

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FWD

UP

FWD

C

C

B-B

5

3

4

3

2

1.50

0.70

0.60

4

EXISTING

BRACKET

C-C

A

Xfs=227.000

4

1357644

(SHEET 2 OF 3)
 FIGURE 2: JUMPER INSTALLATION - TANK 2

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill SUPPORT - 1 Locate, drill and process hole for 

HL326-6 pin. Refer to DC-10 or 

MD-10 SRM 51-33-01 as an 

accepted procedure. 

3 Apply BOND - - Faying surfaces common to 

jumper terminals, support, and 

fill valve controller for current 

path return. Refer to DC-10 or 

MD-10 SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) CABLE, JUMPER RC11307-10SS4 1 Terminal lug of cable jumper 

may be bent for ease of 

installation. Refer to DC-10 or 

MD-10 SWPM 20-20-01as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

Install (New) WASHER NAS1149F0332P 2

Install (New) PIN HL326-6-2 1 Refer to DC-10 or MD-10 SRM 

51-33-01 as an accepted 

procedure.

Install (New) NUT MS21042L3 1

5 Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of cable jumper 

may be bent for ease of 

installation. Refer to DC-10 or 

MD-10 SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

(SHEET 3 OF 3)
 FIGURE 3: JUMPER INSTALLATION - TANK 3

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FIGURE 3: JUMPER INSTALLATION - TANK 3

INBD

UP

B B

4.50

1.50

Xfs=-918.00

2

SEE A

RIGHT SIDE

LOOKING AFT AT FRONT SPAR

BEFORE

A 1

1357563

(SHEET 1 OF 4)
 FIGURE 3: JUMPER INSTALLATION - TANK 3

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INBD

UP

INBD

FWD B-B

0.44

4

RIGHT SIDE

LOOKING AFT AT FRONT SPAR

AFTER

A

Xfs=-918.00

C C

D D

LOOKING UP

0.50 

(2 LOCATIONS)

3 2

1357565

(SHEET 2 OF 4)
 FIGURE 3: JUMPER INSTALLATION - TANK 3

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

C-C D-D

5

3

3

6

1357566

(SHEET 3 OF 4)
 FIGURE 3: JUMPER INSTALLATION - TANK 3

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET 

ASSEMBLY

ABN7210-539 1 Locate, drill and process 2 holes 

for HL326-6 pin. Refer to DC-10 

or MD-10 SRM 51-33-01 as an 

accepted procedure. 

3 Apply BOND - - Faying surfaces common to 

jumper terminals, bracket to 

structure, and fill valve controller 

for current path return. Refer to 

DC-10 or MD-10 SWPM 

20-50-01 as an accepted 

procedure.

4 Install (New) BRACKET 

ASSEMBLY

ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 or MD-10 SRM 

51-33-01 as an accepted 

procedure.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Install (New) CABLE, JUMPER RC11307-10SS6 1 Terminal lug of cable jumper 

may be bent for ease of 

installation. Refer to DC-10 or 

MD-10 SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against 

fuel pipes, fuel tank, cables or 

moving parts.

Install (New) WASHER NAS1149F0332P 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) SCREW NAS1801-3-9 1

6 Install (New) CABLE, JUMPER RC11307-10SS6 - Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 or MD-10 

SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against 

fuel pipes, fuel tank, cables or 

moving parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

(SHEET 4 OF 4)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

UP

OUTBD

SEE A

LOOKING FORWARD AT REAR SPAR

STATION Y=1370.000

LOWER AUXILIARY FUEL TANK

A

BEFORE

X=0.000

AIRPLANE CENTERLINE

SEE D

B

B

1

Z=-105.000

1357852

(SHEET 1 OF 7)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FWD

UP

FWD

UP

OUTBD

0.88

0.47

C C

B-B

BEFORE

B-B

AFTER

C-C

5

2

2 4

7 8

8

5

STA

Y=1370.000

STA

Y=1370.000

1.70

3

6 7

EXISTING

HOLE

1357853

(SHEET 2 OF 7)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

FWD

3.70

3.10

D

9

X=0.000

(2 LOCATIONS)

10

6.00

5.00

1357854

(SHEET 3 OF 7)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

A

AFTER

LOOKING FORWARD AT STATION Y=1370.000

LOWER AUXILIARY FUEL TANK

F

E

F

E

12

1357855

(SHEET 4 OF 7)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

F-F

11

11

E-E

12

10

10

10

1357739

(SHEET 5 OF 7)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 83

BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER - 1 Refer to DC-10 or MD-10 AMM 28-

21-02 as an accepted procedure.

Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Remove/Keep BRACKET ANL7132-1 1 Clamp and associated hardware.

3 Fill - 1 Plug existing hole with AD 

material.

4 Drill BRACKET ANL7132-1 1 Locate, drill .218/.229 diameter 

hole. Refer to DC-10 or MD-10 

SRM 51-31-01 as an accepted 

procedure. 

5 Apply BOND - - Faying surfaces common to 

jumper terminals, and bracket to 

structure for current path return. 

Refer to DC-10 or MD-10 SWPM 

20-50-01 as an accepted 

procedure.

6 Drill BRACKET ANL7132-1 1 Re-locate, drill and process 2 

holes for HL326-6 pin. Refer to 

DC-10 or MD-10 SRM 51-31-01 as 

an accepted procedure. 

7 Install (Kept) BRACKET ANL7132-1 1 Clamp and associated hardware.

Install (New) PIN HL326-6-2 2 Refer to DC-10 or MD-10 SRM 51-

33-01 as an accepted procedure. 

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

8 Install (New) JUMPER S2891103-10SS6 1 Terminal lug of jumper may be 

bent for ease of installation. 

Acceptable to locate screw head 

and bonding jumper terminal lug 

on outboard side (flat side) of 

ANL7132-1 bracket. Refer to DC10 or MD-10 SWPM 20-20-01 as 

an accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or moving 

parts.

Install (New) WASHER NAS1149F0332P 2

Install (New) SCREW NAS1801-3-9 1

Install (New) NUT MS21042L3 1

(SHEET 6 OF 7)
 FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

9 Drill SHROUD ANL7131-1 1 Drill .218/.229 diameter hole. 

Refer to DC-10 or MD-10 SRM 51-

31-01 as an accepted procedure. 

10 Apply BOND - - Faying surfaces common to 

jumper terminals, shroud, and fill 

valve controller for fault current 

protection. Refer to DC-10 or MD10 SWPM 20-50-01 as an 

accepted procedure.

11 Install (New) JUMPER S2891103-10SS6 - Acceptable to form jumper lug to 

contour of fill valve controller 

shroud to achieve maximum faying 

surface contact with fill valve 

contoller shroud. Terminal lug of 

jumper may be bent for ease of 

installation. Refer to DC-10 or MD10 SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or moving 

parts.

Install (New) CABLE, JUMPER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2

Install (New) SCREW NAS1801-3-9 1

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to DC-10 

or MD-10 SRM 51-41-01 as an 

accepted procedure. 

12 Install (Kept) WASHER - 1

Install (Kept) BOLT - 1

Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be 

bent for ease of installation. Refer 

to DC-10 or MD-10 SWPM 

20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving parts.

Install (Kept) COVER - 1 Refer to DC-10 or MD-10 AMM 

28-21-02 as an accepted 

procedure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

UP

OUTBD

SEE A

A

BEFORE

LOOKING FORWARD AT REAR SPAR

STATION Y=1370.000

UPPER AUXILIARY FUEL TANK

X=0.000

AIRPLANE CENTERLINE

Zirs=11.380

B

B

SEE D

1

1358412

(SHEET 1 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FWD

UP

STA

Y=1370.000

3

5

B-B

C-C

C C

0.80

0.50

(2 LOCATIONS)

2

LOOKING UP

Zcw=15.200

(APPROX)

STA

Y=1370.000

4

1.50

0.20

1358413

(SHEET 2 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FWD

3.70

3.10

D

7

6

X=0.000

(2 PLACES)

1.00

1358414

(SHEET 3 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

A

AFTER

LOOKING FORWARD AT REAR SPAR

STATION Y=1370.000

UPPER AUXILIARY FUEL TANK

E

F

E

F

9

1358415

(SHEET 4 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 83

BOEING SERVICE BULLETIN DC10-28-249

F-F

7

7

8

E-E

9

7

8

1358416

(SHEET 5 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 83

BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER - 1 Refer to DC-10 or MD-10 AMM 28-

21-02 as an accepted procedure.

Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET ABN7294-793 1 Locate, drill and process 2 holes for 

HL326-6 pin. Refer to DC-10 or MD10 SRM 51-33-01 as an accepted 

procedure. 

3 Apply BOND - - Faying surfaces common to jumper 

terminals, and bracket to structure 

for current path return. Refer to DC10 or MD-10 SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) BRACKET ABN7294-793 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 or MD-10 SRM 51-

33-01 as an accepted procedure.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Install (New) CABLE, JUMPER RC11309-10SS4 1 Terminal lug of cable jumper may be 

bent for ease of installation. Refer to 

DC-10 or MD-10 SWPM 20-20-01 as 

an accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or moving 

parts.

Install (New) WASHER NAS1149FN832P 1

Install (New) LOCKWASHER MS35338-42 1

Install (New) SCREW NAS1801-08-10 1

6 Drill SHROUD ANL7131-1 1 Drill .218/.229 diameter hole. Refer 

to DC-10 or MD-10 SRM 51-31-01 

as an accepted procedure.

7 Apply BOND - - Faying surfaces common to jumper 

terminals, shroud, and fill valve 

controller for current path return. 

Refer to DC-10 or MD-10 SWPM 

20-50-01 as an accepted procedure.

(SHEET 6 OF 7)
 FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

8 Install (New) CABLE, JUMPER RC11309-10SS4 - Acceptable to form jumper lug to 

contour of fill valve controller shroud 

to achieve maximum faying surface 

contact with fill valve controller 

shroud. Terminal lug of jumper may 

be bent for ease of installation. Refer 

to DC-10 or MD-10 SWPM 20-20-01 

as an accepted procedure. Make 

sure jumper does not rest against 

fuel pipes, fuel tank, cables or 

moving parts.

Install (New) CABLE, JUMPER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2

Install (New) SCREW NAS1801-3-9 1

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to DC-10 or 

MD-10 SRM 51-41-01 as an 

accepted procedure. 

9 Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be bent 

for ease of installation. Refer to DC10 or MD-10 SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or moving 

parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

Install (Kept) COVER - 1 Refer to DC-10 or MD-10 AMM 28-

21-02 as an accepted procedure. 

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 7)
 FIGURE 6: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 83

BOEING SERVICE BULLETIN DC10-28-249

FIGURE 6: JUMPER INSTALLATION - UPPER AUXILIARY TANK

UP

OUTBD

SEE A

A

BEFORE

LOOKING FORWARD AT REAR SPAR

STATION Y=1370.000

UPPER AUXILIARY FUEL TANK

X=0.000

AIRPLANE CENTERLINE

Z=11.380

1.50

0.50

B B

1

1358418

(SHEET 1 OF 4)
 FIGURE 6: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

UP

OUTBD

B-B

0.44

2

A

D D C C

AFTER

LOOKING FORWARD AT REAR SPAR

STATION Y=1370.000

UPPER AUXILIARY FUEL TANK

0.50

(2 LOCATIONS)

3

4

1357645

(SHEET 2 OF 4)
 FIGURE 6: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

C-C

3

5

D-D

6

3

1359741

(SHEET 3 OF 4)
 FIGURE 6: JUMPER INSTALLATION - UPPER AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 62 of 83

BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane. 

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET 

ASSEMBLY

ABN7210-539 1 Locate, drill and process 2 holes 

for HL326-6 pin. Refer to DC-10 

or MD-10 SRM 51-33-01 as an 

accepted procedure. 

3 Apply BOND - - Faying surfaces common to 

jumper terminals, bracket, and 

fill valve controller for current 

path return. Refer to DC-10 or 

MD-10 SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) BRACKET 

ASSEMBLY

ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 or MD-10 SRM 

51-33-01 as an accepted 

procedure. 

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Install (New) CABLE, JUMPER RC11307-10SS4 1 Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 or MD-10 SWPM 

20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving parts.

Install (New) WASHER NAS1149F0332P 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) SCREW NAS1801-3-9 1

6 Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 or MD-10 

SWPM 20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

(SHEET 4 OF 4)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

X=-58.220 X=-48.220 SEE A

A

SEE D

B

B

1

Z=-51.250

BEFORE

LOOKING AFT AT STATION Y=1792.000

AFT AUXILIARY FUEL TANK

1359758

(SHEET 1 OF 7)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FWD

UP

LOOKING UP

2

C-C 5

6

C C

1.50

0.50

B-B

0.50

(2 LOCATIONS)

4

3

0.44

1.50

0.50

1359759

(SHEET 2 OF 7)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 65 of 83

BOEING SERVICE BULLETIN DC10-28-249

FWD

3.70

3.10

D

8

7

X=-53.220

(2 LOCATIONS)

6.00

5.00

1359760

(SHEET 3 OF 7)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 66 of 83

BOEING SERVICE BULLETIN DC10-28-249

X=-58.220 X=-48.220

A

AFTER

LOOKING AFT AT STATION Y=1792.000

AFT AUXILIARY FUEL TANK

E

F

E

F

10

1359761

(SHEET 4 OF 7)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 67 of 83

BOEING SERVICE BULLETIN DC10-28-249

E-E F-F

8

8

9

9

10

8

1360046

(SHEET 5 OF 7)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 68 of 83

BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER - 1 Refer to DC-10 AMM 28-21-02 as 

an accepted procedure.

Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET 

ASSEMBLY

ABN7210-539 1 Locate, drill and process 2 holes 

for HL326-6 pin. Refer to DC-10 

SRM 51-33-01 as an accepted 

procedure. 

3 Apply BOND - - Faying surfaces common to 

jumper terminals, and bracket for 

current path return. Refer to DC10 SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) BRACKET 

ASSEMBLY

ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 SRM 51-33-01 as 

an accepted procedure.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Bond - - - Faying surfaces common to 

jumper terminals, and bracket for 

current path return. Refer to DC10 SWPM 20-50-01 as an 

accepted procedure.

6 Install (New) JUMPER S2891103-10SS6 1 Terminal lug of jumper may be 

bent for ease of installation. Refer 

to DC-10 SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or moving 

parts. 

Install (New) WASHER NAS1149F0332P 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) SCREW NAS1801-3-9 1

7 Drill SHROUD AGL7031-1 1 Drill .218/.229 diameter hole. 

Refer to DC-10 SRM 51-31-01 as 

an accepted procedure. 

8 Apply BOND - - Apply surfaces common to jumper 

terminals, shroud, and fill valve 

controller for current path return. 

Refer to DC-10 SWPM 20-50-01 

as an accepted procedure.

(SHEET 6 OF 7)
 FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

9 Install (New) JUMPER S2891103-10SS6 - Acceptable to form jumper lug to 

contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with valve 

controller shroud. Terminal lug of 

jumper may be bent for ease of 

installation. Refer to DC-10 

SWPM 20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving parts. 

Install (New) CABLE, JUMPER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2

Install (New) SCREW NAS1801-3-9 1

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to DC-10 

SRM 51-41-01 as an accepted 

procedure. 

10 Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be 

bent for ease of installation. Refer 

to DC-10 SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against fuel 

pipes, fuel tank, cables or moving 

parts.

Install (Kept) WASHER - 1

Install (Kept) BOLT - 1

Install (Kept) COVER - 1 Refer to DC-10 AMM 28-21-02 as 

an accepted procedure. 

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 70 of 83

BOEING SERVICE BULLETIN DC10-28-249

FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

OUTBD

UP

Z=-40.141

SEE A

X=-6.000

SEE D

B

B

A

BEFORE

LOOKING FORWARD AT STATION Y=1059.000

FORWARD BODY TANK

1

EXISTING

CLIP

1358417

(SHEET 1 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

FWD

UP

LOOKING UP

C-C

6

5

3

2

C C

B-B

4.40

3.40

0.44

4

0.50

(2 LOCATIONS)

1.70

1.20

(2 LOCATIONS)

EXISTING CLIP

1360047

(SHEET 2 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

FWD

D

8

7

X=-6.000

(2 LOCATIONS)

1.00

1.70

1.10

1360704

(SHEET 3 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

OUTBD

UP

A

AFTER

LOOKING FORWARD AT STATION Y=1059.000

FORWARD BODY TANK

E

F

E

F

10

Z=-40.141

X=-6.000

1360705

(SHEET 4 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

E-E F-F

8

9

8

9 10

8

1360706

(SHEET 5 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER - 1 Refer to DC-10 AMM 28-21-02 

as an accepted procedure. 

Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET 

ASSEMBLY

ABN7210-539 1 Locate, drill and process 2 holes 

for HL326-6 pin. Refer to DC-10 

SRM 51-33-01 as an accepted 

procedure. 

3 Apply BOND - - Faying surfaces common 

bracket to structure for current 

path return. Refer to DC-10 

SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) BRACKET 

ASSEMBLY

ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 SRM 51-33-01 

as an accepted procedure. 

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Bond - - - Faying surfaces common to 

jumper terminals, and bracket 

for current path return. Refer to 

DC-10 SWPM 20-50-01 as an 

accepted procedure.

6 Install (New) JUMPER S2891103-10SS12 1 Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 SWPM 

20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving 

parts. 

Install (New) WASHER NAS1149F0332P 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) SCREW NAS1801-3-9 1

7 Drill SHROUD ANL7131-1 1 Drill .218/.229 diameter hole. 

Refer to DC-10 SRM 51-31-01 

as an accepted procedure. 

(SHEET 6 OF 7)
 FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

8 Apply BOND - - Faying surfaces common to 

jumper terminals, shroud, and 

fill valve controller for current 

path return. Refer to DC-10 

SWPM 20-50-01 as an 

accepted procedure.

9 Install (New) JUMPER S2891103-10SS12 - Acceptable to form jumper lug to 

contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 SWPM 

20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving 

parts. 

Install (New) CABLE, JUMPER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2

Install (New) SCREW NAS1801-3-9 1

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to DC10 SRM 51-41-01 as an 

accepted procedure. 

10 Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 SWPM 

20-20-01 as an accepted 

procedure. Make sure jumper 

does not rest against fuel pipes, 

fuel tank, cables or moving 

parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

Install (Kept) COVER - 1 Refer to DC-10 AMM 28-21-02 

as an accepted procedure. 

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

UP

OUTBD

A

BEFORE

LOOKING AFT AT STATION Y=1521.000

AFT BODY TANK

SEE D

B

B

SEE A

Z=-50.000

X=-54.250

1

Z=-51.340

1360707

(SHEET 1 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

FWD

UP

2

C C

B-B

2.50

1.50

Z=-50.000

LOOKING UP

C-C 5

6

0.44

0.50

(2 LOCATIONS)

3

4

2

1360708

(SHEET 2 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

FWD

1.70

1.10

D

8

7

X=-54.250

(2 LOCATIONS)

6.00

5.00

1360709

(SHEET 3 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

UP

OUTBD

A

AFTER

LOOKING AFT AT STATION Y=1521.000

AFT BODY TANK

E

F

E

F

Z=-51.340

Z=-50.000

X=-54.250

10

1360710

(SHEET 4 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

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BOEING SERVICE BULLETIN DC10-28-249

E-E F-F

8

8

9

9

10

8

1360711

(SHEET 5 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 82 of 83

BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER - 1 Refer to DC-10 AMM 28-21-02 

as an accepted procedure. 

Remove/Keep BOLT - 1

Remove/Keep WASHER - 1

2 Drill BRACKET 

ASSEMBLY

ABN7210-539 1 Locate, drill and process 2 holes 

for HL326-6 pin. Refer to DC-10 

SRM 51-33-01 as an accepted 

procedure. 

3 Apply BOND - - Faying surfaces common 

bracket to structure for current 

path return. Refer to DC-10 

SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) BRACKET 

ASSEMBLY

ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to DC-10 SRM 51-33-01 

as an accepted procedure. 

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Bond - - - Faying surfaces common to 

jumper terminals, and bracket 

for current path return. Refer to 

DC-10 SWPM 20-50-01 as an 

accepted procedure.

6 Install (New) JUMPER S2891103-10SS6 1 Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 SWPM 20-20-01 

as an accepted procedure. 

Make sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts. 

Install (New) WASHER NAS1149F0332P 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) SCREW NAS1801-3-9 1

7 Drill SHROUD ANL7131-1 1 Drill .218/.229 diameter hole. 

Refer to DC-10 SRM 51-31-01 

as an accepted procedure. 

8 Apply BOND - - Faying surfaces common to 

jumper terminals, shroud, and 

fill valve controller for current 

path return. Refer to DC-10 

SWPM 20-50-01 as an 

accepted procedure.

(SHEET 6 OF 7)
 FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK

August 07, 2007

Revision 1: November 06, 2008 DC10-28-249

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BOEING SERVICE BULLETIN DC10-28-249

9 Install (New) JUMPER S2891103-10SS6 - Acceptable to form jumper lug to 

contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with valve 

controller shroud. Terminal lug 

of jumper may be bent for ease 

of installation. Refer to DC-10 

SWPM 20-20-01 as an 

accepted procedure. Make sure 

jumper does not rest against 

fuel pipes, fuel tank, cables or 

moving parts. 

Install (New) CABLE, JUMPER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2

Install (New) SCREW NAS1801-3-9 1

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to DC10 SRM 51-41-01 as an 

accepted procedure. 

10 Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be 

bent for ease of installation. 

Refer to DC-10 SWPM 20-20-01 

as an accepted procedure. 

Make sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (Kept) BOLT - 1

Install (Kept) WASHER - 1

Install (Kept) COVER - 1 Refer to DC-10 AMM 28-21-02 

as an accepted procedure. 

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 7)