August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 83 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 Shut off, Tank All - Install Electrical Bonding Jumper 

## BOEING PROPRIETARY, CONFID ENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document on ly to the extent that the page contains copyrightable subject matter.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 Compan y, 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 intellectua l property license (express or implied) is granted in connection with this document or otherwise.BLANK PAGE August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 2 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

BLANK PAGETable of Contents August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 83 

### 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 Intermix ability 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 Spar es . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 4 FIGURE 2: JUMPER INSTALLATION - TANK 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 8 FIGURE 3: JUMPER INSTALLATION - TANK 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 1 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 . . . . . . . . . . . . . . . . . . . . . . . 77Table of Contents August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 4 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

BLANK PAGEAugust 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 Shut off, Tank All - Install Electrical Bonding Jumper

This Revision includes all pages of the service bulletin.
COMPLIANCE INFORM ATION RELATED TO THIS REVISION No more work is necessary as shown in th e original issue of this service bulletin.
REASON FOR REVISION This revision is sent to incorporate engineering released s ubsequent to the original iss ue of this service bulletin, which relocates ground brackets and jumpers due to in terference with airplane co mponents/structure. Noted changes are based on findings discov ered as a result of se rvice bulletin survey done at an airline facility. This revision removes the no-work condition gi ven in Information Notice DC10-28-249 IN 01. These sections were changed: 1. Paragraph 1.A., Effectiv ity, 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.August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 6 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

12. In Paragraph 3.B., Work Instructions, added in Tables to Gr oup 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 illu stration and step table. 15. In Figure 2, changed illu stration and step table. 16. In Figure 3, changed illu stration and step table. 17. In Figure 4, changed illu stration and step table. 18. In Figure 5, changed illu stration and step table. 19. In Figure 6, changed illu stration and step table. 20. In Figure 7, changed illu stration and step table. 21. In Figure 8, changed illu stration and step table. 22. In Figure 9, changed illu stration 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, exce pt in Paragraph 1.A., Effectiv ity, 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, 2008August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 83 

### 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 Shut off, Tank All - Install Electrical Bonding Jumper

CONCURRENT REQUIREMENTS
None.
BACKGROUND Boeing investigation and analy sis revealed that all the fill valve contro ller installations had inadequate el ectrical bonding. This could allow point-of-co ntact arcing or filament heating da mage in the fuel tanks. Installing electrical bonding jumpers from the fill valve controllers to airplane stru cture will provide a gr ounding path in the event of a fault curren t occurrence in the fill valve controller. If not corrected, a high current occurrence could result in a potential source of igniti on 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 instructi ons to install electrical bonding jum pers 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 (F AA) will possibly release an Airworthin ess Directive related to this service bulletin. The Airworthiness Directiv e will make the compliance tasks and ti mes 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.August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 8 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

MANPOWER Refer to Paragraph 1.G., for manpower information.
MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragr aph 2.A., Material - Price and Availability.

INSTALL ELECTRICAL BONDING JUMPER AND1360712August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 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 Shut off, 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 fu el tank that are modified to MD-10-10F co nfiguration by Boeing Engineering will bec ome 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, CUSTOM ER 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, lo wer, and aft auxiliary fuel tanks configuration. 5 - Applicable to KC-10A airplanes.August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 10 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 248August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 83 

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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 234August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 12 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 381August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 1August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 14 of 83 

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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 GroupAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 83 

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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 GroupAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 16 of 83 

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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 GroupAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

2. Spares Affected
None. B. Concurrent Requirements
None.
C. Reason Boeing investigation and analysis re vealed that all the fill valve cont roller installation s had inadequate electrical bonding. This could allow point-of-contact arcing or filament heating damage in the fuel tanks. Installing electrical bondin g jumpers from the fill valve contro llers to airplane structure will provide a grounding path in the event of a fault curr ent occurrence in the f ill 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 safe ty 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 discove red 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 GroupAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 18 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

D. Description This service bulletin provides inst ructions to install electrical b onding jumpers from the fill valve controllers to the airplane structure.
Revision 1 - No more work is ne cessary as shown in the original issue of this service bulletin.

E. Compliance
The Federal Aviation Admini stration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airwor thiness Directive will ma ke the compliance tas ks 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 No rthwest Mountain Region.

G. Manpower
The table below shows an estimate of the task hour s 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 in clude 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 14.0August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 27.5August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 20 of 83 

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H. Weight and Ba lance 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 31.5August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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

These drawings were used to prepare this servic e 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 bu lletin does not affect interchangeability or intermixability of parts. Document Number Title Change SR10280058 Bonding Impr ovement - Fill Valve Controller, Fuel System, DC-10 E
SR10280062 Bonding Impr ovement - Fill Valve Controller, Fuel System, KC-10A D

Publication Chapter-Section Illustrated Parts Catalog 28-21August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 22 of 83 

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BLANK PAGEAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 condit ions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new pr ice and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your pur chase 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 belo w, refer to Paragraph 2.A., Ma terial - 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 3,805.00August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 24 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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, JUMPERAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 JUMPERAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 26 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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-DeSot o International, Incorporated CAGE 5430 San Fernando Road 83574 Glendale, California 91203August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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.August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 28 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

BLANK PAGEAugust 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

3. ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WO RK. 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 sequen ce of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acrony ms. 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 materi al 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 list ed in the AEPL, Drawing 7595071. 7. A 1/8-inch thick stack of the same type wash ers called for in this service bulletin is the maximum thickness which may be used u nder 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 di mensions 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.August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 30 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

10. These work instructions refer to procedur es included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative pr ocedure can be used. When the words "in accordance with" are included in the instru ction, the procedure in the Boeing document must be used. 11. Cover Fill Valve Controller to protect it from any debris during sh roud assembly rework. Fill Valve Controller may be re moved 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 3August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

Group 2: 1. Gain access to area of change by opening and keeping the panel and associated hardware as follows:

2. Install electrical bond ing 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 6August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 32 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 Adjust ment/Test Engine Fuel S upply 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 Rig ht Side DC-10 AMM 06-38-01August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

2. Install electrical bond ing jumper as follows:

3. If Fill Valve Controller is remove d, do an Adjust ment/Test Engine Fuel Su pply 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 bond ing jumper as follows:

3. If Fill Valve Controller is remove d, do an Adjust ment/Test Engine Fuel Su pply 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 9FIGURE 1: JUMPER INSTALLATION - TANK 1 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 34 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FIGURE 1: JUMPER INSTALLATION - TANK 1

OUTBD UP B B 2



### A A SEE

1 4.50 1.50 Xfs=918.00

LEFT SIDE LOOKING AFT AT FRONT SPAR 

### BEFORE1356567

(SHEET 1 OF 4)FIGURE 1: JUMPER INSTALLATION - TANK 1 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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 UP1356568

(SHEET 2 OF 4)FIGURE 1: JUMPER INSTALLATION - TANK 1 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 36 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

C-C D-D 3 5 6

31356569

(SHEET 3 OF 4)FIGURE 1: JUMPER INSTALLATION - TANK 1 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 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 ASSY ABN7210-539 - Loc ate, 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 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 38 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FIGURE 2: JUMPER INSTALLATION - TANK 2

INBD UP

Xfs=-227.00
RIGHT SIDE LOOKING AFT AT FRONT SPAR B B 1

A SEE1357643

(SHEET 1 OF 3)FIGURE 2: JUMPER INSTALLATION - TANK 2 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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

41357644

(SHEET 2 OF 3)FIGURE 2: JUMPER INSTALLATION - TANK 2 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 40 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FIGURE 3: JUMPER INSTALLATION - TANK 3

INBD UP B B 4.50 1.50 Xfs=-918.00

2 A SEE

RIGHT SIDE LOOKING AFT AT FRONT SPAR 

### BEFORE A 11357563

(SHEET 1 OF 4)FIGURE 3: JUMPER INSTALLATION - TANK 3 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 42 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

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) 2 31357565

(SHEET 2 OF 4)FIGURE 3: JUMPER INSTALLATION - TANK 3 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

D-D C-C 5

3 3 61357566

(SHEET 3 OF 4)FIGURE 3: JUMPER INSTALLATION - TANK 3 August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 44 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 f ill 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 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK

UP

OUTBD A SEE

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=-105.0001357852

(SHEET 1 OF 7)FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 46 of 83 

### 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 HOLE1357853

(SHEET 2 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. 47 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FWD 3.70 3.10



### D 9 X=0.000

(2 LOCATIONS) 10 6.00 5.001357854

(SHEET 3 OF 7)FIGURE 4: JUMPER INSTALLATION - LOWER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 48 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

A AFTER LOOKING FORWARD AT STATION Y=1370.000 LOWER AUXILIARY FUEL TANK F E

F E 121357855

(SHEET 4 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. 49 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

F-F 11

11 

### E-E 12

10 10 101357739

(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 © U npublished Work - See page 1 for details. 50 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 Loc ate, 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 R e-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) ofANL7132-1 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 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

9 Drill SHROUD ANL7131-1 1 D rill .218/.229 di ameter 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 currentprotection. 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 ofinstallation. 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, JUM PER 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 INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 52 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FIGURE 5: JUMPER INSTALLATION - UPPER AUXILIARY TANK

UP

OUTBD A SEE



### 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
11358412

(SHEET 1 OF 7)FIGURE 5: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 83 

### 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 0.201358413

(SHEET 2 OF 7)FIGURE 5: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 54 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FWD 3.70 3.10



### D 7 6 X=0.000

(2 PLACES) 1.001358414

(SHEET 3 OF 7)FIGURE 5: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 83 

### 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 91358415

(SHEET 4 OF 7)FIGURE 5: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 56 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

F-F 7 7

8 

### E-E 9

7 81358416

(SHEET 5 OF 7)FIGURE 5: JUMPER INSTA LLATION - 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 Locat e, drill and process 2 holes forHL326-6 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 re turn. 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 in stallation. 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 diamet er 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 INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 58 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

8 Install (New) CABLE, JUMPER RC11309-10SS4 - Acceptable to form jumper lug to contour of fill valv e 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, JUM PER RC11307-10SS4 1

Install (New) WASHER N AS1149F0332P 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 installa tion. 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 INSTA LLATION - 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 INSTALLA TION - UPPER AUXILIARY TANK

UP

OUTBD A SEE



### 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 11358418

(SHEET 1 OF 4)FIGURE 6: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 60 of 83 

### 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 41357645

(SHEET 2 OF 4)FIGURE 6: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 61 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

C-C 3 5



### D-D 6

31359741

(SHEET 3 OF 4)FIGURE 6: JUMPER INSTA LLATION - UPPER AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 62 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of part s 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 INSTA LLATION - AFT AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 63 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FIGURE 7: JUMPER INSTA LLATION - AFT AUXILIARY TANK

X=-48.220 A SEE X=-58.220



### A D SEE

B B 1

Z=-51.250



### BEFORE LOOKING AFT AT STATION Y=1792.000 AFT AUXILIARY FUEL TANK1359758

(SHEET 1 OF 7)FIGURE 7: JUMPER INSTALLATION - AFT AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 64 of 83 

### 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 0.501359759

(SHEET 2 OF 7)FIGURE 7: JUMPER INSTA LLATION - 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 5.001359760

(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 © U npublished Work - See page 1 for details. 66 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

X=-48.220 X=-58.220



### A AFTER LOOKING AFT AT STATION Y=1792.000 AFT AUXILIARY FUEL TANK E F

E F 101359761

(SHEET 4 OF 7)FIGURE 7: JUMPER INSTA LLATION - 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

81360046

(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 © U npublished Work - See page 1 for details. 68 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 forcurrent 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 forcurrent 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 D rill .218/.229 di ameter 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 INSTA LLATION - AFT AUXILIARY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 69 of 83 

### 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, JUM PER 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 © U npublished 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 A SEE

X=-6.000 D SEE

B B



### A BEFORE LOOKING FORWARD AT STATION Y=1059.000 FORWARD BODY TANK 1

EXISTING CLIP1358417

(SHEET 1 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. 71 of 83 

### 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 CLIP1360047

(SHEET 2 OF 7)FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 72 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FWD



### D 8 7 X=-6.000

(2 LOCATIONS) 1.00 1.70 1.101360704

(SHEET 3 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. 73 of 83 

### 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=-6.0001360705

(SHEET 4 OF 7)FIGURE 8: JUMPER INSTALLATION - FWD BODY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 74 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

E-E F-F 8

9 8 9 10

81360706

(SHEET 5 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. 75 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 S2891103-10SS12 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 D rill .218/.229 di ameter 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 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 76 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

8 Apply BOND - - Faying surfaces common to jumper terminals, shroud, and fill valve contro ller 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, JUM PER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2 Install (New) SCREW NAS1801-3-9 1Install (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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 77 of 83 

### 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 D SEE

B B A SEE

Z=-50.000 X=-54.250

1

Z=-51.3401360707

(SHEET 1 OF 7)FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 78 of 83 

### 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

21360708

(SHEET 2 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. 79 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

FWD 1.70 1.10



### D 8 7 X=-54.250

(2 LOCATIONS) 6.00 5.001360709

(SHEET 3 OF 7)FIGURE 9: JUMPER INSTALLATION - AFT BODY TANK August 07, 2007 Revision 1: November 06, 2008 DC10-28-249 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 80 of 83 

### 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

101360710

(SHEET 4 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. 81 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

E-E F-F 8 8 9

9 10

81360711

(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 © U npublished Work - See page 1 for details. 82 of 83 

### BOEING SERVICE BULLETIN DC10-28-249

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 Dr ill .218/.229 di ameter 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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 83 of 83 

### 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, JUM PER RC11307-10SS4 1

Install (New) WASHER NAS1149F0332P 2 Install (New) SCREW NAS1801-3-9 1Install (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)