**McDonnell Douglas** 

### Commercial **Airplanes** 

# DC10 Service Bulletin **Number: DC10-28-252** Original Issue: November 25, 2008 Revision 1: January 06, 2010 ATA System: 2800 **SUBJECT:**FUEL - Fuel Systems - Install Fuel Tank Float Level Switch and Aft Auxiliary Tank Fuel Pump Pressure Switch In-line Fuses Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 1 of 83 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 2 of 83 **BOEING SERVICE BULLETIN DC10-28-252**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 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:. . . . . . . . . . . 20 4. Process Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 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:. . . . . . . . . . . . . . . . . . . . . . . . 37 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 37 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 Appendix A: FUEL TANK 1 - MD-10-10F AND MD-10-30F [Group 1-2]. . . . . . . . . . . . . . . . . . 46 Appendix B: FUEL TANK 1 - DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30 W/AFT TANK 1500 AND 3200 GALLONS, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F (KDC-10), DC-10-40, DC-10-40F [Group 3-7]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 Appendix C: FUEL TANK 2 - MD-10-10F AND MD-10-30F [Group 1-2]. . . . . . . . . . . . . . . . . . 48 Appendix D: FUEL TANK 2- 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 [Group 3, 6-7]. . . . . . . . . . . . . . . . . 49 Appendix E: FUEL TANK 2 - DC-10-30 W/AFT TANK 1500 AND 3200 GALLONS [Group 4-5]. . . . . 50 Appendix F: FUEL TANK 3 - MD-10-10F AND MD-10-30F [Group 1-2]. . . . . . . . . . . . . . . . . . 51

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 3 of 83 **BOEING SERVICE BULLETIN DC10-28-252**Appendix G: FUEL TANK 3 - DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30 W/AFT TANK 1500 AND 3200 GALLONS, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F (KDC-10), DC-10-40, DC-10-40F [Group 3-7]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 Appendix H: UPPER AND LOWER AUXILIARY FUEL TANKS - MD-10-30F [Group 2]. . . . . . . . . 53 Appendix I: CENTER WING TANKS - DC-10-30F (KC-10A) AND DC-10-30F (KDC-10) [Group 6-7] . 54 Appendix J: FORWARD AND AFT AUXILIARY - DC-10-30F (KC-10A) [Group 6]. . . . . . . . . . . . 55 Appendix K: AFT AUXILIARY FUEL TANK - DC-10-30 W/AFT TANK 1500 GALLONS [Group 4]. . . . 56 Appendix L: UPPER AND LOWER AUXILIARY TANKS - DC-10-30 W/AFT 1500 AND 3200 GALLONS [Group 4-5]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 Appendix M: AFT AUXILIARY FUEL TANK - DC-10-30 W/AFT 3200 GALLONS [Group 5]. . . . . . . 58 Appendix N: MD-10-10F - FUSE FUNCTIONAL TEST [Group 1]. . . . . . . . . . . . . . . . . . . . . 59 Appendix O: MD-10-30F - FUSE FUNCTIONAL TEST [Group 2]. . . . . . . . . . . . . . . . . . . . . 60 Appendix P: DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-40 AND DC-10-40F - FUSE FUNCTIONAL TEST [Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62 Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST [Group 4]. . . . . 63 Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST [Group 5]. . . . . 71 Appendix S: DC-10-30F (KC-10A) - FUSE FUNCTIONAL TEST [Group 6]. . . . . . . . . . . . . . . . 80 Appendix T: DC-10-30F (KDC-10) - FUSE FUNCTIONAL TEST [Group 7]. . . . . . . . . . . . . . . . 82

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 4 of 83 **BOEING SERVICE BULLETIN DC10-28-252 McDonnell Douglas**  

### Commercial **Airplanes** 

# DC10 Service Bulletin **Revision Transmittal Sheet Number: DC10-28-252**  Original Issue: November 25, 2008 Revision 1: January 06, 2010 ATA System: 2800 **SUBJECT:**FUEL - Fuel Systems - Install Fuel Tank Float Level Switch and Aft Auxiliary Tank Fuel Pump Pressure Switch In-line Fuses This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** More work is necessary on airplane changed in accordance with the original issue of this service bulletin. The more work involved is to change wire identifications Q 835 G22 and Q 835 H22 to Q 835 M22 and Q 835 N22 respectively in accordance with Drawing SR10280063 "D" change. **REASON FOR REVISION** This revision is sent to change wire identifications Q 835 G22 and Q 835 H22 to Q 835 M22 and Q 835 N22 respectively in accordance with Drawing SR10280063 "D" change. These sections were changed: 1. In Paragraph 1.A.1., Airplanes, moved airplanes from Group 3 to Groups 1 and 2. 2. In Paragraph 1.D., Description, added Maintenance Zones. 3. In Paragraph 1.F., Approval, change statement. 4. In Paragraph 1.J.2.a., Drawings, changed drawing change D. 5. In Paragraph 1.K., Publications Affected, added Tolerance Based Structural Inspections data. 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** November 25, 2008 Original Issue: January 06, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 5 of 83BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 6 of 83 **BOEING SERVICE BULLETIN DC10-28-252**

BLANK PAGE**McDonnell Douglas** 

### Commercial **Airplanes** 

# DC10 Service Bulletin **Summary Number: DC10-28-252**  Original Issue: November 25, 2008 Revision 1: January 06, 2010 ATA System: 2800 **SUBJECT:**FUEL - Fuel Systems - Install Fuel Tank Float Level Switch and Aft Auxiliary Tank Fuel Pump Pressure Switch In-line Fuses **CONCURRENT REQUIREMENTS** None. **BACKGROUND** An investigation by Boeing has determined that float level switch wires located on the left and right wing forward spar, right main landing gear wheel well, forward and aft cargo compartments and fuel pump pressure switch wires located in the aft cargo compartment are routed in the same bundles as power wires. If a short circuit between a float level or fuel pump pressure switch wire and a power wire occurs, an over current can cause excessive temperatures in the float level or fuel pump pressure switch wires, resulting in damage. Adding an in-line fuse as a self-contained component in each float level and pressure switch circuit and sleeving the wires between the fuel tank and the in-line fuse will minimize the possibility of excessive temperatures in the float level or pressure switch wires. If not corrected, and there is a short circuit of the float level or pressure switch wire to a power wire, possible damage to the float level or fuel pump pressure switch wire could occur, and become a potential ignition source for the fuel tank. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements. **ACTION Group 1-3, 6-7:**  This service bulletin installs fuel tank float level switch in-line fuses. **Group 4-5:** This service bulletin installs fuel tank float level switch and aft auxiliary tank fuel pump pressure switch in-line fuses. **EFFECTIVITY** DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F(KC-10A), DC-10-30F(KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 7 of 83**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 that the change given in this service bulletin be done within 5 years after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G., for Manpower information. **MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 8 of 83 **BOEING SERVICE BULLETIN DC10-28-252 McDonnell Douglas**  

### Commercial **Airplanes** 

# DC10 Service Bulletin **Number: DC10-28-252** Original Issue: November 25, 2008 Revision 1: January 06, 2010 ATA System: 2800 **SUBJECT:**FUEL - Fuel Systems - Install Fuel Tank Float Level Switch and Aft Auxiliary Tank Fuel Pump Pressure Switch In-line Fuses
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes **NOTE:**Any Group 3 DC-10-10, DC-10-10F, and DC-10-15 Airplane modified to MD-10-10F by Boeing Engineering, become Group 1 Airplanes. Any Group 3 DC-10-30 and DC-10-30F Airplanes modified to MD-10-30F by Boeing Engineering, become Group 2 Airplanes. Airplane fuselage number 404 had this modification incorporated at the operator's facility in accordance with Drawing SR10280063-7011.
**DESCRIPTION CONFIGURATION**  **GROUP** Applicable to DC-10-10, DC-10-10F and MD-10-10F airplanes.

- 1 Applicable to DC-10-30F and MD-10-30F airplanes.

- 2 Applicable to DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-40 and DC-10-40F airplanes. - 3
Applicable to DC-10-30 airplanes with 1500 gallon aft auxiliary fuel tank. - 4
Applicable to DC-10-30 airplanes with 3200 gallon aft auxiliary fuel tank. - 5
Applicable to DC-10-30F (KC-10A) airplanes.

- 6 Applicable to DC-10-30F (KDC-10) airplanes.

- 7

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 9 of 83**Group Fuselage Num-**  **ber** 3 100 2 103 3 106 2 110 1 112 3 114 - 115 3 117 1 119 3 122 - 123 3 127 3 129 3 131 - 135 3 137 1 138 - 140 1 142 1 144 - 145 3 146 - 147 1 148 1 15 3 150 3 152 1 153 - 155 3 156 - 158 3 160 3 162 3 165 - 166 1 169 1 17 3 170 - 171 1 173 3 174 1 177

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 10 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group**  **Fuselage Num- ber**  3 178 - 179 3 183 - 184 3 187 - 190 3 192 1 194 3 195 - 196 1 198 3 199 3 2 3 201 1 203 3 204 1 205 3 206 1 207 - 210 3 211 - 216 2 219 3 220 - 221 3 223 - 227 3 229 - 232 3 234 7 235 3 236 3 239 - 242 3 244 - 246 1 247 3 248 1 249 1 25 1 250 3 251 - 256 2 257

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 11 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group**  **Fuselage Num- ber**  1 26 3 261 - 263 7 264 3 265 - 268 1 269 1 27 1 270 - 273 3 274 - 275 2 277 3 281 2 282 3 285 - 286 3 289 - 291 4 292 1 294 3 296 1 297 - 298 3 299 - 306 1 307 3 308 1 309 3 310 6 311 3 312 - 316 2 317 3 318 1 319 1 32 1 321 1 323 3 324 - 325 2 326

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 12 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group**  **Fuselage Num- ber**  3 327 3 329 1 33 2 330 3 332 6 333 3 334 - 339 3 34 3 340 5 341 3 342 - 343 1 344 5 345 3 346 1 347 3 349 1 35 1 351 1 353 3 355 - 356 3 358 6 359 - 361 6 363 3 366 - 367 3 372 6 373 6 375 - 378 1 379 6 380 3 381 6 383 - 389 1 39

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 13 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group**  **Fuselage Num- ber**  6 390 - 399 3 40 6 400 - 408 2 409 3 41 6 410 - 411 2 412 6 413 - 415 2 416 6 417 - 418 2 419 1 42 6 420 - 421 2 422 6 423 - 429 3 43 6 430 - 432 2 433 5 434 - 438 6 439 2 440 6 441 2 442 - 444 3 445 - 446 1 55 1 59 1 6 3 60 - 61 1 62 3 65 1 70 3 71 - 72

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 14 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group**  **Fuselage Num- ber**  1 76 1 78 1 8 3 83 1 86 1 89 3 90 2 96 3 99 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** An investigation by Boeing has determined that float level switch wires located on the left and right wing forward spar, right main landing gear wheel well, forward and aft cargo compartments and fuel pump pressure switch wires located in the aft cargo compartment are routed in the same bundles as power wires. If a short circuit between a float level or fuel pump pressure switch wire and a power wire occurs, an over current can cause excessive temperatures in the float level or fuel pump pressure switch wires, resulting in damage. Adding an in-line fuse as a self-contained component in each float level and pressure switch circuit and sleeving the wires between the fuel tank and the in-line fuse will minimize the possibility of excessive temperatures in the float level or pressure switch wires. If not corrected, and there is a short circuit of the float level or pressure switch wire to a power wire, possible damage to the float level or fuel pump pressure switch wire could occur, and become a potential ignition source for the fuel tank. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements. Revision 1 is sent to change wire identifications Q 835 G22 and Q 835 H22 to Q 835 M22 and Q 835 N22 respectively in accordance with Drawing SR10280063 "D" change. **D. Description Group 1-3, 6-7:**  This service bulletin installs fuel tank float level switch in-line fuses.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 15 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 4-5:**  This service bulletin installs fuel tank float level switch and aft auxiliary tank fuel pump pressure switch in-line fuses. Revision 1 - More work is necessary on airplane changed in accordance with the original issue of this service bulletin. The more work involved is to change wire identifications Q 835 G22 and Q 835 H22 to Q 835 M22 and Q 835 N22 respectively in accordance with Drawing SR10280063 "D" change. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 516, 526, 527, 537, 616, 626, 627, 637 DC-10-10F, MD-10-10F **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 516, 526, 527, 537, 616, 626, 627, 637 DC-10-30F, MD-10-30F **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 516, 526, 527, 537, 616, 626, 627, 637 DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC10-30F (KDC-10), DC-10-40, DC-10-40F **Group 4-5:**
**Affected Maintenance Zones Zone**  **Model** 516, 526, 527, 537, 616, 626, 627, 637 DC-10-30 **Group 6:**
**Affected Maintenance Zones Zone**  **Model** 511, 521, 531, 611, 621, 631 DC-10-30F (KC-10A)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 16 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 7:** 
**Affected Maintenance Zones Zone**  **Model** 511, 521, 531, 611, 621, 631 DC-10-30F (KDC-10) **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 that the change given in this service bulletin be done within 5 years after the original issue date of this service bulletin. **F. Approval** For MD-10 Models: This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. For DC-10 Models: This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this modification 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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 17 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 1:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  10.5 21.0 2 Open Access 47.7 95.4 2 Change 4.8 9.6 2 Test 12.5 25.0 2 Close Access 75.5 151.0 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 53.0 106.0 2 Change 5.3 10.6 2 Test 12.5 25.0 2 Close Access 81.3 162.6 TOTAL FOR EACH AIRPLANE **Group 3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 31.8 63.6 2 Change 3.2 6.4 2 Test 12.5 25.0 2 Close Access 58.0 116.0 TOTAL FOR EACH AIRPLANE **Group 4: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 61.0 122.0 2 Change 6.1 12.2 2 Test 12.5 25.0 2 Close Access 90.1 180.2 TOTAL FOR EACH AIRPLANE **Group 5: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 66.0 132.0 2 Change 6.6 13.2 2 Test

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 18 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 5:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  12.5 25.0 2 Close Access 95.6 191.2 TOTAL FOR EACH AIRPLANE **Group 6: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 45.0 90.0 2 Change 4.5 9.0 2 Test 12.5 25.0 2 Close Access 72.5 145.0 TOTAL FOR EACH AIRPLANE **Group 7: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 37.0 74.0 2 Change 3.7 7.4 2 Test 12.5 25.0 2 Close Access 63.7 127.4 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Moment Change**  **(MEW) IN.-LBS Mfr's Empty Weight**  **(MEW) LBS Approximate Station**  **(Inches) Airplane**  **Group** + 8542.4 + 6.1 1400.4 1 + 9904.5 + 7.1 1395.0 2 + 5950.8 + 4.3 1383.9 3 + 10039.5 + 6.9 1455.0 4 + 11139.8 + 7.5 1485.3 5 + 7915.8 + 5.8 1364.8 6 + 6762.5 + 4.9 1380.1 7
**I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 19 of 83 **BOEING SERVICE BULLETIN DC10-28-252 J. References**  1. Existing Data: a. DC-10 Aircraft Maintenance Manual (AMM) 06-21-00, 06-27-00, 06-32-09, 06-32-11, 06-35-00, 06-36-00, 12-11-04, 12-11-05 and 28-43-01. b. MD-10 Aircraft Maintenance Manual (AMM) 06-27-00, 06-35-00, 06-36-00, 12-11-05 and 28-43-01. c. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-09, 20-00-13, 20-00-16, 20-10-01, 20-10-04, 20-20-02, 20-20-03 and 20-40-01. d. DC-10, MD-10-10 Structural Repair Manual (SRM) 51. e. Wire Diagram Manual (WDM) Chapters 28-21-01, 28-21-03, 28-22-05, 28-22-06, 28-22-07, 28-22-08, 28-41-09, 28-43-01, 28-43-02, 28-44-01, 28-44-04, 28-46-01 and 28-62-01. 2. Data supplied with this Service Bulletin: No data is supplied with this service bulletin. To obtain the data necessary to support this service bulletin submit a data request to: Data and Services Management MS D800-0019 3855 Lakewood Boulevard Long Beach, California 90846 Phone: (562) 593-6996 Fax: (562) 593-2001 E-mail: dse.boecom@boeing.com a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- D DWG Electrical Installation - In-line fuse SR10280063 3. Installation Drawings Used in the Preparation of this Service Bulletin: None 4. Process Data: Douglas Process Specifications referred to on the drawing are not given in this service bulletin since these procedures are frequently used as standard shop practices. **K. Publications Affected** 1. Publications:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 20 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Chapter-Section**  **Publication** 05-53, 28-12, 28-21, 28- 22, 28-25, 28-30, 28-43, 28-46 and 36-13 Aircraft Maintenance Manual

36-23 Fault Isolation Manual (MD-10) 28-42 Illustrated Parts Catalog 28-02, 28-41 and 36-23 DC-10 TAFI PT1 36-23 Turnaround Fault Isolation Manual (DC-10, KC-10 and KDC-10)28-00, 28-21, 28-22, 28- 41, 28-43, 28-44, 28-46 and 28-62 Wiring Diagram Manual

2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 21 of 83 **BOEING SERVICE BULLETIN DC10-28-252**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 22 of 83 **BOEING SERVICE BULLETIN DC10-28-252**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits/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 kits/parts, a supply sequence is given by Spares. More kits/parts become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
**Unit Price thru February 28, 2009**  **ROLT (Weeks)**  **QTY Name**  **Kit Number** $3,139.00 17 1 Service Kit SB10280252-3 3,589.00 17 1 Service Kit SB10280252-5 3,394.00 17 1 Service Kit SB10280252-7 5,378.00 17 1 Service Kit SB10280252-9 5,598.00 17 1 Service Kit SB10280252-11 5,398.00 17 1 Service Kit SB10280252-13 4,505.00 17 1 Service Kit SB10280252-15
**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. **Group 1: Kit SB10280252**  **Notes Name**  **QTY New Part Number** **-3** (a) SCREW 3 3D0005-08-10 (a) SCREW 34 3D0005-08-8

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 23 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 1:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -3**  (a) SCREW 4 3D0005-3-22 (a) SCREW 6 3D0005-3-26 (a) SCREW 1 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 12 5D0086-3 (a) TERMINAL LUG 762 3 5D0086-6 (a) SEALING PLUG 36 5D0206-20 IN-LINE FUSE 18 65053-220 BRACKET 1 ANN0012-1 SOCKET T/C 524 3 M39029/22-192 COVER ASSY 1 MS18029-6S8 RIVET 4 MS20470AD5-5D NUT 67 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 TERMINAL BOARD 1 MS27212-6-8 LOCKWASHER 33 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 40 NAS1252-10L WASHER 3 NAS1252-8H WASHER 104 NAS1252-8L SPACER 4 NAS43DD3-48FC SPACER 6 NAS43DD3-64FC SPACER 1 NAS43DD3-72FC WASHER 3 NAS620A4 BOLT 3 NAS7700-3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 24 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 1:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -3**  (a) CLAMP 1 S7934111-2SA (a) CLAMP 19 S7934111-3SA (a) CLAMP 1 S7934111-4SA (a) CLAMP 2 S7934111-5SA (a) CLAMP 1 S7934111-6SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 18 S7934111-9SA WIRE KIT 1 SR10280063-102 WIRE KIT 1 SR10280063-103 SLEEVING 165 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent TIE TAPE 50 YDS SR10280063-7 (DMS 2089) or equivalent BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 1: Wire Kit SR10280063**  **Notes Name**  **QTY QTY**  **New Part Number -103**  **-102** WIRE CODE 801 60 FT 107 FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 13 20 M39029/22-192 (a) TERMINAL LUG 878 11 13 5D0086-3 (a) TERMINAL LUG 762 2 7 5D0086-6 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 2: Kit SB10280252**  **Notes Name**  **QTY New Part Number** **-5** (a) SCREW 7 3D0005-08-10

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 25 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 2:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -5**  (a) SCREW 37 3D0005-08-8 (a) SCREW 5 3D0005-3-22 (a) SCREW 6 3D0005-3-26 (a) SCREW 2 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 13 5D0086-3 (a) TERMINAL LUG 762 4 5D0086-6 (a) SEALING PLUG 40 5D0206-20 IN-LINE FUSE 20 65053-220 BRACKET 1 ANN0012-1 SOCKET T/C 524 3 M39029/22-192 COVER ASSY 1 MS18029-6S8 RIVET 4 MS20470AD5-5D NUT 74 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 TERMINAL BOARD 1 MS27212-6-8 LOCKWASHER 37 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 46 NAS1252-10L WASHER 7 NAS1252-8H WASHER 118 NAS1252-8L SPACER 5 NAS43DD3-48FC SPACER 6 NAS43DD3-64FC SPACER 2 NAS43DD3-72FC WASHER 3 NAS620A4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 26 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 2:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -5**  BOLT 3 NAS7700-3 (a) CLAMP 1 S7934111-2SA (a) CLAMP 22 S7934111-3SA (a) CLAMP 5 S7934111-4SA (a) CLAMP 3 S7934111-5SA (a) CLAMP 1 S7934111-6SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 1 S7934111-8SA (a) CLAMP 20 S7934111-9SA WIRE KIT 1 SR10280063-101 WIRE KIT 1 SR10280063-102 WIRE KIT 1 SR10280063-103 SLEEVING 191 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent TIE TAPE 50 YDS SR10280063-7 (DMS 2089) or equivalent BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071.

**Group 2: Wire Kit SR10280063**  **Notes Name**  **QTY QTY**  **QTY New Part Number**  **-103 -102**  **-101** WIRE CODE 801 60 FT 107 FT 26 FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 13 20 4 M39029/22-192 (a) TERMINAL LUG 878 11 13

- 5D0086-3 (a) TERMINAL LUG 762 2 7 4 5D0086-6 (a) Or approved equivalent, refer to AEPL, Drawing 7595071.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 27 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 3:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -7**  (a) SCREW 3 3D0005-08-10 (a) SCREW 22 3D0005-08-8 (a) SCREW 5 3D0005-3-26 (a) SCREW 1 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 9 5D0086-3 (a) SEALING PLUG 24 5D0206-20 IN-LINE FUSE 12 65053-220 SOCKET T/C 524 3 M39029/22-192 NUT 43 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 LOCKWASHER 27 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 24 NAS1252-10L WASHER 3 NAS1252-8H WASHER 47 NAS1252-8L SPACER 5 NAS43DD3-64FC SPACER 1 NAS43DD3-72FC (a) CLAMP 12 S7934111-3SA (a) CLAMP 12 S7934111-9SA WIRE KIT 1 SR10280063-111 WIRE KIT 1 SR10280063-113 SLEEVING 125 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent TIE TAPE 50 YDS SR10280063-7 (DMS 2089) or equivalent

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 28 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 3:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -7**  BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 3: Wire Kit SR10280063**  **Notes Name**  **QTY QTY**  **New Part Number -113**  **-111** WIRE CODE 801 48 FT 69 FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 9 12 M39029/22-192 (a) TERMINAL LUG 878 9 12 5D0086-3 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 4: Kit SB10280252**  **Notes Name**  **QTY New Part Number**  **-9** (a) SCREW 14 3D0005-08-10 (a) SCREW 27 3D0005-08-8 (a) SCREW 4 3D0005-3-22 (a) SCREW 5 3D0005-3-26 (a) SCREW 2 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 9 5D0086-3 (a) SEALING PLUG 46 5D0206-20 IN-LINE FUSE 23 65053-220 (a) BRACKET 2 9D0062-3-12-08 (a) BRACKET 3 9D0230-1D080624 SOCKET T/C 524 14 M39029/22-192 RIVET 10 MS20470AD4-5D NUT 60 MS21042L08 NUT 2 MS21042L3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 29 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 4:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -9**  CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 LOCKWASHER 27 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 40 NAS1252-10L WASHER 8 NAS1252-8H WASHER 101 NAS1252-8L SPACER 4 NAS43DD3-48FC SPACER 5 NAS43DD3-64FC SPACER 2 NAS43DD3-72FC (a) CLAMP 2 S7934111-10SA (a) CLAMP 2 S7934111-11SA (a) CLAMP 11 S7934111-3SA (a) CLAMP 3 S7934111-4SA (a) CLAMP 3 S7934111-7SA (a) CLAMP 3 S7934111-8SA (a) CLAMP 25 S7934111-9SA WIRE KIT 1 SR10280063-105 WIRE KIT 1 SR10280063-107 WIRE KIT 1 SR10280063-112 WIRE KIT 1 SR10280063-113 SLEEVING 170 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent SLEEVING 15 FT X .187 I.D. SR10280063-5 (DMS 2379, Type 4, Class 4) or equivalent TIE TAPE 50 YDS SR10280063-7 (DMS 2089) or equivalent BRACKET 2 TA4012F21

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 30 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 4:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -9**  (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 4: Wire Kit SR10280063**  **Notes Name**  **QTY QTY**  **QTY QTY**  **New Part Number -113**  **-112 -107**  **-105** WIRE CODE 801

- - 14 FT

- DC2426-1C-20NM(DMS 2426) or equivalent WIRE CODE 801 48 FT 74 FT 21 FT 43 FT DC2426-1C-22NM(DMS 2426) or equivalent SOCKET T/C 524 9 13 5 5 M39029/22-192 (a) PIN T/C 601/701

- - 5
- S00023-20P (a) TERMINAL LUG 878 9 13

- 5 5D0086-3 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 5: Kit SB10280252**  **Notes Name**  **QTY New Part Number**  **-11** (a) SCREW 16 3D0005-08-10 (a) SCREW 27 3D0005-08-8 (a) SCREW 4 3D0005-3-22 (a) SCREW 5 3D0005-3-26 (a) SCREW 2 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 9 5D0086-3 (a) SEALING PLUG 50 5D0206-20 IN-LINE FUSE 25 65053-220 (a) BRACKET 2 9D0062-3-12-08 (a) BRACKET 4 9D0230-1D080624 SOCKET T/C 524 16 M39029/22-192

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 31 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 5:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -11**  RIVET 12 MS20470AD4-5D NUT 62 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 LOCKWASHER 27 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 40 NAS1252-10L WASHER 8 NAS1252-8H WASHER 105 NAS1252-8L SPACER 4 NAS43DD3-48FC SPACER 5 NAS43DD3-64FC SPACER 2 NAS43DD3-72FC (a) CLAMP 2 S7934111-10SA (a) CLAMP 3 S7934111-12SA (a) CLAMP 11 S7934111-3SA (a) CLAMP 3 S7934111-4SA (a) CLAMP 3 S7934111-7SA (a) CLAMP 3 S7934111-8SA (a) CLAMP 27 S7934111-9SA WIRE KIT 1 SR10280063-105 WIRE KIT 1 SR10280063-108 WIRE KIT 1 SR10280063-112 WIRE KIT 1 SR10280063-113 SLEEVING 182 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent SLEEVING 20 FT X .187 I.D. SR10280063-5 (DMS 2379, Type 4 Class 4) or equivalent

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 32 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 5:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -11**  TIE TAPE 50 YDS SR10280063-7 (DMS 2089) or equivalent BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 5: Wire Kit SR10280063**  **Notes Name**  **QTY QTY**  **QTY QTY**  **New Part Number -113**  **-112 -108**  **-105** WIRE CODE 801

- - 14 FT

- DC2426-1C-20NM(DMS 2426) or equivalent WIRE CODE 801 48 FT 74 FT 35 FT 43 FT DC2426-1C-22NM(DMS 2426) or equivalent SOCKET T/C 524 9 13 7 5 M39029/22-192 (a) PIN T/C 601/701

- - 7
- S00023-20P (a) TERMINAL LUG 878 9 13

- 5 5D0086-3 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 6: Kit SB10280252**  **Notes Name**  **QTY New Part Number**  **-13** (a) SCREW 8 3D0005-08-10 (a) SCREW 4 3D0005-08-12 (a) SCREW 30 3D0005-08-8 (a) SCREW 1 3D0005-3-22 (a) SCREW 6 3D0005-3-26 (a) SCREW 1 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 13 5D0086-3 (a) SEALING PLUG 34 5D0206-20 IN-LINE FUSE 17 65053-220

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 33 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 6:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -13**  (a) BRACKET 2 9D0062-3F08-10 SOCKET T/C 524 4 M39029/22-192 RIVET 4 MS20470AD4-5D NUT 69 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 LOCKWASHER 30 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 30 NAS1252-10L WASHER 3 NAS1252-8H WASHER 115 NAS1252-8L SPACER 1 NAS43DD3-48FC SPACER 6 NAS43DD3-64FC SPACER 1 NAS43DD3-72FC (a) CLAMP 5 NMC1001-1 (a) CLAMP 3 NMC1001-2 (a) CLAMP 15 S7934111-3SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 17 S7934111-9SA WIRE KIT 1 SR10280063-104 WIRE KIT 1 SR10280063-106 WIRE KIT 1 SR10280063-109 WIRE KIT 1 SR10280063-110 WIRE KIT 1 SR10280063-111 WIRE KIT 1 SR10280063-113 SLEEVING 160 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 34 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 6:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -13**  SLEEVING 10 FT X .187 I.D. SR10280063-5 (DMS 2379, Type 4, Class 4) or equivalent TIE TAPE 50 YDS SR10280063-7(DMS 2089) or equivalent BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 6: Wire Kit SR10280063**  **Notes Name**  **QTY QTY**  **QTY QTY**  **QTY QTY**  **New Part Number -113**  **-111 -110**  **-109 -106**  **-104** WIRE CODE 801 48 FT 69 FT 14 FT 14 FT 28 FT 7 FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 9 12 2 2 4 1 M39029/22-192 (a) TERMINAL LUG 878 9 12 2 2 4 1 5D0086-3 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 7: Kit SB10280252**  **Notes Name**  **QTY New Part Number**  **-15** (a) SCREW 3 3D0005-08-10 (a) SCREW 29 3D0005-08-8 (a) SCREW 1 3D0005-3-22 (a) SCREW 6 3D0005-3-26 (a) SCREW 1 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 10 5D0086-3 (a) SEALING PLUG 28 5D0206-20 IN-LINE FUSE 14 65053-220 SOCKET T/C 524 4 M39029/22-192 NUT 53 MS21042L08

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 35 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 7:**  **Kit SB10280252 Notes**  **Name QTY**  **New Part Number -15**  NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 LOCKWASHER 24 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 30 NAS1252-10L WASHER 3 NAS1252-8H WASHER 85 NAS1252-8L SPACER 1 NAS43DD3-48FC SPACER 6 NAS43DD3-64FC SPACER 1 NAS43DD3-72FC (a) CLAMP 15 S7934111-3SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 14 S7934111-9SA WIRE KIT 1 SR10280063-104 WIRE KIT 1 SR10280063-110 WIRE KIT 1 SR10280063-111 WIRE KIT 1 SR10280063-113 SLEEVING 140 FT X .166 I.D. SR10280063-3 (DMS 2109, Type 1) or equivalent TIE TAPE 50 YDS SR10280063-7 (DMS 2089) or equivalent BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 36 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 7:**  **Wire Kit SR10280063 Notes**  **Name QTY**  **QTY QTY**  **QTY New Part Number**  **-113 -111**  **-110 -104**  WIRE CODE 801 48 FT 69 FT 14 FT 7 FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 9 12 2 1 M39029/22-192 (a) TERMINAL LUG 878 9 12 2 1 5D0086-3 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. 2. Parts and Materials Supplied by the Operator: None. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 37 of 83 **BOEING SERVICE BULLETIN DC10-28-252**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 38 of 83 **BOEING SERVICE BULLETIN DC10-28-252**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **WARNING:**IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. **WARNING:**WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS CAN OCCUR. **CAUTION:**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 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. Equivalent parts are listed in the AEPL, Drawing 7595071. 4. Use the approved fastener and process material substitutions, DC-10, MD-10 SRM 51. 5. Any protrusion of threads is acceptable provided that the threads do not rub or ride against nearby wire assemblies or components. 6. 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. 7. Refer to the following Standard Wiring Practices Manual (SWPM) chapters for applicable operation: Operation Chapter General - Maintenance Safety Practices SWPM 20-00-00Electrical Identification and Shop Practices SWPM 20-00-09

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 39 of 83 **BOEING SERVICE BULLETIN DC10-28-252**Electrical Wire Codes SWPM 20-00-13Electrical Wire End Termination Codes SWPM 20-00-16Fabricating and Installing Wire Harness - Commercial SWPM 20-10-01
Coil and Stow - Maintenance Practices SWPM 20-10-04Terminal Blocks - Maintenance Practices SWPM 20-20-02General Installation Hardwares - Maintenance Practices SWPM 20-20-03

Power Distribution Bus - Maintenance Practice SWPM 20-40-01

8. Obey all of the warnings and cautions given in the specified manual sections as applicable. 9. Review and understand all general notes of Service Rework Drawing SR10280063 sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 3.10, and 7 before start of modification. 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. **B. WORK INSTRUCTIONS Group 1:**  1. Make fuel system safe for maintenance. Refer to MD-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** MD-10 AMM 06-35-00 Access Panel Left Wing Leading Edge and Vent Box 516AB, 516EB, 526DB, 527AB, 537AB
MD-10 AMM 06-36-00 Access Panel Right Wing Leading Edge and Vent Box 616AB, 616EB, 626DB, 627AB, 637AB

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix Location**  A Fuel Tank 1 C Fuel Tank 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 40 of 83 **BOEING SERVICE BULLETIN DC10-28-252 In Accordance with Appendix**  **Location** F Fuel Tank 3 4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix N. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 2:** 1. Make fuel system safe for maintenance. Refer to MD-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** MD-10 AMM 06-35-00 Access Panel Left Wing Leading Edge and Vent Box 516AB, 516EB, 526DB, 527AB, 537AB
MD-10 AMM 06-36-00 Access Panel Right Wing Leading Edge and Vent Box 616AB, 616EB, 626DB, 627AB, 637AB
MD-10 AMM 06-27-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix Location**  A Fuel Tank 1 C Fuel Tank 2 F Fuel Tank 3 H Upper and Lower Auxiliary Fuel Tanks 4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix O. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 3:** 1. Make fuel system safe for maintenance. Refer to DC-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 41 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Refer to**  **Name/Location Panel Number**  DC-10 AMM 06-35-00 Access Panel Left Wing Leading Edge and Vent Box 516AB, 516EB, 526DB, 527AB, 537AB
DC-10 AMM 06-36-00 Access Panel Right Wing Leading Edge and Vent Box 616AB, 616EB, 626DB, 627AB, 637AB

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix Location**  B Fuel Tank 1 D Fuel Tank 2 G Fuel Tank 3 4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix P. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 4:** 1. Make fuel system safe for maintenance. Refer to DC-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** DC-10 AMM 06-35-00 Access Panel Left Wing Leading Edge and Vent Box 516AB, 516EB, 526DB, 527AB, 537AB
DC-10 AMM 06-36-00 Access Panel Right Wing Leading Edge and Vent Box 616AB, 616EB, 626DB, 627AB, 637AB
DC-10 AMM 06-27-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door
DC-10 AMM 06-21-00 Center Cargo Com- partment Center Cargo Compartment Door

3. Install fuel tank float level and pressure switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix**

**Location** B Fuel Tank 1

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 42 of 83 **BOEING SERVICE BULLETIN DC10-28-252 In Accordance with Appendix**  **Location** E Fuel Tank 2 G Fuel Tank 3 K Aft Auxiliary Fuel Tank L Upper and Lower Auxiliary Fuel Tanks 4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix Q. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 5:** 1. Make fuel system safe for maintenance. Refer to DC-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** DC-10 AMM 06-35-00 Access Panel Left Wing Leading Edge and Vent Box 516AB, 516EB, 526DB, 527AB, 537AB
DC-10 AMM 06-36-00 Access Panel Right Wing Leading Edge and Vent Box 616AB, 616EB, 626DB, 627AB, 637AB
DC-10 AMM 06-27-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door
DC-10 AMM 06-21-00 Center Cargo Com- partment Center Cargo Compartment Door

3. Install fuel tank float level and pressure switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix Location**  B Fuel Tank 1 E Fuel Tank 2 G Fuel Tank 3 L Upper and Lower Auxiliary Fuel TanksM Aft Auxiliary Fuel Tank

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 43 of 83 **BOEING SERVICE BULLETIN DC10-28-252**4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix R. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 6:** 1. Make fuel system safe for maintenance. Refer to DC-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** DC-10 AMM 06-35-00 Access Panels Left Wing Leading Edge and Vent Box 510KB, 510PB, 520KB, 520RB, 530JB
DC-10 AMM 06-36-00 Access Panels Right Wing Leading Edge and Vent Box 610KB, 610PB, 620KB, 620RB, 630JB
DC-10 AMM 06-27-00 Left and Right Main Land- ing Gear Wheel Wells Left and Right Main Landing Gear Doors DC-10 AMM 06-32-09 Mid Passenger Compart- ment Floor panel, and Float Switch Cover AZZ7656-1, AAL7173-1

DC-10 AMM 06-32-11 Aft Auxiliary fuel tank pan- els, Float Switch Coverand Aft Passenger Compartment Floor panel (ARO Hatch), AWE9267-503, AWE9270- 517, AAL7173-1 and 291HF,

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix Location**  B Fuel Tank 1 D Fuel Tank 2 G Fuel Tank 3 I Center Wing Fuel Tanks J Forward and Aft Auxiliary Fuel Tank 4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix S. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 44 of 83 **BOEING SERVICE BULLETIN DC10-28-252 Group 7:**  1. Make fuel system safe for maintenance. Refer to DC-10 AMM 28-43-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** DC-10 AMM 06-35-00 Access Panels Left Wing Leading Edge and Vent Box 510KB, 510PB, 520KB, 520RB, 530JB
DC-10 AMM 06-36-00 Access Panels Right Wing Leading Edge and Vent Box 610KB, 610PB, 620KB, 620RB, 630JB
DC-10 AMM 06-27-00 Left and Right Main Landing Gear Wheel Wells Left and Right Main Landing Gear Doors

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In Accordance with Appendix Location**  B Fuel Tank 1 D Fuel Tank 2 G Fuel Tank 3 I Center Wing Fuel Tanks 4. Do return-to-service test of fuel tank float level or pressure switches in accordance with Appendix T. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1: January 06, 2010 45 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 1-2.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 11, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.14, 102.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-119 within float level switch reference designator S1-119 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.14, 102.201, 302.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-120 within float level switch reference designator S1-120 wiring. 2

Install fuel tank float level switch In-line fuse, reference designator F1-121 within float level switch reference designator S1-121 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.15, 102.201, 302.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-176 within float level switch reference designator S1-176 wiring. 4

In accordance with Drawing SR10280063 sheets 10, 14, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.15, 102.201 and 302.201. Install fuel tank float level switch In-line fuse, reference designator F1-1391within float level switch reference designator S1-1391 wiring. 5

In accordance with Drawing SR10280063 sheets 10, 13, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.15, 102.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1392within float level switch reference designator S1-1392 wiring. 6

In accordance with Drawing SR10280063 sheets 10, 12, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.16, 102.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-735 within float level switch reference designator S1-735 wiring. 7

**Appendix A: FUEL TANK 1 - MD-10-10F AND MD-10-30F (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 46 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 3-7.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 11, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.21, 111.201 or 112.201 and 310.201, 311.203 312.202 or 313.202. Install fuel tank float level switch In-line fuse, reference designator F1-119 within float level switch reference designator S1-119 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.21, 111.201 or 112.201 and 307.201, 310.201, 311.202, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-120 within float level switch reference designator S1-120 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.21, 111.201 or 112.201 and 310.201, 311.202, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-121 within float level switch reference designator S1-121 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.22, 111.201 or 112.201 and 307.201, 310.201, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-176 within float level switch reference designator S1-176 wiring. 4

In accordance with Drawing SR10280063 sheets 10, 12, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.22, 111.201 or 112.201 and 310.201 or 311.203 or 312.202 or 313.202. Install fuel tank float level switch In-line fuse, reference designator F1-735 within float level switch reference designator S1-735 wiring. 5

**Appendix B: FUEL TANK 1 - DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30 W/AFT TANK 1500 AND 3200 GALLONS, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F (KDC-10), DC-10-40, DC-10-40F**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 47 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 1-2.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 16, 16.5, 3, 3.1, 3.3, 3.5, 3.6, and 3.9. Install new Terminal Board, item number S3-454. 1 In accordance with Drawing SR10280063 sheets 10, 16, 16.3, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.16, 102.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-90 within float level switch reference designator S1- 90 wiring. 2

Install fuel tank float level switch In-line fuse, reference designator F1-177 within float level switch reference designator S1- 177 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 16, 16.3, 16.4, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.17, 102.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1363 within float level switch reference designator S1- 1363 wiring. 4

Install fuel tank float level switch In-line fuse, reference designator F1-1393 within float level switch reference designator S1- 1393 wiring. 5

**Appendix C: FUEL TANK 2 - MD-10-10F AND MD-10-30F (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 48 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 3, 6-7.** 

**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.22, 111.201 and 310.201 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-90 within float level switch reference designator S1- 90 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 16, 16.1, 3, 3.1, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.23, 111.201 and 310.201 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-177 within float level switch reference designator S1- 177 wiring. 2

**Appendix D: FUEL TANK 2 - 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**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 49 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 4-5.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 16, 16.2, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.22, 112.201 and 311.201 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-90 within float level switch reference designator S1- 90 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 16, 16.2, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.23, 112.201 and 311.202 or 312.202. Install fuel tank float level switch In-line fuse, reference designator F1-177 within float level switch reference designator S1- 177 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 16, 16.2, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.23, 112.201 and 311.201 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1363 within float level switch reference designator S1- 1363 wiring. 3

**Appendix E: FUEL TANK 2 - DC-10-30 W/AFT TANK 1500 AND 3200 GALLONS (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 50 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 1-2.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 17, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.17, 103.201 and 304.202. Install fuel tank float level switch In-line fuse, reference designator F1-124 within level switch reference designator S1-124 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.18, 103.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-122within float level switch reference designator S1-122 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.18, 103.201, 303.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-123within float level switch reference designator S1-123 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.18, 103.201 and 303.201 or 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-178within float level switch reference designator S1-178 wiring. 4

In accordance with Drawing SR10280063 sheets 10, 20, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.19, 103.201 and 303.201. Install fuel tank float level switch In-line fuse, reference designator F1-1394within float level switch reference designator S1-1394 wiring. 5

In accordance with Drawing SR10280063 sheets 10, 19, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.19, 103.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1395within float level switch reference designator S1-1395 wiring. 6

In accordance with Drawing SR10280063 sheets 10, 18, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.19, 103.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-734within float level switch reference designator S1-734 wiring. 7

**Appendix F: FUEL TANK 3 - MD-10-10F AND MD-10-30F (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 51 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 3-7.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 17, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.23, 113.201 and 310.202, 311.203, 312.203 or 313.202. Install fuel tank float level switch In-line fuse, reference designator F1-124 within level switch reference designator S1-124 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.24, 113.201 and 310.201, 311.202, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-122within float level switch reference designator S1-122 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.24, 113.201 and 308.201, 310.201, 311.202, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-123within float level switch reference designator S1-123 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.24, 113.201 and 308.201, 310.201, 311.202, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-178within float level switch reference designator S1-178 wiring. 4

In accordance with Drawing SR10280063 sheets 10, 18, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.25, 113.201 and 310.201, 311.202, 312.202 or 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-734within float level switch reference designator S1-734 wiring. 5

**Appendix G: FUEL TANK 3 - DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30 W/AFT TANK 1500 AND 3200 GALLONS, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F (KDC-10), DC-10-40, DC-10-40F**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 52 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 2.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 22, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.20, 101.201 and 301.201. Install fuel tank float level switch In-line fuse, reference designator F1-1359 within float level switch reference designator S1- 1359 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 23.1, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 3.10, 7, 9.13, 9.20, 101.201 and 301.201. Install fuel tank float level switch In-line fuse, reference designator F1-1360 within float level switch reference designator S1- 1360 wiring. 2

**Appendix H: UPPER AND LOWER AUXILIARY FUEL TANKS - MD-10-30F (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 53 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 6-7.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 24, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.30, 104.201 and 313.201 Install fuel tank float level switch In-line fuse, reference designator F1-1328 within float level switch reference designator S1- 1328 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 24.1, 3, 3.1, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.30, 110.201 and 313.201. Install fuel tank float level switch In-line fuse, reference designator F1-1374 within float level switch reference designator S1- 1374 wiring. 2

**Appendix I: CENTER WING TANKS - DC-10-30F (KC-10A) AND DC-10-30F (KDC-10) (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 54 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 6.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 25, 25.1, 25.2, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.31, 106.201 and 306.201. Install fuel tank float level switch In-line fuse, reference designator F1-1277 within level switch reference designator S1-1277 wiring. 1

Install fuel tank float level switch In-line fuse, reference designator F1-1293within float level switch reference designator S1-1293 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 26, 26.1, 26.2, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.31, 109.201 and 309.201. Install fuel tank float level switch In-line fuse, reference designator F1-1327within float level switch reference designator S1-1327 wiring. 3

**Appendix J: FORWARD AND AFT AUXILIARY - DC-10-30F (KC-10A) (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 55 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 4.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 27, 27.1, 27.3, 27.4, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.27, 107.201 and 312.202. Install fuel tank pressure switch In-line fuse, reference designator F1-972within pressure switch reference designator S1-972 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 27, 27.1, 27.3, 27.4, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.27, 107.201 and 312.201. Install fuel tank pressure switch In-line fuse, reference designator F1-973within pressure switch reference designator S1-973 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 27, 27.1, 27.4, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.27, 107.201 and 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1361within float level switch reference designator S1-1361 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 27, 27.1, 27.4, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.28, 107.201 and 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1362Awithin float level switch reference designator S1-1362 wiring. 4

Install fuel tank float level switch In-line fuse, reference designator F1-1362Bwithin float level switch reference designator S1-1362 wiring. 5

**Appendix K: AFT AUXILIARY FUEL TANK - DC-10-30 W/AFT TANK 1500 GALLONS (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 56 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 4-5.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 22.1, 22.2, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.26, 105.201 and 311.201 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1358 within float level switch reference designator S1- 1358 wiring. 1

In accordance with Drawing SR10280063 sheets 10, 22.1, 22.2, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.26, 105.201 and 311.202 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1364 within float level switch reference designator S1- 1364 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 22.1, 22.2, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.26, 105.201 and 311.201 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1376 within float level switch reference designator S1- 1376 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 22.1, 22.2, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.25, 105.201 and 311.201 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1359 within float level switch reference designator S1- 1359 wiring. 4

In accordance with Drawing SR10280063 sheets 10, 23, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.25, 105.201 and 311.201 or 312.201. Install fuel tank float level switch In-line fuse, reference designator F1-1360 within float level switch reference designator S1- 1360 wiring. 5

**Appendix L: UPPER AND LOWER AUXILIARY TANKS - DC-10-30 W/AFT 1500 AND 3200 GALLONS (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 57 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 5.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR10280063 sheets 10, 27, 27.2, 27.3, 27.4, 3, 3.1, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.27, 108.201 and 311.202. Install fuel tank pressure switch In-line fuse, reference designator F1-972 within pressure switch reference designator S1- 972 wiring. 1

Install fuel tank pressure switch In-line fuse, reference designator F1-973 within pressure switch reference designator S1- 973 wiring. 2

In accordance with Drawing SR10280063 sheets 10, 27, 27.2, 27.3, 27.4, 3, 3.1, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.27, 108.201 and 311.201. Install fuel tank float level switch In-line fuse, reference designator F1-1361 within float level switch reference designator S1- 1361 wiring. 3

In accordance with Drawing SR10280063 sheets 10, 27, 27.2, 27.3, 27.4, 3, 3.1, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 7, 9.13, 9.29, 108.201 and 311.201. Install fuel tank float level switch In-line fuse, reference designator F1-1362 within float level switch reference designator S1- 1362 wiring. 4

Install fuel tank float level switch In-line fuse, reference designator F1-1365 within float level switch reference designator S1- 1365 wiring. 5

Install fuel tank float level switch In-line fuse, reference designator F1-1381Awithin float level switch reference designator S1-1381 wiring. 6

Install fuel tank float level switch In-line fuse, reference designator F1-1381Bwithin float level switch reference designator S1-1381 wiring. 7

**Appendix M: AFT AUXILIARY FUEL TANK - DC-10-30 W/AFT 3200 GALLONS (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 58 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 1.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each fuse as it is installed. REFERENCES (AMM) Tasks: PAGE BLOCK MD-10 AMM 12-11-05 (12-11-05/301 - DEFUELING SERVICING) This procedure should be used as necessary. Depower the Fuse system or open the associated Circuit Breakers. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 6 & 2 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-1301 LOOP CONTINUITY F1-1391 TK 1 INBD FULL 1 & 2 S3-1300 LOOP CONTINUITY F1-1392 TK 1 OUTBD FULL 1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP 1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL (VENT BOX) TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-1302 LOOP CONTINUITY F1-1394 TK 3 INBD FULL 1 & 2 S3-1303 LOOP CONTINUITY F1-1395 TK 3 OUTBD FULL 1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP 1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL (VENT BOX) TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP 2 & 6 S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB 3 & GND S3-454 EMPTY CONT TO GND F1-1363 TK 2 10000 LB 7 & 4 S3-454 LOOP CONTINUITY F1-1393 TK 2 FULL

**Appendix N: MD-10-10F - FUSE FUNCTIONAL TEST (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 59 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 2.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each fuse as it is installed. REFERENCES (AMM) Tasks: PAGE BLOCK MD-10 AMM 12-11-05 (12-11-05/301 - DEFUELING SERVICING) This procedure should be used as necessary. Depower the Fuse system or open the associated Circuit Breakers. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 6 & 2 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-1301 LOOP CONTINUITY F1-1391 TK 1 INBD FULL 1 & 2 S3-1300 LOOP CONTINUITY F1-1392 TK 1 OUTBD FULL 1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP Vent Box 1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-1302 LOOP CONTINUITY F1-1394 TK 3 INBD FULL 1 & 2 S3-1303 LOOP CONTINUITY F1-1395 TK 3 OUTBD FULL 1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP Vent Box 1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP 2 & 6 S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB 3 S3-454 EMPTY CONT TO GND F1-1363 TK 2 10000 LB 7 & 4 S3-454 LOOP CONTINUITY F1-1393 TK 2 FULL AUX TANKS

**Appendix O: MD-10-30F - FUSE FUNCTIONAL TEST (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 60 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  1 & 2 S3-1186 LOOP CONTINUITY F1-1359 UPR AUX FULL 4 & 5 S3-805 LOOP CONTINUITY F1-1360 LWR AUX FULL

**Appendix O: MD-10-30F - FUSE FUNCTIONAL TEST (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 61 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 3.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each fuse as it is installed. REFERENCES (AMM) Tasks: PAGE BLOCK DC-10 AMM 12-11-05 (12-11-05/301 - DEFUELING SERVICING) This procedure should be used as necessary. Depower the Fuse system or open the associated Circuit Breakers. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 6 & 2 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP
1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL (VENT BOX) TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP
1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL (VENT BOX) TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP Optional 1 S3-454 Pin 2 & Fuse Pin C S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB OPTIONAL 1 - If the tank 2 is open this float switch circuit can be checked by moving the float of the float switch up and down and reading the circuit open/ground at S3-454 pin 2.

**Appendix P: DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-40 AND DC-10-40F - FUSE FUNCTIONAL TEST** 

**(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 62 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 4.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES I** This test should be performed in the order shown below. REFERENCES (AMM) Tasks: DC-10 AMM 12-11-04, PRESSURE REFUELING - SERVICING AUTOMATIC PRESSURE REFUELING DC-10 AMM 12-11-05, DEFUELING - SERVICING NOTES: Sufficient fuel should be in the Tank 2 and Upper Aux Tank to do the AFT tank test (see specifics in each test procedure) aWhen fueling the aircraft if any Aux Tanks are to receive fuel, schedule at least 6000 pounds (2722 Kilograms) in the UPPER Aux tank to prevent conflicts between what fuel has been loaded and the quantity indication. b

To read fuel quantity in any individual Aux tanks use the appropriate "AUX TANK QTY SEL" switch on the flight engineer (FE) panel. c

WARNING: This test moves fuel to and from AFT Aux tank. This procedure assumes that the aircraft is empty of cargo and passengers while the test is being conducted. Fuel is placed in main and UPR Aux tanks to counterbalance the fuel in the AFT Aux tank. Following the filling and emptying sequence provided in this procedure will avoid aircraft tip over. The following C/Bs should be closed for the functional test:LOCATION C/B NO. BUS BATT BUS OVERHEAD B1-474 FUEL TANK FILL VLV & BATT BUS SENS- ING OVERHEAD B1-723 APU START PUMP OVERHEAD B1-724 APU ADVISORY LTS OVERHEAD B1-728 APU CONTROL & FUEL VLV BATT DIRECT OVERHEAD B1-475 GROUND REFUEL PWR OVERHEAD B1-479 GND REFUEL INV PWR & HI LEVEL TEST 115 VAC - 1 UPPER MAIN B1-499 FUEL QTY TRANSFER RELAY UPPER MAIN B1-589 FUEL QTY NORMAL PWR

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 1 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 63 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** LOCATION C/B NO. BUS 115 VAC - 1 (CONT.) UPPER MAIN B1-609 FUEL PUMP CONTROL TANK 2 FWD UPPER MAIN B1-615 FUEL PUMP CONTROL TANK 1 FWD UPPER MAIN B1-619 FUEL PUMP CONTROL TANK 2 TRANS UPPER MAIN B1-1206 UPR & LWR AUX TANK R UPR UPPER MAIN B1-1645 FUEL PUMP CONTROL L AFT AUX TANK 115 VAC - 2 UPPER MAIN B1-603 FUEL PUMP CONTROL TANK 2 R AFT UPPER MAIN B1-611 FUEL PUMP CONTROL TANK 1 TRANSF UPPER MAIN B1-621 FUEL PUMP CONTROL TANK 3 AFT UPPER MAIN B1-769 FUEL QTY ALT PWR UPPER MAIN B1-1207 UPR & LWR AUX TANK L UPR UPPER MAIN B1-1209 AUX TANK L LWR 115 VAC - 3 UPPER MAIN B1-590 FUEL QTY RPTRS & XFER UPPER MAIN B1-613 FUEL PUMP CONTROL TANK 1 AFT UPPER MAIN B1-617 FUEL PUMP CONTROL TANK 3 FWD UPPER MAIN B1-757 FUEL PUMP CONTROL TANK 2 TRANS UPPER MAIN B1-1208 AUX TANK R LWR UPPER MAIN B1-1644 FUEL PUMP CONTROL R AFT AUX TANK 115 VAC GEN-1 UPPER MAIN B1-608 FUEL PUMP POWER TANK 2 FWD UPPER MAIN B1-614 FUEL PUMP POWER TANK 1 FWD UPPER MAIN B1-618 FUEL PUMP POWER TANK 3 TRANS UPPER MAIN B1-1250 FUEL PUMP PWR R UPR UPPER MAIN B1-1647 FUEL PUMP PWR L AFT 115 VAC GEN-2 UPPER MAIN B1-596 FUEL PUMP POWER TANK 2 R AFT UPPER MAIN B1-610 FUEL PUMP POWER TANK 1 TRANS

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 2 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 64 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** UPPER MAIN B1-620 FUEL PUMP POWER TANK 3 AFT UPPER MAIN B1-1248 FUEL PUMP PWR L UPR UPPER MAIN B1-1249 FUEL PUMP PWR L LWR
LOCATION C/B NO. BUS 115 VAC GEN-3 UPPER MAIN B1-612 FUEL PUMP POWER TANK 1 AFT UPPER MAIN B1-616 FUEL PUMP POWER TANK 3 FWD UPPER MAIN B1-756 FUEL PUMP POWER TANK 2 TRANS UPPER MAIN B1-1251 FUEL PUMP PWR R LWR UPPER MAIN B1-1646 FUEL PUMP PWR R AFT 115 VAC R EMERGENCY OVERHEAD B1-680 FUEL PUMP TANK 2 LEFT AFT 28 VDC-1 UPPER MAIN B1-450 FUEL X-FEED CONT 1 UPPER MAIN B1-451 FUEL X-FEED VALVE LT 1 UPPER MAIN B1-458 L FUEL DUMP VALVE CONT UPPER MAIN B1-498 FWD PUMPS PRESS LOW LTS UPPER MAIN B1-1246 FUEL PUMP PRESS LOW LTS R AUX 28 VDC-2 UPPER MAIN B1-452 DUMP V IND & FUEL LOW LVL SHUTOFF UPPER MAIN B1-453 FUEL X-FEED CONT 2 UPPER MAIN B1-454 FUEL X-FEED VALVE LT 2 UPPER MAIN B1-497 R AFT PUMPS PRESS LOW LTS UPPER MAIN B1-1247 FUEL PUMP PRESS LOW LTS L AUX 28 VDC-3 UPPER MAIN B1-455 FUEL X-FEED CONT 3 UPPER MAIN B1-456 FUEL X-FEED VALVE LT 3 UPPER MAIN B1-457 R FUEL DUMP VALVE CONT UPPER MAIN B1-460 FUEL TK OFF SCHEDULE LTS

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 3 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 65 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** UPPER MAIN B1-496 L AFT PUMPS PRESS LOW LTS UPPER MAIN B1-2004 AFT AUX PUMP FUEL CONTROL

Tank 1, 2, 3, UPPER and AFT Test I-1The following test should be done with empty tanks as fuse are installed. It is a continuity test and should be performed for each individual fuse. Following table gives the details of each test.
REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED
TANK 1 7 & 8 S3-450 LOOP CONTINU- ITY F1-176 - TANK 1 DUMP
1 & 2 S3-450 LOOP CONTINU- ITY F1-121 Tank 1 4000 lb
5 & 6 S3-450 LOOP CONTINU- ITY F1-120 Tank 1 6000 lb
1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP
1 & 2 S3-684 LOOP CONTINU- ITY F1-735 L WING OVERFILL (VENT BOX)

TANK 3 7 & 8 S3-451 LOOP CONTINU- ITY F1-178 - TANK 3 DUMP
1 & 2 S3-451 LOOP CONTINU- ITY F1-122 Tank 3 4000 lb
5 & 6 S3-451 LOOP CONTINU- ITY F1-123 Tank 3 6000 lb
1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP
1 & 2 S3-683 LOOP CONTINU- ITY F1-734 R WING OVERFILL (VENT BOX)

TANK 2 1 & 5 S3-454 LOOP CONTINU- ITY F1-177 TK 2 DUMP

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 4 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 66 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** Optional 1 2 & C S3-454 LOOP CONTINU- ITY F1-90 TK 2 40000 LB

UPPER AUX TANK 1 & GND S3-1186 CONT TO GND ON EMPTY F1-1364 UPPER AUX
2 & 3 S3-1186 LOOP CONT ON EMPTY F1-1376 UPPER AUX
REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED AFT AUX TANK S & R R5-4817 LOOP CONT W/PUMP OFF F1-972
V & U R5-4817 LOOP CONT W/PUMP OFF F1-973
OPTIONAL 1 - If the tank 2 is open this float switch circuit can be checked by moving the float of the float switch up and down and reading the circuit open/ground at S3-454 pin 2. Job Close-up The test continues for Auxiliary Tanks. I-2Use the existing AMM procedures to bring the airplane to the following configuration: Tank 1, 2 & 3 minimum 12000 +/- 300 pounds, UPR tank 6000 pounds and LWR tank full with fuel. I-2.1Verify that auxiliary tank FUEL SCHED light, located on the flight engineer's panel is ON when the LWR tank is full. This verifies the F1-1359 and F1-1360 fuses. Transfer fuel from LWR Aux tank to UPR Aux tank as follows: Verify the following C/Bs to be open STATUS NUMBER NAME OPEN B1-1248 FUEL PUMP PWR L UPR OPEN B1-1250 FUEL PUMP PWR R UPR Place L & R UPR & LWR pumps switches on the Flight Engineer panel to BOTH position. The "LWR Tank Press Lo" lights should be ON and then OFF and the "UPR Tank Press Lo" lights are steady ON. During the transfer verify that auxiliary tank FUEL SCHED light, located on the flight engineer's panel turns OFF. Continue fuel transfer from LWR to UPR Aux tank until the "LWR Tank Press Lo" light is ON steady. Place L & R UPR & LWR AUX pumps switches on the Flight Engineer panel to OFF position and close the following C/Bs: STATUS NUMBER NAME

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 5 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 67 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** CLOSED B1-1248 FUEL PUMP PWR L UPR CLOSED B1-1250 FUEL PUMP PWR R UPRUse DC10 AMM 12-11-04 procedure - PRESSURE REFUELING - SERVICING AUTOMATIC PRESSURE REFUELING to fill the UPR AUX tank until completely full. LWR and AFT AUX tanks are empty. Verify the position of the following C/Bs to be: I-2.2 STATUS NUMBER NAME OPEN B1-1647 FUEL PUMP POWER L AFT OPEN B1-1645 FUEL PUMP CONTROL L AFT AUX TANK OPEN B1-1644 FUEL PUMP CONTROL R AFT AUX TANK OPEN B1-475 GROUND REFUEL POWER OPEN B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING CLOSED B1-2004 AFT AUX FUEL PUMP CONTROL NOTE: Be sure that the fuel quantity in each main tanks 1,2, & 3 is over 11500 pounds. Actuate the AFT AUX TANK LEFT PUMP switch on Flight Engineer panel to OVRD position. Verify that auxiliary tank FUEL SCHED light, located on the Flight Engineer panel is ON. This verifies the fuses F1-1359 & -1362B. Actuate the AFT AUX TANK LEFT PUMP switch to OFF position. Verify that auxiliary tank FUEL SCHED light, located on the Flight Engineer's panel turns OFF. Close the following C/Bs: STATUS NUMBER NAME CLOSED B1-1647 FUEL PUMP PWR L AFT CLOSED B1-1645 FUEL PUMP CONTROL L AFT AUX TANK CLOSED B1-1644 FUEL PUMP CONTROL R AFT AUX TANK CLOSED B1-475 GROUND REFUEL POWER CLOSED B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING CLOSED B1-2004 AFT AUX FUEL PUMP CONTROL Transfer 3000 pounds fuel from UPR AUX tank to AFT AUX tank and then 3000 pounds from Tank 2 to AFT AUX tank as follows: I-2.3Access and arm the Refueling Panel located in the right wing leading edge.

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 6 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 68 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I**Open the AFT Aux fill valve placing AFT Aux Fill valve switch on the Refueling panel to OPEN position. Place L & R UPR & LWR pump switches on the Flight Engineer panel to UPR position. Verify the AFT Aux Fill valve open light is ON. After 3000 pounds fuel was transferred shut off the pumps by placingthe UPR pump switches on the Flight Engineer panel to OFF position. To read fuel quantity in any individual Aux tanks use the appropriate "AUX TANK QTY SEL" switch on the flight engineer (FE) panel. Turn on Tank 2 transfer pump placing the pump switch on Flight Engineer panel to ON position. Transfer approx. 3000 pounds fuel from Tank 2 to AFT tank and observe that auxiliary tank FUEL SCHED light, located on the FE panel turns ON. This verifies the fuses F1-1361 and -1363. Place the AFT Aux tank fill valve switch to the CLOSE position. Observe AFT Aux Fill valve open light goes OFF. Turn off Tank 2 TRANSFER pump on the Flight Engineer panel. Disarm the Refueling panel. Transfer fuel from UPR tank to fill up tank 2 as follows: Turn ON the UPR Aux transfer pumps by placing the L& R UPR & LWR tank pump switches located on Flight Engineer panel to UPR position. Place the Tank 2 fill valve switch on Flight Engineer panel to the OPEN position. Tank 2 fill valve light will be ON while the tank is filling then extinguishes when Tank 2 is completely full. Verify that the Aux Tank FUEL SCHED light goes OUT during this transfer. Disarm the Tank 2 fill valve by placing its switch on Flight Engineer panel to CLOSE position. Continue to transfer fuel from UPR Aux tank to Tanks 1 & 3 as follows: Place Tank 1 & 3 fill valve switch to the OPEN position. Observe the Fill Valve Open light for each tank come ON. When each tank 1 & 3 reaches 19000 pounds place the appropriate Fill Valve switch to the CLOSE position. When tanks 1& 3 are at the correct level place the L & R UPR & LWR tank pumps switch to OFF position. Access the Refueling Panel located in the right wing leading edge. Make sure all fill valve switches are in the CLOSE position then arm the refueling panel. Transfer fuel from UPR Aux tank to fill the AFT Aux tank as follows: Place the L & R UPR & LWR Tank pump switches to the UPR position. Place the AFT Aux tank fill valve switch on the Refueling panel to OPEN position and verify that the AFT Aux fill valve light is ON. Continue transferring fuel to AFT Aux until the tank is full (valve open light extinguishes). Move the AFT Aux fill valve switch on the Refueling panel to the CLOSE position to disarm the valve. Turn OFF the UPR Aux pumps by placing the L & R UPR & LWR tank pump switches to the OFF position. Disarm the Refueling panel. Verify the position of the following C/Bs to be closed: POSITION NUMBER NAME CLOSED B1-475 GROUND REFUEL POWER CLOSED B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 7 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 69 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I**With Upper Aux Tank pump not running move Tank 1 & 3 fill valve switch to OPEN position and verify that they remain latched . This verifies fuse F1- 90 . Move Tank 1 & 3 fill valve switch to Close position. Verify the position of the following C/Bs to be closed: I-2.4 POSITION NUMBER NAME OPEN B1-1647 FUEL PUMP POWER L AFT CLOSED B1-1645 FUEL PUMP CONTROL L AFT AUX TANK CLOSED B1-1644 FUEL PUMP CONTROL R AFT AUX TANK OPEN B1-475 GROUND REFUEL POWER POSITION NUMBER NAME OPEN B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING OPEN B1-2004 AFT AUX FUEL PUMP CONTROL Actuate the AFT AUX TANK LEFT PUMP switch on Flight Engineer panel to OVRD position. Verify that the auxiliary tank FUEL SCHED light, located on the Flight Engineer's panel is ON. This verifies the fuses F1-1358 and -1362A . Actuate the AFT AUX TANK LEFT PUMP switch to OFF position. Verify that the auxiliary tank FUEL SCHED light, located on the Flight Engineer's panel turns OFF. Transfer fuel from AFT Aux tank to UPR Aux tank until AFT Aux tank is empty as follows: Arm Refueling panel. Actuate the L & R AFT AUX TANK PUMP switches on the Flight Engineer panel to OVRD position. Place the UPR Aux fill valve switch on Refueling panel to OPEN position. Transfer fuel until AFT Aux tank is empty (AFT tank pump press low light steady ON). Stop L & R AUX AFT tank pumps by placing the L & R AFT AUX TANK PUMP switch in OFF position and close the UPR tank fill valve by placing UPR Aux fill valve switch to CLOSE position. Disarm the Refueling panel. Job Close-up - remove all the tools and equipment from the work area. Make sure the area is clean.

**Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST (SHEET 8 OF 8)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 70 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 5.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES I** This test should be performed in the order shown below. REFERENCES (AMM) Tasks:DC-10 AMM 12-11-04, PRESSURE REFUELING - SERVICING AUTOMATIC PRESSURE REFUELING DC-10 AMM 12-11-05, DEFUELING - SERVICING NOTES: Sufficient fuel should be in the Tank 2 and Upper Aux Tank to do the AFT tank test (see specifics in each test procedure) aWhen fueling the aircraft if any Aux Tanks are to receive fuel, schedule at least 6000 pounds (2722 Kilograms) in the UPPER Aux tank to prevent conflicts between what fuel has been loaded and the quantity indication. b

To read fuel quantity in any individual Aux tanks use the appropriate "AUX TANK QTY SEL" switch on the flight engineer (FE) panel. c

WARNING: This test moves fuel to and from AFT Aux tank. This procedure assumes that the aircraft is empty of cargo and passengers while the test is being conducted. Fuel is placed in main and UPR Aux tanks to counterbalance the fuel in the AFT Aux tank. Following the filling and emptying sequence provided in this procedure will avoid aircraft tip over. The following C/Bs should be closed for the functional test:LOCATION C/B NO. BUS BATT BUS OVERHEAD B1-474 FUEL TANK FILL VLV & BATT BUS SENS- ING OVERHEAD B1-723 APU START PUMP OVERHEAD B1-724 APU ADVISORY LTS OVERHEAD B1-728 APU CONTROL & FUEL VLV BATT DIRECT OVERHEAD B1-475 GROUND REFUEL PWR OVERHEAD B1-479 GND REFUEL INV PWR & HI LEVEL TEST 115 VAC - 1 UPPER MAIN B1-499 FUEL QTY TRANSFER RELAY

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 1 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 71 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** UPPER MAIN B1-589 FUEL QTY NORMAL PWR LOCATION C/B NO. BUS 115 VAC - 1 (CONT.) UPPER MAIN B1-609 FUEL PUMP CONTROL TANK 2 FWD UPPER MAIN B1-615 FUEL PUMP CONTROL TANK 1 FWD UPPER MAIN B1-619 FUEL PUMP CONTROL TANK 2 TRANS UPPER MAIN B1-1206 UPR & LWR AUX TANK R UPR UPPER MAIN B1-1645 FUEL PUMP CONTROL L AFT AUX TANK 115 VAC - 2 UPPER MAIN B1-603 FUEL PUMP CONTROL TANK 2 R AFT UPPER MAIN B1-611 FUEL PUMP CONTROL TANK 1 TRANSF UPPER MAIN B1-621 FUEL PUMP CONTROL TANK 3 AFT UPPER MAIN B1-769 FUEL QTY ALT PWR UPPER MAIN B1-1207 UPR & LWR AUX TANK L UPR UPPER MAIN B1-1209 AUX TANK L LWR 115 VAC - 3 UPPER MAIN B1-590 FUEL QTY RPTRS & XFER UPPER MAIN B1-613 FUEL PUMP CONTROL TANK 1 AFT UPPER MAIN B1-617 FUEL PUMP CONTROL TANK 3 FWD UPPER MAIN B1-757 FUEL PUMP CONTROL TANK 2 TRANS UPPER MAIN B1-1208 AUX TANK R LWR UPPER MAIN B1-1644 FUEL PUMP CONTROL R AFT AUX TANK 115 VAC GEN-1 UPPER MAIN B1-608 FUEL PUMP POWER TANK 2 FWD UPPER MAIN B1-614 FUEL PUMP POWER TANK 1 FWD UPPER MAIN B1-618 FUEL PUMP POWER TANK 3 TRANS UPPER MAIN B1-1250 FUEL PUMP PWR R UPR UPPER MAIN B1-1647 FUEL PUMP PWR L AFT 115 VAC GEN-2 UPPER MAIN B1-596 FUEL PUMP POWER TANK 2 R AFT

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 2 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 72 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** UPPER MAIN B1-610 FUEL PUMP POWER TANK 1 TRANS UPPER MAIN B1-620 FUEL PUMP POWER TANK 3 AFT UPPER MAIN B1-1248 FUEL PUMP PWR L UPR UPPER MAIN B1-1249 FUEL PUMP PWR L LWR
LOCATION C/B NO. BUS 115 VAC GEN-3 UPPER MAIN B1-612 FUEL PUMP POWER TANK 1 AFT UPPER MAIN B1-616 FUEL PUMP POWER TANK 3 FWD UPPER MAIN B1-756 FUEL PUMP POWER TANK 2 TRANS UPPER MAIN B1-1251 FUEL PUMP PWR R LWR UPPER MAIN B1-1646 FUEL PUMP PWR R AFT 115 VAC R EMERGENCY OVERHEAD B1-680 FUEL PUMP TANK 2 LEFT AFT 28 VDC-1 UPPER MAIN B1-450 FUEL X-FEED CONT 1 UPPER MAIN B1-451 FUEL X-FEED VALVE LT 1 UPPER MAIN B1-458 L FUEL DUMP VALVE CONT UPPER MAIN B1-498 FWD PUMPS PRESS LOW LTS UPPER MAIN B1-1246 FUEL PUMP PRESS LOW LTS R AUX 28 VDC-2 UPPER MAIN B1-452 DUMP V IND & FUEL LOW LVL SHUTOFF UPPER MAIN B1-453 FUEL X-FEED CONT 2 UPPER MAIN B1-454 FUEL X-FEED VALVE LT 2 UPPER MAIN B1-497 R AFT PUMPS PRESS LOW LTS UPPER MAIN B1-1247 FUEL PUMP PRESS LOW LTS L AUX 28 VDC-3 UPPER MAIN B1-455 FUEL X-FEED CONT 3 UPPER MAIN B1-456 FUEL X-FEED VALVE LT 3 UPPER MAIN B1-457 R FUEL DUMP VALVE CONT

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 3 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 73 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** UPPER MAIN B1-460 FUEL TK OFF SCHEDULE LTS UPPER MAIN B1-496 L AFT PUMPS PRESS LOW LTS UPPER MAIN B1-2004 AFT AUX PUMP FUEL CONTROL

Tank 1, 2, 3, UPPER AND AFT Test I-1The following test should be done with empty tanks as fuse are installed. It is a continuity test and should be performed for each individual fuse. Following table gives the details of each test.
REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED
TANK 1 7 & 8 S3-450 LOOP CONTI- NUITY F1-176 - TANK 1 DUMP
1 & 2 S3-450 LOOP CONTI- NUITY F1-121 Tank 1 4000 lb
5 & 6 S3-450 LOOP CONTI- NUITY F1-120 Tank 1 6000 lb
1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP
1 & 2 S3-684 LOOP CONTI- NUITY F1-735 L WING OVERFILL (VENT BOX)

TANK 3 7 & 8 S3-451 LOOP CONTI- NUITY F1-178 - TANK 3 DUMP
1 & 2 S3-451 LOOP CONTI- NUITY F1-122 Tank 3 4000 lb
5 & 6 S3-451 LOOP CONTI- NUITY F1-123 Tank 3 6000 lb
1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP
1 & 2 S3-683 LOOP CONTI- NUITY F1-734 R WING OVERFILL (VENT BOX)

TANK 2

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 4 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 74 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** 1 & 5 S3-454 LOOP CONTI- NUITY F1-177 TK 2 DUMP Optional 1 2 & C S3-454 LOOP CONTI- NUITY F1-90 TK 2 40000 LB

UPPER AUX TANK 1 & GND S3-1186 CONT TO GND ON EMPTY F1-1364 UPPER AUX

2 & 3 S3-1186 LOOP CONT ON EMPTY F1-1376 UPPER AUX
REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED AFT AUX TANK S & R R5-4817 LOOP CONT W/PUMP OFF F1-972
V & U R5-4817 LOOP CONT W/PUMP OFF F1-973
OPTIONAL 1 - If the tank 2 is open this float switch circuit can be checked by moving the float of the float switch up and down and reading the circuit open/ground at S3-454 pin 2. Job Close-up The test continues for Auxiliary Tanks. I-2Bring the airplane to the following configuration: Tank 1, 2 & 3 minimum 12000 pounds, UPR tank 6000 pounds and LWR tank full with fuel. I-2.1Verify that auxiliary tank FUEL SCHED light, located on the flight engineer's panel is ON when the LWR tank is full. This verifies the F1-1359 and F1-1360 fuses. Place the LWR Aux Fill valve switch on the Refueling Panel in CLOSE position. Empty the LWR tank and fill the UPR tank as follows: Transfer fuel from LWR Aux tank to UPR Aux tank as follows Verify the following C/Bs to be open STATUS NUMBER NAME OPEN B1-1248 FUEL PUMP PWR L UPR OPEN B1-1250 FUEL PUMP PWR R UPR

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 5 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 75 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I**Place L & R UPR & LWR pumps switches on the Flight Engineer panel to BOTH position. The "LWR Tank Press Lo" lights should be ON and then OFF and the "UPR Tank Press Lo" lights are steady ON. During the transfer verify that auxiliary tank FUEL SCHED light, located on the flight engineer's panel turns OFF. Continue fuel transfer from LWR to UPR Aux tank until the "LWR Tank Press Lo" light is ON steady. Place L & R UPR & LWR AUX pumps switches on the Flight Engineer panel to OFF position and close the following C/Bs: STATUS NUMBER NAME CLOSED B1-1248 FUEL PUMP PWR L UPR CLOSED B1-1250 FUEL PUMP PWR R UPR Use DC10 AMM 12-11-04 procedure - PRESSURE REFUELING - SERVICING AUTOMATIC PRESSURE REFUELING to fill the UPR AUX tank until completely full. LWR and AFT AUX tanks are empty. Verify the position of the following C/Bs to be: I-3.2 STATUS NUMBER NAME OPEN B1-1647 FUEL PUMP POWER L AFT OPEN B1-1645 FUEL PUMP CONTROL L AFT AUX TANK OPEN B1-1644 FUEL PUMP CONTROL R AFT AUX TANK OPEN B1-475 GROUND REFUEL POWER OPEN B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING CLOSED B1-2004 AFT AUX FUEL PUMP CONTROL NOTE: Be sure that the fuel quantity in each main Tanks 1, 2, & 3 is over 11500 pounds. Actuate the AFT AUX TANK LEFT PUMP switch on Flight Engineer panel to OVRD position. Verify that auxiliary tank FUEL SCHED light, located on the Flight Engineer panel is ON. This verifies the fuses F1-1359 & -1381B. Actuate the AFT AUX TANK LEFT PUMP switch to OFF position. Verify that auxiliary tank FUEL SCHED light, located on the Flight Engineer's panel turns OFF. Close the following C/Bs: STATUS NUMBER NAME CLOSED B1-1647 FUEL PUMP PWR L AFT CLOSED B1-1645 FUEL PUMP CONTROL L AFT AUX TANK CLOSED B1-1644 FUEL PUMP CONTROL R AFT AUX TANK

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 6 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 76 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** CLOSED B1-475 GROUND REFUEL POWER CLOSED B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING CLOSED B1-2004 AFT AUX FUEL PUMP CONTROL Verify AFT AUX TANK BALLAST CONTROL SW located on the Flight Engineer Equipment panel is in the OFF position. I-3.3
Transfer 3000 pounds fuel from UPR AUX tank to AFT AUX Tank and then 3000 pounds from Tank 2 to AFT AUX tank as follows: Access and arm the Refueling Panel located in the right wing leading edge. Open the AFT Aux fill valve placing AFT Aux Fill valve switch on the Refueling panel to OPEN position. Place L & R UPR & LWR tank pump switches on the Flight Engineer panel to UPR position. Verify the AFT Aux Fill valve open light is ON. After 3000 pounds fuel was transferred shut off the pumps by placing the UPR pump switches on the Flight Engineer panel to OFF position. To read fuel quantity in any individual Aux tanks use the appropriate "AUX TANK QTY SEL" switch on the flight engineer (FE) panel. Turn on Tank 2 transfer pump placing the pump switch on Flight Engineer panel to ON position. Transfer approx. 3000 pounds fuel from Tank 2 to AFT tank and observe that auxiliary tank FUEL SCHED light, located on the FE panel turns ON. This verifies the fuses F1-1361 and -1363. Place the AFT Aux tank fill valve switch to the CLOSE position. Observe AFT Aux Fill valve open light goes OFF. Turn off Tank 2 Transfer pump on the Flight Engineer panel. Disarm the Refueling panel. Transfer fuel from UPR tank to fill up tank 2 as follows: Turn ON the UPR Aux transfer pumps by placing the L& R UPR & LWR tank pump switches located on Flight Engineer panel to UPR position. Place the Tank 2 fill valve switch on Flight Engineer panel to the OPEN position. Tank 2 fill valve light will be ON while the tank is filling then extinguishes when Tank 2 is completely full. Verify that the Aux Tank FUEL SCHED light goes OUT during this transfer. Disarm the Tank 2 fill valve by placing its switch on Flight Engineer panel to CLOSE position. Continue to transfer fuel from UPR Aux tank to Tanks 1 and 3 as follows: Place Tank 1 & 3 fill valve switch to the OPEN position. Observe the Fill Valve Open light for each tank come ON. When each tank 1 & 3 reaches 19000 pounds place the appropriate Fill Valve switch to the CLOSE position. When tanks 1& 3 are at the correct level place the L & R UPR & LWR tank pumps switch to OFF position. Access the Refueling Panel located in the right wing leading edge. Make sure all fill valve switches are in the CLOSE position then arm the refueling panel Transfer fuel from UPR Aux tank to fill the AFT Aux tank as follows: Place the L & R UPR & LWR Tank pump switches to the UPR position.

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 7 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 77 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I**Place the AFT Aux tank fill valve switch on the Refueling panel to OPEN position and verify that the AFT Aux fill valve light is ON. Continue transferring fuel to AFT Aux until AFT Aux tank fuel quantity is above 10000 pounds but not above 12000 pounds and the UPR Aux quantity is less than 10000 pounds. Move the AFT Aux fill valve switch on the Refueling panel to the CLOSE position to disarm the valve. Turn OFF the UPR Aux pumps by placing the L & R UPR & LWR tank pump switches to the OFF position. Disarm the Refueling panel. Verify the position of the following C/Bs to be: POSITION NUMBER NAME CLOSED B1-475 GROUND REFUEL POWER CLOSED B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING With Upper Aux Tank pump not running move Tank 1 & 3 fill valve switch to OPEN position and verify that they remain latched. This verifies fuse F1- 90 . Move Tank 1 & 3 fill valve switch to Close position. Verify the position of the following C/Bs to be: I-3.4
POSITION NUMBER NAME OPEN B1-1647 FUEL PUMP POWER L AFT CLOSED B1-1645 FUEL PUMP CONTROL L AFT AUX TANK CLOSED B1-1644 FUEL PUMP CONTROL R AFT AUX TANK OPEN B1-475 GROUND REFUEL POWER OPEN B1-474 FUEL TANK FILL VALVE & BAT BUS SENSING OPEN B1-2004 AFT AUX FUEL PUMP CONTROL Actuate the AFT AUX TANK LEFT PUMP switch to OVRD position. Verify that the auxiliary tank FUEL SCHED light, located on the flight engineer's panel is ON. This verifies the fuses F1-1358 and -1381A . Actuate the AFT AUX TANK LEFT PUMP switch to OFF position. Verify that the auxiliary tank FUEL SCHED light, located on the Flight Engineer's panel turns OFF. Transfer fuel to AFT AUX tank from UPR AUX tank and then from tanks 1 and 3 as follows: I-3.5

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 8 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 78 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I**Arm the refueling panel. Start the UPR tank pumps by placing the L & R UPR & LWR TANK PUMP switches located on Flight Engineer panel to UPR position. Place the AFT Aux tank fill valve switch on the Refueling panel to OPEN position and verify that the AFT Aux fill valve light is ON. Continue transferring fuel to AFT Aux tank until UPR tank fuel quantity is 6000 pounds. Stop the UPR pump by placing the L & R UPR & LWR TANK PUMP switches located on Flight Engineer panel to OFF position. Turn Tank 1 and Tank 3 transfer pumps switches on the flight engineer panel ON to transfer from these tanks until AFT Aux tank is full (AFT AUX valve light on the Refueling panel turns OFF). Verify that auxiliary tank FUEL SCHED light, located on the flight engineer's panel is ON. This verifies the fuses F1-1362 and -1359: Place the AFT Aux tank fill valve switch to close position. Turn OFF tank 1 & 3 transfer pumps. Open the following C/B POSITION NUMBER NAME UPPER MAIN B1-460 FUEL TK OFF SCHEDULE LTS FLT ENG UPPR MAIN CB PNL B1-1246 FUEL PUMPS PRESS LOW LTS R AUX FLT ENG UPPR MAIN CB PNL B1-1247 FUEL PUMPS PRESS LOW LTS L AUXGain access to AFT AUX Transfer fuse F-1365 through the Center Cargo Compartment Door. Disconnect the connector P1-4817 and on the receptacle side measure the continuity between pins C & D. Continuity between these pins verifies fuse F1-1365. Reconnect P1-4817 connector, remove tools and close the access door. Transfer fuel from AFT Aux tank to UPR Aux tank until AFT Aux tank is empty as follows: Arm Refueling panel. Actuate the L & R AFT TANK PUMP switches on the Flight Engineer panel to OVRD position. Place the UPR Aux fill valve switch on Refueling panel to OPEN position. Transfer fuel until AFT Aux tank is empty (AFT tank pump press low light steady ON). Stop L & R AFT tank pumps by placing the L & R AFT TANK PUMP switch in OFF position and close the UPR tank fill valve by placing UPR Aux fill valve switch to CLOSE position. Disarm the Refueling panel. Job Close-up - remove all the tools and equipment from the work area. Make sure the area is clean.

**Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST (SHEET 9 OF 9)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 79 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 6.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES I** This test should be performed in the order shown below. REFERENCES (AMM) Tasks:DC-10 AMM 12-11-04, PRESSURE REFUELING - SERVICING AUTOMATIC PRESSURE REFUELING DC-10 AMM 12-11-05, DEFUELING - SERVICING This procedure should be used as necessary. Depower the Fuse system or open the associated Circuit Breakers. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. Tank 1, 2, 3, CENTER WING, FWD AUX. and AFT AUX. Test I-1The following test should be done with empty tanks as fuse are installed. It is a continuity test and should be performed for each individual fuse. Following table gives the details of each test. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTI- NUITY F1-176 - TANK 1 DUMP
1 & 2 S3-450 LOOP CONTI- NUITY F1-121 Tank 1 4000 lb
5 & 6 S3-450 LOOP CONTI- NUITY F1-120 Tank 1 6000 lb
1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP
1 & 2 S3-684 LOOP CONTI- NUITY F1-735 L WING OVERFILL (VENT BOX)

TANK 3 7 & 8 S3-451 LOOP CONTI- NUITY F1-178 - TANK 3 DUMP
1 & 2 S3-451 LOOP CONTI- NUITY F1-122 Tank 3 4000 lb
5 & 6 S3-451 LOOP CONTI- NUITY F1-123 Tank 3 6000 lb

**Appendix S: DC-10-30F (KC-10A) - FUSE FUNCTIONAL TEST (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 80 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** 1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP
1 & 2 S3-683 LOOP CONTI- NUITY F1-734 R WING OVERFILL (VENT BOX)
REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 2 1 & 5 S3-454 LOOP CONTI- NUITY F1-177 TK 2 DUMP Optional 1 2 & C S3-454 LOOP CONTI- NUITY F1-90 TK 2 40000 LB

AFT AUX TANK 2 & 5 S3-1110 LOOP CONTI- NUITY F1-1327 AFT FUS LL

FWD AUX TANK 2 & 14 S3-1277 LOOP CONTI- NUITY F1-1277 FWD FUS LL
12 & 13 S3-1109 LOOP CONTI- NUITY F1-1293 FWD FUS INT OPTIONAL 1 - If the tank 2 is open this float switch circuit can be checked by moving the float of the float switch up and down and reading the circuit open/ground at S3-454 pin 2. AERIAL REFUELING PUMP CONTROL FLOAT SWITCHES I-1To perform this test minimum 7000 lbs fuel is necessary in the UPR Aux tank. I-1.1After the correct amount of fuel Gain access to F1-1374 and F1-1328 fuses through Left and Right Main Landing Gear Wheel Wells. Do the continuity test for the following fuses: F1-1374, -1328. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED CENTER WING TANKS 5 & 6 S3-802 LOOP CONTI- NUITY CENTER WING FUEL TANK LOW LEVEL R, F1-1374 5 & 6 S3-803 LOOP CONT ON EMPTY CENTER WING FUEL TANK LOW LEVEL L, F1-1328 Job Close-up - remove all the tools and equipment from the work area. Make sure the area is clean.

**Appendix S: DC-10-30F (KC-10A) - FUSE FUNCTIONAL TEST (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 81 of 83 **BOEING SERVICE BULLETIN DC10-28-252 This Appendix applies only to: Group 7.** 
**RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES I** This test should be performed in the order shown below. REFERENCES (AMM) Tasks:DC-10 AMM 12-11-04, PRESSURE REFUELING - SERVICING AUTOMATIC PRESSURE REFUELING DC-10 AMM 12-11-05, DEFUELING - SERVICING This procedure should be used as necessary. Depower the Fuse system or open the associated Circuit Breakers. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. Tank 1, 2, 3, and CENTER WING Test I-1The following test should be done with empty tanks as fuse are installed. It is a continuity test and should be performed for each individual fuse. Following table gives the details of each test. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTI- NUITY F1-176 - TANK 1 DUMP
1 & 2 S3-450 LOOP CONTI- NUITY F1-121 Tank 1 4000 lb
5 & 6 S3-450 LOOP CONTI- NUITY F1-120 Tank 1 6000 lb
1 & 2 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP
1 & 2 S3-684 LOOP CONTI- NUITY F1-735 L WING OVERFILL (VENT BOX)

TANK 3 7 & 8 S3-451 LOOP CONTI- NUITY F1-178 - TANK 3 DUMP
1 & 2 S3-451 LOOP CONTI- NUITY F1-122 Tank 3 4000 lb
5 & 6 S3-451 LOOP CONTI- NUITY F1-123 Tank 3 6000 lb

**Appendix T: DC-10-30F (KDC-10) - FUSE FUNCTIONAL TEST (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 82 of 83 **BOEING SERVICE BULLETIN DC10-28-252 RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  **I** 1 & 2 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP
1 & 2 S3-683 LOOP CONTI- NUITY F1-734 R WING OVERFILL (VENT BOX)

TANK 2 1 & 5 S3-454 LOOP CONTI- NUITY F1-177 TK 2 DUMP Optional 1 2 & C S3-454 LOOP CONTI- NUITY F1-90 TK 2 40000 LB
OPTIONAL 1 - If the tank 2 is open this float switch circuit can be checked by moving the float of the float switch up and down and reading the circuit open/ground at S3-454 pin 2. AERIAL REFUELING PUMP CONTROL FLOAT SWITCHES I-1To perform this test minimum 7000 lbs fuel is necessary in the UPR Aux tank. I-1.1After the correct amount of fuel Gain access to F1-1374 and F1-1328 fuses through Left and Right Main Landing Gear Wheel Wells. Do the continuity test for the following fuses: F1-1374, -1328. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED CENTER WING TANKS 5 & 6 S3-802 LOOP CONTI- NUITY CENTER WING FUEL TANK LOW LEVEL R, F1-1374 5 & 6 S3-803 LOOP CONT ON EMPTY CENTER WING FUEL TANK LOW LEVEL L, F1-1328 Job Close-up - remove all the tools and equipment from the work area. Make sure the area is clean.

**Appendix T: DC-10-30F (KDC-10) - FUSE FUNCTIONAL TEST (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 DC10-28-252 Revision 1 January 06, 2010 83 of 83 **BOEING SERVICE BULLETIN DC10-28-252**