Commercial McDonnell Douglas

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.

ECCN: 9E991

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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Unpublished Work - All Rights Reserved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.

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3.0
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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

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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

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BOEING SERVICE BULLETIN DC10-28-252
Commercial McDonnell Douglas

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

Original Issue: November 25, 2008

Revision 1: January 06, 2010

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BLANK PAGE
Commercial McDonnell Douglas

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.

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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.

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BOEING SERVICE BULLETIN DC10-28-252
Commercial McDonnell Douglas

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.

GROUP CONFIGURATION DESCRIPTION

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

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

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 -

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

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

Airplane Models:

DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F

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

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Fuselage Num- Group

ber

100 3

103 2

106 3

110 2

112 1

114 - 115 3

117 3

119 1

122 - 123 3

127 3

129 3

131 - 135 3

137 3

138 - 140 1

142 1

144 - 145 1

146 - 147 3

148 1

15 1

150 3

152 3

153 - 155 1

156 - 158 3

160 3

162 3

165 - 166 3

169 1

17 1

170 - 171 3

173 1

174 3

177 1

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Fuselage Num- Group

ber

178 - 179 3

183 - 184 3

187 - 190 3

192 3

194 1

195 - 196 3

198 1

199 3

2 3

201 3

203 1

204 3

205 1

206 3

207 - 210 1

211 - 216 3

219 2

220 - 221 3

223 - 227 3

229 - 232 3

234 3

235 7

236 3

239 - 242 3

244 - 246 3

247 1

248 3

249 1

25 1

250 1

251 - 256 3

257 2

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Fuselage Num- Group

ber

26 1

261 - 263 3

264 7

265 - 268 3

269 1

27 1

270 - 273 1

274 - 275 3

277 2

281 3

282 2

285 - 286 3

289 - 291 3

292 4

294 1

296 3

297 - 298 1

299 - 306 3

307 1

308 3

309 1

310 3

311 6

312 - 316 3

317 2

318 3

319 1

32 1

321 1

323 1

324 - 325 3

326 2

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Fuselage Num- Group

ber

327 3

329 3

33 1

330 2

332 3

333 6

334 - 339 3

34 3

340 3

341 5

342 - 343 3

344 1

345 5

346 3

347 1

349 3

35 1

351 1

353 1

355 - 356 3

358 3

359 - 361 6

363 6

366 - 367 3

372 3

373 6

375 - 378 6

379 1

380 6

381 3

383 - 389 6

39 1

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Fuselage Num- Group

ber

390 - 399 6

40 3

400 - 408 6

409 2

41 3

410 - 411 6

412 2

413 - 415 6

416 2

417 - 418 6

419 2

42 1

420 - 421 6

422 2

423 - 429 6

43 3

430 - 432 6

433 2

434 - 438 5

439 6

440 2

441 6

442 - 444 2

445 - 446 3

55 1

59 1

6 1

60 - 61 3

62 1

65 3

70 1

71 - 72 3

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Fuselage Num- Group

ber

76 1

78 1

8 1

83 3

86 1

89 1

90 3

96 2

99 3

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.

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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

Model Zone

DC-10-10F, MD-10-10F 516, 526, 527, 537, 616, 626, 627, 637

Group 2:

Affected Maintenance Zones

Model Zone

DC-10-30F, MD-10-30F 516, 526, 527, 537, 616, 626, 627, 637

Group 3:

Affected Maintenance Zones

Model Zone

DC-10-10, DC-10-10F, DC-10- 516, 526, 527, 537, 616, 626, 627, 637

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

DC-10-40F

Group 4-5:

Affected Maintenance Zones

Model Zone

DC-10-30 516, 526, 527, 537, 616, 626, 627, 637

Group 6:

Affected Maintenance Zones

Model Zone

DC-10-30F (KC-10A) 511, 521, 531, 611, 621, 631

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BOEING SERVICE BULLETIN DC10-28-252
Group 7:

Affected Maintenance Zones

Model Zone

DC-10-30F (KDC-10) 511, 521, 531, 611, 621, 631

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.

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 95.4 47.7

Test 2 9.6 4.8

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 151.0 75.5

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 106.0 53.0

Test 2 10.6 5.3

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 162.6 81.3

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 63.6 31.8

Test 2 6.4 3.2

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 116.0 58.0

Group 4:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 122.0 61.0

Test 2 12.2 6.1

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 180.2 90.1

Group 5:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 132.0 66.0

Test 2 13.2 6.6

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BOEING SERVICE BULLETIN DC10-28-252
Group 5:

Task Number of Persons Task Hours Elapsed Hours

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 191.2 95.6

Group 6:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 90.0 45.0

Test 2 9.0 4.5

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 145.0 72.5

Group 7:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 74.0 37.0

Test 2 7.4 3.7

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 127.4 63.7

H. Weight and Balance Changes

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

Group

1 1400.4 + 6.1 + 8542.4

2 1395.0 + 7.1 + 9904.5

3 1383.9 + 4.3 + 5950.8

4 1455.0 + 6.9 + 10039.5

5 1485.3 + 7.5 + 11139.8

6 1364.8 + 5.8 + 7915.8

7 1380.1 + 4.9 + 6762.5

I. Electrical Load Data

Not changed.

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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:

Drawing No Title Sheet DCN/REV ADCN

SR10280063 Electrical Installation - In-line fuse DWG D -

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:

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BOEING SERVICE BULLETIN DC10-28-252
Publication Chapter-Section

05-53, 28-12, 28-21, 28-

22, 28-25, 28-30, 28-43,

28-46 and 36-13

Aircraft Maintenance Manual

Fault Isolation Manual (MD-10) 36-23

Illustrated Parts Catalog 28-42

DC-10 TAFI PT1 28-02, 28-41 and 36-23

Turnaround Fault Isolation Manual (DC-10, KC-10 and KDC-10) 36-23

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.

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BOEING SERVICE BULLETIN DC10-28-252
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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)

Kit Number Name QTY

SB10280252-3 Service Kit 1 17 $3,139.00

SB10280252-5 Service Kit 1 17 3,589.00

SB10280252-7 Service Kit 1 17 3,394.00

SB10280252-9 Service Kit 1 17 5,378.00

SB10280252-11 Service Kit 1 17 5,598.00

SB10280252-13 Service Kit 1 17 5,398.00

SB10280252-15 Service Kit 1 17 4,505.00

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

New Part Number QTY Name Notes

-3

3D0005-08-10 3 SCREW (a)

3D0005-08-8 34 SCREW (a)

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Original Issue: November 25, 2008

Revision 1: January 06, 2010 DC10-28-252

23 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 1:

Kit SB10280252

New Part Number QTY Name Notes

-3

3D0005-3-22 4 SCREW (a)

3D0005-3-26 6 SCREW (a)

3D0005-3-28 1 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 12 TERMINAL LUG 878 (a)

5D0086-6 3 TERMINAL LUG 762 (a)

5D0206-20 36 SEALING PLUG (a)

65053-220 18 IN-LINE FUSE

ANN0012-1 1 BRACKET

M39029/22-192 3 SOCKET T/C 524

MS18029-6S8 1 COVER ASSY

MS20470AD5-5D 4 RIVET

MS21042L08 67 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS27212-6-8 1 TERMINAL BOARD

MS35338-42 33 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 40 WASHER

NAS1252-8H 3 WASHER

NAS1252-8L 104 WASHER

NAS43DD3-48FC 4 SPACER

NAS43DD3-64FC 6 SPACER

NAS43DD3-72FC 1 SPACER

NAS620A4 3 WASHER

NAS7700-3 3 BOLT

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Original Issue: November 25, 2008

Revision 1: January 06, 2010 DC10-28-252

24 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 1:

Kit SB10280252

New Part Number QTY Name Notes

-3

S7934111-2SA 1 CLAMP (a)

S7934111-3SA 19 CLAMP (a)

S7934111-4SA 1 CLAMP (a)

S7934111-5SA 2 CLAMP (a)

S7934111-6SA 1 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-9SA 18 CLAMP (a)

SR10280063-102 1 WIRE KIT

SR10280063-103 1 WIRE KIT

165 FT X SLEEVING

.166 I.D.

SR10280063-3

(DMS 2109, Type 1)

or equivalent

SR10280063-7 50 YDS TIE TAPE

(DMS 2089) or

equivalent

TA4012F21 2 BRACKET

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

Group 1:

Wire Kit SR10280063

New Part Number QTY QTY Name Notes

-102 -103

DC2426-1C-22NM (DMS 2426) 107 FT 60 FT WIRE CODE 801

or equivalent

M39029/22-192 20 13 SOCKET T/C 524

5D0086-3 13 11 TERMINAL LUG 878 (a)

5D0086-6 7 2 TERMINAL LUG 762 (a)

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

Group 2:

Kit SB10280252

New Part Number QTY Name Notes

-5

3D0005-08-10 7 SCREW (a)

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Copyright © Unpublished Work - See page 1 for details.

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25 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 2:

Kit SB10280252

New Part Number QTY Name Notes

-5

3D0005-08-8 37 SCREW (a)

3D0005-3-22 5 SCREW (a)

3D0005-3-26 6 SCREW (a)

3D0005-3-28 2 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 13 TERMINAL LUG 878 (a)

5D0086-6 4 TERMINAL LUG 762 (a)

5D0206-20 40 SEALING PLUG (a)

65053-220 20 IN-LINE FUSE

ANN0012-1 1 BRACKET

M39029/22-192 3 SOCKET T/C 524

MS18029-6S8 1 COVER ASSY

MS20470AD5-5D 4 RIVET

MS21042L08 74 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS27212-6-8 1 TERMINAL BOARD

MS35338-42 37 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 46 WASHER

NAS1252-8H 7 WASHER

NAS1252-8L 118 WASHER

NAS43DD3-48FC 5 SPACER

NAS43DD3-64FC 6 SPACER

NAS43DD3-72FC 2 SPACER

NAS620A4 3 WASHER

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

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26 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 2:

Kit SB10280252

New Part Number QTY Name Notes

-5

NAS7700-3 3 BOLT

S7934111-2SA 1 CLAMP (a)

S7934111-3SA 22 CLAMP (a)

S7934111-4SA 5 CLAMP (a)

S7934111-5SA 3 CLAMP (a)

S7934111-6SA 1 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-8SA 1 CLAMP (a)

S7934111-9SA 20 CLAMP (a)

SR10280063-101 1 WIRE KIT

SR10280063-102 1 WIRE KIT

SR10280063-103 1 WIRE KIT

191 FT X SLEEVING

.166 I.D.

SR10280063-3 (DMS

2109, Type 1) or

equivalent

SR10280063-7 (DMS 50 YDS TIE TAPE

2089) or equivalent

TA4012F21 2 BRACKET

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

Group 2:

Wire Kit SR10280063

New Part Number QTY QTY QTY Name Notes

-101 -102 -103

DC2426-1C-22NM (DMS 26 FT 107 FT 60 FT WIRE CODE 801

2426) or equivalent

M39029/22-192 4 20 13 SOCKET T/C 524

5D0086-3 - 13 11 TERMINAL LUG 878 (a)

5D0086-6 4 7 2 TERMINAL LUG 762 (a)

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

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27 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 3:

Kit SB10280252

New Part Number QTY Name Notes

-7

3D0005-08-10 3 SCREW (a)

3D0005-08-8 22 SCREW (a)

3D0005-3-26 5 SCREW (a)

3D0005-3-28 1 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 9 TERMINAL LUG 878 (a)

5D0206-20 24 SEALING PLUG (a)

65053-220 12 IN-LINE FUSE

M39029/22-192 3 SOCKET T/C 524

MS21042L08 43 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS35338-42 27 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 24 WASHER

NAS1252-8H 3 WASHER

NAS1252-8L 47 WASHER

NAS43DD3-64FC 5 SPACER

NAS43DD3-72FC 1 SPACER

S7934111-3SA 12 CLAMP (a)

S7934111-9SA 12 CLAMP (a)

SR10280063-111 1 WIRE KIT

SR10280063-113 1 WIRE KIT

125 FT X SLEEVING

.166 I.D.

SR10280063-3 (DMS 2109,

Type 1) or equivalent

SR10280063-7 (DMS 2089) or 50 YDS TIE TAPE

equivalent

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: January 06, 2010 DC10-28-252

28 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 3:

Kit SB10280252

New Part Number QTY Name Notes

-7

TA4012F21 2 BRACKET

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

Group 3:

Wire Kit SR10280063

New Part Number QTY QTY Name Notes

-111 -113

DC2426-1C-22NM (DMS 69 FT 48 FT WIRE CODE 801

2426) or equivalent

M39029/22-192 12 9 SOCKET T/C 524

5D0086-3 12 9 TERMINAL LUG 878 (a)

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

Group 4:

Kit SB10280252

New Part Number QTY Name Notes

-9

3D0005-08-10 14 SCREW (a)

3D0005-08-8 27 SCREW (a)

3D0005-3-22 4 SCREW (a)

3D0005-3-26 5 SCREW (a)

3D0005-3-28 2 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 9 TERMINAL LUG 878 (a)

5D0206-20 46 SEALING PLUG (a)

65053-220 23 IN-LINE FUSE

9D0062-3-12-08 2 BRACKET (a)

9D0230-1D080624 3 BRACKET (a)

M39029/22-192 14 SOCKET T/C 524

MS20470AD4-5D 10 RIVET

MS21042L08 60 NUT

MS21042L3 2 NUT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

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29 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 4:

Kit SB10280252

New Part Number QTY Name Notes

-9

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS35338-42 27 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 40 WASHER

NAS1252-8H 8 WASHER

NAS1252-8L 101 WASHER

NAS43DD3-48FC 4 SPACER

NAS43DD3-64FC 5 SPACER

NAS43DD3-72FC 2 SPACER

S7934111-10SA 2 CLAMP (a)

S7934111-11SA 2 CLAMP (a)

S7934111-3SA 11 CLAMP (a)

S7934111-4SA 3 CLAMP (a)

S7934111-7SA 3 CLAMP (a)

S7934111-8SA 3 CLAMP (a)

S7934111-9SA 25 CLAMP (a)

SR10280063-105 1 WIRE KIT

SR10280063-107 1 WIRE KIT

SR10280063-112 1 WIRE KIT

SR10280063-113 1 WIRE KIT

170 FT X SLEEVING

.166 I.D.

SR10280063-3 (DMS 2109, Type

1) or equivalent

15 FT X SLEEVING

.187 I.D.

SR10280063-5 (DMS 2379, Type

4, Class 4) or equivalent

SR10280063-7 (DMS 2089) or 50 YDS TIE TAPE

equivalent

TA4012F21 2 BRACKET

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

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30 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 4:

Kit SB10280252

New Part Number QTY Name Notes

-9

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

Group 4:

Wire Kit SR10280063

New Part Number QTY QTY QTY QTY Name Notes

-105 -107 -112 -113

DC2426-1C-20NM - 14 FT - - WIRE CODE 801

(DMS 2426) or equivalent

DC2426-1C-22NM 43 FT 21 FT 74 FT 48 FT WIRE CODE 801

(DMS 2426) or equivalent

M39029/22-192 5 5 13 9 SOCKET T/C 524

S00023-20P - 5 - - PIN T/C 601/701 (a)

5D0086-3 5 - 13 9 TERMINAL LUG 878 (a)

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

Group 5:

Kit SB10280252

New Part Number QTY Name Notes

-11

3D0005-08-10 16 SCREW (a)

3D0005-08-8 27 SCREW (a)

3D0005-3-22 4 SCREW (a)

3D0005-3-26 5 SCREW (a)

3D0005-3-28 2 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 9 TERMINAL LUG 878 (a)

5D0206-20 50 SEALING PLUG (a)

65053-220 25 IN-LINE FUSE

9D0062-3-12-08 2 BRACKET (a)

9D0230-1D080624 4 BRACKET (a)

M39029/22-192 16 SOCKET T/C 524

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

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31 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 5:

Kit SB10280252

New Part Number QTY Name Notes

-11

MS20470AD4-5D 12 RIVET

MS21042L08 62 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS35338-42 27 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 40 WASHER

NAS1252-8H 8 WASHER

NAS1252-8L 105 WASHER

NAS43DD3-48FC 4 SPACER

NAS43DD3-64FC 5 SPACER

NAS43DD3-72FC 2 SPACER

S7934111-10SA 2 CLAMP (a)

S7934111-12SA 3 CLAMP (a)

S7934111-3SA 11 CLAMP (a)

S7934111-4SA 3 CLAMP (a)

S7934111-7SA 3 CLAMP (a)

S7934111-8SA 3 CLAMP (a)

S7934111-9SA 27 CLAMP (a)

SR10280063-105 1 WIRE KIT

SR10280063-108 1 WIRE KIT

SR10280063-112 1 WIRE KIT

SR10280063-113 1 WIRE KIT

182 FT X SLEEVING

.166 I.D.

SR10280063-3 (DMS 2109, Type

1) or equivalent

20 FT X SLEEVING

.187 I.D.

SR10280063-5 (DMS 2379, Type

4 Class 4) or equivalent

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

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32 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 5:

Kit SB10280252

New Part Number QTY Name Notes

-11

SR10280063-7 (DMS 2089) or 50 YDS TIE TAPE

equivalent

TA4012F21 2 BRACKET

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

Group 5:

Wire Kit SR10280063

New Part Number QTY QTY QTY QTY Name Notes

-105 -108 -112 -113

DC2426-1C-20NM - 14 FT - - WIRE CODE 801

(DMS 2426) or equivalent

DC2426-1C-22NM 43 FT 35 FT 74 FT 48 FT WIRE CODE 801

(DMS 2426) or equivalent

M39029/22-192 5 7 13 9 SOCKET T/C 524

S00023-20P - 7 - - PIN T/C 601/701 (a)

5D0086-3 5 - 13 9 TERMINAL LUG 878 (a)

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

Group 6:

Kit SB10280252

New Part Number QTY Name Notes

-13

3D0005-08-10 8 SCREW (a)

3D0005-08-12 4 SCREW (a)

3D0005-08-8 30 SCREW (a)

3D0005-3-22 1 SCREW (a)

3D0005-3-26 6 SCREW (a)

3D0005-3-28 1 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 13 TERMINAL LUG 878 (a)

5D0206-20 34 SEALING PLUG (a)

65053-220 17 IN-LINE FUSE

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

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33 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 6:

Kit SB10280252

New Part Number QTY Name Notes

-13

9D0062-3F08-10 2 BRACKET (a)

M39029/22-192 4 SOCKET T/C 524

MS20470AD4-5D 4 RIVET

MS21042L08 69 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS35338-42 30 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 30 WASHER

NAS1252-8H 3 WASHER

NAS1252-8L 115 WASHER

NAS43DD3-48FC 1 SPACER

NAS43DD3-64FC 6 SPACER

NAS43DD3-72FC 1 SPACER

NMC1001-1 5 CLAMP (a)

NMC1001-2 3 CLAMP (a)

S7934111-3SA 15 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-9SA 17 CLAMP (a)

SR10280063-104 1 WIRE KIT

SR10280063-106 1 WIRE KIT

SR10280063-109 1 WIRE KIT

SR10280063-110 1 WIRE KIT

SR10280063-111 1 WIRE KIT

SR10280063-113 1 WIRE KIT

160 FT X SLEEVING

.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

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34 of 83

BOEING SERVICE BULLETIN DC10-28-252
Group 6:

Kit SB10280252

New Part Number QTY Name Notes

-13

10 FT X SLEEVING

.187 I.D.

SR10280063-5 (DMS 2379, Type

4, Class 4) or equivalent

SR10280063-7(DMS 2089) or 50 YDS TIE TAPE

equivalent

TA4012F21 2 BRACKET

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

Group 6:

Wire Kit SR10280063

New Part Number QTY QTY QTY QTY QTY QTY Name Notes

-104 -106 -109 -110 -111 -113

DC2426-1C-22NM 7 FT 28 FT 14 FT 14 FT 69 FT 48 FT WIRE CODE 801

(DMS 2426) or

equivalent

M39029/22-192 1 4 2 2 12 9 SOCKET T/C 524

5D0086-3 1 4 2 2 12 9 TERMINAL LUG 878 (a)

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

Group 7:

Kit SB10280252

New Part Number QTY Name Notes

-15

3D0005-08-10 3 SCREW (a)

3D0005-08-8 29 SCREW (a)

3D0005-3-22 1 SCREW (a)

3D0005-3-26 6 SCREW (a)

3D0005-3-28 1 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 10 TERMINAL LUG 878 (a)

5D0206-20 28 SEALING PLUG (a)

65053-220 14 IN-LINE FUSE

M39029/22-192 4 SOCKET T/C 524

MS21042L08 53 NUT

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BOEING SERVICE BULLETIN DC10-28-252
Group 7:

Kit SB10280252

New Part Number QTY Name Notes

-15

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS35338-42 24 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 30 WASHER

NAS1252-8H 3 WASHER

NAS1252-8L 85 WASHER

NAS43DD3-48FC 1 SPACER

NAS43DD3-64FC 6 SPACER

NAS43DD3-72FC 1 SPACER

S7934111-3SA 15 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-9SA 14 CLAMP (a)

SR10280063-104 1 WIRE KIT

SR10280063-110 1 WIRE KIT

SR10280063-111 1 WIRE KIT

SR10280063-113 1 WIRE KIT

140 FT X SLEEVING

.166 I.D.

SR10280063-3 (DMS 2109, Type

1) or equivalent

SR10280063-7 (DMS 2089) or 50 YDS TIE TAPE

equivalent

TA4012F21 2 BRACKET

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

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BOEING SERVICE BULLETIN DC10-28-252
Group 7:

Wire Kit SR10280063

New Part Number QTY QTY QTY QTY Name Notes

-104 -110 -111 -113

DC2426-1C-22NM 7 FT 14 FT 69 FT 48 FT WIRE CODE 801

(DMS 2426) or

equivalent

M39029/22-192 1 2 12 9 SOCKET T/C 524

5D0086-3 1 2 12 9 TERMINAL LUG 878 (a)

(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.

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BOEING SERVICE BULLETIN DC10-28-252
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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:

Chapter Operation

SWPM 20-00-00 General - Maintenance Safety Practices

SWPM 20-00-09 Electrical Identification and Shop Practices

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BOEING SERVICE BULLETIN DC10-28-252
SWPM 20-00-13 Electrical Wire Codes

SWPM 20-00-16 Electrical Wire End Termination Codes

Fabricating and Installing Wire Harness -

Commercial

SWPM 20-10-01

SWPM 20-10-04 Coil and Stow - Maintenance Practices

SWPM 20-20-02 Terminal Blocks - Maintenance Practices

General Installation Hardwares - Maintenance

Practices

SWPM 20-20-03

Power Distribution Bus - Maintenance PracticeSWPM 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:

Panel Number Name/Location Refer to

Access Panel Left MD-10 AMM 06-35-00

Wing Leading Edge

and Vent Box

516AB, 516EB, 526DB, 527AB,

537AB

Access Panel Right MD-10 AMM 06-36-00

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:

Location In Accordance with Appendix

Fuel Tank 1 A

Fuel Tank 2 C

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Location In Accordance with Appendix

Fuel Tank 3 F

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:

Panel Number Name/Location Refer to

Access Panel Left MD-10 AMM 06-35-00

Wing Leading Edge

and Vent Box

516AB, 516EB, 526DB, 527AB,

537AB

Access Panel Right MD-10 AMM 06-36-00

Wing Leading Edge

and Vent Box

616AB, 616EB, 626DB, 627AB,

637AB

Right Main Landing MD-10 AMM 06-27-00

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:

Location In Accordance with Appendix

Fuel Tank 1 A

Fuel Tank 2 C

Fuel Tank 3 F

Upper and Lower Auxiliary Fuel Tanks H

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:

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BOEING SERVICE BULLETIN DC10-28-252
Panel Number Name/Location Refer to

Access Panel Left DC-10 AMM 06-35-00

Wing Leading Edge

and Vent Box

516AB, 516EB, 526DB, 527AB,

537AB

Access Panel Right DC-10 AMM 06-36-00

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:

Location In Accordance with Appendix

Fuel Tank 1 B

Fuel Tank 2 D

Fuel Tank 3 G

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:

Panel Number Name/Location Refer to

Access Panel Left DC-10 AMM 06-35-00

Wing Leading Edge

and Vent Box

516AB, 516EB, 526DB, 527AB,

537AB

Access Panel Right DC-10 AMM 06-36-00

Wing Leading Edge

and Vent Box

616AB, 616EB, 626DB, 627AB,

637AB

Right Main Landing DC-10 AMM 06-27-00

Gear Wheel Well

Right Main Landing Gear Door

Center Cargo Com- DC-10 AMM 06-21-00

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:

Location In Accordance with Appendix

Fuel Tank 1 B

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BOEING SERVICE BULLETIN DC10-28-252
Location In Accordance with Appendix

Fuel Tank 2 E

Fuel Tank 3 G

Aft Auxiliary Fuel Tank K

Upper and Lower Auxiliary Fuel Tanks L

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:

Panel Number Name/Location Refer to

Access Panel Left DC-10 AMM 06-35-00

Wing Leading Edge

and Vent Box

516AB, 516EB, 526DB, 527AB,

537AB

Access Panel Right DC-10 AMM 06-36-00

Wing Leading Edge

and Vent Box

616AB, 616EB, 626DB, 627AB,

637AB

Right Main Landing DC-10 AMM 06-27-00

Gear Wheel Well

Right Main Landing Gear Door

Center Cargo Com- DC-10 AMM 06-21-00

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:

Location In Accordance with Appendix

Fuel Tank 1 B

Fuel Tank 2 E

Fuel Tank 3 G

Upper and Lower Auxiliary Fuel Tanks L

Aft Auxiliary Fuel Tank M

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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:

Panel Number Name/Location Refer to

Access Panels Left Wing DC-10 AMM 06-35-00

Leading Edge and Vent

Box

510KB, 510PB, 520KB,

520RB, 530JB

Access Panels Right Wing DC-10 AMM 06-36-00

Leading Edge and Vent

Box

610KB, 610PB, 620KB,

620RB, 630JB

Left and Right Main Land- DC-10 AMM 06-27-00

ing Gear Wheel Wells

Left and Right Main Landing

Gear Doors

Mid Passenger Compart- DC-10 AMM 06-32-09

ment Floor panel, and

Float Switch Cover

AZZ7656-1, AAL7173-1

Aft Auxiliary fuel tank pan- DC-10 AMM 06-32-11

els, Float Switch Cover

and 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:

Location In Accordance with Appendix

Fuel Tank 1 B

Fuel Tank 2 D

Fuel Tank 3 G

Center Wing Fuel Tanks I

Forward and Aft Auxiliary Fuel Tank J

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.

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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:

Panel Number Name/Location Refer to

Access Panels Left DC-10 AMM 06-35-00

Wing Leading Edge

and Vent Box

510KB, 510PB, 520KB, 520RB,

530JB

Access Panels Right DC-10 AMM 06-36-00

Wing Leading Edge

and Vent Box

610KB, 610PB, 620KB, 620RB,

630JB

Left and Right Main DC-10 AMM 06-27-00

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:

Location In Accordance with Appendix

Fuel Tank 1 B

Fuel Tank 2 D

Fuel Tank 3 G

Center Wing Fuel Tanks I

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.

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BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 1-2.

STEP DESCRIPTION OF TASK MORE DATA

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 F1-1391

within 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 F1-1392

within 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)

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BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 3-7.

STEP DESCRIPTION OF TASK MORE DATA

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)

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BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 1-2.

STEP DESCRIPTION OF TASK MORE DATA

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)

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BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 3, 6-7.

STEP DESCRIPTION OF TASK MORE DATA

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)

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BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 4-5.

STEP DESCRIPTION OF TASK MORE DATA

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

Revision 1 January 06, 2010 DC10-28-252

50 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 1-2.

STEP DESCRIPTION OF TASK MORE DATA

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 F1-122

within 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 F1-123

within 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 F1-178

within 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 F1-1394

within 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 F1-1395

within 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 F1-734

within 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

Revision 1 January 06, 2010 DC10-28-252

51 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 3-7.

STEP DESCRIPTION OF TASK MORE DATA

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 F1-122

within 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 F1-123

within 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 F1-178

within 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 F1-734

within 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

Revision 1 January 06, 2010 DC10-28-252

52 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 2.

STEP DESCRIPTION OF TASK MORE DATA

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

Revision 1 January 06, 2010 DC10-28-252

53 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 6-7.

STEP DESCRIPTION OF TASK MORE DATA

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

Revision 1 January 06, 2010 DC10-28-252

54 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 6.

STEP DESCRIPTION OF TASK MORE DATA

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 F1-1293

within 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 F1-1327

within 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

Revision 1 January 06, 2010 DC10-28-252

55 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 4.

STEP DESCRIPTION OF TASK MORE DATA

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 F1-972

within 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 F1-973

within 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 F1-1361

within 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 F1-1362A

within float level switch reference designator S1-1362 wiring.

4

Install fuel tank float level switch In-line

fuse, reference designator F1-1362B

within 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

Revision 1 January 06, 2010 DC10-28-252

56 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 4-5.

STEP DESCRIPTION OF TASK MORE DATA

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

Revision 1 January 06, 2010 DC10-28-252

57 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 5.

STEP DESCRIPTION OF TASK MORE DATA

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 F1-1381A

within float level switch reference designator S1-1381 wiring.

6

Install fuel tank float level switch In-line

fuse, reference designator F1-1381B

within 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

Revision 1 January 06, 2010 DC10-28-252

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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 6 & 2

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

F1-1391 TK 1 INBD FULL LOOP CONTINUITY S3-1301 1 & 2

F1-1392 TK 1 OUTBD FULL LOOP CONTINUITY S3-1300 1 & 2

F1-119 TK 1 TIP LOOP CONT NOT FULL S3-366 1 & 2

F1-735 L WING OVERFILL (VENT BOX) LOOP CONTINUITY S3-684 1 & 2

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

F1-1394 TK 3 INBD FULL LOOP CONTINUITY S3-1302 1 & 2

F1-1395 TK 3 OUTBD FULL LOOP CONTINUITY S3-1303 1 & 2

F1-124 TK 3 TIP LOOP CONT NOT FULL S3-452 1 & 2

F1-734 R WING OVERFILL (VENT BOX) LOOP CONTINUITY S3-683 1 & 2

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454 2 & 6

F1-1363 TK 2 10000 LB EMPTY CONT TO GND S3-454 3 & GND

F1-1393 TK 2 FULL LOOP CONTINUITY S3-454 7 & 4

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

Revision 1 January 06, 2010 DC10-28-252

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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 6 & 2

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

F1-1391 TK 1 INBD FULL LOOP CONTINUITY S3-1301 1 & 2

F1-1392 TK 1 OUTBD FULL LOOP CONTINUITY S3-1300 1 & 2

F1-119 TK 1 TIP LOOP CONT NOT FULL S3-366 1 & 2

F1-735 L WING OVERFILL LOOP CONTINUITY S3-684 1 & 2 Vent Box

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

F1-1394 TK 3 INBD FULL LOOP CONTINUITY S3-1302 1 & 2

F1-1395 TK 3 OUTBD FULL LOOP CONTINUITY S3-1303 1 & 2

F1-124 TK 3 TIP LOOP CONT NOT FULL S3-452 1 & 2

F1-734 R WING OVERFILL LOOP CONTINUITY S3-683 1 & 2 Vent Box

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454 2 & 6

F1-1363 TK 2 10000 LB EMPTY CONT TO GND S3-454 3

F1-1393 TK 2 FULL LOOP CONTINUITY S3-454 7 & 4

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

Revision 1 January 06, 2010 DC10-28-252

60 of 83

BOEING SERVICE BULLETIN DC10-28-252
RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

F1-1359 UPR AUX FULL LOOP CONTINUITY S3-1186 1 & 2

F1-1360 LWR AUX FULL LOOP CONTINUITY S3-805 4 & 5

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

Revision 1 January 06, 2010 DC10-28-252

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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 6 & 2

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

LOOP CONT NOT S3-366 1 & 2

FULL

F1-119 TK 1 TIP

F1-735 L WING OVERFILL (VENT LOOP CONTINUITY S3-684 1 & 2

BOX)

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

LOOP CONT NOT S3-452 1 & 2

FULL

F1-124 TK 3 TIP

F1-734 R WING OVERFILL (VENT LOOP CONTINUITY S3-683 1 & 2

BOX)

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

S3-454 Pin 2 & Optional 1

Fuse Pin C

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454

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

Revision 1 January 06, 2010 DC10-28-252

62 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 4.

I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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)

a

When 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:

BUS C/B NO. LOCATION

BATT BUS

FUEL TANK FILL VLV & BATT BUS SENS- B1-474 OVERHEAD

ING

APU START PUMP B1-723 OVERHEAD

APU ADVISORY LTS B1-724 OVERHEAD

APU CONTROL & FUEL VLV B1-728 OVERHEAD

BATT DIRECT

GROUND REFUEL PWR B1-475 OVERHEAD

GND REFUEL INV PWR & HI LEVEL TEST B1-479 OVERHEAD

115 VAC - 1

FUEL QTY TRANSFER RELAY B1-499 UPPER MAIN

FUEL QTY NORMAL PWR B1-589 UPPER MAIN

Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 1 OF 8)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

BUS C/B NO. LOCATION

115 VAC - 1 (CONT.)

FUEL PUMP CONTROL TANK 2 FWD B1-609 UPPER MAIN

FUEL PUMP CONTROL TANK 1 FWD B1-615 UPPER MAIN

FUEL PUMP CONTROL TANK 2 TRANS B1-619 UPPER MAIN

UPR & LWR AUX TANK R UPR B1-1206 UPPER MAIN

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 UPPER MAIN

115 VAC - 2

FUEL PUMP CONTROL TANK 2 R AFT B1-603 UPPER MAIN

FUEL PUMP CONTROL TANK 1 TRANSF B1-611 UPPER MAIN

FUEL PUMP CONTROL TANK 3 AFT B1-621 UPPER MAIN

FUEL QTY ALT PWR B1-769 UPPER MAIN

UPR & LWR AUX TANK L UPR B1-1207 UPPER MAIN

AUX TANK L LWR B1-1209 UPPER MAIN

115 VAC - 3

FUEL QTY RPTRS & XFER B1-590 UPPER MAIN

FUEL PUMP CONTROL TANK 1 AFT B1-613 UPPER MAIN

FUEL PUMP CONTROL TANK 3 FWD B1-617 UPPER MAIN

FUEL PUMP CONTROL TANK 2 TRANS B1-757 UPPER MAIN

AUX TANK R LWR B1-1208 UPPER MAIN

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 UPPER MAIN

115 VAC GEN-1

FUEL PUMP POWER TANK 2 FWD B1-608 UPPER MAIN

FUEL PUMP POWER TANK 1 FWD B1-614 UPPER MAIN

FUEL PUMP POWER TANK 3 TRANS B1-618 UPPER MAIN

FUEL PUMP PWR R UPR B1-1250 UPPER MAIN

FUEL PUMP PWR L AFT B1-1647 UPPER MAIN

115 VAC GEN-2

FUEL PUMP POWER TANK 2 R AFT B1-596 UPPER MAIN

FUEL PUMP POWER TANK 1 TRANS B1-610 UPPER MAIN

Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 2 OF 8)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

FUEL PUMP POWER TANK 3 AFT B1-620 UPPER MAIN

FUEL PUMP PWR L UPR B1-1248 UPPER MAIN

FUEL PUMP PWR L LWR B1-1249 UPPER MAIN

BUS C/B NO. LOCATION

115 VAC GEN-3

FUEL PUMP POWER TANK 1 AFT B1-612 UPPER MAIN

FUEL PUMP POWER TANK 3 FWD B1-616 UPPER MAIN

FUEL PUMP POWER TANK 2 TRANS B1-756 UPPER MAIN

FUEL PUMP PWR R LWR B1-1251 UPPER MAIN

FUEL PUMP PWR R AFT B1-1646 UPPER MAIN

115 VAC R EMERGENCY

FUEL PUMP TANK 2 LEFT AFT B1-680 OVERHEAD

28 VDC-1

FUEL X-FEED CONT 1 B1-450 UPPER MAIN

FUEL X-FEED VALVE LT 1 B1-451 UPPER MAIN

L FUEL DUMP VALVE CONT B1-458 UPPER MAIN

FWD PUMPS PRESS LOW LTS B1-498 UPPER MAIN

FUEL PUMP PRESS LOW LTS R AUX B1-1246 UPPER MAIN

28 VDC-2

DUMP V IND & FUEL LOW LVL SHUTOFF B1-452 UPPER MAIN

FUEL X-FEED CONT 2 B1-453 UPPER MAIN

FUEL X-FEED VALVE LT 2 B1-454 UPPER MAIN

R AFT PUMPS PRESS LOW LTS B1-497 UPPER MAIN

FUEL PUMP PRESS LOW LTS L AUX B1-1247 UPPER MAIN

28 VDC-3

FUEL X-FEED CONT 3 B1-455 UPPER MAIN

FUEL X-FEED VALVE LT 3 B1-456 UPPER MAIN

R FUEL DUMP VALVE CONT B1-457 UPPER MAIN

FUEL TK OFF SCHEDULE LTS B1-460 UPPER MAIN

Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 3 OF 8)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

L AFT PUMPS PRESS LOW LTS B1-496 UPPER MAIN

AFT AUX PUMP FUEL CONTROL B1-2004 UPPER MAIN

I-1 Tank 1, 2, 3, UPPER and AFT Test

The 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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

LOOP CONTINU- S3-450 7 & 8

ITY

F1-176 - TANK 1 DUMP

LOOP CONTINU- S3-450 1 & 2

ITY

F1-121 Tank 1 4000 lb

LOOP CONTINU- S3-450 5 & 6

ITY

F1-120 Tank 1 6000 lb

LOOP CONT S3-366 1 & 2

NOT FULL

F1-119 TK 1 TIP

LOOP CONTINU- S3-684 1 & 2

ITY

F1-735 L WING OVERFILL (VENT BOX)

TANK 3

LOOP CONTINU- S3-451 7 & 8

ITY

F1-178 - TANK 3 DUMP

LOOP CONTINU- S3-451 1 & 2

ITY

F1-122 Tank 3 4000 lb

LOOP CONTINU- S3-451 5 & 6

ITY

F1-123 Tank 3 6000 lb

LOOP CONT S3-452 1 & 2

NOT FULL

F1-124 TK 3 TIP

LOOP CONTINU- S3-683 1 & 2

ITY

F1-734 R WING OVERFILL (VENT BOX)

TANK 2

LOOP CONTINU- S3-454 1 & 5

ITY

F1-177 TK 2 DUMP

Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 4 OF 8)

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I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

LOOP CONTINU- S3-454 2 & C Optional 1

ITY

F1-90 TK 2 40000 LB

UPPER AUX TANK

CONT TO GND S3-1186 1 & GND

ON EMPTY

F1-1364 UPPER AUX

LOOP CONT ON S3-1186 2 & 3

EMPTY

F1-1376 UPPER AUX

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

AFT AUX TANK

LOOP CONT R5-4817 S & R

W/PUMP OFF

F1-972

LOOP CONT R5-4817 V & U

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

I-2 The test continues for Auxiliary Tanks.

Use 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-2.1

Verify 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

NAME NUMBER STATUS

FUEL PUMP PWR L UPR B1-1248 OPEN

FUEL PUMP PWR R UPR B1-1250 OPEN

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:

NAME NUMBER STATUS

Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 5 OF 8)

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I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

FUEL PUMP PWR L UPR B1-1248 CLOSED

FUEL PUMP PWR R UPR B1-1250 CLOSED

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.

I-2.2 Verify the position of the following C/Bs to be:

NAME NUMBER STATUS

FUEL PUMP POWER L AFT B1-1647 OPEN

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 OPEN

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 OPEN

GROUND REFUEL POWER B1-475 OPEN

FUEL TANK FILL VALVE & BAT BUS B1-474 OPEN

SENSING

AFT AUX FUEL PUMP CONTROL B1-2004 CLOSED

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:

NAME NUMBER STATUS

FUEL PUMP PWR L AFT B1-1647 CLOSED

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 CLOSED

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 CLOSED

GROUND REFUEL POWER B1-475 CLOSED

FUEL TANK FILL VALVE & BAT BUS B1-474 CLOSED

SENSING

AFT AUX FUEL PUMP CONTROL B1-2004 CLOSED

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-2.3

Access 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)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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 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 & 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:

NAME NUMBER POSITION

GROUND REFUEL POWER B1-475 CLOSED

FUEL TANK FILL VALVE & BAT BUS B1-474 CLOSED

SENSING

Appendix Q: DC-10-30 W/AFT TANK 1500 GALLONS - FUSE FUNCTIONAL TEST

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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.

I-2.4 Verify the position of the following C/Bs to be closed:

NAME NUMBER POSITION

FUEL PUMP POWER L AFT B1-1647 OPEN

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 CLOSED

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 CLOSED

GROUND REFUEL POWER B1-475 OPEN

NAME NUMBER POSITION

FUEL TANK FILL VALVE & BAT BUS B1-474 OPEN

SENSING

AFT AUX FUEL PUMP CONTROL B1-2004 OPEN

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)

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BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 5.

I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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)

a

When 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:

BUS C/B NO. LOCATION

BATT BUS

FUEL TANK FILL VLV & BATT BUS SENS- B1-474 OVERHEAD

ING

APU START PUMP B1-723 OVERHEAD

APU ADVISORY LTS B1-724 OVERHEAD

APU CONTROL & FUEL VLV B1-728 OVERHEAD

BATT DIRECT

GROUND REFUEL PWR B1-475 OVERHEAD

GND REFUEL INV PWR & HI LEVEL TEST B1-479 OVERHEAD

115 VAC - 1

FUEL QTY TRANSFER RELAY B1-499 UPPER MAIN

Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 1 OF 9)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

FUEL QTY NORMAL PWR B1-589 UPPER MAIN

BUS C/B NO. LOCATION

115 VAC - 1 (CONT.)

FUEL PUMP CONTROL TANK 2 FWD B1-609 UPPER MAIN

FUEL PUMP CONTROL TANK 1 FWD B1-615 UPPER MAIN

FUEL PUMP CONTROL TANK 2 TRANS B1-619 UPPER MAIN

UPR & LWR AUX TANK R UPR B1-1206 UPPER MAIN

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 UPPER MAIN

115 VAC - 2

FUEL PUMP CONTROL TANK 2 R AFT B1-603 UPPER MAIN

FUEL PUMP CONTROL TANK 1 TRANSF B1-611 UPPER MAIN

FUEL PUMP CONTROL TANK 3 AFT B1-621 UPPER MAIN

FUEL QTY ALT PWR B1-769 UPPER MAIN

UPR & LWR AUX TANK L UPR B1-1207 UPPER MAIN

AUX TANK L LWR B1-1209 UPPER MAIN

115 VAC - 3

FUEL QTY RPTRS & XFER B1-590 UPPER MAIN

FUEL PUMP CONTROL TANK 1 AFT B1-613 UPPER MAIN

FUEL PUMP CONTROL TANK 3 FWD B1-617 UPPER MAIN

FUEL PUMP CONTROL TANK 2 TRANS B1-757 UPPER MAIN

AUX TANK R LWR B1-1208 UPPER MAIN

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 UPPER MAIN

115 VAC GEN-1

FUEL PUMP POWER TANK 2 FWD B1-608 UPPER MAIN

FUEL PUMP POWER TANK 1 FWD B1-614 UPPER MAIN

FUEL PUMP POWER TANK 3 TRANS B1-618 UPPER MAIN

FUEL PUMP PWR R UPR B1-1250 UPPER MAIN

FUEL PUMP PWR L AFT B1-1647 UPPER MAIN

115 VAC GEN-2

FUEL PUMP POWER TANK 2 R AFT B1-596 UPPER MAIN

Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 2 OF 9)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

FUEL PUMP POWER TANK 1 TRANS B1-610 UPPER MAIN

FUEL PUMP POWER TANK 3 AFT B1-620 UPPER MAIN

FUEL PUMP PWR L UPR B1-1248 UPPER MAIN

FUEL PUMP PWR L LWR B1-1249 UPPER MAIN

BUS C/B NO. LOCATION

115 VAC GEN-3

FUEL PUMP POWER TANK 1 AFT B1-612 UPPER MAIN

FUEL PUMP POWER TANK 3 FWD B1-616 UPPER MAIN

FUEL PUMP POWER TANK 2 TRANS B1-756 UPPER MAIN

FUEL PUMP PWR R LWR B1-1251 UPPER MAIN

FUEL PUMP PWR R AFT B1-1646 UPPER MAIN

115 VAC R EMERGENCY

FUEL PUMP TANK 2 LEFT AFT B1-680 OVERHEAD

28 VDC-1

FUEL X-FEED CONT 1 B1-450 UPPER MAIN

FUEL X-FEED VALVE LT 1 B1-451 UPPER MAIN

L FUEL DUMP VALVE CONT B1-458 UPPER MAIN

FWD PUMPS PRESS LOW LTS B1-498 UPPER MAIN

FUEL PUMP PRESS LOW LTS R AUX B1-1246 UPPER MAIN

28 VDC-2

DUMP V IND & FUEL LOW LVL SHUTOFF B1-452 UPPER MAIN

FUEL X-FEED CONT 2 B1-453 UPPER MAIN

FUEL X-FEED VALVE LT 2 B1-454 UPPER MAIN

R AFT PUMPS PRESS LOW LTS B1-497 UPPER MAIN

FUEL PUMP PRESS LOW LTS L AUX B1-1247 UPPER MAIN

28 VDC-3

FUEL X-FEED CONT 3 B1-455 UPPER MAIN

FUEL X-FEED VALVE LT 3 B1-456 UPPER MAIN

R FUEL DUMP VALVE CONT B1-457 UPPER MAIN

Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 3 OF 9)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

FUEL TK OFF SCHEDULE LTS B1-460 UPPER MAIN

L AFT PUMPS PRESS LOW LTS B1-496 UPPER MAIN

AFT AUX PUMP FUEL CONTROL B1-2004 UPPER MAIN

I-1 Tank 1, 2, 3, UPPER AND AFT Test

The 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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

LOOP CONTI- S3-450 7 & 8

NUITY

F1-176 - TANK 1 DUMP

LOOP CONTI- S3-450 1 & 2

NUITY

F1-121 Tank 1 4000 lb

LOOP CONTI- S3-450 5 & 6

NUITY

F1-120 Tank 1 6000 lb

LOOP CONT S3-366 1 & 2

NOT FULL

F1-119 TK 1 TIP

LOOP CONTI- S3-684 1 & 2

NUITY

F1-735 L WING OVERFILL (VENT BOX)

TANK 3

LOOP CONTI- S3-451 7 & 8

NUITY

F1-178 - TANK 3 DUMP

LOOP CONTI- S3-451 1 & 2

NUITY

F1-122 Tank 3 4000 lb

LOOP CONTI- S3-451 5 & 6

NUITY

F1-123 Tank 3 6000 lb

LOOP CONT S3-452 1 & 2

NOT FULL

F1-124 TK 3 TIP

LOOP CONTI- S3-683 1 & 2

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)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

LOOP CONTI- S3-454 1 & 5

NUITY

F1-177 TK 2 DUMP

LOOP CONTI- S3-454 2 & C Optional 1

NUITY

F1-90 TK 2 40000 LB

UPPER AUX TANK

1 &

GND

CONT TO S3-1186

GND ON

EMPTY

F1-1364 UPPER AUX

LOOP CONT S3-1186 2 & 3

ON EMPTY

F1-1376 UPPER AUX

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

AFT AUX TANK

LOOP CONT R5-4817 S & R

W/PUMP OFF

F1-972

LOOP CONT R5-4817 V & U

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

I-2 The test continues for Auxiliary Tanks.

Bring the airplane to the following configuration: Tank 1, 2 & 3 minimum 12000 pounds, UPR tank

6000 pounds and LWR tank full with fuel.

I-2.1

Verify 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

NAME NUMBER STATUS

FUEL PUMP PWR L UPR B1-1248 OPEN

FUEL PUMP PWR R UPR B1-1250 OPEN

Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 5 OF 9)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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:

NAME NUMBER STATUS

FUEL PUMP PWR L UPR B1-1248 CLOSED

FUEL PUMP PWR R UPR B1-1250 CLOSED

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.

I-3.2 Verify the position of the following C/Bs to be:

NAME NUMBER STATUS

FUEL PUMP POWER L AFT B1-1647 OPEN

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 OPEN

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 OPEN

GROUND REFUEL POWER B1-475 OPEN

FUEL TANK FILL VALVE & BAT BUS B1-474 OPEN

SENSING

AFT AUX FUEL PUMP CONTROL B1-2004 CLOSED

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:

NAME NUMBER STATUS

FUEL PUMP PWR L AFT B1-1647 CLOSED

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 CLOSED

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 CLOSED

Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 6 OF 9)

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Copyright © Unpublished Work - See page 1 for details.

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76 of 83

BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

GROUND REFUEL POWER B1-475 CLOSED

FUEL TANK FILL VALVE & BAT BUS B1-474 CLOSED

SENSING

AFT AUX FUEL PUMP CONTROL B1-2004 CLOSED

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)

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Copyright © Unpublished Work - See page 1 for details.

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77 of 83

BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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:

NAME NUMBER POSITION

GROUND REFUEL POWER B1-475 CLOSED

FUEL TANK FILL VALVE & BAT BUS B1-474 CLOSED

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.

I-3.4 Verify the position of the following C/Bs to be:

NAME NUMBER POSITION

FUEL PUMP POWER L AFT B1-1647 OPEN

FUEL PUMP CONTROL L AFT AUX TANK B1-1645 CLOSED

FUEL PUMP CONTROL R AFT AUX TANK B1-1644 CLOSED

GROUND REFUEL POWER B1-475 OPEN

FUEL TANK FILL VALVE & BAT BUS B1-474 OPEN

SENSING

AFT AUX FUEL PUMP CONTROL B1-2004 OPEN

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.

I-3.5 Transfer fuel to AFT AUX tank from UPR AUX tank and then from tanks 1 and 3 as follows:

Appendix R: DC-10-30 W/AFT TANK 3200 GALLONS - FUSE FUNCTIONAL TEST

(SHEET 8 OF 9)

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78 of 83

BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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

NAME NUMBER POSITION

FUEL TK OFF SCHEDULE LTS B1-460 UPPER MAIN

FUEL PUMPS PRESS LOW LTS R AUX B1-1246 FLT ENG UPPR MAIN CB PNL

FUEL PUMPS PRESS LOW LTS L AUX B1-1247 FLT ENG UPPR MAIN CB PNL

Gain 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

Revision 1 January 06, 2010 DC10-28-252

79 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 6.

I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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.

I-1 Tank 1, 2, 3, CENTER WING, FWD AUX. and AFT AUX. Test

The 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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

LOOP CONTI- S3-450 7 & 8

NUITY

F1-176 - TANK 1 DUMP

LOOP CONTI- S3-450 1 & 2

NUITY

F1-121 Tank 1 4000 lb

LOOP CONTI- S3-450 5 & 6

NUITY

F1-120 Tank 1 6000 lb

LOOP CONT S3-366 1 & 2

NOT FULL

F1-119 TK 1 TIP

LOOP CONTI- S3-684 1 & 2

NUITY

F1-735 L WING OVERFILL (VENT BOX)

TANK 3

LOOP CONTI- S3-451 7 & 8

NUITY

F1-178 - TANK 3 DUMP

LOOP CONTI- S3-451 1 & 2

NUITY

F1-122 Tank 3 4000 lb

LOOP CONTI- S3-451 5 & 6

NUITY

F1-123 Tank 3 6000 lb

Appendix S: DC-10-30F (KC-10A) - FUSE FUNCTIONAL TEST

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

LOOP CONT S3-452 1 & 2

NOT FULL

F1-124 TK 3 TIP

LOOP CONTI- S3-683 1 & 2

NUITY

F1-734 R WING OVERFILL (VENT BOX)

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 2

LOOP CONTI- S3-454 1 & 5

NUITY

F1-177 TK 2 DUMP

LOOP CONTI- S3-454 2 & C Optional 1

NUITY

F1-90 TK 2 40000 LB

AFT AUX TANK

LOOP CONTI- S3-1110 2 & 5

NUITY

F1-1327 AFT FUS LL

FWD AUX TANK

LOOP CONTI- S3-1277 2 & 14

NUITY

F1-1277 FWD FUS LL

LOOP CONTI- S3-1109 12 & 13

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.

I-1 AERIAL REFUELING PUMP CONTROL FLOAT SWITCHES

I-1.1 To perform this test minimum 7000 lbs fuel is necessary in the UPR Aux tank.

After 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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

CENTER WING TANKS

LOOP CONTI- S3-802 5 & 6

NUITY

CENTER WING FUEL TANK LOW LEVEL R,

F1-1374

LOOP CONT S3-803 5 & 6

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

Revision 1 January 06, 2010 DC10-28-252

81 of 83

BOEING SERVICE BULLETIN DC10-28-252
This Appendix applies only to: Group 7.

I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

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.

I-1 Tank 1, 2, 3, and CENTER WING Test

The 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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

LOOP CONTI- S3-450 7 & 8

NUITY

F1-176 - TANK 1 DUMP

LOOP CONTI- S3-450 1 & 2

NUITY

F1-121 Tank 1 4000 lb

LOOP CONTI- S3-450 5 & 6

NUITY

F1-120 Tank 1 6000 lb

LOOP CONT S3-366 1 & 2

NOT FULL

F1-119 TK 1 TIP

LOOP CONTI- S3-684 1 & 2

NUITY

F1-735 L WING OVERFILL (VENT BOX)

TANK 3

LOOP CONTI- S3-451 7 & 8

NUITY

F1-178 - TANK 3 DUMP

LOOP CONTI- S3-451 1 & 2

NUITY

F1-122 Tank 3 4000 lb

LOOP CONTI- S3-451 5 & 6

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

Revision 1 January 06, 2010 DC10-28-252

82 of 83

BOEING SERVICE BULLETIN DC10-28-252
I RETURN-TO SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

LOOP CONT S3-452 1 & 2

NOT FULL

F1-124 TK 3 TIP

LOOP CONTI- S3-683 1 & 2

NUITY

F1-734 R WING OVERFILL (VENT BOX)

TANK 2

LOOP CONTI- S3-454 1 & 5

NUITY

F1-177 TK 2 DUMP

LOOP CONTI- S3-454 2 & C Optional 1

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.

I-1 AERIAL REFUELING PUMP CONTROL FLOAT SWITCHES

I-1.1 To perform this test minimum 7000 lbs fuel is necessary in the UPR Aux tank.

After 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.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

CENTER WING TANKS

LOOP CONTI- S3-802 5 & 6

NUITY

CENTER WING FUEL TANK LOW LEVEL R,

F1-1374

LOOP CONT S3-803 5 & 6

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

Revision 1 January 06, 2010 DC10-28-252

83 of 83

BOEING SERVICE BULLETIN DC10-28-252