# Boeing Service Bulletin DC9-28-217: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2010-0958; AD 2011-07-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin DC9-28-217](https://openairdocs.org/service-documents/boeing/dc9-28-217.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 166
- PDF: https://openairdocs.org/files/sha256/c5/e5/c5e599d050f2c6865cb598d0989b936c1bf513bdb7c1178bc7c58e3190ec3041
- Page: https://openairdocs.org/service-documents/boeing/dc9-28-217/file/c5e599d050f2

## Text

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### Page 1

Commercial 
Airplanes
DC9
Service Bulletin
Number: DC9-28-217
Original Issue: December 01, 2009
Revision 1: August 12, 2010
ATA System: 2821 2822
SUBJECT: FUEL - Switch Fuel Level Float - Fuel Level Float and Pressure Switch In-Line Fuse
Installation
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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 6
B. Concurrent Requirements ...................................... 2 7
C. Reason ................................................ 2 7
D. Description .............................................. 2 7
E. Compliance .............................................. 3 0
F. Approval ............................................... 3 0
G. Manpower .............................................. 3 0
H. Weight and Balance Changes .................................... 3 6
I. Electrical Load Data ......................................... 3 8
J. References .............................................. 3 8
1. Existing Data .......................................... 3 8
2. Data supplied with this Service Bulletin ............................ 3 8
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 3 9
4. Process Data: ......................................... 3 9
K. Publications Affected ........................................ 3 9
L. Interchangeability and Intermixability of Parts ........................... 3 9
2. MATERIAL INFORMATION ........................................ 4 1
A. Material - Price and Availability ................................... 4 1
B. Industry Support Information .................................... 4 1
C. Parts Necessary For Each Airplane ................................. 4 2
1. Kits/Parts ............................................ 4 2
2. Parts and Materials Supplied by the Operator ........................ 5 5
3. Parts Modified and Reidentified ................................ 5 8
4. Parts Removed and Not Replaced .............................. 5 8
D. Parts Necessary to Change Spares ................................. 5 8
E. Special Tooling - Price and Availability ............................... 5 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 5 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 1
A. GENERAL INFORMATION ..................................... 6 1
B. WORK INSTRUCTIONS ....................................... 6 2
FIGURE 1: FUEL LEVEL FLOAT SWITCH IN-LINE FUSE INSTALLATION [Group 1] ......... 8 8
FIGURE 2: FUEL LEVEL FLOAT SWITCH IN-LINE FUSE INSTALLATION [Group 2] ......... 9 1
FIGURE 3: FUEL LEVEL FLOAT SWITCH IN-LINE FUSE INSTALLATION [Group 3] ......... 9 3
FIGURE 4: FUEL LEVEL FLOAT SWITCH IN-LINE FUSE INSTALLATION [Group 4] ......... 9 6
FIGURE 5: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 5]
.................................................. 9 9
FIGURE 6: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 6]
................................................. 1 0 2
FIGURE 7: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 7]
................................................. 1 0 5
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FIGURE 8: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 8]
................................................. 1 0 8
FIGURE 9: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 9]
................................................. 1 1 1
FIGURE 10: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 10]
................................................. 1 1 4
FIGURE 11: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 11]
................................................. 1 1 8
FIGURE 12: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 12]
................................................. 1 2 1
FIGURE 13: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 13]
................................................. 1 2 4
FIGURE 14: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 14]
................................................. 1 2 7
FIGURE 15: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 15]
................................................. 1 3 1
FIGURE 16: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 16]
................................................. 1 3 4
FIGURE 17: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 17]
................................................. 1 3 7
FIGURE 18: FUEL LEVEL FLOAT AND PRESSURE SWITCH IN-LINE FUSE INSTALLATION [Group 18]
................................................. 1 4 1
FIGURE 19: FUEL LEVEL FLOAT SWITCH IN-LINE FUSE INSTALLATION [Group 19] ........ 1 4 5
APPENDIX A: CONTINUITY CHECK [Group 1] ............................... 1 4 8
APPENDIX B: CONTINUITY CHECK [Group 2] ............................... 1 4 9
APPENDIX C: CONTINUITY CHECK [Group 3] ............................... 1 5 0
APPENDIX D: CONTINUITY CHECK [Group 4] ............................... 1 5 1
APPENDIX E: CONTINUITY CHECK [Group 5] ............................... 1 5 2
APPENDIX F: CONTINUITY CHECK [Group 6] ............................... 1 5 3
APPENDIX G: CONTINUITY CHECK [Group 7] ............................... 1 5 4
APPENDIX H: CONTINUITY CHECK [Group 8] ............................... 1 5 5
APPENDIX I: CONTINUITY CHECK [Group 9] ............................... 1 5 6
APPENDIX J: CONTINUITY CHECK [Group 10] .............................. 1 5 7
APPENDIX K: CONTINUITY CHECK [Group 11] .............................. 1 5 8
APPENDIX L: CONTINUITY CHECK [Group 12] .............................. 1 5 9
APPENDIX M: CONTINUITY CHECK [Group 13] .............................. 1 6 0
APPENDIX N: CONTINUITY CHECK [Group 14] .............................. 1 6 1
APPENDIX O: CONTINUITY CHECK [Group 15] .............................. 1 6 2
APPENDIX P: CONTINUITY CHECK [Group 16] .............................. 1 6 3
APPENDIX Q: CONTINUITY CHECK [Group 17] .............................. 1 6 4
APPENDIX R: CONTINUITY CHECK [Group 18] .............................. 1 6 5
APPENDIX S: CONTINUITY CHECK  [Group 19] .............................. 1 6 6
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Commercial 
Airplanes
DC9
Service Bulletin
Revision Transmittal SheetNumber: DC9-28-217Original Issue: December 01, 2009
Revision 1: August 12, 2010
ATA System: 2821 2822
SUBJECT: FUEL - Switch Fuel Level Float - Fuel Level Float and Pressure Switch In-Line Fuse
Installation
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
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.
No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.
REASON FOR REVISION
This revision is sent to incorporate engineering released subsequent to the Original Issue of this service bulletin,
which adds a new configuration. The new configuration consists of airplanes that were previously in Group 3
but also had forward and rear auxiliary fuel tanks. This revision adds Group 19 consisting of the airplanes with
forward and rear auxiliary fuel tanks that were previously included in Group 3.
These sections were changed:
1. In Paragraph 1.A., Effectivity, added Group 19, which consists of airplanes previously in Group 3.
2. In Paragraph 1.D., Description, changed description and maintenance zone tables to account for Group
19.
3. In Paragraph 1.G., Manpower, changed tables to account for Group 19 and to include data for applicable
figures.
4. In Paragraph 1.H., Weight and Balance Changes, changed tables to account for Group 19.
5. In Paragraph 1.J.2.a., Drawings, changed drawing revision letter.
6. In Paragraph 1.J.4., Process Data, added process specification statement.
7. In Paragraph 2.A., Material - Price and Availability, added SB09280217-39 Service Kit, updated pricing and
Reorder Lead Time (ROLT).
8. In Paragraph 2.C.1., Kits/Parts, added SB09280217-39 Service Kit table and SB09280217-37 Wire Package
data.
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9. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added Group 19 to applicable parts
table.
10. In Paragraph 3.A., General Information, changed Note 7 and added Notes 10, 11, 12 and 13.
11. In Paragraph 3.B., Work Instructions, added work instructions for Group 19.
12. Added Figure 19 and Appendix S, which are applicable to Group 19.
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
December 01, 2009Original Issue:
August 12, 2010Revision 1:
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Commercial 
Airplanes
DC9
Service Bulletin
SummaryNumber: DC9-28-217Original Issue: December 01, 2009
Revision 1: August 12, 2010
ATA System: 2821 2822
SUBJECT: FUEL - Switch Fuel Level Float - Fuel Level Float and Pressure Switch In-Line Fuse
Installation
CONCURRENT REQUIREMENTS
None.
BACKGROUND
An investigation by Boeing has determined that fuel level float switch wires located on the left and right wing
forward spars, the center tank forward spar, and the forward and aft auxiliary fuel tanks and pressure switch
wires located on the forward and aft auxiliary fuel tanks are routed in the same bundles as power wires. If a
short circuit between a fuel level float or pressure switch wire and a power wire occurs, an over current can
cause excessive temperature in the fuel level float or pressure switch wire, resulting in damage and become a
potential ignition source. Adding an in-line fuse as a self-contained component in each fuel level float and
pressure switch circuit will minimize the possibility of excessive temperatures in the fuel level float or pressure
switch wires. If not corrected, and there is a short circuit of a fuel level float or pressure switch wire to a power
wire, possible damage to the fuel level float or 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, 3-4:
This service bulletin installs fuel level float switch in-line fuses on the left and right wing forward spars and the
center wing forward spar.
Group 2:
This service bulletin installs fuel level float switch in-line fuses on the left and right wing forward spars.
Group 5:
This service bulletin installs fuel level float and pressure switch in-line fuses on the left and right wing forward
spars, the center wing forward spar and the aft auxiliary fuel tank.
Group 6-9, 11-13, 15-16:
This service bulletin installs fuel level float and pressure switch in-line fuses on the left and right wing forward
spars, the center wing forward spar, and the forward auxiliary fuel tank.
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Group 10, 14, 17-18:
This service bulletin installs fuel level float and pressure switch in-line fuses on the left and right wing forward
spars, the center wing forward spar, and the forward and aft auxiliary fuel tanks.
Group 19:
This service bulletin installs fuel level float switch in-line fuses on the left and right wing forward spars, the center
wing forward spar, and the forward and aft auxiliary fuel tanks.
EFFECTIVITY
DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32(VC-9C), DC-9-32F, DC-9-32F(C-9A),
DC-9-32F(C9-B), DC-9-33F, DC-9-34, DC-9-34F, DC9-41 and DC-9-51 Airplanes. Refer to Paragraph 1.A.1.,
Airplanes for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends 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
Elapsed HoursTotal Task HoursGroup(s)
5.210.41, 3
3.87.62
6.412.84, 6, 8, 11-12, 15-16
7.615.25, 7, 9, 13
8.416.810, 14, 17-18
7.014.019
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN DC9-28-217
FUEL LEVEL FLOAT AND
PRESSURE SWITCH IN-LINE
FUSE INSTALLATION
1824389
Original Issue: December 01, 2009
Revision 1: August 12, 2010  BOEING PROPRIETARY -  DC9-28-217
Copyright © Unpublished Work - See page 1 for details.  9 of 166

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Commercial 
Airplanes
DC9
Service Bulletin
Number: DC9-28-217
Original Issue: December 01, 2009
Revision 1: August 12, 2010
ATA System: 2821 2822
SUBJECT: FUEL - Switch Fuel Level Float - Fuel Level Float and Pressure Switch In-Line Fuse
Installation
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
NOTE: The intent of this installation was done on fuselage number 834 prior to the original issue
of this service bulletin in accordance with Service Rework Drawing SR09280100 Revision
B.
DESCRIPTIONCONFIGURATIONGROUP
DC-9-14, DC-9-15 and DC-9-15F airplanes with left wing, right wing
and center wing fuel tanks affected by SR09280100-7001 and -7021
drawing configurations.
-1
DC-9-14 airplanes with left wing and right wing fuel tanks affected
by SR09280100-7011 and -7023 drawing configurations.
-2
DC-9-21, DC-9-31, DC-9-32, DC-9-32F, DC-9-33F, and DC-9-51
airplanes with left wing, right wing and center wing fuel tanks affected
by SR09280100-7001 and -7025 drawing configurations.
-3
DC-9-32 and DC-9-32F airplanes with left wing, right wing and center
wing fuel tanks affected by SR09280100-7013 and -7027 drawing
configurations.
-4
DC-9-34F airplanes with left wing, right wing, center wing and aft
auxiliary fuel tanks affected by SR09280100-7003 and -7029 drawing
configurations.
-5
DC-9-32 and DC-9-33F airplanes with left wing, right wing, center
wing and forward auxiliary fuel tanks affected by SR09280100-7005
and -7031 drawing configurations.
-6
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DESCRIPTIONCONFIGURATIONGROUP
DC-9-31, DC-9-32, DC-9-32F and DC-9-33F airplanes with left wing,
right wing, center wing and forward auxiliary fuel tanks affected by
SR09280100-7007 and -7033 drawing configurations.
-7
DC-9-32 and DC-9-33F airplanes with left wing, right wing, center
wing and forward auxiliary fuel tanks affected by SR09280100-7005
and -7035 drawing configurations.
-8
DC-9-32 airplanes with left wing, right wing, center wing and forward
auxiliary fuel tanks affected by SR09280100-7007 and -7037 drawing
configurations.
-9
DC-9-34 and DC-9-34F airplanes with left wing, right wing, center
wing, forward auxiliary and aft auxiliary fuel tanks affected by
SR09280100-7009 and -7039 drawing configurations.
-10
DC-9-41 airplanes with left wing, right wing, center wing and forward
auxiliary fuel tanks affected by SR09280100-7005 and -7041 drawing
configurations.
-11
DC-9-41 airplanes with left wing, right wing, center wing and forward
auxiliary fuel tanks affected by SR09280100-7005 and -7043 drawing
configurations.
-12
DC-9-41 airplanes with left wing, right wing, center wing and forward
auxiliary fuel tanks affected by SR09280100-7007 and -7045 drawing
configurations.
-13
DC-9-41 airplanes with left wing, right wing, center wing, forward
auxiliary and aft auxiliary fuel tanks affected by SR09280100-7009
and -7047 drawing configurations.
-14
DC-9-51 airplanes with left wing, right wing, the center wing, and the
forward auxiliary fuel tanks affected by SR09280100-7005 and -7049
drawing configurations.
-15
DC-9-51 airplanes with left wing, right wing, center wing and forward
auxiliary fuel tanks affected by SR09280100-7005 and -7051 drawing
configurations.
-16
DC-9-51 airplanes with left wing, right wing, center wing, forward
auxiliary and aft auxiliary fuel tanks affected by SR09280100-7009
and -7053 drawing configurations.
-17
DC-9-51 airplanes with left wing, right wing, center wing, forward
auxiliary and aft auxiliary fuel tanks affected by SR09280100-7009
and -7055 drawing configurations.
-18
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DESCRIPTIONCONFIGURATIONGROUP
DC-9-32, DC-9-32(VC-9C), DC-9-32F, DC-9-32F(C-9A),
DC-9-32F(C-9B), and DC-9-34 airplanes with left wing, right wing,
center wing, forward auxiliary and aft auxiliary fuel tanks affected by
SR09280100-7015 and -7057 drawing configurations.
-19
Airplane Models:
DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32(VC-9C), DC-9-32F,
DC-9-32F(C-9A), DC-9-32F(C-9B), DC-9-33F, DC-9-34, DC-9-34F, DC-9-41, DC-9-51
GroupFuselage Num-
ber
12
14
17
19 - 10
115
216
117 - 19
123
129 - 30
132
134 - 35
237
139
141
145 - 46
150 - 51
154 - 57
159
161 - 62
164
167 - 69
171 - 72
175 - 76
179
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GroupFuselage Num-
ber
381
182
184
386 - 87
190
193 - 94
395 - 96
197
398 - 99
1101 - 102
3103 - 104
3108
1115
3117
3123 - 124
1125
1127
1129
3130
7132
9133
7135
4136
3137 - 138
1139 - 141
9144
7145
1147
3150 - 151
4154
1156
9159
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GroupFuselage Num-
ber
1165
9167
4168
3169
1170
7172
7174
3177
1178
4179 - 180
4183
1184
1186
7187
4189 - 190
3191
3193
1194
4195
7198
7200
7205
1207
7208
9213
7214
1216
13218
1219
7220 - 221
1224
3227
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GroupFuselage Num-
ber
1228
7229 - 230
3232 - 233
1234
7235 - 236
4237
3239
7240
3243
7246
3247
3249
7251 - 252
3255 - 256
3258 - 259
13261
7263
9264
3266 - 267
4268
3270
3272
7273
3275 - 276
9278
4279
7280
19281
3282 - 283
7286
3292
3294 - 295
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GroupFuselage Num-
ber
4296
3297
3301
9302
19304
13308
3309 - 310
7311
4312
7314
4317
3318
13319
3320
9321
3322
13323
7324
3326
3329
3331
13335
7337
9339
19340
3342
7343
7347
3351
9353
13354
13359
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GroupFuselage Num-
ber
13364
3365
9367
13369
3370
3376
19377
3382
9383 - 384
6385 - 387
3389 - 391
9394
4395
4397
19399
3401
9402
1405
6411
6413
3415 - 416
19421
6423
6425
9427
3429
19438
3439
3444
6445
9446
6447
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GroupFuselage Num-
ber
3450 - 452
19458
6459
3460
3462
3464 - 465
6467 - 469
3474
6476
3479
6480
3482
9483
3485 - 486
3488 - 492
6497
3498
3501 - 502
3505
3507
3512
6514
3515
6517
3518
3520 - 521
4527
3529
19530
3533 - 536
9538
19539
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GroupFuselage Num-
ber
3540 - 541
8543
3545
3547
19548
3551
19552
3554
13555
13557
13559
3560
13562
6564
13566
13568
6569
6573
12575
9576
3583
8584
3589
9593
3596 - 599
12601
3602
12604
9605
3606
9607
3609
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GroupFuselage Num-
ber
9610
3611
3617 - 618
6619
6621
3622 - 623
6630
3633
8637 - 638
3642
12643
3644
12645
8646
19647
19650
19653
6654
9655
19656
9658
19659
9661
19662
9664
19665
19668
6669
19670
6671
6673
6675
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GroupFuselage Num-
ber
12677 - 679
3684
19686
3691
19692
3694
19696
19698
19700
19702
19704
3706
19707
3708 - 709
3711
9712
12714
6715
3718
9719
3721
3723
11724
9726
12728
11732
11736
12740
12743
6750
14751
6754
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GroupFuselage Num-
ber
18757
14759
3760
6761
18763
19765
11768
19769
3771
6772
3773
19774
11777
6778 - 779
18780
6781
18783
19784
19786
18787
15788
6793
19795
15796
18798
19801
18805 - 808
19809
18810
19811
15813 - 814
3815
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GroupFuselage Num-
ber
10817
15818
10819
3820
10821
6822
10823
3825
18827
6828
18829 - 830
15833 - 834
6835
6837
3838
15841 - 842
19843
15845
3847 - 848
15852 - 854
17857
17859
16860 - 864
11871
5872
18873
11874 - 876
15877
3879
15880 - 881
18883
15884
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GroupFuselage Num-
ber
11887
15888 - 889
18890 - 891
15892 - 893
11894 - 895
18899
6900 - 901
18902
15904 - 905
6908
15912
6913 - 915
6918
3919
3921 - 922
6923
6926
16927
10929
6930
16931 - 932
19934
16935 - 937
16939
3940
3942 - 943
16945
3947
3949
3951
19954
6956
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GroupFuselage Num-
ber
6959
3961
3964
3968
18980
19982
16984
18987
16990
18993
31014
31017
31021
31024
31027
31030
31033
31039
31042
31044
31046
31048
31050
31052
31054
31056
31058
191081
191084
2. Spares Affected
None.
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B. Concurrent Requirements
None.
C. Reason
An investigation by Boeing has determined that fuel level float switch wires located on the left and right
wing forward spars, the center tank forward spar, and the forward and aft auxiliary fuel tanks and
pressure switch wires located on the forward and aft auxiliary fuel tanks are routed in the same bundles
as power wires. If a short circuit between a fuel level float or pressure switch wire and a power wire
occurs, an over current can cause excessive temperature in the fuel level float or pressure switch wire,
resulting in damage and become a potential ignition source. Adding an in-line fuse as a self-contained
component in each fuel level float and pressure switch circuit will minimize the possibility of excessive
temperatures in the fuel level float or pressure switch wires. If not corrected, and there is a short circuit
of a fuel level float or pressure switch wire to a power wire, possible damage to the fuel level float or
pressure switch wire could occur, and become a potential ignition source for the fuel tank.
Revision 1 is sent to incorporate engineering released subsequent to the Original Issue of this service
bulletin, which adds a new configuration. The new configuration consists of airplanes that were previously
in Group 3 but also had forward and rear auxiliary fuel tanks. This revision adds Group 19 consisting
of the airplanes with forward and rear auxiliary fuel tanks that were previously included in Group 3.
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.
D. Description
Group 1, 3-4:
This service bulletin installs fuel level float switch in-line fuses on the left and right wing forward spars
and the center wing forward spar.
Group 2:
This service bulletin installs fuel level float switch in-line fuses on the left and right wing forward spars.
Group 5:
This service bulletin installs fuel level float and pressure switch in-line fuses on the left and right wing
forward spars, the center wing forward spar and the aft auxiliary fuel tank.
Group 6-9, 11-13, 15-16:
This service bulletin installs fuel level float and pressure switch in-line fuses on the left and right wing
forward spars, the center wing forward spar, and the forward auxiliary fuel tank.
Group 10, 14, 17-18:
This service bulletin installs fuel level float and pressure switch in-line fuses on the left and right wing
forward spars, the center wing forward spar, and the forward and aft auxiliary fuel tanks.
Group 19:
This service bulletin installs fuel level float switch in-line fuses on the left and right wing forward spars,
the center wing forward spar, and the forward and aft auxiliary fuel tanks.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin.
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The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
11, 12, 23DC-9-14, DC-9-15, DC-9-15F
Group 2:
Affected Maintenance Zones
ZoneModel
11, 12DC-9-14
Group 3:
Affected Maintenance Zones
ZoneModel
11, 12, 23DC-9-21, DC-9-31, DC-9-32,
DC-9-32F, DC-9-33F, DC-9-51
Group 4:
Affected Maintenance Zones
ZoneModel
11, 12, 23DC-9-32, DC-9-32F
Group 5:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 57DC-9-34F
Group 6, 8:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51DC-9-32, DC-9-33F
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Group 7:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51DC-9-31, DC-9-32, DC-9-32F,
DC-9-33F
Group 9:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51DC-9-32
Group 10:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51, 57DC-9-34, DC-9-34F
Group 11-13:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51DC-9-41
Group 14:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51, 57DC-9-41
Group 15-16:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51DC-9-51
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Group 17-18:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51, 57DC-9-51
Group 19:
Affected Maintenance Zones
ZoneModel
11, 12, 23, 51, 57DC-9-32, DC-9-32(VC-9C), DC-
9-32F, DC-9-32F(C-9A), DC-9-
32F(C-9B), DC-9-34
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
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 tables below show an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
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Group 1:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
1.42.82Install Hardware
0.30.62FIGURE 1
0.30.62Test
1.63.22Close Access
5.210.4TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.12.22Open Access
1.02.02Install Hardware
0.40.82FIGURE 2
0.20.42Test
1.12.22Close Access
3.87.6TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
1.42.82Install Hardware
0.30.62FIGURE 3
0.30.62Test
1.63.22Close Access
5.210.4TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
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Group 4:
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.40.82FIGURE 4
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 5:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.83.62Open Access
3.06.02Install Hardware
0.51.02FIGURE 5
0.51.02Test
1.83.62Close Access
7.615.2TOTAL FOR EACH AIRPLANE
Group 6:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
0.40.82FIGURE 6
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 7:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.83.62Open Access
3.06.02Install Hardware
0.51.02FIGURE 7
0.51.02Test
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Group 7:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.83.62Close Access
7.615.2TOTAL FOR EACH AIRPLANE
Group 8:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
0.40.82FIGURE 8
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 9:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.83.62Open Access
3.06.02Install Hardware
0.51.02FIGURE 9
0.51.02Test
1.83.62Close Access
7.615.2TOTAL FOR EACH AIRPLANE
Group 10:
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.24.42Open Access
3.06.02Install Hardware
0.51.02FIGURE 10
0.51.02Test
2.24.42Close Access
8.416.8TOTAL FOR EACH AIRPLANE
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Group 11:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
0.40.82FIGURE 11
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 12:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
0.40.82FIGURE 12
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 13:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.83.62Open Access
3.06.02Install Hardware
0.51.02FIGURE 13
0.51.02Test
1.83.62Close Access
7.615.2TOTAL FOR EACH AIRPLANE
Group 14:
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.24.42Open Access
3.06.02Install Hardware
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Group 14:
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.51.02FIGURE 14
0.51.02Test
2.24.42Close Access
8.416.8TOTAL FOR EACH AIRPLANE
Group 15:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
0.40.82FIGURE 15
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 16:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.63.22Open Access
2.44.82Install Hardware
0.40.82FIGURE 16
0.40.82Test
1.63.22Close Access
6.412.8TOTAL FOR EACH AIRPLANE
Group 17:
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.24.42Open Access
3.06.02Install Hardware
0.51.02FIGURE 17
0.51.02Test
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Group 17:
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.24.42Close Access
8.416.8TOTAL FOR EACH AIRPLANE
Group 18:
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.24.42Open Access
3.06.02Install Hardware
0.51.02FIGURE 18
0.51.02Test
2.24.42Close Access
8.416.8TOTAL FOR EACH AIRPLANE
Group 19:
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.24.42Open Access
1.83.62Install Hardware
0.40.82FIGURE 19
0.40.82Test
2.24.42Close Access
7.014.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1, 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+333.3+0.6555.5DC-9-14, DC-9-15, DC-9-15F,
DC-9-21
+401.5+0.6669.1DC-9-31, DC-9-32, DC-9-32F,
DC-9-33F
+458.8+0.6764.6DC-9-51
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Group 2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+228.6+0.4571.5DC-9-14
Group 4:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+539.0+0.8673.7DC-9-32, DC-9-32F
Group 5:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+966.1+1.4690.1DC-9-34F
Group 6, 8, 11-12, 15-16:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+936.6+1.5624.4DC-9-32, DC-9-33F
+994.1+1.5662.7DC-9-41
+1079.6+1.5719.7DC-9-51
Group 7, 9, 13:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+1018.6+1.6636.6DC-9-31, DC-9-32, DC-9-32F,
DC-9-33F
+1147.2+1.7674.8DC-9-41
Group 10, 14, 17-18:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+1444.1+2.2656.4DC-9-34, DC-9-34F
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Group 10, 14, 17-18:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+1544.8+2.2702.2DC-9-41
+1670.5+2.2759.3DC-9-51
Group 19:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+932.3+1.4666.0DC-9-32, DC-9-32(VC-9C), DC-
9-32F, DC-9-32F(C-9A), DC-9-
32F(C-9B), DC-9-34
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-16, 20-10-01, 20-20-02
and 20-31-00.
b. DC9 Aircraft Maintenance Manual (AMM) 12-13-0, 25-23-0, 53-20-1, 6-11-1 and 6-11-4.
c. Special Compliance Item Report MDC-92K9145 (CDCCL 20-13).
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:
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ADCNDCN/REVSheetTitleDrawing No
E-AEOFLOAT SWITCH WIRING OVERCURRENT
PROTECTION
SR09280100
-DDWG
3. Installation Drawings Used in the Preparation of this Service Bulletin
None.
4. Process Data:
Douglas Process Specifications referred to on the drawings are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-20Illustrated Parts Catalog
28-20, 28-40, 30-10Aircraft Maintenance Manual
28-23, 28-24, 28-31Wiring 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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BLANK PAGE

### Page 41

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits/parts are subject to the terms and conditions of the Boeing standard purchase order
acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the Revision 1
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 1 date of
this Service Bul-
letin (Calendar
Days)
NameKit Number
$454.00120Service KitSB09280217-3
289.00120Service KitSB09280217-5
587.00120Service KitSB09280217-7
1,018.00120Service KitSB09280217-9
860.00120Service KitSB09280217-11
986.00120Service KitSB09280217-13
860.00120Service KitSB09280217-15
994.00120Service KitSB09280217-17
1,353.00120Service KitSB09280217-19
1,004.00120Service KitSB09280217-21
1,340.00120Service KitSB09280217-23
1,449.00120Service KitSB09280217-25
849.00120Service KitSB09280217-39
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
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C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Group 1, 3:
SB09280217-3
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
WASHER22NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP5S7934111-9SA
NUT-CLIP63D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE565053-219
(a)SEALING PLUG105D0206-20
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### Page 43

Group 1, 3:
SB09280217-3
NotesNameQTYNew Part Number
SLEEVE165 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
165 IN. X 3/16 IN.
SOCKET T/C 52410M39029/22-192
or
CTS-S20/20
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 2:
SB09280217-5
NotesNameQTYNew Part Number
SCREW4NAS1096-3-32
WASHER16NAS1252-10L
SPACER4NAS43DD3-80FC
(a)CLAMP4S7934111-9SA
(a)NUT-CLIP63D0039-16
IN-LINE FUSE465053-219
(a)SEALING PLUG85D0206-20
SLEEVE135 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
135 IN. X 3/16 IN.
SOCKET T/C 5248M39029/22-192
or
CTS-S20/20
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
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### Page 44

Group 4:
SB09280217-7
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW6NAS1096-3-32
WASHER30NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER6NAS43DD3-80FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP7S7934111-9SA
NUT-CLIP83D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE765053-219
(a)SEALING PLUG145D0206-20
SLEEVE235 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
235 IN. X 3/16 IN.
SOCKET T/C 52414M39029/22-192
or
CTS-S20/20
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 5:
SB09280217-9
NotesNameQTYNew Part Number
SCREW3NAS1096-3-8
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### Page 45

Group 5:
SB09280217-9
NotesNameQTYNew Part Number
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
WASHER24NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
CLAMP1MS25281R17
RIVET6MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP8S7934111-9SA
NUT-CLIP83D0039-16
BRACKET39D0062-3F08-10
IN-LINE FUSE865053-219
(a)SEALING PLUG165D0206-20
SLEEVE320 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
320 IN. X 3/16 IN.
SOCKET T/C 52416M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-27
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 46

Group 6, 11, 15-16:
SB09280217-11
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
SCREW1NAS1096-3-50
WASHER25NAS1252-10L
SPACER1NAS43DD3-32FC
SCREW4NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP8S7934111-9SA
NUT-CLIP73D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE865053-219
(a)SEALING PLUG165D0206-20
SLEEVE320 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
320 IN. X 3/16 IN.
SOCKET T/C 52416M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-29
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 47

Group 7:
SB09280217-13
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW6NAS1096-3-32
SCREW1NAS1096-3-50
WASHER33NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER6NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP10S7934111-9SA
NUT-CLIP93D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE1065053-219
(a)SEALING PLUG205D0206-20
SLEEVE385 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
385 IN. X 3/16 IN.
SOCKET T/C 52420M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-29
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 48

Group 8, 12:
SB09280217-15
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
SCREW1NAS1096-3-50
WASHER25NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP8S7934111-9SA
NUT-CLIP73D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE865053-219
(a)SEALING PLUG165D0206-20
SLEEVE320 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
320 IN. X 3/16 IN.
SOCKET T/C 52416M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-31
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 49

Group 9:
SB09280217-17
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW6NAS1096-3-32
SCREW1NAS1096-3-50
WASHER33NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER6NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP10S7934111-9SA
NUT-CLIP93D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE1065053-219
(a)SEALING PLUG205D0206-20
SLEEVE385 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
385 IN. X 3/16 IN.
SOCKET T/C 52420M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-31
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 50

Group 10, 17:
SB09280217-19
NotesNameQTYNew Part Number
SCREW3NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
SCREW1NAS1096-3-50
WASHER27NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET6MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP10S7934111-9SA
NUT-CLIP93D0039-16
BRACKET39D0062-3F08-10
IN-LINE FUSE1065053-219
(a)SEALING PLUG205D0206-20
SLEEVE440 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
440 IN. X 3/16 IN.
SOCKET T/C 52420M39029/22-192
or
CTS-S20/20
SOCKET T/C 7064LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-33
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 51

Group 13:
SB09280217-21
NotesNameQTYNew Part Number
SCREW1NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW6NAS1096-3-32
SCREW1NAS1096-3-50
WASHER33NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER6NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET2MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP10S7934111-9SA
NUT-CLIP93D0039-16
BRACKET19D0062-3F08-10
IN-LINE FUSE1065053-219
(a)SEALING PLUG205D0206-20
SLEEVE440 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
440 IN. X 3/16 IN.
SOCKET T/C 52420M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-31
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 52

Group 14:
SB09280217-23
NotesNameQTYNew Part Number
SCREW3NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
SCREW1NAS1096-3-50
WASHER27NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET6MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP10S7934111-9SA
NUT-CLIP93D0039-16
BRACKET39D0062-3F08-10
IN-LINE FUSE1065053-219
(a)SEALING PLUG205D0206-20
SLEEVE330 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
330 IN. X 3/16 IN.
SOCKET T/C 52420M39029/22-192
or
CTS-S20/20
SOCKET T/C 7064LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-33
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 53

Group 18:
SB09280217-25
NotesNameQTYNew Part Number
SCREW3NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
SCREW1NAS1096-3-50
WASHER27NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET6MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP10S7934111-9SA
NUT-CLIP93D0039-16
BRACKET39D0062-3F08-10
IN-LINE FUSE1065053-219
(a)SEALING PLUG205D0206-20
SLEEVE440 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
440 IN. X 3/16 IN.
SOCKET T/C 52420M39029/22-192
or
CTS-S20/20
SOCKET T/C 7064LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-35
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 54

Group 19:
SB09280217-39
NotesNameQTYNew Part Number
SCREW2NAS1096-3-8
SCREW1NAS1096-3-10
SCREW1NAS1096-3-18
SCREW4NAS1096-3-32
SCREW1NAS1096-3-50
WASHER26NAS1252-10L
SPACER1NAS43DD3-32FC
SPACER4NAS43DD3-80FC
SPACER1NAS43DD3-160FC
CLAMP1MS25281R17
RIVET4MS20470AD4-5D
NUT2MS21042L3
(a)CLAMP2S7934111-2SA
CLAMP7S7934111-9SA
NUT-CLIP83D0039-16
BRACKET29D0062-3F08-10
IN-LINE FUSE765053-219
(a)SEALING PLUG145D0206-20
SLEEVE235 IN. X .093 IDSR09280100-3
(DMS 2109 Type 1)
BEN-HAR 1151 FR-B
or
Alternate
(DMS 2379 Type 4, Class 4)
5676000507
.
.
.
235 IN. X 3/16 IN.
SOCKET T/C 52414M39029/22-192
or
CTS-S20/20
SOCKET T/C 7062LRC16M-32DJ5
(b)WIRE PACKAGE1SB09280217-37
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Package Table for wire package contents.
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### Page 55

Group 5-19:
Wire Package Table
-37-35-33-31-29-27SB09280217
Wire LengthWire Number
60 IN.60 IN.60 IN.60 IN.Q286L20
60 IN.60 IN.60 IN.Q278L20
60 IN.60 IN.60 IN.60 IN.Q279H20
60 IN.60 IN.60 IN.60 IN.Q360T20
60 IN.60 IN.Q280E20
2. Parts and Materials Supplied by the Operator
Group 1-3:
NotesNameQTYPart Number / Specifica-
tion
(a)TERMINAL LUG T/C 765As Required5D0086-25
(b)WIREAs RequiredD2426-1C-20NM
(c)SILICONE RUBBER COATED
GLASS CLOTH
As RequiredDMS 1953
(2127-1)
or
Equivalent
(d)TIE TAPEAs RequiredDMS 2089
(18XTZ), (23XTZ)
or
Equivalent
(e)HIGH-TEMPERATURE SELF-
ADHERING ELECTRICAL INSU-
LATION TAPE
As RequiredDMS 2186
(RL-6000-SA-Series)
or
Equivalent
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Can be purchased from: Standard Wire and Cable Company, 2050 East Villa Bella
Way, Rancho Dominguez, California 90220, CAGE 04946.
(c) Can be purchased from: Fabricote Division of A and S Glass Fabrics Company In-
corporated, 724 East 60th Street, Los Angeles, California 90001, CAGE 9S607.
(d) Can be purchased from: Gudebrod, Incorporated, 274 Shoemaker Road, Pottstown,
Pennsylvania, 19464, CAGE 82110.
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### Page 56

Group 1-3:
NotesNameQTYPart Number / Specifica-
tion
(e) Can be purchased from: Evco Tape Company, 3901 Northeast Kimball Drive, Kansas
City, Missouri 64161, CAGE 0JY72.
Group 4:
NotesNameQTYPart Number / Specifica-
tion
(a)TERMINAL LUG T/C 762As Required5D0086-6
TERMINAL LUG T/C 765As Required5D0086-25
(b)WIREAs RequiredD2426-1C-20NM
(c)SILICONE RUBBER COATED
GLASS CLOTH
As RequiredDMS 1953
(2127-1)
or
Equivalent
(d)TIE TAPEAs RequiredDMS 2089
(18XTZ), (23XTZ)
or
Equivalent
(e)HIGH-TEMPERATURE SELF-
ADHERING ELECTRICAL INSU-
LATION TAPE
As RequiredDMS 2186
(RL-6000-SA-Series)
or
Equivalent
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Can be purchased from: Standard Wire and Cable Company, 2050 East Villa Bella
Way, Rancho Dominguez, California 90220, CAGE 04946.
(c) Can be purchased from: Fabricote Division of A and S Glass Fabrics Company In-
corporated, 724 East 60th Street, Los Angeles, California 90001, CAGE 9S607.
(d) Can be purchased from: Gudebrod, Incorporated, 274 Shoemaker Road, Pottstown,
Pennsylvania, 19464, CAGE 82110.
(e) Can be purchased from: Evco Tape Company, 3901 Northeast Kimball Drive, Kansas
City, Missouri 64161, CAGE 0JY72.
Group 5-6, 8, 10-12, 14-19:
NotesNameQTYPart Number / Specifica-
tion
(a)TERMINAL LUG T/C 765As Required5D0086-25
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### Page 57

Group 5-6, 8, 10-12, 14-19:
NotesNameQTYPart Number / Specifica-
tion
(b)WIREAs RequiredD2426-1C-20NM
(c)SILICONE RUBBER COATED
GLASS CLOTH
As RequiredDMS 1953
(2127-1)
or
Equivalent
(d)TIE TAPEAs RequiredDMS 2089
(18XTZ), (23XTZ)
or
Equivalent
(e)HIGH-TEMPERATURE SELF-
ADHERING ELECTRICAL INSU-
LATION TAPE
As RequiredDMS 2186
(RL-6000-SA-Series)
or
Equivalent
(f)SOCKET T/C 706As RequiredLRC16M-32DJ5
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Can be purchased from: Standard Wire and Cable Company, 2050 East Villa Bella
Way, Rancho Dominguez, California 90220, CAGE 04946.
(c) Can be purchased from: Fabricote Division of A and S Glass Fabrics Company In-
corporated, 724 East 60th Street, Los Angeles, California 90001, CAGE 9S607.
(d) Can be purchased from: Gudebrod, Incorporated, 274 Shoemaker Road, Pottstown,
Pennsylvania, 19464, CAGE 82110.
(e) Can be purchased from: Evco Tape Company, 3901 Northeast Kimball Drive, Kansas
City, Missouri 64161, CAGE 0JY72.
(f) Can be purchased from: Souriau USA, Incorporated, 25 Grumbacher Road, York,
Pennsylvania 17406, CAGE 09922.
Group 7, 9, 13:
NotesNameQTYPart Number / Specifica-
tion
(a)TERMINAL LUG T/C 762As Required5D0086-6
TERMINAL LUG T/C 765As Required5D0086-25
(b)WIREAs RequiredD2426-1C-20NM
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### Page 58

Group 7, 9, 13:
NotesNameQTYPart Number / Specifica-
tion
(c)SILICONE RUBBER COATED
GLASS CLOTH
As RequiredDMS 1953
(2127-1)
or
Equivalent
(d)TIE TAPEAs RequiredDMS 2089
(18XTZ), (23XTZ)
or
Equivalent
(e)HIGH-TEMPERATURE SELF-
ADHERING ELECTRICAL INSU-
LATION TAPE
As RequiredDMS 2186
(RL-6000-SA-Series)
or
Equivalent
(f)SOCKET T/C 706As RequiredLRC16M-32DJ5
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Can be purchased from: Standard Wire and Cable Company, 2050 East Villa Bella
Way, Rancho Dominguez, California 90220, CAGE 04946.
(c) Can be purchased from: Fabricote Division of A and S Glass Fabrics Company In-
corporated, 724 East 60th Street, Los Angeles, California 90001, CAGE 9S607.
(d) Can be purchased from: Gudebrod, Incorporated, 274 Shoemaker Road, Pottstown,
Pennsylvania, 19464, CAGE 82110.
(e) Can be purchased from: Evco Tape Company, 3901 Northeast Kimball Drive, Kansas
City, Missouri 64161, CAGE 0JY72.
(f) Can be purchased from: Souriau USA, Incorporated, 25 Grumbacher Road, York,
Pennsylvania 17406, CAGE 09922.
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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2009
DC9-28-217Revision 1: August 12, 2010
58 of 166
BOEING SERVICE BULLETIN DC9-28-217

### Page 59

F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2009
DC9-28-217Revision 1: August 12, 2010
59 of 166
BOEING SERVICE BULLETIN DC9-28-217

### Page 60

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2009
DC9-28-217Revision 1: August 12, 2010
60 of 166
BOEING SERVICE BULLETIN DC9-28-217
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