# Boeing Service Bulletin DC8-28-090: No revision named

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- Document: [Boeing Service Bulletin DC8-28-090](https://openairdocs.org/service-documents/boeing/dc8-28-090.md)
- Title as filed: Boeing Service Bulletin
- Pages: 93
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### Page 1

McDonnell DouglasCommercial 
Airplanes
DC8
Service Bulletin
Number: DC8-28-090
Original Issue: October 09, 2009
ATA System: 2820
SUBJECT: FUEL - Fuel Tank Fill Control Indicating System - Install Fuel Tank Float 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.
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Unpublished Work - All Rights Reserved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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4.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 2
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 2
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 4
J. References .............................................. 1 4
1. Existing Data .......................................... 1 4
2. Data supplied with this Service Bulletin ............................ 1 4
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 4
K. Publications Affected ........................................ 1 4
L. Interchangeability and Intermixability of Parts ........................... 1 4
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary For Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 8
3. Parts Modified and Reidentified ................................ 2 0
4. Parts Removed and Not Replaced .............................. 2 0
D. Parts Necessary to Change Spares ................................. 2 0
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 4
FIGURE 1: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-115) - INSTALLATION [Group 1, 3] . . 28
FIGURE 2: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-101) - INSTALLATION [Group 1] .... 3 2
FIGURE 3: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-117) - INSTALLATION [Group 1, 3] . . 36
FIGURE 4: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-116) - INSTALLATION [Group 1, 3] . . 39
FIGURE 5: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-102) - INSTALLATION [Group 1] .... 4 3
FIGURE 6: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-118) - INSTALLATION [Group 1, 3] . . 47
FIGURE 7: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-101, F1-103 AND F1-105) - INSTALLATION
[Group 2] ............................................ 5 0
FIGURE 8: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-107) - INSTALLATION [Group 2] .... 5 4
FIGURE 9: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-109) - INSTALLATION [Group 2] .... 5 7
FIGURE 10: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-111 AND F1-112) - INSTALLATION [Group
2 ]  ................................................ 6 0
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FIGURE 11: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-102, F1-104 AND F1-106) - INSTALLATION
[Group 2] ............................................ 6 3
FIGURE 12: IN-LNE FUSE (EQUIPMENT ITEM NUMBER F1-108) - INSTALLATION [Group 2] .... 6 7
FIGURE 13: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-110) - INSTALLATION [Group 2] .... 7 0
FIGURE 14: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-113 AND F1-114) - INSTALLATION [Group
2 ]  ................................................ 7 3
FIGURE 15: [Group 1] ............................................ 7 6
FIGURE 16: [Group 2] ............................................ 8 0
FIGURE 17: [Group 3] ............................................ 8 8
APPENDIX A: DC-8 SERVICE BULLETIN FUEL LEVEL FLOAT SWITCH TEST PROCEDURE [Group 1] . 91
APPENDIX B: DC-8 SERVICE BULLETIN FUEL LEVEL FLOAT SWITCH TEST PROCEDURE [Group 2] . 92
APPENDIX C: DC-8 SERVICE BULLETIN FUEL LEVEL FLOAT SWITCH TEST PROCEDURE [Group 3] . 93
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McDonnell DouglasCommercial 
Airplanes
DC8
Service Bulletin
SummaryNumber: DC8-28-090Original Issue: October 09, 2009
ATA System: 2820
SUBJECT: FUEL - Fuel Tank Fill Control Indicating System - Install Fuel Tank Float Switch In-Line
Fuses
CONCURRENT REQUIREMENTS
None.
BACKGROUND
An analysis by Boeing has determined that float switch wires located on the left and right wing leading edge at
the front spar are routed in the same bundles as power lines. If a short circuit between a float switch wire and
a power wire occurs, an over current can cause excessive temperatures in the float switch wires, resulting in
damage. Adding an in-line fuse as a self-contained component in each float switch circuit will minimize the
possibility of excessive temperatures in the float switch wires. If not corrected, and there is a short circuit of the
float switch wire to a power wire, possible damage to the float switch wire could occur, and become a potential
ignition source into the fuel tank and consequent fire or explosion.
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.
Critical Design Configuration Control Limitation (CDCCL) 20-10 from Report MDC-02K9030 affects airplane
maintenance documents.
ACTION
This service bulletin installs fuel tank float switch in-line fuses in the left and right wing leading edge front spar.
EFFECTIVITY
DC-8-33, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8F-54, DC-8-55, DC-8F-55, DC-8-61, DC-8-61F,
DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71F, DC-8-72, DC-8-72F, DC-8-73F. 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.
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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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McDonnell DouglasCommercial 
Airplanes
DC8
Service Bulletin
Number: DC8-28-090
Original Issue: October 09, 2009
ATA System: 2820
SUBJECT: FUEL - Fuel Tank Fill Control Indicating System - Install Fuel Tank Float Switch In-Line
Fuses
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
DESCRIPTIONCONFIGURATIONGROUP
Applicable to Airplanes with Intermediate Fuel Level Float Switch
and 2 Fuel Level Float Switch Alert.
-1
Applicable to Airplanes with Intermediate Fuel Level Float Switch
and 6 Fuel Level Float Switch Alert.
-2
Applicable to Airplanes without Intermediate Fuel Level Float Switch
and 2 Fuel Level Float Switch Alert.
-3
Airplane Models:
DC-8-33, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8-61, DC-8-61F,
DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71F, DC-8-72, DC-8-72F, DC-8-73F, DC-8F-54,
DC-8F-55
GroupFuselage Num-
ber
3107
3115
3122
3134
3139
3153
3163
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GroupFuselage Num-
ber
3182
3185
3187
3189
3202 - 203
3207 - 208
321
3218
3223
3233 - 234
3241
3246 - 247
3251
3254
3259
3261 - 262
3274
3276 - 277
3283 - 284
2286
3288
3290
3292
3294 - 295
2298
3305
2307
2309
3316
2319
3320 - 321
2322 - 323
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GroupFuselage Num-
ber
3326
2327
3329 - 331
2333 - 335
3337
1338
2344
2347 - 348
1351
1354
3358
1360
2361
3363
2371
3372
3374
2375 - 377
2379 - 380
3381 - 382
2385
3387
2389
2392 - 396
2401
2403
1405
2407
3408
3410
2411
2413
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GroupFuselage Num-
ber
2416 - 417
1418 - 419
3420
2421 - 423
3425 - 426
2427 - 428
2431 - 432
2434
1435 - 436
2437 - 440
2442 - 447
3449 - 450
2451
2453 - 456
2458
3459 - 460
2463 - 469
3477
2478 - 483
2485
2487 - 491
3492
2493
3495
2496
2500 - 504
2508 - 509
2511
2515 - 516
2519 - 525
2527 - 531
2534 - 535
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GroupFuselage Num-
ber
2538 - 540
2542
2546 - 549
2551
2554 - 556
379
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
An analysis by Boeing has determined that float switch wires located on the left and right wing leading
edge at the front spar are routed in the same bundles as power lines. If a short circuit between a float
switch wire and a power wire occurs, an over current can cause excessive temperatures in the float
switch wires, resulting in damage. Adding an in-line fuse as a self-contained component in each float
switch circuit will minimize the possibility of excessive temperatures in the float switch wires. If not
corrected, and there is a short circuit of the float switch wire to a power wire, possible damage to the
float switch wire could occur, and become a potential ignition source into the fuel tank and consequent
fire or explosion.
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.
Critical Design Configuration Control Limitation (CDCCL) 20-10 from Report MDC-02K9030 affects
airplane maintenance documents.
D. Description
This service bulletin installs fuel tank float switch in-line fuses in the left and right wing leading edge
front spar.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
107, 108, 112, 115, 116DC-8-61, DC-8-61F, DC-8-71F
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Group 2:
Affected Maintenance Zones
ZoneModel
107, 108, 112, 115, 116DC-8-62, DC-8-62F, DC-8-63,
DC-8-63F, DC-8-72, DC-8-72F,
DC-8-73F
Group 3:
Affected Maintenance Zones
ZoneModel
107, 108, 112, 115, 116DC-8-33, DC-8-42, DC-8-43,
DC-8-51, DC-8-52, DC-8-53,
DC-8-55, DC-8-61, DC-8-61F,
DC-8-71F, DC-8F-54, DC-8F-55
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 table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
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 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.53.02Open Access
12.012.01Install
1.01.01Test
1.53.02Close Access
16.019.0TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.53.02Open Access
28.028.01Install
1.01.01Test
1.53.02Close Access
32.035.0TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.53.02Open Access
8.08.01Install
1.01.01Test
1.53.02Close Access
12.015.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane Group
+1072.1+1.1974.61
+2304.6+2.31002.02
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Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane Group
+773.2+0.8966.53
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01,
20-10-02, 20-10-03, 20-10-04, 20-20-02, 20-20-03, and 20-31-00.
b. DC8 Aircraft Maintenance Manual (AMM) 28-04-09, 28-42-01, and 6-11-2.
c. DC8 Wiring Diagram Manual 28-01.
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
ChangeTitleDocument Number
BFloat Switch Wiring Overcurrent Pro-
tection
SR08280008
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
K. Publications Affected
Chapter-SectionPublication
28-02, 28-04, 28-21, 28-42, 30-01, 30-10,
and 36-00
Aircraft Maintenance Manual
28-01Wiring Diagram Manual
MDC-02K9030 (CDCCL 20-10)Special Compliance Item Report
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits 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, a supply sequence is given by Spares.
More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the
date Boeing gets the purchase order.
Unit Price thru
December 31,
2010
ROLT (Weeks)NameKit Number
$1,974.0017Service KitSB08280090-3
3,646.0017Service KitSB08280090-5
1,043.0017Service KitSB08280090-7
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
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Group 1:
Kit SB08280090
NotesExisting Part
Number
NameQTYNew Part Number
-3
(a)NUT-CLIP43D0039-14
(a)SEALING PLUG125D0206-20
IN-LINE FUSE665053-220
(a)BRACKET29D0230-3M080808
SOCKET T/C 52412M39029/22-192
NUT6MS21042L3
SCREW3NAS1096-3-29
SCREW1NAS1096-3-30
SCREW2NAS1096-3-8
SCREW4NAS1096-3-9
WASHER24NAS1252-10L
SPACER4NAS43DD3-64FC
(a)CLAMP2S7913536-8
(a)CLAMP2S7934111-1SA
(a)CLAMP2S7934111-2SA
(a)CLAMP6S7934111-9SA
SLEEVE400
IN. x
.093
I.D.
SR08280008-3
(DMS 2109 Type 1)
BEN-HAR 1151
FR-B or ES 4400
R-A-1 or Alternate
(DMS 2379 Type 4,
Class 4)
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
Group 2:
Kit SB08280090
NotesExisting Part
Number
NameQTYNew Part Number
-5
(a)NUT-CLIP103D0039-14
(a)SEALING PLUG285D0206-20
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Group 2:
Kit SB08280090
NotesExisting Part
Number
NameQTYNew Part Number
-5
IN-LINE FUSE1465053-220
(a)BRACKET29D0230-3M080808
SOCKET T/C 52428M39029/22-192
NUT2MS21042L08
CLAMP2MS25281R2
SCREW2NAS1096-2-9
SCREW2NAS1096-3-29
SCREW2NAS1096-3-30
SCREW2NAS1096-3-44
SCREW4NAS1096-3-9
WASHER22NAS1252-10L
WASHER4NAS1252-8L
SPACER2NAS43DD3-128FC
SPACER4NAS43DD3-64FC
(a)CLAMP14S7934111-9SA
SLEEVE900
IN. x
.093
I.D.
SR08280008-3
(DMS 2109 Type 1)
BEN-HAR 1151
FR-B or ES 4400
R-A-1 or Alternate
(DMS 2379 Type 4,
Class 4)
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
Group 3:
Kit SB08280090
NotesExisting Part
Number
NameQTYNew Part Number
-7
(a)SEALING PLUG85D0206-20
IN-LINE FUSE465053-220
(a)SOCKET T/C 5248M39029/22-192
NUT6MS21042L3
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Group 3:
Kit SB08280090
NotesExisting Part
Number
NameQTYNew Part Number
-7
SCREW3NAS1096-3-29
SCREW1NAS1096-3-30
SCREW2NAS1096-3-9
WASHER20NAS1252-10L
SPACER4NAS43DD3-64FC
(a)CLAMP2S7913536-8
(a)CLAMP2S7934111-1SA
(a)CLAMP2S7934111-2SA
(a)CLAMP4S7934111-9SA
SLEEVE300
IN. x
.093
I.D.
SR08280008-3
(DMS 2109 Type 1)
BEN-HAR 1151
FR-B or ES 4400
R-A-1 or Alternate
(DMS 2379 Type 4,
Class 4)
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
2. Parts and Materials Supplied by the Operator
Group 1:
NotesNameQTYPart Number /
Specification
(a)SPLICE65D0085-01
(a)CAP, INSULATING65D0229-1
(b)TIE TAPEAs re-
quired
DMS 2089
(18XTZ), (23XTZ)
Or
Equivalent
(c).WIREAs re-
quired
D2426-1C-22NMG
(DMS 2426)
Or
Equivalent
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Group 1:
NotesNameQTYPart Number /
Specification
(c)WIREAs re-
quired
D2426-1C-24NMG
(DMS2426)
Or
Equivalent
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
CAGEGudebrod, Incorporated(b) Can be pur-
chased from: 82110274 Shoemaker Road
Pottstown, Pennsylvania 19464
3CAV5Tensolite Company(c) Can be pur-
chased from: 2400 Grand Avenue
Long Beach, California 90815-1762
Group 2:
NotesNameQTYPart Number /
Specification
(a)SPLICE245D0085-01
(a)CAP, INSULATING205D0229-1
(b)SLEEVE.125 DIA. x
7.5 IN.
DMS 2381 Class 1
(W5DL Series)
Or
Equivalent
(c)TIE TAPEAs re-
quired
DMS 2089
(18XTZ), (23XTZ)
Or
Equivalent
(d).WIREAs re-
quired
D2426-1C-22NMG
(DMS 2426)
Or
Equivalent
(d)WIREAs re-
quired
D2426-1C-24NMG
(DMS2426)
Or
Equivalent
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
CAGESumitomo Electric International Products,
Incorporated
(b) Can be pur-
chased from: 1JX75
915 Armorlite Drive
San Marcos, California 92069-1440
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### Page 20

Group 2:
NotesNameQTYPart Number /
Specification
CAGEGudebrod, Incorporated(c) Can be pur-
chased from: 82110274 Shoemaker Road
Pottstown, Pennsylvania 19464
3CAV5Tensolite Company(d) Can be pur-
chased from: 2400 Grand Avenue
Long Beach, California 90815-1762
Group 3:
NotesNameQTYPart Number /
Specification
(a)SPLICE45D0085-01
(a)CAP, INSULATING45D0229-1
(b)TIE TAPEAs re-
quired
DMS 2089
(18XTZ), (23XTZ)
Or
Equivalent
(c)WIREAs re-
quired
D2426-1C-24NMG
(DMS2426)
Or
Equivalent
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
CAGEGudebrod, Incorporated(b) Can be pur-
chased from: 82110274 Shoemaker Road
Pottstown, Pennsylvania 19464
3CAV5Tensolite Company(c) Can be pur-
chased from: 2400 Grand Avenue
Long Beach, California 90815-1762
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
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### Page 21

E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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BLANK PAGE

### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
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.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Equivalent parts are listed in the AEPL, Drawing 7595071.
4. Use the approved fastener and process material substitutions. Refer to DC8 SRM
51.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards in SRM Chapter 51, then a fastener of the same specification,
or an approved substitute, with a length which meets the installation standards in
SRM Chapter 51 may be used.
6. 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. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch.
– Torque limits to tighten nuts and bolts are in SRM, Chapter 51.
8. Refer to these SWPM chapters for applicable operations, as accepted procedures:
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### Page 24

– TITLECHAPTER
IDENTIFICATION OF ELECTRICAL WIRE - COMMER-
CIAL
SWPM 20-00-03
GENERAL MAINTENANCE PRACTICES - ELECTRI-
CAL
SWPM 20-00-09
ELECTRICAL WIRE CODESSWPM 20-00-13
ELECTRICAL WIRE END TERMINATION CODES
AND TOOL CODES
SWPM 20-00-16
FABRICATING AND INSTALLING WIRE HARNESSES
- COMMERCIAL
SWPM 20-10-01
SHIELDING - MAINTENANCE PRACTICESSWPM 20-10-02
WIRE SPLICING - MAINTENANCE PRACTICESSWPM 20-10-03
COIL AND STOW - MAINTENANCE PRACTICESSWPM 20-10-04
TERMINAL BLOCKS - MAINTENANCE PRACTICESSWPM 20-20-02
GENERAL INSTALLATIONS HARDWARE - MAINTE-
NANCE PRACTICES
SWPM 20-20-03
ELECTRICAL CONNECTORS - MAINTENANCE
PRACTICES
SWPM 20-31-00
9. Obey all of the warnings and cautions given in the specified manual sections.
10. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
11. Any protrusion of threads is acceptable provided that the threads do not rub or ride
against nearby wire assemblies or components.
12. Locate/position clamps as required to clear airplane structure/components.
13. Reference structure and wiring in Figures may not represent existing airplane
configuration.
14. Access panel numbers and locations may vary among models.
15. Ensure in-line fuses are installed on power wires.
B. WORK INSTRUCTIONS
Group 1:
1. Gain access to area of change by opening and keeping the following:
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### Page 25

Refer toPanel Number
DC8 AMM 6-
11-2
519B, 519C, 520A, 522B, 524A.
2. Install fuel tank float switch in-line fuse in the left/right wing in accordance with Figures relative to
equipment item numbers shown below:
FigureEquipment Item Number (Left Wing)
1 and 15F1-115
2 and 15F1-101
3 and 15F1-117
FigureEquipment Item Number (Right Wing)
4 and 15F1-116
5 and 15F1-102
6 and 15F1-118
3. Do return-to-service test of fuel tank float switch in-line fuse in accordance with Appendix A.
4. Close the following kept access panels and associated hardware.
Refer toPanel Number
DC8 AMM 6-
11-2
519B, 519C, 520A, 522B, 524A.
5. Put the airplane back to serviceable condition.
Group 2:
1. Gain access to area of change by opening and keeping the following:
Refer toPanel Number
DC8 AMM 6-
11-2
517A, 517B, 518A, 519B, 519C,
520A, 520B, 520H, 520J, 522B,
524A.
2. Install fuel tank float switch in-line fuse in the left/right wing in accordance with Figures relative to
equipment item numbers shown below:
FigureEquipment Item Number (Left Wing)
7 and 16F1-101
F1-103
F1-105
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### Page 26

FigureEquipment Item Number (Left Wing)
8 and 16F1-107
9 and 16F1-109
10 and 16F1-111
F1-112
FigureEquipment Item Number (Right Wing)
11 and 16F1-102
F1-104
F1-106
12 and 16F1-108
13 and 16F1-110
14 and 16F1-113
F1-114
3. Do return-to-service test of fuel tank float switch in-line fuse in accordance with Appendix B.
4. Close the following kept access panels and associated hardware.
Refer toPanel Number
DC8 AMM 6-
11-2
517A, 517B, 518A, 519B, 519C,
520A, 520B, 520H, 520J, 522B,
524A.
5. Put the airplane back to serviceable condition.
Group 3:
1. Gain access to area of change by opening and keeping the following:
Refer toPanel Number
DC8 AMM 6-
11-2
519B, 519C, 520A, 522B, 524A.
2. Install fuel tank float switch in-line fuse in the left/right wing in accordance with Figures relative to
equipment item numbers shown below:
FigureEquipment Item Number (Left Wing)
1 and 17F1-115
3 and 17F1-117
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### Page 27

FigureEquipment Item Number (Right Wing)
4 and 17F1-116
6 and 17F1-118
3. Do return-to-service test of fuel tank float switch in-line fuse in accordance with Appendix C.
4. Close the following kept access panels and associated hardware.
Refer toPanel Number
DC8 AMM 6-
11-2
519B, 519C, 520A, 522B, 524A.
5. Put the airplane back to serviceable condition.
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Copyright © Unpublished Work - See page 1 for details.
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### Page 28 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 1, 3.
LEFT SIDE
Хfs=289.000
1474653
FIGURE 1: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-115) - INSTALLATION
(SHEET 1 OF 4)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=289.000
SUPPORT
BRACKET
BEFORE  • CONDUIT
1439468
FIGURE 1: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-115) - INSTALLATION
(SHEET 2 OF 4)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=289.000
SUPPORT
BRACKET
S1-473
FLOAT SWITCH
FEEDTHRU
1.25
INSO
AFTER
1474657
FIGURE 1: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-115) - INSTALLATION
(SHEET 3 OF 4)
Original Issue: October 09, 2009
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Copyright © Unpublished Work - See page 1 for details.  30 of 93

### Page 31

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
(a)-SR08280008-3SLEEVEInstall (New)2
4NAS1252-10LWASHERInstall (New)3
1NAS43DD3-64FCSPACERInstall (New)
1S7934111-1SACLAMPInstall (New)
1S7934111-9SACLAMPInstall (New)
1NAS1096-3-29SCREWInstall (New)
1MS21042L3NUTInstall (New)
(b)165053-220IN-LINE FUSEInstall (New)
1S7934111-2SACLAMPInstall (New)4
1S7913536-8CLAMPInstall (New)
2NAS1252-10LWASHERInstall (New)
1NAS1096-3-9SCREWInstall (New)
1MS21042L3NUTInstall (New)
(a) Start at float switch feed-through and end to fuse. Do not block feed-through vent tubes. String tie to ex-
isting wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-115. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 1: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-115) - INSTALLATION
(SHEET 4 OF 4)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 1.
LEFT SIDE
Хfs=295.095
1475556
FIGURE 2: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-101) - INSTALLATION
(SHEET 1 OF 4)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=301.887
Xfs=295.095
Хfs=288.474
Xfs=295.095
BEFORE
FWD
CONDUIT-  1475557
FIGURE 2: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-101) - INSTALLATION
(SHEET 2 OF 4)
Original Issue: October 09, 2009
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### Page 34 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=301.887
Хfs=295.095
Xfs=288.474
Xfs=295.095
FWD
AFTER
S1-630
FLOAT SWITCH
FEEDTHRU
1475558
FIGURE 2: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-101) - INSTALLATION
(SHEET 3 OF 4)
Original Issue: October 09, 2009
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Copyright © Unpublished Work - See page 1 for details.  34 of 93

### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
1-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
23D0039-14NUT-CLIPInstall (New)3
19D0230-3M080808BRACKETInstall (New)
1-CLAMPInstall (Kept)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-9SCREWInstall (New)
1S7934111-9SACLAMPInstall (New)4
(b)165053-220IN-LINE FUSEInstall (New)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
(a) Start at float switch feed-through and end just before drip loop. Do not block feed-through vent tubes.
String tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-101. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 2: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-101) - INSTALLATION
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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### Page 36 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 1, 3.
LEFT SIDE
Xfs=776.957
xfs=770.082
Xfs=763.207
S1-471
FLOAT SWITCH
FEEDTHRU
BEFORE
FWD
1475673
FIGURE 3: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-117) - INSTALLATION
(SHEET 1 OF 3)
Original Issue: October 09, 2009
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### Page 37 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=776.957
Xfs=770.082
Xfs=763.207
S1-471
FLOAT SWITCH
FEEDTHRU
FWD
AFTER
1475675
FIGURE 3: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-117) - INSTALLATION
(SHEET 2 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  37 01 93

### Page 38

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
2-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
1S7934111-9SACLAMPInstall (New)3
2-CLAMPInstall (Kept)
4NAS1252-10LWASHERInstall (New)
1NAS43DD3-64FCSPACERInstall (New)
(b)165053-220IN-LINE FUSEInstall (New)
1NAS1096-3-29SCREWInstall (New)
1MS21042L3NUTInstall (New)
(a) Start at float switch feed-through and end just before drip loop. Do not block feed-through vent tubes.
String tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-117. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 3: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-117) - INSTALLATION
(SHEET 3 OF 3)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 1, 3.
RIGHT SIDE
Xfs=-289.000
1475922
FIGURE 4: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-116) - INSTALLATION
(SHEET 1 OF 4)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=-289.000
Xfs=-289.000
INED  BEFORE  DUCT
CONDUIT
1475923
FIGURE 4: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-116) - INSTALLATION
(SHEET 2 OF 4)
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### Page 41 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=-289.000
WIRE
AFTER  S1-474
FLOAT SWITCH  FEEDTHRU  DUCT  CONDUIT
Xfs=-289.000
1475925
FIGURE 4: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-116) - INSTALLATION
(SHEET 3 OF 4)
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BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  41 of 93

### Page 42

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
2-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
1S7934111-9SACLAMPInstall (New)3
1S7934111-1SACLAMPInstall (New)
2-CLAMPInstall (Kept)
4NAS1252-10LWASHERInstall (New)
1NAS43DD3-64FCSPACERInstall (New)
(b)165053-220IN-LINE FUSEInstall (New)
1NAS1096-3-30SCREWInstall (New)
1MS21042L3NUTInstall (New)
1S7913536-8CLAMPInstall (New)4
1S7934111-2SACLAMPInstall (New)
2NAS1252-10LWASHERInstall (New)
1NAS1096-3-9SCREWInstall (New)
1MS21042L3NUTInstall (New)
(a) Start at float switch feed-through and end to fuse. Do not block feed-through vent tubes. String tie to ex-
isting wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-116. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 4: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-116) - INSTALLATION
(SHEET 4 OF 4)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 1.
RIGHT SIDE
Xfs=-295.095
1475927
FIGURE 5: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-102) - INSTALLATION
(SHEET 1 OF 4)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=-301.887
Xfs=-295.095
Xfs=-288.274
Xfs=-295.095
BEFORE
FWD
1475928
FIGURE 5: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-102) - INSTALLATION
(SHEET 2 OF 4)
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### Page 45 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=-301.887
Xfs=-295.095
S1-631
FLOAT SWITCH
FEEDTHRU
Xfs=-288.274
— CONDUIT
AFTER
FWD
EXISTING
BRACKET
Xfs=-295.095
-(2)  1475929
FIGURE 5: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-102) - INSTALLATION
(SHEET 3 OF 4)
Original Issue: October 09, 2009
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  DC8-28-090  45 of 93

### Page 46

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
1-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
23D0039-14NUT-CLIPInstall (New)3
19D0230-3M080808BRACKETInstall (New)
1-CLAMPInstall (Kept)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-9SCREWInstall (New)
1S7934111-9SACLAMPInstall (New)4
1NAS1252-10LWASHERInstall (New)
(b)165053-220IN-LINE FUSEInstall (New)
1NAS1096-3-8SCREWInstall (New)
(a) Start at float switch feed-through and end just before drip loop. Do not block feed-through vent tubes.
String tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-102. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 5: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-102) - INSTALLATION
(SHEET 4 OF 4)
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DC8-28-090
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BOEING SERVICE BULLETIN DC8-28-090

### Page 47 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 1, 3.
RIGHT SIDE
Xfs=-763.207
BEFORE
FWD
1475930
FIGURE 6: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-118) - INSTALLATION
(SHEET 1 OF 3)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Хfs=-770.082
Xfs=-763.207
V
FWD
AFTER
S1-472
FLOAT SWITCH
FEEDTHRU
1475931
FIGURE 6: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-118) - INSTALLATION
(SHEET 2 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  48 of 93

### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
2-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
1NAS1096-3-29SCREWInstall (New)3
4NAS1252-10LWASHERInstall (New)
1NAS43DD3-64FCSPACERInstall (New)
2-CLAMPInstall (Kept)
1S7934111-9SACLAMPInstall (New)
(b)165053-220IN-LINE FUSEInstall (New)
1MS21042L3NUTInstall (New)
(a) Start at float switch feed-through and end just before drip loop. Do not block feed-through vent tubes.
String tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-118. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 6: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-118) - INSTALLATION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 09, 2009
DC8-28-090
49 of 93
BOEING SERVICE BULLETIN DC8-28-090

### Page 50 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 2.
LEFT SIDE
Хfs=295.095
1475690
FIGURE 7: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-101, F1-103 AND F1-105) - INSTALLATION
(SHEET 1 OF 4)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  50 of 93

### Page 51 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xts=301.887
Xfs=295.095
Хfs=288.474
Xfs=295.095
BEFORE
FWD
CONDUIT-  1475691
FIGURE 7: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-101, F1-103 AND F1-105) - INSTALLATION
(SHEET 2 OF 4)
Original Issue: October 09, 2009
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  DC8-28-090  51 of 93

### Page 52 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=295.095
S1-634
FLOAT SWITCH
FEEDTHRU
S1-630
FLOAT SWITCH
FEEDTHRU \
S1-632
FLOAT SWITCH
FEEDTHRU —
EXISTING
Xfs=295.095  BRACKET
CONDUIT
FWD
AFTER
F1-101
F1-105  1475692
F1-103
FIGURE 7: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-101, F1-103 AND F1-105) - INSTALLATION
(SHEET 3 OF 4)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  52 of 93

### Page 53

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
1-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
23D0039-14NUT-CLIPInstall (New)3
19D0230-3M080808BRACKETInstall (New)
1-CLAMPInstall (Kept)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-9SCREWInstall (New)
3S7934111-9SACLAMPInstall (New)4
3NAS1252-10LWASHERInstall (New)
1NAS43DD3-128FCSPACERInstall (New)
(b)365053-220IN-LINE FUSEInstall (New)
1NAS1096-3-44SCREWInstall (New)
(a) For F1-101 fuse, start at float switch feed-through and end just before drip loop. For F1-103 and F1-105
fuses, start at float switch feed-through and end at fuses. Do not block feed-through vent tubes. String
tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-101, F1-103, and F1-105. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 7: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-101, F1-103 AND F1-105) - INSTALLATION
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 09, 2009
DC8-28-090
53 of 93
BOEING SERVICE BULLETIN DC8-28-090

### Page 54 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 2.
LEFT SIDE
Xfs=508.580
Xfs=502.688
XfS=497.212
Xfs=502.688
BEFORE
FWD
1475694
FIGURE 8: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-107) - INSTALLATION
(SHEET 1 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  54 of 93

### Page 55 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Xfs=508.580
S1-636
FLOAT SWITCH
FEEDTHRU
Xfs=502.688
XIS=497.212
FWD
Xfs=502.688
AFTER
EXISTING
BRACKET  EXISTING
CLAMP
1475695
FIGURE 8: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-107) - INSTALLATION
(SHEET 2 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  55 of 93

### Page 56

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
1-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)2
13D0039-14NUT-CLIPInstall (New)3
3NAS1252-10LWASHERInstall (New)
1NAS43DD3-64FCSPACERInstall (New)
1S7934111-9SACLAMPInstall (New)
1-CLAMPInstall (Kept)
(b)165053-220IN-LINE FUSEInstall (New)
1NAS1096-3-29SCREWInstall (New)
(a) Start at float switch feed-through and end just before drip loop. Do not block feed-through vent tubes.
String tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-107. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 8: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-107) - INSTALLATION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 09, 2009
DC8-28-090
56 of 93
BOEING SERVICE BULLETIN DC8-28-090

### Page 57 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 2.
Xfs=770.082
Xfs=763.207
Хfs=756.332
LEFT SIDE
FWD
BEFORE
Xfs=763.207
1475845
FIGURE 9: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-109) - INSTALLATION
(SHEET 1 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  57 of 93

### Page 58 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
Хfs=770.082
Xfs=763.207
S1-638
FLOAT SWITCH
FEEDTHRU
Xfs=756.332
FWD
Xfs=763.207
AFTER
1475847
FIGURE 9: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-109) - INSTALLATION
(SHEET 2 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  58 of 93

### Page 59

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
2-WASHERRemove
1-NUTRemove
1-CLAMPRemove / Keep
1-SCREWRemove2
2-WASHERRemove
1-NUTRemove
1-CLAMPRemove / Keep
(a)-SR08280008-3SLEEVEInstall (New)3
13D0039-14NUT-CLIPInstall (New)4
1-CLAMPInstall (Kept)
1NAS1252-10LWASHERInstall (New)
1S7934111-9SACLAMPInstall (New)
(b)165053-220IN-LINE FUSEInstall (New)
1NAS1096-3-9SCREWInstall (New)
1MS25281R2CLAMPInstall (New)5
1-CLAMPInstall (Kept)
2NAS1252-8LWASHERInstall (New)
1NAS1096-2-9SCREWInstall (New)
1MS21042L08NUTInstall (New)
(a) Start at float switch feed-through and end just before drip loop. Do not block feed-through vent tubes.
String tie to existing wire bundle. Refer to SWPM 20-10-01 as an accepted procedure.
(b) Identify in-line fuse F1-109. Refer to SWPM 20-00-09 as an accepted procedure.
FIGURE 9: IN-LINE FUSE (EQUIPMENT ITEM NUMBER F1-109) - INSTALLATION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 09, 2009
DC8-28-090
59 of 93
BOEING SERVICE BULLETIN DC8-28-090

### Page 60 (OCR)

BOEING SERVICE BULLETIN DC8-28-090
This Figure applies only to: Group 2.
Xfs=880.003
LEFT SIDE
Xfs=873.003
Xfs=866.534
Хfs=873.003
BEFORE
1475853
FIGURE 10: IN-LINE FUSE (EQUIPMENT ITEM NUMBERS F1-111 AND F1-112) - INSTALLATION
(SHEET 1 OF 3)
Original Issue: October 09, 2009
BOEING PROPRIETARY -  DC8-28-090
Copyright © Unpublished Work - See page 1 for details.  60 of 93

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