# Boeing Alert Service Bulletin 767-28A0053: Boeing - Service Bulletin

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- Pages: 72
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### Page 1

Commercial 
Airplanes
767
Service Bulletin
Number: 767-28A0053
Original Issue: October 29, 1998
Revision 3: November 11, 2011
ATA System: 2822 2830
SUBJECT: FUEL - Distribution - Engine Fuel Feed Boost and Override/Jettison Pump Wire Bundle
Sleeve Inspection/Replacement
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 © 1998 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Unpublished Work - All Rights Reserved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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3.0

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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 ........................................ 1 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 8
D. Description .............................................. 1 8
E. Compliance .............................................. 1 9
F. Approval ............................................... 1 9
G. Manpower .............................................. 2 0
H. Weight and Balance Changes .................................... 2 0
I. Electrical Load Data ......................................... 2 0
J. References .............................................. 2 0
1. Existing Data: ......................................... 2 0
2. Data supplied with this Service Bulletin: ........................... 2 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 1
K. Publications Affected ........................................ 2 1
L. Interchangeability and Intermixability of Parts ........................... 2 1
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts: ........................................... 2 3
2. Parts and Materials Supplied by the Operator: ........................ 2 4
3. Parts Modified and Reidentified: ............................... 2 5
4. Parts Removed and Not Replaced: .............................. 2 5
D. Parts Necessary to Change Spares ................................. 2 5
E. Special Tooling - Price and Availability ............................... 2 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 8
FIGURE 1: GET ACCESS TO THE FUEL PUMP CONNECTORS .................... 3 3
FIGURE 2: 767-200/-300/-300F AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE
CONDUIT [Group 1-2] ..................................... 3 5
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES [Group 1-2]
.................................................. 3 8
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
[Group 1-2] ........................................... 4 4
FIGURE 5: PUT BACK THE FUEL PUMP ACCESS COVERS ...................... 5 3
FIGURE 6: 767-400ER AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE CONDUIT
[Group 3-4] ........................................... 5 5
FIGURE 7: 767-400ER AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES [Group 3-4] . 59
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FIGURE 8: 767-400ER AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
[Group 3-4] ........................................... 6 5
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Commercial 
Airplanes
767
Service Bulletin
Revision Transmittal SheetNumber: 767-28A0053Original Issue: October 29, 1998
Revision 3: November 11, 2011
ATA System: 2822 2830
SUBJECT: FUEL - Distribution - Engine Fuel Feed Boost and Override/Jettison Pump Wire Bundle
Sleeve Inspection/Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Airplanes VF181-VF184 were added to this service bulletin effectivity.
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2000-11-06 is related to this service bulletin.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2010-NM-148-AD is related to
this service bulletin.
The accomplishment of the change given in Boeing Service Bulletin 767-28-0104 is the terminating action for
the repetitive inspection given in this service bulletin.
No more work is necessary on airplanes changed in accordance with Revision 1 or Revision 2 of this service
bulletin.
REASON FOR REVISION
This revision is sent to revise the effectivity, replace service bulletins 767-28A0079 and 767-28A0080, clarify
the accomplishment instructions, and remove the optional fuel pump check.
These sections were changed:
1. Summary - Background and Paragraph 1.C., Reason: Added references and data.
2. Summary - Industry Support Information and Paragraph 2.B., Industry Support Information: Included a
separate warranty statement for Group 2 and Group 4 airplanes.
3. Summary - Material Information, Paragraph 1.L., Interchangeability and Intermixability of Parts, Paragraph
2.A, Material - Price and Availability, and Paragraph 2.F., Special Tooling Necessary to do this Service
Bulletin: Corrected paragraph references.
4. Paragraph 1.A., Effectivity: Limited effectivity to line numbers 1-989, added VF181-VF184, and divided
airplanes into four groups.
5. Paragraph 1.E., Compliance: Added references, clarified date.
6. Paragraph 1.J., References: Updated references.
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7. Paragraph 1.K., Publications Affected: Added publication.
8. Paragraph 2.A., Material - Price and Availability: Updated kit ordering information, Reorder Lead Time
(ROLT) and price.
9. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added part numbers.
10. Paragraph 3.A., General Information: Added new notes and references.
11. Paragraph 3.B., Work Instructions: Revised the inspection procedure, added circuit breakers, updated
references, and removed the optional fuel pump check.
12. Figure 1: Added footnote and references.
13. Figure 2: Moved damage check and sleeve removal to Paragraph 3.B, deleted illustration, clarified part
quantities.
14. Figures 3 and 4: Revised titles, added footnote and references, clarified part quantities.
15. Figure 4: Corrected illustration.
16. Figures 6-8: Created new figures for the 767-400ER configuration.
Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph
3.A., General Information - Notes.
The data given in Information Notice 767-28A0053 IN 05 is included in this revision.
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
October 29, 1998Original Issue:
August 05, 1999Revision 1:
June 24, 2010Revision 2:
November 11, 2011Revision 3:
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Commercial 
Airplanes
767
Service Bulletin
SummaryNumber: 767-28A0053Original Issue: October 29, 1998
Revision 3: November 11, 2011
ATA System: 2822 2830
SUBJECT: FUEL - Distribution - Engine Fuel Feed Boost and Override/Jettison Pump Wire Bundle
Sleeve Inspection/Replacement
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This inspection/replacement will make sure the fuel tank boost pump and override/jettison pump wiring is not
chafed and will not cause arcing inside the fuel tank.
The fuel tank boost pump and override/jettison pump wiring is installed with a double layer of Teflon sleeving in
the conduit. The sleeving is installed to prevent arcing between the boost pump power wiring and the conduit
caused by wire chafing.
767 Maintenance Planning Data (MPD) Section 9, Airworthiness Limitation (AWL) 28-AWL-30 is applicable to
airplanes after incorporation of this service bulletin.
For Group 2 airplanes, this service bulletin now replaces Boeing Service Bulletin 767-28A0079. For Group 4
airplanes, this service bulletin now replaces Boeing Service Bulletin 767-28A0080.
Boeing Fleet Team Digest (FTD) 767 FTD 28-07001 is related to this service bulletin.
ACTION
Remove the four fuel pump access doors. Remove the boost and override/jettison pump wire bundles from the
conduit. Remove the wire bundles from the conduits. Do an inspection of the sleeves and the wires and repair
any damage that is found. Install the wire bundles in the conduits. Install the four fuel pump access doors. Do
a test of the boost and override/jettison pumps.
EFFECTIVITY
767-200, 767-300, 767-300F and 767-400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of
affected airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
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INDUSTRY SUPPORT INFORMATION
Group 1, 3:
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service
bulletin.
Group 2, 4:
Boeing warranty remedies are available for airplanes in warranty as of July 11, 2002. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Elapsed Time
(Hours)
Total
Man-Hours
Airplanes
3.756.5With Jettison Pumps
3.05.25Without Jettison Pumps
MATERIAL INFORMATION
Boeing Supplied Kits.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-28A0053
GET ACCESS TO THE LEFT AUXILIARY
TANK OVERRIDE/JETTISON PUMP(S)  GET ACCESS TO THE LEFT
MAIN TANK BOOST PUMPS
GET ACCESS TO THE
RIGHT AUXILIARY TANK
OVERRIDE/JETTISON PUMP (S)
•
REAR SPAR
REAR SPAR
INSPECT/REPLACE THE FUEL
PUMP WIRE BUNDLE SLEEVES.
GET ACCESS TO
THE RIGHT MAIN  S45929
TANK BOOST PUMPS
Original Issue: October 29, 1998
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Commercial 
Airplanes
767
Service Bulletin
Number: 767-28A0053
Original Issue: October 29, 1998
Revision 3: November 11, 2011
ATA System: 2822 2830
SUBJECT: FUEL - Distribution - Engine Fuel Feed Boost and Override/Jettison Pump Wire Bundle
Sleeve Inspection/Replacement
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP
767-200/-300/-300F airplanes with line numbers 1-720, 862-900,
920-929 and 931-989
-1
767-200/-300/-300F airplanes with line numbers 721-858, 860-861,
901-919 and 930
-2
767-400ER airplanes with line numbers 859-989-3
767-400ER airplanes with line numbers 721-858-4
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
1VA001 - VA020
1VA301 - VA315
1VA501 - VA530
1VA701 - VA719
1VA801 - VA810
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GroupVariable Number
1VB001 - VB002
1VB051 - VB055
1VB101 - VB125
1VB201 - VB202
1VB251 - VB253
1VB281 - VB284
1VB301 - VB302
1VB321 - VB332
1VB371 - VB373
1VB401
1VB441 - VB444
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE086
1VE101 - VE104
1VE116 - VE118
1VE121 - VE126
1VE141 - VE152
1VE171 - VE172
1VF001 - VF002
1VF041 - VF042
1VF051
1VF061 - VF062
1VF071 - VF072
1VF091 - VF093
1VF101 - VF102
1VF161 - VF162
1VF171 - VF172
1VF180 - VF184
1VF251
1VK001 - VK016
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GroupVariable Number
1VK021 - VK022
1VK031 - VK056
1VK081 - VK113
1VK131 - VK133
1VK141 - VK148
1VK161 - VK164
1VK171
1VK181
1VK186
1VL001 - VL006
1VL011
1VL701 - VL703
1VL751 - VL755
1VL806 - VL807
1VL871 - VL873
1VL891 - VL900
1VL911 - VL914
1VL931 - VL932
1VL941
1VN001 - VN041
1VN051 - VN064
1VN081 - VN099
1VN111 - VN127
1VN130 - VN137
1VN151 - VN158
1VN163 - VN168
1VN171 - VN174
1VN191 - VN198
1VN211 - VN212
1VN221 - VN225
1VN231 - VN234
1VN241 - VN243
1VN251 - VN276
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GroupVariable Number
1VN291 - VN293
1VN301 - VN314
1VN371 - VN372
1VN376
1VN381 - VN388
1VN421 - VN427
1VN436
1VN471 - VN472
1VN491 - VN513
1VN531 - VN532
1VN536 - VN537
1VN541 - VN542
1VN546 - VN547
1VN551
1VN556 - VN557
1VN561 - VN562
1VN631 - VN638
1VN651 - VN658
1VN671 - VN672
1VN676
1VN681 - VN691
1VN731 - VN732
1VN751 - VN753
1VN791 - VN792
1VN811 - VN813
1VN921 - VN922
1VN931 - VN936
1VN951 - VN953
1VN966 - VN972
4VQ001 - VQ018
3VQ019 - VQ021
4VQ071 - VQ076
3VQ077 - VQ086
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GroupVariable Number
3VQ111
2VR051 - VR060
2VR081
2VR084
2VR086 - VR087
1VR088 - VR089
1VR106 - VR109
1VR201
2VR202 - VR211
1VR251
2VR256 - VR260
1VR266 - VR270
1VR401
1VR421
2VR422 - VR423
1VR426
2VR441
1VR461
2VR471 - VR472
1VS051 - VS052
2VS053 - VS056
1VS061
1VS066 - VS070
1VS073
2VS074 - VS078
1VS091 - VS094
2VS095 - VS104
1VS111
2VS112 - VS113
1VS131 - VS132
2VS133
2VS136 - VS137
1VS176 - VS177
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GroupVariable Number
1VS186 - VS187
1VS196 - VS199
2VS200 - VS203
1VS206 - VS207
2VS208
2VS211
2VS216 - VS217
2VS231
1VS246 - VS248
1VS261
2VS262
1VS263
1VS266 - VS267
2VS268 - VS274
2VS291 - VS293
2VS301 - VS303
2VS306 - VS311
2VS316
2VS321 - VS324
2VS331 - VS333
1VS336 - VS337
2VS366 - VS367
2VS381 - VS382
2VS391 - VS392
2VS401
1VS426 - VS428
2VS466 - VS472
2VS486
2VS496 - VS497
2VS506 - VS507
2VS526
2VS546 - VS549
1VS701 - VS703
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GroupVariable Number
2VS704 - VS708
1VS709 - VS728
2VS729
1VS730 - VS736
1VS751 - VS753
2VS754 - VS759
1VS821 - VS823
2VS824 - VS825
1VS841 - VS843
2VS844
2VS861
2VS881
1VS882 - VS883
1VS891
1VS896
1VS901 - VS912
1VS916
1VS921 - VS925
1VS931 - VS933
1VT501
1VT511 - VT513
1VT521 - VT523
1VT531 - VT533
1VT541 - VT543
1VV001
1VW701 - VW721
1VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
This inspection/replacement will make sure the fuel tank boost pump and override/jettison pump wiring
is not chafed and will not cause arcing inside the fuel tank.
The fuel tank boost pump and override/jettison pump wiring is installed with a double layer of Teflon
sleeving in the conduit. The sleeving is installed to prevent arcing between the boost pump power
wiring and the conduit caused by wire chafing.
767 Maintenance Planning Data (MPD) Section 9, Airworthiness Limitation (AWL) 28-AWL-30 is
applicable to airplanes after incorporation of this service bulletin.
For Group 2 airplanes, this service bulletin now replaces Boeing Service Bulletin 767-28A0079. For
Group 4 airplanes, this service bulletin now replaces Boeing Service Bulletin 767-28A0080.
Boeing Fleet Team Digest (FTD) 767 FTD 28-07001 is related to this service bulletin.
Revision 1 was sent to tell operators that two top kits are required for each airplane. Also, steps 3.J.20,
note 1, 3.J.21.e are changed to refer to the P37 panel. On pages 31, 38, and 39 more details are
referenced in the views. On page 41, all the wires have been changed to 14 gage. On page 42, the
correct part numbers for the inner and outer sleeves have been added.
Revision 2 is sent to tell operators that Compliance is revised. Operators have reported finding fuel
pump wire bundle chafing before 30,000 flight cycles, or 60,000 flight hours. The wire bundle chafing
could possibly wear away the sleeving, jacket and wire installation and expose metal conductors, which
could result in electrical arcing. Boeing recommends that the operators accomplish the wiring inspection
given in this service bulletin within 15,000 flight hours from the last inspection, or 6,000 flight hours
from the date of this revision, whichever occurs later, but not to exceed 60,000 flight hours from the
last inspection. The inspection will be required to be repeated every 15,000 flight hours from the previous
inspection.
Revision 3 is sent to revise the effectivity, replace service bulletins 767-28A0079 and 767-28A0080,
clarify the accomplishment instructions, and remove the optional fuel pump check.
D. Description
The four fuel pump access doors are removed. The boost and override/jettison pump wire bundles are
removed from the conduits. The sleeves and wires are inspected and any damage that is found is
repaired. The wire bundles are installed back into the conduits. The four fuel pump access doors are
installed. A test of the boost and override/jettison pumps is done.
Revision 1 - More work may be necessary on airplanes changed as shown in the initial release of this
service bulletin. Operators must make sure that the wiring and sleeve configuration to the override/jettison
pumps is the same as shown in this revision.
Revision 2 - No more work is necessary on airplanes changed as shown in the revision 1 of this service
bulletin.
Revision 3 - No more work is necessary on airplanes changed in accordance with Revision 1 or Revision
2 of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1-2:
Affected Maintenance Zones
ZoneModel
531, 532, 631, 632767-200, 767-300, 767-300F
Group 3-4:
Affected Maintenance Zones
ZoneModel
531, 532, 631, 632767-400ER
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2000-11-06 is related to this service
bulletin.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2010-NM-148-AD is
related to this service bulletin.
Boeing recommends that the operators accomplish the wiring inspection given in this service bulletin
within 15,000 flight hours from the last inspection, or 6,000 flight hours from the date of Revision 2,
whichever occurs later, but not to exceed 60,000 flight hours from the last inspection. The inspection
will be required to be repeated every 15,000 flight hours from the previous inspection.
The accomplishment of the change given in Boeing Service Bulletin 767-28-0104 is the terminating
action for the repetitive inspection given in 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.
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office approves the inspection and the replacement, as required, of the engine fuel feed
boost and override/jettison pump wire bundle and sleeves, as described in this service bulletin, as an
alternative method of compliance with the requirements of paragraphs (a),(b),(c) and (d) of FAA AD
2000-11-06. All provisions of FAA AD 2000-11-06 that are not specifically referenced in the above
statement remain fully applicable and must be met.
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G. Manpower
The table below shows an estimate of the man-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
man-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
0.250.251Prepare
0.51.02Open Access
Change:
2.03.752With Jet Pumps
1.52.752W/O Jet Pumps
0.51.02Close Access
Test:
0.50.51With Jet Pumps
0.250.251W/O Jet Pumps
TOTAL FOR EACH AIRPLANE:
3.756.5WITH JETTISON PUMPS
3.05.25WITHOUT JETTISON PUMPS
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletins 767-28-0027, 767-28-0104, 767-28A0079, 767-28A0080
b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2000-11-06
c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2010-NM-148-AD
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d. Standard Wiring Practices Manual (SWPM) 20-00-10, 20-00-13, 20-10-11, 20-10-12, 20-10-13,
20-10-18, 20-10-19, 20-20-00
e. 767 Aircraft Maintenance Manual (AMM) 06-44-00, 20-10-09, 28-11-00, 28-22-00, 28-31-00
f. 767 Fleet Team Digest (FTD) 28-07001
g. 767-400 Aircraft Maintenance Manual (AMM) 06-44-00, 20-10-09, 28-11-00, 28-22-00, 28-31-00
h. 767 Maintenance Planning Data (MPD) Section 9, Airworthiness Limitation (AWL) 28-AWL-30
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Equipment Installation - Engine Fuel Feed System343T0002
Tubing Installation - Engine Fuel Feed System343T0010
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-22767 Aircraft Maintenance 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
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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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. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits 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 3
date of this Service Bulletin (US
Dollars)
ROLT as of the Revision 3
date of this Service Bulletin
(Calendar Days)
NameKit Number
$1452.00149Top Kit, Fuel Pump Wire
Bundle Sleeves
015T0872-30
B. Industry Support Information
Group 1, 3:
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
Group 2, 4:
Boeing warranty remedies are available for 767 airplanes in warranty as of July 11, 2002. For task hour
and material reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Commercial Airplanes Group - Warranties.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
NOTE: Two top kits are necessary for each airplane. The operator supplied materials shown
below are for reference only. These parts may be necessary only if repairs are made to
the airplane wiring.
Kit, Fuel Pump Wire Bundle Sleeves015T0872
-30-3-4
NamePart NumberQTY
Top Kit, Fuel Pump Sleeves015T0872-30-..
Kit, Boost Pump015T0872-32-.
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Kit, Fuel Pump Wire Bundle Sleeves015T0872
-30-3-4
NamePart NumberQTY
Kit, Override/Jettison Pumps015T0872-42.-
Sleeve, Inner015T0872-10.1.
Sleeve, Inner015T0872-20..1
Sleeve, Outer015T0872-21.1.
Sleeve, Outer015T0872-22..1
2. Parts and Materials Supplied by the Operator:
NamePart Number (Specification)QTY
Contact, Boost PumpsBACC47CP2T-
Contact, Override/Jettison PumpsBACC47CP3T-
Connector, Boost PumpsBACC63BP14A7SNL-
(BACC63BP14H7SN optional)
Connector, Override/Jettison PumpsBACC63BP18A8SNL-
(BACC63BP18H8SN optional)
Lug, Shield GroundBACT12AR204-
Wire, Boost Pumps, PowerBMS 13-48, Type 12, Class 3, AWG 18 (EDP
Code VH) (b) (c)
14 feet (a)
Wire, Override/Jettison Pumps, PowerBMS 13-48, Type 15, Class 3, AWG 14 (EDP
Code OC) (b) (c)
14 feet (a)
Wire, Boost Pumps, GroundBMS 13-48, Type 8, Class 1, AWG 18 (EDP
Code UA) (b) (c)
14 feet (a)
Wire, Override/Jettison Pumps, GroundBMS 13-48, Type 8, Class 1, AWG 14 (EDP
Code UA) (b) (c)
14 feet (a)
Lacing TapeBMS 13-54, Grade D, Type II or III, Class 1,
Finish C, Width 0.11 inches, Color White (b)
-
Splice, 18 Gauge WireD436-37 (d)-
Splice, 14 Gauge WireD436-38 (d)-
Sleeve, Inner, Boost Pumps (Main Tank)TFE-2X, Standard Wall, Size #6 (0.30 ID), Color
Natural (also M23053/12-218C)
12 feet (a) (e)
Sleeve, Outer, Boost Pumps (Main Tank)TFE-2X, Standard Wall, Size #2 (0.43 ID), Color
Natural (also M23053/12-223C), (TFE-2XTW,
Thin Wall, M23053/12-327C Optional)
12 feet (a) (e)
Sleeve, Inner, Override/Jettison Pumps (Aux
Tank)
TFE-2X, Standard Wall, Size #4 (0.37 ID), Color
Natural (also M23053/12-221C)
12 feet (a) (e)
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NamePart Number (Specification)QTY
Sleeve, Outer, Override/Jettison Pumps (Aux
Tank)
TFE-2X, Standard Wall, Size #0 (0.47 ID), Color
Natural (also M23053-12-225C), (TFE-2XTW,
Thin Wall, M23053-12-329C Optional) (f)
12 feet (a) (e)
Conduit, Right Boost Pump343T0010-121
Conduit, Right Override Pump343T0010-361
Conduit, Left Boost Pump343T0010-511
Conduit, Left Override/Jettison Pump343T0010-591
Conduit, Right Override/Jettison Pump343T0010-601
Conduit, Left Override Pump343T0010-1091
(a) Lengths are adequate for repair at any of the conduit locations.
(b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(c) Refer to the Standard Wiring Practices Manual SWPM 20-00-13 for optional wire.
(d) Raychem Corp. (V06090), 300 Constitution Drive, Menlo Park California 94025-1111.
(e) Port Plastics Incorporated, 1228 Andover Park East, Tukwila Washington 98188, Phone: (206) 575-4994,
Fax: (206) 575-6920. Port Plastics has agreed to provide this material in 12 foot lengths as necessary to
support this inspection.
(f) M23053-12-226C or M23053-12-227C is optional to M23053-12-225C.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. 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
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51 and Boeing
Drawing 012W6100.
5. Refer to SWPM 20-00-10 for the safety procedures, SWPM 20-10-11 and SWPM
20-10-12 for the wire installation procedures, SWPM 20-10-13 for the wire bundle
repair procedures, SWPM 20-10-18 for the sleeve installation procedures, and SWPM
20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
8. 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.
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9. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
11. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
12. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
B. WORK INSTRUCTIONS
1. Open these circuit breakers and attach DO-NOT-CLOSE tags:
NomenclatureC/B Panel
L FWD FUEL BOOST PUMPP6, G24
L AFT FUEL BOOST PUMPP6, G15
R FWD FUEL BOOST PUMPP6, G18
R AFT FUEL BOOST PUMPP6, G21
L FUEL OVRD PUMPP6, F15
R FUEL OVRD PUMPP6, F21
FUEL PUMPS R FWD / L AFTP11, M16
FUEL PUMPS L FWD / R AFTP11, M25
L CTR FUEL PUMPSP11, M15
R CTR FUEL PUMPSP11, M24
If the fuel jettison pumps are installed:
L FUEL JTSN CONTP11, M13
L FUEL JETT PUMPP36, F4 or G7
L FUEL JETT PUMPP89
(airplanes with service bulletin 767-28-0027)
R FUEL JTSN CONTP11, M22
R FUEL JETT PUMPP37, F4 or G4
R FUEL JETT PUMPP89
(airplanes with service bulletin 767-28-0027)
2. Remove the access covers 531AB, 532AB, 631AB and 632AB in accordance with FIGURE 1.
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3. Remove the fuel pump wire bundles from the conduits in accordance with the figure below.
a. Group 1-2:
Use FIGURE 2.
b. Group 3-4:
Use FIGURE 6.
4. For each wire bundle, do an inspection of the outer sleeve for these conditions:
a. The sleeve is not one continuous piece through the conduit (more than one piece of sleeve)
b. Cuts, splits, holes, or worn areas
c. Ties on the outside of the sleeve, except at the ends.
5. For each wire bundle:
a. If none of the above conditions are found, no further inspection is necessary. Go to step 9.
b. If one or more of the above conditions is found:
(1) Remove the outer and inner sleeves between the pump connector and the first clamp on
the rear spar.
(2) Continue to step 6.
6. Do an inspection of the wires.
a. If no damage is found, no further inspection is necessary. Go to Step 9.
b. If damage is found, continue to step 7.
7. Find if the wire damage was caused by arcing.
NOTE: Arcing can show as very small blackened holes in the insulation or as deformation or
pitting of the copper wire. Worn areas with a black material around the edge is not a sign
of arcing; the black material is aluminum oxide.
a. If the wire damage is not caused by arcing:
(1) Repair or replace the damaged wires.
(2) Go to step 9.
b. If damage caused by arcing is found, continue to step 8.
8. Do an inspection for signs of fuel inside the conduit or on the wires.
a. If signs of fuel are found:
(1) Replace the conduit. Refer to 767 AMM 20-10-09 or 767-400 AMM 20-10-09 as an
accepted procedure.
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(2) Replace the damaged wires.
NOTE: Repair of the damaged wires is not permitted. Refer to FAA AD 2000-11-06,
paragraph (c)(2)(ii).
(3) Continue to step 9.
b. If no sign of fuel is found:
(1) Repair or replace the damaged wires.
(2) Do one of these tests to find if there is a fuel leak in the electrical conduit:
(a) Use the necessary fittings to plug one end of the conduit. Use the backblowing
procedure to do a leak check. Refer to 767 AMM 28-11-00 or 767-400 AMM 28-11-00,
Air Pressure and Bubble Solution (Backblowing) Procedure, as an accepted
procedure.
(b) Use the necessary fittings to plug one end of the conduit. Connect a pressure gage
and air supply to the other end of the conduit. Pressurize the conduit to 20 PSIG and
shut off the air supply. Wait 5 minutes. Examine the gage. Make sure the pressure
has not dropped more than 0.5 PSIG.
(c) Fill the applicable fuel tank with fuel to Volumetric Top-Off (VTO). After 5 minutes,
make sure there is no sign of fuel leakage at the ends of the electrical conduit.
Examine both the end of the electrical conduit at the rear spar, and the end near the
fuel pump.
(d) Fill the applicable fuel tank with fuel to Volumetric Top-Off (VTO). Pull a clean cloth
through the electrical conduit with a string. Make sure there is no fuel on the cloth.
(3) After the leak test:
(a) If there is no fuel leak in the electrical conduit, do step 1 or step 2 below.
1) Replace the conduit immediately. Refer to 767 AMM 20-10-09 or 767-400 AMM
20-10-09 as an accepted procedure.
2) Replace the conduit within 6000 flight hours or 18 months, whichever comes
first. Repeat step 8.b.2. every 500 flight hours until the conduit is replaced.
(b) If there is a fuel leak in the electrical conduit, replace the conduit. Refer to 767 AMM
20-10-09 or 767-400 AMM 20-10-09 as an accepted procedure.
(c) Continue to step 9.
9. Install the wire bundle in the conduit in accordance with the figure below.
a. Group 1-2:
(1) Use FIGURE 3 for a boost pump wire bundle.
(2) Use FIGURE 4 for an override or override/jettison pump wire bundle.
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b. Group 3-4:
(1) Use FIGURE 7 for a boost pump wire bundle.
(2) Use FIGURE 8 for an override/jettison pump wire bundle.
10. Go back to step 4 to inspect the next wire bundle. When all wire bundles have been inspected and
installed in the conduits, continue to Step 11.
11. Close these circuit breakers and remove the DO-NOT-CLOSE tags:
NomenclatureC/B Panel
L FWD FUEL BOOST PUMPP6, G24
L AFT FUEL BOOST PUMPP6, G15
R FWD FUEL BOOST PUMPP6, G18
R AFT FUEL BOOST PUMPP6, G21
L FUEL OVRD PUMPP6, F15
R FUEL OVRD PUMPP6, F21
FUEL PUMPS R FWD / L AFTP11, M16
FUEL PUMPS L FWD / R AFTP11, M25
L CTR FUEL PUMPSP11, M15
R CTR FUEL PUMPSP11, M24
If the fuel jettison pumps are installed:
L FUEL JTSN CONTP11, M13
L FUEL JETT PUMPP36, F4 or G7
L FUEL JETT PUMPP89
(airplanes with service bulletin 767-28-0027)
R FUEL JTSN CONTP11, M22
R FUEL JETT PUMPP37, F4 or G4
R FUEL JETT PUMPP89
(airplanes with service bulletin 767-28-0027)
12. Do an operational check of the boost pumps. Refer to 767 AMM 28-22-00 or 767-400 AMM
28-22-00, Test of the Left Forward Boost Pump, Test of the Left Aft Boost Pump, Test of the Right
Forward Boost Pump and Test of the Right Aft Boost Pump, as accepted procedures.
13. Do an operational check of the override pumps. Refer to 767 AMM 28-22-00 or 767-400 AMM
28-22-00, Test of the Override Pumps and Pressure Switches in the Auxiliary Fuel Tank, as an
accepted procedure.
14. If installed, do an operational check of the jettison pumps. Refer to 767 AMM 28-31-00 or 767-400
AMM 28-31-00, Test of the Left Override/Jettison Pump and Test of the Right Override/Jettison
Pump, as accepted procedures.
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15. Put back the access covers 531AB, 532AB, 631AB and 632AB in accordance with FIGURE 5.
16. Put the airplane back into serviceable condition.
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BOEING SERVICE BULLETIN 767-28A0053
ACCESS COVER 3  ACCESS COVER
531 AB  532AB
SEE
SEE
00•00
ACCESS COVER 5
631 AB
SEE A
ACCESS COVER 7)
632AB
SEE A
UP
LANYARD
DRAIN HOLE
COVER
BOLT
DRAIN HOLE  (8 LOCATIONS)
S44899
FIGURE 1: GET ACCESS TO THE FUEL PUMP CONNECTORS
(SHEET 1 OF 2)
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### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART
NUMBER
NAMETASKSTEP
(a)1-Cover (532AB)Hold1
8-BoltRemove and Save
Let the lanyard hold the access cover.1-CoverLower2
(a)1-Cover (531AB)Hold3
8-BoltRemove and Save
Let the lanyard hold the access cover.1-CoverLower4
(a)1-Cover (631AB)Hold5
8-BoltRemove and Save
Let the lanyard hold the access cover.1-CoverLower6
(a)1-Cover (632AB)Hold7
8-BoltRemove and Save
Let the lanyard hold the access cover.1-CoverLower8
(a) Refer to 767 AMM 06-44-00 or 767-400 AMM 06-44-00 for the cover location.
FIGURE 1: GET ACCESS TO THE FUEL PUMP CONNECTORS
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 767-28A0053
This Figure applies only to: Group 1-2.
SEE
BOOST PUMPS
SEE
OVERRIDE/JETTISON PUMPS
SEE
OVERRIDE PUMP WITHOUT JETTISON PUMPS  00000
OVERRIDE/JETTISON PUMPS
OVERRIDE PUMP WITHOUT
JETTISON PUMPS
SEE
BOOST PUMPS
SEE (C
FWD C
FWD<
BOOST PUMPS (ALL AIRPLANES)
OVERRIDE PUMP
OVERRIDE/ JETTISON PUMPS
(AIRPLANES WITHOUT JETTISON PUMPS)
FIGURE 2: 767-200/-300/-300F AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE
CONDUIT
(SHEET 1 OF 3)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
REAR SPAR
WS
273
FWD
• INBD
LEFT SIDE SHOWN,
RIGHT SIDE OPPOSITE
S45910
FIGURE 2: 767-200/-300/-300F AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE
CONDUIT
(SHEET 2 OF 3)
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### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the total number of parts necessary for the airplane.
NOTESQTYPART
NUMBER
NAMETASKSTEP
6 or 8 (a)-Pump ConnectorDisconnect /1
Remove / Save
4-Clamps and FastenersRemove and Save2
6 or 8 (a)-Ground wireDisconnect3
The cord must be long enough
to go all the way through the
conduit.
4-CordTie4
4-Clamps and FastenersRemove and Save5
6 or 8 (a)-Wire bundlePull6
(a) Quantity = 6 if the airplane has override pumps only. Quantity = 8 if jettison pumps are installed.
FIGURE 2: 767-200/-300/-300F AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE
CONDUIT
(SHEET 3 OF 3)
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This Figure applies only to: Group 1-2.
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 1 OF 6)
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BOEING SERVICE BULLETIN 767-28A0053
PUMP POWER WIRES  SHIELD
TERMINATION
SEE C
SHIELD
TERMINATION
TASKS  CLAMP
BEFORE CLAMP  INSTALLATION
INSTALLATION  TASKS
BOOST PUMP WIRING
LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE
3 PUMP
SHIELD GROUND WIRE
POWER
CASE GROUND WIRE
WIRES
SHIELD TERMINATION
S45921
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 2 OF 6)
Original Issue: October 29, 1998
Revision 3 November 11, 2011  Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  767-28A0053  39 of 72

### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
SEE •G
® SEE O
SEE • AND  FWD  O SEE O AND E
BOOST PUMPS
B
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 3 OF 6)
Original Issue: October 29, 1998
Revision 3 November 11, 2011  767-28A0053
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### Page 41 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
SHIELD
TERMINATION
10
SHIELD TERMINATION
BEFORE CLAMP
CONFIGURATION 1
SHIELD
TERMINATION
10)
SHIELD TERMINATION
AFTER CLAMP
CONFIGURATION 2
S54852
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 4 OF 6)
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
GD4042-S 110
W478-302B-18
R  W478-302R-18
W478-302Y-18
GD3438-S 11/0R  W478-002-18
D1540
M335 RIGHT AFT
FUEL BOOST PUMP
GD4042-S 1I0
W476-301B-18
W476-301R-18
W476-301Y-18
GD3436-S I10  W476-001-18
D3986
M334 RIGHT FORWARD
FUEL BOOST PUMP
GD4048-S 110
W460-301B-18
111  W460-301R-18
W460-  -301Y-18
R
W460-001-18
D1 550
M332 LEFT FORWARD
GD4048-S 110  FUEL BOOST PUMP
W444-301B-18
W444-301R-18
W444-301Y-18
GD4110-S 'I0  W444-001-18
D1542
M333 LEFT AFT
FUEL BOOST PUMP
REFERENCE: 767 WIRING DIAGRAM 28-22-11
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 5 OF 6)
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### Page 43

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the total number of parts necessary for the airplane.
NOTESQTYPART NUMBERNAMETASKSTEP
Temporarily tie the shield ground wire
to the pump power wires.
4-Lacing TapeTie1
Leave the sleeves uncut. Do not put
ties on the sleeves except as shown in
this service bulletin. Make sure both
pieces of sleeving are one piece
through the conduit. Install ties only at
the ends of the sleeves.
4015T0872-10 or
equivalent
Sleeve, InnerInstall2 (a)
4015T0872-21 or
equivalent
Sleeve, Outer
Install the clamps and fasteners saved
in Figure 2. Put the sleeves under the
clamp.
2-Clamps and FastenersInstall3
Put the wire bundles back through the
conduits. Use the cords in the conduits.
4-Wire BundlesPull4
Install the clamps and fasteners saved
in Figure 2.
2-Clamps and FastenersInstall5
Cut the installed sleeves at the clamp
or at the shield termination. See Detail
D. Use ties if necessary to hold sleeve
ends. Make sure both pieces of sleeving
are one piece through the conduit. In-
stall ties only at the ends of the sleeves.
8-SleevesCut6 (a)
8-Temporary Lacing Tape
and Cord
Remove7
Use the remaining pieces of sleeve. Tie
the new sleeves as close to the installed
sleeves as practical. Install ties only at
the ends of the sleeves.
4015T0872-10 or
equivalent
Sleeve, InnerInstall8 (a)
4015T0872-21 or
equivalent
Sleeve, Outer
Cut the sleeves to end near the wire
contact barrels.
8-SleevesCut9 (a)
Put the sleeves under the connector
backshells.
4-Pump ConnectorsInstall /
Connect
10
Install the boost pump shield termina-
tion ground wires. Maximum resistance
is 0.005 ohms. Refer to SWPM 20-20-
00 as an accepted procedure.
4-Ground WiresInstall11
(a) Do this step only if the sleeves were removed.
FIGURE 3: 767-200/-300/-300F AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 6 OF 6)
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43 of 72
BOEING SERVICE BULLETIN 767-28A0053

### Page 44

This Figure applies only to: Group 1-2.
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 1 OF 9)
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44 of 72
BOEING SERVICE BULLETIN 767-28A0053

### Page 45 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
SHIELD
TERMINATION
UP
LOOKING FORWARD
AT LEFT REAR SPAR
SHIELD GROUND WIRE
OVERRIDE PUMP
CASE GROUND WIRE  WIRE BUNDLE
JETTISON PUMP
WIRE BUNDLE  •SHIELD
(IF INSTALLED)  TERMINATIONS
3 PUMP  UP
POWER
WIRES  LOOKING FORWARD  S54404
AT LEFT REAR SPAR
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 2 OF 9)
Original Issue: October 29, 1998
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
LOOKING FORWARD
AT RIGHT REAR SPAR
SHIELD
TERMINATION
SHIELD
GROUND
WIRE
JETTISON PUMP
WIRE BUNDLE
(IF INSTALLED)
3 PUMP
OVERRIDE PUMP
POWER WIRES  WIRE BUNDLE  UP
CASE
GROUND  LOOKING  FORWARD
WIRE  AT RIGHT REAR SPAR
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 3 OF 9)
Original Issue: October 29, 1998
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
SEE €6
3 SEE E
SEE A AND I M  FWD  0 SEE € AND F
OVERRIDE/ JETTISON PUMPS
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 4 OF 9)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
• SEE E
FWD
(7)  ® SEE €
FWD
0 SEE € AND F
FWD
OVERRIDE PUMP
(AIRPLANES WITHOUT JETTISON PUMPS)
S55055
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 5 OF 9)
Original Issue: October 29, 1998
Revision 3 November 11, 2011  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  ZL 10 8₺

### Page 49 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
SHIELD
TERMINATION
10
SHIELD TERMINATION
BEFORE CLAMP
CONFIGURATION 1
SHIELD
TERMINATION
(10)
SHIELD TERMINATION
AFTER CLAMP
CONFIGURATION 2
S55028
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 6 OF 9)
Original Issue: October 29, 1998
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
GD4058-S 110
R W478-301B-14
1R W478-301R-14
R W478-301Y-14
GD3438-5110R W478-001-14
D2804
M637 RIGHT AUX TANK
FUEL BOOST OVERRIDE PUMP
GD4052-S 1I0
• W444-302B-14
- W444-302R-14
- W444-302Y-14
GD4110-S II0  - W444-002-14
D2802
M636 LEFT AUX TANK FUEL
BOOST OVERRIDE PUMP
GD4058-S I
- W478-300Y-14
• W478-300R-14
_R W478-300B-14
GD4108-S 1I0  - W478-006-14
D12190
M1731 RIGHT JETTISON PUMP
GD4052-S I|
- W444-300Y-14
• W444-300R-14
W444-300B-14
GD4072-S 1I0  - W444-006-14
D12188
M1730 LEFT JETTISON PUMP
REFERENCE: 767 WIRING DIAGRAMS 28-22-12 AND 28-31-21  S55053
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 7 OF 9)
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Copyright © Unpublished Work - See page 1 for details.  50 of 72

### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the total number of parts necessary for the airplane.
NOTESQTYPART NUMBERNAMETASKSTEP
Temporarily tie the shield ground wire
to the pump power wires.
4-Lacing TapeTie1
Leave the sleeves uncut. Do not put
ties on the sleeves except as shown
in this service bulletin. Make sure both
pieces of sleeving are one piece
through the conduit. Install ties only
at the ends of the sleeves.
4015T0872-20 or
equivalent
Sleeve, InnerInstall2 (a)
4015T0872-22 or
equivalent
Sleeve, Outer
Install the clamps and fasteners saved
in Figure 2. For the jettison pump wire
bundles, put the sleeves under the
clamp. For the override pump wire
bundles, tie the sleeve at the break-
out.
2-Clamps and Fasten-
ers
Install3
Put the wire bundles back through the
conduits. Use the cords in the con-
duits.
2 or 4 (b)-Wire BundlesPull4
Install the clamps and fasteners saved
in Figure 2.
2-Clamps and Fasten-
ers
Install5
Cut the installed sleeves at the clamp
or at the shield termination. See Detail
E. Use ties if necessary to hold sleeve
ends. Make sure both pieces of
sleeving are one piece through the
conduit. Install ties only at the ends of
the sleeves.
8-SleevesCut6 (a)
8-Temporary Lacing
Tape and Cord
Remove7
Use the remaining pieces of sleeve.
Tie the new sleeves as close to the
installed sleeves as practical. Install
ties only at the ends of the sleeves.
4015T0872-20 or
equivalent
Sleeve, InnerInstall8 (a)
4015T0872-22 or
equivalent
Sleeve, Outer
Cut the sleeves to end near the wire
contact barrels.
8-SleevesCut9 (a)
Put the sleeves under the connector
backshells.
2 or 4 (b)-Pump ConnectorsInstall /
Connect
10
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 8 OF 9)
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BOEING SERVICE BULLETIN 767-28A0053

### Page 52

NOTESQTYPART NUMBERNAMETASKSTEP
Install the override/jettison pump
shield termination ground wires. Max-
imum resistance is 0.005 ohms. Refer
to SWPM 20-20-00 as an accepted
procedure.
2 or 4 (b)-Ground WiresInstall11
(a) Do this step only if the sleeves were removed.
(b) Quantity = 2 if the airplane has override pumps only. Quantity = 4 if jettison pumps are installed.
FIGURE 4: 767-200/-300/-300F AIRPLANES - INSTALL THE OVERRIDE/JETTISON PUMP WIRE BUNDLES
(SHEET 9 OF 9)
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BOEING SERVICE BULLETIN 767-28A0053

### Page 53 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
ACCESS COVER 2  ACCESS COVER
531 AB  532AB
SEE C
SEE
00•00
ACCESS COVER 3
631 AB
SEE
ACCESS COVER 4)
632AB
SEE A
DRAIN HOLE
LANYARD
COVER
BOLT
DRAIN HOLE
(8 LOCATIONS)
• FWD
S54400
FIGURE 5: PUT BACK THE FUEL PUMP ACCESS COVERS
(SHEET 1 OF 2)
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### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART NUMBERNAMETASKSTEP
-1-Cover (532AB)Install1
Saved in Figure 1.8-BoltUse:
-1-Cover (531AB)Install2
Saved in Figure 1.8-BoltUse:
-1-Cover (631AB)Install3
Saved in Figure 1.8-BoltUse:
-1-Cover (632AB)Install4
Saved in Figure 1.8-BoltUse:
FIGURE 5: PUT BACK THE FUEL PUMP ACCESS COVERS
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 767-28A0053

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
This Figure applies only to: Group 3-4.
SEE A
BOOST PUMPS
SEE
OVERRIDE/JETTISON PUMPS
OVERRIDE/  pooooo
JETTISON PUMPS
SEE
SEE A
BOOST PUMPS
SEE ©  SEE B
FWD C
BOOST PUMPS (ALL AIRPLANES)
OVERRIDE/ JETTISON PUMPS
2059886
FIGURE 6: 767-400ER AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE CONDUIT
(SHEET 1 OF 4)
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### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
REAR SPAR
WS
273
FWD
• INBD
LEFT SIDE
2059997
FIGURE 6: 767-400ER AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE CONDUIT
(SHEET 2 OF 4)
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### Page 57 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
REAR SPAR
WS
273
FWD
INBD
RIGHT SIDE
2060009
FIGURE 6: 767-400ER AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE CONDUIT
(SHEET 3 OF 4)
Original Issue: October 29, 1998
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### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the total number of parts necessary for the airplane.
NOTESQTYPART
NUMBER
NAMETASKSTEP
8-Pump ConnectorDisconnect /1
Remove / Save
4-Clamps and FastenersRemove and Save2
8-Ground wireDisconnect3
The cord must be long enough to go
all the way through the conduit.
4-CordTie4
optional (a)1-Clamp and FastenerRemove and Save5
8-Wire bundlePull6
(a) This clamp is installed on the left override/jettison pump wire bundle only. It may not be installed on all
airplanes. Remove this clamp if necessary to pull the wire bundle out of the conduit.
FIGURE 6: 767-400ER AIRPLANES - REMOVE THE FUEL PUMP WIRE BUNDLES FROM THE CONDUIT
(SHEET 4 OF 4)
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58 of 72
BOEING SERVICE BULLETIN 767-28A0053

### Page 59

This Figure applies only to: Group 3-4.
FIGURE 7: 767-400ER AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 1 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 29, 1998
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59 of 72
BOEING SERVICE BULLETIN 767-28A0053

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-28A0053
PUMP POWER WIRES
SHIELD
TERMINATION
→ SEE
SHIELD
TERMINATION
TASKS  CLAMP
BEFORE CLAMP  INSTALLATION
INSTALLATION  TASKS
BOOST PUMP WIRING
LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE
(A)
SHIELD GROUND WIRE  3 PUMP
POWER
CASE GROUND WIRE
WIRES
SHIELD TERMINATION
2060319
FIGURE 7: 767-400ER AIRPLANES - INSTALL THE BOOST PUMP WIRE BUNDLES
(SHEET 2 OF 6)
Original Issue: October 29, 1998
Revision 3 November 11, 2011  BOEING PROPRIETARY -  767-28A0053
Copyright © Unpublished Work - See page 1 for details.  60 of 72

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