# Boeing Alert Service Bulletin 727-28A0133: No revision named

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- Document: [Boeing Alert Service Bulletin 727-28A0133](https://openairdocs.org/service-documents/boeing/727-28a0133.md)
- Title as filed: Boeing - Commercial Airplanes - Service Bulletin 727
- Pages: 300
- PDF: https://openairdocs.org/files/sha256/3e/54/3e5428f021d5a68a842be48d93b45d80fd53b235f25e3fc301da3a04cc3a97f8
- Page: https://openairdocs.org/service-documents/boeing/727-28a0133/file/3e5428f021d5

## Text

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### Page 1

Commercial 
Airplanes
727
Service Bulletin
ALERT
Number: 727-28A0133
Original Issue: October 05, 2011
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Wing and Center Tank Fuel Boost Pump Wire
Bundle Replacement and Convoluted Liner Installation
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2011 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 5
B. Concurrent Requirements ...................................... 1 6
C. Reason ................................................ 1 6
D. Description .............................................. 1 7
E. Compliance .............................................. 1 7
F. Approval ............................................... 1 7
G. Manpower .............................................. 1 8
H. Weight and Balance Changes .................................... 2 1
I. Electrical Load Data ......................................... 2 1
J. References .............................................. 2 1
1. Existing Data .......................................... 2 1
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 2
L. Interchangeability and Intermixability of Parts ........................... 2 2
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 4
C. Parts Necessary For Each Airplane ................................. 2 4
1. Kits/Parts ............................................ 2 4
2. Parts and Materials Supplied by the Operator ........................ 3 5
3. Parts Modified and Reidentified ................................ 3 5
4. Parts Removed and Not Replaced .............................. 3 5
D. Parts Necessary to Change Spares ................................. 3 5
E. Special Tooling - Price and Availability ............................... 3 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 7
A. GENERAL INFORMATION ..................................... 3 7
B. WORK INSTRUCTIONS ....................................... 3 8
FIGURE 1: STATION 720F UPPER LEFT GROUND BRACKET - INSTALLATION ........... 5 5
FIGURE 2: STATION 720F LOWER LEFT GROUND BRACKET - INSTALLATION .......... 5 8
FIGURE 3: STATION 720F RIGHT GROUND BRACKET - INSTALLATION .............. 6 1
FIGURE 4: STATION 740 BULKHEAD STIFFENER GROUND BRACKET - INSTALLATION ..... 6 4
FIGURE 5: LEFT WING - NO. 1 TANK AND NO. 2 TANK FUEL BOOST PUMP REMOVAL, AND RIGHT
WING NO. 2 TANK AND NO. 3 TANK FUEL BOOST PUMP - REMOVAL ......... 6 6
FIGURE 6: LEFT WING - NO. 1 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W488 AND NO. 2 TANK
LEFT AFT FUEL BOOST PUMP WIRE BUNDLE W492 - REMOVAL ............ 6 8
FIGURE 7: LEFT WING - NO. 1 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W488 - REMOVAL . 72
FIGURE 8: LEFT WING - NO. 2 TANK LEFT AFT FUEL BOOST PUMP WIRE BUNDLE W492 - REMOVAL
.................................................. 7 3
FIGURE 9: LEFT WING - NO. 1 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W486 AND NO.
2 TANK LEFT FORWARD FUEL BOOST PUMP WIRE BUNDLE W490 - REMOVAL . . . 74
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FIGURE 10: LEFT WING - NO. 1 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W486 - REMOVAL
.................................................. 7 8
FIGURE 11: LEFT WING - NO. 2 TANK LEFT FORWARD FUEL BOOST PUMP WIRE BUNDLE W490 -
REMOVAL ........................................... 7 9
FIGURE 12: LEFT WING - NO. 1 TANK AFT FUEL TANK CONDUIT - REPLACEMENT ........ 8 0
FIGURE 13: LEFT WING - NO. 2 TANK LEFT AFT FUEL TANK CONDUIT - REPLACEMENT ..... 8 3
FIGURE 14: LEFT WING - NO. 1 TANK FORWARD FUEL TANK CONDUIT - REPLACEMENT .... 8 6
FIGURE 15: LEFT WING - NO. 2 TANK LEFT FORWARD FUEL TANK CONDUIT - REPLACEMENT . 89
FIGURE 16: LEFT WING FRONT SPAR WIRE BUNDLE W488 AND WIRE BUNDLE W492 - ROUTING
.................................................. 9 2
FIGURE 17: NO. 1 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W488 - REMOVAL OR STOWAGE
.................................................. 9 6
FIGURE 18: NO. 2 TANK LEFT AFT FUEL BOOST PUMP WIRE BUNDLE W492 - REMOVAL OR STOWAGE
................................................. 1 0 0
FIGURE 19: LEFT WING FRONT SPAR CONVOLUTED LINERS, WIRE BUNDLE W488, AND WIRE BUNDLE
W492 - INSTALLATION ................................... 1 0 4
FIGURE 20: LEFT WING FRONT SPAR WIRE BUNDLE W488 AND WIRE BUNDLE W492 - ROUTING
................................................. 1 1 1
FIGURE 21: LEFT WING - NO. 1 TANK AFT FUEL BOOST PUMP - INSTALLATION ......... 1 1 7
FIGURE 22: LEFT WING - NO. 1 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W488 - WIRING CHANGE
................................................. 1 2 1
FIGURE 23: LEFT WING - NO. 2 TANK LEFT AFT FUEL BOOST PUMP - INSTALLATION ...... 1 2 6
FIGURE 24: LEFT WING - NO. 2 TANK LEFT AFT FUEL BOOST PUMP WIRE BUNDLE W492 - WIRING
CHANGE ........................................... 1 3 0
FIGURE 25: STATION 720F UPPER LEFT GROUND STUD ASSEMBLY - WIRE BUNDLE W488 AND WIRE
BUNDLE W492 ........................................ 1 3 5
FIGURE 26: LEFT WING REAR SPAR WIRE BUNDLE W486 AND WIRE BUNDLE W490 - ROUTING . 138
FIGURE 27: NO. 1 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W486 - REMOVAL OR
STOWAGE .......................................... 1 4 2
FIGURE 28: NO. 2 TANK LEFT FORWARD FUEL BOOST PUMP WIRE BUNDLE W490 - REMOVAL OR
STOWAGE .......................................... 1 4 6
FIGURE 29: LEFT WING REAR SPAR CONVOLUTED LINER, WIRE BUNDLE W486, AND WIRE BUNDLE
W490 - INSTALLATION ................................... 1 5 0
FIGURE 30: LEFT WING REAR SPAR FUEL BOOST PUMP WIRE BUNDLE W486 AND WIRE BUNDLE
W490 - ROUTING ....................................... 1 5 7
FIGURE 31: LEFT WING - NO. 1 TANK FORWARD FUEL BOOST PUMP - INSTALLATION ..... 1 6 3
FIGURE 32: LEFT WING - NO. 1 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W486 - WIRING
CHANGE ........................................... 1 6 7
FIGURE 33: LEFT WING - NO. 2 TANK LEFT FORWARD FUEL BOOST PUMP - INSTALLATION . 172
FIGURE 34: LEFT WING - NO. 2 TANK LEFT FORWARD FUEL BOOST PUMP WIRE BUNDLE W490 -
WIRING CHANGE ...................................... 1 7 6
FIGURE 35: STATION 720F LOWER LEFT GROUND STUD ASSEMBLY - WIRE BUNDLE W486 AND
WIRE BUNDLE W490 .................................... 1 8 1
FIGURE 36: RIGHT WING - NO. 2 TANK RIGHT AFT FUEL BOOST PUMP WIRE BUNDLE W496 AND NO.
3 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W500 - REMOVAL .......... 1 8 4
FIGURE 37: RIGHT WING - NO. 2 TANK RIGHT AFT FUEL BOOST PUMP WIRE BUNDLE W496 -
REMOVAL ........................................... 1 8 8
FIGURE 38: RIGHT WING - NO. 3 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W500 - REMOVAL
................................................. 1 8 9
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FIGURE 39: RIGHT WING - NO. 2 TANK RIGHT FORWARD FUEL BOOST PUMP WIRE BUNDLE W494
AND NO. 3 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W498 - REMOVAL . 190
FIGURE 40: RIGHT WING - NO. 2 TANK RIGHT FORWARD FUEL BOOST PUMP WIRE BUNDLE W494
- REMOVAL .......................................... 1 9 4
FIGURE 41: RIGHT WING - NO. 3 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W498 - REMOVAL
................................................. 1 9 5
FIGURE 42: RIGHT WING - NO. 2 TANK RIGHT AFT FUEL TANK CONDUIT - REPLACEMENT . . 196
FIGURE 43: RIGHT WING - NO. 3 TANK AFT FUEL TANK CONDUIT - REPLACEMENT ....... 1 9 9
FIGURE 44: RIGHT WING - NO. 2 TANK RIGHT FORWARD FUEL TANK CONDUIT - REPLACEMENT
................................................. 2 0 2
FIGURE 45: RIGHT WING - NO. 3 TANK FORWARD FUEL TANK CONDUIT - REPLACEMENT . . 205
FIGURE 46: RIGHT WING FRONT SPAR FUEL BOOST PUMP WIRE BUNDLE W496 AND WIRE BUNDLE
W500 - ROUTING ....................................... 2 0 8
FIGURE 47: NO. 2 TANK RIGHT AFT FUEL BOOST PUMP WIRE BUNDLE W496 - REMOVAL OR
STOWAGE .......................................... 2 1 2
FIGURE 48: NO. 3 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W500 - REMOVAL OR STOWAGE
................................................. 2 1 6
FIGURE 49: RIGHT WING FRONT SPAR CONVOLUTED LINERS, WIRE BUNDLE W496, AND WIRE
BUNDLE W500 - INSTALLATION .............................. 2 2 0
FIGURE 50: RIGHT WING FRONT SPAR FUEL BOOST PUMP WIRE BUNDLE W496 AND WIRE BUNDLE
W500 - ROUTING ....................................... 2 2 7
FIGURE 51: RIGHT WING - NO. 2 TANK RIGHT AFT FUEL BOOST PUMP - INSTALLATION .... 2 3 3
FIGURE 52: NO. 2 TANK RIGHT AFT FUEL BOOST PUMP WIRE BUNDLE W496 - WIRING CHANGE . 237
FIGURE 53: RIGHT WING - NO. 3 TANK AFT FUEL BOOST PUMP - INSTALLATION ........ 2 4 2
FIGURE 54: NO. 3 TANK AFT FUEL BOOST PUMP WIRE BUNDLE W500 - WIRING CHANGE . . . 246
FIGURE 55: STATION 720F RIGHT GROUND STUD ASSEMBLY - WIRE BUNDLE W496 AND WIRE
BUNDLE W500 ........................................ 2 5 1
FIGURE 56: RIGHT WING FRONT SPAR FUEL BOOST PUMP WIRE BUNDLE W494 AND WIRE BUNDLE
W498 - ROUTING ....................................... 2 5 4
FIGURE 57: NO. 2 TANK RIGHT FORWARD FUEL BOOST PUMP WIRE BUNDLE W494 - REMOVAL OR
STOWAGE .......................................... 2 5 8
FIGURE 58: NO. 3 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W498 - REMOVAL OR
STOWAGE .......................................... 2 6 2
FIGURE 59: RIGHT WING REAR SPAR CONVOLUTED LINERS, WIRE BUNDLE W494, AND WIRE BUNDLE
W498 - INSTALLATION ................................... 2 6 6
FIGURE 60: RIGHT WING REAR SPAR FUEL BOOST PUMP WIRE BUNDLE W494 AND WIRE BUNDLE
W498 - ROUTING ....................................... 2 7 3
FIGURE 61: RIGHT WING - NO. 2 TANK RIGHT FORWARD FUEL BOOST PUMP - INSTALLATION . 279
FIGURE 62: NO. 2 TANK RIGHT FORWARD FUEL BOOST PUMP WIRE BUNDLE W494 - WIRING CHANGE
................................................. 2 8 3
FIGURE 63: RIGHT WING - NO. 3 TANK FORWARD FUEL BOOST PUMP - INSTALLATION .... 2 8 8
FIGURE 64: NO. 3 TANK FORWARD FUEL BOOST PUMP WIRE BUNDLE W498 - WIRING CHANGE . 292
FIGURE 65: STATION 740 BULKHEAD STIFFENER GROUND STUD ASSEMBLY - WIRE BUNDLE W494
AND WIRE BUNDLE W498 ................................. 2 9 7
APPENDIX A: SHIELDED WIRE INSTALLATION - GENERAL SCOPE OF WORK ........... 3 0 0
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Commercial 
Airplanes
727
Service Bulletin
ALERT
SummaryNumber: 727-28A0133Original Issue: October 05, 2011
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Wing and Center Tank Fuel Boost Pump Wire
Bundle Replacement and Convoluted Liner Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
This service bulletin installs new fuel boost pump wire bundles in the wing and center fuel tanks. New shielded
wire bundles in convoluted liners are installed in the fuel tank conduits with wire shield grounding at the fuel
boost pump housing and pressure seal. Boeing has issued this service bulletin so that the wiring and sleeve no
longer need to be removed and inspected every 15,000 hours in accordance with Boeing Service Bulletin
727-28A0132 and the subject of Federal Aviation Administration (FAA) Airworthiness Directive AD 2007-11-08.
Boeing Service Bulletin 727-28A0132 was issued because damage was found during the repetitive inspection
in accordance with Boeing Service Bulletin 737-28A1120 and mandated by Federal Aviation Administration
(FAA) Airworthiness Directive AD 99-21-15. The damage was found to the sleeve, jacket, and insulation on the
electrical wire. The sleeve was worn through at three locations. At two of the locations the damage was also
through the jacket of the electrical wire and exposed the insulation on the electrical wire inside the jacket. The
wear did not expose the conductor of the electrical wire. The damage was found approximately 21,000 hours
after installation of the sleeve. The 21,000 hours is less than the 30,000 repeat inspection interval hours specified
in Federal Aviation Administration (FAA) Airworthiness Directive AD 99-21-15.
Boeing has issued this service bulletin as a final solution to this condition and to replace Boeing Service Bulletin
727-28A0132. Accomplishment of this service bulletin installs new shielded wire bundles in convoluted liners in
the wing and center fuel tank conduits. The convoluted liner will decrease the chance of wire bundle damage.
The new shielded wiring will provide a ground path for the Ground Fault Interrupter (GFI) to trip if there is shorting
in the wiring. This installation will help prevent potential ignition sources that can cause consequent fire or
explosion. The GFI is installed by Boeing Service Bulletin 727-28A0128.
This change affects Airworthiness Limitations document D6-8766-AWL. The new Airworthiness Limitations
(AWL) that follow are added: 28-AWL-20 and 28-AWL-21. These AWLs provide maintenance instructions and
replace the requirements of Airworthiness Limitation 28-AWL-14.
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Accomplishment of the work in accordance with this service bulletin gives terminating action to the repeat
inspections in accordance with service bulletin 727-28A0132.
Boeing Service Related Problem (SRP) 727-SRP-28-0113 is related to this service bulletin.
ACTION (PRR 24852-RS)
Get access to the left wing and right wing front spar and rear spar, tank No. 1 forward and aft fuel boost pumps,
tank No. 2 left forward, left aft, right forward, and right aft fuel boost pumps, tank No. 3 forward and aft fuel boost
pumps, center fuselage splice areas, and air conditioning distribution bay splice area, as necessary. Remove
or stow fuel boost pump wire bundles from between each fuel boost pump and center fuselage splice areas or
air conditioning bay splice area, as applicable. Do a test of the fuel boost pump conduits for leaks and repair or
replace the conduit if any leak is found. Install new wire bundles and convoluted liners in the tank No. 1, tank
No. 2, and tank No. 3 fuel boost pump conduits and connect wire bundles to each fuel boost pump, as applicable.
Route new wire bundles along the left wing and right wing front spar or rear spar, as applicable, to the center
fuselage splice area or air conditioning bay splice area, as applicable, and connect. Do a test of the fuel boost
pumps. Install the tank No. 1, tank No. 2, and tank No. 3 fuel boost pump access panels, as necessary.
EFFECTIVITY
727, 727-100, -100C, -200, -200F, 727C airplanes. Refer to Paragraph 1.A., Effectivity 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 60 months after the original
issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits.
Operator Supplied Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 9 (OCR)

BOEING SERVICE BULLETIN 727-28A0133
ALERT  ALERT
INSTALL NEW GROUND
BRACKETS AS APPLICABLE.
DISCONNECT ELECTRICAL CONNECTORS FROM THE
FUEL BOOST PUMPS.
REMOVE FUEL BOOST PUMPS AS NECESSARY.
NSTALL NEW WIRE BUNDLES TO FUEL BOOST PUMPS
INSTALL AND TEST FUEL BOOST PUMPS AS NECESSARY.
0000  000000000
00000
PULL WIRE BUNDLES AND TEFLON SLEEVES OUT OF
THE FUEL TANK CONDUITS.
REMOVE OR STOW WIRE BUNDLES AS APPLICABLE.
CLEAN FUEL TANK CONDUITS AND INSPECT FOR
LEAKS AS NECESSARY.
INSTALL NEW WIRE BUNDLES AND NEW CONVOLUTED
LINERS INTO FUEL TANK CONDUITS.
ROUTE WIRE BUNDLES TO SPLICE AREA AND GROUND
BRACKETS IN  FUSELAGE AND CONNECT.
1898814
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Commercial 
Airplanes
727
Service Bulletin
ALERT
Number: 727-28A0133
Original Issue: October 05, 2011
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Wing and Center Tank Fuel Boost Pump Wire
Bundle Replacement and Convoluted Liner Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-9825 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. Refer to PRR 24852-RS for data about this
change.
DESCRIPTIONCONFIGURATIONGROUP
727, 727-100, -100C, -200, -200F, 727C Airplanes.-1
Airplane Models:
727, 727-100, 727-100C, 727-200, 727-200F, 727C
GroupVariable Number
1E0001 - E0042
1E0101 - E0140
1E0201 - E0216
1E0301 - E0351
1E0401 - E0423
1E3001 - E3006
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GroupVariable Number
1E3011 - E3014
1E3021 - E3040
1E3059
1E3061 - E3077
1E3101 - E3103
1E3111 - E3118
1E3141 - E3152
1E3171 - E3177
1E3201 - E3206
1E3221 - E3224
1E3241 - E3290
1E3341 - E3350
1E3401 - E3421
1E3451 - E3452
1E3471 - E3474
1E3501 - E3513
1E3516 - E3523
1E3551 - E3553
1E3571 - E3578
1E3601 - E3604
1E3621 - E3622
1E3651 - E3655
1E3677
1E3681 - E3684
1E3701 - E3704
1E3751 - E3755
1E3781 - E3784
1E5001 - E5011
1E5031 - E5068
1E5101 - E5116
1E5141 - E5143
1E5161 - E5164
1E5201 - E5203
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GroupVariable Number
1E5221 - E5245
1E5251 - E5252
1E5271 - E5281
1E5301 - E5306
1E5351 - E5353
1E5381 - E5382
1E5401 - E5424
1E5426 - E5429
1E5433
1E5435
1E5451 - E5455
1E5481 - E5483
1E5501 - E5502
1QA001 - QA046
1QA051 - QA099
1QA101 - QA199
1QA201 - QA225
1QA301 - QA349
1QA351 - QA376
1QA378
1QA401 - QA499
1QA501 - QA537
1QA551 - QA579
1QA581 - QA585
1QA601 - QA688
1QA701 - QA753
1QA801 - QA805
1QA851 - QA899
1QA901 - QA946
1QA949
1QB001 - QB002
1QB031 - QB049
1QB051 - QB068
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GroupVariable Number
1QB101 - QB110
1QB114 - QB119
1QB121 - QB149
1QB151 - QB158
1QB201 - QB220
1QB301 - QB316
1QB351 - QB352
1QB401 - QB407
1QB451 - QB458
1QB501 - QB575
1QB601 - QB629
1QB651
1QB701 - QB705
1QB801 - QB810
1QB901 - QB904
1QD001 - QD012
1QD031 - QD046
1QD085 - QD088
1QD101 - QD105
1QD121 - QD127
1QD141 - QD149
1QD161 - QD164
1QD191 - QD192
1QD201 - QD239
1QD281 - QD284
1QD301 - QD305
1QD321 - QD330
1QD351
1QD401 - QD403
1QD407
1QD410
1QD421 - QD427
1QD441 - QD453
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GroupVariable Number
1QD471 - QD475
1QD501 - QD518
1QD551 - QD558
1QD571 - QD572
1QD581 - QD583
1QD601 - QD607
1QD621 - QD624
1QD641
1QD661 - QD663
1QD681 - QD685
1QD691 - QD692
1QD701 - QD702
1QD711 - QD717
1QD741
1QD761 - QD769
1QD781 - QD782
1QD791
1QD801 - QD804
1QD821 - QD828
1QD901 - QD910
1QD931 - QD932
1QD951 - QD954
1QD971 - QD973
1QD991 - QD992
1QE001 - QE002
1QL001 - QL008
1QL031 - QL032
1QL081
1QL501 - QL515
2. Spares Affected
None.
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B. Concurrent Requirements
The service bulletin listed below must be done before or at the same time as this service bulletin:
DescriptionService BulletinCompany
This service bulletin gives instructions
to replace the Fuel Quantity Indication
System (FQIS) wire bundles outside the
fuel tanks and pressurized areas.
Service Bulletin 727-28-0131
Original Issue
Boeing
C. Reason
This service bulletin installs new fuel boost pump wire bundles in the wing and center fuel tanks. New
shielded wire bundles in convoluted liners are installed in the fuel tank conduits with wire shield grounding
at the fuel boost pump housing and pressure seal. Boeing has issued this service bulletin so that the
wiring and sleeve no longer need to be removed and inspected every 15,000 hours in accordance with
Boeing Service Bulletin 727-28A0132 and the subject of Federal Aviation Administration (FAA)
Airworthiness Directive AD 2007-11-08.
Boeing Service Bulletin 727-28A0132 was issued because damage was found during the repetitive
inspection in accordance with Boeing Service Bulletin 737-28A1120 and mandated by Federal Aviation
Administration (FAA) Airworthiness Directive AD 99-21-15. The damage was found to the sleeve, jacket,
and insulation on the electrical wire. The sleeve was worn through at three locations. At two of the
locations the damage was also through the jacket of the electrical wire and exposed the insulation on
the electrical wire inside the jacket. The wear did not expose the conductor of the electrical wire. The
damage was found approximately 21,000 hours after installation of the sleeve. The 21,000 hours is
less than the 30,000 repeat inspection interval hours specified in Federal Aviation Administration (FAA)
Airworthiness Directive AD 99-21-15.
Boeing has issued this service bulletin as a final solution to this condition and to replace Boeing Service
Bulletin 727-28A0132. Accomplishment of this service bulletin installs new shielded wire bundles in
convoluted liners in the wing and center fuel tank conduits. The convoluted liner will decrease the
chance of wire bundle damage. The new shielded wiring will provide a ground path for the Ground
Fault Interrupter (GFI) to trip if there is shorting in the wiring. This installation will help prevent potential
ignition sources that can cause consequent fire or explosion. The GFI is installed by Boeing Service
Bulletin 727-28A0128.
This change affects Airworthiness Limitations document D6-8766-AWL. The new Airworthiness
Limitations (AWL) that follow are added: 28-AWL-20 and 28-AWL-21. These AWLs provide maintenance
instructions and replace the requirements of Airworthiness Limitation 28-AWL-14.
Accomplishment of the work in accordance with this service bulletin gives terminating action to the
repeat inspections in accordance with service bulletin 727-28A0132.
Boeing Service Related Problem (SRP) 727-SRP-28-0113 is related to this service bulletin.
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D. Description
Get access to the left wing and right wing front spar and rear spar, tank No. 1 forward and aft fuel boost
pumps, tank No. 2 left forward, left aft, right forward, and right aft fuel boost pumps, tank No. 3 forward
and aft fuel boost pumps, center fuselage splice areas, and air conditioning distribution bay splice area,
as necessary. Remove or stow fuel boost pump wire bundles from between each fuel boost pump and
center fuselage splice areas or air conditioning bay splice area, as applicable. Do a test of the fuel
boost pump conduits for leaks and repair or replace the conduit if any leak is found. Install new wire
bundles and convoluted liners in the tank No. 1, tank No. 2, and tank No. 3 fuel boost pump conduits
and connect wire bundles to each fuel boost pump, as applicable. Route new wire bundles along the
left wing and right wing front spar or rear spar, as applicable, to the center fuselage splice area or air
conditioning bay splice area, as applicable, and connect. Do a test of the fuel boost pumps. Install the
tank No. 1, tank No. 2, and tank No. 3 fuel boost pump access panels, as necessary.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
1-13, 1-14, 1-32, 1-33, 1-34, 1-35, 1-36, 1-74, 5-
63, 5-72, 5-73, 5-84, 6-64, 6-75, 6-76, 6-85
727, 727-100, 727-100C, 727-
200, 727-200F, 727C
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 60 months 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.
In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the accomplishment
of the modification defined in this service bulletin as an alternative method of compliance with the
inspection, engine fuel suction feed operational test, and applicable corrective actions in accordance
with service bulletin 727-28A0132, Original Release, dated February 22, 2007, as required by paragraph
(l) of AD 2007-11-08. The accomplishment of the modification defined in this service bulletin terminates
the repeat inspection and engine fuel suction feed operational test required by paragraph (l) of AD
2007-11-08. All provisions of AD 2007-11-08 that are not specifically referenced above remain fully
applicable and must be complied with accordingly.
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G. Manpower
The table below shows an estimate of the task hours necessary to do this service bulletin for each
airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with
operator task hour data if necessary. The estimate does not include lost time. These are some examples
of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed
Hours
Task HoursNumber of
Persons
Task
3.7515.004Open Access
1.251.251FIGURE 1
1.251.251FIGURE 2
1.251.251FIGURE 3
1.251.251FIGURE 4
3.006.002FIGURE 5
0.750.751FIGURE 6
0.300.301FIGURE 7
0.300.301FIGURE 8
0.750.751FIGURE 9
0.300.301FIGURE 10
0.300.301FIGURE 11
2.002.001FIGURE 12
2.002.001FIGURE 13
2.002.001FIGURE 14
2.002.001FIGURE 15
---FIGURE 16 (Wire routing only)
2.204.402FIGURE 17 Option 1:
Remove wire bundle W488
0.600.601FIGURE 17 Option 2:
Cap and stow wire bundle W488
1.953.902FIGURE 18 Option 1:
Remove wire bundle W492
0.600.601FIGURE 18 Option 2:
Cap and stow wire bundle W492
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Elapsed
Hours
Task HoursNumber of
Persons
Task
1.753.502FIGURE 19
2.002.001FIGURE 20
1.751.751FIGURE 21
4.258.502FIGURE 22
1.751.751FIGURE 23
4.008.002FIGURE 24
0.250.251FIGURE 25
---FIGURE 26 (Wire routing only)
2.655.302FIGURE 27 Option 1:
Remove wire bundle W486
0.600.601FIGURE 27 Option 2:
Cap and stow wire bundle W486
2.404.802FIGURE 28 Option 1:
Remove wire bundle W490
0.600.601FIGURE 28 Option 2:
Cap and stow wire bundle W490
1.753.502FIGURE 29
2.002.001FIGURE 30
1.751.751FIGURE 31
5.1510.302FIGURE 32
1.751.751FIGURE 33
4.959.902FIGURE 34
0.250.251FIGURE 35
0.750.751FIGURE 36
0.300.301FIGURE 37
0.300.301FIGURE 38
0.750.751FIGURE 39
0.300.301FIGURE 40
0.300.301FIGURE 41
2.002.001FIGURE 42
2.002.001FIGURE 43
2.002.001FIGURE 44
2.002.001FIGURE 45
---FIGURE 46 (Wire routing only)
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Elapsed
Hours
Task HoursNumber of
Persons
Task
2.204.402FIGURE 47 Option 1:
Remove wire bundle W496
0.600.601FIGURE 47 Option 2:
Cap and stow wire bundle W496
1.953.902FIGURE 48 Option 1:
Remove wire bundle W500
0.600.601FIGURE 48 Option 2:
Cap and stow wire bundle W500
1.753.502FIGURE 49
2.002.001FIGURE 50
1.751.751FIGURE 51
4.258.502FIGURE 52
1.751.751FIGURE 53
4.008.002FIGURE 54
0.250.251FIGURE 55
---FIGURE 56 (Wire routing only)
2.655.302FIGURE 57 Option 1:
Remove wire bundle W494
0.600.601FIGURE 57 Option 2:
Cap and stow wire bundle W494
2.404.802FIGURE 58 Option 1:
Remove wire bundle W498
0.600.601FIGURE 58 Option 2:
Cap and stow wire bundle W498
1.753.502FIGURE 59
2.002.001FIGURE 60
1.751.751FIGURE 61
5.1510.302FIGURE 62
1.751.751FIGURE 63
4.959.902FIGURE 64
0.250.251FIGURE 65
3.7515.004Close Access
2.002.001Test
(a)(a)TOTAL FOR EACH AIRPLANE
(a) The total Task Hours and Elapsed Hours are not given as the work done on each
airplane is variable.
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H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 3,000.0+ 4.0727, 727-100, -100C, -200, -200F, 727C
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data
a. Engineering Change Memo PRR 24852-RS.
b. Boeing Service Bulletin 727-28A0128, 727-28A0132, 737-28A1120.
c. Boeing Service Related Problem (SRP) 727-SRP-28-0113.
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2007-11-08, 99-21-15.
e. Standard Overhaul Practices Manual (SOPM) 20-11-03, 20-41-02, 20-43-03, 20-50-00,
20-50-02, 20-50-05, 20-50-19.
f. Standard Wiring Practices Manual (SWPM) 20-00-10, 20-00-11, 20-10-11, 20-10-11, 20-10-12,
20-10-12, 20-10-15, 20-10-19, 20-10-20, 20-20-00, 20-20-10, 20-30-11, 20-30-12, 20-30-16,
20-30-16, 20-30-22, 20-60-07, 20-60-08, 20-60-09, 20-61-11.
g. 727 Aircraft Maintenance Manual (AMM) 12-11-02, 12-30-02, 12-30-03, 25-52-02, 27-81-00,
28-10-00, 28-11-21, 28-22-21, 28-23-00, 28-42-00, 52-31-00, 52-35-00, 57-30-11.
h. 727 Structural Repair Manual (SRM) 51-30-02.
i. 727 Wiring Diagram Manual (WDM) 28-23-01.
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
FRAME INSTALLATION BODY STATION 72065-15939
BULKHEAD INSTL - BODY STATION 74065-15940
WIRE BUNDLE INSTL SECT 20 LH LEADING EDGE AND FRONT SPAR BBL 70.5
- FSS 774.9
65-23101
WIRE BUNDLE INSTL SECT 20 RH LEADING EDGE AND FRONT SPAR BBL 705
- FSS 774.9
65-23102
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TitleDrawing Number
WIRE BUNDLE INSTL SECT 20 LH INBD INSPAR - WSTA 70.5 - 41065-23103
WIRE BUNDLE INSTL SECT 20 RH INBD INSPAR - WSTA 70.5 - 41065-23104
WIRE BUNDLE INSTL SECT 20 LH FILLET AREA WSTA 166.95 - 356.0565-23109
WIRE BUNDLE INSTL SECT 20 RH FILLET AREA WSTA 166.95 - 356.0565-23110
WIRE BUNDLE INSTL KEEL BEAM AND LWR STUB AREA SECT.46 - STA 740 -
870
65-23150
WIRE BUNDLE INSTL SECT 46 LH WHEEL WELL AND AFT BODY FAIRING STA
870 - 1010
65-23151
WIRE BUNDLE INSTL SECT 46 RH WHEEL WELL AND STA 870 - 95065-23152
WIRE BUNDLE INSTL SECT 46 BODY FAIRING FWD - STA 600 - 74065-23157
WIRE BUNDLE INSTL LWR LH SIDE SECT 53 - STA 720 -74065-23196
WIRE BUNDLE INSTL SECT 43 LWR RH SIDE CARGO AREA STA 720 -74065-23197
FRAME INSTL. FWD EMERGENCY EXIT65-63130
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
Section DD6-8766-AWL, 727-100/200 Airworthiness
Limitations
28-22727 Aircraft Maintenance Manual
28-23727 Wiring Diagram Manual
28-40, 28-41727 Illustrated Parts Catalog
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 affects FCS but no new DTIs are necessary.
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. 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
original issue date of
this Service Bulletin
(US Dollars)
ROLT as of the original
issue date of this Service
Bulletin (Calendar Days)
QTYDateNameKit Number
$28,771.002801Nov 30, 2010TOP KIT,
WIRE INSTL -
FUEL BOOST
PUMP
WIRING
CHANGE
65C38807-1
$28,771.002804Dec 23, 2010
$28,771.002805Jan 10, 2011
$28,771.002805Jan 17, 2011
$28,771.002805Jan 24, 2011
The parts that follow are only necessary for the replacement of the existing fuel tank conduit(s), as
applicable.
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
original issue date of
this Service Bulletin
(US Dollars)
ROLT as of the original
issue date of this Service
Bulletin (Calendar Days)
NamePart Number
$494.00-TUBE ASSY.65-16701-63
$489.00-TUBE ASSY.65-16701-64
$489.00-TUBE ASSY.65-16701-65
$539.00-TUBE ASSY.65-16701-66
$539.00-TUBE ASSY.65-16701-67
$583.00-TUBE ASSY.65-16701-68
$534.00-TUBE ASSY.65-16701-69
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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
original issue date of
this Service Bulletin
(US Dollars)
ROLT as of the original
issue date of this Service
Bulletin (Calendar Days)
NamePart Number
$541.00-TUBE ASSY.65-16701-77
$629.00-TUBE ASSY.65-16701-79
$579.00-TUBE ASSY.65-16701-80
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 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.
Kit 65C38807
NotesExisting Part
Number
NameQTYNew Part Number
-1
TOP KIT, WIRE INSTL - FUEL BOOST PUMP WIRING
CHANGE
-65C38807-1
WIRE KIT - FINAL BOOST PUMP WIRING161-12915-1
WIRE KIT - FINAL BOOST PUMP WIRING161-12915-2
KIT INSTL - GROUNDING BRACKET, BOOST PUMP165C38808-1
KIT-INSTL, CONDUIT TERMINAL SHIELD165C38811-2
Kit 65C38808
NotesExisting Part
Number
NameQTYNew Part Number
-1
KIT INSTL - GROUNDING BRACKET, BOOST PUMP-65C38808-1
INSTALLATION ADAPTER FOR LINER ASSEMBLY121A00355-1
CONVOLUTED LINER823A03595-2
KIT - ELECTRICAL BRACKET, NITROGEN GENERA-
TION SYSTEM
465C38706-2
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Kit 65C38808
NotesExisting Part
Number
NameQTYNew Part Number
-1
TAPE, ID165C38808-10
TAPE, ID165C38808-11
TAPE, ID165C38808-12
TAPE, ID165C38808-13
TAPE, LACING165C38808-14
TAPE165C38808-15
TAPE, ID165C38808-2
TAPE, ID165C38808-3
TAPE, ID165C38808-4
TAPE, ID165C38808-5
TAPE, ID165C38808-6
TAPE, ID165C38808-7
TAPE, ID165C38808-8
TAPE, ID165C38808-9
(a)CLAMP, WIRE BUNDLE12BACC10GU103
(a)CLAMP, WIRE BUNDLE4BACC10GU106
(BACC10GU107,
BACC10GU108 op-
tional)
(a)CLAMP, WIRE BUNDLE4BACC10GU107
(a)CLAMP, WIRE BUNDLE4BACC10GU108
NUT4BACN10YR3CD
(b)RIVET, UNIVERSAL HD9BACR15BB6D4C
(b)RIVET, UNIVERSAL HD3BACR15BB6D6C
(b)BOLT32BACS12HN3-10
(b)BOLT4BACS12HN3-7
SPACER8BACS18AY3
SPACER8BACS18AY6
SEAL32BACS45A13
WASHER12NAS1149D0316H
(a) There are more parts than are necessary.
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Kit 65C38808
NotesExisting Part
Number
NameQTYNew Part Number
-1
(b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
Kit 65C38811
NotesExisting Part
Number
NameQTYNew Part Number
-2
KIT-INSTL, CONDUIT TERMINAL SHIELD-65C38811-2
(a)BOLT-SHOULDER86-84527-1
(a)BOLT8BACB30LM4-10
WASHER, FLAT16NAS1149D0416H
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-1
WIRE KIT - FINAL BOOST PUMP WIRING-61-12915-1
ASSY - W486161-12915-141
ASSY - W488161-12915-142
ASSY - W490161-12915-143
ASSY - W492161-12915-144
ASSY - W494161-12915-145
ASSY - W496161-12915-146
ASSY - W498161-12915-147
ASSY - W500161-12915-148
LACING TAPE - WHITE161-12915-2001
THERMOFIT SLEEVE, TFE-2X, SIZE 8161-12915-2002
THERMOFIT SLEEVE, TFE-2X, SIZE 6161-12915-2003
THERMOFIT SLEEVE, YELLOW, 0.093 IN I.D.161-12915-2004
THERMOFIT SLEEVE, YELLOW, 0.375 IN I.D.161-12915-2005
THERMOFIT SLEEVE, YELLOW, 0.500 IN I.D.161-12915-2006
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Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-2
WIRE KIT - FINAL BOOST PUMP WIRING-61-12915-2
ASSY - W486 SUPPLEMENTAL161-12915-125
ASSY - W488 SUPPLEMENTAL161-12915-126
ASSY - W490 SUPPLEMENTAL161-12915-127
ASSY - W492 SUPPLEMENTAL161-12915-128
ASSY - W494 SUPPLEMENTAL161-12915-129
ASSY - W496 SUPPLEMENTAL161-12915-130
ASSY - W498 SUPPLEMENTAL161-12915-131
ASSY - W500 SUPPLEMENTAL161-12915-132
LACING TAPE - WHITE161-12915-2007
THERMOFIT SLEEVE, TFE-2X, SIZE 8161-12915-2008
THERMOFIT SLEEVE, TFE-2X, SIZE 6161-12915-2009
THERMOFIT SLEEVE - TFE-4X - 0.25 IN. I.D.161-12915-2010
THERMOFIT SLEEVE - TFE-4X - 0.375 IN. I.D.161-12915-2011
THERMOFIT SLEEVE, YELLOW, 0.375 IN I.D.161-12915-2012
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-128-127-126-125
ASSY - W486 SUPPLEMENTAL...-61-12915-125
ASSY - W488 SUPPLEMENTAL..-.61-12915-126
ASSY - W490 SUPPLEMENTAL.-..61-12915-127
ASSY - W492 SUPPLEMENTAL-...61-12915-128
(a)TERMINAL2222322320
SPLICE I.D. SLEEVE - SM9..1161-12915-12501
WIRE LIST...161-12915-125W
WIRE LIST..1.61-12915-126W
SPLICE I.D. SLEEVE - SM1011..61-12915-12701
WIRE LIST.1..61-12915-127W
WIRE LIST1...61-12915-128W
(a)TERMINAL, LUG2222BACT12AC8
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Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-128-127-126-125
(a)SPLICE2222D-436-37
(a) There are more parts than are necessary.
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-132-131-130-129
ASSY - W494 SUPPLEMENTAL...-61-12915-129
ASSY - W496 SUPPLEMENTAL..-.61-12915-130
ASSY - W498 SUPPLEMENTAL.-..61-12915-131
ASSY - W500 SUPPLEMENTAL-...61-12915-132
(a)TERMINAL2222322320
SPLICE I.D. SLEEVE - SM9..1161-12915-12501
SPLICE I.D. SLEEVE - SM1011..61-12915-12701
WIRE LIST...161-12915-129W
WIRE LIST..1.61-12915-130W
WIRE LIST.1..61-12915-131W
WIRE LIST1...61-12915-132W
(a)TERMINAL, LUG2222BACT12AC8
(a)SPLICE2222D-436-37
(a) There are more parts than are necessary.
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-144-143-142-141
ASSY - W486...-61-12915-141
ASSY - W488..-.61-12915-142
ASSY - W490.-..61-12915-143
ASSY - W492-...61-12915-144
(a)TERMINAL2222322320
WIRE I.D. SLEEVE - W0486-
405R,6B,7Y,8G-18
...161-12915-10101
SPLICE I.D. SLEEVE - SM1..1161-12915-10102
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Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-144-143-142-141
SPLICE I.D. SLEEVE - SM2..1161-12915-10103
SPLICE I.D. SLEEVE - SM3..1161-12915-10104
SPLICE I.D. SLEEVE - SM4..1161-12915-10105
WIRE I.D. SLEEVE - W0488-
405R,6B,7Y,8G-18
..1.61-12915-10201
WIRE I.D. SLEEVE - W0490-
405R,6B,7Y,8G-18
.1..61-12915-10301
SPLICE I.D. SLEEVE - SM511..61-12915-10302
SPLICE I.D. SLEEVE - SM611..61-12915-10303
SPLICE I.D. SLEEVE - SM711..61-12915-10304
SPLICE I.D. SLEEVE - SM811..61-12915-10305
WIRE I.D. SLEEVE - W0492-
405R,6B,7Y,8G-18
1...61-12915-10401
ASSY - W486, PARTIAL PRE-FAB...161-12915-141A
WIRE LIST...161-12915-141W
ASSY - W488, PARTIAL PRE-FAB..1.61-12915-142A
WIRE LIST..1.61-12915-142W
ASSY - W490, PARTIAL PRE-FAB.1..61-12915-143A
WIRE LIST.1..61-12915-143W
ASSY - W492, PARTIAL PRE-FAB1...61-12915-144A
WIRE LIST1...61-12915-144W
(a)CONTACT, SOCKET, SIZE 165555BACC47CP2S
(a)SLEEVE2222BACS13S165B
(a)SLEEVE2222BACS13S175B
(a)SLEEVE2222BACS13S187B
(a)SLEEVE2222BACS13S232C
(a)SLEEVE2222BACS13S261C
(a)SLEEVE2222BACS13S275C
(a)SLEEVE2222BACS13S287C
(a)TERMINAL, LUG2222BACT12AC3
(a)SLEEVE, HEAT SHRINK10101010BACT63D1
(a)SLEEVE, HEAT SHRINK10101010BACT63D2
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Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-144-143-142-141
(a)SPLICE5555D-436-37
(a) There are more parts than are necessary.
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-148-147-146-145
ASSY - W494...-61-12915-145
ASSY - W496..-.61-12915-146
ASSY - W498.-..61-12915-147
ASSY - W500-...61-12915-148
(a)TERMINAL2222322320
SPLICE I.D. SLEEVE - SM1..1161-12915-10102
SPLICE I.D. SLEEVE - SM2..1161-12915-10103
SPLICE I.D. SLEEVE - SM3..1161-12915-10104
SPLICE I.D. SLEEVE - SM4..1161-12915-10105
SPLICE I.D. SLEEVE - SM511..61-12915-10302
SPLICE I.D. SLEEVE - SM611..61-12915-10303
SPLICE I.D. SLEEVE - SM711..61-12915-10304
SPLICE I.D. SLEEVE - SM811..61-12915-10305
WIRE I.D. SLEEVE - W0494-
405R,6B,7Y,8G-18
...161-12915-10501
WIRE I.D. SLEEVE - W0496-
405R,6B,7Y,8G-18
..1.61-12915-10601
WIRE I.D. SLEEVE - W0498-
405R,6B,7Y,8G-18
.1..61-12915-10701
WIRE I.D. SLEEVE - W0500-
405R,6B,7Y,8G-18
1...61-12915-10801
ASSY - W494, PARTIAL PRE-FAB...161-12915-145A
WIRE LIST...161-12915-145W
ASSY - W496, PARTIAL PRE-FAB..1.61-12915-146A
WIRE LIST..1.61-12915-146W
ASSY - W498, PARTIAL PRE-FAB.1..61-12915-147A
WIRE LIST.1..61-12915-147W
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Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-148-147-146-145
ASSY - W500, PARTIAL PRE-FAB1...61-12915-148A
WIRE LIST1...61-12915-148W
(a)CONTACT, SOCKET, SIZE 165555BACC47CP2S
(a)SLEEVE2222BACS13S165B
(a)SLEEVE2222BACS13S175B
(a)SLEEVE2222BACS13S187B
(a)SLEEVE2222BACS13S232C
(a)SLEEVE2222BACS13S261C
(a)SLEEVE2222BACS13S275C
(a)SLEEVE2222BACS13S287C
(a)TERMINAL, LUG2222BACT12AC3
(a)SLEEVE, HEAT SHRINK10101010BACT63D1
(a)SLEEVE, HEAT SHRINK10101010BACT63D2
(a)SPLICE5555D-436-37
(a) There are more parts than are necessary.
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-128W-127W-126W-125W
WIRE LIST...-61-12915-125W
Wire, identified as W486-004-
18, Length 18 inches
...1-
WIRE LIST..-.61-12915-126W
Wire, identified as W488-004-
18, Length 18 inches
..1.-
WIRE LIST.-..61-12915-127W
Wire, identified as W490-004-
18, Length 18 inches
.1..-
WIRE LIST-...61-12915-128W
Wire, identified as W492-004-
18, Length 18 inches
1...-
Wire1111BMS13-
60T10C01G018
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Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-132W-131W-130W-129W
WIRE LIST...-61-12915-129W
Wire, identified as W494-004-
18, Length 18 inches
...1-
WIRE LIST..-.61-12915-130W
Wire, identified as W496-004-
18, Length 18 inches
..1.-
WIRE LIST.-..61-12915-131W
Wire, identified as W498-004-
18, Length 18 inches
.1..-
WIRE LIST-...61-12915-132W
Wire, identified as W500-004-
18, Length 18 inches
1...-
Wire1111BMS13-
60T10C01G018
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-144W-143W-142W-141W
WIRE LIST...-61-12915-141W
(a)Wire, identified as W486-002-
20, Length 18 inches
...1-
(b)Wire, identified as W486-102-
18, Length 240 inches
...1-
WIRE LIST..-.61-12915-142W
(a)Wire, identified as W488-002-
20, Length 18 inches
..1.-
(b)Wire, identified as W488-102-
18, Length 120 inches
..1.-
WIRE LIST.-..61-12915-143W
(a)Wire, identified as W490-003-
20, Length 18 inches
.1..-
(b)Wire, identified as W490-103-
18, Length 240 inches
.1..-
WIRE LIST-...61-12915-144W
(a)Wire, identified as W492-003-
20, Length 18 inches
1...-
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### Page 33

Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-144W-143W-142W-141W
(b)Wire, identified as W492-103-
18, Length 120 inches
1...-
WIRE1111BMS13-
48T10C01G018
WIRE1111BMS13-
48T10C01G020
(a) Make from BMS 13-48, Type 10, Class 1, AWG 20.
(b) Make from BMS 13-48, Type 10, Class 1, AWG 18.
Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-148W-147W-146W-145W
WIRE LIST...-61-12915-145W
(a)Wire, identified as W494-002-
20, Length 18 inches
...1-
(b)Wire, identified as W494-102-
18, Length 240 inches
...1-
WIRE LIST..-.61-12915-146W
(a)Wire, identified as W496-002-
20, Length 18 inches
..1.-
(b)Wire, identified as W496-102-
18, Length 120 inches
..1.-
WIRE LIST.-..61-12915-147W
(a)Wire, identified as W498-003-
20, Length 18 inches
.1..-
(b)Wire, identified as W498-103-
18, Length 240 inches
.1..-
WIRE LIST-...61-12915-148W
(a)Wire, identified as W500-003-
20, Length 18 inches
1...-
(b)Wire, identified as W500-103-
18, Length 120 inches
1...-
WIRE1111BMS13-
48T10C01G018
WIRE1111BMS13-
48T10C01G020
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### Page 34

Kit 61-12915
NotesExisting Part
Number
NameQTYNew Part Number
-148W-147W-146W-145W
(a) Make from BMS 13-48, Type 10, Class 1, AWG 20.
(b) Make from BMS 13-48, Type 10, Class 1, AWG 18.
The parts that follow are only necessary for the replacement of the existing fuel tank conduit(s), as ap-
plicable.
Kit 65-16701
NotesExisting Part
Number
NameQTYNew Part Number
-67-66-65-64-63
(a)TUBE ASSY....-65-16701-63
(a)TUBE ASSY...-.65-16701-64
(a)TUBE ASSY..-..65-16701-65
(a)TUBE ASSY.-...65-16701-66
(a)TUBE ASSY-....65-16701-67
COUPLING, NUT222.2BACN10CS08D
COUPLING, NUT...2.BACN10CS8D
SLEEVE, FLARELESS22222BACS13AP8
ALUMINUM ALLOY TUBING;
SEE RM PL FOR COMPLETE
DESCRIPTION
11111MR674X
(a) Discard the existing part.
The parts that follow are only necessary for the replacement of the existing fuel tank conduit(s), as ap-
plicable.
Kit 65-16701
NotesExisting Part
Number
NameQTYNew Part Number
-80-79-77-69-68
(a)TUBE ASSY....-65-16701-68
(a)TUBE ASSY...-.65-16701-69
(a)TUBE ASSY..-..65-16701-77
(a)TUBE ASSY.-...65-16701-79
(a)TUBE ASSY-....65-16701-80
COUPLING, NUT22222BACN10CS08D
SLEEVE, FLARELESS22222BACS13AP8
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### Page 35

The parts that follow are only necessary for the replacement of the existing fuel tank conduit(s), as ap-
plicable.
Kit 65-16701
NotesExisting Part
Number
NameQTYNew Part Number
-80-79-77-69-68
ALUMINUM ALLOY TUBING;
SEE RM PL FOR COMPLETE
DESCRIPTION
11111MR674X
(a) Discard the existing part.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number / Specification
(a)CHEMICAL CONVERSION COATING12 OuncesALODINE 600
(a)SEALANT24 OuncesBMS5-26
(a)SEALANT24 OuncesBMS5-37
(a)SEALANT24 OuncesBMS5-95
(a)PRIMER24 OuncesBMS10-11, TYPE 1
(a) (b)BEARING GREASE, LIGHT OR MEDI-
UM
24 OuncesDOW CORNING MOLYCOTE
33
(a)THREAD LOCKING COMPOUND12 OuncesLOCTITE 222
(a)LOCKWIRE10 FeetMS20995NC20
(a)ADHESIVE TAPE, WIDTH 0.5 IN1 RollSCOTCH 63
Used as mold for vapor
and pressure seal.
PAPER TAPE1 Roll-
Length 120 inches.PULL WIRE, #16 OR #18 GAGE8-
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(b) As an approved alternative use Cetyl Alcohol (Boelube).
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
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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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### Page 37

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 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.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. 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.
7. 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.
8. Only use approved test equipment. The test equipment used must be approved for
use in areas subject to combustion, fire, and explosion as defined in UL Standard
913 for a Class I, Group A, atmosphere. Below are two electrical bonding meters
that are approved.
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– Manufacturer - Avtron Manufacturing Incorporated, Model - T477W Bonding
Meter.
– Manufacturer - BCD Electronics Limited, Model - M1 Bonding Meter, Serial
Number A0000112 (and any subsequent serial numbers).
9. Refer to Appendix A for a general schematic overview of the scope of work for a
Shielded Wire Installation for a typical fuel boost pump.
10. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
11. 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.
12. 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.
The removed part can be discarded if a new or serviceable part is installed.
13. 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.
B. WORK INSTRUCTIONS
1. Set the switches for the fuel boost pumps on the third crewman's lower instrument panel to the
OFF position.
2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags:
NUMBERNAMEPANEL / LOCATION
C801FUEL PUMP 1 FWDP6-2
C802FUEL PUMP 1 AFTP6-2
C803FUEL PUMP 2 L FWDP6-2
C804FUEL PUMP 2 L AFTP6-2
C805FUEL PUMP 2 R FWDP6-2
C806FUEL PUMP 2 R AFTP6-2
C807FUEL PUMP 3 FWDP6-2
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NUMBERNAMEPANEL / LOCATION
C808FUEL PUMP 3 AFTP6-2
WARNING: PRESSURIZING HYDRAULIC SYSTEMS FOR OPERATION OF THE LEADING EDGE
FLAPS AND SLATS ALSO PERMITS OPERATION OF THE TRAILING EDGE FLAPS
AND GROUND SPOILERS SIMPLY BY MOVING THE RESPECTIVE CONTROLS.
OTHER FLIGHT CONTROL SYSTEMS MAY BE ISOLATED BY SHUTOFF VALVES.
ISOLATE OR TAG ALL FLIGHT CONTROL SYSTEMS NOT BEING TESTED AND
ENSURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF CONTROL
SURFACES BEFORE APPLYING HYDRAULIC POWER.
WARNING: INSTALL LEADING EDGE FLAP AND SLAT LOCKS TO PREVENT INADVERTENT
OPERATION OF LEADING EDGE FLAPS AND SLATS. FLAPS AND SLATS ARE FAST
ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
3. Extend the leading edge slats and install locks. Refer to 727 AMM 27-81-00 as an accepted
procedure.
4. Remove the left wing-to-body fairings 3342 and 3343 and right wing-to-body fairings 3442 and
3443. Refer to 727 AMM 12-30-02 for panel locations.
5. Remove the left overwing fairings 3516 and 3517 and right overwing fairings 3616 and 3617. Refer
to 727 AMM 12-30-03 for panel locations.
6. Get access to the following areas for wire bundle routing to the air conditioning distribution bay:
a. Left and right main wheel well.
b. Keel beam station 740 to 870.
c. Lower left stub area and lower right stub area.
d. Left hand forward body fairing area at station 740.
7. Remove the panels that follow for access to the No.1 Tank fuel boost pumps. Refer to 727 AMM
57-30-11 as an accepted procedure.
a. Panel 7201 (Tank No. 1, forward fuel boost pump).
b. Panel 7203 (Tank No. 1, aft fuel boost pump).
8. Remove the panels that follow for access to the No. 2 Tank fuel boost pumps. Refer to 727 AMM
57-30-11 as an accepted procedure.
a. Panel 7301 (Tank No. 2, left forward fuel boost pump).
b. Panel 7302 (Tank No. 2, left aft fuel boost pump).
c. Panel 7501 (Tank No. 2, right forward fuel boost pump).
d. Panel 7502 (Tank No. 2, right aft fuel boost pump).
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9. Remove the panels that follow for access to the No. 3 Tank fuel boost pumps. Refer to 727 AMM
57-30-11 as an accepted procedure.
a. Panel 7601 (Tank No. 3, forward fuel boost pump).
b. Panel 7603 (Tank No. 3, aft fuel boost pump).
10. Open the forward cargo door to get access to the forward cargo compartment. Refer to 727 AMM
52-31-00 or 727 AMM 52-35-00, as applicable, as an accepted procedure.
11. Get access to the air conditioning distribution bay by removing the center panel of the forward
cargo compartment aft bulkhead at station 680.
12. In the air conditioning distribution bay between station 720D and station 740, remove and keep
the left sidewall lining and right sidewall lining, as required. Refer to727 AMM 25-52-02 as an
accepted procedure.
13. In the air conditioning distribution bay between station 720D and station 740, remove and keep
the ceiling lining, as required. Refer to 727 AMM 25-52-02 as an accepted procedure.
14. Install a new ground bracket at station 720F on the left side of the air conditioning distribution bay
in accordance with FIGURE 1.
15. Install a new ground bracket at station 720F on the left side of the air conditioning distribution bay
in accordance with FIGURE 2.
16. Install a new ground bracket at station 720F on the right side of the air conditioning distribution
bay in accordance with FIGURE 3.
17. Install a new ground bracket on the station 740 bulkhead at the aft end of the air conditioning
distribution bay in accordance with FIGURE 4.
18. Remove the fuel boost pumps that follow from the applicable fuel boost pump housing in accordance
with FIGURE 5.
a. No. 1 Tank forward fuel boost pump.
b. No. 1 Tank aft fuel boost pump.
c. No.2 Tank left forward fuel boost pump.
d. No.2 Tank left aft fuel boost pump.
e. No.2 Tank right forward fuel boost pump.
f. No.2 Tank right aft fuel boost pump.
g. No.3 Tank forward fuel boost pump.
h. No.3 Tank aft fuel boost pump.
19. Remove wire bundle W488 and sleeve, if sleeve is installed, from between the No. 1 tank aft fuel
boost pump housing and left wing front spar area in accordance with FIGURE 6 and FIGURE 7.
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20. Remove wire bundle W492 and sleeve, if sleeve is installed, from between the No. 2 tank left aft
fuel boost pump housing and left wing front spar area in accordance with FIGURE 6 and FIGURE
8.
21. Remove wire bundle W486 and sleeve, if sleeve is installed, from between the No. 1 tank forward
fuel boost pump housing and left wing rear spar area in accordance with FIGURE 9 and FIGURE
10.
22. Remove wire bundle W490 and sleeve, if sleeve is installed, from between the No. 2 tank left
forward fuel boost pump housing and left wing rear spar area in accordance with FIGURE 9 and
FIGURE 11.
23. Do one of the three tests that follow to find a leak in the left wing fuel tank conduits.
a. Test 1:
(1) Fill the applicable fuel tank with fuel to full, covering the conduit.
(2) After 5 minutes make sure there are no sign of fuel leakage at the ends of the fuel tank
conduit at the front spar or rear spar, as applicable, and in the fuel boost pump housing.
b. Test 2:
(1) Fill the applicable fuel tank with fuel to full, covering the conduit.
(2) Pull a clean cotton wiper through the fuel tank conduit with lacing tape.
(3) Make sure there is no fuel on the cotton wiper.
c. Test 3:
NOTE: You can do this test with any quantity of fuel in the tank.
(1) Use the necessary fittings to plug one end of the fuel tank conduit and to connect a
pressure gage and air supply to the other end of the fuel tank conduit.
NOTE: You must connect the pressure gage so that it reads the pressure in the fuel
tank conduit even when the air supply is shut-off.
(2) Pressurize the fuel tank conduit to 20 psi and shut-off the air supply.
(3) After 5 minutes with no supply of air make sure the pressure shown on the pressure gage
did not decrease.
d. If a leak is found, repair or replace the fuel tank conduit in accordance with Step 24.
e. If no leak is found it is not necessary to repair or replace the fuel tank conduit, go to Step 25.
24. Repair fuel tank conduit leaks.
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a. Defuel and purge the fuel tank. Refer to 727 AMM 28-10-00 and 727 AMM 28-23-00 as
accepted procedures.
b. Remove the fuel tank access panel as necessary. Refer to 727 AMM 28-11-21 as an accepted
procedure.
c. Check for leaks in the fuel tank conduit in accordance with Step 23, Test 3.
d. If the leak is at the fuel tank conduit B-nuts, tighten as necessary.
(1) Remove sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(2) Remove lockwire. Refer to SOPM 20-50-02 as an accepted procedure.
(3) Torque the B-nuts to 266 - 294 inch-pounds. Refer to SOPM 20-50-00 as an accepted
procedure.
(4) Install lockwire. Refer to SOPM 20-50-02 as an accepted procedure.
(5) Apply sealant. Refer to SOPM 20-50-19 as an accepted procedure.
e. If the leak is in the left wing No. 1 tank aft fuel tank conduit replace the conduit in accordance
with FIGURE 12.
f. If the leak is in the left wing No. 2 tank left aft fuel tank conduit replace the conduit in
accordance with FIGURE 13.
g. If the leak is in the left wing No. 1 tank forward fuel tank conduit replace the conduit in
accordance with FIGURE 14.
h. If the leak is in the left wing No. 2 tank left forward fuel tank conduit replace the conduit in
accordance with FIGURE 15.
i. Check for leaks in the applicable fuel tank conduit in accordance with Step 23, Test 3.
25. Internally clean the left wing fuel boost pump conduits as necessary. Use compressed air (20 psi
maximum) to blow out any contamination or pull a wiper through the conduits with lacing tape.
26. Remove or stow No. 1 tank aft fuel boost pump wire bundle W488 in accordance with FIGURE 16
and FIGURE 17.
27. Remove or stow No. 2 tank left aft fuel boost pump wire bundle W492 in accordance with FIGURE
16 and FIGURE 18.
28. Install new convoluted liners, new wire bundle W488, and new wire bundle W492 in the fuel tank
conduits between the applicable fuel boost pump housing and left wing front spar in accordance
with FIGURE 19.
29. Route new wire bundle W488 and new wire bundle W492 in accordance with FIGURE 20.
30. Install the No. 1 tank aft fuel boost pump in accordance with FIGURE 21 and make the changes
to wire bundle W488 in accordance with FIGURE 22.
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31. Install the No. 2 tank left aft fuel boost pump in accordance with FIGURE 23 and make the changes
to wire bundle W492 in accordance with FIGURE 24.
32. Install the upper left ground stud assembly at station 720F for wire bundle W488 and wire bundle
W492 in accordance with FIGURE 25.
33. Remove or stow No. 1 tank forward fuel boost pump wire bundle W486 in accordance with FIGURE
26 and FIGURE 27.
34. Remove or stow No. 2 tank left forward fuel boost pump wire bundle W490 in accordance with
FIGURE 26 and FIGURE 28.
35. Install new convoluted liners, new wire bundle W486, and new wire bundle W490 in the fuel tank
conduits between the applicable fuel boost pump housing and left wing rear spar in accordance
with FIGURE 29.
36. Route new wire bundle W486 and new wire bundle W490 in accordance with FIGURE 30.
37. Install the No. 1 tank forward fuel boost pump in accordance with FIGURE 31 and make the
changes to wire bundle W486 in accordance with FIGURE 32.
38. Install the No. 2 tank left forward fuel boost pump in accordance with FIGURE 33 and make the
changes to wire bundle W490 in accordance with FIGURE 34.
39. Install the lower left ground stud assembly at station 720F for wire bundle W486 and wire bundle
W490 in accordance with FIGURE 35.
40. Remove wire bundle W496 and sleeve, if sleeve is installed, from between the No. 2 tank right aft
fuel boost pump housing and right wing front spar area in accordance with FIGURE 36 and FIGURE
37.
41. Remove wire bundle W500 and sleeve, if sleeve is installed, from between the No. 3 tank aft fuel
boost pump housing and right wing front spar area in accordance with FIGURE 36 and FIGURE
38.
42. Remove wire bundle W494 and sleeve, if sleeve is installed, from between the No. 2 tank right
forward fuel boost pump housing and right wing rear spar area in accordance with FIGURE 39
and FIGURE 40.
43. Remove wire bundle W498 and sleeve, if sleeve is installed, from between the No. 3 tank forward
fuel boost pump housing and right wing rear spar area in accordance with FIGURE 39 and FIGURE
41.
44. Do one of the three tests that follow to find a leak in the right wing fuel tank conduits.
a. Test 1:
(1) Fill the applicable fuel tank with fuel to full, covering the conduit.
(2) After 5 minutes make sure there are no sign of fuel leakage at the ends of the fuel tank
conduit at the front spar or rear spar, as applicable, and in the fuel boost pump housing.
b. Test 2:
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(1) Fill the applicable fuel tank with fuel to full, covering the conduit.
(2) Pull a clean cotton wiper through the fuel tank conduit with lacing tape.
(3) Make sure there is no fuel on the cotton wiper.
c. Test 3:
NOTE: You can do this test with any quantity of fuel in the tank.
(1) Use the necessary fittings to plug one end of the fuel tank conduit and to connect a
pressure gage and air supply to the other end of the fuel tank conduit.
NOTE: You must connect the pressure gage so that it reads the pressure in the fuel
tank conduit even when the air supply is shut-off.
(2) Pressurize the fuel tank conduit to 20 psi and shut-off the air supply.
(3) After 5 minutes with no supply of air make sure the pressure shown on the pressure gage
did not decrease.
d. If a leak is found, repair or replace the fuel tank conduit in accordance with Step 45.
e. If no leak is found it is not necessary to repair or replace the fuel tank conduit, go to Step 46.
45. Repair fuel tank conduit leaks.
a. Defuel and purge the fuel tank. Refer to 727 AMM 28-10-00 and 727 AMM 28-23-00 as
accepted procedures.
b. Remove the fuel tank access panel as necessary. Refer to 727 AMM 28-11-21 as an accepted
procedure.
c. Check for leaks in the fuel tank conduit in accordance with Step 44, Test 3.
d. If the leak is at the fuel tank conduit B-nuts, tighten as necessary.
(1) Remove sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(2) Remove lockwire. Refer to SOPM 20-50-02 as an accepted procedure.
(3) Torque the B-nuts to 266 - 294 inch-pounds. Refer to SOPM 20-50-00 as an accepted
procedure.
(4) Install lockwire. Refer to SOPM 20-50-02 as an accepted procedure.
(5) Apply sealant. Refer to SOPM 20-50-19 as an accepted procedure.
e. If the leak is in the right wing No. 2 tank right aft fuel tank conduit replace the conduit in
accordance with FIGURE 42.
f. If the leak is in the right wing No. 3 tank aft fuel tank conduit replace the conduit in accordance
with FIGURE 43.
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g. If the leak is in the right wing No. 2 tank right forward fuel tank conduit replace the conduit in
accordance with FIGURE 44.
h. If the leak is in the right wing No. 3 tank forward fuel tank conduit replace the conduit in
accordance with FIGURE 45.
i. Check for leaks in the applicable fuel tank conduit in accordance with Step 44, Test 3.
46. Internally clean the right wing fuel boost pump conduits as necessary. Use compressed air (20
psi maximum) to blow out any contamination or pull a wiper through the conduits with lacing tape.
47. Remove or stow No. 2 tank right aft fuel boost pump wire bundle W496 in accordance with FIGURE
46 and FIGURE 47.
48. Remove or stow No. 3 tank aft fuel boost pump wire bundle W500 in accordance with FIGURE 46
and FIGURE 48.
49. Install new convoluted liners, new wire bundle W496, and new wire bundle W500 in the fuel tank
conduits between the applicable fuel boost pump housing and right wing front spar in accordance
with FIGURE 49.
50. Route new wire bundle W496 and new wire bundle W500 in accordance with FIGURE 50.
51. Install the No. 2 tank right aft fuel boost pump in accordance with FIGURE 51 and make the
changes to wire bundle W496 in accordance with FIGURE 52.
52. Install the No. 3 tank aft fuel boost pump in accordance with FIGURE 53 and make the changes
to wire bundle W500 in accordance with FIGURE 54.
53. Install the right ground stud assembly at station 720F for wire bundle W496 and wire bundle W500
in accordance with FIGURE 55.
54. Remove or stow No. 2 tank right forward fuel boost pump wire bundle W494 in accordance with
FIGURE 56 and FIGURE 57.
55. Remove or stow No. 3 tank forward fuel boost pump wire bundle W498 in accordance with FIGURE
56 and FIGURE 58.
56. Install new convoluted liners, new wire bundle W494, and new wire bundle W498 in the fuel tank
conduits between the applicable fuel boost pump housing and right wing rear spar in accordance
with FIGURE 59.
57. Route new wire bundle W494 and new wire bundle W498 in accordance with FIGURE 60.
58. Install the No. 2 tank right forward fuel boost pump in accordance with FIGURE 61 and make the
changes to wire bundle W494 in accordance with FIGURE 62.
59. Install the No. 3 tank forward fuel boost pump in accordance with FIGURE 63 and make the
changes to wire bundle W498 in accordance with FIGURE 64.
60. Install the ground stud assembly at station 740 for wire bundle W494 and wire bundle W498 in
accordance with FIGURE 65.
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61. Do the tests that follow of the fuel boost pumps to make sure there is sufficient fuel boost pump
pressure.
NOTE: If the connector installation is not correct, the pumps operate but may not give sufficient
pressure. The test steps below make sure that the operation of the pumps is correct.
a. Prepare for Test
(1) Make sure there is a minimum fuel quantity of 2,000 pounds (900 kilograms) in the No.
2 Fuel Tank (center tank) and a minimum fuel quantity of 1,700 pounds (770 kilograms)
in the No. 1 Fuel Tank (left main tank), and a minimum fuel quantity of 1,700 pounds (770
kilograms) in the No. 3 Fuel Tank (right main tank). Refer to 727 AMM 12-11-02 as an
accepted procedure. There must be a person in the flight compartment to monitor the
fuel quantities and the pump low pressure indications, so that the pumps do not run dry.
(2) Set the switches for the fuel boost pumps on the third crewman's lower instrument panel
P4 to the OFF position.
(3) Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags:
NUMBERNAMEPANEL / LOCATION
C801FUEL PUMP 1 FWDP6-2
C802FUEL PUMP 1 AFTP6-2
C803FUEL PUMP 2 L FWDP6-2
C804FUEL PUMP 2 L AFTP6-2
C805FUEL PUMP 2 R FWDP6-2
C806FUEL PUMP 2 R AFTP6-2
C807FUEL PUMP 3 FWDP6-2
C808FUEL PUMP 3 AFTP6-2
b. Operate the Center Tank Left Aft Fuel Boost pump to Transfer Fuel from Center Tank to Left
Main Tank.
(1) Record in Table 1 the initial fuel quantity reading for the center tank, (Ctr Tank Qty 1).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the center tank to the left main tank
using the left center tank aft fuel boost pump. Refer to 727 AMM 28-23-00 as an accepted
procedure.
(3) Set the No. 2 Tank L AFT FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 2 Tank L AFT FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
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(5) Record in Table 1 the final center tank fuel quantity, (Ctr Tank Qty 2).
(6) Calculate in Table 1 the amount of fuel that was transferred from the center tank to the
left main tank, the difference equal to [(Ctr Tank Qty 1) minus (Ctr Tank Qty 2)].
Table 1:
Center Tank Fuel Quantity Transferred =
Ctr Tank Qty 1 minus Ctr Tank Qty 2
Ctr Tank Qty 2
Final Fuel Quantity
Ctr Tank Qty 1
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 400 pounds (180 kilograms). If the
difference is less than 400 pounds (180 kilograms), check the wiring phase relationship
is correct at the Center Tank Left Aft Fuel Boost Pump connector D8 and fuselage splice
area in accordance with FIGURE 24.
(a) Make the necessary changes to the wiring to correct the Center Tank Left Aft Fuel
Boost Pump phase relationship.
c. Operate the No. 1 Tank Aft Fuel Boost pump to Transfer Fuel from Left Main Tank to Center
Tank.
(1) Record in Table 2 the initial fuel quantity reading for the No. 1 tank, (Left Tank Qty 1).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the left main tank to the center tank
using the No. 1 Tank Aft fuel boost pump. Refer to 727 AMM 28-23-00 as an accepted
procedure.
(3) Set the No. 1 Tank AFT FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 1 Tank AFT FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 2 the final No. 1 tank fuel quantity, (Left Tank Qty 2).
(6) Calculate in Table 2 the amount of fuel that was transferred from the left main tank to the
center tank, the difference equal to [(Left Tank Qty 1) minus (Left Tank Qty 2)].
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Table 2:
Left Tank Fuel Quantity Transferred =
Left Tank Qty 1 minus Left Tank Qty 2
Left Tank Qty 2
Final Fuel Quantity
Left Tank Qty 1
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 200 pounds (90 kilograms). If the
difference is less than 200 pounds (90 kilograms), check the wiring phase relationship is
correct at the No. 1 Tank Aft Fuel Boost Pump connector D4 and fuselage splice area in
accordance with FIGURE 22.
(a) Make the necessary changes to the wiring to correct the No. 1 Tank Aft Fuel Boost
Pump phase relationship.
d. Operate the Center Tank Left Forward Fuel Boost pump to Transfer Fuel from Center Tank
to Left Main Tank.
(1) Record in Table 3 the initial fuel quantity reading for the center tank, (Ctr Tank Qty 3).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the center tank to the left main tank
using the left center tank forward fuel boost pump. Refer to 727 AMM 28-23-00 as an
accepted procedure.
(3) Set the No. 2 Tank L FWD FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 2 Tank L FWD FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 3 the final center tank fuel quantity, (Ctr Tank Qty 4).
(6) Calculate in Table 3 the amount of fuel that was transferred from the center tank to the
left main tank, the difference equal to [(Ctr Tank Qty 3) minus (Ctr Tank Qty 4)].
Table 3:
Center Tank Fuel Quantity Transferred =
Ctr Tank Qty 3 minus Ctr Tank Qty 4
Ctr Tank Qty 4
Final Fuel Quantity
Ctr Tank Qty 3
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 400 pounds (180 kilograms). If the
difference is less than 400 pounds (180 kilograms), check the wiring phase relationship
is correct at the Center Tank Left Forward Fuel Boost Pump connector D6 and fuselage
splice area in accordance with FIGURE 34.
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(a) Make the necessary changes to the wiring to correct the Center Tank Left Forward
Fuel Boost Pump phase relationship.
e. Operate the No. 1 Tank Forward Fuel Boost pump to Transfer Fuel from Left Main Tank to
Center Tank.
(1) Record in Table 4 the initial fuel quantity reading for the No. 1 tank, (Left Tank Qty 3).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the left main tank to the center tank
using the No. 1 Tank Forward fuel boost pump. Refer to 727 AMM 28-23-00 as an
accepted procedure.
(3) Set the No. 1 Tank FWD FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 1 Tank FWD FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 4 the final No. 1 tank fuel quantity, (Left Tank Qty 4).
(6) Calculate in Table 4 the amount of fuel that was transferred from the left main tank to the
center tank, the difference equal to [(Left Tank Qty 3) minus (Left Tank Qty 4)].
Table 4:
Left Tank Fuel Quantity Transferred =
Left Tank Qty 3 minus Left Tank Qty 4
Left Tank Qty 4
Final Fuel Quantity
Left Tank Qty 3
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 200 pounds (90 kilograms). If the
difference is less than 200 pounds (90 kilograms), check the wiring phase relationship is
correct at the No. 1 Tank Forward Fuel Boost Pump connector D2 and fuselage splice
area in accordance with FIGURE 32.
(a) Make the necessary changes to the wiring to correct the No. 1 Tank Forward Fuel
Boost Pump phase relationship.
f. Operate the Center Tank Right Forward Fuel Boost pump to Transfer Fuel from Center Tank
to Right Main Tank.
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(1) Record in Table 5 the initial fuel quantity reading for the center tank, (Ctr Tank Qty 5).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the center tank to the right main
tank using the right center tank forward fuel boost pump. Refer to 727 AMM 28-23-00 as
an accepted procedure.
(3) Set the No. 2 Tank R FWD FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 2 Tank R FWD FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 5 the final center tank fuel quantity, (Ctr Tank Qty 6).
(6) Calculate in Table 5 the amount of fuel that was transferred from the center tank to the
right main tank, the difference equal to [(Ctr Tank Qty 5) minus (Ctr Tank Qty 6)].
Table 5:
Center Tank Fuel Quantity Transferred =
Ctr Tank Qty 5 minus Ctr Tank Qty 6
Ctr Tank Qty 6
Final Fuel Quantity
Ctr Tank Qty 5
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 400 pounds (180 kilograms). If the
difference is less than 400 pounds (180 kilograms), check the wiring phase relationship
is correct at the Center Tank Right Forward Fuel Boost Pump connector D10 and fuselage
splice area in accordance with FIGURE 62.
(a) Make the necessary changes to the wiring to correct the Center Tank Right Forward
Fuel Boost Pump phase relationship.
g. Operate the No. 3 Tank Forward Fuel Boost pump to Transfer Fuel from Right Main Tank to
Center Tank.
(1) Record in Table 6 the initial fuel quantity reading for the No. 3 tank, (Right Tank Qty 1).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the right main tank to the center
tank using the No. 3 Tank Forward fuel boost pump. Refer to 727 AMM 28-23-00 as an
accepted procedure.
(3) Set the No. 3 Tank FWD FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
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(4) After two minutes, set the No. 3 Tank FWD FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 6 the final No. 3 tank fuel quantity, (Right Tank Qty 2).
(6) Calculate in Table 6 the amount of fuel that was transferred from the right main tank to
the center tank, the difference equal to [(Right Tank Qty 1) minus (Right Tank Qty 2)].
Table 6:
Right Tank Fuel Quantity Transferred =
Right Tank Qty 1 minus Right Tank Qty 2
Right Tank Qty 2
Final Fuel Quantity
Right Tank Qty 1
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 200 pounds (90 kilograms). If the
difference is less than 200 pounds (90 kilograms), check the wiring phase relationship is
correct at the No. 3 Tank Forward Fuel Boost Pump connector D14 and fuselage splice
area in accordance with FIGURE 64.
(a) Make the necessary changes to the wiring to correct the No. 3 Tank Forward Fuel
Boost Pump phase relationship.
h. Operate the Center Tank Right Aft Fuel Boost pump to Transfer Fuel from Center Tank to
Right Main Tank.
(1) Record in Table 7 the initial fuel quantity reading for the center tank, (Ctr Tank Qty 7).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the center tank to the right main
tank using the right center tank aft fuel boost pump. Refer to 727 AMM 28-23-00 as an
accepted procedure.
(3) Set the No. 2 Tank R AFT FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 2 Tank R AFT FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 7 the final center tank fuel quantity, (Ctr Tank Qty 8).
(6) Calculate in Table 7 the amount of fuel that was transferred from the center tank to the
right main tank, the difference equal to [(Ctr Tank Qty 7) minus (Ctr Tank Qty 8)].
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Table 7:
Center Tank Fuel Quantity Transferred =
Ctr Tank Qty 7 minus Ctr Tank Qty 8
Ctr Tank Qty 8
Final Fuel Quantity
Ctr Tank Qty 7
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 400 pounds (180 kilograms). If the
difference is less than 400 pounds (180 kilograms), check the wiring phase relationship
is correct at the Center Tank Right Aft Fuel Boost Pump connector D12 and fuselage
splice area in accordance with FIGURE 52.
(a) Make the necessary changes to the wiring to correct the Center Tank Right Aft Fuel
Boost Pump phase relationship.
i. Operate the No. 3 Tank Aft Fuel Boost pump to Transfer Fuel from Right Main Tank to Center
Tank.
(1) Record in Table 8 the initial fuel quantity reading for the No. 3 tank, (Right Tank Qty 3).
(2) Do the set-up for Transfer Fuel from Tank to Tank for the right main tank to the center
tank using the No. 3 Tank Aft fuel boost pump. Refer to 727 AMM 28-23-00 as an accepted
procedure.
(3) Set the No. 3 Tank AFT FUEL BOOST PUMP switch on the third crewman's lower
instrument panel P4 to the ON position for a period of two minutes.
NOTE: Immediately set the fuel boost pump switch to OFF if the LOW PRESSURE light
comes on and stays on. Refer to 727 AMM 28-42-00 as an accepted procedure
to find the cause of the indication.
(4) After two minutes, set the No. 3 Tank AFT FUEL BOOST PUMP switch on the third
crewman's lower instrument panel P4 to the OFF position.
(5) Record in Table 8 the final No. 3 tank fuel quantity, (Right Tank Qty42).
(6) Calculate in Table 8 the amount of fuel that was transferred from the right main tank to
the center tank, the difference equal to [(Right Tank Qty 3) minus (Right Tank Qty 4)].
Table 8:
Right Tank Fuel Quantity Transferred =
Right Tank Qty 3 minus Right Tank Qty 4
Right Tank Qty 4
Final Fuel Quantity
Right Tank Qty 3
Initial Fuel Quantity
Total:
(7) Make sure that the difference is more than or equal to 200 pounds (90 kilograms). If the
difference is less than 200 pounds (90 kilograms), check the wiring phase relationship is
correct at the No. 3 Tank Aft Fuel Boost Pump connector D16 and fuselage splice area
in accordance with FIGURE 54.
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(a) Make the necessary changes to the wiring to correct the No. 3 Tank Aft Fuel Boost
Pump phase relationship.
62. Install the left sidewall lining and right sidewall lining in the air conditioning distribution bay between
station 720D and station 740. Refer to 727 AMM 25-52-02 as an accepted procedure.
63. Install the ceiling lining in the air conditioning distribution bay between station 720D and station
740, as required. Refer to 727 AMM 25-52-02 as an accepted procedure.
64. Close access to the air conditioning distribution bay by replacing the center panel of the forward
cargo compartment aft bulkhead at station 680 and close the forward cargo compartment.
65. Install the panels that follow for the No. 1 Tank fuel boost pumps. Refer to 727 AMM 57-30-11 as
an accepted procedure.
a. Panel 7201 (Tank No. 1, forward fuel boost pump).
b. Panel 7203 (Tank No. 1, aft fuel boost pump).
66. Install the panels that follow for the No. 2 Tank fuel boost pumps. Refer to 727 AMM 57-30-11 as
an accepted procedure.
a. Panel 7301 (Tank No. 2, left forward fuel boost pump).
b. Panel 7302 (Tank No. 2, left aft fuel boost pump).
c. Panel 7501 (Tank No. 2, right forward fuel boost pump).
d. Panel 7502 (Tank No. 2, right aft fuel boost pump).
67. Install the panels that follow for the No. 3 Tank fuel boost pumps. Refer to 727 AMM 57-30-11 as
an accepted procedure.
a. Panel 7601 (Tank No. 3, forward fuel boost pump).
b. Panel 7603 (Tank No. 3, aft fuel boost pump).
68. Close access to the areas that follow:
a. Keel beam station 740 to 870.
b. Lower left stub area and lower right stub area.
c. Left hand forward body fairing area at station 740.
69. Install the left wing-to-body fairings 3342 and 3343 and right wing-to-body fairings 3442 and 3443.
Refer to 727 AMM 12-30-02 for panel locations.
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BOEING SERVICE BULLETIN 727-28A0133
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### Page 54

70. Install the left overwing fairings 3516 and 3517 and right overwing fairings 3616 and 3617. Refer
to 727 AMM 12-30-03 for panel locations.
71. Remove the locks from the leading edge slats. Refer to 727 AMM 27-81-00 as an accepted
procedure.
72. Put the airplane back to a serviceable condition.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011
727-28A0133
54 of 300
BOEING SERVICE BULLETIN 727-28A0133
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 727-28A0133
ALERT  ALERT
STA
720F
FLOOR BEAM
AT STA 720F
FRAME AT
STA 720F
LOOKING FWD  1898817
FIGURE 1: STATION 720F UPPER LEFT GROUND BRACKET - INSTALLATION
(SHEET 1 OF 3)
Original Issue: October 05, 2011
BOEING PROPRIETARY -  727-28A0133
Copyright © Unpublished Work - See page 1 for details.  55 of 300

### Page 56

FIGURE 1: STATION 720F UPPER LEFT GROUND BRACKET - INSTALLATION
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011
727-28A0133
56 of 300
BOEING SERVICE BULLETIN 727-28A0133
ALERTALERT

### Page 57

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
On Frame at STA 720F to the dimen-
sions shown.
165C38706-2KIT - ELECTRICAL
BRACKET, NITROGEN
GENERATION SYS-
TEM
Put / Hold1
Match drill 0.190 - 0.196 inch diam-
eter holes from bracket into frame.
3-HOLEDrill2
For driven rivet electrical bond. (a)3-HOLEPrepare3
165C38706-2KIT - ELECTRICAL
BRACKET, NITROGEN
GENERATION SYS-
TEM
Install
(New)
4
Refer to 727 SRM 51-30-02 as an
accepted procedure.
3BACR15BB6D4CRIVET, UNIVERSAL
HD
Install
(New)
between the bracket and the struc-
ture. Refer to SOPM 20-11-03 as an
accepted procedure. (b)
--BOND RESISTANCEMeasure5
Imprinted "GD4010-S". Locate ap-
proximately as shown. Refer to
SOPM 20-50-05 as an accepted
procedure.
165C38808-11TAPE, IDInstall
(New)
6
(a) Make sure the rivet holes are bare metal. Primer, paint, or other finishes and contaminants inside the rivet
holes can cause the measured resistance of the category 7 driven electrical bond to exceed the resistance
requirements.
(b) Make sure the resistance between the bracket and the structure is less than or equal to 0.0005 Ohms (0.5
milliohms). If the bond resistance is more than 0.0005 Ohms (0.5 milliohms) between the bracket and the
structure repair the bond between the bracket and the structure. Refer to SOPM 20-11-03 as an accepted
procedure.
FIGURE 1: STATION 720F UPPER LEFT GROUND BRACKET - INSTALLATION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011
727-28A0133
57 of 300
BOEING SERVICE BULLETIN 727-28A0133
ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 727-28A0133
ALERT  ALERT
STA
720F
FLOOR BEAM
AT STA 720F
FRAME A
STA 720I
LOOKING FWD  1899218
FIGURE 2: STATION 720F LOWER LEFT GROUND BRACKET - INSTALLATION
(SHEET 1 OF 3)
Original Issue: October 05, 2011
BOEING PROPRIETARY -  727-28A0133
Copyright © Unpublished Work - See page 1 for details.  58 of 300

### Page 59

FIGURE 2: STATION 720F LOWER LEFT GROUND BRACKET - INSTALLATION
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011
727-28A0133
59 of 300
BOEING SERVICE BULLETIN 727-28A0133
ALERTALERT

### Page 60

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
On Frame at STA 720F to the dimen-
sions shown.
165C38706-2KIT - ELECTRICAL
BRACKET, NITROGEN
GENERATION SYS-
TEM
Put / Hold1
Match drill 0.190 - 0.196 inch diam-
eter holes from bracket into frame.
3-HOLEDrill2
For driven rivet electrical bond. (a)3-HOLEPrepare3
165C38706-2KIT - ELECTRICAL
BRACKET, NITROGEN
GENERATION SYS-
TEM
Install
(New)
4
Refer to 727 SRM 51-30-02 as an
accepted procedure.
3BACR15BB6D4CRIVET, UNIVERSAL
HD
Install
(New)
between the bracket and the struc-
ture. Refer to SOPM 20-11-03 as an
accepted procedure. (b)
--BOND RESISTANCEMeasure5
Imprinted "GD4008-S". Locate ap-
proximately as shown. Refer to
SOPM 20-50-05 as an accepted
procedure.
165C38808-12TAPE, IDInstall
(New)
6
(a) Make sure the rivet holes are bare metal. Primer, paint, or other finishes and contaminants inside the rivet
holes can cause the measured resistance of the category 7 driven electrical bond to exceed the resistance
requirements.
(b) Make sure the resistance between the bracket and the structure is less than or equal to 0.0005 Ohms (0.5
milliohms). If the bond resistance is more than 0.0005 Ohms (0.5 milliohms) between the bracket and the
structure repair the bond between the bracket and the structure. Refer to SOPM 20-11-03 as an accepted
procedure.
FIGURE 2: STATION 720F LOWER LEFT GROUND BRACKET - INSTALLATION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011
727-28A0133
60 of 300
BOEING SERVICE BULLETIN 727-28A0133
ALERTALERT

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