# Boeing Alert Service Bulletin 737-28A1228: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-1068; AD 2016-18-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-28A1228](https://openairdocs.org/service-documents/boeing/737-28a1228.md)
- Title as filed: Boeing - Service Bulletin
- Pages: 261
- PDF: https://openairdocs.org/files/sha256/3b/e2/3be2e599d9fc8c8e235fdcb3272bb2ded34151f7b0c86cf7926f4d5361e1bd20
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-28A1228
Original Issue: August 02, 2010
ATA System: 2822
SUBJECT: FUEL - Distribution - Installation of the Auto Shutoff Protection for the Center and
Auxiliary Fuel Tank Boost Pumps
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 © 2010 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Unpublished Work - All Rights Reserved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 ........................................ 2 0
B. Concurrent Requirements ...................................... 2 0
C. Reason ................................................ 2 1
D. Description .............................................. 2 1
E. Compliance .............................................. 2 3
F. Approval ............................................... 2 3
G. Manpower .............................................. 2 4
H. Weight and Balance Changes .................................... 5 2
I. Electrical Load Data ......................................... 5 2
J. References .............................................. 5 3
1. Existing Data: ......................................... 5 3
2. Data supplied with this Service Bulletin: ........................... 5 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 5 4
K. Publications Affected ........................................ 5 4
L. Interchangeability and Intermixability of Parts ........................... 5 5
2. MATERIAL INFORMATION ........................................ 5 7
A. Material - Price and Availability ................................... 5 7
B. Industry Support Information .................................... 5 8
C. Parts Necessary For Each Airplane ................................. 5 8
1. Kits/Parts: ........................................... 5 8
2. Parts and Materials Supplied by the Operator: ........................ 7 9
3. Parts Modified and Reidentified: ............................... 7 9
4. Parts Removed and Not Replaced: .............................. 7 9
D. Parts Necessary to Change Spares ................................. 8 0
E. Special Tooling - Price and Availability ............................... 8 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 8 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 8 1
A. GENERAL INFORMATION ..................................... 8 1
B. WORK INSTRUCTIONS ....................................... 8 2
FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 2-11] ............ 9 8
FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 12-16] ............ 9 9
FIGURE 3: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 2-11]
................................................. 1 0 0
FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 [Group 2-11] ............... 1 0 1
FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 [Group 2-11] ............... 1 0 4
FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 12-16]
................................................. 1 0 7
FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 [Group 12-16] .............. 1 0 8
FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 [Group 12-16] .............. 1 1 0
FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 [Group 12-16] .............. 1 1 3
FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 [Group 12-16] .............. 1 1 5
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FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER [Group 2-16] ......... 1 1 8
FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 2-11] .............. 1 1 9
FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 12-16] ............. 1 2 2
FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E2 SUPPORT POST [Group
2-16] .............................................. 1 2 5
FIGURE 15: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E2 SUPPORT POST [Group
2-16] .............................................. 1 2 8
FIGURE 16: INSTALLATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS [Group 2-11]
................................................. 1 3 0
FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group
12-16] ............................................. 1 3 2
FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS [Group 2-16] ......... 1 3 4
FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 2-11] ............ 1 3 7
FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 2-11] ......... 1 3 9
FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 [Group 2, 10-11] ............. 1 4 0
FIGURE 22: CONNECTION OF WIRE BUNDLE W036 [Group 8-9] ................... 1 4 3
FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036 [Group 3] ................. 1 4 6
FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 [Group 4] ................. 1 4 9
FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036 [Group 5] ................. 1 5 2
FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 [Group 6] ................. 1 5 5
FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036 [Group 7] ................. 1 5 8
FIGURE 28: REMOVAL OF THE RELAYS, P6 PANEL [Group 12-16] .................. 1 6 1
FIGURE 29: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 12-16] ........ 1 6 3
FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 [Group 12-13, 15] ............. 1 6 4
FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 [Group 12-13, 15] ............. 1 6 7
FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036 [Group 12-13, 15] ............. 1 6 9
FIGURE 33: CONNECTION OF THE WIRE BUNDLE W036 [Group 14, 16] .............. 1 7 1
FIGURE 34: CONNECTION OF THE WIRE BUNDLE W036 [Group 14, 16] .............. 1 7 4
FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 [Group 14, 16] .............. 1 7 6
FIGURE 36: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 2-11] ......... 1 7 8
FIGURE 37: CONNECTION OF WIRE BUNDLE W044 [Group 2] .................... 1 7 9
FIGURE 38: CONNECTION OF WIRE BUNDLE W044 [Group 3, 8-11, Configuration 1] ........ 1 8 2
FIGURE 39: CONNECTION OF THE WIRE BUNDLE W044 [Group 3, 8-11, Configuration 2] ..... 1 8 5
FIGURE 40: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 1] ........ 1 8 8
FIGURE 41: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 2] ........ 1 9 1
FIGURE 42: CONNECTION OF THE WIRE BUNDLE W044 [Group 5-6, Configuration 1] ....... 1 9 4
FIGURE 43: CONNECTION OF THE WIRE BUNDLE W044 [Group 5-6, Configuration 2] ....... 1 9 6
FIGURE 44: CONNECTION OF THE WIRE BUNDLE W044 [Group 7, Configuration 1] ........ 1 9 8
FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 [Group 7, Configuration 2] ........ 2 0 0
FIGURE 46: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 12-16] ........ 2 0 2
FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 [Group 13] ................ 2 0 3
FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 [Group 13, Configuration 1] ....... 2 0 6
FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 [Group 13, Configuration 2] ....... 2 0 9
FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 14-16, Configuration 1] . . . 212
FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 14-16, Configuration 2] . . . 215
FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 14-16, Configuration 1] . . . 218
FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 14-16, Configuration 2] . . . 221
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FIGURE 54: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 [Group 2-16] . . 224
FIGURE 55: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 2, 4-5, 11] ........ 2 2 8
FIGURE 56: CONNECTION OF THE WIRE BUNDLE W368 AND WIRE BUNDLE W1764 [Group 8] . 231
FIGURE 57: CONNECTION OF THE WIRE BUNDLE W368 AND WIRE BUNDLE W1764 [Group 9] . 233
FIGURE 58: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 10] ............ 2 3 5
FIGURE 59: CONNECTION OF WIRE BUNDLE W368 / W1764 [Group 3, 6-7] ............. 2 3 7
FIGURE 60: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 12-16] .......... 2 4 0
FIGURE 61: CONNECTION OF WIRE BUNDLE W386 AND W1774 [Group 2, 4-5, 7-11] ....... 2 4 3
FIGURE 62: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 3, 6] .............. 2 4 6
FIGURE 63: CONNECTION OF WIRE BUNDLE W386 AND W1774 [Group 12-16] .......... 2 4 9
FIGURE 64: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group
2-11] .............................................. 2 5 2
FIGURE 65: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group
12-16] ............................................. 2 5 5
FIGURE 66: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 2-11] ........... 2 5 8
FIGURE 67: INSTALLATION OF THE RELAYS, P6 PANEL [Group 12-16] ............... 2 6 0
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-28A1228Original Issue: August 02, 2010
ATA System: 2822
SUBJECT: FUEL - Distribution - Installation of the Auto Shutoff Protection for the Center and
Auxiliary Fuel Tank Boost Pumps
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 is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank System Fault
Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis shows that fuel boost
pumps that run dry could cause an overheat condition external of the fuel pump explosion resistance area that
is open to the fuel pump inlet. An overheat condition in this area could possibly cause an unwanted ignition
source for the fuel vapors in the fuel tank and could cause a fire or explosion.
This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system for the
fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped, also in the auxiliary
fuel tank. Time delay relays are installed in the new J2802 box assembly that will shut off the fuel boost pumps
if the pumps operate with continuous low pressure for 15 seconds. The 15 second time delay relay prevents
extended dry operation of the fuel boost pumps and allows for sufficient time for fuel pump inlet reprime to
prevent nuisance automatic shutoffs. The flight crew stays in primary control, with the auto shut off system as
a backup, to stop the fuel boost pumps after a low pressure indication.
The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel tank
against sparks possibly caused by friction overheat damage.
This change affects the Fuel Systems Airworthiness Limitations section of Boeing document
"737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) andCertification Maintenance Requirements
(CMRs), D6-38278-CMR," New AWL"28-AWL-21" will be added to include an operational check of the boost
pump automatic shutoff system for the center fuel tank. AWL "28-AWL-22" will be added to include an operational
check of the fuel boost pump automatic shutoff system for the auxiliary fuel tank, if installed by Boeing. This
change also affects Section 1 and Section 3 of the FAA approved Airplane Flight Manual (AFM).
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ACTION (PRR 35442-RS)
Group 1:
Operators should tell Boeing about this modification to get the engineering and accomplishment instructions.
Group 2-16:
Operators do these to change the airplane:
NOTE: Airplanes in group 15 and 16 were delivered, or modified by other Boeing change, to have only Auxiliary
Fuel Tank wire provisions installed on airplane. Operators that installed AUX tanks with Fuel Boost
Pumps on these airplanes need to install an Auto Shutoff system. FAA may release an AD to require
that all airplanes that have AUX tanks with Fuel Boost Pumps should install an Auto Shutoff system.
NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service bulletin in
the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these airplanes. If Boeing
is not notified about the Auxiliary Tanks, Boeing will assume that the airplanes in these groups do not
have Auxiliary (AUX) tanks and no AUX Tank changes to the affected manuals will be done.
— Work Package 1: In the J2802 box assembly, install the wire bundles W1760 and W1770.
— Work Package 2: Get access into the main electronics compartment. Between the E2 and E3 rack support
posts, install the J2802 box assembly.
— Work Package 3: In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6
relay modules. Above the P5 overhead panel, make a change to the wire bundles W036, W368 and W386.
Between the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W044. For the airplanes that have an auxiliary fuel tank, between the P6 disconnect panel and the
fuel boost pump relays R146 and R147, make a change to the wire bundle W044.
— In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box
assembly, install the new wire bundles W1764 and W1774.
— In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318 and
R3321. For the airplanes that have auxiliary fuel tank, at the J2802 box assembly, install the time delay
relays R3327 and R3329.
— Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
EFFECTIVITY
All 737-100/200/200C airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
NOTE: Airplanes in group 15 and 16 were delivered, or modified by other Boeing change, to have only Auxiliary
Fuel Tank wire provisions installed on airplane. Operators that installed AUX tanks with Fuel Boost
Pumps on these airplanes need to install an Auto Shutoff system. FAA may release an AD to require
that all airplanes that have AUX tanks with Fuel Boost Pumps should install an Auto Shutoff system.
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.
Group 1:
Operators should tell Boeing about this modification to get the engineering and accomplishment instructions.
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Group 2-16:
Boeing recommends that the change given in this service bulletin be done within 36 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/Parts. Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 737-28A1228
ALERT  ALERT
CHANGE WIRE BUNDLES
W036/W368/W386
INSTALL WIRE BUNDLES
W1764/W1774
CHANGE WIRE BUNDLE WO44
P6 RELAY
PANEL/MODULE
INSTALL WIRE BUNDLES W1760/W1770
INSTALL J2802 BOX ASSEMBLY
INSTALL RELAYS
D35641
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-28A1228
Original Issue: August 02, 2010
ATA System: 2822
SUBJECT: FUEL - Distribution - Installation of the Auto Shutoff Protection for the Center and
Auxiliary Fuel Tank Boost Pumps
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
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR 35442-RS for data about this change.
Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes from line numbers 1 through 291.-1
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-3
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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DESCRIPTIONCONFIGURATIONGROUP
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-4
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-5
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-6
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-7
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-8
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-9
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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DESCRIPTIONCONFIGURATIONGROUP
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-10
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that do not have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-11
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.2
737 airplanes with line numbers higher than 291 that have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-12
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-13
Airplanes from line numbers higher than 291 that have the auxiliary
fuel tanks, have different wire connection configurations at the P5
and P6 panels, and did not incorporate the SB 737-28A1212 R00.
1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that have the
auxiliary fuel tanks and have different wire configurations at the P5
and P6 panels.
-14
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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DESCRIPTIONCONFIGURATIONGROUP
737 airplanes with line numbers higher than 291 that have only
Auxiliary Fuel Tank wire provisions installed on airplane and have
different wire configurations at the P5 and P6 panels.
-15
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
737 airplanes with line numbers higher than 291 that have only
Auxiliary Fuel Tank wire provisions installed on airplane and have
different wire configurations at the P5 and P6 panels.
-16
737 airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
737 airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplane Models:
737-100, 737-200, 737-200C
GroupVariable Number
1PA001 - PA022
1PA099
1PA231 - PA232
1PC001 - PC005
1PG001 - PG075
1PG199
1PG201 - PG230
1PG251 - PG255
1PG271 - PG279
1PG301 - PG314
1PG331 - PG332
1PG351 - PG356
1PG375
1PG401 - PG403
1PG431 - PG442
1PG471 - PG475
1PG501 - PG505
1PG571 - PG583
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GroupVariable Number
11PG584 - PG586
1PG621 - PG630
1PG651 - PG652
1PG701 - PG705
11PH001
11PH011 - PH013
11PH021 - PH024
1PH701 - PH715
1PH731 - PH732
1PH741 - PH742
11PH743
1PJ001 - PJ002
11PJ003 - PJ006
12PJ007 - PJ009
1PJ031 - PJ032
1PJ071 - PJ072
1PJ101 - PJ104
8PJ105 - PJ119
14PJ201 - PJ219
11PK026 - PK029
4PK041 - PK053
11PK061 - PK067
14PK068 - PK070
11PK081 - PK082
11PK091 - PK099
11PK101 - PK103
11PK111 - PK120
4PK141 - PK146
11PK201 - PK204
11PK211 - PK223
11PK231 - PK241
11PK251 - PK256
16PK257
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GroupVariable Number
11PK258
11PK271 - PK274
11PK281 - PK289
11PK291
4PK301 - PK310
3PK311 - PK318
3PK341
11PK351 - PK355
12PK356 - PK359
15PK360
11PK361
11PK391
4PK431 - PK433
4PK451 - PK452
4PK461 - PK469
4PK495
11PK501
15PK502 - PK504
11PK511 - PK515
11PK519
11PK521 - PK528
11PK541 - PK565
11PK581
11PK591 - PK599
9PK601 - PK604
11PK605 - PK606
12PK607 - PK610
11PK611 - PK617
11PK621 - PK637
11PK641 - PK642
14PK661
11PK662 - PK666
11PK671 - PK681
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GroupVariable Number
11PK691 - PK697
11PK711 - PK716
11PK731 - PK765
11PK771 - PK779
10PK801 - PK804
8PK819 - PK827
8PK830
11PK861 - PK863
15PK871 - PK872
12PK873
15PK874
11PK881 - PK884
4PK901 - PK938
4PK971 - PK974
11PL001 - PL028
11PL061
11PL081
5PL101 - PL113
11PL151
11PL171 - PL172
11PL201 - PL203
11PL221
11PL401 - PL408
12PL409 - PL410
11PL411
12PL412
11PL413 - PL417
15PL421
11PL441
11PL451 - PL456
11PL471
11PL491
12PL501
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GroupVariable Number
15PL502 - PL503
12PL504 - PL506
4PL551 - PL562
11PL581
12PL601 - PL603
11PL611
11PL621 - PL626
12PL631 - PL632
1PL711 - PL712
1PL716
11PL717 - PL725
7PL726 - PL728
6PL729 - PL730
3PL731 - PL735
11PL736 - PL747
11PL756
11PL758
11PL761 - PL770
11PL781 - PL788
11PL793
1PL801 - PL803
11PM001 - PM006
11PM016 - PM017
4PM021 - PM023
11PM051 - PM066
12PM101 - PM107
15PM108 - PM119
15PM141 - PM142
11PM171
11PM181
11PM251 - PM255
11PM281 - PM283
12PN001 - PN002
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GroupVariable Number
11PN021 - PN043
4PN081 - PN086
4PN101 - PN117
11PN131 - PN163
11PN401 - PN420
11PN431 - PN433
11PN451 - PN456
11PN471 - PN474
11PN481
11PN491 - PN493
11PN501
2PN502
11PN511
2PN512
13PN521
1PX071
1PX701
1PY001 - PY008
1PY021
11PY022
1PY031
6PY036 - PY037
11PY046 - PY048
11PY051 - PY053
11PY056 - PY057
11PY101 - PY103
11PY111 - PY113
11PY131 - PY135
4PY141 - PY143
11PY151 - PY154
11PY156 - PY157
11PY161 - PY162
11PY166
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GroupVariable Number
11PY191
11PY201
11PY221 - PY222
11PY231
11PY241 - PY244
11PY270 - PY275
11PY281
11PY286
1PY301 - PY304
1PY321 - PY323
1PY341 - PY346
1PY361 - PY362
1PY381
11PY401
11PY409 - PY411
11PY421 - PY422
11PY441
11PY451
11PY461 - PY463
11PY591 - PY595
11PY611 - PY612
11PY621
11PY631
11PY651
11PY671 - PY672
11PY721
11PY741
2. Spares Affected
None.
B. Concurrent Requirements
Group 1:
Operators should tell Boeing about this modification to get the engineering and accomplishment
instructions.
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Group 2-16:
The service bulletin(s) listed below must be done before or at the same time as this service bulletin:
DescriptionService BulletinCompany
Gives instruction to install a new printed
circuit assembly in the P5-2 fuel system
module assembly to supply Low fuel pres-
sure master caution Annunciation.
BAE Systems SB 69-37335-28-04, Revision
2, dated Feb 10/2010
BAE Systems
Gives instruction to replace the P5-2 fuel
system module assembly to supply Low
fuel pressure master caution Annunciation.
737-28A1210, Original IssueBoeing
C. Reason
This service bulletin is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank
System Fault Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis
shows that fuel boost pumps that run dry could cause an overheat condition external of the fuel pump
explosion resistance area that is open to the fuel pump inlet. An overheat condition in this area could
possibly cause an unwanted ignition source for the fuel vapors in the fuel tank and could cause a fire
or explosion.
This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system
for the fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped,
also in the auxiliary fuel tank. Time delay relays are installed in the new J2802 box assembly that will
shut off the fuel boost pumps if the pumps operate with continuous low pressure for 15 seconds. The
15 second time delay relay prevents extended dry operation of the fuel boost pumps and allows for
sufficient time for fuel pump inlet reprime to prevent nuisance automatic shutoffs. The flight crew stays
in primary control, with the auto shut off system as a backup, to stop the fuel boost pumps after a low
pressure indication.
The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel
tank against sparks possibly caused by friction overheat damage.
This change affects the Fuel Systems Airworthiness Limitations section of Boeing document
"737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) andCertification Maintenance
Requirements (CMRs), D6-38278-CMR," New AWL"28-AWL-21" will be added to include an operational
check of the boost pump automatic shutoff system for the center fuel tank. AWL "28-AWL-22" will be
added to include an operational check of the fuel boost pump automatic shutoff system for the auxiliary
fuel tank, if installed by Boeing. This change also affects Section 1 and Section 3 of the FAA approved
Airplane Flight Manual (AFM).
Other related airplane service bulletins are Service Bulletin 737-28A1216 for the 737-300/400/500
airplanes and Service Bulletin 737-28A1206 for the 737-600/700/800/900 airplanes.
D. Description
Group 1:
Operators should tell Boeing about this modification to get the engineering and accomplishment
instructions.
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Group 2-16:
Operators do these to change the airplane:
NOTE: Airplanes in group 15 and 16 were delivered, or modified by other Boeing change, to have
only Auxiliary Fuel Tank wire provisions installed on airplane. Operators that installed AUX
tanks with Fuel Boost Pumps on these airplanes need to install an Auto Shutoff system. FAA
may release an AD to require that all airplanes that have AUX tanks with Fuel Boost Pumps
should install an Auto Shutoff system.
NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service
bulletin in the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these
airplanes. If Boeing is not notified about the Auxiliary Tanks, Boeing will assume that the
airplanes in these groups do not have Auxiliary (AUX) tanks and no AUX Tank changes to
the affected manuals will be done.
— Work Package 1: In the J2802 box assembly, install the wire bundles W1760 and W1770.
— Work Package 2: Get access into the main electronics compartment. Between the E2 and E3 rack
support posts, install the J2802 box assembly.
— Work Package 3: In the flight compartment, get access to the P5 overhead panel, P6 relay panel
or P6 relay modules. Above the P5 overhead panel, make a change to the wire bundles W036,
W368 and W386. Between the P6 disconnect panel and the fuel boost pump relays R54 and R55,
make a change to the wire bundle W044. For the airplanes that have an auxiliary fuel tank, between
the P6 disconnect panel and the fuel boost pump relays R146 and R147, make a change to the
wire bundle W044.
— In the flight and main electronics compartments, between the P6 disconnect panel and the J2802
box assembly, install the new wire bundles W1764 and W1774.
— In the main electronics compartment, at the J2802 box assembly, install the time delay relays
R3318 and R3321. For the airplanes that have auxiliary fuel tank, at the J2802 box assembly,
install the time delay relays R3327 and R3329.
— Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
1-2, 2-2, 2-5737-100, 737-200, 737-200C
Group 2-3, 5, 7-10, 12-16:
Affected Maintenance Zones
ZoneModel
1-2, 2-2, 2-5737-200
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Group 4, 6, 11:
Affected Maintenance Zones
ZoneModel
1-2, 2-2, 2-5737-200, 737-200C
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.
Group 1:
Operators should tell Boeing about this modification to get the engineering and accomplishment
instructions.
Group 2-16:
Boeing recommends that the change given in this service bulletin be done within 36 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.
This SB has been approved by the FAA. In addition, the Manager of the FAASeattle Aircraft Certification
Office approves the installation of the automatic shutoff system for the center tank fuel pumps in
accordance with this service bulletin and the installation of a modified P5-2 Fuel System Module in
accordance with Service Bulletin 737-28A1210, Original Issue, as an alternative method of compliance
(AMOC) with the requirements of paragraph (a) of AD 2001-08-24. Compliance with the conditions of
this AMOC approval requires concurrent incorporation of the associated revisions to Airplane Flight
Manual Sections 1 and 3, and incorporation of Airworthiness Limitations (AWL) 28-AWL-21 in Boeing
document "737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR," into the operator's maintenance documentation.
In order to operate a mixed fleet of airplanes, some having automatic shutoff installed and others without
automatic shutoff, it will be necessary to install a placard in the flight deck of airplanes that do not have
automatic shutoff installed to alert the crew that the procedures required by paragraph (a) of AD
2001-08-24 must be followed on that airplane. The placard should read as follows (alternative placard
wording may be used if approved by an appropriate FAA Principal Operations Inspector):"AD 2001-08-24
fuel usage restrictions required"If an operator would like to use a different method of placarding their
airplanes for operation as a mixed fleet, a request for approval of an AMOC should be submitted to
the Seattle Aircraft Certification Office. All provisions of AD 2001-08-24 that are not specifically referenced
in the above statement remain fully applicable and must be complied with.
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G. Manpower
The table below shows an estimate of the task-hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to inspect the work
— Time to cure the materials
— Time to find the tools.
Group 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 21
--1Figure 36 (a)
3.803.801Figure 37
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
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Group 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
48.8591.60TOTAL FOR EACH GROUP 2 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 3, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 23
--1Figure 36 (a)
3.803.801Figure 38
--2Figure 54 (a)
8.2016.402Figure 59
7.6015.202Figure 62
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 3 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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Group 3, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 23
--1Figure 36 (a)
3.803.801Figure 39
--2Figure 54 (a)
8.2016.402Figure 59
7.6015.202Figure 62
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 3 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 4, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
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Group 4, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 24
--1Figure 36 (a)
3.803.801Figure 40
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 4 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 4, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
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Group 4, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 24
--1Figure 36 (a)
3.803.801Figure 41
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 4 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 5, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
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Group 5, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 20 (a)
2.755.502Figure 25
--1Figure 36 (a)
3.803.801Figure 42
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 5 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 5, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 25
--1Figure 36 (a)
3.803.801Figure 43
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Group 5, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 5 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 6, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 26
--1Figure 36 (a)
3.803.801Figure 42
--2Figure 54 (a)
8.2016.402Figure 59
7.6015.202Figure 62
1.501.501Figure 64
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Group 6, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 6 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 6, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 26
--1Figure 36 (a)
3.803.801Figure 43
--2Figure 54 (a)
8.2016.402Figure 59
7.6015.202Figure 62
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 6 AIRPLANE
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Group 6, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 7, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 27
--1Figure 36 (a)
3.803.801Figure 44
--2Figure 54 (a)
8.2016.402Figure 59
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 7 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 33

Group 7, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 27
--1Figure 36 (a)
3.803.801Figure 45
--2Figure 54 (a)
8.2016.402Figure 59
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 7 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 8, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
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### Page 34

Group 8, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 22
--1Figure 36 (a)
3.803.801Figure 38
--2Figure 54 (a)
8.2016.402Figure 56
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 8 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 8, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
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### Page 35

Group 8, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 22
--1Figure 36 (a)
3.803.801Figure 39
--2Figure 54 (a)
8.2016.402Figure 56
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 8 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 9, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
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### Page 36

Group 9, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 20 (a)
2.755.502Figure 22
--1Figure 36 (a)
3.803.801Figure 38
--2Figure 54 (a)
8.2016.402Figure 57
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 9 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 9, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 22
--1Figure 36 (a)
3.803.801Figure 39
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### Page 37

Group 9, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 54 (a)
8.2016.402Figure 57
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 9 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 10, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 21
--1Figure 36 (a)
3.803.801Figure 38
--2Figure 54 (a)
8.2016.402Figure 58
7.6015.202Figure 61
1.501.501Figure 64
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### Page 38

Group 10, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 10 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 10, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 21
--1Figure 36 (a)
3.803.801Figure 39
--2Figure 54 (a)
8.2016.402Figure 58
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 10 AIRPLANE
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### Page 39

Group 10, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 11, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 21
--1Figure 36 (a)
3.803.801Figure 38
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 11 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 40

Group 11, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 1
--2Figure 3 (a)
3.607.202Figure 4
3.607.202Figure 5
0.150.151Figure 11
1.001.001Figure 12
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 16
1.001.001Figure 18
1.501.501Figure 19
--2Figure 20 (a)
2.755.502Figure 21
--1Figure 36 (a)
3.803.801Figure 39
--2Figure 54 (a)
8.2016.402Figure 55
7.6015.202Figure 61
1.501.501Figure 64
1.501.501Figure 66
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH GROUP 11 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 12, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
--2Figure 6 (a)
3.607.202Figure 7
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### Page 41

Group 12, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31
2.304.602Figure 32
--1Figure 46 (a)
3.803.801Figure 50
3.803.801Figure 52
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH GROUP 12 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 12, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
--2Figure 6 (a)
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### Page 42

Group 12, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.607.202Figure 7
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31
2.304.602Figure 32
--1Figure 46 (a)
3.803.801Figure 51
3.803.801Figure 53
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH GROUP 12 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 13:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
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### Page 43

Group 13:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 6 (a)
3.607.202Figure 7
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31
2.304.602Figure 32
--1Figure 46 (a)
3.803.801Figure 47
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH GROUP 13 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 13, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
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### Page 44

Group 13, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 6 (a)
3.607.202Figure 7
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31
2.304.602Figure 32
--1Figure 46 (a)
3.803.801Figure 48
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH GROUP 13 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 13, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
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### Page 45

Group 13, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 6 (a)
3.607.202Figure 7
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31
2.304.602Figure 32
--1Figure 46 (a)
3.803.801Figure 49
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH GROUP 13 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 14, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
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### Page 46

Group 14, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 6 (a)
3.607.202Figure 7
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 33
2.304.602Figure 34
2.304.602Figure 35
--1Figure 46 (a)
3.803.801Figure 50
3.803.801Figure 52
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH GROUP 14 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 14, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
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### Page 47

Group 14, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.150.151Figure 2
--2Figure 6 (a)
3.607.202Figure 7
3.607.202Figure 8
3.607.202Figure 9
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 33
2.304.602Figure 34
2.304.602Figure 35
--1Figure 46 (a)
3.803.801Figure 51
3.803.801Figure 53
--2Figure 54 (a)
16.3032.602Figure 60
15.1030.202Figure 63
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
65.95124.30TOTAL FOR EACH GROUP 14 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 48

Group 15, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
--2Figure 6 (a)
3.607.202Figure 7 (b)
3.607.202Figure 8
3.607.202Figure 9 (b)
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31(b)
2.304.602Figure 32 (b)
--1Figure 46 (a)
3.803.801Figure 50
3.803.801Figure 52 (b)
--2Figure 54 (a)
16.3032.602Figure 60 (c)
15.1030.202Figure 63 (d)
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
65.95124.30TOTAL FOR EACH GROUP 12 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) It is necessary to do the change given in this figure only if Auxiliary Fuel Tanks with Fuel
Boost pumps are installed on the airplane.
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### Page 49

Group 15, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
Group 15, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
--2Figure 6 (a)
3.607.202Figure 7 (b)
3.607.202Figure 8
3.607.202Figure 9 (b)
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 30
2.304.602Figure 31 (b)
2.304.602Figure 32 (b)
--1Figure 46 (a)
3.803.801Figure 51
3.803.801Figure 53 (b)
--2Figure 54 (a)
16.3032.602Figure 60 (c)
15.1030.202Figure 63 (d)
3.003.001Figure 65
1.501.501Figure 67
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### Page 50

Group 15, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Close Access
1.002.002Test
65.95124.30TOTAL FOR EACH GROUP 12 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) It is necessary to do the change given in this figure only if Auxiliary Fuel Tanks with Fuel
Boost pumps are installed on the airplane.
(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
Group 16, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
--2Figure 6 (a)
3.607.202Figure 7 (b)
3.607.202Figure 8
3.607.202Figure 9 (b)
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
--2Figure 29 (a)
2.755.502Figure 33
2.304.602Figure 34 (b)
2.304.602Figure 35 (b)
--1Figure 46 (a)
3.803.801Figure 50
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### Page 51

Group 16, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.803.801Figure 52 (b)
--2Figure 54 (a)
16.3032.602Figure 60 (c)
15.1030.202Figure 63 (c)
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
65.95124.3TOTAL FOR EACH GROUP 14 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) It is necessary to do the change given in this figure only if Auxiliary Fuel Tanks with Fuel
Boost pumps are installed on the airplane.
(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
Group 16, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151Figure 2
--2Figure 6 (a)
3.607.202Figure 7 (b)
3.607.202Figure 8
3.607.202Figure 9 (b)
3.607.202Figure 10
0.150.151Figure 11
1.001.001Figure 13
1.001.001Figure 14
2.002.001Figure 15
0.500.501Figure 17
1.001.001Figure 18
1.501.501Figure 28
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### Page 52

Group 16, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2Figure 29 (a)
2.755.502Figure 33
2.304.602Figure 34 (b)
2.304.602Figure 35 (b)
--1Figure 46 (a)
3.803.801Figure 51
3.803.801Figure 53 (b)
--2Figure 54 (a)
16.3032.602Figure 60 (c)
15.1030.202Figure 63 (d)
3.003.001Figure 65
1.501.501Figure 67
4.0012.003Close Access
1.002.002Test
65.95124.3TOTAL FOR EACH GROUP 14 AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) It is necessary to do the change given in this figure only if Auxiliary Fuel Tanks with Fuel
Boost pumps are installed on the airplane.
(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost pumps are installed on the airplane.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+ 1,650+ 6Each 737 Airplane
I. Electrical Load Data
1. Direct Current (DC) Loads:
Group 2-11:
BusAmperesCircuit Breaker
28V DC Bus 1150 MilliamperesC3318
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Group 2-11:
BusAmperesCircuit Breaker
28V DC Bus 2150 MilliamperesC3320
Group 12-16:
BusAmperesCircuit Breaker
28V DC Bus 1150 MilliamperesC3318
28V DC Bus 2150 MilliamperesC3320
28V DC Bus 1150 MilliamperesC3327
28V DC Bus 2150 MilliamperesC3329
2. Alternating Current (AC) Loads:
None.
3. Type:
Intermittent.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 35442-RS
b. Boeing Parts Standards Document D-590
c. Boeing Service Bulletin 737-28A1206, 737-28A1210, 737-28A1212, 737-28A1216
d. Federal Aviation Administration (FAA) Airworthiness Directive 2001-08-24
e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03, 20-50-19
f. Standard Wiring Practices Manual (SWPM) 20-10-04, 20-10-11, 20-10-12, 20-10-14, 20-10-18,
20-20-00, 20-20-10, 20-20-11, 20-30-00, 20-30-11, 20-30-12, 20-30-22, 20-60-00, 20-60-08,
20-61-11, 20-71-11, 20-81-11, 20-81-17, 20-81-19, 20-81-22, 20-90-11
g. 737-100/200 Aircraft Maintenance Manual (AMM) 12-31-11, 20-10-111, 24-22-0, 24-31-11,
25-11-0, 25-16-11, 25-51-01, 28-22-0, 52-48-41, 52-61-0, 52-61-100
h. 737-100/200 Wiring Diagram Manual (WDM) 28-23-01, 28-23-02, 28-43-01
i. BAE Systems Service Bulletin BAE Systems SB 69-37335-28-04, Revision 2, dated Feb
10/2010
j. Special Federal Aviation Regulation (SFAR) 88
k. Boeing Service Bulletins Index Document D6-19567
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2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Kit- Wire Installation, Auto Shut Off System61-74478
Wire Bundle Installation- Flight Compartment65-48315
Wire Bundle Installation- Flight Compartment65-48322
Wire Bundle Installation- Flight Compartment65-48325
Disconnect Panel Installation- Flight Compartment65-49731
Support Post Installation- E2 and E3 Rack65-63811
Top Kit- Fuel Boost Pump, Auto Shut Off System, Center Fuel Tank65C38471
Kit- J2802 Box Installation, Auto Shut Off System,65C38484
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
(a)737 FAA Approved Airplane Flight Manual
1, 12, NP and NNC737 Operations Manual
28-22737 Maintenance Manual
28-23, 28-43737 Wiring Diagram Manual
28-23, 28-43737 Illustrated Parts Catalog
28737 Dispatch Deviation Guide
28737 Minimum Equipment List
(a) This change affects Sections 1 and 3 of the FAA Approved Airplane Flight Manual.
Operators will receive applicable data.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
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L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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### Page 57

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. If
there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits
become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing
gets the purchase order.
Group 2-11:
Unit Price thru
(4-30-2011)
ROLT
(Weeks)
QTYDateNameKit Number
$10,12775605-5-2010Top Kit- Fuel Tank
Boost Pump Auto Shut
Off System, Center Fu-
el Tank
65C38471-5 (a)
$10,12775305-12-2010Top Kit- Fuel Tank
Boost Pump Auto Shut
Off System, Center Fu-
el Tank
65C38471-5 (a)
(a) One top kit is necessary for each Groups 2 through 11 airplane.
Group 12-16:
Unit Price thru
(4-30-2011)
ROLT
(Weeks)
QTYDateNameKit Number
$15,12375105-5-2010Top Kit- Fuel Tank Boost
Pump Auto Shut Off
System, Center and
Auxiliary Fuel Tanks
65C38471-6 (a)
(b)
(a) One top kit is necessary for each Groups 12 through 16 airplane.
(b) Airplanes in Group 15 and Group 16 have been delivered with wire provisions for Auxiliary
Tanks installation. If Auxiliary Tanks have been installed on these airplanes operators need to
order this kit. If Auxiliary Tanks have not been installed on these airplanes there are more parts
than necessary in this kit. Operators need to order only the necessary parts to incorporate the
Auto Shutoff system for the Center Tanks. The necessary parts can be ordered as end item parts.
Contact Boeing Spares for ordering the necessary end item parts from kit 65C38471-6.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
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Reference this service bulletin and submit your purchase order by one of the methods that
follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle,
Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Group 2-11:
Kit 65C38471
NotesExisting Part
Number
NameQTYNew Part Number
-5
(a).TOP KIT-FUEL BOOST PUMP,
AUTO SHUT OFF SYSTEM, CEN-
TER TANK 737-100/-200
-65C38471-5
(a).WIRE KIT161-74815-1
(a).KIT - JBOX INSTALLATION FOR
AIRPLANES WITHOUT AUX TANK
165C38484-8
(a) This part is not used in production.
Group 12-16:
Kit 65C38471
NotesExisting Part
Number
NameQTYNew Part Number
-6
(a).TOP KIT-FUEL BOOST PUMP,
AUTO SHUT OFF SYSTEM, CTR
& AUX TANK 737-100/-200
-65C38471-6
(a).WIRE KIT161-74815-2
(a).KIT - JBOX INSTALLATION FOR
AIRPLANES WITH AUX TANK
165C38484-9
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Group 12-16:
Kit 65C38471
NotesExisting Part
Number
NameQTYNew Part Number
-6
(a) This part is not used in production.
Group 2-11:
Kit 61-74815
NotesExisting Part
Number
NameQTYNew Part Number
-1
(a).WIRE KIT-61-74815-1
(a).ASSY - W036161-74815-101
(a).ASSY - W044161-74815-103
(a).ASSY - W1760161-74815-105
(a).ASSY - W1770161-74815-107
(a).ASSY - W368, W1764161-74815-109
(a).ASSY - W386, W1774161-74815-111
(a).LACING TAPE - WHITE161-74815-2001
(a).THERMOFIT SLEEVE - 0.125 I.D.161-74815-2003
(a).EXPANDABLE SLEEVE, 0.5 IN.
I.D.
161-74815-2004
.CONTACT, PIN3BACC47CN1S
(a) This part is not used in production.
Group 12-16:
Kit 61-74815
NotesExisting Part
Number
NameQTYNew Part Number
-2
(a).WIRE KIT-61-74815-2
(a).ASSY - W036161-74815-102
(a).ASSY - W044161-74815-104
(a).ASSY - W1760161-74815-106
(a).ASSY - W1770161-74815-108
(a).ASSY - W368, W1764161-74815-110
(a).ASSY - W386, W1774161-74815-112
(a).LACING TAPE - WHITE161-74815-2001
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Group 12-16:
Kit 61-74815
NotesExisting Part
Number
NameQTYNew Part Number
-2
(a).THERMOFIT SLEEVE - 0.125 I.D.161-74815-2003
(a).EXPANDABLE SLEEVE, 0.5 IN.
I.D.
161-74815-2004
.CONTACT, PIN3BACC47CN1S
(a) This part is not used in production.
Group 2-11:
Kit 61-74815
NotesExisting Part
Number
NameQTYNew Part Number
-101-101W
(a).ASSY - W036-.61-74815-101
(b).SPLICE, PARALLEL, SOLIS-
TRAND
3.34137
.WIRE LIST1-61-74815-101W
(c).CONNECTOR I.D. TAPE -
D04070P
1.61-74815-10101
(c).CONNECTOR I.D. TAPE -
D04076P
1.61-74815-10102
(c).CONNECTOR I.D. TAPE -
D04072P
1.61-74815-10103
(c).CONNECTOR I.D. TAPE -
D04180P
1.61-74815-10104
(c).CONNECTOR I.D. TAPE -
D04238P
1.61-74815-10105
(c).CONNECTOR I.D. TAPE -
D04240P
1.61-74815-10106
(d).SPLICE I.D. SLEEVE - SM1161.61-74815-10107
(d).SPLICE I.D. SLEEVE - SM1181.61-74815-10108
(b) (f).FILLER WIRE1.61-74815-10109
(b).CONTACT, PIN5.BACC47CN1S
(b).CONTACT, SOCKET5.BACC47CP1S
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