# Boeing Alert Service Bulletin 737-28A1216: Boeing - Service Bulletin

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- Document: [Boeing Alert Service Bulletin 737-28A1216](https://openairdocs.org/service-documents/boeing/737-28a1216.md)
- Title as filed: Boeing - Service Bulletin
- Pages: 327
- PDF: https://openairdocs.org/files/sha256/74/c3/74c3c361f4cda21e81a916ed6bc7ed2b218a14cefe28ea24573ec56fbc2e94a5
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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-28A1216
Original Issue: July 29, 2010
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - 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Unpublished Work - All Rights Reserved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 4
F. Approval ............................................... 2 5
G. Manpower .............................................. 2 5
H. Weight and Balance Changes .................................... 5 5
I. Electrical Load Data ......................................... 5 5
J. References .............................................. 5 5
1. Existing Data: ......................................... 5 5
2. Data supplied with this Service Bulletin: ........................... 5 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 5 6
K. Publications Affected ........................................ 5 6
L. Interchangeability and Intermixability of Parts ........................... 5 7
2. MATERIAL INFORMATION ........................................ 5 9
A. Material - Price and Availability ................................... 5 9
B. Industry Support Information .................................... 6 0
C. Parts Necessary For Each Airplane ................................. 6 0
1. Kits/Parts: ........................................... 6 0
2. Parts and Materials Supplied by the Operator: ........................ 8 4
3. Parts Modified and Reidentified: ............................... 8 4
4. Parts Removed and Not Replaced: .............................. 8 4
D. Parts Necessary to Change Spares ................................. 8 4
E. Special Tooling - Price and Availability ............................... 8 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 8 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 8 7
A. GENERAL INFORMATION ..................................... 8 7
B. WORK INSTRUCTIONS ....................................... 8 8
FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 1-16] ............ 1 0 5
FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 17-20] ........... 1 0 6
FIGURE 3: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 1-16]
................................................. 1 0 7
FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 [Group 1-16] ............... 1 0 8
FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 [Group 1-16] ............... 1 1 1
FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 17-20]
................................................. 1 1 4
FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20] .............. 1 1 5
FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20] .............. 1 1 7
FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20] .............. 1 2 0
FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20] .............. 1 2 2
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FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER [Group 1-20] ......... 1 2 5
FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 1-16] .............. 1 2 6
FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 17-20] ............. 1 2 9
FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST [Group
1-20] .............................................. 1 3 2
FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS [Group 1-20]
................................................. 1 3 5
FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group
1-16] .............................................. 1 3 7
FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group
17-20] ............................................. 1 3 9
FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS [Group 1-20] ......... 1 4 1
FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 1-16] ............ 1 4 4
FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 1-16] ......... 1 4 6
FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 [Group 1] ................. 1 4 7
FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036 [Group 2-3] ................ 1 5 0
FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036 [Group 4-5] ................ 1 5 3
FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 [Group 6-7] ................ 1 5 6
FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036 [Group 8] ................. 1 5 9
FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 [Group 9] ................. 1 6 2
FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036 [Group 10-11] ............... 1 6 5
FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036 [Group 12] ................ 1 6 8
FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036 [Group 13] ................ 1 7 1
FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 [Group 14] ................ 1 7 4
FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 [Group 15] ................ 1 7 7
FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036 [Group 16] ................ 1 8 0
FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 17-20] ........... 1 8 3
FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 17-20] ........ 1 8 5
FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 [Group 19] ................ 1 8 6
FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036 [Group 19] ................ 1 8 9
FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036 [Group 19] ................ 1 9 2
FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 1 9 5
FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 1 9 8
FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 0 1
FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 0 4
FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 0 7
FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 1 0
FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 1-16] ......... 2 1 3
FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 [Group 1] ................. 2 1 4
FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, Configuration 1] ........ 2 1 6
FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, Configuration 2] ........ 2 1 8
FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 [Group 3, 16] ............... 2 2 0
FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 1] ........ 2 2 2
FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 2] ........ 2 2 4
FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 [Group 5, 8] ................ 2 2 6
FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, Configuration 1] ........ 2 2 8
FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, Configuration 2] ........ 2 3 0
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FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044 [Group 9] ................. 2 3 2
FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044 [Group 10] ................ 2 3 4
FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, Configuration 1] ....... 2 3 6
FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, Configuration 2] ....... 2 3 8
FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044 [Group 13] ................ 2 4 0
FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044 [Group 7] ................. 2 4 2
FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 1] ....... 2 4 4
FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 2] ....... 2 4 6
FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, Configuration 1] ....... 2 4 8
FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, Configuration 2] ....... 2 5 0
FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 1] ....... 2 5 2
FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 2] ....... 2 5 4
FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 17-20] ........ 2 5 6
FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 1] ....... 2 5 7
FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] ....... 2 6 0
FIGURE 69: CONNECTION OF WIRE BUNDLE W044 [Group 17, Configuration 1] .......... 2 6 3
FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] ....... 2 6 6
FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] ....... 2 6 9
FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] ....... 2 7 2
FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] ....... 2 7 5
FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] ....... 2 7 8
FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 [Group 19] ................ 2 8 1
FIGURE 76: CONNECTION OF WIRE BUNDLE W044 [Group 19, Configuration 1] .......... 2 8 4
FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, Configuration 2] ....... 2 8 7
FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] ....... 2 9 0
FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] ....... 2 9 3
FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] ....... 2 9 6
FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] ....... 2 9 9
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 [Group 1-20] . . 302
FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 1-16] ........... 3 0 6
FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 17-20] .......... 3 0 8
FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 8, 16] ............. 3 1 1
FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 1-7, 9-15] ........... 3 1 3
FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 17-20] ............. 3 1 5
FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group
1-16] .............................................. 3 1 8
FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group
17-20] ............................................. 3 2 1
FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 1-16] ........... 3 2 4
FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 17-20] ........... 3 2 6
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-28A1216Original Issue: July 29, 2010
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - 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 shutoff. The flight crew stays in primary control, with the auto shutoff 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) and Certification Maintenance Requirements
(CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational check of the boost
pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" 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)
The work instructions are divided into 20 airplane groups, 3 parts and 3 work packages because of the different
changes.
PART 1, PART 2, and PART 3 work instructions are divided into 3 work packages because of the different wire
bundle changes.
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.
Group 1-16:
PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install the
J2802 box assembly.
3. 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 W36, W368 and W386. Between the P6
disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire bundle W44.
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.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Group 17-18:
PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install the
J2802 box assembly.
3. Work Package 3:
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NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary Tank
installation. 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.
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 W36, W368 and W386. Between the P6
disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire bundle W44.
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 W44.
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.
Group 19-20:
PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install the
J2802 box assembly.
3. 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 W36, W368 and W386. Between the P6
disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire bundle W44.
Between the P6 disconnect panel and the fuel boost pump relays R146 and R147, make a change to the
wire bundle W44.
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. 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
737-300/400/500 airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
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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 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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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-28A1216
Original Issue: July 29, 2010
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - 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.
NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary
Tank installation. 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.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-1
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-2
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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### Page 12

DESCRIPTIONCONFIGURATIONGROUP
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-3
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-4
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-5
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-6
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-7
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-8
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-9
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-10
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-11
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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DESCRIPTIONCONFIGURATIONGROUP
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-12
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-13
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-14
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-15
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-16
Airplanes delivered with wire provision for Auxiliary Tank installation
and have different wiring configurations at the P5 and P6 panels.
-17
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes delivered with wire provision for Auxiliary Tank installation
and have different wiring configurations at the P5 and P6 panels.
-18
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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DESCRIPTIONCONFIGURATIONGROUP
Airplanes that have the auxiliary fuel tanks and have different wiring
configurations at the P5 and P6 panels.
-19
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that have the auxiliary fuel tanks and have different wiring
configurations at the P5 and P6 panels.
-20
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplane Models:
737-300, 737-400, 737-500
GroupVariable Number
1PJ301 - PJ302
1PJ551 - PJ561
1PJ601 - PJ615
19PJ811
1PJ816 - PJ817
2PM381 - PM399
2PM401 - PM417
2PM541 - PM550
3PM551 - PM564
6PP001 - PP054
12PP101 - PP169
6PP181 - PP187
7PP188 - PP199
6PP201 - PP205
14PP221
6PP231 - PP243
6PP281 - PP286
6PP301 - PP305
6PP351 - PP353
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GroupVariable Number
6PP376 - PP384
6PP391 - PP393
6PP401 - PP440
20PP471 - PP475
18PP501 - PP520
6PP521 - PP522
6PP631 - PP634
6PP651 - PP652
6PP671 - PP689
20PP690 - PP694
6PP695 - PP699
6PP701 - PP706
20PP707 - PP716
6PP717 - PP733
6PP771 - PP779
6PP801 - PP808
6PP821 - PP827
2PP831 - PP848
11PP851 - PP852
11PP861 - PP877
11PP891 - PP899
11PP901 - PP936
11PP946 - PP948
11PP951 - PP952
11PP961 - PP965
3PP966 - PP967
11PP981 - PP982
3PP983 - PP990
11PP991
3PP993
11PQ001 - PQ016
11PQ026 - PQ041
11PQ051 - PQ092
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GroupVariable Number
11PQ101 - PQ199
11PQ201 - PQ202
3PQ221 - PQ230
11PQ231 - PQ232
10PQ233 - PQ237
11PQ241 - PQ242
10PQ243
10PQ251 - PQ267
10PQ281 - PQ299
10PQ301 - PQ307
10PQ331 - PQ332
10PQ341 - PQ348
10PQ361 - PQ373
10PQ391 - PQ395
10PQ401 - PQ418
10PQ421
10PQ431 - PQ438
10PQ447 - PQ448
10PQ451
10PQ454
10PQ471 - PQ475
10PQ479 - PQ481
10PQ486 - PQ487
10PQ491 - PQ493
10PQ771 - PQ772
10PQ791 - PQ793
16PQ801 - PQ805
16PQ931 - PQ935
10PQ951
10PQ971 - PQ997
3PR001 - PR017
3PR021 - PR034
3PR041 - PR045
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GroupVariable Number
3PR061 - PR072
3PR077 - PR082
3PR091 - PR092
3PR096
3PR101
3PR121 - PR122
3PR131 - PR132
3PR141 - PR143
3PR161 - PR172
16PR181
2PS601 - PS631
2PS636 - PS638
2PS641 - PS644
3PS651 - PS657
10PS666 - PS669
3PS691 - PS692
11PS701 - PS706
12PS751 - PS799
3PS811
3PS836 - PS837
2PS841 - PS846
2PS851 - PS852
2PS856
17PS861 - PS863
17PS866 - PS868
2PS871 - PS874
2PS896 - PS897
15PS901 - PS941
17PS956 - PS957
3PS961 - PS963
3PS971 - PS978
3PT001 - PT015
3PT021 - PT031
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GroupVariable Number
3PT041 - PT064
3PT101 - PT105
3PT121 - PT138
3PT146 - PT148
3PT161 - PT170
9PT181 - PT188
3PT211 - PT220
3PT295
3PT301 - PT309
10PT331 - PT360
3PT381 - PT399
3PT401 - PT438
10PT501 - PT517
3PT561 - PT565
3PT581 - PT586
10PT611 - PT621
3PT641 - PT644
3PT651 - PT656
10PT671 - PT672
3PT681 - PT685
13PT701 - PT703
3PT716 - PT717
3PT721 - PT725
10PT801 - PT834
3PT851 - PT854
3PT871 - PT886
10PT901 - PT930
10PT971 - PT973
3PT981 - PT985
3PT996
10PU001 - PU025
3PU301
3PU311 - PU313
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GroupVariable Number
4PV001
5PV002 - PV055
1PV201 - PV209
1PV226 - PV229
8PV231 - PV237
1PV271 - PV272
1PV281 - PV287
1PV296
1PV301 - PV302
1PV351
1PV356 - PV357
1PW001 - PW054
1PW061 - PW068
1PW072
1PW086 - PW088
1PW091 - PW094
1PW101 - PW102
1PW106
1PW111 - PW120
1PW156 - PW157
1PW161 - PW171
1PW201 - PW252
1PW261 - PW268
1PW271 - PW276
1PW278
1PW281 - PW293
1PW296
8PW301 - PW327
1PW401 - PW408
1PW411 - PW418
1PW421 - PW424
1PW431 - PW435
8PW441 - PW450
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GroupVariable Number
1PW461 - PW467
1PW501 - PW504
19PW511 - PW522
19PW524
1PW525 - PW529
19PW530
5PW531 - PW550
5PW556 - PW557
1PW561 - PW564
1PW571 - PW576
1PW591 - PW596
5PW611 - PW622
5PW631 - PW637
5PW661 - PW662
5PW681 - PW683
19PW701 - PW702
1PW711 - PW717
5PW741 - PW742
5PW761
1PW771
1PW831
1PW851 - PW856
2. Spares Affected
None.
B. Concurrent Requirements
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
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DescriptionService BulletinCompany
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) and Certification Maintenance
Requirements (CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational
check of the boost pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" 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 737-28A1228 for the 737-100/200 airplanes
and Service Bulletin 737-28A1206 for the 737-600/700/800/900 airplanes.
D. Description
The work instructions are divided into 20 airplane groups, 3 parts and 3 work packages because of the
different changes.
PART 1, PART 2, and PART 3 work instructions are divided into 3 work packages because of the
different wire bundle changes.
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.
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Group 1-16:
PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL
TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. 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 W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44.
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.
Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.
Group 17-18:
PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX)
FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. Work Package 3:
NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary
Tank installation. 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.
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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 W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. 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 W44.
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.
Group 19-20:
PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. 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 W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147,
make a change to the wire bundle W44.
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. 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.
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Group 1, 4-5, 8, 19:
Affected Maintenance Zones
ZoneModel
102, 205737-400
Group 2, 6-7, 11-12, 14-18, 20:
Affected Maintenance Zones
ZoneModel
102, 205737-300
Group 3:
Affected Maintenance Zones
ZoneModel
102, 205737-300, 737-400, 737-500
Group 9, 13:
Affected Maintenance Zones
ZoneModel
102, 205737-500
Group 10:
Affected Maintenance Zones
ZoneModel
102, 205737-300, 737-500
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 36 months after the
original issue date of this service bulletin.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office approves the 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) to 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-20
in Boeing document "737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR," into the 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.
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.
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Group 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 44 (a)
3.803.801FIGURE 45
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 2, 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 2, 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 44 (a)
3.803.801FIGURE 46
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 2, 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 2, 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 44 (a)
3.803.801FIGURE 47
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 3:
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 3:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 20 (a)
2.755.502FIGURE 22
--1FIGURE 44 (a)
3.803.801FIGURE 48
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH 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
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 44 (a)
3.803.801FIGURE 49
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Group 4, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH 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
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 23
--1FIGURE 44 (a)
3.803.801FIGURE 50
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
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### Page 31

Group 4, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 5:
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 44 (a)
3.803.801FIGURE 51
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
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### Page 32

Group 5:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(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 24
--1FIGURE 44 (a)
3.803.801FIGURE 52
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 33

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 24
--1FIGURE 44 (a)
3.803.801FIGURE 53
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 7:
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 7:
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 44 (a)
3.803.801FIGURE 59
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 8:
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:
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 25
--1FIGURE 44 (a)
3.803.801FIGURE 51
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 85
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 9:
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:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 20 (a)
2.755.502FIGURE 26
--1FIGURE 44 (a)
3.803.801FIGURE 54
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 10:
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 44 (a)
3.803.801FIGURE 55
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### Page 37

Group 10:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(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 27
--1FIGURE 44 (a)
3.803.801FIGURE 62
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
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### Page 38

Group 11, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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 27
--1FIGURE 44 (a)
3.803.801FIGURE 63
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
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### Page 39

Group 11, 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 12, 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 28
--1FIGURE 44 (a)
3.803.801FIGURE 56
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 40

Group 12, 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 28
--1FIGURE 44 (a)
3.803.801FIGURE 57
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH 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 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
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### Page 41

Group 13:
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 29
--1FIGURE 44 (a)
3.803.801FIGURE 58
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH 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 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 42

Group 14, Configuration 1:
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 30
--1FIGURE 44 (a)
3.803.801FIGURE 60
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH 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
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 43

Group 14, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 20 (a)
2.755.502FIGURE 30
--1FIGURE 44 (a)
3.803.801FIGURE 61
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 15, 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 31
--1FIGURE 44 (a)
3.803.801FIGURE 64
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### Page 44

Group 15, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 15, 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 31
--1FIGURE 44 (a)
3.803.801FIGURE 65
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
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### Page 45

Group 15, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 16:
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 32
--1FIGURE 44 (a)
3.803.801FIGURE 48
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 85
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
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### Page 46

Group 16:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 17, 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 33
--2FIGURE 34 (a)
2.755.502FIGURE 38
2.304.602FIGURE 39 (b)
2.304.602FIGURE 40 (b)
--2FIGURE 66 (a)
3.803.801FIGURE 67
3.803.802FIGURE 69 (b)
--2FIGURE 82 (a)
16.3032.602FIGURE 84 (c)
15.1030.202FIGURE 87 (d)
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
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### Page 47

Group 17, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
65.95124.30TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the
total "Task-Hours" and total "Elapsed Hours" time.
(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 air-
plane.
(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 air-
plane.
Group 17, 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 33
--2FIGURE 34 (a)
2.755.502FIGURE 38
2.304.602FIGURE 39 (b)
2.304.602FIGURE 40 (b)
--1FIGURE 66 (a)
3.803.801FIGURE 68
3.803.801FIGURE 70 (b)
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### Page 48

Group 17, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 82 (a)
16.3032.602FIGURE 84 (c)
15.1030.202FIGURE 87 (d)
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
65.95124.30TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the
total "Task-Hours" and total "Elapsed Hours" time.
(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 air-
plane.
(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 air-
plane.
Group 18, 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 33
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### Page 49

Group 18, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 34 (a)
2.755.502FIGURE 41
2.304.602FIGURE 42 (b)
2.304.602FIGURE 43 (b)
--1FIGURE 66 (a)
3.803.801FIGURE 71
3.803.801FIGURE 73 (b)
--2FIGURE 82 (a)
16.3032.602FIGURE 84 (c)
15.1030.202FIGURE 87 (d)
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
65.95124.30TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the
total "Task-Hours" and total "Elapsed Hours" time.
(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 air-
plane.
(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 air-
plane.
Group 18, 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
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### Page 50

Group 18, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
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 33
--2FIGURE 34 (a)
2.755.502FIGURE 41
2.304.602FIGURE 42 (b)
2.304.602FIGURE 43 (b)
--1FIGURE 66 (a)
3.803.801FIGURE 72
3.803.801FIGURE 74 (b)
--2FIGURE 82 (a)
16.3032.602FIGURE 84 (c)
15.1030.202FIGURE 87 (d)
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
65.95124.30TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the
total "Task-Hours" and total "Elapsed Hours" time.
(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 air-
plane.
(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 air-
plane.
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### Page 51

Group 19, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
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 33
--2FIGURE 34 (a)
2.755.502FIGURE 35
2.304.602FIGURE 36
2.304.602FIGURE 37
--1FIGURE 66 (a)
3.803.801FIGURE 75
3.803.801FIGURE 76
--2FIGURE 82 (a)
16.3032.602FIGURE 84
15.1030.202FIGURE 87
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 52

Group 19, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
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 33
--2FIGURE 34 (a)
2.755.502FIGURE 35
2.304.602FIGURE 36
2.304.602FIGURE 37
--1FIGURE 66 (a)
3.803.801FIGURE 75
3.803.801FIGURE 77
--2FIGURE 82 (a)
16.3032.602FIGURE 84
15.1030.202FIGURE 87
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 53

Group 20, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
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 33
--2FIGURE 34 (a)
2.755.502FIGURE 41
2.304.602FIGURE 42
2.304.602FIGURE 43
--1FIGURE 66 (a)
3.803.801FIGURE 78
3.803.801FIGURE 80
--2FIGURE 82 (a)
16.3032.602FIGURE 84
15.1030.202FIGURE 87
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 54

Group 20, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
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 33
--2FIGURE 34 (a)
2.755.502FIGURE 41
2.304.602FIGURE 42
2.304.602FIGURE 43
--1FIGURE 66 (a)
3.803.801FIGURE 79
3.803.801FIGURE 81
--2FIGURE 82 (a)
16.3032.602FIGURE 84
15.1030.202FIGURE 87
3.003.001FIGURE 89
1.501.501FIGURE 91
4.0012.003Close Access
1.002.002Test
81.55151.70TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
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### Page 55

H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+1,300+6Each 737-300
+900+6Each 737-400
+1,650+6Each 737-500
I. Electrical Load Data
1. Direct Current (DC) Loads
Group 1-16:
BusAmperesCircuit Breaker
28V DC Bus 1150 MilliampereC3318
28V DC Bus 2150 MilliampereC3320
Group 17-20:
BusAmperesCircuit Breaker
28V DC Bus 1150 MilliampereC3318
28V DC Bus 2150 MilliampereC3320
28V DC Bus 1150 MilliampereC3327
28V DC Bus 2150 MilliampereC3329
2. Alternating Current (AC) Loads
None,
3. Type
Intermittent
J. References
1. Existing Data:
a. Engineering Change Memo PRR 35442-RS
b. Boeing Service Bulletin 737-28A1206, 737-28A1210, 737-28A1228
c. Federal Aviation Administration (FAA) Airworthiness Directive 2001-08-24
d. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03, 20-50-19
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### Page 56

e. Standard Wiring Practices Manual (SWPM) 20-10-04, 20-10-11, 20-10-11, 20-10-12, 20-10-12,
20-10-14, 20-10-18, 20-10-19, 20-10-19, 20-20-00, 20-20-00, 20-20-10, 20-20-11, 20-20-11,
20-30-00, 20-30-11, 20-30-12, 20-60-00, 20-60-00, 20-60-08, 20-61-11, 20-81-11, 20-81-11,
20-81-17, 20-81-19, 20-81-22, 20-90-11
f. 737-300/400/500 Aircraft Maintenance Manual (AMM) 12-31-11, 24-22-00, 24-31-11, 25-10-00,
25-11-21, 25-51-01, 28-22-00, 32-00-01, 52-48-41, 52-61-00, 52-61-10
g. 737-300/400/500 Wiring Diagram Manual (WDM) 28-23-01, 28-23-02, 28-43-01
h. BAE Systems Service Bulletin 69-37335-28-04
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
*737 FAA Approved Airplane Flight Manual
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
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### Page 57

Chapter-SectionPublication
28737 Minimum Equipment List
* This change affects Sections 1 and 3.1 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.
L. Interchangeability and Intermixability of Parts
None.
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### Page 59

2.    MATERIAL INFORMATION
A. Material - Price and Availability
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
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 1-16:
Unit Price thru
(04-30-2011)
ROLT
(Weeks)
QTYDateNameKit Number
$9,8697520005-05-2010Top Kit- Fuel Tank Boost
Pump Auto Shut Off Sys-
tem, Center Fuel Tank
65C38471-7 (a)
(a) One top kit is necessary for each Groups 1 through 16 airplane.
Group 17-20:
Unit Price thru
(04-30-2011)
ROLT
(Weeks)
QTYDateNameKit Number
$14,265751005-05-2010Top Kit- Fuel Tank Boost
Pump Auto Shut Off Sys-
tem, Center and Auxiliary
Fuel Tanks
65C38471-8 (a)
(a) One top kit is necessary for each Groups 17 through 20 airplane.
(b) Airplanes in Group 17 and Group 18 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 65C38471-8.
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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### Page 60

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 1-16:
Kit 65C38471
NotesExisting Part
Number
NameQTYNew Part Number
-7
(a).TOP KIT-FUEL BOOST PUMP,
AUTO SHUT OFF SYSTEM,
CENTER TANK 737-300/-400/-
500
-65C38471-7
(a).WIRE KIT161-74478-1
(a).JBOX INSTALLATION FOR
AIRPLANES WITHOUT AUX
TANK
165C38484-8
(a) This part is not used in production.
Group 17-20:
Kit 65C38471
NotesExisting Part
Number
NameQTYNew Part Number
-8
(a).TOP KIT-FUEL BOOST PUMP,
AUTO SHUT OFF SYSTEM,
CTR & AUX TANK 737-300/-
400/-500
-65C38471-8
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