# Boeing Alert Service Bulletin 737-28A1201: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2008-0269; AD 2010-17-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-28A1201](https://openairdocs.org/service-documents/boeing/737-28a1201.md)
- Title as filed: U.S. DOT/FAA - 2008-0269; Dir. ID 2007-NM-320-AD Service Bulletin
- Pages: 45
- PDF: https://openairdocs.org/files/sha256/7f/5e/7f5ec58d330e57c3a8782c042dcad2d66ddf715aa2141ecbe121905d5ca27839
- Page: https://openairdocs.org/service-documents/boeing/737-28a1201/file/7f5ec58d330e

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-28A1201
Original Issue: February 19, 2007
Revision 1: May 28, 2009
ATA System: 2820
SUBJECT: FUEL - Engine Fuel Feed System - Fuel Pump Control Ground Fault Interrupter (GFI)
Relay Installation
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2007 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Unpublished Work - All Rights Reserved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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737-28A1201Revision 1: May 28, 2009
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ..................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 9
B. Concurrent Requirements ...................................... 1 9
C. Reason ................................................ 1 9
D. Description .............................................. 2 0
E. Compliance .............................................. 2 1
F . Approval ............................................... 2 1
G. Manpower .............................................. 2 1
H. Weight and Balance Changes .................................... 2 2
I. Electrical Load Data ......................................... 2 2
J. References .............................................. 2 3
1. Existing Data: .......................................... 2 3
2. Data supplied with this Service Bulletin: ........................... 2 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 3
K. Publications Affected ......................................... 2 3
L. Interchangeability and Intermixability of Parts ........................... 2 3
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 5
C. Parts Necessary For Each Airplane ................................. 2 5
1. Kits/Parts: ............................................ 2 5
2. Parts and Materials Supplied by the Operator: ........................ 2 5
3. Parts Modified and Reidentified: ................................ 2 5
4. Parts Removed and Not Replaced: .............................. 2 9
D. Parts Necessary to Change Spares ................................. 2 9
E. Special Tooling - Price and Availability ............................... 2 9
F . Special Tooling Necessary to do this Service Bulletin ....................... 2 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1
A. GENERAL INFORMATION ..................................... 3 1
B. WORK INSTRUCTIONS ....................................... 3 1
FIGURE 1: P91 POWER DISTRIBUTION PANEL CHANGE ....................... 4 2
FIGURE 2: P92 POWER DISTRIBUTION PANEL CHANGE ....................... 4 4
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737-28A1201Revision 1: May 28, 2009
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-28A1201Original Issue: February 19, 2007
Revision 1: May 28, 2009
ATA System: 2820
SUBJECT: FUEL - Engine Fuel Feed System - Fuel Pump Control Ground Fault Interrupter (GFI)
Relay Installation
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2007-NM-320-AD, is related to
this service bulletin.
More work is required for airplanes that have done the initial release of this service bulletin. Operators must
measure the electrical resistance between the GFI relays mounting flange and a point on the panel cross member
of the P91 and P92 Panels. in accordance with Honeywell SB 1151932-24-61, Revision 5, dated Jan 22/2009
and Honeywell SB 1151934-24-62, Revision 5, dated Jan 22/2009. For more information see Paragraph 3.B,
WORK INSTRUCTIONS, Group 1, Configuration 2, Part 2.
REASON FOR REVISION
This revision is sent to tell operators that supplier service bulletins, Honeywell ASCa Inc. 1151932-24-61, Revision
5, dated Jan 22/2009 and 1151934-24-62, Revision 5, dated Jan 22/2009 were changed to add a resistance
check between the GFI relays mounting flange and a point on the panel cross member of the P91 and P92
Panels. Operators that have done the initial release of this service bulletin must measure the electrical resistance
between the GFI relays mounting flange and a point on the panel cross member of the P91 and P92 Panels in
accordance with the latest version of these supplier service bulletins.
Two new configurations were added to Group 1. Configuration 1 is now all the airplanes that are applicable to
this service bulletin that have not yet done this service bulletin. Configuration 2 is now all the applicable airplanes
to this service bulletin that have done this service bulletin by the initial release.
These sections were changed:
1. SUMMARY
 Revised the SUMMARY , COMPLIANCE, to add NPRM 2007-NM-320-AD and to revise the compliance
time to within 60 months of the date on revision 1 of this service bulletin.
 Revised the SUMMARY , ACTION, to add a Part 1 and Part 2 Work Instructions.
2. PLANNING INFORMATION
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 Revised Paragraph 1.A., Effectivity to add new Configuration 1 and 2 to GROUP 1 in the group
configuration table
 Revised Paragraph 1.C., Reason to add a list of changes for Revision 1 of this service bulletin
 Revised Paragraph 1.D., Description to add a paragraph to tell operators that more work is required
for Configuration 2 airplanes, See Paragraph 3.B., Work Instructions, Part 2
 Revised Paragraph 1.E., Compliance to add NPRM-NM-320-AD and to revise the compliance time to
within 60 months of the date on revision 1 of this service bulletin.
3. ACCOMPLISHMENT INSTRUCTIONS
 Revised Paragraph 3.A., General Information Note 3 to change "as given in" to "in accordance with"
 Revised Paragraph 3.B., Work Instructions to add a new Part 1 for all Group1, Configuration 1 airplanes
 Revised Paragraph 3.B., Work Instructions to add a new Part 2 and a new step 1 to measure resistance
between the GFI relays mounting flange and a point on the panel cross member of the P91 and P92
Panels, for Group 1, Configuration 2 airplanes.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
February 19, 2007Original Issue:
May 28, 2009Revision 1:
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Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-28A1201Original Issue: February 19, 2007
Revision 1: May 28, 2009
ATA System: 2820
SUBJECT: FUEL - Engine Fuel Feed System - Fuel Pump Control Ground Fault Interrupter (GFI)
Relay Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY . IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
Honeywell Service Bulletins 1151932-24-61, Revision 5, dated Jan 22/2009 and 1151934-24-62, Revision 5,
dated Jan 22/2009 are necessary to be accomplished prior to or concurrent with this service bulletin.
BACKGROUND
This service bulletin gives the instructions to replace the power control relays for the fuel boost pump and override
pumps. The relays are located in the P91 and P92 power distribution panels. The new relays include a ground
fault interrupt (GFI) feature.The GFI feature will protect the fuel pumps from damage caused by electrical arcing.
Electrical arcing could create a possible source of ignition of flammable fuel vapors in the fuel tanks. Ignition of
flammable fuel vapors could cause a fire or explosion which could put the airplane in an unsafe condition.
This change affects section 9 of the Maintenance Planning Data (MPD) Document. New Airworthiness Limitations
(AWL) "28-AWL-20" will be added to section 9 of the MPD to include a functional check of the ground fault
interrupt (GFI) relays for the fuel boost pumps and override pumps.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank
System Fault Tolerance Evaluation Requirements".
ACTION (PRR 38545-10S)
PART 1
In the electrical/electronics compartment, get access to the P91 and P92 power distribution panels. Change the
P91 and P92 power distribution panels as shown in the Honeywell Service Bulletins 1151932-24-61, Revision
5, dated Jan 22/2009 and 1151934-24-62, Revision 5, dated Jan 22/2009. Do an operational test of the GFI
relays installed in the P91 and P92 panels.
PART 2
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Measure the resistance in accordance with supplier service bulletin Honeywell ASCa Inc. 1151932-24-61,
Revision 5, dated Jan 22/2009, and 1151934-24-62, Revision 5, dated Jan 22/2009.
EFFECTIVITY
737-600/700/700C/800/900 airplanes line numbers 1 - 1980, 1982 - 2092, 2094 - 2209. Refer to Paragraph
1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2007-NM-320-AD, is related to this
service bulletin.
Boeing recommends that operators do this change within 60 months of the date on Revision 01 of this service
bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task Hours
3.503.50
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 737-28A1201
ALERT  ALERT
CHANGE THE P91 AND P92
POWER DISTRIBUTION PANELS
ELECTRICAL AND
ELECTRONICS  ELECTRONIC
COMPARTMENT
EQUIPMENT
SEE  ACCESS DOOR,
117A
0000
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
ELECTRICAL AND ELECTRONICS COMPARMENT
J65466
Original Issue: February 19, 2007
Revision 1: May 28, 2009  737-28A1201
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737-28A1201Revision 1: May 28, 2009
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ALERTALERT
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-28A1201
Original Issue: February 19, 2007
Revision 1: May 28, 2009
ATA System: 2820
SUBJECT: FUEL - Engine Fuel Feed System - Fuel Pump Control Ground Fault Interrupter (GFI)
Relay Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY . IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR38545-10S for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
737-600/700/700C/800/900 Airplanes Line Numbers 1 - 1980,
1982-2092, 2094-2209.
-1
All applicable airplanes that have not done this service bulletin.1
All applicable airplanes that have done the initial release of this
service bulletin.
2
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900
GroupVariable Number
1YA001 - YA099
1YA101 - YA199
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GroupVariable Number
1YA201 - YA211
1YA221
1YA231 - YA242
1YA251 - YA256
1YA271 - YA272
1YA291
1YA301 - YA302
1YA311 - YA314
1YA321 - YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
1YA501 - YA536
1YA541 - YA552
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
1YA671 - YA672
1YA681 - YA691
1YA701 - YA710
1YA721 - YA722
1YA731 - YA734
1YA751 - YA756
1YA801 - YA803
1YA809
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GroupVariable Number
1YA811 - YA814
1YA831 - YA835
1YA841 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA978
1YB001 - YB006
1YB101 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB392
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
1YB561 - YB598
1YB601 - YB632
1YB651
1YB656
1YB671
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
1YB901 - YB903
1YB911
1YB961 - YB966
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GroupVariable Number
1YC001 - YC030
1YC051 - YC083
1YC091 - YC094
1YC101 - YC104
1YC111 - YC113
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC178
1YC186 - YC189
1YC201 - YC203
1YC206 - YC207
1YC301 - YC305
1YC321 - YC387
1YC391 - YC394
1YC396
1YC401 - YC417
1YC421 - YC422
1YC426 - YC428
1YC436 - YC438
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
1YC471 - YC499
1YC501 - YC526
1YC571 - YC583
1YC587 - YC589
1YC591 - YC593
1YC601 - YC655
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GroupVariable Number
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC748
1YC751 - YC752
1YC761 - YC770
1YC781 - YC793
1YC801 - YC892
1YC901 - YC907
1YC921 - YC922
1YC931 - YC932
1YC941 - YC951
1YC971 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD110
1YD121 - YD126
1YD151 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
1YD391
1YD401 - YD410
1YD412 - YD414
1YD481 - YD485
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GroupVariable Number
1YD491 - YD496
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD601 - YD612
1YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG103
1YG111 - YG112
1YG116
1YG201 - YG205
1YG211 - YG214
1YG251
1YG501 - YG509
1YG601 - YG602
1YJ001 - YJ006
1YJ011 - YJ013
1YJ021
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GroupVariable Number
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ558
1YJ591 - YJ594
1YJ631 - YJ632
1YJ671 - YJ686
1YJ690 - YJ694
1YJ801 - YJ867
1YJ871
1YJ901 - YJ902
1YJ911 - YJ928
1YJ931 - YJ936
1YJ941 - YJ949
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK132
1YK136 - YK137
1YK141 - YK142
1YK146 - YK147
1YK151 - YK154
1YK161 - YK164
1YK301 - YK307
1YK321 - YK334
1YK361 - YK369
1YK401 - YK406
1YK426 - YK427
1YK431 - YK447
1YK456 - YK460
1YK476
1YK480 - YK484
1YK511 - YK514
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GroupVariable Number
1YK551 - YK565
1YK571
1YK576 - YK577
1YK580 - YK582
1YK601 - YK602
1YK606
1YK611 - YK614
1YK621 - YK623
1YK631 - YK632
1YK641 - YK642
1YK651 - YK655
1YK701 - YK707
1YK716
1YK721 - YK731
1YK791 - YK792
1YK796
1YK801 - YK841
1YK901 - YK907
1YK921
1YK941 - YK945
1YK961 - YK965
1YK981 - YK982
1YL001 - YL005
1YL011 - YL015
1YL051 - YL052
1YL056 - YL057
1YL061
1YL201 - YL202
1YL271 - YL272
1YL301 - YL303
1YL311
1YL421
1YL461 - YL466
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GroupVariable Number
1YM101 - YM103
1YM201 - YM222
1YM251 - YM299
1YM301 - YM318
1YM471
1YM481 - YM484
1YM501 - YM512
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM591 - YM593
1YM631 - YM634
1YM641
1YN001 - YN009
1YN021
1YN061
1YN071 - YN075
1YN101 - YN110
2. Spares Affected
Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts
Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for
the recommended use.
B. Concurrent Requirements
The related Honeywell Service Bulletins are 1151932-24-61, Revision 5, dated Jan 22/2009 and
1151934-24-62, Revision 5, dated Jan 22/2009.
C. Reason
This service bulletin gives the instructions to replace the power control relays for the fuel boost pump
and override pumps. The relays are located in the P91 and P92 power distribution panels. The new
relays include a ground fault interrupt (GFI) feature. The GFI feature will protect the fuel pumps from
damage caused by electrical arcing. Electrical arcing could create a possible source of ignition of
flammable fuel vapors in the fuel tanks. Ignition of flammable fuel vapors could cause a fire or explosion
which could put the airplane in an unsafe condition.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
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### Page 20

This change affects section 9 of the Maintenance Planning Data (MPD) Document. New Airworthiness
Limitations (AWL) "28-AWL-20" will be added to section 9 of the MPD to include a functional check of
the ground fault interrupt (GFI) relays for the fuel boost pumps and override pumps.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel
Tank System Fault Tolerance Evaluation Requirements".
Revision 1 is sent to tell operators supplier service bulletins, Honeywell ASCa Inc. 1151932-24-61,
Revision 5, dated Jan 22/2009 and 1151934-24-62, Revision 5, dated Jan 22/2009 were changed to
add a resistance check between the GFI relays mounting flange and a point on the panel cross member
of the P91 and P92 Panels. Operators that have done the initial release of this service bulletin must
re-check these airplanes in accordance with the latest version of these supplier service bulletins. For
more information see Paragraph 3.B. WORK INSTRUCTIONS, Group 1, Configuration 2, Part 2.
These sections were changed:
1. SUMMARY
 Revised the SUMMARY , COMPLIANCE, to add NPRM 2007-NM-320-AD and to revise the
compliance time to within 60 months of the date on revision 1 of this service bulletin.
 Revised the SUMMARY , ACTION, to add Part 1 and Part 2, Work Instructions.
2. PLANNING INFORMATION
 Revised Paragraph 1.A., Effectivity to add new Configuration 1 and 2 to GROUP 1 in the
group configuration table
 Revised Paragraph 1.C., Reason to add a list of changes for Revision 1 of this service bulletin
 Revised Paragraph 1.D., Description to add a paragraph to tell operators that more work is
required for Configuration 2 airplanes, See Paragraph 3.B., Work Instructions, Part 2
 Revised Paragraph 1.E., Compliance to add NPRM-NM-320-AD and to revise the compliance
time to within 60 months of the date on revision 1 of this service bulletin.
3. ACCOMPLISHMENT INSTRUCTIONS
 Revised Paragraph 3.A., General Information Note 3 to change "as given in" to "in accordance
with"
 Revised Paragraph 3.B., Work Instructions to add a new Part 1 for all Group1, Configuration
1 airplanes
 Revised Paragraph 3.B., Work Instructions to add a new Part 2 and a new step 1 to measure
resistance between the GFI relays mounting flange and a point on the panel cross member
of the P91 and P92 Panels, for Group 1, Configuration 2 airplanes.
D. Description
PART 1
In the electrical/electronics compartment, get access to the P91 and P92 power distribution panels.
Change the P91 and P92 power distribution panels as shown in the Honeywell Service Bulletins
1151932-24-61, Revision 5, dated Jan 22/2009 and 1151934-24-62, Revision 5, dated Jan 22/2009.
Do an operational test of the GFI relays installed in the P91 and P92 panels.
PART 2
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Measure the resistance in accordance with supplier service bulletin Honeywell ASCa Inc. 1151932-24-61,
Revision 5, dated Jan 22/2009 and 1151934-24-62, Revision 5, dated Jan 22/2009.
Revision 1:
More work is required for Group 1, Configuration 2 airplanes. (Airplanes that have done the initial
release of this service bulletin) See Paragraph 3.B., Work Instructions, Part 2.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
123, 124737-600, 737-700, 737-700C,
737-800, 737-900
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2007-NM-320-AD, is related
to this service bulletin.
Boeing recommends that operators do this change within 60 months of the date on Revision 01 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 Federal Aviation Regulations (14 CFR Part 25) and
Joint Aviation Requirements (JAR-25) and are FAA/JAA approved. This service bulletin and FAA/JAA
approval were based on the airplane in it's original Boeing delivery configuration or as modified by
other FAA/JAA 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.
NOTE: Joint Airworthiness Requirements (JAR) compliance status may be found in the Service Bulletin
Index, Part 1.
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 examine the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
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Elapsed HoursTask-HoursNumber of PersonsTask
0.500.501Open Access
(a)(a)(a)Change
0.500.501Close Access
2.502.501Test
3.503.50TOTAL FOR EACH AIRPLANE
(a) The changes to the P91 and P92 power distribution panels as given in Honeywell SB
1151932-24-61, Revision 5, dated Jan 22/2009 and Honeywell SB 1151934-24-62, Revision
5, dated Jan 22/2009 are not included.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+ 259+ 0.94737-600
+ 208+ 0.94737-700/700C
+ 97+ 0.94737-800
+ 37+ 0.94737-900
None.
I. Electrical Load Data
1. Direct Current (DC) Loads
None.
2. Alternating Current (AC) Loads
BusPhaseVolt-Ampere-
Reactive
(VARs)
WattsAirplanes
115V AC Transfer Bus No.
1
C- 0.90- 1.04737-600/700/700C/800/900
115V AC Transfer Bus No.
2
C- 0.90- 1.04737-600/700/700C/800/900
3. Type
Continuous
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J. References
1. Existing Data:
a. Engineering Change Memo PRR38545-10S
b. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 24-22-00/201
c. Honeywell Service Bulletins 1151932-24-61, Revision 5, dated Jan 22/2009 and
1151934-24-62, Revision 5, dated Jan 22/2009.
NOTE: The supplier was told to send copies of the service bulletin to each operator.
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
Chapter-SectionPublication
28-22737 Maintenance Manual
28-22737 Fault Isolation Manual
28-22737 Illustrated Parts Catalog
28-23737 Schematic Diagram Manual
Section 9737 Maintenance Planning Document (MPD)
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For each
Airplane. Refer to Honeywell SB 1151932-24-61, Revision 5, dated Jan 22/2009 and Honeywell SB
1151934-24-62, revision 5, dated Jan 22/2009.
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:
None.
2. Parts and Materials Supplied by the Operator:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a) (b)KDA-E4FGround Fault Interrupt Relay6KDAG-X4F-001
(a) Refer to Honeywell SB 1151932-24-61, Revision 5, dated Jan 22/2009 and Honeywell SB 1151934-24-
62, Revision 5, dated Jan 22/2009 for supplier information.
(b) Discard the existing part.
3. Parts Modified and Reidentified:
The parts shown below are changed as shown in this service bulletin.
P91 Power Distribution Panel
Boeing Part Number
S281A601-xxxx (After
Modification)
Boeing Part Number
S281A601-xxxx (Be-
fore Modification)
-5004-1004
-5014-1014
-5022-1022
-5050-1050
-5058-1058
-5072-1072
-5092-1092
-5109-1109
-5112-1112
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P91 Power Distribution Panel
Boeing Part Number
S281A601-xxxx (After
Modification)
Boeing Part Number
S281A601-xxxx (Be-
fore Modification)
-5127-1127
-5164-1164
-5181-1181
-5217-1217
-5218-1218
-5219-1219
-5220-1220
-5221-1221
-5222-1222
-5223-1223
-5224-1224
-5225-1225
-5226-1226
-5227-1227
-5228-1228
-5230-1230
-5231-1231
-5232-1232
-5233-1233
-5234-1234
-5235-1235
-5236-1236
-5237-1237
-5238-1238
-5239-1239
-5240-1240
-7217-7701
-7221-7702
-7222-7703
-7223-7704
-7232-7705
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P91 Power Distribution Panel
Boeing Part Number
S281A601-xxxx (After
Modification)
Boeing Part Number
S281A601-xxxx (Be-
fore Modification)
-7226-7706
-7227-7707
-7233-7708
-7234-7709
-7235-7710
-7236-7711
-7004-7712
-7050-7713
-7127-7714
-7224-7715
P92 Power Distribution Panel
Boeing Part Number
S281A601-xxxx
Boeing Part Number
S281A601-xxxx
-6005-2005
-6009-2009
-6014-2014
-6015-2015
-6017-2017
-6115-2115
-6163-2163
-6169-2169
-6218-2218
-6224-2224
-6273-2273
-6277-2277
-6311-2311
-6327-2327
-6381-2381
-6383-2383
-6435-2435
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P92 Power Distribution Panel
Boeing Part Number
S281A601-xxxx
Boeing Part Number
S281A601-xxxx
-6436-2436
-6437-2437
-6438-2438
-6439-2439
-6440-2440
-6441-2441
-6442-2442
-6443-2443
-6444-2444
-6445-2445
-6446-2446
-6447-2447
-6448-2448
-6449-2449
-6450-2450
-6451-2451
-6453-2453
-6454-2454
-6455-2455
-6456-2456
-6457-2457
-6458-2458
-6462-2462
-6464-2464
-6466-2466
-6474-2474
-6532-2532
-8435-8701
-8437-8702
-8438-8703
-8440-8704
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P92 Power Distribution Panel
Boeing Part Number
S281A601-xxxx
Boeing Part Number
S281A601-xxxx
-8441-8705
-8442-8706
-8446-8707
-8450-8708
-8451-8709
-8456-8710
-8005-8711
-8015-8712
-8273-8713
-8327-8714
-8466-8715
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. These work instructions refer to procedures included on other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
B. WORK INSTRUCTIONS
Group 1, Configuration 1:
Part 1 - Airplanes that have not done this service bulletin.
1. Remove electrical power from the airplane. Put a DO-NOT -CLOSE tag on each opened circuit
breaker. Refer to 737-600/700/800/900 AMM 24-22-00 as an accepted procedure.
WARNING: REMOVE ELECTRICAL POWER BEFORE REMOVING OR INSTALLING POWER
DISTRIBUTION PANELS. HIGH VOLTAGES PRESENT CAN CAUSE INJURY TO
PERSONS.
2. Make sure the following fuel boost pump switches on the P5-2 fuel management control panel on
the P5 overhead panel are in the OFF position.
— FUEL PUMP TANK 1 - AFT
— FUEL PUMP TANK 1 - FWD
— FUEL PUMP CTR TANK - LEFT
— FUEL PUMP TANK 2 - AFT
— FUEL PUMP TANK 2 - FWD
— FUEL PUMP CTR TANK - RIGHT
3. Open the electronic equipment door 117A to get access to the electronic equipment compartment.
Make sure that all the power warning lights on the P91 and P92 power distribution panels are off.
4. Get access to the front of the P91 and P92 power distribution panels from the electronic equipment
compartment.
5. Open the P91 and P92 power distribution panel doors to get access to the circuit breakers and
relay installation locations.
6. Open the circuit breakers shown below and install DO-NOT -CLOSE tags:
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Circuit
Breaker
NameLocation (Pan-
el/Grid)
C00826FUEL BOOST PUMP TANK 1 AFTP92/D2
C00827FUEL BOOST PUMP TANK 1 FWDP91/D2
C00828FUEL BOOST PUMP TANK 2 AFTP91/D4
C00829FUEL BOOST PUMP TANK 2 FWDP92/D4
C00845FUEL BOOST PUMP CTR TANK LEFTP91/D6
C00846FUEL BOOST PUMP CTR TANK RIGHTP92/D6
7. Change the P91 and P92 power distribution panels as given in Figures 1 and 2.
8. Close the circuit breakers shown below and remove the DO-NOT -CLOSE tags:
Circuit
Breaker
NameLocation (Pan-
el/Grid)
C00826FUEL BOOST PUMP TANK 1 AFTP92/D2
C00827FUEL BOOST PUMP TANK 1 FWDP91/D2
C00828FUEL BOOST PUMP TANK 2 AFTP91/D4
C00829FUEL BOOST PUMP TANK 2 FWDP92/D4
C00845FUEL BOOST PUMP CTR TANK LEFTP91/D6
C00846FUEL BOOST PUMP CTR TANK RIGHTP92/D6
9. Restore electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as an
accepted procedure.
10. Do the following operational test of the GFI relay installation:
a. Make sure there is 500 LB (250 KG) of fuel or more in the number 1 tank.
b. Make sure there is 500 LB (250 KG) of fuel or more in the number 2 tank.
c. Make sure there is 1000 LB (500 KG) of fuel or more in the center fuel tank.
d. Get access to the flight compartment and the P91 and P92 panels.
e. Do the following test of the FUEL PUMP TANK 1 - AFT (GFI Relay R18 - P92 Panel)
installation:
(1) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - AFT switch to the ON position.
(2) Listen and make sure the FUEL PUMP TANK 1 - AFT pump operates.
(3) Make sure the FUEL PUMP TANK 1 - AFT low pressure light on the fuel management
panel goes off.
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CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 1 - AFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(4) Push the FUEL PUMP TANK 1 - AFT switch to the OFF position.
(5) Listen and make sure the FUEL PUMP TANK 1 - AFT pump does not operate.
(6) Make sure the FUEL PUMP TANK 1 - AFT low pressure light comes on.
(7) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - AFT switch to the ON position.
(8) Listen and make sure the FUEL PUMP TANK 1 - AFT pump operates.
(9) Make sure the FUEL PUMP TANK 1 - AFT low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 1 - AFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(10) Push the test button on the FUEL PUMP TANK 1 - AFT GFI relay (R18).
(11) Listen and make sure the FUEL PUMP TANK 1 - AFT pump does not operate.
(12) Make sure the FUEL PUMP TANK 1 - AFT low pressure light comes on.
(13) Make sure the RESET button on the FUEL PUMP TANK 1 - AFT GFI relay (R18) has
moved up, with a visible white band.
NOTE: The RESET button located at the top edge of the GFI relay (R18) moves up, to
expose a narrow white band when the GFI circuit turns off the R18 relay due to
a ground fault, or results when you push the TEST button located on the top
surface of the R18 relay.
(14) Push the FUEL PUMP TANK 1 - AFT switch to the OFF position.
(15) Push the RESET button on the FUEL PUMP TANK 1 - AFT GFI relay (R18). Make sure
the RESET button does not move up and the white band is not visible.
(16) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - AFT switch to the ON position.
(17) Listen and make sure the FUEL PUMP TANK 1 - AFT pump operates.
(18) Make sure the FUEL PUMP TANK 1 - AFT low pressure light on the fuel management
panel goes off.
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CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 1 - AFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(19) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - AFT switch to the OFF position.
(20) Listen and make sure the FUEL PUMP TANK 1 - AFT pump does not operate.
(21) Make sure the FUEL PUMP TANK 1 - AFT low pressure light comes on.
f. Do the following test of the FUEL PUMP TANK 1 - FWD (GFI Relay R19 - P91 Panel)
installation:
(1) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - FWD switch to the ON position.
(2) Listen and make sure the FUEL PUMP TANK 1 - FWD pump operates.
(3) Make sure the FUEL PUMP TANK 1 - FWD low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 1 - FWD SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(4) Push the FUEL PUMP TANK 1 - FWD switch to the OFF position.
(5) Listen and make sure the FUEL PUMP TANK 1 - FWD pump does not operate.
(6) Make sure the FUEL PUMP TANK 1 - FWD low pressure light comes on.
(7) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - FWD switch to the ON position.
(8) Listen and make sure the FUEL PUMP TANK 1 - FWD pump operates.
(9) Make sure the FUEL PUMP TANK 1 - FWD low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 1 - FWD SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(10) Push the test button on the FUEL PUMP TANK 1 - FWD GFI relay (R19).
(11) Listen and make sure the FUEL PUMP TANK 1 - FWD pump does not operate.
(12) Make sure the FUEL PUMP TANK 1 - FWD low pressure light comes on.
(13) Make sure the RESET button on the FUEL PUMP TANK 1 - FWD GFI relay (R19) has
moved up, with a visible white band.
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NOTE: The RESET button located at the top edge of the GFI relay (R19) moves up, to
expose a narrow white band when the GFI circuit turns off the R19 relay due to
a ground fault, or results when you push the TEST button located on the top
surface of the R19 relay.
(14) Push the FUEL PUMP TANK 1 - FWD switch to the OFF position.
(15) Push the RESET button on the FUEL PUMP TANK 1 - FWD GFI relay (R19). Make sure
the RESET button does not move up and the white band is not visible.
(16) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - FWD switch to the ON position.
(17) Listen and make sure the FUEL PUMP TANK 1 - FWD pump operates.
(18) Make sure the FUEL PUMP TANK 1 - FWD low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 1 - FWD SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(19) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 1 - FWD switch to the OFF position.
(20) Listen and make sure the FUEL PUMP TANK 1 - FWD pump does not operate.
(21) Make sure the FUEL PUMP TANK 1 - FWD low pressure light comes on.
g. Do the following test of the FUEL PUMP CTR TANK - LEFT (GFI Relay R54 - P91 Panel)
installation:
(1) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - LEFT switch to the ON position.
(2) Listen and make sure the FUEL PUMP CTR TANK - LEFT pump operates.
(3) Make sure the FUEL PUMP CTR TANK - LEFT low pressure light on the fuel management
panel goes OFF .
NOTE: Low pressure light will come on momentarily after pump switch is set to the ON
position.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
CTR TANK - LEFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(4) Push the FUEL PUMP CTR TANK - LEFT switch to the OFF position.
(5) Listen and make sure the FUEL PUMP CTR TANK - LEFT pump does not operate.
(6) Make sure the FUEL PUMP CTR TANK - LEFT low pressure light stays OFF .
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(7) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - LEFT switch to the ON position.
(8) Listen and make sure the FUEL PUMP CTR TANK - LEFT pump operates.
(9) Make sure the FUEL PUMP CTR TANK - LEFT low pressure light on the fuel management
panel goes off.
NOTE: Low pressure light will come on momentarily after pump switch is set to the ON
position.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
CTR TANK - LEFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART TEST FROM STEP (1)
ABOVE.
(10) Push the test button on the FUEL PUMP CTR TANK - LEFT GFI relay (R54).
(11) Listen and make sure the FUEL PUMP CTR TANK - LEFT pump does not operate.
(12) Make sure the FUEL PUMP CTR TANK - LEFT low pressure light comes on.
(13) Make sure the RESET button on the FUEL PUMP CTR TANK - LEFT GFI relay (R54)
has moved up, with a visible white band.
NOTE: The RESET button located at the top edge of the GFI relay (R54) moves up, to
expose a narrow white band when the GFI circuit turns off the R54 relay due to
a ground fault, or results when you push the TEST button located on the top
surface of the R54 relay.
(14) Push the FUEL PUMP CTR TANK - LEFT switch to the OFF position.
(15) Push the RESET button on the FUEL PUMP CTR TANK - LEFT GFI relay (R54). Make
sure the RESET button does not move up and the white band is not visible.
(16) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - LEFT switch to the ON position.
(17) Listen and make sure the FUEL PUMP CTR TANK - LEFT pump operates.
(18) Make sure the FUEL PUMP CTR TANK - LEFT low pressure light on the fuel management
panel goes off.
NOTE: Low pressure light will come on momentarily after pump switch is set to the ON
position.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
36 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 37

CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
CTR TANK - LEFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART TEST FROM STEP (1)
ABOVE.
(19) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - LEFT switch to the OFF position.
(20) Listen and make sure the FUEL PUMP CTR TANK - LEFT pump does not operate.
(21) Make sure the FUEL PUMP CTR TANK - LEFT low pressure light stays OFF .
h. Do the following test of the FUEL PUMP TANK 2 - AFT (GFI Relay R20 - P91 Panel)
installation:
(1) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - AFT switch to the ON position.
(2) Listen and make sure the FUEL PUMP TANK 2 - AFT pump operates.
(3) Make sure the FUEL PUMP TANK 2 - AFT low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 2 - AFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(4) Push the FUEL PUMP TANK 2 - AFT switch to the OFF position.
(5) Listen and make sure the FUEL PUMP TANK 2 - AFT pump does not operate.
(6) Make sure the FUEL PUMP TANK 2 - AFT low pressure light comes on.
(7) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - AFT switch to the ON position.
(8) Listen and make sure the FUEL PUMP TANK 2 - AFT pump operates.
(9) Make sure the FUEL PUMP TANK 2 - AFT low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 2 - AFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(10) Push the test button on the FUEL PUMP TANK 2 - AFT GFI relay (R20).
(11) Listen and make sure the FUEL PUMP TANK 2 - AFT pump does not operate.
(12) Make sure the FUEL PUMP TANK 2 - AFT low pressure light comes on.
(13) Make sure the RESET button on the FUEL PUMP TANK 2 - AFT GFI relay (R20) has
moved up, with a visible white band.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
37 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 38

NOTE: The RESET button located at the top edge of the GFI relay (R20) moves up, to
expose a narrow white band when the GFI circuit turns off the R20 relay due to
a ground fault, or results when you push the TEST button located on the top
surface of the R20 relay.
(14) Push the FUEL PUMP TANK 2 - AFT switch to the OFF position.
(15) Push the RESET button on the FUEL PUMP TANK 2 - AFT GFI relay (R20). Make sure
the RESET button does not move up and the white band is not visible.
(16) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - AFT switch to the ON position.
(17) Listen and make sure the FUEL PUMP TANK 2 - AFT pump operates.
(18) Make sure the FUEL PUMP TANK 2 - AFT low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 2 - AFT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(19) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - AFT switch to the OFF position.
(20) Listen and make sure the FUEL PUMP TANK 2 - AFT pump does not operate.
(21) Make sure the FUEL PUMP TANK 2 - AFT low pressure light comes on.
i. Do the following test of the FUEL PUMP TANK 2 - FWD (GFI Relay R21 - P92 Panel)
installation:
(1) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - FWD switch to the ON position.
(2) Listen and make sure the FUEL PUMP TANK 2 - FWD pump operates.
(3) Make sure the FUEL PUMP TANK 2 - FWD low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 2 - FWD SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(4) Push the FUEL PUMP TANK 2 - FWD switch to the OFF position.
(5) Listen and make sure the FUEL PUMP TANK 2 - FWD pump does not operate.
(6) Make sure the FUEL PUMP TANK 2 - FWD low pressure light comes on.
(7) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - FWD switch to the ON position.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
38 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 39

(8) Listen and make sure the FUEL PUMP TANK 2 - FWD pump operates.
(9) Make sure the FUEL PUMP TANK 2 - FWD low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 2 - FWD SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(10) Push the test button on the FUEL PUMP TANK 2 - FWD GFI relay (R21).
(11) Listen and make sure the FUEL PUMP TANK 2 - FWD pump does not operate.
(12) Make sure the FUEL PUMP TANK 2 - FWD low pressure light comes on.
(13) Make sure the RESET button on the FUEL PUMP TANK 2 - FWD GFI relay (R21) has
moved up, with a visible white band.
NOTE: The RESET button located at the top edge of the GFI relay (R21) moves up, to
expose a narrow white band when the GFI circuit turns off the R21 relay due to
a ground fault, or results when you push the TEST button located on the top
surface of the R21 relay.
(14) Push the FUEL PUMP TANK 2 - FWD switch to the OFF position.
(15) Push the RESET button on the FUEL PUMP TANK 2 - FWD GFI relay (R21). Make sure
the RESET button does not move up and the white band is not visible.
(16) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - FWD switch to the ON position.
(17) Listen and make sure the FUEL PUMP TANK 2 - FWD pump operates.
(18) Make sure the FUEL PUMP TANK 2 - FWD low pressure light on the fuel management
panel goes off.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
TANK 2 - FWD SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART FROM STEP (1) ABOVE.
(19) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
TANK 2 - FWD switch to the OFF position.
(20) Listen and make sure the FUEL PUMP TANK 2 - FWD pump does not operate.
(21) Make sure the FUEL PUMP TANK 2 - FWD low pressure light comes on.
j. Do the following test of the FUEL PUMP CTR TANK - RIGHT (GFI Relay R55 - P92 Panel)
installation:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
39 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 40

(1) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - RIGHT switch to the ON position.
(2) Listen and make sure the FUEL PUMP CTR TANK - RIGHT pump operates.
(3) Make sure the FUEL PUMP CTR TANK - RIGHT low pressure light on the fuel
management panel goes OFF .
NOTE: Low pressure light will come on momentarily after pump switch is set to the ON
position.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
CTR TANK - RIGHT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART TEST FROM STEP (1)
ABOVE.
(4) Push the FUEL PUMP CTR TANK - RIGHT switch to the OFF position.
(5) Listen and make sure the FUEL PUMP CTR TANK - RIGHT pump does not operate.
(6) Make sure the FUEL PUMP CTR TANK - RIGHT low pressure light stays OFF .
(7) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - RIGHT switch to the ON position.
(8) Listen and make sure the FUEL PUMP CTR TANK -RIGHT pump operates.
(9) Make sure the FUEL PUMP CTR TANK - RIGHT low pressure light on the fuel
management panel goes off.
NOTE: Low pressure light will come on momentarily after pump switch is set to the ON
position.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
CTR TANK - RIGHT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART TEST FROM STEP (1)
ABOVE.
(10) Push the test button on the FUEL PUMP CTR TANK - RIGHT GFI relay (R55).
(11) Listen and make sure the FUEL PUMP CTR TANK - RIGHT pump does not operate.
(12) Make sure the FUEL PUMP CTR TANK - RIGHT low pressure light comes on.
(13) Make sure the RESET button on the FUEL PUMP CTR TANK - RIGHT GFI relay (R55)
has moved up, with a visible white band.
NOTE: The RESET button located at the top edge of the GFI relay (R55) moves up, to
expose a narrow white band when the GFI circuit turns off the R55 relay due to
a ground fault, or results when you push the TEST button located on the top
surface of the R55 relay.
(14) Push the FUEL PUMP CTR TANK - RIGHT switch to the OFF position.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
40 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 41

(15) Push the RESET button on the FUEL PUMP CTR TANK - RIGHT GFI relay (R55). Make
sure the RESET button does not move up and the white band is not visible.
(16) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - RIGHT switch to the ON position.
(17) Listen and make sure the FUEL PUMP CTR TANK - RIGHT pump operates.
(18) Make sure the FUEL PUMP CTR TANK - RIGHT low pressure light on the fuel
management panel goes off.
NOTE: Low pressure light will come on momentarily after pump switch is set to the ON
position.
CAUTION: IF THE AMBER LOW PRESSURE LIGHT STAYS ON, SET THE FUEL PUMP
CTR TANK - RIGHT SWITCH ON THE P5 OVERHEAD PANEL TO THE OFF
POSITION. FIND THE CAUSE, THEN RESTART TEST FROM STEP (1)
ABOVE.
(19) In the flight compartment on the P5-2 fuel management panel, push the FUEL PUMP
CTR TANK - RIGHT switch to the OFF position.
(20) Listen and make sure the FUEL PUMP CTR TANK - RIGHT pump does not operate.
(21) Make sure the FUEL PUMP CTR TANK - RIGHT low pressure light stays OFF .
11. Close the P91 and P92 power distribution panel doors.
12. Close the electronic equipment door 117A used to get access to the electronic equipment
compartment.
13. Put the airplane back to a serviceable condition.
Group 1, Configuration 2:
Part 2 - Airplanes that have incorporated initial release of this service bulletin
1. Measure the resistance in accordance with supplier service bulletin Honeywell ASCa Inc.
1151932-24-61, Revision 5, dated Jan 22/2009 and 1151934-24-62, Revision 5, dated jan 22/2009.
NOTE: Supplier service bulletin Honeywell ASCa Inc. 1151932-24-61, Revision 5, dated Jan
22/2009 and 1151934-24-62, Revision 5, dated Jan 22/2009 were changed to add a
resistance check between the GFI relays mounting flange and a point on the panel cross
member of the P91 and P92 Panels.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1: May 28, 2009
41 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-28A1201
ALERT  ALERT
ELECTRICAL AND
ELECTRONICS
COMPARTMENT  ELECTRONIC EQUIPMENT
SEE  ACCESS DOOR, 117A
P91 POWER
DISTRIBUTION
PANEL
0000
DEND
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
ELECTRICAL AND ELECTRONICS COMPARMENT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
FIGURE 1: P91 POWER DISTRIBUTION PANEL CHANGE
(SHEET 1 OF 2)
Original Issue: February 19, 2007
Revision 1 May 28, 2009  BOEING PROPRIETARY -  737-28A1201
Copyright © Unpublished Work - See page 1 for details.  42 of 45

### Page 43

NOTESQTYPART NUMBERNAMETASKSTEP
Change the P91 panel as given in Honeywell
Service Bulletin 1151932-24-61,Revision 5,
dated Jan 22/2009. (a)
1S281A601-( )P91 Power Distri-
bution Panel
Change1
Part numbers for the P91 panel will change after installation of new GFI relays. Refer to Honeywell
Service Bulletin 1151932-24-61, Revision 5, dated Jan 22/2009 for identification instructions and
paragraph 2.E., Parts Modified and Re-identified of this service bulletin for part number information.
(a)
FIGURE 1: P91 POWER DISTRIBUTION PANEL CHANGE
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1 May 28, 2009
43 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-28A1201
ALERT  ALERT
ELECTRICAL AND
ELECTRONICS
COMPARTMENT  ELECTRONIC EQUIPMENT
SEE  ACCESS DOOR, 117A
P92 POWER
DISTRIBUTION
PANEL
R18
0000
FWD
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
ELECTRICAL AND ELECTRONICS COMPARMENT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
FIGURE 2: P92 POWER DISTRIBUTION PANEL CHANGE
(SHEET 1 OF 2)
Original Issue: February 19, 2007
Revision 1 May 28, 2009  737-28A1201
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  44 of 45

### Page 45

NOTESQTYPART NUMBERNAMETASKSTEP
Change the P92 panel as given in Honeywell
Service Bulletin 1151934-24-62, Revision 5,
dated Jan 22/2009.
1S281A601-( )P92 Power Distribu-
tion Panel
Change1
Part numbers for the P92 panels will change after installation of new GFI relays. Refer to Honeywell
Service Bulletin 1151934-24-62, Revision 5, dated Jan 22/2009 for identification instructions and
paragraph 2.E., Parts Modified and Re-identified of this service bulletin for part number information.
(a)
FIGURE 2: P92 POWER DISTRIBUTION PANEL CHANGE
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: February 19, 2007
737-28A1201Revision 1 May 28, 2009
45 of 45
BOEING SERVICE BULLETIN 737-28A1201
ALERTALERT

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