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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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,

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connection with this document unless provided in writing by Boeing.

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3.0
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BOEING SERVICE BULLETIN 737-28A1201

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BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ..................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 23

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 29

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 1: P91 POWER DISTRIBUTION PANEL CHANGE . . . . . . . . . . . . . . . . . . . . . . . 42

FIGURE 2: P92 POWER DISTRIBUTION PANEL CHANGE . . . . . . . . . . . . . . . . . . . . . . . 44

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

ALERT

Revision Transmittal Sheet 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 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

Original Issue: February 19, 2007

Revision 1: May 28, 2009

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Summary 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.

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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Revision 1: May 28, 2009 737-28A1201

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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

Total Task Hours Elapsed Hours

3.50 3.50

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

BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

737-600/700/700C/800/900 Airplanes Line Numbers 1 - 1980,

1982-2092, 2094-2209.

1 -

1 All applicable airplanes that have not done this service bulletin.

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

Variable Number Group

YA001 - YA099 1

YA101 - YA199 1

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Variable Number Group

YA201 - YA211 1

YA221 1

YA231 - YA242 1

YA251 - YA256 1

YA271 - YA272 1

YA291 1

YA301 - YA302 1

YA311 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA536 1

YA541 - YA552 1

YA571 - YA578 1

YA601 - YA615 1

YA621 - YA622 1

YA626 - YA631 1

YA635 - YA636 1

YA641 - YA642 1

YA645 - YA650 1

YA656 - YA659 1

YA666 - YA667 1

YA671 - YA672 1

YA681 - YA691 1

YA701 - YA710 1

YA721 - YA722 1

YA731 - YA734 1

YA751 - YA756 1

YA801 - YA803 1

YA809 1

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BOEING SERVICE BULLETIN 737-28A1201

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Variable Number Group

YA811 - YA814 1

YA831 - YA835 1

YA841 - YA862 1

YA881 - YA882 1

YA891 - YA892 1

YA961 - YA978 1

YB001 - YB006 1

YB101 - YB132 1

YB151 - YB153 1

YB156 - YB158 1

YB161 - YB164 1

YB171 - YB172 1

YB181 - YB184 1

YB201 - YB208 1

YB271 1

YB276 1

YB301 - YB310 1

YB371 - YB392 1

YB501 - YB502 1

YB521 - YB526 1

YB541 - YB544 1

YB551 1

YB561 - YB598 1

YB601 - YB632 1

YB651 1

YB656 1

YB671 1

YB851 - YB863 1

YB871 - YB874 1

YB881 - YB893 1

YB901 - YB903 1

YB911 1

YB961 - YB966 1

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BOEING SERVICE BULLETIN 737-28A1201

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Variable Number Group

YC001 - YC030 1

YC051 - YC083 1

YC091 - YC094 1

YC101 - YC104 1

YC111 - YC113 1

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC178 1

YC186 - YC189 1

YC201 - YC203 1

YC206 - YC207 1

YC301 - YC305 1

YC321 - YC387 1

YC391 - YC394 1

YC396 1

YC401 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC438 1

YC441 - YC448 1

YC451 - YC455 1

YC459 1

YC461 - YC467 1

YC471 - YC499 1

YC501 - YC526 1

YC571 - YC583 1

YC587 - YC589 1

YC591 - YC593 1

YC601 - YC655 1

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
Variable Number Group

YC681 - YC696 1

YC701 - YC715 1

YC720 - YC725 1

YC727 - YC748 1

YC751 - YC752 1

YC761 - YC770 1

YC781 - YC793 1

YC801 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 1

YC941 - YC951 1

YC971 - YC978 1

YC981 - YC983 1

YD001 - YD007 1

YD021 - YD025 1

YD041 - YD057 1

YD081 - YD084 1

YD101 - YD110 1

YD121 - YD126 1

YD151 - YD159 1

YD171 - YD172 1

YD201 - YD203 1

YD206 - YD209 1

YD216 - YD219 1

YD251 - YD254 1

YD256 - YD257 1

YD261 1

YD301 - YD334 1

YD391 1

YD401 - YD410 1

YD412 - YD414 1

YD481 - YD485 1

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Variable Number Group

YD491 - YD496 1

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

YD561 - YD564 1

YD571 - YD572 1

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE020 1

YE051 1

YE101 - YE109 1

YE151 - YE157 1

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE383 1

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG103 1

YG111 - YG112 1

YG116 1

YG201 - YG205 1

YG211 - YG214 1

YG251 1

YG501 - YG509 1

YG601 - YG602 1

YJ001 - YJ006 1

YJ011 - YJ013 1

YJ021 1

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Variable Number Group

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ558 1

YJ591 - YJ594 1

YJ631 - YJ632 1

YJ671 - YJ686 1

YJ690 - YJ694 1

YJ801 - YJ867 1

YJ871 1

YJ901 - YJ902 1

YJ911 - YJ928 1

YJ931 - YJ936 1

YJ941 - YJ949 1

YK001 - YK007 1

YK101 - YK104 1

YK111 - YK112 1

YK121 - YK122 1

YK131 - YK132 1

YK136 - YK137 1

YK141 - YK142 1

YK146 - YK147 1

YK151 - YK154 1

YK161 - YK164 1

YK301 - YK307 1

YK321 - YK334 1

YK361 - YK369 1

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK447 1

YK456 - YK460 1

YK476 1

YK480 - YK484 1

YK511 - YK514 1

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
Variable Number Group

YK551 - YK565 1

YK571 1

YK576 - YK577 1

YK580 - YK582 1

YK601 - YK602 1

YK606 1

YK611 - YK614 1

YK621 - YK623 1

YK631 - YK632 1

YK641 - YK642 1

YK651 - YK655 1

YK701 - YK707 1

YK716 1

YK721 - YK731 1

YK791 - YK792 1

YK796 1

YK801 - YK841 1

YK901 - YK907 1

YK921 1

YK941 - YK945 1

YK961 - YK965 1

YK981 - YK982 1

YL001 - YL005 1

YL011 - YL015 1

YL051 - YL052 1

YL056 - YL057 1

YL061 1

YL201 - YL202 1

YL271 - YL272 1

YL301 - YL303 1

YL311 1

YL421 1

YL461 - YL466 1

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
Variable Number Group

YM101 - YM103 1

YM201 - YM222 1

YM251 - YM299 1

YM301 - YM318 1

YM471 1

YM481 - YM484 1

YM501 - YM512 1

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM591 - YM593 1

YM631 - YM634 1

YM641 1

YN001 - YN009 1

YN021 1

YN061 1

YN071 - YN075 1

YN101 - YN110 1

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.

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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

Model Zone

737-600, 737-700, 737-700C, 123, 124

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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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
Task Number of Persons Task-Hours Elapsed Hours

Open Access 1 0.50 0.50

Change (a) (a) (a)

Close Access 1 0.50 0.50

Test 1 2.50 2.50

TOTAL FOR EACH AIRPLANE 3.50 3.50

(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

737-600 + 0.94 + 259

737-700/700C + 0.94 + 208

737-800 + 0.94 + 97

737-900 + 0.94 + 37

None.

I. Electrical Load Data

1. Direct Current (DC) Loads

None.

2. Alternating Current (AC) Loads

Volt-Ampere- Phase Bus

Reactive

(VARs)

Airplanes Watts

115V AC Transfer Bus No.

1

737-600/700/700C/800/900 - 1.04 - 0.90 C

115V AC Transfer Bus No.

2

737-600/700/700C/800/900 - 1.04 - 0.90 C

3. Type

Continuous

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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

Publication Chapter-Section

737 Maintenance Manual 28-22

737 Fault Isolation Manual 28-22

737 Illustrated Parts Catalog 28-22

737 Schematic Diagram Manual 28-23

737 Maintenance Planning Document (MPD) Section 9

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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ALERT ALERT
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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT

BLANK PAGE
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:

Part Number / QTY Name Existing Part Number Notes

Specification

KDAG-X4F-001 6 Ground Fault Interrupt Relay KDA-E4F (a) (b)

(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 (Before Modification)

-1004 -5004

-1014 -5014

-1022 -5022

-1050 -5050

-1058 -5058

-1072 -5072

-1092 -5092

-1109 -5109

-1112 -5112

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
P91 Power Distribution Panel

Boeing Part Number

S281A601-xxxx (After

Modification)

Boeing Part Number

S281A601-xxxx (Before Modification)

-1127 -5127

-1164 -5164

-1181 -5181

-1217 -5217

-1218 -5218

-1219 -5219

-1220 -5220

-1221 -5221

-1222 -5222

-1223 -5223

-1224 -5224

-1225 -5225

-1226 -5226

-1227 -5227

-1228 -5228

-1230 -5230

-1231 -5231

-1232 -5232

-1233 -5233

-1234 -5234

-1235 -5235

-1236 -5236

-1237 -5237

-1238 -5238

-1239 -5239

-1240 -5240

-7701 -7217

-7702 -7221

-7703 -7222

-7704 -7223

-7705 -7232

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
P91 Power Distribution Panel

Boeing Part Number

S281A601-xxxx (After

Modification)

Boeing Part Number

S281A601-xxxx (Before Modification)

-7706 -7226

-7707 -7227

-7708 -7233

-7709 -7234

-7710 -7235

-7711 -7236

-7712 -7004

-7713 -7050

-7714 -7127

-7715 -7224

P92 Power Distribution Panel

Boeing Part Number

S281A601-xxxx

Boeing Part Number

S281A601-xxxx

-2005 -6005

-2009 -6009

-2014 -6014

-2015 -6015

-2017 -6017

-2115 -6115

-2163 -6163

-2169 -6169

-2218 -6218

-2224 -6224

-2273 -6273

-2277 -6277

-2311 -6311

-2327 -6327

-2381 -6381

-2383 -6383

-2435 -6435

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ALERT ALERT
P92 Power Distribution Panel

Boeing Part Number

S281A601-xxxx

Boeing Part Number

S281A601-xxxx

-2436 -6436

-2437 -6437

-2438 -6438

-2439 -6439

-2440 -6440

-2441 -6441

-2442 -6442

-2443 -6443

-2444 -6444

-2445 -6445

-2446 -6446

-2447 -6447

-2448 -6448

-2449 -6449

-2450 -6450

-2451 -6451

-2453 -6453

-2454 -6454

-2455 -6455

-2456 -6456

-2457 -6457

-2458 -6458

-2462 -6462

-2464 -6464

-2466 -6466

-2474 -6474

-2532 -6532

-8701 -8435

-8702 -8437

-8703 -8438

-8704 -8440

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ALERT ALERT
P92 Power Distribution Panel

Boeing Part Number

S281A601-xxxx

Boeing Part Number

S281A601-xxxx

-8705 -8441

-8706 -8442

-8707 -8446

-8708 -8450

-8709 -8451

-8710 -8456

-8711 -8005

-8712 -8015

-8713 -8273

-8714 -8327

-8715 -8466

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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ALERT ALERT
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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT

BLANK PAGE
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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ALERT ALERT
Circuit

Breaker

Location (Pan- Name

el/Grid)

P92/D2 FUEL BOOST PUMP TANK 1 AFT C00826

P91/D2 FUEL BOOST PUMP TANK 1 FWD C00827

P91/D4 FUEL BOOST PUMP TANK 2 AFT C00828

P92/D4 FUEL BOOST PUMP TANK 2 FWD C00829

P91/D6 FUEL BOOST PUMP CTR TANK LEFT C00845

P92/D6 FUEL BOOST PUMP CTR TANK RIGHT C00846

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

Location (Pan- Name

el/Grid)

P92/D2 FUEL BOOST PUMP TANK 1 AFT C00826

P91/D2 FUEL BOOST PUMP TANK 1 FWD C00827

P91/D4 FUEL BOOST PUMP TANK 2 AFT C00828

P92/D4 FUEL BOOST PUMP TANK 2 FWD C00829

P91/D6 FUEL BOOST PUMP CTR TANK LEFT C00845

P92/D6 FUEL BOOST PUMP CTR TANK RIGHT C00846

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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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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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ALERT ALERT
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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ALERT ALERT
(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.

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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.

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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.

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
(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:

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
(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.

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
(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.

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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)

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
STEP TASK NAME PART NUMBER QTY NOTES

Change the P91 panel as given in Honeywell

Service Bulletin 1151932-24-61,Revision 5,

dated Jan 22/2009. (a)

P91 Power Distri- S281A601-( ) 1

bution Panel

1 Change

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)

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
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)

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT
STEP TASK NAME PART NUMBER QTY NOTES

Change the P92 panel as given in Honeywell

Service Bulletin 1151934-24-62, Revision 5,

dated Jan 22/2009.

P92 Power Distribu- S281A601-( ) 1

tion Panel

1 Change

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)

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BOEING SERVICE BULLETIN 737-28A1201

ALERT ALERT