### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 1 of 45 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 2 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 3 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 4 of 45 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 5 of 45• 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, 2007 Original Issue: May 28, 2009 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 6 of 45 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 7 of 45Measure 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 Hours**  **Total Task Hours** 3.50 3.50
**MATERIAL INFORMATION** Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 8 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 9 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 10 of 45 **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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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 **Group Variable Number**  1 YA001 - YA099 1 YA101 - YA199

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 11 of 45**Group Variable Number**  1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 12 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 13 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 14 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 15 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 16 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 17 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 18 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Group**  **Variable Number** 1 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 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 737-28A1201 Revision 1: May 28, 2009 19 of 45 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 20 of 45 **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 Zone**  **Model** 123, 124 737-600, 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. **NO TE:**  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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 21 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access (a) (a) (a) Change 0.50 0.50 1 Close Access 2.50 2.50 1 Test 3.50 3.50 TOTAL 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 + 0.94 737-600 + 208 + 0.94 737-700/700C + 97 + 0.94 737-800 + 37 + 0.94 737-900
None. **I. Electrical Load Data** 1. Direct Current (DC) Loads None. 2. Alternating Current (AC) Loads

**Bus Phase**  **Volt-Ampere- Reactive**  **(VARs) Watts**  **Airplanes**

115V AC Transfer Bus No. 1 C - 0.90 - 1.04 737-600/700/700C/800/900

115V AC Transfer Bus No. 2 C - 0.90 - 1.04 737-600/700/700C/800/900

3. Type Continuous

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 22 of 45 **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. **NO TE:**  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-Section** 

**Publication** 28-22 737 Maintenance Manual 28-22 737 Fault Isolation Manual 28-22 737 Illustrated Parts Catalog 28-23 737 Schematic Diagram Manual Section 9 737 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 23 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 24 of 45 **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:

**Notes Existing Part Number**  **Name QTY**  **Part Number / Specification**  (a) (b) KDA-E4F Ground Fault Interrupt Relay 6 KDAG-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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 25 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 26 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 27 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 28 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 29 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 30 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CA UTION:**  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. **NO TE:**  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:**  **P ar** **t 1 - Airplanes that ha ve not done this ser** **vice b ulletin.**  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. **W**

**ARNING:** 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 31 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT Circuit**  **Breaker Name**  **Location (Pan- el/Grid)**  C00826 FUEL BOOST PUMP TANK 1 AFT P92/D2 C00827 FUEL BOOST PUMP TANK 1 FWD P91/D2 C00828 FUEL BOOST PUMP TANK 2 AFT P91/D4 C00829 FUEL BOOST PUMP TANK 2 FWD P92/D4 C00845 FUEL BOOST PUMP CTR TANK LEFT P91/D6 C00846 FUEL BOOST PUMP CTR TANK RIGHT P92/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**  **Name Location (Pan-**  **el/Grid)** C00826 FUEL BOOST PUMP TANK 1 AFT P92/D2 C00827 FUEL BOOST PUMP TANK 1 FWD P91/D2 C00828 FUEL BOOST PUMP TANK 2 AFT P91/D4 C00829 FUEL BOOST PUMP TANK 2 FWD P92/D4 C00845 FUEL BOOST PUMP CTR TANK LEFT P91/D6 C00846 FUEL BOOST PUMP CTR TANK RIGHT P92/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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 32 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT CA** **UTION:** 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. **CA UTION:**  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. **NO TE:**  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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 33 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT CA** **UTION:** 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. **CA UTION:**  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. **CA UTION:**  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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 34 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT NO** **TE:** 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. **CA UTION:**  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. **NO TE:**  Low pressure light will come on momentarily after pump switch is set to the ON position. **CA UTION:**  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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1: May 28, 2009 35 of 45 **BOEING SERVICE BULLETIN 737-28A1201 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. **NO TE:**  Low pressure light will come on momentarily after pump switch is set to the ON position. **CA UTION:**  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. **NO TE:**  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. **NO TE:**  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 737-28A1201 Revision 1: May 28, 2009 36 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT CA** **UTION:** 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. **CA UTION:**  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. **CA UTION:**  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 737-28A1201 Revision 1: May 28, 2009 37 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT NO** **TE:** 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. **CA UTION:**  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. **CA UTION:**  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 737-28A1201 Revision 1: May 28, 2009 38 of 45 **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. **CA UTION:**  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. **NO TE:**  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. **CA UTION:**  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 737-28A1201 Revision 1: May 28, 2009 39 of 45 **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. **NO TE:**  Low pressure light will come on momentarily after pump switch is set to the ON position. **CA UTION:**  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. **NO TE:**  Low pressure light will come on momentarily after pump switch is set to the ON position. **CA UTION:**  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. **NO TE:**  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 737-28A1201 Revision 1: May 28, 2009 40 of 45 **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. **NO TE:**  Low pressure light will come on momentarily after pump switch is set to the ON position. **CA UTION:**  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: P** **ar t 2 - Airplanes that ha** **ve incorporated initial release of this ser vice b** **ulletin** 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. **NO TE:**  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 737-28A1201 Revision 1: May 28, 2009 41 of 45 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1 May 28, 2009 42 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** Change the P91 panel as given in Honeywell Service Bulletin 1151932-24-61,Revision 5, dated Jan 22/2009. (a) 1 S281A601-( ) P91 Power Distri- bution Panel Change 1

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 737-28A1201 Revision 1 May 28, 2009 43 of 45 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 19, 2007 737-28A1201 Revision 1 May 28, 2009 44 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** Change the P92 panel as given in Honeywell Service Bulletin 1151934-24-62, Revision 5, dated Jan 22/2009. 1 S281A601-( ) P92 Power Distribu- tion Panel Change 1

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 737-28A1201 Revision 1 May 28, 2009 45 of 45 **BOEING SERVICE BULLETIN 737-28A1201 ALERT**  **ALERT**