### Commercial Airplanes 

# 737 Service Bulletin ALERT Number: 737-28A1212 Original Issue: July 23, 2009 Revision 2: October 18, 2012 ATA System: 2822 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 300-774). 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 © 2009 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, DreamlinerTM, 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 Boeing liveries 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 is a trademark of Boeing Management Company.

Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 1 of 123 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 2 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 42 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 42 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 42 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 49 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 52 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 FIGURE 1: M181, M182, M183 RELAY MODULE ASSEMBLY - REPLACEMENT [Group 1, 8]. . . . 58 FIGURE 2: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 2, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59 FIGURE 3: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 3, 10-13, Configuration 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61 FIGURE 4: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 4, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 FIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 5, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 FIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 6, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 3 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 7, 9, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76 FIGURE 8: W0044 WIRE BUNDLE - LOCATION [Group 2-3, 6-7, 9-13, Configuration 1]. . . . . . . 82 FIGURE 9: WIRE BUNDLE W0044 - WIRING CHANGES [Group 2, Configuration 1]. . . . . . . . . 83 FIGURE 10: WIRE BUNDLE W0044 - WIRING CHANGES [Group 3, 12, Configuration 1]. . . . . . . 85 FIGURE 11: WIRE BUNDLE W0044 - WIRING CHANGES [Group 6-7, 9, Configuration 1]. . . . . . . 87 FIGURE 12: WIRE BUNDLE W0044 - WIRING CHANGES [Group 10, Configuration 1]. . . . . . . . . 88 FIGURE 13: WIRE BUNDLE W0044 - WIRING CHANGES [Group 11, 13, Configuration 1]. . . . . . . 89 FIGURE 14: FUEL BOOST PUMP CONNECTOR - WIRE LOCATION [Group 8]. . . . . . . . . . . . 91 FIGURE 15: FUEL BOOST PUMP GROUNDS - WIRE LOCATION [Group 8]. . . . . . . . . . . . . . 92 FIGURE 16: FUEL BOOST PUMP CONNECTOR - WIRING CHANGES [Group 8] . . . . . . . . . . . 93 FIGURE 17: FUEL BOOST PUMP CONNECTOR - WIRE LOCATION [Group 8]. . . . . . . . . . . . 94 FIGURE 18: FUEL BOOST PUMP GROUNDS - WIRE LOCATION [Group 8]. . . . . . . . . . . . . . 95 FIGURE 19: FUEL BOOST PUMP CONNECTOR - WIRING CHANGES [Group 8] . . . . . . . . . . . 96 FIGURE 20: FUEL BOOST PUMP CONTROL GROUND FAULT INTERRUPTER (GFI) CONTROL RELAY - REFERENCE [Group 2-7, 9-13, Configuration 1]. . . . . . . . . . . . . . . . . . . . . . 97 FIGURE 21: WIRE BUNDLE W0044 - WIRING CHANGES [Group 1, 8]. . . . . . . . . . . . . . . . . 98 FIGURE 22: P6-2 RELAY PANEL - GROUND STUDS AND BONDING JUMPER - INSTALLATION [Group 2-4; Group 5, Configuration 1-2; Group 6, Configuration 1-2; Group 7, Configuration 1-2; Group 9, Configuration 1-2; Group 10-13]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99 FIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN [Group 5, Configuration 2-3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103 FIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN [Group 6, Configuration 2-3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 108 FIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN [Group 7, Configuration 2-3; Group 9, Configuration 2-3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113 Appendix A: ELECTRICAL BONDING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 118

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 4 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT

### Commercial Airplanes 

# 737 Service Bulletin ALERT Revision Transmittal Sheet Number: 737-28A1212 Original Issue: July 23, 2009 Revision 2: October 18, 2012 ATA System: 2822 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) Airworthiness Directive AD 2011-12-09 is related to this service bulletin. More work is necessary for Group 5, 6, 7 and 9 airplanes that have been changed in accordance with the Original Issue or Revision 1 of this service bulletin:- – For airplanes that have incorporated the Original Issue of this service bulletin, but not Revision 1, it is necessary to change the position of two Ground Fault Interrupt (GFI) relays, on the P6-2 relay panel, install a bonding jumper between the P6-2 relay panel and P6 Load Control Center structure, do a bonding check of the GFI relays and do a GFI operational test. This work is identified as Configuration 2 for these groups. – For airplanes that have incorporated Revision 1 of this service bulletin, it is necessary to change the position of two GFI relays on the P6-2 relay panel, do a bonding check and a GFI operational test, for related fuel boost pumps. This work is identified as Configuration 3 for these groups. More work is necessary for Group 2-4 and Group 10-13 airplanes that have been changed in accordance with the Original Issue of this service bulletin. It is necessary to install a bonding jumper between the P6-2 relay panel and P6 Load Control Center structure, then do a GFI operational test of the fuel boost pumps. This work is identified as Configuration 2 for these groups. No more work is necessary for Group 2-4 and Group 10-13 airplanes that have been changed in accordance with Revision 1 of this service bulletin. The Alternative Method Of Compliance (AMOC) to the requirements of paragraph (g), (h), (i), (j) and (k) of AD 2011-12-09, for Revision 2 of this bulletin, does not apply to Group 1 and 8 airplanes (line numbers 1 thru 291), operators should contact the Boeing company for more instructions to do this change.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 5 of 123REASON FOR REVISION This revision is sent to update the installation of new GFI relays because the GFI system might not function correctly after their installation on Groups 5, 6, 7 and 9 airplanes. Boeing received a report from one operator that told of incorrect operation of new 9524G-10674 GFI relays. A subsequent investigation and test found that Electromagnetic Interference (EMI), between the new 9524G-10674 relays and adjacent KCG-X4L-001 relays could cause problems with the function of new relays and thus the operation of GFI system. The instructions have therefore been updated to change the position of the GFI relays. Other groups are not affected by this problem because of differences in the P6-2 relay panel layout. This revision is a final solution to the problem described in 737-28A1212 IN 02 and requires no new parts to be supplied or kit changes. Operators of airplanes in Groups 5, 6 and 7 can now continue to incorporate this service bulletin at this revision. In addition, instructions to change airplane line numbers 1-291, in Groups 1 and 8, are removed. Operators with these airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change. As a result of Boeing checks on the Group Configuration, the airplanes that follow are moved between groups of the service bulletin effectivity. 1. Airplanes line numbers 263 thru 267 and 269 thru 291 are moved from Group 2 to Group 1. 2. Airplanes variable numbers PQ951, PR077-PR080 and PT681-PT685 are moved from Group 4 to Group 5. 3. Airplanes variable numbers PW511-PW512 are moved from Group 6 to Group 7. 4. Airplane variable number PW702, and thus Group 9, is changed to be applicable to Figure 7 and not Figure 3. These sections are changed: 1. In Summary, Concurrent Requirements: Removed data for withdrawn Groups 1 and 8. Added none. 2. In Summary, Background: Added reference to Boeing Fleet Team Digest 737 FTD 28-04005 and Boeing Service Letter 737-SL-28-070. 3. In Summary, Action: Added Part descriptions, new group configurations and Part 3 for withdrawn Groups 1 and 8. Added more work in Parts 1, 2 and new Part 4. Added Part 1, Step 6. 4. In Summary, Compliance: Added FAA AD 2011-12-09. Added statement for withdrawn Groups 1 and 8. Updated statement for other groups based on more work required and revision. 5. In Summary, Illustration: Added more work for Configuration 2 and 3 and updated Configuration 1 description. 6. In Paragraph 1.A., Effectivity: Added Configuration 3 for Groups 5, 6, 7 and 9. Updated the Group Configuration table descriptions. Corrected the Group of airplanes given above. Removed Configurations for Groups 1 and 8. 7. In Paragraph 1.B., Concurrent Requirements: Removed data for withdrawn Groups 1 and 8. Added none.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 6 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT8. In Paragraph 1.C., Reason: Added reference to Boeing Fleet Team Digest 737 FTD 28-04005 and Boeing Service Letter 737-SL-28-070. 9. In Paragraph 1.D., Description: Added Part descriptions, new group configurations and Part 3 for withdrawn Groups 1 and 8. Added more work in Parts 1, 2 and new Part 4. Added Part 1, Step 6. 10. In Paragraph 1.E., Compliance: Added FAA AD 2011-12-09. Added statement for withdrawn Groups 1 and 8. Updated statement for other groups based on more work required and revision. 11. In Paragraph 1.F., Approval: Added Alternative Method of Compliance statement with reference to FAA Airworthiness Directive AD 2011-12-09. 12. In Paragraph 1.G., Manpower: Added Part descriptions, new group configurations and Part 3 for withdrawn Groups 1 and 8. Added Figures and estimates for more work in Parts 1, 2 and new Part 4. Changed Group 9 applicability. 13. In Paragraph 1.K., Publications Affected: Added Equipment List to Wiring Diagram Manual sections. 14. In Paragraph 1.I., Electrical Load Data: Added note for withdrawn Groups 1 and 8. Applied Group Configurations. Corrected DC Load Table - added Group 13 and moved Group 9. 15. Added Paragraph 1.M., Software Accomplishment Summary: New service bulletin section - not affected. 16. In Paragraph 1.J., References: Updated to include items added at Revision 2 and not added at Revision 1. 17. In Paragraph 2.A., Material - Price and Availability: Updated tables and new Pricing and ROLT. Separated tables for new group configurations and Kit applicability. Added note for withdrawn Groups 1 and 8. 18. In Paragraph 2.C.1., Kits/Parts: Added note for withdrawn Groups 1 and 8. Applied new group configurations to tables. Added missing footnote (a) reference and note for Configuration 3. 19. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added note for withdrawn Groups 1 and 8 and removed related part numbers from tables. Added new table for consumable materials, added at Revision 1. Separated part tables by Group / Configuration and added existing parts column, with instructions. Changed parts applicable to Group 9. 20. In .Paragraph 2.C.3., Parts Modified and Reidentified: Added note for withdrawn Groups 1 and 8 and removed related table. Added note for other groups. 21. In Paragraph 3.B., Work Instructions: Added note for withdrawn Groups 1 and 8. 22. In Paragraph 3.B., Work Instructions, Part 1: Updated title. Removed Groups 1 and 8 and renumbered all steps. Moved Group 9 applicability. Added more work in Steps 10 thru 12. Corrected Steps 5, 18 and 21. Added Step 25. 23. In Paragraph 3.B., Work Instructions, Part 2: Updated title and Step 5. Added more work for Configuration 2, applicable to Groups 5-7 and 9 in Step 4. Added test detail in Step 6. 24. In Paragraph 3.B., Work Instructions, Part 3: Deleted - applicable to withdrawn Groups 1 and 8. 25. Added Paragraph 3.B., Work Instructions, Part 4: To give Configuration 3 work instructions for Groups 5-7 and 9.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 7 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT26. Figure 1: Deleted - applicable to withdrawn Groups 1 and 8. 27. In Figures 2, 3 and 4: Updated titles, Alodine naming and related more data and cleaning step quantity to agree with other figures. 28. In Figure 3: Removed Group 9 applicability. 29. In Figures 5, 6 and 7: Changed Illustrations and Step Tables to add more work for Configuration 1 and update formats. Added Steps 3, 4, 8, 9, 10 and 13 and footnotes (d) thru (i). Updated titles, cleaning step quantity, Alodine naming and related more data. 30. In Figure 7: Added Group 9 applicability. 31. In Figure 8: Updated title. 32. Figures 14 thru 19: Deleted - applicable to withdrawn Group 8. 33. Figure 21: Deleted - applicable to withdrawn Groups 1 and 8. 34. In Figure 22: Updated title, Alodine naming, and Applicability. Corrected Sheet 3 illustration. 35. Added Figures 23, 24 and 25: To give more work for Groups 5-7 and 9, Configuration 2 and 3. 36. In Appendix A: Added titles for Figure 1 and Figure 2. Corrected Paragraphs 1.a.(3), 1.a.(4), 2.a.(4), 2.a.(7) and 5.a.(1).(a). The data given in Information Notices 737-28A1212 IN 01 and 737-28A1212 IN 02 is included in this revision, as applicable. 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 July 23, 2009 Original Issue: August 27, 2010 Revision 1: October 18, 2012 Revision 2:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 8 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT

### Commercial Airplanes 

# 737 Service Bulletin ALERT Summary Number: 737-28A1212 Original Issue: July 23, 2009 Revision 2: October 18, 2012 ATA System: 2822 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 None. BACKGROUND This service bulletin gives the instructions to replace the power control relays for the fuel boost pumps. The relays are located in the P6 circuit breaker panel in the flight compartment. The new relays include a Ground Fault Interrupt (GFI) feature. The GFI relay feature will protect the fuel pumps from damage caused by electrical arcing because the electrical power will be removed from the pump if a ground fault is detected. 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 service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". This change affects section 9 of the Maintenance Planning Data (MPD) Document. The Airworthiness Limitations (AWL) "28-AWL-23" (737-100/200/200C airplanes) and "28-AWL-22" (737-300/400/500 airplanes) are related to this service bulletin. Boeing Fleet Team Digest 737 FTD 28-04005 is related to this service bulletin. Boeing Service Letter 737-SL-28-070 is related to this service bulletin. ACTION (PRR 35440-10RS) Group 2-7, 9-13, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT 1. Get access to the flight compartment.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 9 of 1232. At the P6 Load Control Center install two ground studs and a ground bonding jumper. 3. Measure the electrical bonding between the P6-2 relay panel and P6 Load Control Center structure. 4. Replace relays on the P6-2 relay panel with new Ground Fault Interrupt (GFI) relays as follows:

a.Group 2, 4, Configuration 1: Replace six relays. b.Group 3, 10-13, Configuration 1: Replace eight relays.

c.Group 5, Configuration 1: Replace six relays, with R18 and R19 turned 180 degrees. d.Group 6-7, 9, Configuration 1: Replace eight relays, with R146 and R147 turned 180 degrees. 5. Measure the electrical bonding between each of the new GFI relays and the P6-2 relay panel and repair the bond if necessary. 6.Group 2-3, 6-7, 9-13, Configuration 1: Change the W0044 wire bundle. 7. Do a Ground Fault Interrupter (GFI) - Operational Test of the GFI relay installation for the fuel boost pumps. Group 2-7, 9-13, Configuration 2: PART 2 - MORE WORK - GROUND STUDS AND BONDING JUMPER INSTALLATION AND GFI RELAY POSITION CHANGE 1. Get access to the flight compartment. 2. At the P6 Load Control Center install two ground studs and a ground bonding jumper. 3. Measure the electrical bonding between the P6-2 relay panel and P6 Load Control Center structure.
4.Group 5-7, 9, Configuration 2: Remove and keep two GFI relays on the P6-2 relay panel, turn the relay sockets 180 degrees, then install the kept relays in the new position. 5. Do a Ground Fault Interrupter (GFI) - Operational Test of the GFI relay installation for the fuel boost pumps. Group 1, 8: PART 3 - THIS PART IS DELETED 1. Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 10 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 5-7, 9, Configuration 3: PART 4 - MORE WORK - GFI RELAY POSITION CHANGE 1. Get access to the flight compartment. 2. Remove and keep two GFI relays on the P6-2 relay panel, turn the relay sockets 180 degrees, then install the kept relays in the new position. 3. Measure the electrical bonding between each of the changed GFI relays and the P6-2 relay panel and repair the bond if necessary. 4. Do a Ground Fault Interrupter (GFI) - Operational Test of the GFI relay installation for the related fuel boost pumps. EFFECTIVITY 737-100/-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-12-09 is related to this service bulletin. Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions within 60 months after the effective date of Revision 01 of this service bulletin. Group 2-4, 10-13: Boeing recommends that operators make the changes shown in this service bulletin within 60 months after the effective date of Revision 01 of this service bulletin. Group 5-7, 9: Boeing recommends that operators make the changes shown in this service bulletin within 60 months after the effective date of Revision 02 of this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 11 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 12 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT

### Commercial Airplanes 

# 737 Service Bulletin ALERT Number: 737-28A1212 Original Issue: July 23, 2009 Revision 2: October 18, 2012 ATA System: 2822 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 D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. Refer to PRR35440-10RS for data about this change.
DESCRIPTION CONFIGURATION GROUP 737-100/200/200C Airplanes, line numbers 42 thru 291. Operators should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. - 1

737-100/200/200C/300/400 Airplanes, line numbers 292 thru 3132, that require replacement of 6 Relays, without spacers, on the P6-2 panel, and changes to the W0044 Wire Bundle. - 2

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 13 of 123DESCRIPTION CONFIGURATION GROUP 737-200 Airplanes, line numbers 292 thru 985, delivered equipped for Auxiliary Fuel Tanks, that require replacement of 8 Relays, without spacers, on the P6-2 panel and changes to the W0044 Wire Bundle. - 3

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
737-200/300/400/500 Airplanes, line numbers 1494 thru 3132, that require replacement of 6 Relays, with spacers, on the P6-2 panel. - 4
Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
737-300/400/500 Airplanes, line numbers 1663 thru 3132, that require replacement of 2 Relays without spacers and 4 Relays with spacers, on the P6-2 panel. - 5

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
Airplanes that have accomplished Revision 1 of this service bulletin. 3 737-400 Airplanes, line numbers 1707 thru 3132, delivered equipped for Auxiliary Fuel Tanks, that require replacement of 4 Relays without spacers and 4 Relays with spacers, on the P6-2 panel, and changes to the W0044 Wire Bundle. - 6

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
Airplanes, equipped with Auxiliary Fuel Tanks, that have accomplished Revision 1 of this service bulletin. 3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 14 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTDESCRIPTION CONFIGURATION GROUP 737-400 Airplanes, line numbers 1687, 1697 and 2043, delivered equipped for Auxiliary Fuel Tanks, that require replacement of 2 Relays without spacers and 6 Relays with spacers, on the P6-2 panel, and changes to the W0044 Wire Bundle. - 7

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
Airplanes, equipped with Auxiliary Fuel Tanks, that have accomplished Revision 1 of this service bulletin. 3
737-100/200 Airplanes, line numbers 1 thru 41, that have different service bulletin effectivities. Operators should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. - 8

737-400 Airplane, line number 2432, delivered equipped for Auxiliary Fuel Tanks, that require replacement of 2 Relays without spacers and 6 Relays with spacers, on the P6-2 panel, and changes to the W0044 Wire Bundle. - 9

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
Airplanes, equipped with Auxiliary Fuel Tanks, that have accomplished Revision 1 of this service bulletin. 3
737-200 Airplane, line number 1585, delivered equipped for Auxiliary Fuel Tanks, that require replacement of 8 Relays, without spacers, on the P6-2 panel and different changes to the W0044 Wire Bundle. - 10

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 15 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTDESCRIPTION CONFIGURATION GROUP 737-300 Airplanes, line numbers 1124 thru 1385, delivered equipped for Auxiliary Fuel Tanks, that require replacement of 8 Relays, without spacers, on the P6-2 panel and different changes to the W0044 Wire Bundle. - 11

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
737-200 Airplanes, line numbers 458 thru 987, delivered with provisional wires for Auxiliary Tanks, that require replacement of 8 Relays (or 6 without auxiliary tanks), without spacers, on the P6-2 panel and changes to the W0044 Wire Bundle. - 12

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2
737-300 Airplanes, line numbers 1111 thru 3132, delivered with provisional wires for Auxiliary Tanks, that require replacement of 8 Relays (or 6 without auxiliary tanks), without spacers, on the P6-2 panel and different changes to the W0044 Wire Bundle. - 13

Airplanes that have not accomplished this service bulletin. 1 Airplanes that have accomplished the Original Issue, but not Revision 1 of this service bulletin. 2

Airplane Models: 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Group Variable Number8 PA001 - PA014 1 PA015 - PA022 8 PA099 1 PA231 - PA232 1 PC001 - PC005 8 PG001 - PG017 1 PG018 - PG075 8 PG199

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 16 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number8 PG201 - PG202 1 PG203 - PG230 1 PG251 - PG255 8 PG271 - PG273 1 PG274 - PG279 8 PG301 - PG302 1 PG303 - PG314 8 PG331 1 PG332 1 PG351 - PG356 1 PG375 1 PG401 - PG403 1 PG431 - PG442 1 PG471 - PG475 1 PG501 - PG505 1 PG571 - PG583 2 PG584 - PG586 1 PG621 - PG630 1 PG651 - PG652 1 PG704 - PG705 2 PH001 2 PH011 - PH013 2 PH021 - PH024 1 PH701 - PH715 1 PH731 - PH732 1 PH741 - PH742 2 PH743 1 PJ001 - PJ002 2 PJ003 - PJ006 3 PJ007 - PJ009 1 PJ031 - PJ032 1 PJ071 - PJ072 1 PJ101 - PJ104

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 17 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PJ105 - PJ119 3 PJ201 - PJ219 4 PJ301 - PJ302 4 PJ551 - PJ561 4 PJ601 - PJ615 6 PJ811 5 PJ816 - PJ817 2 PK026 - PK029 2 PK041 - PK053 2 PK061 - PK067 3 PK068 - PK070 2 PK081 - PK082 2 PK091 - PK099 2 PK101 - PK103 2 PK111 - PK120 2 PK141 - PK146 2 PK201 - PK204 2 PK211 - PK223 2 PK231 - PK241 2 PK251 - PK256 12 PK257 2 PK258 2 PK271 - PK274 2 PK281 - PK289 2 PK291 2 PK301 - PK318 2 PK341 2 PK351 - PK355 3 PK356 - PK359 12 PK360 2 PK361 2 PK391 2 PK431 - PK433

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 18 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PK451 - PK452 2 PK461 - PK469 2 PK495 2 PK501 12 PK502 - PK504 2 PK511 - PK515 2 PK519 2 PK521 - PK528 2 PK541 - PK565 2 PK581 2 PK591 - PK599 2 PK601 - PK606 3 PK607 - PK610 2 PK611 - PK617 2 PK621 - PK637 2 PK641 - PK642 3 PK661 2 PK662 - PK666 2 PK671 - PK681 2 PK691 - PK697 2 PK711 - PK716 2 PK731 - PK765 2 PK771 - PK779 2 PK801 - PK804 2 PK819 - PK827 2 PK830 2 PK861 - PK863 12 PK871 - PK872 3 PK873 12 PK874 2 PK881 - PK884 2 PK901 - PK938 2 PK971 - PK974

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 19 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PL001 - PL028 2 PL061 2 PL081 2 PL101 - PL113 2 PL151 2 PL171 - PL172 2 PL201 - PL203 2 PL221 2 PL401 - PL408 3 PL409 - PL410 2 PL411 3 PL412 2 PL413 - PL417 12 PL421 2 PL441 2 PL451 - PL456 2 PL471 2 PL491 3 PL501 12 PL502 - PL503 3 PL504 - PL506 2 PL551 - PL562 2 PL581 3 PL601 - PL603 2 PL611 2 PL621 - PL626 3 PL631 - PL632 1 PL711 - PL712 1 PL716 2 PL717 - PL747 2 PL756 2 PL758 2 PL761 - PL770

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 20 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PL781 - PL788 2 PL793 1 PL801 - PL803 2 PM001 - PM006 2 PM016 - PM017 2 PM021 - PM023 2 PM051 - PM066 3 PM101 - PM107 12 PM108 - PM119 12 PM141 - PM142 2 PM171 2 PM181 2 PM251 - PM255 2 PM281 - PM283 2 PM381 - PM399 2 PM401 - PM417 2 PM541 - PM550 4 PM551 - PM564 3 PN001 - PN002 2 PN021 - PN043 2 PN081 - PN086 2 PN101 - PN117 2 PN131 - PN163 2 PN401 - PN420 2 PN431 - PN433 2 PN451 - PN456 2 PN471 - PN474 2 PN481 2 PN491 - PN493 2 PN501 4 PN502 2 PN511 4 PN512

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 21 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number10 PN521 2 PP001 - PP054 2 PP101 - PP169 2 PP181 - PP187 4 PP188 - PP199 2 PP201 - PP205 2 PP221 2 PP231 - PP243 2 PP281 - PP286 2 PP301 - PP305 2 PP351 - PP353 2 PP376 - PP384 2 PP391 - PP393 2 PP401 - PP440 11 PP471 - PP475 13 PP501 - PP520 2 PP521 - PP522 2 PP631 - PP634 2 PP651 - PP652 2 PP671 - PP689 11 PP690 - PP694 2 PP695 - PP699 2 PP701 - PP706 11 PP707 - PP716 2 PP717 - PP733 2 PP771 - PP779 2 PP801 - PP808 2 PP821 - PP827 2 PP831 - PP848 2 PP851 - PP852 2 PP861 - PP877 2 PP891 - PP899 2 PP901 - PP936

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 22 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PP946 - PP948 2 PP951 - PP952 2 PP961 - PP965 4 PP966 - PP967 2 PP981 - PP982 4 PP983 - PP990 2 PP991 4 PP993 2 PQ001 - PQ016 2 PQ026 - PQ041 2 PQ051 - PQ092 2 PQ101 - PQ199 2 PQ201 - PQ202 4 PQ221 - PQ230 2 PQ231 - PQ232 4 PQ233 - PQ237 2 PQ241 - PQ242 4 PQ243 4 PQ251 - PQ267 4 PQ281 - PQ299 4 PQ301 - PQ307 4 PQ331 - PQ332 4 PQ341 - PQ348 4 PQ361 - PQ373 4 PQ391 - PQ395 4 PQ401 - PQ418 4 PQ421 4 PQ431 - PQ438 4 PQ447 - PQ448 4 PQ451 4 PQ454 4 PQ471 - PQ475 4 PQ479 - PQ481

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 23 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number4 PQ486 - PQ487 4 PQ491 - PQ493 4 PQ771 - PQ772 4 PQ791 - PQ793 4 PQ801 - PQ805 5 PQ931 - PQ935 5 PQ951 4 PQ971 - PQ997 4 PR001 - PR017 4 PR021 - PR034 5 PR041 - PR045 5 PR061 - PR072 5 PR077 - PR082 4 PR091 - PR092 4 PR096 4 PR101 4 PR121 - PR122 4 PR131 - PR132 4 PR141 - PR143 4 PR161 - PR172 4 PR181 2 PS601 - PS631 2 PS636 - PS638 2 PS641 - PS644 4 PS651 - PS657 4 PS666 - PS669 4 PS691 - PS692 2 PS701 - PS706 2 PS751 - PS799 4 PS811 4 PS836 - PS837 2 PS841 - PS846 2 PS851 - PS852

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 24 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PS856 13 PS861 - PS863 13 PS866 - PS868 2 PS871 - PS874 2 PS896 - PS897 2 PS901 - PS941 13 PS956 - PS957 4 PS961 - PS963 4 PS971 - PS978 4 PT001 - PT015 4 PT021 - PT031 4 PT041 - PT064 4 PT101 - PT105 5 PT121 - PT138 4 PT146 - PT148 4 PT161 - PT170 5 PT181 - PT188 4 PT211 - PT220 5 PT295 4 PT301 - PT309 5 PT331 - PT360 4 PT381 - PT399 4 PT401 - PT438 4 PT501 - PT517 4 PT561 - PT565 4 PT581 - PT586 4 PT611 - PT621 4 PT641 - PT644 4 PT651 - PT656 4 PT671 - PT672 5 PT681 - PT685 4 PT701 - PT703 4 PT716 - PT717

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 25 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number4 PT721 - PT725 4 PT801 - PT834 4 PT851 - PT854 5 PT871 - PT886 4 PT901 - PT930 4 PT971 - PT973 4 PT981 - PT985 4 PT996 4 PU001 - PU025 4 PU301 4 PU311 - PU313 2 PV001 4 PV002 - PV055 4 PV201 - PV209 4 PV226 - PV229 5 PV231 - PV237 4 PV271 - PV272 5 PV281 - PV287 4 PV296 4 PV301 - PV302 5 PV351 4 PV356 - PV357 4 PW001 - PW054 4 PW061 - PW068 4 PW072 4 PW086 - PW088 4 PW091 - PW094 4 PW101 - PW102 4 PW106 4 PW111 - PW120 4 PW156 - PW157 4 PW161 - PW171 4 PW201 - PW252

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 26 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number4 PW261 - PW268 4 PW271 - PW276 4 PW278 4 PW281 - PW293 4 PW296 5 PW301 - PW327 4 PW401 - PW408 4 PW411 - PW418 4 PW421 - PW424 4 PW431 - PW435 5 PW441 - PW450 5 PW461 - PW467 5 PW501 - PW504 7 PW511 - PW512 6 PW513 - PW522 6 PW524 5 PW525 - PW529 6 PW530 4 PW531 - PW550 4 PW556 - PW557 5 PW561 - PW564 5 PW571 - PW576 4 PW591 - PW596 4 PW611 - PW622 4 PW631 - PW637 4 PW661 - PW662 4 PW681 - PW683 7 PW701 9 PW702 5 PW711 - PW717 4 PW741 - PW742 4 PW761 4 PW771

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 27 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number4 PW831 4 PW851 - PW856 1 PX071 1 PX701 1 PY001 - PY008 1 PY021 2 PY022 1 PY031 2 PY036 - PY037 2 PY046 - PY048 2 PY051 - PY053 2 PY056 - PY057 2 PY101 - PY103 2 PY111 - PY113 2 PY131 - PY135 2 PY141 - PY143 2 PY151 - PY154 2 PY156 - PY157 2 PY161 - PY162 2 PY166 2 PY191 2 PY201 2 PY221 - PY222 2 PY231 2 PY241 - PY244 2 PY270 - PY275 2 PY281 2 PY286 1 PY301 - PY304 1 PY321 - PY323 1 PY341 - PY346 1 PY361 - PY362 1 PY381

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 28 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup Variable Number2 PY401 2 PY409 - PY411 2 PY421 - PY422 2 PY441 2 PY451 2 PY461 - PY463 2 PY591 - PY595 2 PY611 - PY612 2 PY621 2 PY631 2 PY651 2 PY671 - PY672 2 PY721 2 PY741 2. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin gives the instructions to replace the power control relays for the fuel boost pumps. The relays are located in the P6 circuit breaker panel in the flight compartment. The new relays include a ground fault interrupt (GFI) feature. The GFI relay feature will protect the fuel pumps from damage caused by electrical arcing because the electrical power will be removed from the pump if a ground fault is detected. 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 service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". This change affects section 9 of the Maintenance Planning Data (MPD) Document. The Airworthiness Limitations (AWL) "28-AWL-23" (737-100/200/200C airplanes) and "28-AWL-22" (737-300/400/500 airplanes) are related to this service bulletin. Boeing Fleet Team Digest 737 FTD 28-04005 is related to this service bulletin. Boeing Service Letter 737-SL-28-070 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 29 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTRevision 1 was sent to change the sections that follow: 1. Airplanes PM541-PM548 are added to the service bulletin effectivity. Added new airplane configurations to the group configuration table. 2. Group 12 and Group 13 had been added to the configuration table. Airplanes delivered with Auxiliary Tank wire provisions have been moved to Group 12 and Group 13. Group/Configuration information has been added to define those airplanes that have already accomplished initial release of the service bulletin. 3. Changed the concurrent requirements reference from original issue of BAE Component Service Bulletin 65-49808-24-01 to Revision 1 of the BAE Component Service Bulletin 65-49808-24-01. 4. Removed the reference to the Fault Isolation Manual and changed the IPC reference in Paragraph 1.K., Publications affected. The 737-100/-200/-300/-400/-500 airplane models do not have a Fault Isolation Manual. 5. Task hour tables had been added for each airplane group configuration. The task hour estimates were changed to include the removal and installation of the galley number one. 6. Three kits, availability, and price information was added to paragraph 2.A. Material Information. 7. The work instructions were changed to include:
a. The removal and installation of the galley number one to get access to the work location. b. The installation of a bonding jumper. c. To prepare/clean the contact surfaces of the relays and mounting panel to obtain the required electrical bonding. d. To measure the bonding resistance between the GFI relays and mounting panel. e. To measure the bonding resistance between the mounting panel and P6 Load Control Center structure. f. Added Part 2 and Part 3 for airplanes that incorporated original issue of the service bulletin. 8. Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph 3.A. General Information - Notes. 9. Figure 1 was changed to change the reference to Revision 1 of the BAE Component Service Bulletin 65-49808-24-01. Step was added to measure the electrical bonding resistance between Relay Module Assemblies M181, M182, and M183 and the P6 Load Control Center structure. 10. Figure 2, 3, 4, 5, 6, 7 have been changed to prepare/clean the contact surfaces of the relays and mounting panel in order to obtain the required electrical bonding. 11. Figure 22 has been added. this figure provides instructions to add a bonding jumper between relay mounting panel and P6 Load Control Center structure and measure the bonding resistance between the relay mounting panel and P6 Load Control Center structure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 30 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT12. Appendix A that provides information for electrical bonding was added to Paragraph 3.A., Work Instructions. Revision 2 is sent to update the installation of new GFI relays because the GFI system might not function correctly after their installation on Groups 5, 6, 7 and 9 airplanes. Boeing received a report from one operator that told of incorrect operation of new 9524G-10674 GFI relays. A subsequent investigation and test found that Electromagnetic Interference (EMI), between the new 9524G-10674 relays and adjacent KCG-X4L-001 relays could cause problems with the function of new relays and thus the operation of GFI system. The instructions have therefore been updated to change the position of the GFI relays. Other groups are not affected by this problem because of differences in the P6-2 relay panel layout. This revision is a final solution to the problem described in 737-28A1212 IN 02 and requires no new parts to be supplied or kit changes. Operators of airplanes in Groups 5, 6 and 7 can now continue to incorporate this service bulletin at this revision. In addition, at revision 2, instructions to change airplane line numbers 1-291, in Groups 1 and 8, are removed. Operators with these airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change. D. Description Group 2-7, 9-13, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT 1. Get access to the flight compartment. 2. At the P6 Load Control Center install two ground studs and a ground bonding jumper. 3. Measure the electrical bonding between the P6-2 relay panel and P6 Load Control Center structure. 4. Replace relays on the P6-2 relay panel with new Ground Fault Interrupt (GFI) relays as follows:

a.Group 2, 4, Configuration 1: Replace six relays. b.Group 3, 10-13, Configuration 1: Replace eight relays.

c.Group 5, Configuration 1: Replace six relays, with R18 and R19 turned 180 degrees. d.Group 6-7, 9, Configuration 1: Replace eight relays, with R146 and R147 turned 180 degrees. 5. Measure the electrical bonding between each of the new GFI relays and the P6-2 relay panel and repair the bond if necessary. 6.Group 2-3, 6-7, 9-13, Configuration 1: Change the W0044 wire bundle. 7. Do a Ground Fault Interrupter (GFI) - Operational Test of the GFI relay installation for the fuel boost pumps.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 31 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 2-7, 9-13, Configuration 2: PART 2 - MORE WORK - GROUND STUDS AND BONDING JUMPER INSTALLATION AND GFI RELAY POSITION CHANGE 1. Get access to the flight compartment. 2. At the P6 Load Control Center install two ground studs and a ground bonding jumper. 3. Measure the electrical bonding between the P6-2 relay panel and P6 Load Control Center structure.
4.Group 5-7, 9, Configuration 2: Remove and keep two GFI relays on the P6-2 relay panel, turn the relay sockets 180 degrees, then install the kept relays in the new position. 5. Do a Ground Fault Interrupter (GFI) - Operational Test of the GFI relay installation for the fuel boost pumps. Group 1, 8: PART 3 - THIS PART IS DELETED 1. Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. Group 5-7, 9, Configuration 3: PART 4 - MORE WORK - GFI RELAY POSITION CHANGE 1. Get access to the flight compartment. 2. Remove and keep two GFI relays on the P6-2 relay panel, turn the relay sockets 180 degrees, then install the kept relays in the new position. 3. Measure the electrical bonding between each of the changed GFI relays and the P6-2 relay panel and repair the bond if necessary. 4. Do a Ground Fault Interrupter (GFI) - Operational Test of the GFI relay installation for the related fuel boost pumps. Revision 1 - More work is necessary on airplanes changed in accordance with the original issue of this service bulletin. Group 2 through 7 Airplanes and Group 9 through 11 airplanes that incorporated original issue of this service bulletin have to incorporate Accomplishment Instructions, Work instructions, Part 2 that provides work instructions to install a Bonding Jumper between the relay mounting panel and P6 Load Control Center structure, and measure the electrical bonding resistance between the GFI relays and the relay mounting panel. Group 1 and Group 8 airplanes that incorporated original issue of this service bulletin have to incorporate Accomplishment Instructions, Work instructions, Part 3 that provides work instructions to measure the electrical bonding resistance between the GFI relays and the Relay Module Assemblies M181, M182, and M183 in accordance with Revision 1 of BAE Service Bulletin 65-49808-24-01, and to measure the electrical bonding resistance between the Relay Module Assemblies M181, M182, and M183 and the P6 Load Control Center structure. Revision 2 - More work is necessary for Group 5, 6, 7 and 9 airplanes that have been changed in accordance with the Original Issue or Revision 1 of this service bulletin:-

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 32 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT– For airplanes that have incorporated the Original Issue of this service bulletin, but not Revision 1, it is necessary to change the position of two Ground Fault Interrupt (GFI) relays, on the P6-2 relay panel, install a bonding jumper between the P6-2 relay panel and P6 Load Control Center structure, do a bonding check of the GFI relays and do a GFI operational test. This work is identified as Configuration 2 for these groups. – For airplanes that have incorporated Revision 1 of this service bulletin, it is necessary to change the position of two GFI relays on the P6-2 relay panel, do a bonding check and a GFI operational test, for related fuel boost pumps. This work is identified as Configuration 3 for these groups. Revision 2 - More work is necessary for Group 2-4 and Group 10-13 airplanes that have been changed in accordance with the Original Issue of this service bulletin. It is necessary to install a bonding jumper between the P6-2 relay panel and P6 Load Control Center structure, then do a GFI operational test of the fuel boost pumps. This work is identified as Configuration 2 for these groups. Revision 2 - No more work is necessary for Group 2-4 and Group 10-13 airplanes that have been changed in accordance with Revision 1 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1:
Affected Maintenance ZonesZone Model 1-2 737-100, 737-200, 737-200C Group 2:
Affected Maintenance ZonesZone Model 1-2 737-200, 737-200C Group 2:
Affected Maintenance ZonesZone Model 102 737-300, 737-400 Group 3-4, 10, 12:
Affected Maintenance ZonesZone Model 1-2 737-200

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 33 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 4-5:
Affected Maintenance ZonesZone Model 102 737-300, 737-400, 737-500 Group 6-7, 9:
Affected Maintenance ZonesZone Model 102 737-400 Group 8:
Affected Maintenance ZonesZone Model 1-2, 3-5, 4-5 737-100, 737-200 Group 11, 13:
Affected Maintenance ZonesZone Model 102 737-300 E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-12-09 is related to this service bulletin. Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions within 60 months after the effective date of Revision 01 of this service bulletin. . Group 2-7, 9-13: Boeing recommends that operators make the changes shown in this service bulletin within 60 months after the effective date of Revision 02 of this service bulletin. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 34 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTIf 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. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (g), (h), (i), (j) and (k) of AD 2011-12-09 for airplanes line numbers 292 through 3132. All provisions of AD 2011-12-09 that are not specifically referenced in the above statement remain fully applicable and must be complied with. The AMOC for Revision 2 of this bulletin does not apply to Group 1 and 8 airplanes (line numbers 1 thru 291), operators should contact the Boeing company for more instructions to do this change. 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. Group 2, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 4.00 8.00 2 Removal of the Galley number one 3.50 3.50 1 FIGURE 2 0.40 0.40 1 FIGURE 9 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 4.00 12.00 3 Installation of the Galley number one 1.25 2.50 2 Test 15.15 28.40 TOTAL FOR EACH AIRPLANE - PART 1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 35 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 3, 12, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 4.00 8.00 2 Removal of the Galley number one 4.50 4.50 1 FIGURE 3 1.60 1.60 1 FIGURE 10 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 4.00 12.00 3 Installation of the Galley number one 1.25 2.50 2 Test 17.35 30.60 TOTAL FOR EACH AIRPLANE - PART 1 Group 4, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 3.50 3.50 1 FIGURE 4 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 1.25 2.50 2 Test 6.75 8.00 TOTAL FOR EACH AIRPLANE - PART 1 Group 5, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 5.00 5.00 1 FIGURE 5 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 1.25 2.50 2 Test 8.25 9.50 TOTAL FOR EACH AIRPLANE - PART 1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 36 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 6, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 4.00 8.00 2 Removal of the Galley number one 5.50 5.50 1 FIGURE 6 0.40 0.40 1 FIGURE 11 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 4.00 12.00 3 Installation of the Galley number one 1.25 2.50 2 Test 17.15 30.40 TOTAL FOR EACH AIRPLANE - PART 1 Group 7, 9, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 4.00 8.00 2 Removal of the Galley number one 6.00 6.00 1 FIGURE 7 0.40 0.40 1 FIGURE 11 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 4.00 12.00 3 Installation of the Galley number one 1.25 2.50 2 Test 17.65 30.90 TOTAL FOR EACH AIRPLANE - PART 1 Group 10, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 4.00 8.00 2 Removal of the Galley number one 4.50 4.50 1 FIGURE 3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 37 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 10, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.40 0.40 1 FIGURE 12 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 4.00 12.00 3 Installation of the Galley number one 1.25 2.50 2 Test 16.15 29.40 TOTAL FOR EACH AIRPLANE - PART 1 Group 11, 13, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 4.00 8.00 2 Removal of the Galley number one 4.50 4.50 1 FIGURE 3 1.60 1.60 1 FIGURE 13 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 4.00 12.00 3 Installation of the Galley number one 1.25 2.50 2 Test 17.35 30.60 TOTAL FOR EACH AIRPLANE - PART 1 Group 2-4, 10-13, Configuration 2: PART 2 - MORE WORK - GROUND STUDS AND BONDING JUMPER INSTALLATION Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.00 1.00 1 FIGURE 22 0.50 0.50 1 Close Access 1.25 2.50 2 Test 3.25 4.50 TOTAL FOR EACH AIRPLANE - PART 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 38 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 5, Configuration 2: PART 2 - MORE WORK - GROUND STUDS AND BONDING JUMPER INSTALLATION AND GFI RELAY POSITION CHANGE Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.00 1.00 1 FIGURE 22 1.50 1.50 1 FIGURE 23 0.50 0.50 1 Close Access 1.25 2.50 2 Test 4.75 6.00 TOTAL FOR EACH AIRPLANE - PART 2 Group 6, Configuration 2: PART 2 - MORE WORK - GROUND STUDS AND BONDING JUMPER INSTALLATION AND GFI RELAY POSITION CHANGE Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.00 1.00 1 FIGURE 22 1.50 1.50 1 FIGURE 24 0.50 0.50 1 Close Access 1.25 2.50 2 Test 4.75 6.00 TOTAL FOR EACH AIRPLANE - PART 2 Group 7, 9, Configuration 2: PART 2 - MORE WORK - GROUND STUDS AND BONDING JUMPER INSTALLATION AND GFI RELAY POSITION CHANGE Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.00 1.00 1 FIGURE 22 1.50 1.50 1 FIGURE 25 0.50 0.50 1 Close Access 1.25 2.50 2 Test 4.75 6.00 TOTAL FOR EACH AIRPLANE - PART 2 Group 1, 8: PART 3 - THIS PART IS DELETED 1. Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 39 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 5, Configuration 3: PART 4 - MORE WORK - GFI RELAY POSITION CHANGE Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.50 1.50 1 FIGURE 23 0.50 0.50 1 Close Access 0.75 1.50 2 Test 3.25 4.00 TOTAL FOR EACH AIRPLANE - PART 4 Group 6, Configuration 3: PART 4 - MORE WORK - GFI RELAY POSITION CHANGE Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.50 1.50 FIGURE 24 0.50 0.50 1 Close Access 0.75 1.50 2 Test 3.25 4.00 TOTAL FOR EACH AIRPLANE - PART 4 Group 7, 9, Configuration 3: PART 4 - MORE WORK - GFI RELAY POSITION CHANGE Elapsed Hours Task-Hours Number of Persons Task 0.50 0.50 1 Open Access 1.50 1.50 1 FIGURE 25 0.50 0.50 1 Close Access 0.75 1.50 2 Test 3.25 4.00 TOTAL FOR EACH AIRPLANE - PART 4 H. Weight and Balance Changes None. I. Electrical Load Data Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. 1. Direct Current (DC) Loads

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 40 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTBus Amperes Airplanes DC Bus 1 - 0.71 Group 2 DC Bus 2 - 0.71 DC Bus 1 - 0.95 Groups 3, 10, 11, 12 and 13 DC Bus 2 - 0.95 DC Bus 1 + 0.03 Group 4 DC Bus 2 + 0.03 DC Bus 1 - 0.22 Group 5 DC Bus 2 - 0.22 DC Bus 1 - 0.46 Group 6 DC Bus 2 - 0.46 DC Bus 1 - 0.21 Group 7, 9 DC Bus 2 - 0.21 2. Type Continuous. J. References 1. Existing Data: a. Engineering Change Memo PRR 35440-10RS. b. Boeing Service Bulletin 737-24-1145. c. Boeing Service Letter 737-SL-28-070. d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-12-09. e. Service Bulletin Index D6-19567. f. Standard Overhaul Practices Manual (SOPM) 20-11-03, 20-41-02, 20-43-03, 20-60-02. g. Standard Wiring Practices Manual (SWPM) 20-00-11, 20-10-11, 20-10-12, 20-10-19, 20-20-00, 20-30-12, 20-60-00, 20-81-11, 20-81-22. h. 737 Fleet Team Digest (FTD) 28-04005. i. 737-100/200 Aircraft Maintenance Manual (AMM) 24-22-00, 25-11-0, 25-11-11, 25-16-11, 25-31-11, 28-22-18, 28-22-41. j. 737-100/200 Structural Repair Manual (SRM) 51-30-02, 51-30-05. k. 737-100/200 Wiring Diagram Manual (WDM) 28-23-01, 28-23-02.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 41 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTl. 737-300/400/500 Aircraft Maintenance Manual (AMM) 24-22-00, 25-11-11, 25-11-21, 25-31-11, 28-22-18, 28-22-41. m. 737-300/400/500 Wiring Diagram Manual (WDM) 28-23-01, 28-23-02. n. 737-300 Structural Repair Manual (SRM) 51-40-05. o. 737-400 Structural Repair Manual (SRM) 51-40-05. p. 737-500 Structural Repair Manual (SRM) 51-40-05. 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
Title Drawing Number RELAY ASSY - LOAD CONTROL CENTER 69-73627-( ) LOAD CONTROL CENTER (STRUCTURE) P-6 PANEL 65-49815 LOAD CONTROL CENTER INSTL - P6 PANEL 65C25703 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-Section Publication 28-22 737 Maintenance Manual 28-23, Equipment List 737 Wiring Diagram Manual 24-50, 28-20 737-100/200 Illustrated Parts Catalog 28-22, 28-23 737-300/400/500 Illustrated Parts Catalog 28-20 737 Schematic Diagram Section 9 737 Maintenance Planning Document 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 42 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTM. Software Accomplishment Summary Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 43 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 44 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT

BLANK PAGE2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. Group 2, Configuration 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the Revision 02date of this Service Bulletin (US Dollars) ROLT as of the Revision 02 date

of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$326.00 189 262 09/07/10 KIT - RETROFIT GFIRELAYS IN P6 - NONAUX CONFIGURATION 65C37854-12

Group 3, 6-7, 9-13, Configuration 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the Revision 02date of this Service Bulletin (US Dollars) ROLT as of the Revision 02 date

of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$354.00 189 24 09/07/10 KIT - RETROFIT GFI RELAYS IN P6 - AUX OR AUX PROVISIONS CONFIGURATION 65C37854-13 (a)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 45 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 3, 6-7, 9-13, Configuration 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the Revision 02date of this Service Bulletin (US Dollars) ROLT as of the Revision 02 date

of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

(a) Airplanes in Group 12 and 13 have been delivered with wire provisions for Auxiliary Tank installation. If Auxiliary Tanks have been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed on these airplanes there are more parts than necessary in this kit. Operators need to order only the necessary parts to incorporate this service bulletin. The necessary parts can be ordered as end item parts. Contact Boeing Spares for ordering the necessary end item parts from kit 65C37854- 13. Group 2-3, Configuration 2; Group 4; Group 5, Configuration 1-2; Group 6-7, 9-13, Configuration 2: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the Revision 02date of this Service Bulletin (US Dollars) ROLT as of the Revision 02 date

of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$4.50 189 33 09/07/10 KIT - RETROFIT BONDING JUMPER 65C37854-14
Group 5-7, 9, Configuration 3: None. B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE:One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 46 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 2-3, 6-7, 9-13, Configuration 1:
Kit 65C37854 Notes Existing Part Number Name QTY New Part Number -13 -12 KIT - RETROFIT, GFI RELAYS IN P6- NON-AUX CONFIGURATION . - 65C37854-12

KIT - RETROFIT, GFI RELAYS IN P6 - AUX OR AUX PROVISIONS CONFIGURATION - . 65C37854-13

KIT - RETROFIT BONDING JUMPER 1 1 65C37854-14

TOP KIT - GFI RELAYS IN P6 -NON-AUX CONFIGURATION . 1 61-74479-1

TOP KIT - GFI RELAYS IN P6 - AUXOR AUX PROVISIONS CONFIGURATION 1

. 61-74479-2

Group 2-4; Group 5, Configuration 1-2; Group 6, Configuration 1-2; Group 7, Configuration 1-2; Group 9, Configuration 1-2; Group 10-13:
Kit 65C37854 Notes Existing Part Number Name QTY New Part Number-14KIT - RETROFIT BONDING JUMPER - 65C37854-14

BONDING JUMPER 1 BACJ40K5A5A6
NUT 2 BACN10YR3CD (a) SCREW 2 BACS12GU3K10 WASHER 6 NAS1149D0316H

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 47 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 2-4; Group 5, Configuration 1-2; Group 6, Configuration 1-2; Group 7, Configuration 1-2; Group 9, Configuration 1-2; Group 10-13:
Kit 65C37854 Notes Existing Part Number Name QTY New Part Number-14 (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Group 2-3, 6-7, 9-13, Configuration 1:
Kit 61-74479 Notes Name New Part Number -1 -2 -101 -102 (a) Top Kit, GFI Relays in P6 - Non- Aux Configuration

- . . . 61-74479-1 (b) Top Kit, GFI Relays in P6 - Aux or Aux Provisions Configuration . - . . 61-74479-2
Wire Kit, W0044 Wire Bundle 1

. . . 61-74479-101 Wire Kit, W0044 Wire Bundle

. 1

. . 61-74479-102 (a) Lacing Tape, White 1 1

. . 61-74479-2001 (b) Filler Wire 1 1

. . 61-74479-2002 Connector Identification Tape, Imprinted "D01606 M/W R00055 CTR R B/P" . . 1 1 61-74478-10301 Connector Identification Tape, Imprinted "D01608 M/W R00054 CTR L B/P" . . 1 1 61-74478-10302 Connector Identification Tape, Imprinted "D01818 M/W R00146 AFT AUX FWD BOOST PUMP" . . . 1 61-74478-10401 Connector Identification Tape, Imprinted "D01820 M/W R00147 AFT AUX AFT BOOST PUMP" . . . 1 61-74478-10402 Connector Identification Tape, Imprinted "D01602 M/W R00020 AFT B/P 2" . . 1 1 61-74479-10101 Connector Identification Tape, Imprinted "D01604 M/W R00021 FWD B/P 2" . . 1 1 61-74479-10102 Connector Identification Tape, Imprinted "D01610 M/W R00019 FWD B/P 1" . . 1 1 61-74479-10103 Connector Identification Tape, Imprinted "D01612 M/W R00018 AFT B/P 1" . . 1 1 61-74479-10104
Contact

. . 14 18 BACC47CP2T (a) Make from BMS 13-54, Type 3, Class 1, length as required.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 48 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 2-3, 6-7, 9-13, Configuration 1:
Kit 61-74479 Notes Name New Part Number -1 -2 -101 -102 (b) Make from BMS 13-48 Type 10, Class 1, AWG 18, length as required. Group 5-7, 9, Configuration 3: None. 2. Parts and Materials Supplied by the Operator: The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. Group 2-4, 9-13:
Notes Name QTY Part Number / Specification (a) Chemical Conversion Coating As Necessary ALODINE (b) Epoxy Primer As Necessary BMS 10-11, TYPE 1 (a) Refer to SOPM 20-43-03 for application procedure, specification and material sources of Chemical Conversion Coating. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. Group 5-7, 9:
Notes Name QTY Part Number / Specification (a) Chemical Conversion Coating As Necessary ALODINE (b) Epoxy Primer As Necessary BMS 10-11, TYPE 1 Replaces BMS 3-2. (b) Naphtha, Aliphatic As Necessary TT-N-95 or equivalent Tape 6 inches Dymo 358 (3M 425 optional) (a) Refer to SOPM 20-43-03 for application procedure, specification and material sources of Chemical Conversion Coating. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 49 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 2, Configuration 1:
Notes Existing Part Number Name QTY Part Number / Specification (a) 10-60450-1 (b) Ground Fault Interrupter (GFI) Relay 6 S283A004-1 (LEACH P/N 9524G-10674) (a) Leach International North America (V58657) 6900 Orangethorpe Avenue, P.O. Box 5032 Buena Park, CA 90622-5032 Phone: (714) 739-0770, FAX: (714) 670-1145. (b) Keep the existing part if there are other uses for it. Group 3, 10-13, Configuration 1:
Notes Existing Part Number Name QTY Part Number / Specification (a) (b) 10-60450-6 (c) Ground Fault Interrupter (GFI) Relay 8 S283A004-1 (LEACH P/N 9524G-10674) (a) Leach International North America (V58657) 6900 Orangethorpe Avenue, P.O. Box 5032 Buena Park, CA 90622-5032 Phone: (714) 739-0770, FAX: (714) 670-1145. (b) Airplanes in Group 12 and 13 have been delivered with wire provisions for Auxiliary Tank installation. If Auxiliary Tanks have not been installed on these airplanes there are more parts than necessary given in this table. Operators only need to obtain the necessary parts to incorporate this service bulletin. (c) Keep the existing part if there are other uses for it. Group 4, Configuration 1:
Notes Existing Part Number Name QTY Part Number / Specification (a) KCD4N (b) Ground Fault Interrupter (GFI) Relay 6 S283A004-6 (LEACH P/N KCG- X4L-001) (a)

- Relay Installation Kit 6 002-9667-001-000 (a) Leach International North America (V58657) 6900 Orangethorpe Avenue, P.O. Box 5032 Buena Park, CA 90622-5032 Phone: (714) 739-0770, FAX: (714) 670-1145 (b) Keep the existing part if there are other uses for it. Group 5, Configuration 1:
Notes Existing Part Number Name QTY Part Number / Specification (a) 10-60450-6 (b) Ground Fault Interrupter (GFI) Relay 2 S283A004-1 (LEACH P/N 9524G-10674) (a) KCD4N (b) Ground Fault Interrupter (GFI) Relay 4 S283A004-6 (LEACH P/N KCG- X4L-001) (a)

- Relay Installation Kit 4 002-9667-001-000 (a) Leach International North America (V58657) 6900 Orangethorpe Avenue, P.O. Box 5032 Buena Park, CA 90622-5032 Phone: (714) 739-0770, FAX: (714) 670-1145 (b) Keep the existing part if there are other uses for it.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 50 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 6, Configuration 1:
Notes Existing Part Number Name QTY Part Number / Specification (a) 10-60450-6 (b) Ground Fault Interrupter (GFI) Relay 4 S283A004-1 (LEACH P/N 9524G-10674) (a) KCD4N (b) Ground Fault Interrupter (GFI) Relay 4 S283A004-6 (LEACH P/N KCG- X4L-001) (a)

- Relay Installation Kit 4 002-9667-001-000 (a) Leach International North America (V58657) 6900 Orangethorpe Avenue, P.O. Box 5032 Buena Park, CA 90622-5032 Phone: (714) 739-0770, FAX: (714) 670-1145 (b) Keep the existing part if there are other uses for it. Group 7, 9, Configuration 1:
Notes Existing Part Number Name QTY Part Number / Specification (a) 10-60450-6 (b) Ground Fault Interrupter (GFI) Relay 2 S283A004-1 (LEACH P/N 9524G-10674) (a) KCD4N (b) Ground Fault Interrupter (GFI) Relay 6 S283A004-6 (LEACH P/N KCG- X4L-001) (a)

- Relay Installation Kit 6 002-9667-001-000 (a) Leach International North America (V58657) 6900 Orangethorpe Avenue, P.O. Box 5032 Buena Park, CA 90622-5032 Phone: (714) 739-0770, FAX: (714) 670-1145 (b) Keep the existing part if there are other uses for it.
3. Parts Modified and Reidentified: Group 1, 8: Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. Group 2-7, 9-13: None. 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 51 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTF. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 52 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT3. 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. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets are in Structural Repair Manual (SRM) 51 – Torque limits to tighten nuts and bolts are in SRM 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 7. These work instructions refer to procedures included in 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. 8. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 9. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 53 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT10. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. The removed part can be discarded if a new or serviceable part is installed. 11. This service bulletin includes functional test procedures for the systems changed or modified by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. B. WORK INSTRUCTIONS Group 2-7, 9-13, Configuration 1: PART 1 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND FUEL BOOST PUMP RELAYS REPLACEMENT 1. Remove the electrical power from the airplane. Refer to 737-100/200 AMM 24-22-00 or 737-300/400/500 AMM 24-22-00 as an accepted procedure. 2. Get access to the flight compartment. 3. In the flight compartment, move the First Officer's seat forward to create room in front of P6 Load Control Panel. Refer to 737-100/200 AMM 25-11-0 or 737-300/400/500 AMM 25-11-11 as an accepted procedure. If necessary remove the First Officer's seat. Refer to 737-100/200 AMM 25-11-11 or 737-300/400/500 AMM 25-11-11 as an accepted procedure. 4. In the flight compartment, remove and keep the adjacent lining panels outboard of the P6-2 circuit breaker panel. Refer to 737-100/200 AMM 25-16-11 or 737-300/400/500 AMM 25-11-21 as an accepted procedure. 5. Open and lower the P6-1 (65C25704-( ) ) and P6-2 (65C25704-( ) ) panels. 6.Group 2-7, 9-13, Configuration 1: Install Ground Studs and Bonding Jumper and measure the electrical bonding resistance between P6-2 relay panel and the P6 side panel in accordance with FIGURE 22.
7.Group 2, Configuration 1: Replace the fuel pump power relays R18, R19, R20, R21, R54, and R55 and measure the electrical bonding between each new relay and P6-2 relay panel in accordance with FIGURE 2. 8.Group 3, 10-13, Configuration 1: Replace the fuel pump power relays R18, R19, R20, R21, R54, R55, R146, and R147 and measure the electrical bonding between each new relay and P6-2 relay panel in accordance with FIGURE 3. 9.Group 4, Configuration 1: Replace the fuel pump power relays R18, R19, R20, R21, R54, and R55 and measure the electrical bonding between each new relay and P6-2 relay panel in accordance with FIGURE 4. 10.Group 5, Configuration 1: Replace the fuel pump power relays R18, R19, R20, R21, R54, and R55, install R18 and R19 turned 180 degrees from their original position, then measure the electrical bonding between each new relay and P6-2 relay panel in accordance with FIGURE 5.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 54 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT11.Group 6, Configuration 1: Replace the fuel pump power relays R18, R19, R20, R21, R54, R55, R146, and R147, install R146 and R147 turned 180 degrees from their original position, then measure the electrical bonding between each new relay and P6-2 relay panel in accordance with FIGURE 6.
12.Group 7, 9, Configuration 1: Replace the fuel pump power relays R18, R19, R20, R21, R54, R55, R146, and R147, install R146 and R147 turned 180 degrees from their original position, then measure the electrical bonding between each new relay and P6-2 relay panel in accordance with FIGURE 7. 13.Group 2-3, 6-7, 9-13, Configuration 1: Remove the galley number one to get access to the W0044 wire bundle in the P6 panel. Refer to 737-100/200 AMM 25-31-11 or 737-300/400/500 AMM 25-31-11 as an accepted procedure.
14.Group 2, Configuration 1: Change the W0044 wire bundle in accordance with FIGURE 8, FIGURE 9, and FIGURE 20. 15.Group 3, 12, Configuration 1: Change the W0044 wire bundle in accordance with FIGURE 8, FIGURE 10, and FIGURE 20. 16.Group 6-7, 9, Configuration 1: Change the W0044 wire bundle in accordance with FIGURE 8, FIGURE 11, and FIGURE 20.
17.Group 10, Configuration 1: Change the W0044 wire bundle in accordance with FIGURE 8, FIGURE 12, and FIGURE 20. 18.Group 11, 13, Configuration 1: Change the W0044 wire bundle in accordance with FIGURE 8, FIGURE 13, and FIGURE 20. 19.Group 2-3, 6-7, 9-13, Configuration 1: Install the galley number one. Refer to 737-100/200 AMM 25-31-11 or 737-300/400/500 AMM 25-31-11 as an accepted procedure. 20. In the flight compartment, install the adjacent lining panels outboard of the P6-2 circuit breaker panel. Refer to 737-100/200 AMM 25-16-11 or 737-300/400/500 AMM 25-11-21 as an accepted procedure. 21. Close the P6-1 (65C25704-( ) ) and P6-2 (65C25704-( ) ) panels. 22. Restore the position of the First Officer's seat if it was moved forward to create room in front of P6 Load Control Panel. Refer to 737-100/200 AMM 25-11-0 or 737-300/400/500 AMM 25-11-11 as an accepted procedure. If the First Officer's seat was removed, install the First Officer's seat. Refer to 737-100/200 AMM 25-11-11 or 737-300/400/500 AMM 25-11-11 as an accepted procedure. 23. Supply electrical power to the airplane. Refer to 737-100/200 AMM 24-22-00 or 737-300/400/500 AMM 24-22-00 as an accepted procedure. 24. Do the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST". Refer, as applicable, to 737-100/200 AMM 28-22-41 or 737-300/400/500 AMM 28-22-41 as an accepted procedure. 25. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 55 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 2-7, 9-13, Configuration 2: PART 2 - GROUND STUDS AND BONDING JUMPER INSTALLATION AND GFI RELAY POSITION CHANGE - MORE WORK FOR AIRPLANES THAT HAVE BEEN CHANGED IN ACCORDANCE WITH THE ORIGINAL ISSUE OF THIS SERVICE BULLETIN. 1. Remove the electrical power from the airplane. Refer to 737-100/200 AMM 24-22-00 or 737-300/400/500 AMM 24-22-00 as an accepted procedure. 2. Get access to the flight compartment. 3. Install Ground Studs and Bonding Jumper in accordance with FIGURE 22.
4.Group 5-7, 9, Configuration 2: Remove and keep two GFI relays on the P6-2 relay panel, turn the relay sockets 180 degrees then install the kept relays in the new position as follows:

a.Group 5, Configuration 2: R18 and R19 in accordance with FIGURE 23. b.Group 6, Configuration 2: R146 and R147 in accordance with FIGURE 24.

c.Group 7, 9, Configuration 2: R146 and R147 in accordance with FIGURE 25. 5. Supply electrical power to the airplane. Refer to 737-100/200 AMM 24-22-00 or 737-300/400/500 AMM 24-22-00 as an accepted procedure. 6. Do the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST" on all GFI relays. Refer to 737-100/200 AMM 28-22-41 or 737-300/400/500 AMM 28-22-41 as an accepted procedure. a. If any of the GFI relays fail the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST", make sure that the bonding resistance between the GFI relay flange and the mounting panel is 0.0025 Ohms (2.5 milliohms) or less, in accordance with APPENDIX A, Paragraph 5.b. (1) If the resistance measurement is greater than 0.0025 Ohms (2.5 milliohms), then remove the relay, clean the faying surfaces, install the relay again and measure the bonding resistance, in accordance with APPENDIX A. (2) If the resistance measurement is 0.0025 Ohms (2.5 milliohms) or less replace the GFI relay. Refer to 737-100/200 AMM 28-22-18 or 737-300/400/500 AMM 28-22-18 as an accepted procedure. (3) Repeat the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST". Refer to 737-100/200 AMM 28-22-41 or 737-300/400/500 AMM 28-22-41 as an accepted procedure. 7. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 56 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTGroup 1, 8: PART 3 - THIS PART IS DELETED 1. Operators with Group 1 and Group 8 airplanes should contact The Boeing Company to get engineering and accomplishment instructions for this change and do the instructions. Group 5-7, 9, Configuration 3: PART 4 - GFI RELAY POSITION CHANGE - MORE WORK FOR AIRPLANES THAT HAVE BEEN CHANGED IN ACCORDANCE WITH REVISION 1 OF THIS SERVICE BULLETIN 1. Remove the electrical power from the airplane. Refer to 737-100/200 AMM 24-22-00 or 737-300/400/500 AMM 24-22-00 as an accepted procedure. 2. Get access to the flight compartment. 3. Remove and keep two GFI relays on the P6-2 relay panel, turn the relay sockets 180 degrees then install the kept relays in the new position as follows:

a.Group 5, Configuration 3: R18 and R19 in accordance with FIGURE 23. b.Group 6, Configuration 3: R146 and R147 in accordance with FIGURE 24.

c.Group 7, 9, Configuration 3: R146 and R147 in accordance with FIGURE 25. 4. Supply electrical power to the airplane. Refer to 737-100/200 AMM 24-22-00 or 737-300/400/500 AMM 24-22-00 as an accepted procedure. 5. Do the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST" on all GFI relays. Refer to 737-100/200 AMM 28-22-41 or 737-300/400/500 AMM 28-22-41 as an accepted procedure. a. If any of the GFI relays fail the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST", make sure that the bonding resistance between the GFI relay flange and the mounting panel is 0.0025 Ohms (2.5 milliohms) or less, in accordance with APPENDIX A, Paragraph 5.b. (1) If the resistance measurement is greater than 0.0025 Ohms (2.5 milliohms), then remove the relay, clean the faying surfaces, install the relay again and measure the bonding resistance, in accordance with APPENDIX A. (2) If the resistance measurement is 0.0025 Ohms (2.5 milliohms) or less replace the GFI relay. Refer to 737-100/200 AMM 28-22-18 or 737-300/400/500 AMM 28-22-18 as an accepted procedure. (3) Repeat the "GROUND FAULT INTERRUPTER (GFI) - OPERATIONAL TEST". Refer to 737-100/200 AMM 28-22-41 or 737-300/400/500 AMM 28-22-41 as an accepted procedure. 6. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2: October 18, 2012 57 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 1, 8.

FIGURE 1: M181, M182, M183 RELAY MODULE ASSEMBLY - REPLACEMENT (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 58 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 2, Configuration 1.

FIGURE 2: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 59 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R18, R19, R20, R21, R54, and R55. 6 10-60450-1 Fuel Pump Power Relay Remove 1 Remove the paint around the relay cutout, from the side of the panel that will be in contact with the relay. (a) - - Surface Clean 2

On the bare surfaces. Refer to SOPM 20-43- 03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 3

The contact surfaces of the relay and thepanel to remove contamination. (b) - - Surface Clean 4

R18, R19, R20, R21, R54, and R55. Refer to SWPM 20-81-22 asan accepted procedure for installation of similar LEACH relays. 6 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / New 5

Between the flange of the relay and the mounting panel. (c) 6 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 6

On any bare metalaround the relays. Refer to SOPM 20-41-02as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 7

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is greater than 0.0025 Ohms (2.5 milliohms), then remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again.

FIGURE 2: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 60 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 3, 10-13, Configuration 1.

FIGURE 3: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 61 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R18, R19, R20, R21, R54, R55, R146, and R147. 8 10-60450-6 Fuel Pump Power Relay Remove 1 Remove the paint around the relay cutout, from the side of the panel that will be in contact with the relay. (a) - - Surface Clean 2

On the bare surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 3

The contact surfaces of therelays and the panel to remove contamination. (b) - - Surface Clean 4

R18, R19, R20, R21, R54,R55, R146, and R147. Refer to SWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. (d) 8 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / New 5

Between the flange of the relay and the mounting panel. (c) 8 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 6

On any bare metal around the relays. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 7

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is greater than 0.0025 Ohms (2.5 milliohms), then remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Airplanes in Group 12 and 13 have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have been installed on these airplanes operators need to order this kit. If AuxiliaryTanks have not been installed on these airplanes there are more parts than necessary in this kit. Operators need to obtain only the necessary parts to incorporate this service bulletin for Tank 1, Tank 2, and Center Tank.

FIGURE 3: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 62 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 4, Configuration 1.

FIGURE 4: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 63 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R18, R19, R20, R21, R54, and R55. 6 KCD4N Fuel Pump Power Relay Remove 1 Remove the paint from both sides of the panel that will be in contact with the relay spacers and spacer hardware. (a) - - Surface Clean 2

On the bare surfaces. Refer to SOPM 20-43-03as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 3

The contact surfaces of the relays, spacers, andthe panel, to remove contamination. (b) - - Surface Clean 4

R18, R19, R20, R21, R54, and R55. Refer to SWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. 6 S283A004-6(LEACH P/N KCGX4L-001) Fuel Pump Power (GFI) Relay Install / New 5

6 002-9667-001-000 Relay Spacer Kit
Between the flange of the relay and the mounting panel. (c) 6 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 6

On any bare metal around spacers. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 7

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b.. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is greater than 0.0025 Ohms (2.5 milliohms), then remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again.

FIGURE 4: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 64 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 5, Configuration 1.

FIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 65 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 66 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 67 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R20, R21, R54, and R55. 4 KCD4N Fuel Pump Power Relay Remove 1 R18 and R19. 2 10-60450-6 Fuel Pump Power Relay Remove 2 For R18 and R19 and related hardware. 2 10-60450-5 Fuel Pump Power Relay Socket Remove / Keep 3
Diameter 0.151 to 0.161 inch. (d) (e) 6

- Holes Drill 4 Remove the paint from both sides of the panel that will be in contact with the relay spacers and spacer hardware. (a) - - Surface Clean 5

Remove the paint around the relay cutout, from the side of the panel that willbe in contact with the relay. (a) - - Surface Clean 6

On the bare surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 7

Approximately as shown. Use Dymo 358 Aluminium tape or equivalent. (h) 1

- Decal Make 8

To prepare to install the Decal and tape to cover holes. Use TT-N-95 or equivalent. Do not allow to evaporate, but wipe dry with a clean cloth. - - Surface Clean 9

Remove the backing and install the Decal and tape on the P6-2 panel. Take care not to contaminate the adhesive and make sure the tape has sufficient clearance to avoid contact with the new relay spacers and does not overlap the relay cut-out. (i) 5 DYMO 358 (3M 425 optional) Tape and Decal Install 10

FIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 68 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP The contact surfaces of the relays, spacers, andthe panel, to remove contamination. (b) - - Surface Clean 11

R20, R21, R54, and R55. Refer to SWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. 4 S283A004-6(LEACH P/N KCGX4L-001) Fuel Pump Power (GFI) Install / New 12

4 002-9667-001-000 Relay Spacer Kit For R18 and R19, and related hardware, turned 180 degrees. Refer to SWPM 20-81-22 as an accepted procedure. (f) 2 10-60450-5 Fuel Pump Power Relay Socket Install / Kept 13

R18 and R19 in the changed sockets. Refer toSWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. (g) 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / New 14

Between the flange of the relay and the mounting panel. (c) 6 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 15

On any bare metal around the relays and spacers and plugs. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 16

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is more than 0.0025 Ohms (2.5 milliohms), remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Use the Fuel Pump Power (GFI) Relay, LEACH P/N 9524G-10674, as a template to mark the new holes. Put the relay into the existing cutout, turned 180 degrees from its original position, then mark and drill the new holes. (e) It is not necessary to change the size or shape of the cut-out in the relay panel. The existing cut-out is acceptable to allow installation of relay turned 180 degrees. (f) Use the new holes for installation. The original holes are not used. (g) Install the existing connectors for R18 and R19 turned 180 degrees to agree with the changed sockets. Adjust wire bundles if necessary. Refer to SWPM 20-10-11 and SWPM 20-10-12, as accepted procedures.

FIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 69 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP (h) Use Dymo M11 Tapewriter or equivalent to emboss the Decal. Use one, two or three pieces of tape, as necessary, for the decal. Trim the tape and decal, as necessary, to fit the locations shown in Detail A - AFTER. (i) Install the decal at the approximate location shown.

FIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 70 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 6, Configuration 1.

FIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 71 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 72 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 73 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R20, R21, R54, and R55. 4 KCD4N Fuel Pump Power Relay Remove 1 R146, R147, R18, and R19. 4 10-60450-6 Fuel Pump Power Relay Remove 2 For R146 and R147 and related hardware. 2 10-60450-5 Fuel Pump Power Relay Sock- et Remove / Keep 3
Diameter 0.151 to 0.161 inch. (d) (e) 6

- Holes Drill 4 Remove the paint from both sides of the panel that will be in contact with the relayspacers and spacer hardware. (a) - - Surface Clean 5

Remove the paint around the relay cutout, from the side ofthe panel that will be in contact with the relay. (a) - - Surface Clean 6

On the bare surfaces. Referto SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 7

Approximately as shown. Use Dymo 358 Aluminium tape or equivalent. (h) 1

- Decal Make 8

To prepare to install the Decal and tape to cover holes. Use TT-N-95 or equivalent. Do not allow to evaporate, but wipe dry with a clean cloth. - - Surface Clean 9

Remove the backing and install the Decal and tape on the P6-2 panel. Take care not to contaminate the adhesive and make sure the tape has sufficient clearance to avoid contact with the new relay spacers and does not overlap the relay cut-out. (i) 5 DYMO 358 (3M 425 optional) Tape and Decal Apply 10

The contact surfaces of therelays, spacers, and the panel, to remove contamination. (b) - - Surface Clean 11

FIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 74 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP R20, R21, R54, and R55. Refer to SWPM 20-81-22 as anaccepted procedure for installation of similar LEACH relays. 4 S283A004-6(LEACH P/N KCGX4L-001) Fuel Pump Power (GFI) Install / New 12

4 002-9667-001-000 Relay Spacer Kit For R146 and R147, and related hardware, turned 180 degrees. Refer to SWPM 20-81- 22 as an accepted procedure. (f) 1 10-60450-5 Fuel Pump Power Relay Sock- et Install / Kept 13

R146, R147, R18, and R19. Refer to SWPM 20-81-22 asan accepted procedure for installation of similar LEACH relays. (g) 4 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / New 14

Between the flange of the relay and the mounting panel. (c) 8 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 15

On any bare metal around the relays and spacers. Refer toSOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 16

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is more than 0.0025 Ohms (2.5 milliohms), remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Use the Fuel Pump Power (GFI) Relay, LEACH P/N 9524G-10674, as a template to mark the new holes. Put the relay into the existing cutout, turned 180 degrees from its original position, then mark and drill the new holes. (e) It is not necessary to change the size or shape of the cut-out in the relay panel. The existing cut-out is acceptable to allow installation of relay turned 180 degrees. (f) Use the new holes for installation. The original holes are not used. (g) Install the existing connectors for R146 and R147 turned 180 degrees to agree with the changed sockets. Adjust wire bundles if necessary. Refer to SWPM 20-10-11 and SWPM 20-10-12, as accepted procedures. (h) Use Dymo M11 Tapewriter or equivalent to emboss the Decal. Use one, two or three pieces of tape, as necessary, for the decal. Trim the tape and decal, as necessary, to fit the locations shown in Detail A - AFTER. (i) Install the decal at the approximate location shown.

FIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 75 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 7, 9, Configuration 1.

FIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 76 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 77 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 78 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R18, R19, R20, R21, R54, and R55. 6 KCD4N Fuel Pump Power Relay Remove 1
R146 and R147. 2 10-60450-6 Fuel Pump Power Relay Remove 2
For R146 and R147 and related hardware. 2 10-60450-5 Fuel Pump Power Relay Socket Remove / Keep 3
Diameter 0.151 to 0.161 inch. (d) (e) 6

- Holes Drill 4 Remove the paint from both sides of the panel that will be in contact with the relay spacers and spacer hardware. (a) - - Surface Clean 5

Remove the paint around the relay cutout, from the side of the panel that willbe in contact with the relay. (a) - - Surface Clean 6

On the bare surfaces. Refer to SOPM 20-43-03as an accepted procedure. - ALODINE Chemical Conver- sion Coating Apply 7

Approximately as shown. Use Dymo 358 Aluminium tape or equivalent. (h) 1

- Decal Make 8

To prepare to install the Decal and tape to cover holes. Use TT-N-95 or equivalent. Do not allow to evaporate, but wipe dry with a clean cloth. - - Surface Clean 9

FIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 79 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP Remove the backing and install the Decal and tape on the P6-2 panel. Take care not to contaminate the adhesive and makesure the tape has sufficient clearance to avoid contact with the new relay spacers and does not overlap the relay cut-out. (i) DYMO 358 (3M 425 optional) Tape and Decal Apply 10

The contact surfaces of the relays, spacers, andthe panel, to remove contamination. (b) - - Surface Clean 11

R18, R19, R20, R21, R54, and R55. Refer to SWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. 6 S283A004-6(LEACH P/N KCGX4L-001) Fuel Pump Power (GFI) Install / New 12

6 002-9667-001-000 Relay Spacer Kit
For R146 and R147, and related hardware, turned 180 degrees. Refer to SWPM 20-81-22 as an accepted procedure. (f) 2 10-60450-5 Fuel Pump Power Relay Socket Install / Kept 13

R146 and R147 in the changed sockets. Refer to SWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. (g) 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / New 14

Between the flange of the relay and the mounting panel. (c) 8 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 15

On any bare metal around the relays and spacers. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 16

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b.

FIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 80 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is more than 0.0025 Ohms (2.5 milliohms), remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Use the Fuel Pump Power (GFI) Relay, LEACH P/N 9524G-10674, as a template to mark the new holes. Put the relay into the existing cutout, turned 180 degrees from its original position, then mark and drill the new holes. (e) It is not necessary to change the size or shape of the cut-out in the relay panel. The existing cut-out is acceptable to allow installation of relay turned 180 degrees. (f) Use the new holes for installation. The original holes are not used. (g) Install the existing connectors for R146 and R147 turned 180 degrees to agree with the changed sockets. Adjust wire bundles if necessary. Refer to SWPM 20-10-11 and SWPM 20-10-12, as accepted procedures. (h) Use Dymo M11 Tapewriter or equivalent to emboss the Decal. Use one, two or three pieces of tape, as necessary, for the decal. Trim the tape and decal, as necessary, to fit the locations shown in Detail A - AFTER. (i) Install the decal at the approximate location shown.

FIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 81 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 2-3, 6-7, 9-13, Configuration 1.

FIGURE 8: W0044 WIRE BUNDLE - LOCATION (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 82 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 2, Configuration 1.

Refer to 737-100/200 WDM 28-23-01 or 737-300/400/500 WDM 28-23-01 as applicable. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 9: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 83 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE Use filler wire to build up diameter of wire inside contact. Refer to SWPM 20-60-00and SWPM 20-81-11 as accepted procedures. 12 BACC47CP2T Contact 1

- 61-74479-2002 Filler Wire

Use color white. Refer to SWPM 20-10-11 as an accepted procedure. - 61-74479-2001 Lacing Tape 2 Imprinted "D1602 M/W R00020 AFT B/P 2". Install within 6 inches of connector. 1 61-74479-10101 Connector Identifi- cation Tape 3 Imprinted "D1608 M/W R00054 CTR L B/P". Install within 6 inches of connector. 1 61-74478-10302 Connector Identifi- cation Tape 4 Imprinted "D1604 M/W R00021 FWD B/P 2". Install within 6 inches of connector. 1 61-74479-10102 Connector Identifi- cation Tape 5 Imprinted "D1610 M/W R00019 FWD B/P 1". Install within 6 inches of connector. 1 61-74479-10103 Connector Identifi- cation Tape 6 Imprinted "D1606 M/W R00055 CTR R B/P". Install within 6 inches of connector. 1 61-74478-10301 Connector Identifi- cation Tape 7 Imprinted "D1612 M/W R00018 AFT B/P 1". Install within 6 inches of connector. 1 61-74479-10104 Connector Identifi- cation Tape 8

FIGURE 9: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 84 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 3, 12, Configuration 1.

FIGURE 10: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 85 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTRefer to 737-100/200 WDM 28-23-01 and 737-100/200 WDM 28-23-02 or 737-300/400/500 WDM 28-23-01 and 737-300/400/500 WDM 28-23-02 as applicable. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Use filler wire to build up diameter of AWG 22 wire inside contact. Refer to SWPM 20-60-00 and SWPM 20-81-11 as accepted procedures. (a) 1 BACC47CP2T Contact 1

- 61-74479-2002 Filler Wire

Use color white. Refer to SWPM 20-10- 11 as an accepted procedure. - 61-74479-2001 Lacing Tape 2 Imprinted "D1602 M/W R00020 AFT B/P 2". Install within 6 inches of connector. 1 61-74479-10101 Connector Identifi- cation Tape 3 Imprinted "D1608 M/W R00054 CTR L B/P". Install within 6 inches of connector. 1 61-74478-10302 Connector Identifi- cation Tape 4 Imprinted "D1604 M/W R00021 FWD B/P 2". Install within 6 inches of connector. 1 61-74479-10102 Connector Identifi- cation Tape 5 Imprinted "D1610 M/W R00019 FWD B/P 1". Install within 6 inches of connector. 1 61-74479-10103 Connector Identifi- cation Tape 6 Imprinted "D1606 M/W R00055 CTR R B/P". Install within 6 inches of connector. 1 61-74478-10301 Connector Identifi- cation Tape 7 Imprinted "D1612 M/W R00018 AFT B/P 1". Install within 6 inches of connector. 1 61-74479-10104 Connector Identifi- cation Tape 8 Imprinted "D1818 M/W R00146 AFT AUX FWD BOOST PUMP". Install within 6 inches of connector. (a) 1 61-74478-10401 Connector Identifi- cation Tape 9

Imprinted "D1820 M/W R00147 AFT AUX AFT BOOST PUMP". Install within 6 inches of connector. (a) 1 61-74478-10402 Connector Identifi- cation Tape 10

(a) Airplanes in Group 12 have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed on these airplanes there are more parts than necessary in this kit. Operators need to obtain only the necessary parts to incorporate this service bulletin for Tank 1, Tank 2, and Center Tank.

FIGURE 10: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 86 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 6-7, 9, Configuration 1.

Refer to 737-300/400/500 WDM 28-23-02. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Use filler wire to build up diameter of AWG 24 wire inside contact. Refer to SWPM 20-60-00 and SWPM 20-81-11 as accepted procedures. 4 BACC47CP2T Contact 1

- 61-74479-2002 Filler Wire

Use color white. Refer to SWPM 20-10- 11 as an accepted procedure. - 61-74479-2001 Lacing Tape 2 Imprinted "D1818 M/W R00146 AFT AUX FWD BOOST PUMP". Install within 6 inches of connector. 1 61-74478-10401 Connector Identifi- cation Tape 3

Imprinted "D1820 M/W R00147 AFT AUX AFT BOOST PUMP". Install within 6 inches of connector. 1 61-74478-10402 Connector Identifi- cation Tape 4

FIGURE 11: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 87 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 10, Configuration 1.

Refer to 737-100/200 WDM 28-23-02. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Use filler wire to build up diameter of AWG 22 wire inside contact. Refer to SWPM 20-60-00 and SWPM 20-81-11 as accepted procedures. 4 BACC47CP2T Contact 1

- 61-74479-2002 Filler Wire Use color white. Refer to SWPM 20-10-11 as an accepted procedure. - 61-74479-2001 Lacing Tape 2 Imprinted "D1818 M/W R00146 AFT AUX FWDBOOST PUMP". Install within 6 inches of connector. 1 61-74478-10401 Connector Identifi- cation Tape 3

Imprinted "D1820 M/W R00147 AFT AUX AFTBOOST PUMP". Install within 6 inches of connector. 1 61-74478-10402 Connector Identifi- cation Tape 4

FIGURE 12: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 88 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 11, 13, Configuration 1.

FIGURE 13: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 89 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTRefer to 737-300/400/500 WDM 28-23-01 and 737-300/400/500 WDM 28-23-02. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Use filler wire to build up diameter of AWG 22 and AWG 24 wire inside contact. Refer to SWPM 20-60-00 and SWPM 20-81-11 as accepted procedures. (a) 16 BACC47CP2T Contact 1

- 61-74479-2002 Filler Wire

Use color white. Refer to SWPM 20-10-11 as an accepted procedure. - 61-74479-2001 Lacing Tape 2 Imprinted "D1602 M/W R00020 AFT B/P 2". Install within 6 inches of connector. 1 61-74479-10101 Connector Identifi- cation Tape 3 Imprinted "D1608 M/W R00054 CTR L B/P". Install within 6 inches of connector. 1 61-74478-10302 Connector Identifi- cation Tape 4 Imprinted "D1604 M/W R00021 FWD B/P 2". Install within 6 inches of connector. 1 61-74479-10102 Connector Identifi- cation Tape 5 Imprinted "D1610 M/W R00019 FWD B/P 1". Install within 6 inches of connector. 1 61-74479-10103 Connector Identifi- cation Tape 6 Imprinted "D1606 M/W R00055 CTR R B/P". Install within 6 inches of connector. 1 61-74478-10301 Connector Identifi- cation Tape 7 Imprinted "D1612 M/W R00018 AFT B/P 1". Install within 6 inches of connector. 1 61-74479-10104 Connector Identifi- cation Tape 8 Imprinted "D1818 M/W R00146 AFT AUX FWD BOOST PUMP". Install within 6 inches of connector. (a) 1 61-74478-10401 Connector Identifi- cation Tape 9

Imprinted "D1820 M/W R00147 AFT AUX AFT BOOST PUMP". Install within 6 inches of connector. (a) 1 61-74478-10402 Connector Identifi- cation Tape 10

(a) Airplanes in Group 13 have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed on these airplanes there are more parts than necessary in this kit. Operators need to obtain only the necessary parts to incorporate this service bulletin for Tank 1, Tank 2, and Center Tank.

FIGURE 13: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 90 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 8.

FIGURE 14: FUEL BOOST PUMP CONNECTOR - WIRE LOCATION (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 91 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 8.

FIGURE 15: FUEL BOOST PUMP GROUNDS - WIRE LOCATION (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 92 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 8.

FIGURE 16: FUEL BOOST PUMP CONNECTOR - WIRING CHANGES (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 93 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 8.

FIGURE 17: FUEL BOOST PUMP CONNECTOR - WIRE LOCATION (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 94 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 8.

FIGURE 18: FUEL BOOST PUMP GROUNDS - WIRE LOCATION (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 95 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 8.

FIGURE 19: FUEL BOOST PUMP CONNECTOR - WIRING CHANGES (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 96 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 2-7, 9-13, Configuration 1.

FIGURE 20: FUEL BOOST PUMP CONTROL GROUND FAULT INTERRUPTER (GFI) CONTROL RELAY - REFERENCE (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 97 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 1, 8.

FIGURE 21: WIRE BUNDLE W0044 - WIRING CHANGES (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 98 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 2-4; Group 5, Configuration 1-2; Group 6, Configuration 1-2; Group 7, Configuration 1-2; Group 9, Configuration 1-2; Group 10-13.

FIGURE 22: P6-2 RELAY PANEL - GROUND STUDS AND BONDING JUMPER - INSTALLATION (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 99 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 22: P6-2 RELAY PANEL - GROUND STUDS AND BONDING JUMPER - INSTALLATION (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 100 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP In accordance with 737-100/200 SRM 51-30-02 or 737-300 SRM 51-40-05, or 737-400 SRM 51- 40-05, or 737-500 SRM 51-40- 05 as applicable. (a) 1 BACR15BB5D( ) Rivet Remove/Dis- card 1

With 0.218-0.229 inch diameter in accordance with 737-100/200 SRM 51-30-05 or 737-300 SRM 51-40-05, or 737-400 SRM 51- 40-05, or 737-500 SRM 51-40- 05 as applicable. 2

- Hole Drill 2

In accordance with 737-100/200 SRM 51-30-05 or 737-300 SRM 51-40-05, or 737-400 SRM 51- 40-05, or 737-500 SRM 51-40- 05 as applicable. 2

- Hole Deburr 3

Remove the paint on both side, the panel area around the hole, and the support angle around the hole. (b) 4

- Surface Clean 4

On any bare metal around the holes. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conver- sion Coating Apply 5

FIGURE 22: P6-2 RELAY PANEL - GROUND STUDS AND BONDING JUMPER - INSTALLATION (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 101 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP To remove the contamination. (c) 4

- Surface Clean 6
In accordance with APPENDIX A, Paragraph 1. 2 BACS12GU3K10 Bolt Install (New) 7 6 NAS1149D0316H Washer Install (New) 2 BACN10YR3CD Nut Install (New) 1 BACJ40K5A5A6 Bonding Jumper Install (New) To 35 to 40 Inch-Pound in accordance with APPENDIX A, Paragraph 1. 2

- Nut Torque

Between bonding jumper terminal lug and structure. Make sure that the resistance is 0.001 Ohms (1.0 milliohms) or less. (d) 2 0.001 OHMS (1.0 MILLIOHMS) Resistance Measure 8

Between the relay mounting panel and P6 Load Control Center structure. Make sure that the resistance is 0.0025 Ohms (2.5 milliohms) or less. (d) 1 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 9

On any bare metal around the ground studs. Refer to SOPM20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 10

(a) Operators that incorporated Boeing Service Bulletin 737-24-1145 have to use the "Optional" installation of the ground studs in accordance with Detail C. Step 1 needs to be done only if the optional installation is used. (b) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (c) Use Solvent to clean the surface area around the holes in accordance with APPENDIX A, Paragraph 2.b. (d) If the resistance measurement is greater than the maximum resistance shown, then disassemble parts, clean faying surfaces, install parts and measure bonding resistance again. Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 22: P6-2 RELAY PANEL - GROUND STUDS AND BONDING JUMPER - INSTALLATION (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 102 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 5, Configuration 2-3.

FIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 103 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 104 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 105 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R18 and R19. 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Remove / Keep 1

For R18 and R19 and related hardware. 2 10-60450-5 Fuel Pump Power (GFI) Relay Socket Remove / Keep Diameter 0.151 to 0.161 inch. (d) (e) 6

- Holes Drill 2 If necessary, remove the paint around the relay cutout, from the side of the panel that will be in contact with the relay. (a) - - Surface Clean 3

If necessary, on the bare surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 4

Approximately as shown. Use Dymo 358 Aluminium tape or equivalent. (h) 1

- Decal Make 5

To prepare to install the Decal and tape to cover holes. Use TT-N-95 or equivalent. Do not allow to evaporate, but wipe dry with a clean cloth. - - Surface Clean 6

Remove the backing and install the Decal and tape on the P6-2 panel. Take care not to contaminate the adhesive and make sure the tape has sufficient clearance to avoid contact with the new relay spacers and does not overlap the relay cut-out. (i) 5 DYMO 358 (3M 425 optional) Tape and Decal Install 7

The contact surfaces of the relays and the panel to remove contamination. (b) - - Surface Clean 8

FIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 106 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP For R18 and R19, and related hardware, in the same location, but turned 180 degrees. Refer toSWPM 20-81-22 as an accepted procedure. (f) 2 10-60450-5 Fuel Pump Power (GFI) Relay Socket Install / Kept 9

R18 and R19 in the changed sockets. Refer toSWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. (g) 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / Kept

Between the flanges of R18 and R19 and the relay mounting panel. (c) 2 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 10

If necessary, on any bare metal around the relays. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 11

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is more than 0.0025 Ohms (2.5 milliohms), remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Use the Fuel Pump Power (GFI) Relay, LEACH P/N 9524G-10674, as a template to mark the new holes. Put the relay into the existing cutout, turned 180 degrees from its original position, then mark and drill the new holes. (e) It is not necessary to change the size or shape of the cut-out in the relay panel. The existing cut-out is acceptable to allow installation of relay turned 180 degrees. (f) Use the new holes for installation. The original holes are not used. (g) Install the existing connectors for R18 and R19 turned 180 degrees to agree with the changed sockets. Adjust wire bundles if necessary. Refer to SWPM 20-10-11 and SWPM 20-10-12, as accepted procedures. (h) Use Dymo M11 Tapewriter or equivalent to emboss the Decal. Use one, two or three pieces of tape, as necessary, for the decal. Trim the tape and decal, as necessary, to fit the locations shown in Detail A - AFTER. (i) Install the decal at the approximate location shown.

FIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 107 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 6, Configuration 2-3.

FIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 108 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 109 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 110 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R146 and R147. 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Remove / Keep 1

For R146 and R147 and related hardware. 2 10-60450-5 Fuel Pump Power (GFI) Relay Socket Remove / Keep Diameter 0.151 to 0.161 inch. (d) (e) 6

- Hole Drill 2 If necessary, remove the paint around the relay cutout, from the side of the panel that will be in contact with the relay. (a) - - Surface Clean 3

If necessary, on the bare surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 4

Approximately as shown. Use Dymo 358 Aluminium tape or equivalent. (h) 1

- Decal Make 5

To prepare to install the Decal and tape to cover holes. Use TT-N-95 or equivalent. Do not allow to evaporate, but wipe dry with a clean cloth. - - Surface Clean 6

Remove the backing and install the Decal and tape on the P6-2 panel. Take care not to contaminate the adhesive and make sure the tape has sufficient clearance to avoid contact with the new relay spacers and does not overlap the relay cut-out. (i) 5 DYMO 358 (3M 425 optional) Tape and Decal Install 7

The contact surfaces of the relays and the panel to remove contamination. (b) - - Surface Clean 8

FIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 111 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP For R146 and R147, and related hardware, in the same location, but turned 180 degrees. Refer toSWPM 20-81-22 as an accepted procedure. (f) 1 10-60450-5 Fuel Pump Power (GFI) Relay Socket Install / Kept 9

R146 and R147 in the changed sockets. Refer toSWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. (g) 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / Kept

Between the flange of R146 and R147 and the relay mounting panel. (c) 2 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 10

If necessary, on any bare metal around the relays. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 11

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is more than 0.0025 Ohms (2.5 milliohms), remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Use the Fuel Pump Power (GFI) Relay, LEACH P/N 9524G-10674, as a template to mark the new holes. Put the relay into the existing cutout, turned 180 degrees from its original position, then mark and drill the new holes. (e) It is not necessary to change the size or shape of the cut-out in the relay panel. The existing cut-out is acceptable to allow installation of relay turned 180 degrees. (f) Use the new holes for installation. The original holes are not used. (g) Install the existing connectors for R146 and R147 turned 180 degrees to agree with the changed sockets. Adjust wire bundles if necessary. Refer to SWPM 20-10-11 and SWPM 20-10-12, as accepted procedures. (h) Use Dymo M11 Tapewriter or equivalent to emboss the Decal. Use one, two or three pieces of tape, as necessary, for the decal. Trim the tape and decal, as necessary, to fit the locations shown in Detail A - AFTER. (i) Install the decal at the approximate location shown.

FIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 112 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThis Figure applies only to: Group 7, Configuration 2-3; Group 9, Configuration 2-3.

FIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 113 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 114 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 115 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
MORE DATA QTY IDENTIFICATION NAME TASK STEP R146 and R147. 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Remove / Keep 1

For R146 and R147 and attaching hardware. 2 10-60450-5 Fuel Pump Power (GFI) Relay Socket Remove / Keep Diameter 0.151 to 0.161 inch. (d) (e) 6

- Holes Drill 2 If necessary, remove the paint around the relay cutout, from the side of the panel that will be in contact with the relay. (a) - - Surface Clean 3

If necessary, on the bare surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE Chemical Conversion Coating Apply 4

Approximately as shown. Use Dymo 358 Aluminium tape or equivalent. (h) 1

- Decal Make 5

To prepare to install the Decal and tape to cover holes. Use TT-N-95 or equivalent. Do not allow to evaporate, but wipe dry with a clean cloth. - - Surface Clean 6

Remove the backing and install the Decal and tape on the P6-2 panel. Take care not to contaminate the adhesive and make sure the tape has sufficient clearance to avoid contact with the new relay spacers and does not overlap the relay cut-out. (i) 5 DYMO 358 (3M 425 optional) Tape and Decal Install 7

The contact surfaces of the relays and the panel to remove contamination. (b) - - Surface Clean 8

FIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 116 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP For R146 and R147, and related hardware, turned 180 degrees. Refer toSWPM 20-81-22 as an accepted procedure. (f) 2 10-60450-5 Fuel Pump Power (GFI) Relay Socket Install / Kept 9

R146 and R147 in the changed sockets. Refer toSWPM 20-81-22 as an accepted procedure for installation of similar LEACH relays. (g) 2 S283A004-1 (LEACH P/N 9524G-10674) Fuel Pump Power (GFI) Relay Install / Kept

Between the flanges of R146 and R147 and the relay mounting panel. (c) 2 0.0025 OHMS (2.5 MILLIOHMS) Resistance Measure 10

If necessary, on any bare metal around the relays. Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, TYPE 1 Epoxy Primer Apply 11

(a) Abrasive clean by Hand or with a rotary brush in accordance with APPENDIX A, Paragraph 2.a. (b) Use Solvent to clean the contact surfaces in accordance with APPENDIX A, Paragraph 2.b. (c) Make sure that the resistance is 2.5 milliohms or less in accordance with APPENDIX A, Paragraph 5.b. If the resistance measurement is more than 0.0025 Ohms (2.5 milliohms), remove the relay, clean the faying surfaces, install the relay and measure the bonding resistance again. (d) Use the Fuel Pump Power (GFI) Relay, LEACH P/N 9524G-10674, as a template to mark the new holes. Put the relay into the existing cutout, turned 180 degrees from its original position, then mark and drill the new holes. (e) It is not necessary to change the size or shape of the cut-out in the relay panel. The existing cut-out is acceptable to allow installation of relay turned 180 degrees. (f) Use the new holes for installation. The original holes are not used. (g) Install the existing connectors for R146 and R147 turned 180 degrees to agree with the changed sockets. Adjust wire bundles if necessary. Refer to SWPM 20-10-11 and SWPM 20-10-12, as accepted procedures. (h) Use Dymo M11 Tapewriter or equivalent to emboss the Decal. Use one, two or three pieces of tape, as necessary, for the decal. Trim the tape and decal, as necessary, to fit the locations shown in Detail A - AFTER. (i) Install the decal at the approximate location shown.

FIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 117 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTNOTE:APPENDIX A contains electrical bonding data out of BAC5117-4 and BAC5117-6. Operators may use the electrical bonding data in APPENDIX A or BAC5117-4 or BAC5117-6 as applicable. 1. DIRECT STANDARD GROUND STUD INSTALLATION

FIGURE1: DIRECT STANDARD GROUND STUD INSTALLATION a. Surface Preparation (1) Clean the structure surface in accordance with APPENDIX A, Paragraph 2.a. (CM1) and/or Paragraph 2.b. (CM3). (2) Clean a sufficient amount of the surface to ensure the entire area under the corrosion protective washer 1 is clean. (3) Clean the terminal or terminals in accordance with APPENDIX A, Paragraph 2.b. (CM3). (4) Clean the corrosion protective washer 1 in accordance with APPENDIX A, Paragraph 2.b. (CM3). b. Direct Ground Stud Installation (1) Install the direct ground stud and terminal or terminals. (2) Torque the self-locking nut to 35-40 inch-pounds. 2. SURFACE PREPARATION AND CLEANING FOR ELECTRICAL BOND a. Abrasive Clean by Hand (CM1) (Excerpts from; SWPM 20-20-00, 2.A. Cleaning Procedure 1 or SOPM 20-11-03, 3.B. Cleaning Method CM1, (1) Hand Application of Abrasives)

Appendix A: ELECTRICAL BONDING (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 118 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTCAUTION:DO NOT USE THE ABRASIVE MATERIAL ON MATERIAL DIFFERENT FROM THE TYPE ON WHICH IT WAS FIRST USED. (1) Clean the specified surface by hand, using one of the following abrasive materials: (a) Scotch - Brite Pad (b) Garnet Sandpaper (c) Wet/Dry Sandpaper (2) Use a circular motion with the abrasive material. (3) Continue until the coating is removed and the aluminum surface is bright. Remove a minimum amount of aluminum. (4) If the surface finish includes Corrosion Inhibiting Compound (CIC) applied on top of paint or primer, remove the CIC a minimum of 0.10 inch beyond the area where the paint and primer is removed. Use solvent cleaning method in accordance with APPENDIX A, Paragraph 2.b. (CM3) to remove the CIC. (5) Do not allow the cleaned bonding surface to be contaminated. (6) Remove all temporary protective coatings or masking from a cleaned bonding surface just prior to assembly of a bond. (7) Clean the mating bonding surfaces again, in accordance with APPENDIX A, Paragraph 2.b. (CM3). b. Solvent Clean (CM3) (Excerpts from; SWPM 20-20-00, 2.E. Cleaning Procedure 5 or SOPM 20-11-03, 3.D. Cleaning Method CM3) CAUTION:BE SURE TO USE A SOLVENT THAT AGREES WITH THE SURFACE TO BE CLEANED. (1) Solvent clean the surface. (a) Use a solvent from this list: 1) Acetone 2) Ethyl alcohol, denatured 3) Isopropyl alcohol 4) Methyl Ethyl Ketone - sec-butyl alcohol, 1 - to - 1 mix 5) Methyl Propyl Ketone 6) Solvents with FB code in BAC5750
Appendix A: ELECTRICAL BONDING (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 119 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT(b) Solvents used for final cleaning shall be transferred from the original containers only to new or dedicated clean containers using new or dedicated clean equipment. (c) Dispense solvent onto a clean wiper, BMS15-5 Class A. Do not dip wiper into solvent container. (d) Rub the surface to be cleaned with solvent soaked wiper. Immediately wipe dry with a clean, dry wiper. Do not allow solvent to evaporate to dryness. It may be necessary to remove residue with a second dry wiper when using slow-evaporating solvents. (e) Frequently exchange soiled wiper for a clean one. (f) If unwanted matter stays, it could be because of fast solvent evaporation. Try to clean a smaller area at one time. (g) Repeat steps c. through e. until the wiper shows no soil. 3. TEST EQUIPMENT USED IN AREAS SUBJECT TO COMBUSTION, FIRE AND EXPLOSIONS a. The test equipment to be used in Fire Hazard areas or Flammable leakage zones, must be approved by Factory Mutual Approval Standard 3610 or qualified to Underwriters Laboratory (UL) Standard 913, for Class I, Group A, Atmosphere. b. The following meters are approved for use in areas subject to combustion, fire, and explosions as defined in UL Standard 913 for a Class I, Group A, Atmosphere: (1) AVTRON Manufacturing Incorporated - Model T477W Bonding Meter. (2) BCD Electronics Ltd. - Model M1 Bonding Meter, serial number A0000112 and on. 4. REQUIREMENTS a. All designated bonds and all designated grounds must be tested to make sure that the resistance requirements specified in the service bulletin are met. Sampling is not allowed. b. Measure the resistance of designated bonds and designated grounds between the points specified in the service bulletin. c. Only certified personnel are allowed to make resistance measurements of designated bonds and grounds. 5. TEST METHODS a. GENERAL WARNING:USE OF THE WRONG TEST EQUIPMENT MAY CAUSE FIRE OR EXPLOSION (1) Choose test equipment for measuring resistance as follows:

Appendix A: ELECTRICAL BONDING (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 120 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTNOTE:Make sure that the meter to be used has a measuring range equal to or exceeding the maximum allowable resistance for the measurement to be made. (a) When measuring resistance in areas subject to combustion, fire and explosion, use only the test equipment specified in accordance with APPENDIX A, Paragraph 3. Visually check test equipment prior to taking it to areas subject to combustion, fire and explosion and make sure that no physical damage has occurred which might have impaired the vapor tightness of the instrument housing. (2) All meters used for bonding resistance measurement must have a certified measuring range equal to or exceeding the maximum allowable resistance for the measurement to be made. (3) For meters which have range selectors, readings must be taken using the lowest range that contains the measurement to be made. (4) Impressions on electrical wire terminals caused by resistance measuring equipment that do not expose the base metal are acceptable. (5) Use the following conversion factors to convert from a meter reading displayed in milliohms / microhms to an equivalent value in ohms. Ohms = Milliohms / 1,000 Ohms = Microhms / 1,000,000 (6) Do not use test equipment on circuits which have power applied. b. RESISTANCE MEASUREMENT FROM THE GFI RELAY TO THE RELAY MOUNTING PANEL

Appendix A: ELECTRICAL BONDING (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 121 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERTFIGURE2: RESISTANCE MEASUREMENT FROM THE GFI RELAY TO THE RELAY MOUNTING PANEL

Appendix A: ELECTRICAL BONDING (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 122 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT(1) Select the applicable test equipment in accordance with APPENDIX A, Paragraph 3. (2) Put one ohmmeter probe anywhere on the Relay and the other probe on the Mounting Panel, 0.25 Inch from the flange of the Relay or from the spacer, as applicable. (3) If the Panel and/or the Relay is covered by a surface finish, remove a sufficient amount of the surface finish to allow the probes to contact the structure bonding surface. NOTE:Carefully pierce the surface finish with the probes to make contact with the structure bonding surface. (4) Make sure the resistance value shown on the ohmmeter is less than or equal to the resistance requirement specified in the service bulletin. (5) After testing is complete, re-apply chemical conversion coating to areas disturbed by the test probes. Refer to SOPM 20-43-03 as an accepted procedure. For areas disturbed by the test probes where the original finish included BMS 10-20 Type II, repair the chemical conversion coating, then repair the BMS 10-20 Type II. Refer to SOPM 20-43-03 and SOPM 20-60-02 as accepted procedures.

Appendix A: ELECTRICAL BONDING (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 23, 2009 737-28A1212 Revision 2 October 18, 2012 123 of 123 BOEING SERVICE BULLETIN 737-28A1212 ALERT ALERT