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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.
9E991ECCN:
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Unpublished Work.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, Dreamliner™, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and 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 737-28A1212Revision 2: October 18, 2012 1 of 123
2.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 2 of 123 BOEING SERVICE BULLETIN 737-28A1212
ALERTALERT
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
S u m m a r y9
1. PLANNING INFORMATION ........................................ 1 3 A . E f f e c t i v i t y ............................................... 1 3
1. Airplanes ............................................ 1 3 2 . S p a r e s A f f e c t e d ........................................ 2 9 B. Concurrent Requirements ...................................... 2 9 C. Reason ................................................ 2 9 D. Description .............................................. 3 1 E. Compliance .............................................. 3 4 F . A p p r o v a l ............................................... 3 4 G. Manpower .............................................. 3 5 H. Weight and Balance Changes .................................... 4 0 I. Electrical Load Data ......................................... 4 0 J . R e f e r e n c e s .............................................. 4 1
1. Existing Data: ......................................... 4 1
2. Data Supplied with this Service Bulletin: ........................... 4 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 2 K. Publications Affected ........................................ 4 2 L. Interchangeability and Intermixability of Parts ........................... 4 2 M. Software Accomplishment Summary ................................ 4 3
2. MATERIAL INFORMATION ........................................ 4 5 A. Material - Price and Availability ................................... 4 5 B. Industry Support Information .................................... 4 6 C. Parts Necessary for Each Airplane ................................. 4 6 1 . K i t s / P a r t s : ........................................... 4 6
2. Parts and Materials Supplied by the Operator: ........................ 4 9
3. Parts Modified and Reidentified: ............................... 5 1
4. Parts Removed and Not Replaced: .............................. 5 1 D. Parts Necessary to Change Spares ................................. 5 1 E. Special Tooling - Price and Availability ............................... 5 1 F. Special Tooling Necessary to do this Service Bulletin ....................... 5 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 5 3 A. GENERAL INFORMATION ..................................... 5 3 B. WORK INSTRUCTIONS ....................................... 5 4 FIGURE 1: M181, M182, M183 RELAY MODULE ASSEMBLY - REPLACEMENT [Group 1, 8] .... 5 8 FIGURE 2: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 2, Configuration 1 ] ................................................ 5 9 FIGURE 3: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 3, 10-13, Configuration 1] ......................................... 6 1 FIGURE 4: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 4, Configuration 1 ] ................................................ 6 3 FIGURE 5: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 5, Configuration 1 ] ................................................ 6 5 FIGURE 6: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 6, Configuration 1 ] ................................................ 7 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 3 of 123 BOEING SERVICE BULLETIN 737-28A1212
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FIGURE 7: P6-2 RELAY PANEL - FUEL PUMP POWER RELAY - REPLACEMENT [Group 7, 9, Configuration 1 ] ................................................ 7 6 FIGURE 8: W0044 WIRE BUNDLE - LOCATION [Group 2-3, 6-7, 9-13, Configuration 1] ....... 8 2 FIGURE 9: WIRE BUNDLE W0044 - WIRING CHANGES [Group 2, Configuration 1] ......... 8 3 FIGURE 10: WIRE BUNDLE W0044 - WIRING CHANGES [Group 3, 12, Configuration 1] ....... 8 5 FIGURE 11: WIRE BUNDLE W0044 - WIRING CHANGES [Group 6-7, 9, Configuration 1] ....... 8 7 FIGURE 12: WIRE BUNDLE W0044 - WIRING CHANGES [Group 10, Configuration 1] ......... 8 8 FIGURE 13: WIRE BUNDLE W0044 - WIRING CHANGES [Group 11, 13, Configuration 1] ....... 8 9 FIGURE 14: FUEL BOOST PUMP CONNECTOR - WIRE LOCATION [Group 8] ............ 9 1 FIGURE 15: FUEL BOOST PUMP GROUNDS - WIRE LOCATION [Group 8] .............. 9 2 F I G U R E 1 6 : F U E L B O O S T P U M P C O N N E C T O R - W I R I N G C H A N G E S [ G r o u p 8 ] ........... 9 3 FIGURE 17: FUEL BOOST PUMP CONNECTOR - WIRE LOCATION [Group 8] ............ 9 4 FIGURE 18: FUEL BOOST PUMP GROUNDS - WIRE LOCATION [Group 8] .............. 9 5 F I G U R E 1 9 : F U E L B O O S T P U M P C O N N E C T O R - W I R I N G C H A N G E S [ G r o u p 8 ] ........... 9 6 FIGURE 20: FUEL BOOST PUMP CONTROL GROUND FAULT INTERRUPTER (GFI) CONTROL RELAY
- REFERENCE [Group 2-7, 9-13, Configuration 1] ...................... 9 7 FIGURE 21: WIRE BUNDLE W0044 - WIRING CHANGES [Group 1, 8] ................. 9 8 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] .............................. 9 9 FIGURE 23: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN [Group 5, Configuration 2-3] ................................................. 1 0 3 FIGURE 24: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN [Group 6, Configuration 2-3] ................................................. 1 0 8 FIGURE 25: P6-2 RELAY PANEL - FUEL PUMP POWER GFI RELAY - TURN [Group 7, Configuration 2-3;
Group 9, Configuration 2-3] .................................. 1 1 3 Appendix A: ELECTRICAL BONDING ................................... 1 1 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 4 of 123 BOEING SERVICE BULLETIN 737-28A1212
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Commercial Airplanes 737 Service Bulletin ALERT Revision Transmittal SheetNumber: 737-28A1212Original 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.
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Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 5 of 123
REASON 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.
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Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 6 of 123 BOEING SERVICE BULLETIN 737-28A1212
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8. 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 737-28A1212Revision 2: October 18, 2012 7 of 123 BOEING SERVICE BULLETIN 737-28A1212
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26. 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, 2009Original Issue:
August 27, 2010Revision 1:
October 18, 2012Revision 2:
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Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 8 of 123 BOEING SERVICE BULLETIN 737-28A1212
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-28A1212Original 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.
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Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 9 of 123
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.
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.
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Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 10 of 123 BOEING SERVICE BULLETIN 737-28A1212
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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.
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.
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Original Issue: July 23, 2009 737-28A1212Revision 2: October 18, 2012 11 of 123 BOEING SERVICE BULLETIN 737-28A1212
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BOEING SERVICE BULLETIN 737-28A1212
ALERT ALERT I GROUPS 2-7, 9-13, CONFIGURATION 1:
P6 LOAD CONTROL CENTER:
REPLACE 6 OR 8 RELAYS WITH GFI RELAYS.
GROUPS 2-3, 6-7, 9-13, CONFIGURATION 1:
CHANGE BOOST PUMP WIRE TERMINATIONS ON THE WOO44 WIRE BUNDLE.
GROUPS 2-7, 9-13, CONFIGURATION 1-2:
P6 LOAD CONTROL CENTER:
INSTALL A GROUND BONDING JUMPER.
GROUP 5-7, 9, CONFIGURATION 1-3:
REMOVE 2 GFI RELAYS AND INSTALL TURNED BY 180 DEGREES, IN THE SAME LOCATION. J83240 Original Issue: July 23, 2009 Revision 2: October 18, 2012 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-28A1212 Work - See page 1 for details. 12 of 123