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Commercial Airplanes 737 Service Bulletin Number: 737-28A1216 Original Issue: July 29, 2010 Revision 2: November 12, 2012 ATA System: 2822 SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the Center and Auxiliary Fuel Tank Boost Pumps 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 © 2010 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Unpublished Work.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 29, 2010 737-28A1216Revision 2: November 12, 2012 1 of 439
7.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 2 of 439 BOEING SERVICE BULLETIN 737-28A1216
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Table of Contents
Revision Transmittal Sheet7
S u m m a r y..................................................... 1 1
1. PLANNING INFORMATION ........................................ 1 9 A . E f f e c t i v i t y ............................................... 1 9
1. Airplanes ............................................ 1 9 2 . S p a r e s A f f e c t e d ........................................ 3 0 B. Concurrent Requirements ...................................... 3 0 C. Reason ................................................ 3 0 D . D e s c r i p t i o n .............................................. 3 2 E. Compliance .............................................. 3 8 F . A p p r o v a l ............................................... 3 8 G. Manpower .............................................. 3 9 H. Weight and Balance Changes .................................... 8 5 I. Electrical Load Data ......................................... 8 5 J . R e f e r e n c e s .............................................. 8 6
1. Existing Data: ......................................... 8 6
2. Data Supplied with this Service Bulletin: ........................... 8 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 8 6 K. Publications Affected ........................................ 8 7 L. Interchangeability and Intermixability of Parts ........................... 8 7 M. Software Accomplishment Summary ................................ 8 7
2. MATERIAL INFORMATION ........................................ 8 9 A. Material - Price and Availability ................................... 8 9 B. Industry Support Information .................................... 9 2 C . P a r t s N e c e s s a r y f o r E a c h A i r p l a n e ................................. 9 2 1 . K i t s / P a r t s : ........................................... 9 2
2. Parts and Materials Supplied by the Operator: ....................... 1 1 8
3. Parts Modified and Reidentified: ............................... 1 1 9
4. Parts Removed and Not Replaced: ............................. 1 1 9 D. Parts Necessary to Change Spares ................................ 1 1 9 E. Special Tooling - Price and Availability .............................. 1 1 9 F. Special Tooling Necessary to do this Service Bulletin ...................... 1 1 9
3. ACCOMPLISHMENT INSTRUCTIONS ................................. 1 2 1 A. GENERAL INFORMATION .................................... 1 2 1 B. WORK INSTRUCTIONS ...................................... 1 2 2 FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16] ........ 1 4 9 FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 19-20] ........... 1 5 0 FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 1-13, 15-16] ............................ 1 5 1 FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 [Group 1-16, 21-29, 31] ......... 1 5 4 FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 [Group 1-16, 21-29, 31] ......... 1 5 7 FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 19-20] ................................................. 1 6 0 FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30] ............ 1 6 3 FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30] ............ 1 6 5 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 3 of 439 BOEING SERVICE BULLETIN 737-28A1216
FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30] ............ 1 6 8 FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30] ............ 1 7 0 FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16, 19-20] . 173 FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 1-13, 15-16] .......... 1 7 4 FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 19-20] ............. 1 7 7 FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST [Group 1 - 1 3 , 1 5 - 1 6 , 1 9 - 2 0 ] ...................................... 1 8 0 FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS [Group 1-13, 1 5 - 1 6 , 1 9 - 2 0 ] ......................................... 1 8 3 FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group 1 - 1 3 , 1 5 - 1 6 ] .......................................... 1 8 5 FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group 1 9 - 2 0 ]............................................. 1 8 7 FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS [Group 1-13, 15-16, 19-20] . . 189 FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 1-16, 21-29, 31] ...... 1 9 2 FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 1-16, 21-29, 31] . . . 194 FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 [Group 1, 21] ............... 1 9 5 FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036 [Group 2-3, 22-23] ............ 1 9 8 FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036 [Group 4-5, 24] .............. 2 0 1 FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 [Group 6-7, 25] .............. 2 0 4 FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036 [Group 8, 26] ............... 2 0 7 FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 [Group 9, 31] ............... 2 1 0 FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036 [Group 10-11, 27-28] ........... 2 1 3 FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036 [Group 12, 29] .............. 2 1 6 FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036 [Group 13] ................ 2 1 9 FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 [Group 14] ................ 2 2 2 FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 [Group 15] ................ 2 2 5 FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036 [Group 16] ................ 2 2 8 FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 17-20, 30] ......... 2 3 1 FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 17-20, 30] ...... 2 3 3 FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] .............. 2 3 4 FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] .............. 2 3 7 FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] .............. 2 4 0 FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 4 3 FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 4 6 FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 4 9 FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 5 2 FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 5 5 FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 5 8 FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 1-16, 21-29, 31] . . . 261 FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 [Group 1, 21] ............... 2 6 2 FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 1] ...... 2 6 4 FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 2] ...... 2 6 6 FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 [Group 3, 16, 23] ............. 2 6 8 FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 1] ........ 2 7 0 FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 2] ........ 2 7 2 FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 [Group 5, 8, 24, 26] ............ 2 7 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 4 of 439 BOEING SERVICE BULLETIN 737-28A1216
FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 1] ...... 2 7 6 FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 2] ...... 2 7 8 FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044 [Group 9, 31] ............... 2 8 0 FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044 [Group 10, 27] .............. 2 8 2 FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 1] ..... 2 8 4 FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 2] ..... 2 8 6 FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044 [Group 13] ................ 2 8 8 FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044 [Group 7] ................. 2 9 0 FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 1] ....... 2 9 2 FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 2] ....... 2 9 4 FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 1] ..... 2 9 6 FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 2] ..... 2 9 8 FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 1] ....... 3 0 0 FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 2] ....... 3 0 2 FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 17-20, 30] ...... 3 0 4 FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 1] ....... 3 0 5 FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] ....... 3 0 8 FIGURE 69: CONNECTION OF WIRE BUNDLE W044 [Group 17, Configuration 1] .......... 3 1 1 FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] ....... 3 1 4 FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] ....... 3 1 7 FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] ....... 3 2 0 FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] ....... 3 2 3 FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] ....... 3 2 6 FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30] .............. 3 2 9 FIGURE 76: CONNECTION OF WIRE BUNDLE W044 [Group 19, 30, Configuration 1] ........ 3 3 2 FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30, Configuration 2] ..... 3 3 5 FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] ....... 3 3 8 FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] ....... 3 4 1 FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] ....... 3 4 4 FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] ....... 3 4 7 FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 [Group 1-16, 19-20] ................................................. 3 5 0 FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 1-16, 21-29, 31] ..... 3 5 4 FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 17-20, 30] ........ 3 5 7 FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 8, 16, 26] ........... 3 6 0 FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 1-7, 9-15, 21-25, 27-29, 31] . 362 FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 17-20, 30] .......... 3 6 4 FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group 1 - 1 6 ].............................................. 3 6 7 FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group 1 9 - 2 0 ]............................................. 3 7 0 FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 1-16, 21-29, 31] ...... 3 7 3 FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 17-20, 30] ......... 3 7 5 FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 2 1 - 2 9 , 3 1 ] ........................................... 3 7 7 FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 3 0 ]............................................... 3 8 0 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 5 of 439 BOEING SERVICE BULLETIN 737-28A1216
FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 2 1 - 2 9 , 3 1 ] ........................................... 3 8 4 FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 3 0 ]............................................... 3 9 0 FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] ................... 3 9 6 FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 0 0 FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] ................... 4 0 4 FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 1 0 FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR AIRPLANE WITH AIRSTAIRS [Group 14, 21-29, 31] .................... 4 1 6 FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 1 8 FIGURE 102: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] ................... 4 2 0 FIGURE 103: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 2 2 FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS [Group 14, 17-18, 21-31] ................................... 4 2 4 FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS [Group 14, 17-18, 21-31] ............................ 4 3 0 FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] .............................. 4 3 6 FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ................................ 4 3 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 6 of 439 BOEING SERVICE BULLETIN 737-28A1216
Commercial Airplanes 737 Service Bulletin Revision Transmittal SheetNumber: 737-28A1216Original Issue: July 29, 2010 Revision 2: November 12, 2012 ATA System: 2822 SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the Center and Auxiliary Fuel Tank Boost Pumps This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is related to this service bulletin.
No more work is necessary on the airplane(s) Groups 1-16, 19-31 changed in accordance with Revision 1 of this service bulletin, dated March 26, 2012. More work is necessary for airplanes Group 17-18 that changed the airplanes in accordance with Part 7 of Revision 1 of this service bulletin dated March 26, 2012. These airplanes need to do also the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test in accordance with PART 8 if the Auxiliary Tank is installed.
REASON FOR REVISION This revision is sent to tell the operators that Figures 8, 10, 84, 87, 94, 95, 98, 99, 100, 101, 102, 103 have been revised to incorporate minor typographical changes. This revision also changes the Weight and Moments table, that are based on airplanes with and without AUX Tank. Also the Electrical Load Data tables are identified with titles, and missing airplane groups are added to the applicability of the tables. This revision also changes supplemental kit 65C37854-16 for manufacturing purpose. The quantity of the labels in drawing 65C38484-30 is changed from 2 to 1 and, the quantity of 65C38484-30 is changed from 1 to 2 in the supplemental kit 65C37854-16. Also PART 7, PART 8, and PART 9 are added to Summary page, Action paragraph, and to Planning section, Description paragraph.
These sections were changed:
1. Summary:
a. Action: added the descriptions of PART 7, PART 8, and PART 9.
b. Compliance: changed the compliance time from the date of Revision 2 of this service bulletin.
2. Planning Information:
a. Paragraph 1. B., Concurrent Requirements: changed the revision level and date of the concurrent BAE service bulletin, and changed the revision level of the concurrent Boeing service bulletin.
b. Paragraph 1. D., Description: added the descriptions of PART 7, PART 8, and PART 9.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 7 of 439
c. Paragraph 1.E., Compliance: changed the compliance time from the date of Revision 2 of this service bulletin.
d. Paragraph 1.H., Weight and Balance Changes, page 81: Changed the titles of the tables, changed the weight and moments tables for airplanes with and without AUX Tank.
e. Paragraph 1.I, Electrical Load Data: Added titles to the tables and added missing airplane groups to the tables.
3. Material Section:
a. Paragraph 2.A., Material and Price Availability: Added supplemental kit 65C37854-16 to the table applicable to airplane groups 17-20, changed footnote (a), and added new footnote (c). Added a new table with the new top kit 65C38471-12 for groups 17-18.
b. Paragraph 2.C.1., Kits/Parts: The quantity of the 65C38484-30 is changed from 1 to 2 in the supplemental kit 65C37854-16.
c. Paragraph 2.C.1., Kits/Parts: Removed duplicate lines from tables.
d. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added Seal Plugs.
4. Accomplishment Instructions:
a. Paragraph 3.B.8., PART 8: Added the Auxiliary Tank Fuel Boost Pump Auto Shutoff Functional test that needs to be done for airplanes that have an AUX Tank Installed.
b. Figure 8, Figure 10, Figure 84, and Figure 87: Added footnote related to additional seal plugs necessary for airplanes with wire provisions for AUX Tank and with no AUX Tank installed.
c. Figure 94 and Figure 95: moved call-outs for View "A" and view "B" to a different location, changed the reference lines for two dimensions, corrected step instructions, changed the quantity of fasteners and holes in step instructions table.
d. Figure 98 and Figure 99: replaced the word "Shim" with "Filler", deleted one hole related to step instruction 1 that was shown in error, added the filler in section C-C and revised section D-D, added a footnote to step 1, added fillers to step instruction 2, re-numbered the footnotes, changed step instruction 9.
e. Figure 100 and Figure 101: Showed the filler between the J2802 relay box and the stanchion.
f. Figure 102 and Figure 103 sheet 1 of 2, cross sections A-A and B-B: Showed the fillers between the J2802 relay box and the stanchion, corrected fastener size location.
g. Figure 104: Corrected number of holes and fasteners in the step instruction table.
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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 8 of 439 BOEING SERVICE BULLETIN 737-28A1216
REVISION HISTORY July 29, 2010Original Issue:
March 26, 2012Revision 1:
November 12, 2012Revision 2:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 9 of 439 BOEING SERVICE BULLETIN 737-28A1216
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 10 of 439 BOEING SERVICE BULLETIN 737-28A1216
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Commercial Airplanes 737 Service Bulletin SummaryNumber: 737-28A1216Original Issue: July 29, 2010 Revision 2: November 12, 2012 ATA System: 2822 SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the Center and Auxiliary Fuel Tank Boost Pumps
CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND This service bulletin is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis shows that fuel boost pumps that run dry could cause an overheat condition external of the fuel pump explosion resistance area that is open to the fuel pump inlet. An overheat condition in this area could possibly cause an unwanted ignition source for the fuel vapors in the fuel tank and could cause a fire or explosion.
This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system for the fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped, also in the auxiliary fuel tank. Time delay relays are installed in the new J2802 box assembly that will shut off the fuel boost pumps if the pumps operate with continuous low pressure for 15 seconds. The 15 second time delay relay prevents extended dry operation of the fuel boost pumps and allows for sufficient time for fuel pump inlet reprime to prevent nuisance automatic shutoff. The flight crew stays in primary control, with the auto shutoff system as a backup, to stop the fuel boost pumps after a low pressure indication.
The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel tank against sparks possibly caused by friction overheat damage.
This change affects the Fuel Systems Airworthiness Limitations section of Boeing document "737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational check of the boost pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" will be added to include an operational check of the fuel boost pump automatic shutoff system for the auxiliary fuel tank, if installed by Boeing. This change also affects Section 1 and Section 3 of the FAA Approved Airplane Flight Manual (AFM).
ACTION (PRR 35442-RS) The work instructions are divided into 31 airplane groups, 9 parts.
PART 1, PART 2, PART 3, PART 4, and PART 5 work instructions are divided into 3 work packages because of the different wire bundle changes and airplanes without and with Airstairs PART 6 work instructions are for Operators that already ordered the kit from the original release, and want to re-work the kit for airplanes with Airstairs.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 11 of 439
PART 7, PART 8, PART 9 provide instructions to change the J2802 relay box for airplanes that incorporated the original release of the service bulletin.
NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service bulletin in the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these airplanes. If Boeing is not notified about the Auxiliary Tanks, Boeing will assume that the airplanes in these groups do not have Auxiliary (AUX) tanks and no AUX Tank changes to the affected manuals will be done.
Group 1-13, 15-16:
PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318 and R3321.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Group 17-18:
PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX) FUEL
TANKS, AND AIRSTAIRS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install the J2802 box assembly.
3. Work Package 3:
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Original Issue: July 29, 2010 737-28A1216Revision 2: November 12, 2012 12 of 439 BOEING SERVICE BULLETIN 737-28A1216