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Original Issue: January 11, 2006 Revision 2: May 21, 2009 737-28A1206 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 286
ALERT ALERT Commercial Airplanes 737
ALERTALERT Service Bulletin Number: 737-28A1206 Original Issue: January 11, 2006 Revision 2: May 21, 2009 ATA System: 2822 3152 SUBJECT: FUEL - Distribution - Center Fuel Tank Boost Pump Auto Shutoff and Master Caution Logic Change
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2006 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document or otherwise.
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Table of Contents Original Issue: January 11, 2006 Revision 2: May 21, 2009 737-28A1206 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 286 BOEING SERVICE BULLETIN 737-28A1206
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Table of Contents Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71
2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 71
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 72 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 72
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 89
3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90
4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 92
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94 FIGURE 1: J4 JUNCTION BOX - REMOVAL AND SALVAGE . . . . . . . . . . . . . . . . . . . . . 106 FIGURE 2: J4 JUNCTION BOX BOTTOM ASSEMBLY - RELAY AND MARKER INSTALLATION. . . 109 FIGURE 3: J4 JUNCTION BOX BOTTOM ASSEMBLY- RECEPTACLE, RELAY AND MARKER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113 FIGURE 4: J4 JUNCTION BOX - J4 JUNCTION BOX BOTTOM ASSEMBLY, TRANSFORMER AND MARKER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 116 FIGURE 5: J4 JUNCTION BOX - MARKER AND RELAY INSTALLATION . . . . . . . . . . . . . . . 120 FIGURE 6: W0094 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 122 FIGURE 7: WIRE BUNDLE W0094 WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 123 FIGURE 8: J4 JUNCTION BOX - MARKER AND RELAY INSTALLATION . . . . . . . . . . . . . . . 125 FIGURE 9: W0094 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 128
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FIGURE 10: WIRE BUNDLE W0094 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 129 FIGURE 11: J20 JUNCTION BOX - REMOVAL AND SALVAGE . . . . . . . . . . . . . . . . . . . 131 FIGURE 12: J20 JUNCTION BOX PLATE B - MARKER AND RELAY INSTALLATION. . . . . . . . 135 FIGURE 13: J20 JUNCTION BOX PLATE B - MARKER AND RELAY INSTALLATION. . . . . . . . 139 FIGURE 14: J20 JUNCTION BOX, PLATE A AND PLATE B - INSTALLATION . . . . . . . . . . . . 142 FIGURE 15: J20 JUNCTION BOX - REMOVAL AND SALVAGE . . . . . . . . . . . . . . . . . . . 147 FIGURE 16: J20 JUNCTION BOX PLATE A - MARKER AND RELAY INSTALLATION. . . . . . . . 151 FIGURE 17: J20 JUNCTION BOX LOWER PLATE A - MARKER AND RELAY INSTALLATION . . . 155 FIGURE 18: J20 JUNCTION BOX PLATE B - MARKER AND RELAY INSTALLATION. . . . . . . . 158 FIGURE 19: J20 JUNCTION BOX PLATE B - MARKER AND RELAY INSTALLATION. . . . . . . . 162 FIGURE 20: J20 JUNCTION BOX, PLATE A AND PLATE B - INSTALLATION . . . . . . . . . . . . 166 FIGURE 21: J20 JUNCTION BOX - REMOVAL AND SALVAGE . . . . . . . . . . . . . . . . . . . 171 FIGURE 22: J20 JUNCTION BOX PLATE B - MARKER AND RELAY INSTALLATION. . . . . . . . 173 FIGURE 23: J20 JUNCTION BOX PLATE B - MARKER AND RELAY INSTALLATION. . . . . . . . 177 FIGURE 24: J20 JUNCTION BOX, PLATE A AND PLATE B - INSTALLATION . . . . . . . . . . . . 181 FIGURE 25: W0072 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 186 FIGURE 26: WIRE BUNDLE W0072 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 187 FIGURE 27: P5-2 FUEL CONTROL MODULE REPLACEMENT . . . . . . . . . . . . . . . . . . . 189 FIGURE 28: P5-2 FUEL CONTROL MODULE REPLACEMENT . . . . . . . . . . . . . . . . . . . 191 FIGURE 29: P5-2 FUEL CONTROL MODULE REPLACEMENT . . . . . . . . . . . . . . . . . . . 193 FIGURE 30: P61-8 FUEL TEST PANEL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . 195 FIGURE 31: P6-3 PANEL CIRCUIT BREAKER INSTALLATION . . . . . . . . . . . . . . . . . . . 196 FIGURE 32: P6-3 PANEL CIRCUIT BREAKER INSTALLATION . . . . . . . . . . . . . . . . . . . 198 FIGURE 33: W0040 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 FIGURE 34: WIRE BUNDLE W0040 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 203 FIGURE 35: W0040 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 FIGURE 36: WIRE BUNDLE W0040 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 208 FIGURE 37: W0044 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 210 FIGURE 38: WIRE BUNDLE W0044 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 215 FIGURE 39: W0044 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 217 FIGURE 40: WIRE BUNDLE W0044 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 222 FIGURE 41: W2112 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 224 FIGURE 42: W0212 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 229 FIGURE 43: WIRE BUNDLE W0212 AND W2112 WIRING CHANGE. . . . . . . . . . . . . . . . . 230 FIGURE 44: W2218 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 232 FIGURE 45: W0422 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 237 FIGURE 46: WIRE BUNDLE W0422 AND W2218 WIRING CHANGE . . . . . . . . . . . . . . . . 238 FIGURE 47: W5158 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 240 FIGURE 48: WIRE BUNDLE W5158 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 243 FIGURE 49: W5160 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 245 FIGURE 50: WIRE BUNDLE W5160 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 250 FIGURE 51: W5160 WIRE BUNDLE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 251 FIGURE 52: WIRE BUNDLE W5160 WIRING CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 256 FIGURE 53: CONNECTOR RELOCATION ON J4 JUNCTION BOX - WIRE BUNDLES W0094, W5160, W5520, AND W6222 ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 258 FIGURE 54: CONNECTOR RELOCATION ON J4 JUNCTION BOX - WIRE BUNDLES W0094, W5160,
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W5520, AND W6222 WIRING CHANGES . . . . . . . . . . . . . . . . . . . . . . . . 259 FIGURE 55: J4 JUNCTION BOX RELAY INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . 262 FIGURE 56: W0094 WIRE BUNDLE ROUTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265 FIGURE 57: WIRE BUNDLE W0094 WIRING CHANGES . . . . . . . . . . . . . . . . . . . . . . . 266 FIGURE 58: P61-8 FUEL TEST PANEL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . 268 FIGURE 59: P61-8 FUEL TEST PANEL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . 270 FIGURE 60: P61-8 FUEL TEST PANEL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . 272 FIGURE 61: W0094 WIRE BUNDLE ROUTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 274 FIGURE 62: WIRE BUNDLE W0044 WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . 275 FIGURE 63: W0044 WIRE BUNDLE ROUTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 277 FIGURE 64: W0044 WIRE BUNDLE ROUTING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 282
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Original Issue: January 11, 2006 Revision 2: May 21, 2009 737-28A1206 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 286
ALERT ALERT Commercial Airplanes 737
ALERTALERT Service Bulletin Number: 737-28A1206 Revision Transmittal Sheet Original Issue: January 11, 2006 Revision 2: May 21, 2009 ATA System: 2822 3152 SUBJECT: FUEL - Distribution - Center Fuel Tank Boost Pump Auto Shutoff and Master Caution Logic Change This Revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION More work is necessary on airplanes changed as shown in the Original Issue of this service bulletin dated January 11, 2006, or changed as shown in Revision 1 of this service bulletin dated January 30, 2008, and did not incorporate the Emergency AD 2008-24-51 dated November 18, 2008. These airplanes need to perform the operational test given in Accomplishment Instructions, paragraph 3.B, Work Instructions, PART 3.
No more work is necessary on airplanes changed as shown in the Original Issue of this service bulletin dated January 11, 2006 or changed as shown in Revision 1 of this service bulletin dated January 30, 2008 and did accomplish Emergency AD 2008-24-51 dated November 18, 2008.
REASON FOR REVISION This revision is sent to tell Operators that Boeing received a report from one Operator that the Left Hand Fuel Boost Pump of the Center Wing Tank failed to shut off after being selected "OFF" by the flightcrew during flight on a 737-700 airplane. Subsequent to that report, the same failure was found on two additional airplanes.
Boeing determined that the failure was caused by a wire that was installed at a wrong location. During the incorporation of the service bulletin these operators terminated wire W0040-6402-14 incorrectly, to a different terminal block, and not to terminal block TB5060F as given in the instructions provided in Figure 33 and Figure 34, or Figure 35 and Figure 36. Wire W0040-6402-14 must be installed on Terminal Block TB5060F, terminal position 5. This terminal provides 115V AC from Transfer Bus 1, Section 2. If wire is installed incorrectly on terminal TB5060E or any other terminal block, the Auto Shutoff System will not function correctly and the Left Hand Center Tank Boost Pump may continue to operate after being selected off. This could result in a dry running pump. Fuel pumps that run dry and overheat could result in an ignition source in a fuel tank. This misswiring was the reason Airworthiness Directive AD 2008-24-51 was released and mandated by FAA on November 18, 2008.
This revision is sent to tell operators that the AMM 28-22-00 - Center Tank Boost Pump Auto Shutoff Functional Test has been changed to incorporate the requirements of the AD 2008-24-51. The new Center Tank Boost Pump Auto Shutoff Functional Test will detect if the wire W0040-6402-14 is incorrectly installed.
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Also this revision is sent to tell operators that the Accomplishment Instructions, paragraph 3.B., Work Instructions has been changed to a new format and grouped in two parts, PART 1 and PART 2. A new part, PART 3 has been added that provides work instructions for Operators that incorporated the Original Issue of this service bulletin dated January 11, 2006 or Revision 1 of this service bulletin dated January 30, 2008, and did not accomplish Emergency AD 2008-24-51 dated November 18, 2008.
These sections were changed:
1. Summary page, Action:
Changes were made to group existing actions in two parts, PART 1 and PART 2. PART 1 and PART 2 are applicable to airplanes that did not accomplish service bulletin. A new PART 3 has been added that provides work instructions for Operators that incorporated the Original Issue of this service bulletin dated January 11, 2006, or Revision 1 of this service bulletin dated January 30, 2008, and did not accomplish Emergency AD 2008-24-51 dated November 18, 2008.
2. Summary page, Compliance:
The compliance recommendation has been reset to 36 months from the date of Revision 2 of the service bulletin. The related NPRM and the related emergency AD have been referenced.
3. Planning information, Effectivity:
Airplane groups 1 through 18 have been divided in two configurations, configuration 1 formed by airplanes that did not incorporate the Original Issue or Revision 1 of this service bulletin, and configuration 2 formed by airplanes that incorporated the Original Issue of this service bulletin, or Revision 1 of this service bulletin, and did not accomplish Emergency AD 2008-24-51 dated November 18, 2008
4. Planning information, Reason:
A list with all changes has been added to this section.
5. Planning information, Description:
Changes were made to group existing actions in two parts, PART 1 and PART 2. PART 1 and PART 2 are applicable to airplanes that did not accomplish service bulletin original issue or revision 1. A new PART 3 has been added that provide work instructions for Operators that incorporated the original issue of this service bulletin dated January 11, 2006 or revision 1 of this service bulletin dated January 30, 2008 and did not accomplish Emergency AD 2008-24-51 dated November 18, 2008.
The "No More Work" statement for revision 1, that was missing, has been added.
The "No More Work" and "More Work" statements for revision 2 had been added.
6. Planning Information, Compliance:
The compliance recommendation has been reset to 36 months from the date of Revision 2 of the service bulletin. The related NPRM and the related emergency AD have been referenced.
7. Planning Information, Approval:
An AMOC (Alternative Method of Compliance) statement has been added for the Emergency Airworthiness Directive AD 2008-24-51 dated November 18, 2008.
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8. Planning information, Manpower:
A manpower table has been added for configuration 2 airplanes.
9. Material Information:
Kit ROLT, date, and prices are changed.
Changes are made to Kit 233A6253 - P61 Fuel Test Panel Installation to add the new panel part numbers BACP10U0187HC, BACP10U0412HC, and BACP10U0562HC.
Changes are made to the Parts and Materials Supplied by the Operator section to add the new panel part numbers BACP10U0187HC, BACP10U0412HC, and BACP10U0562HC Changes are made to the Parts Modified and Reidentified table to add the existing J4 Junction Box part number 284A1204-116 and the new J4 Junction Box part number 284A9200-135 that has to be marked on the re-worked J4 Junction Box 284A1204-116.
10. Accomplishment Instructions:
Existing Work Instructions section has been changed to a new format and grouped in two parts, PART 1 and PART 2. A new part, PART 3 has been added that provides work instructions for Operators that incorporated the Original Issue of this service bulletin dated January 11, 2006, or Revision 1 of this service bulletin dated January 30, 2008, and did not incorporate the Emergency AD 2008-24-51 dated November 18, 2008.
11. Figures:
The effectivity of all figures has been updated to include configuration 1.
Figure 8- Changes are made to add an existing J4 Junction Box part number 284A1204-116 that was missing from previous revision, and to add the new J4 Junction Box part number 284A9200-135 that has to be marked on the re-worked J4 Junction Box 284A1204-116.
Figure 24, step 11 - Changed the J20 Junction Box part number to correct a typographical error. J20 Junction Box part number was changed from 284A3203-38 to 284A3203-29.
Figure 33 - Changes are made to show the correct the location of Terminal 5 and to add a detail with Terminal Block TB5060F.
Figure 34 - Added note "Phase C" at Terminal 5 of Terminal Block TB5060F.
Figure 35 - Changes are made to show the correct location of Terminal 5 and to add a detail with Terminal Block TB5060F.
Figure 36 - Added note "Phase C" at Terminal 5 of Terminal Block TB5060F.
Figure 55- Changes are made to add an existing J4 Junction Box part number 284A1204-116 that was missing from previous revision, and to add the new J4 Junction Box part number 284A9200-135 that has to be marked on the re-worked J4 Junction Box 284A1204-116.
Figure 58 - Added an optional part number panel to P61-8 Fuel Test Panel Installation.
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Figure 59 - Added an optional part number panel to P61-8 Fuel Test Panel Installation.
Figure 60 - Added an optional part number panel to P61-8 Fuel Test Panel Installation.
The data given in Information Notice 737-28A1206 IN 03 and IN 04 is included in this revision.
Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY Original Issue: January 11, 2006 Revision 1: January 30, 2008 Revision 2: May 21, 2009
Original Issue: January 11, 2006 Revision 2: May 21, 2009 737-28A1206 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 286
ALERT ALERT Commercial Airplanes 737
ALERTALERT Service Bulletin Number: 737-28A1206 Summary Original Issue: January 11, 2006 Revision 2: May 21, 2009 ATA System: 2822 3152 SUBJECT: FUEL - Distribution - Center Fuel Tank Boost Pump Auto Shutoff and Master Caution Logic Change
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 Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND This service bulletin gives the instructions and a kit of parts to install an automatic shut off system for the fuel boost pumps in the center fuel tank. Time delay relays are installed in the J4 and J20 junction boxes that will shut off the pumps if the pumps operate with continuous low pressure for 15 seconds. If no fuel is available, the pump will turn off in 15 seconds. The master caution circuit is changed to provide indication to the flight crew when either center fuel tank pump runs dry for more than 10 seconds. The flight crew stays in primary control, with the automatic shut off system as backup, to stop the pumps after a low pressure indication.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". Boeing found that fuel pump operation with continuous low pressure could result in friction sparks or overheating in the fuel pump inlet. The high temperatures 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. Installation of the automatic shut off system adds fuel pump inlet protection against friction sparks and friction overheat damage in the fuel tanks.
This change affects section 9 of the Maintenance Planning Data (MPD) Document. New Airworthiness Limitations (AWL) "28-AWL-19" will be added to Section 9 of the MPD to include an operational check of the center tank boost pump Auto Shutoff System. This change also affects Section 1 and Section 3 of the FAA Approved Airplane Flight Manual (AFM).
Boeing Service Related Problem (SRP) 737NG-SRP-28-0091 is related to this service bulletin.
Original Issue: January 11, 2006 Revision 2: May 21, 2009 737-28A1206 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 286 BOEING SERVICE BULLETIN 737-28A1206
ALERT ALERT
As a part of a service bulletin validation program, this change was completed on airplane YE003 after the release of the original issue of this Service Bulletin. The change completed on airplane YE003 is equivalent to the change give in Revision 1 of this service bulletin. Airplane YE003 has the configuration of a Group 13 airplane.
ACTION (PRR 38545-20S) PART 1
1. Get access to the flight compartment. At the P5 overhead panel, replace the P5-2 fuel control module. At the P61 panel, install the P61-8 fuel test panel. At the P6-3 circuit breaker panel, add four circuit breakers and markers. Add five wires to the W0040 wire bundle in the P6 circuit breaker panel. Add eight wires to the W0044 wire bundle. These wires are located between the P6-3 circuit breaker and the P61-8 fuel test panels in the flight compartment and the J4 and J20 boxes in the electrical / electronics compartment.
2. Get access to the electrical / electronics compartment. Replace the J20 box. Add two relays and markers at the J20 box. Add ten wires to the W0072 wire bundle in the J20 box. Add two relays and markers at the J4 box. Add ten wires to the W0094 wire bundle in the J4 box. Add five wires to the W0212 wire bundle on the E2-1 electronics shelf in the electrical / electronics compartment. Add two wires to the W2112 wire bundle located between the E2-1 electronics shelf and the P5-2 fuel control panel in the flight compartment. Add three wires to the W0422 wire bundle on the E4-2 electronics shelf in the electrical / electronics compartment. Add one wire to the W2218 wire bundle located between the E4-2 electronics shelf and the P5-2 fuel control panel. Add three wires to the W5158 wire bundle located between the E2- 1 electronics shelf and the J20 box. Add three wires to the W5160 wire bundle located between the E4-2 electronics shelf and the J4 box.
PART 2
1. Do the operational tests of the automatic shutoff system for the fuel boost pumps installed in accordance with PART 1.
PART 3
1. Airplanes that accomplished the original issue of this service bulletin dated January 11, 2006, or revision 1 of this service bulletin dated January 30, 2008, and did not accomplish Emergency AD 2008-24-51 dated November 18, 2008 need to do the operational test given in accomplishment instructions paragraph 3.B, Part 3.
EFFECTIVITY 737-600/700/700C/800/900 airplanes. Refer to Paragraph 1.A.1 Airplanes, for the list of affected airplanes.
COMPLIANCE Boeing recommends that the change given in this service bulletin be done before 36 months after the date on Revision 2 of this service bulletin.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2007-NM-013-AD, is related to this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive 2008-24-51 is related to this service bulletin.