# Boeing Alert Service Bulletin 757-27A0152: Boeing - Service Bulletin - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-0475; AD 2015-08-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 757-27A0152](https://openairdocs.org/service-documents/boeing/757-27a0152.md) - Title as filed: Boeing - Service Bulletin - Pages: 156 - PDF: https://openairdocs.org/files/sha256/f8/5e/f85e6119deca7337f80a2191e291084f1931e84c159ac33e45a61ceecf470bc3 - Page: https://openairdocs.org/service-documents/boeing/757-27a0152/file/f85e6119deca ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-27A0152 Original Issue: April 29, 2009 Revision 1: June 30, 2010 ATA System: 2760 SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings - New Spoiler Control Module Relay Installation Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 1 of 156 4.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 2 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 Summary ...................................................... 9 1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3 1. Airplanes ............................................ 1 3 2. Spares Affected ........................................ 1 8 B. Concurrent Requirements ...................................... 1 8 C. Reason ................................................ 1 8 D. Description .............................................. 1 9 E. Compliance .............................................. 2 0 F. Approval ............................................... 2 0 G. Manpower .............................................. 2 0 H. Weight and Balance Changes .................................... 2 3 I. Electrical Load Data ......................................... 2 3 J. References .............................................. 2 4 1. Existing Data: ......................................... 2 4 2. Data supplied with this Service Bulletin: ........................... 2 4 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 4 K. Publications Affected ........................................ 2 4 L. Interchangeability and Intermixability of Parts ........................... 2 5 2. MATERIAL INFORMATION ........................................ 2 7 A. Material - Price and Availability ................................... 2 7 B. Industry Support Information .................................... 2 8 C. Parts Necessary For Each Airplane ................................. 2 8 1. Kits/Parts: ........................................... 2 8 2. Parts and Materials Supplied by the Operator: ........................ 3 6 3. Parts Modified and Reidentified: ............................... 3 6 4. Parts Removed and Not Replaced: .............................. 3 7 D. Parts Necessary to Change Spares ................................. 3 7 E. Special Tooling - Price and Availability ............................... 3 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 7 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9 A. GENERAL INFORMATION ..................................... 3 9 B. WORK INSTRUCTIONS ....................................... 4 0 FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL [Group 1-5, Configuration 1] .......... 5 7 FIGURE 2: E3-1 ELECTRONICS SHELF - RELAY BRACKET INSTALLATION [Group 1-5, Configuration 1 ] ................................................ 6 0 FIGURE 3: SPOILER CONTROL MODULE - WIRE PIN STRAPPING REMOVAL [Group 1-5, Configuration 1 ] ................................................ 6 7 FIGURE 4: W1265 WIRE BUNDLE ROUTING [Group 1-2, 5, Configuration 1] ............. 6 9 FIGURE 5: W1265 WIRE BUNDLE CHANGES [Group 1, Configuration 1] ............... 7 0 FIGURE 6: W1265 WIRE BUNDLE CHANGES [Group 2, Configuration 1] ............... 7 7 FIGURE 7: W1265 WIRE BUNDLE CHANGES [Group 5, Configuration 1] ............... 8 4 FIGURE 8: W1265 WIRE BUNDLE ROUTING [Group 3, Configuration 1] ................ 9 1 FIGURE 9: W1265 WIRE BUNDLE CHANGES [Group 3, Configuration 1] ............... 9 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 3 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 4 FIGURE 10: W1265 WIRE BUNDLE ROUTING [Group 4, Configuration 1] ................ 9 9 FIGURE 11: W1265 WIRE BUNDLE CHANGES [Group 4, Configuration 1] .............. 1 0 0 FIGURE 12: E3-1 ELECTRONICS SHELF - RELAY BRACKET EQUIPPING [Group 1-5, Configuration 1] ................................................. 1 0 7 FIGURE 13: E3-1 ELECTRONICS SHELF - INSTALLATION [Group 1-5, Configuration 1] ....... 1 1 1 FIGURE 14: W4471 WIRE BUNDLE ROUTING [Group 1-2, 5, Configuration 1] ............ 1 1 5 FIGURE 15: W4471 WIRE BUNDLE CHANGES [Group 1, Configuration 1] .............. 1 2 1 FIGURE 16: W4471 WIRE BUNDLE CHANGES [Group 2, Configuration 1] .............. 1 2 3 FIGURE 17: W4471 WIRE BUNDLE CHANGES [Group 5, Configuration 1] .............. 1 2 5 FIGURE 18: W4471 WIRE BUNDLE ROUTING [Group 3, Configuration 1] ............... 1 2 7 FIGURE 19: W4471 WIRE BUNDLE CHANGES [Group 3, Configuration 1] .............. 1 3 3 FIGURE 20: W4471 WIRE BUNDLE ROUTING [Group 4, Configuration 1] ............... 1 3 5 FIGURE 21: W4471 WIRE BUNDLE CHANGES [Group 4, Configuration 1] .............. 1 4 1 FIGURE 22: E3-1 ELECTRONICS SHELF - REMOVAL [Group 1-5, Configuration 2] ......... 1 4 3 FIGURE 23: E3-1 ELECTRONICS SHELF - RELAY BRACKET ASSEMBLY - TORQUE NUTS [Group 1-5, Configuration 2] ........................................ 1 4 6 FIGURE 24: E3-1 ELECTRONICS SHELF - RELAY BRACKET GROUND STUD - TORQUE NUTS AND BOND RESISTANCE TESTS [Group 1-5, Configuration 2] ................. 1 4 9 FIGURE 25: E3-1 ELECTRONICS SHELF - INSTALLATION [Group 1-5, Configuration 2] ....... 1 5 3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 4 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 5 Commercial Airplanes 757 Service Bulletin ALERT Revision Transmittal SheetNumber: 757-27A0152Original Issue: April 29, 2009 Revision 1: June 30, 2010 ATA System: 2760 SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings - New Spoiler Control Module Relay Installation This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION More work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The Work Instructions to do bond resistance tests between the bracket assemblies and the terminal lugs on the ground studs were not included in the original issue of this service bulletin. Also, the Work Instructions to torque the bracket assembly installation nuts, and the bracket assembly ground stud nuts were not included in the original issue of this service bulletin. REASON FOR REVISION As a part of a service bulletin validation program, this change was completed on airplane ND310 by Service Bulletin 757-27A0152 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane ND310 by Service Bulletin 757-27A0152 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane ND310 has the configuration of a Group 2 airplane. This revision is sent to correct discrepancies found during the validation of the original issue of this service bulletin. These sections were changed: 1. In Summary, Background and Paragraph 1.C., Reason, added service bulletin validation data. 2. In Summary, Action and Paragraph 1.D., Description, added a paragraph that specifies the more work necessary. 3. In Paragraph 1.G., Manpower: a. Changed manpower data for Group 1 thru 5, Configuration 1 airplanes. b. Added manpower table for Group 1 thru 5, Configuration 2 airplanes. 4. In Paragraph 1.H., Weight and Balance Changes, changed weight data. 5. In Paragraph 1.J.1., Existing Data: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 5 of 156 ### Page 6 a. Added Standard Wiring Practices Manual (SWPM) 20-20-10. b. Added 757 Aircraft Maintenance Manual (AMM) 20-11-00. 6. In Paragraph 2.A., Material - Price and Availability, changed top kit pricing data. 7. In Paragraph 2.C.1., Kits/Parts: a. Added wire kit 280N3368-109 and wire list 280N3368-109W data. b. Added note (b). 8. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator: a. Added Teflon sleeve. b. Added note (c). 9. In Paragraph 3.B., Work Instructions: a. Added step to do a continuity check. b. Operational test of the Spoiler/Speedbrake Control System, step 1.b., changed circuit breaker data. c. Operational test of the Spoiler/Speedbrake Control System, steps 2.g., changed text to "15-unit detent". d. Operational test of the Spoiler/Speedbrake Control System, steps 2.o.(1).(a)., changed text to "respond to control wheel commands". e. Added new Work Instructions for airplanes changed in accordance with the original issue of this service bulletin. 10. In Figures 1 and 13, changed sheet 1. 11. In Figure 2, changed sheets 1 thru 5 and step table. 12. In Figures 5 thru 7, 9 and 11: a. Sheets 1 and 2, added flag note 19. b. Sheet 6, wire cut and code table, added note (a). c. Sheet 7, added wire kit 280N3368-109W cut and code table. d. Flag note table, flag note 1, added wire list 280N3368-109W. e. Flag note table, flag note 7, changed terminal lug part number. f. Flag note table, added flag note 19. 13. In Figure 12: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 6 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 7 a. Changed sheets 1 thru 3. b. Step table, step 3, added note to torque the nuts. c. Step table, added step 4. 14. In Figure 13, step table: a. Step 8, changed the 'more data' note. b. Removed note (d). 15. Added new Figures 22 thru 25 to torque the nuts and do bond resistance tests in the E3-1 electronics shelf. The terminology used to refer to procedures in other Boeing documents is changed to agree with the revised Paragraph 3.A., General Information note 8, where necessary. These changes are identified with revision bars, but are not listed in the summary of changes for this revision. 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 April 29, 2009Original Issue: June 30, 2010Revision 1: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 7 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 8 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 8 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT BLANK PAGE ### Page 9 Commercial Airplanes 757 Service Bulletin ALERT SummaryNumber: 757-27A0152Original Issue: April 29, 2009 Revision 1: June 30, 2010 ATA System: 2760 SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings - New Spoiler Control Module 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 instructions to install new relays adjacent to two of the Spoiler Control Modules (SCM's). The new relays will ground a pin at each of the SCM's, M530 spoiler control module 1L and M531 spoiler control module 2L, when landing flaps are selected and prevent deployment of spoiler pairs 1 and 12, and, 5 and 8, during landing operations. If this service bulletin is not done, under certain gusty and windy conditions during landing, the airplane could potentially be put in an unsafe condition because of excessive lateral control. Boeing has received twelve reports of 757 in-service events where the flight crew reported unwanted lateral oscillations during the final approach just before landing. The oscillations are characterized by large wheel inputs at high rates that are out of phase with airplane response. Pilot inputs being out of phase with airplane response is known as pilot induced oscillation (PIO). PIO's are often related to tasks where the pilot is trying to precisely and quickly accomplish a flight maneuver, such as the final phase of a landing in gusty and turbulent wind conditions. To help reduce PIO's Boeing issued Service Bulletin 757-27A0146 (757-200's) and Service Bulletin 757-27A0147 (757-300's) which install a wheel damper to the first officer's lateral control quadrant, and Service Bulletin 757-57A0058 (757-200's) which installs vortex generators on the leading edge of each outboard main flap. This service bulletin adds another level of protection to further reduce the chance of PIO's on the 757 airplanes. The two spoiler pairs 1 and 12, and, 5 and 8, will be disabled from responding to control wheel commands when the flaps are in the landing configuration by the use of relays to ground pins at each affected SCM. The speedbrake operation will be unaffected in-air and during on-ground operation. The airplane will be protected for the most important hydraulic system failures by re-engaging the spoiler pairs 1 and 12 if the right hydraulic system fails. Accomplishment of the service bulletin will reduce the lateral control capability at landing flap (detent 25 and detent 30) by disabling spoiler pairs 1 and 12, and, 5 and 8, during landing operations. Disablement of these spoiler pairs will reduce the chance of a PIO occurrence. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 9 of 156 ### Page 10 Boeing Service Related Problem (SRP) 757-SRP-27-0182 is related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane ND310 by Service Bulletin 757-27A0152 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane ND310 by Service Bulletin 757-27A0152 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane ND310 has the configuration of a Group 2 airplane. ACTION (PRR 54530-278RS) Group 1-5, Configuration 1: Get access to the Electronic Equipment Bay (E/E Bay) and remove the E3-1 electronics shelf from the airplane. Make changes to the E3-1 electronics shelf to install three new bracket assemblies, three new relays, and to make changes to wire bundle W1265. Install the E3-1 electronics shelf to the airplane and make changes to wire bundle W4471 between the E3-1 electronics shelf and the E5-1 electronics shelf. Do a test of the Spoiler/Speedbrake Control System. Group 1-5, Configuration 2: More work is necessary. Get access to the Electronic Equipment Bay (E/E Bay) and remove the E3-1 electronics shelf from the airplane. Torque the bracket assembly installation nuts, and the bracket assembly ground stud nuts. Do bond resistance tests between the bracket assemblies and the terminal lugs on the ground studs. Install the E3-1 electronics shelf to the airplane. EFFECTIVITY All 757-200, -200CB, -200PF, -300 Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 60 months after the original issue date 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 Service Bulletin Manpower Paragraph 1.G., Manpower. MATERIAL INFORMATION Refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 10 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 11 (OCR) BOEING SERVICE BULLETIN 757-27A0152 ALERT ALERT E5-1 ELECTRONICS SHELF: - CHANGE WIRE BUNDLE W4471 E3-1 ELECTRONICS SHELF: -REMOVE ELECTRONICS SHELF -CHANGE WIRE BUNDLES W1265 AND W4471 K10877 -INSTALL CHANGED ELECTRONICS SHELF K10878 K10876 M522 M530 W1265 INSTALL NEW BRACKETS AND RELAYS, AND MAKE CHANGES E3-1 ELECTRONICS SHELF TO WIRE BUNDLE W1265 1441661 (TYPICAL) Original Issue: April 29, 2009 Revision 1: June 30, 2010 757-27A0152 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 156 ### Page 12 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 12 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT BLANK PAGE ### Page 13 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-27A0152 Original Issue: April 29, 2009 Revision 1: June 30, 2010 ATA System: 2760 SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings - New Spoiler Control Module Relay Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index Document D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. Refer to PRR 54530-278RS for data about this change. DESCRIPTIONCONFIGURATIONGROUP 757-200 airplanes with Wiring Configuration Differences.-1 757-200 airplanes with Wiring Configuration Differences that have not accomplished the Original Issue of this service bulletin. 1 757-200 airplanes with Wiring Configuration Differences that have accomplished the Original Issue of this service bulletin. 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 13 of 156 ### Page 14 DESCRIPTIONCONFIGURATIONGROUP 757-200, -200CB, -200PF airplanes with Wiring Configuration Differences. -2 757-200, -200CB, -200PF airplanes with Wiring Configuration Differences that have not accomplished the Original Issue of this service bulletin. 1 757-200, -200CB, -200PF airplanes with Wiring Configuration Differences that have accomplished the Original Issue of this service bulletin. 2 757-300 airplanes with Wiring Configuration Differences.-3 757-300 airplanes with Wiring Configuration Differences that have not accomplished the Original Issue of this service bulletin. 1 757-300 airplanes with Wiring Configuration Differences that have accomplished the Original Issue of this service bulletin. 2 757-200, -300 airplanes with Wiring Configuration Differences.-4 757-200, -300 airplanes with Wiring Configuration Difference that have not accomplished the Original Issue of this service bulletin. 1 757-200, -300 airplanes with Wiring Configuration Differences that have accomplished the Original Issue of this service bulletin. 2 757-200 airplanes with Wiring Configuration Differences.-5 757-200 airplanes with Wiring Configuration Differences that have not accomplished the Original Issue of this service bulletin. 1 757-200 airplanes with Wiring Configuration Differences that have accomplished the Original Issue of this service bulletin. 2 Airplane Models: 757-200, 757-200CB, 757-200PF, 757-300 GroupVariable Number 1NA002 - NA028 1NA191 - NA199 1NA201 - NA239 1NA301 - NA305 1NA341 - NA352 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 14 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 15 GroupVariable Number 1NA391 - NA399 1NA401 - NA408 1NA441 - NA447 2NA501 - NA586 2NB001 - NB004 2NB021 - NB023 2NB036 - NB041 2NB051 - NB053 2NB061 - NB073 2NB079 2NB131 - NB148 2NB161 - NB162 2NB166 - NB168 1NB201 - NB204 1NB221 - NB228 1NB230 1NB236 1NB239 2NB261 - NB267 2NB291 - NB299 2NB301 - NB302 2NB311 - NB312 2NB321 - NB331 2NB421 - NB438 2NB446 2NB451 - NB454 2NB501 - NB523 2NB561 2NB571 2NB581 - NB583 2NC001 - NC033 2NC041 - NC042 2NC051 - NC052 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 15 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 16 GroupVariable Number 2NC056 - NC062 2NC066 - NC084 2NC091 - NC094 2NC151 2NC161 2NC901 - NC951 2NC971 - NC974 2ND001 - ND007 2ND011 - ND059 2ND111 - ND113 2ND161 - ND199 2ND201 - ND203 2ND221 - ND225 2ND241 - ND248 2ND301 - ND322 2ND401 2ND891 2ND895 2NE001 - NE008 2NE011 - NE088 2NE091 - NE094 2NE141 - NE150 1NE161 - NE177 2NE201 - NE204 2NE301 - NE302 2NE311 - NE325 4NJ001 - NJ004 4NJ031 - NJ032 4NJ551 - NJ555 3NL001 - NL002 3NL006 - NL017 4NL101 - NL109 4NL141 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 16 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 17 GroupVariable Number 4NL601 - NL616 2NN001 - NN002 2NN051 - NN052 2NP901 - NP904 2NS601 - NS616 2NT001 - NT009 2NT201 - NT202 1NT231 - NT234 1NT237 - NT240 1NT242 1NT245 - NT248 2NT281 - NT289 2NT341 - NT347 2NT351 - NT360 2NT371 - NT373 2NT375 - NT379 1NT381 - NT386 2NT401 - NT403 5NT404 - NT409 2NT411 - NT412 2NT426 - NT427 2NT431 - NT432 2NT436 - NT438 2NT441 - NT442 2NT446 2NT701 - NT769 2NT791 - NT796 2NT861 - NT862 2NT881 - NT885 2NT901 - NT916 2NT971 - NT985 2NU031 - NU038 3NU701 - NU705 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 17 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 18 GroupVariable Number 3NU721 - NU728 3NU731 - NU732 2. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin gives instructions to install new relays adjacent to two of the Spoiler Control Modules (SCM's). The new relays will ground a pin at each of the SCM's, M530 spoiler control module 1L and M531 spoiler control module 2L, when landing flaps are selected and prevent deployment of spoiler pairs 1 and 12, and, 5 and 8, during landing operations. If this service bulletin is not done, under certain gusty and windy conditions during landing, the airplane could potentially be put in an unsafe condition because of excessive lateral control. Boeing has received twelve reports of 757 in-service events where the flight crew reported unwanted lateral oscillations during the final approach just before landing. The oscillations are characterized by large wheel inputs at high rates that are out of phase with airplane response. Pilot inputs being out of phase with airplane response is known as pilot induced oscillation (PIO). PIO's are often related to tasks where the pilot is trying to precisely and quickly accomplish a flight maneuver, such as the final phase of a landing in gusty and turbulent wind conditions. To help reduce PIO's Boeing issued Service Bulletin 757-27A0146 (757-200's) and Service Bulletin 757-27A0147 (757-300's) which install a wheel damper to the first officer's lateral control quadrant, and Service Bulletin 757-57A0058 (757-200's) which installs vortex generators on the leading edge of each outboard main flap. This service bulletin adds another level of protection to further reduce the chance of PIO's on the 757 airplanes. The two spoiler pairs 1 and 12, and, 5 and 8, will be disabled from responding to control wheel commands when the flaps are in the landing configuration by the use of relays to ground pins at each affected SCM. The speedbrake operation will be unaffected in-air and during on-ground operation. The airplane will be protected for the most important hydraulic system failures by re-engaging the spoiler pairs 1 and 12 if the right hydraulic system fails. Accomplishment of the service bulletin will reduce the lateral control capability at landing flap (detent 25 and detent 30) by disabling spoiler pairs 1 and 12, and, 5 and 8, during landing operations. Disablement of these spoiler pairs will reduce the chance of a PIO occurrence. Boeing Service Related Problem (SRP) 757-SRP-27-0182 is related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane ND310 by Service Bulletin 757-27A0152 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane ND310 by Service Bulletin 757-27A0152 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane ND310 has the configuration of a Group 2 airplane. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 18 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 19 Revision 1 is sent to correct discrepancies found during the validation of the original issue of this service bulletin. D. Description Group 1-5, Configuration 1: Get access to the Electronic Equipment Bay (E/E Bay) and remove the E3-1 electronics shelf from the airplane. Make changes to the E3-1 electronics shelf to install three new bracket assemblies, three new relays, and to make changes to wire bundle W1265.Install the E3-1 electronics shelf to the airplane and make changes to wire bundle W4471 between the E3-1 electronics shelf and the E5-1 electronics shelf. Do a test of the Spoiler/Speedbrake Control System. Group 1-5, Configuration 2: More work is necessary. Get access to the Electronic Equipment Bay (E/E Bay) and remove the E3-1 electronics shelf from the airplane. Torque the bracket assembly installation nuts, and the bracket assembly ground stud nuts. Do bond resistance tests between the bracket assemblies and the terminal lugs on the ground studs. Install the E3-1 electronics shelf to the airplane. Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer to Paragraph 1.K., Publications Affected. Revision 1 - More work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The Work Instructions to do bond resistance tests between the bracket assemblies and the terminal lugs on the ground studs were not included in the original issue of this service bulletin. Also, the Work Instructions to torque the bracket assembly installation nuts, and the bracket assembly ground stud nuts were not included in the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1, 5: Affected Maintenance Zones ZoneModel 119757-200 Group 2: Affected Maintenance Zones ZoneModel 119757-200, 757-200CB, 757- 200PF Group 3: Affected Maintenance Zones ZoneModel 119757-300 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 19 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 20 Group 4: Affected Maintenance Zones ZoneModel 119757-200, 757-300 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 60 months after the original issue date 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. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin 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 inspect the work — Time to cure the materials — Time to make the parts — Time to find the tools. Group 1, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 2.252.251Open Access 0.500.501FIGURE 1 2.302.301FIGURE 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 20 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 21 Group 1, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 0.600.601FIGURE 3 ---FIGURE 4 (Wire Routing only) 8.6517.302FIGURE 5 0.500.501FIGURE 12 0.500.501FIGURE 13 ---FIGURE 14 (Wire Routing only) 3.703.701FIGURE 15 2.252.251Close Access 2.254.502Test 23.5034.40TOTAL FOR EACH AIRPLANE Group 2, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 2.252.251Open Access 0.500.501FIGURE 1 2.302.301FIGURE 2 0.600.601FIGURE 3 ---FIGURE 4 (Wire Routing only) 8.6517.302FIGURE 6 0.500.501FIGURE 12 0.500.501FIGURE 13 ---FIGURE 14 (Wire Routing only) 0.800.801FIGURE 16 2.252.251Close Access 2.254.502Test 20.6031.50TOTAL FOR EACH AIRPLANE Group 3, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 2.252.251Open Access 0.500.501FIGURE 1 2.302.301FIGURE 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 21 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 22 Group 3, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 0.600.601FIGURE 3 ---FIGURE 8 (Wire Routing only) 8.6517.302FIGURE 9 0.500.501FIGURE 12 0.500.501FIGURE 13 ---FIGURE 18 (Wire Routing only) 0.800.801FIGURE 19 2.252.251Close Access 2.254.502Test 20.6031.50TOTAL FOR EACH AIRPLANE Group 4, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 2.252.251Open Access 0.500.501FIGURE 1 2.302.301FIGURE 2 0.600.601FIGURE 3 ---FIGURE 10 (Wire Routing only) 8.6517.302FIGURE 11 0.500.501FIGURE 12 0.500.501FIGURE 13 ---FIGURE 20 (Wire Routing only) 0.800.801FIGURE 21 2.252.251Close Access 2.254.502Test 20.6031.50TOTAL FOR EACH AIRPLANE Group 5, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 2.252.251Open Access 0.500.501FIGURE 1 2.302.301FIGURE 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 22 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 23 Group 5, Configuration 1: Elapsed Hours Task HoursNumber of Persons Task 0.600.601FIGURE 3 ---FIGURE 4 (Wire Routing only) 8.6517.302FIGURE 7 0.500.501FIGURE 12 0.500.501FIGURE 13 ---FIGURE 14 (Wire Routing only) 3.803.801FIGURE 17 2.252.251Close Access 2.254.502Test 23.6034.50TOTAL FOR EACH AIRPLANE Group 1-5, Configuration 2: Elapsed Hours Task HoursNumber of Persons Task 1.503.002Open Access 0.500.501FIGURE 22 0.750.751FIGURE 23 0.500.501FIGURE 24 0.500.501FIGURE 25 1.503.002Close Access 1.503.002Test 6.7511.25TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane + 340+ 0.8All 757-200 airplanes + 220+ 0.8All 757-300 airplanes I. Electrical Load Data Not changed. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 23 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 24 J. References 1. Existing Data: a. Engineering Change Memo PRR 54530-278RS b. Boeing Service Bulletin 757-27A0146, 757-27A0147, 757-57A0058 c. Boeing Service Related Problem (SRP) 757-SRP-27-0182 d. Standard Overhaul Practices Manual (SOPM) 20-11-03, 20-50-05 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00, 20-20-10, 20-30-11, 20-30-12, 20-61-11, 20-74-11, 20-74-12, 20-81-19, 20-81-22, 20-90-11, 20-90-15 f. 757 Aircraft Maintenance Manual (AMM) 20-11-00, 27-09-00, 29-11-00 g. 757 Wiring Diagram Manual (WDM) 27-09-11, 27-09-13, 27-61-13, 27-61-17, 31-51-42 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Equipment / Wire Installation, Reduction of Lateral Control at Landing Flaps012N0053 The drawing was used to prepare this service bulletin. The drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. The drawing may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-SectionPublication 27-09, 27-61, 31-51757 Wiring Diagram Manual 27-61757 Illustrated Parts Catalog 27-09, 27-61, 31-51757 System Schematic Manual 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 24 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 25 L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 25 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 26 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 26 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT BLANK PAGE ### Page 27 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. If there is a limit in the quantity (QTY) of kits, a supply sequence is given by Spares. Group 1, Configuration 1: Unit Price thru Aug 31/10 QTYDateNameKit Number $4,691.0020Oct 13, 2009TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS 012N8932-15 20Oct 27, 2009 Group 2, Configuration 1: Unit Price thru Aug 31/10 QTYDateNameKit Number $4,610.0020Oct 13, 2009TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS 012N8932-16 20Oct 27, 2009 20Nov 10, 2009 20Nov 24, 2009 20Dec 12, 2009 20Jan 04, 2010 20Jan 18, 2010 20Feb 01, 2010 20Feb 15, 2010 15Mar 01, 2010 Group 3, Configuration 1: Unit Price thru Aug 31/10 QTYDateNameKit Number $4,619.005Oct 13, 2009TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS 012N8932-17 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 27 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 28 Group 4, Configuration 1: Unit Price thru Aug 31/10 QTYDateNameKit Number $4,610.009Oct 13, 2009TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS 012N8932-18 Group 5, Configuration 1: Unit Price thru Aug 31/10 QTYDateNameKit Number $4,701.001Oct 13, 2009TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS 012N8932-19 The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Mail to: Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA 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 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 28 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 29 Kit 012N8932 NotesNameQTYNew Part Number -19-18-17-16-15 TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS ....-012N8932-15 TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS ...-.012N8932-16 TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS ..-..012N8932-17 TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS .-...012N8932-18 TOP KIT - 757 REDUCTION OF LATERAL CONTROL SENSITIVITY AT LANDING FLAPS -....012N8932-19 BRACKET ASSY - RELAY33333012N0053-3 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS ....1280N3368-1 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS ...1.280N3368-2 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS ..1..280N3368-3 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS .1...280N3368-4 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS 1....280N3368-5 NUT22222BACN10YR3CD NUT99999BACN10YR4CD RELAY33333BACR13CE2 (a)SCREW99999BACS12HN4-9 WASHER22222NAS1149D0316H (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, BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 29 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 30 Kit 012N8932 NotesNameQTYNew Part Number -19-18-17-16-15 substitute fasteners may be supplied in kits. Boeing Document D-590 and Boeing Drawing 65-88700 are used to determine the part numbers used as substitutes. Kit 280N3368 NotesNameQTYNew Part Number -5-4-3-2-1 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS ....-280N3368-1 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS ...-.280N3368-2 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS ..-..280N3368-3 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS .-...280N3368-4 WIRE KIT - 757 REDUCTION OF LATER- AL CONTROL SENSITIVITY AT LANDING FLAPS -....280N3368-5 ASSY - W12651..11280N3368-101 ASSY - W1265..1..280N3368-102 ASSY - W1265.1...280N3368-103 ASSY - W4471....1280N3368-104 ASSY - W4471...1.280N3368-105 ASSY - W4471..1..280N3368-106 ASSY - W4471.1...280N3368-107 ASSY - W44711....280N3368-108 ASSY - W126511111280N3368-109 Kit 280N3368 NotesNameQTYNew Part Number -104-103-102-101 (b)ASSY - W1265...-280N3368-101 (b)ASSY - W1265..-.280N3368-102 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 30 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 31 Kit 280N3368 NotesNameQTYNew Part Number -104-103-102-101 (b)ASSY - W1265.-..280N3368-103 ASSY - W4471-...280N3368-104 TAPE, CONNECTOR ID.111280N3368-10101 TAPE, CONNECTOR ID.111280N3368-10102 TAPE, CONNECTOR ID.111280N3368-10103 SLEEVE, SPLICE ID.111280N3368-10104 SLEEVE, SPLICE ID.111280N3368-10105 SLEEVE, SPLICE ID.111280N3368-10106 SLEEVE, SPLICE ID.111280N3368-10107 SLEEVE, SPLICE ID.111280N3368-10108 SLEEVE, SPLICE ID.111280N3368-10109 LOCKSTITCH.111280N3368-10110 WIRE LIST...1280N3368-101W WIRE LIST..1.280N3368-102W WIRE LIST.1..280N3368-103W SLEEVE, SPLICE ID1...280N3368-10401 LOCKSTITCH - RED1...280N3368-10402 WIRE LIST1...280N3368-104W (a)CONTACT, PIN3...BACC47CN1S (a)CONTACT, SOCKET...2BACC47CP1S (a)CONTACT, PIN.131313BACC47EF1 (a)CONTACT, SOCKET.363636BACC47ER1 (a)CONTACT.2..BACC47FK1A RELAY SOCKET.333BACS16AF1 (a) (b)TERMINAL, LUG.777BACT12AC2 (a)CONTACT, SOCKET, SIZE 20..2.CTA-0165 (a)SPLICE SEALED CRIMP2...D-436-36 (a)WIRE SPLICE SLEEVE.777D-436-58 (a)CONTACT, PIN, CRIMP REMOVABLE, PER MIL- C-39029/11 ...4M39029/11-145 (a)CONTACT, PIN, SIZE 20.44.S280W555-920 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 31 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 32 Kit 280N3368 NotesNameQTYNew Part Number -104-103-102-101 (a) There are more parts than are necessary. (b) See wire kit 280N3368-109 for alternative parts. Kit 280N3368 NotesNameQTYNew Part Number -109-108-107-106-105 ASSY - W4471....-280N3368-105 ASSY - W4471...-.280N3368-106 ASSY - W4471..-..280N3368-107 ASSY - W4471.-...280N3368-108 ASSY - W1265-....280N3368-109 SLEEVE, SPLICE ID.1111280N3368-10401 LOCKSTITCH - RED.1...280N3368-10402 LOCKSTITCH - RED..111280N3368-10502 WIRE LIST....1280N3368-105W WIRE LIST...1.280N3368-106W WIRE LIST..1..280N3368-107W WIRE LIST1...280N3368-108W WIRE LIST1....280N3368-109W (a)CONTACT, PIN.3..2BACC47CN1S (a)CONTACT..2..BACC47FJ1A (a)CONTACT, PIN, SIZE 20...2.CTA-0166 (a)SPLICE SEALED CRIMP.2222D-436-36 (a)TERMINAL, LUG7....BACT12AC3 (a) There are more parts than are necessary. Kit 280N3368 NotesNameQTYNew Part Number -10105-10104-10103-10102-10101 TAPE, CONNECTOR ID....-280N3368-10101 TAPE, CONNECTOR ID...-.280N3368-10102 TAPE, CONNECTOR ID..-..280N3368-10103 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 32 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 33 Kit 280N3368 NotesNameQTYNew Part Number -10105-10104-10103-10102-10101 SLEEVE, SPLICE ID.-...280N3368-10104 SLEEVE, SPLICE ID-....280N3368-10105 TAPE, ID..111BACT19C-T SLEEVE, IDENTIFICATION, HEAT SHRINKABLE 11...BMS13-69D044B Kit 280N3368 NotesNameQTYNew Part Number -10110-10109-10108-10107-10106 SLEEVE, SPLICE ID....-280N3368-10106 SLEEVE, SPLICE ID...-.280N3368-10107 SLEEVE, SPLICE ID..-..280N3368-10108 SLEEVE, SPLICE ID.-...280N3368-10109 LOCKSTITCH-....280N3368-10110 SLEEVE, IDENTIFICATION, HEAT SHRINKABLE .1111BMS13-69D044B BMS 13-541....NA374H2 Kit 280N3368 NotesNameQTYNew Part Number -10502-10402-10401 SLEEVE, SPLICE ID..-280N3368-10401 LOCKSTITCH - RED.-.280N3368-10402 LOCKSTITCH - RED-..280N3368-10502 SLEEVE, IDENTIFICATION, HEAT SHRINK- ABLE ..1BMS13-69D044B BMS 13-54 GD TIII C1 FC LACING TAPE, FLAT BRAID 11.NR331H Kit 280N3368 NotesNameQTYNew Part Number -104W-103W-102W-101W WIRE LIST...-280N3368-101W WIRE LIST..-.280N3368-102W BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 33 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 34 Kit 280N3368 NotesNameQTYNew Part Number -104W-103W-102W-101W WIRE LIST.-..280N3368-103W WIRE LIST-...280N3368-104W WIRE.111BMS13-48T10C01G020 Wire, Identified as W1265-0737-20, Length 4 Inches .111- Wire, Identified as W1265-0738-20, Length 4 Inches .111- Wire, Identified as W1265-0739-20, Length 4 Inches .111- Wire, Identified as W1265-0740-20, Length 4 Inches .111- Wire, Identified as W1265-0741-20, Length 4 Inches .111- Wire, Identified as W1265-0742-20, Length 4 Inches .111- WIRE1111BMS13-48T10C01G022 Wire, Identified as W1265-0734-22, Length 12 Inches .111- Wire, Identified as W1265-0735-22, Length 12 Inches .111- Wire, Identified as W1265-0736-22, Length 12 Inches .111- Wire, Identified as W1265-0743-22, Length 12 Inches .111- Wire, Identified as W1265-0744-22, Length 12 Inches .111- Wire, Identified as W1265-0745-22, Length 12 Inches .111- Wire, Identified as W1265-0746-2, Length 12 Inches .111- Wire, Identified as W1265-0747-22, Length 12 Inches .111- Wire, Identified as W1265-0748-22, Length 24 Inches .111- Wire, Identified as W1265-0749-22, Length 24 Inches .111- BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 34 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 35 Kit 280N3368 NotesNameQTYNew Part Number -104W-103W-102W-101W Wire, Identified as W1265-0750-22, Length 12 Inches .111- Wire, Identified as W1265-0751-22, Length 12 Inches .111- Wire, Identified as W4471-0285-22, Length 312 Inches 1...- Wire, Identified as W4471-0575-22, Length 24 Inches 1...- WIRE.111BMS13-48T10C02G022 Wire, Identified as W1265-2061B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2062B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2063B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2064B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2065B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2066B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2067B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2068B/R- 22, Length 16 Inches .111- Wire, Identified as W1265-2069B/R- 22, Length 16 Inches .111- Kit 280N3368 NotesNameQTYNew Part Number -109W-108W-107W-106W-105W WIRE LIST....-280N3368-105W WIRE LIST...-.280N3368-106W WIRE LIST..-..280N3368-107W WIRE LIST.-...280N3368-108W WIRE LIST-....280N3368-109W BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 35 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 36 Kit 280N3368 NotesNameQTYNew Part Number -109W-108W-107W-106W-105W WIRE11111BMS13-48T10C01G022 Wire, Identified as W4471-0285- 22, Length 312 Inches .1...- Wire, Identified as W4471-0575- 22, Length 24 Inches .1111- Wire, Identified as W1265-0743- 22, Length 24 Inches 1....- Wire, Identified as W1265-0745- 22, Length 16 Inches 1....- Wire, Identified as W1265-0746- 22, Length 24 Inches 1....- WIRE1....BMS13-48T10C02G022 Wire, Identified as W1265- 2064B/R-22, Length 30 Inches 1....- Wire, Identified as W1265- 2065B/R-22, Length 30 Inches 1....- Wire, Identified as W1265- 2066B/R-22, Length 30 Inches 1....- 2. Parts and Materials Supplied by the Operator: NotesNameQTYPart Number / Specifica- tion (a)SEALANT4 ozBMS 5-95 (b)DYMO VINYL TAPE1SKU# 15809 (c)SLEEVE, TEFLONStandard Wall. Length 9 inches, diameter 1 inch TFE 2X (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Dymo Corporation, 44 Commerce Road Stamford, CT. 06902-4561. Voice Phone Number: 203- 355-9000 Fax Phone Number: 203-355-9071. Cage Code: 0TH24. (c) Zeus Industrial Products, 620 Magnolia St, P.O. Box 2167, Orangeburg, SC. 29116-2167. Cage Code: 6Y609. 3. Parts Modified and Reidentified: None. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 36 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 37 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 37 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 38 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 38 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT BLANK PAGE ### Page 39 3. 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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. 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 given in 757 SRM, Chapter 51 – Torque limits to tighten nuts and bolts are given in 757 SRM, Chapter 51 5. For approved fastener and process material substitutions, refer to 757 SRM, Chapter 51. Alternate fasteners are given in 757 SRM Chapter 51 and Boeing Drawing 65-88700. 6. 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. 7. If the length of any fastener specified in this service bulletin does not meet the 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. 8. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 39 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 40 B. WORK INSTRUCTIONS Group 1, Configuration 1: 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 1. 6. Install the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 2. 7. Remove the wire bundle pin strapping from the Spoiler Control Modules M530 and M531 in accordance with FIGURE 3. 8. Change the W1265 wire bundle, on the E3-1 electronics shelf in accordance with FIGURE 4 and FIGURE 5. 9. Do a continuity check of the new and changed wires in the E3-1 electronics shelf. 10. Install the new relays K10876, K10877, and K10878 to the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 12. 11. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 13. 12. Disconnect electrical connector D41325P (position 16) from the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 40 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 41 13. Change the W4471 wire bundle, on the E3-1 electronic shelf and E5-1 electronics shelf in accordance with FIGURE 14 and FIGURE 15. 14. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 15. Connect electrical connector D41325P to the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 16. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 17. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 18. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 19. Do the operational test of the Spoiler/Speedbrake Control System that follows. Group 2, Configuration 1: 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 41 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 42 NumberNamePanel / Location C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 1. 6. Install the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 2. 7. Remove the wire bundle pin strapping from the Spoiler Control Modules M530 and M531 in accordance with FIGURE 3. 8. Change the W1265 wire bundle, on the E3-1 electronics shelf in accordance with FIGURE 4 and FIGURE 6. 9. Do a continuity check of the new and changed wires in the E3-1 electronics shelf. 10. Install the new relays K10876, K10877, and K10878 to the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 12. 11. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 13. 12. Disconnect electrical connectors D41325P (position 16) and D42187P (position 17) from the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 13. Change the W4471 wire bundle, on the E3-1 electronic shelf and E5-1 electronics shelf in accordance with FIGURE 14 and FIGURE 16. 14. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 15. Connect electrical connectors D41325P and D42187P to the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 16. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 17. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 42 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 43 NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 18. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 19. Do the operational test of the Spoiler/Speedbrake Control System that follows. Group 3, Configuration 1: 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location Airplanes without Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 Airplanes with Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 43 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 44 NumberNamePanel / Location C1538CSEU 1L AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L DC orP11 / C9 FLT CONT ELEC 2L DC 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 1. 6. Install the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 2. 7. Remove the wire bundle pin strapping from the Spoiler Control Modules M530 and M531 in accordance with FIGURE 3. 8. Change the W1265 wire bundle, on the E3-1 electronics shelf in accordance with FIGURE 8 and FIGURE 9. 9. Do a continuity check of the new and changed wires in the E3-1 electronics shelf. 10. Install the new relays K10876, K10877, and K10878 to the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 12. 11. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 13. 12. Disconnect electrical connectors D41325P (position 12) and D42187P (position 17) from the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 13. Change the W4471 wire bundle, on the E3-1 electronic shelf and E5-1 electronics shelf in accordance with FIGURE 18 and FIGURE 19. 14. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 15. Connect electrical connectors D41325P and D42187P to the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 16. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 17. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 44 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 45 NumberNamePanel / Location Airplanes without Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 Airplanes with Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1538CSEU 1L AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L DC orP11 / C9 FLT CONT ELEC 2L DC 18. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 19. Do the operational test of the Spoiler/Speedbrake Control System that follows. Group 4, Configuration 1: 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 45 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 46 NumberNamePanel / Location C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 1. 6. Install the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 2. 7. Remove the wire bundle pin strapping from the Spoiler Control Modules M530 and M531 in accordance with FIGURE 3. 8. Change the W1265 wire bundle, on the E3-1 electronics shelf in accordance with FIGURE 10 and FIGURE 11. 9. Do a continuity check of the new and changed wires in the E3-1 electronics shelf. 10. Install the new relays K10876, K10877, and K10878 to the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 12. 11. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 13. 12. Disconnect electrical connectors D41325P (position C05) and D42187P (position D05) from the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 13. Change the W4471 wire bundle, on the E3-1 electronic shelf and E5-1 electronics shelf in accordance with FIGURE 20 and FIGURE 21. 14. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 15. Connect electrical connectors D41325P and D42187P to the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 16. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 17. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 46 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 47 NumberNamePanel / Location C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC 18. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 19. Do the operational test of the Spoiler/Speedbrake Control System that follows. Group 5, Configuration 1: 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 1. 6. Install the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 2. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 47 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 48 7. Remove the wire bundle pin strapping from the Spoiler Control Modules M530 and M531 in accordance with FIGURE 3. 8. Change the W1265 wire bundle, on the E3-1 electronics shelf in accordance with FIGURE 4 and FIGURE 7. 9. Do a continuity check of the new and changed wires in the E3-1 electronics shelf. 10. Install the new relays K10876, K10877, and K10878 to the new bracket assemblies, on the E3-1 electronics shelf in accordance with FIGURE 12. 11. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 13. 12. Disconnect electrical connector D41325P (position 16) from the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 13. Change the W4471 wire bundle, on the E3-1 electronic shelf and E5-1 electronics shelf in accordance with FIGURE 14 and FIGURE 17. 14. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 15. Connect electrical connector D41325P to the E5-1 electronics shelf disconnect bracket AE0501. Refer to SWPM 20-10-11 as an accepted procedure. 16. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 17. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 18. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 19. Do the operational test of the Spoiler/Speedbrake Control System that follows. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 48 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 49 Group 1-5, Configuration 1: Operational test of the Spoiler/Speedbrake Control System 1. Prepare for the test. a. Supply pressure to the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00 as an accepted procedure. b. Make sure the circuit breakers that follow are closed: NumberNamePanel / Location C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1025FLAP SLAT ELEC UNIT 1 PWRP11 / G12 C1037FLAP SLAT ELEC UNIT 1 SENSORP11 / G14 c. Make sure that the Speedbrake Lever is in its down-and-locked detent position. d. Set the Aileron Trim at 0 units. e. Set the Stabilizer Trim at the Green Band. f. Make sure the Control Wheel is in the neutral position. g. Make sure that the Control Wheel is free to move and responds to manual inputs, and is not being affected by other input signals. 2. Do the Control Wheel Input test that follows: a. The time for the test that follows must be done in 16 seconds or less. (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. (2) Do step (1) again two more times. b. Put the Flap Control Lever in the 20-unit detent. c. The time for the test that follows must be done in 16 seconds or less. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 49 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 50 (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. (a) Make sure spoiler pairs 1 and 12, and, 5 and 8, respond to control wheel commands. (2) Do step (1) again two more times. d. Put the Flap Control Lever in the 25-unit detent. e. The time for the test that follows must be done in 16 seconds or less. (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. (a) Make sure spoiler pairs 1 and 12, and, 5 and 8, do not respond to control wheel commands. (2) Do step (1) again two more times. f. Move the Speedbrake Lever to its up detent position. (1) Make sure spoiler pairs 1 and 12, and, 5 and 8, move up along with other spoiler panels. g. Put the Flap Control Lever in the 15-unit detent. h. The time for the test that follows must be done in 16 seconds or less. (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. (a) Make sure spoiler pairs 1 and 12, and, 5 and 8, respond to control wheel commands. (2) Do step (1) again two more times. i. Move the Speedbrake Lever to its down-and-locked detent position. (1) Make sure spoiler pairs 1 and 12, and, 5 and 8, move down along with other spoiler panels. j. Put the Flap Control Lever in the 25-unit detent. k. Move the Speedbrake Lever to its up detent position. (1) Make sure spoiler pairs 1 and 12, and, 5 and 8, move up along with other spoiler panels. l. The time for the test that follows must be done in 16 seconds or less. (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 50 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 51 (a) Make sure spoiler pairs 1 and 12, and, 5 and 8, stay up for speedbrake function and do not respond to control wheel commands. (2) Do step (1) again two more times. m. Move the Speedbrake Lever to its down-and-locked detent position. (1) Make sure spoiler pairs 1 and 12, and, 5 and 8, move down along with other spoiler panels. n. Remove the power from the right hydraulic system. Refer to 757 AMM 29-11-00 as an accepted procedure. o. The time for the test that follows must be done in 16 seconds or less. (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. (a) Make sure spoiler pairs 1 and 12, respond to control wheel commands. (b) Make sure spoiler pairs 5 and 8, stay down. (2) Do step (1) again two more times. p. Move the Speedbrake Lever to its up detent position. (1) Make sure spoiler pairs 1 and 12, and, 5 and 8, move up along with other speedbrake panels. q. The time for the test that follows must be done in 16 seconds or less. (1) Turn the control wheel from the neutral position fully clockwise then back to the neutral position, then turn the control wheel from the neutral position fully counterclockwise then back to the neutral position. (a) Make sure spoiler pairs 1 and 12, respond to control wheel commands. (b) Make sure spoiler pairs 5 and 8, stay up for speedbrake function and do not respond to control wheel commands. (2) Do step (1) again two more times. r. Move the Speedbrake Lever to its down-and-locked detent position. (1) Make sure spoiler pairs 1 and 12, and, 5 and 8, move down along with other speedbrake panels s. Put the Flap Control Lever in the UP detent. 3. Close up. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 51 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 52 a. Make sure the control wheels are in their neutral position. b. Make sure the Speedbrake Lever is in its down-and-locked detent position. 4. Put the airplane back to a serviceable condition. Group 1-2, 5, Configuration 2: CONDITION: MORE WORK IS NECESSARY - TORQUE NUTS AND BOND RESISTANCE TESTS 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 22. 6. Torque the bracket assembly installation nuts in accordance with FIGURE 23. 7. Torque the bracket assembly ground stud nuts and do bond resistance tests in accordance with FIGURE 24. 8. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 25. 9. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 10. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 52 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 53 11. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 12. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 13. Put the airplane back to a serviceable condition. Group 3, Configuration 2: CONDITION: MORE WORK IS NECESSARY - TORQUE NUTS AND BOND RESISTANCE TESTS 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location Airplanes without Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 53 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 54 NumberNamePanel / Location Airplanes with Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1538CSEU 1L AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L DC orP11 / C9 FLT CONT ELEC 2L DC 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 22. 6. Torque the bracket assembly installation nuts in accordance with FIGURE 23. 7. Torque the bracket assembly ground stud nuts and do bond resistance tests in accordance with FIGURE 24. 8. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 25. 9. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 10. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 11. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: NumberNamePanel / Location Airplanes without Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1017STAB TRIM CONT LP11 / C5 or P11 / H11 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 54 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 55 NumberNamePanel / Location C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC C1031RUD RATIOP11 / D18 or P11 / G10 Airplanes with Yaw Damper / Stabilizer Trim Module C1560YAW DAMPER LP11 / A18 C1538CSEU 1L AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L DC orP11 / C9 FLT CONT ELEC 2L DC 12. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 13. Put the airplane back to a serviceable condition. Group 4, Configuration 2: CONDITION: MORE WORK IS NECESSARY - TORQUE NUTS AND BOND RESISTANCE TESTS 1. Get access to the E3-1 electronics shelf in the Main Equipment Center. 2. Open the circuit breakers that follow and attach "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC 3. Remove the flight control system electronics unit (CSEU) modules from E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 55 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 56 4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 5. Remove the E3-1 electronics shelf from the airplane in accordance with FIGURE 22. 6. Torque the bracket assembly installation nuts in accordance with FIGURE 23. 7. Torque the bracket assembly ground stud nuts and do bond resistance tests in accordance with FIGURE 24. 8. Install the E3-1 electronics shelf to the airplane in accordance with FIGURE 25. 9. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer to SWPM 20-10-11 as an accepted procedure. 10. Install the flight control system electronics unit (CSEU) modules on E3-1 electronics shelf. Refer to 757 AMM 27-09-00 as an accepted procedure. 11. Close the circuit breakers that follow and remove the "DO-NOT-CLOSE" tags: NumberNamePanel / Location C1560YAW DAMPER LP11 / A18 C1538CSEU 1L-AC orP11 / C6 FLT CONT ELEC 1L AC C1534CSEU 1L-DC orP11 / C7 FLT CONT ELEC 1L DC C1537CSEU 2L-AC orP11 / C8 FLT CONT ELEC 2L AC C1533CSEU 2L-DC orP11 / C9 FLT CONT ELEC 2L DC 12. Do the CSEU Modules Installation Test. Refer to 757 AMM 27-09-00 as an accepted procedure. 13. Put the airplane back to a serviceable condition. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1: June 30, 2010 56 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 57 (OCR) BOEING SERVICE BULLETIN 757-27A0152 ALERT ALERT This Figure applies only to: Group 1-5, Configuration 1. E3-1 ELECTRONICS SHELF SEE A SEE E3 RACK STANCHION INBD FWD TRAY 1445353 FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL (SHEET 1 OF 3) Original Issue: April 29, 2009 Revision 1 June 30, 2010 BOEING PROPRIETARY - 757-27A0152 Copyright © Unpublished Work - See page 1 for details. 57 of 156 ### Page 58 (OCR) BOEING SERVICE BULLETIN 757-27A0152 ALERT ALERT E3 RACK STANCHION E3 RACK TRAY _ STANCHION TRAY INBD INBD FWD FWD E3 RACK B ALTERNATE CONFIGURATION STANCHION E3 RACK STANCHION UP UP > INBD — INBD A-A 8-8 (ROTATED 180 DEGREES) FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL (SHEET 2 OF 3) Original Issue: April 29, 2009 Revision 1 June 30, 2010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9911089 ### Page 59 The 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 this figure. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP 2NAS1801-4-11SCREWRemove / Keep1 2NAS1149D0432JWASHERRemove / Keep This step is only applicable if an alternate configuration is not installed. 1BACN10YR3CDNUTRemove / Keep2 1NAS1149D0316JWASHERRemove / Keep 1BACW10P416ANWASHERRemove / Keep 1BACB30NM3K3BOLTRemove / Keep This step is only applicable if an alternate configuration is not installed. 1BACN10YR3CDNUTRemove / Keep3 1BACW10P416ANWASHERRemove / Keep 1NAS1149D0316JWASHERRemove / Keep 1BACB30NM3K5BOLTRemove / Keep This step is only applicable if an alternate configuration is installed. 2BACN10YR3CDNUTRemove / Keep4 2NAS1149D0316JWASHERRemove / Keep 2BACW10P416ANWASHERRemove / Keep 2BACB30NM3K5BOLTRemove / Keep This step is only applicable if an alternate configuration is installed. 2BACN10YR3CDNUTRemove / Keep5 2BACW10P416ANWASHERRemove / Keep 2NAS1149D0316JWASHERRemove / Keep 2BACB30NM3K5BOLTRemove / Keep 1BACN10YR3CDNUTRemove / Keep6 1NAS1149D0316HWASHERRemove / Keep 1-JUMPERRemove / Keep from airplane.1-E3-1 ELECTRONIC SHELF Remove / Keep7 FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL (SHEET 3 OF 3) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1 June 30, 2010 59 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT ### Page 60 This Figure applies only to: Group 1-5, Configuration 1. FIGURE 2: E3-1 ELECTRONICS SHELF - RELAY BRACKET INSTALLATION (SHEET 1 OF 7) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 29, 2009 757-27A0152Revision 1 June 30, 2010 60 of 156 BOEING SERVICE BULLETIN 757-27A0152 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/757-27a0152/file/f85e6119deca.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.