# Boeing Special Attention Service Bulletin 757-22-0096: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-7525; AD 2016-25-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Special Attention Service Bulletin 757-22-0096](https://openairdocs.org/service-documents/boeing/sb-757-22-0096.md)
- Title as filed: U.S. DOT/FAA - SB-757-22-0096
- Pages: 224
- PDF: https://openairdocs.org/files/sha256/e2/e5/e2e58aa5a0109f074a51faa5c4af8913ad840282c23e312a6eb47339cbb3167e
- Page: https://openairdocs.org/service-documents/boeing/sb-757-22-0096/file/e2e58aa5a010

## Text

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### Page 1

Commercial 
Airplanes
757
Service Bulletin
SPECIAL ATTENTION
Number: 757-22-0096
Original Issue: March 23, 2015
ATA System: 2212 2222 3209
SUBJECT: AUTOFLIGHT - Automatic Stabilizer Trim System - On-Ground Stabilizer Autotrim
Inhibit System Installation
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2015 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: March 23, 2015
757-22-0096
1 of 224
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Table of Contents
Summary ...................................................... 7
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 8
E. Compliance .............................................. 2 0
F. Approval ............................................... 2 1
G. Manpower .............................................. 2 1
H. Weight and Balance Changes .................................... 2 3
I. Electrical Load Data ......................................... 2 4
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 5
L. Interchangeability and Intermixability of Parts ........................... 2 5
M. Software Accomplishment Summary ................................ 2 5
2. MATERIAL INFORMATION ........................................ 2 7
A. Material - Price and Availability ................................... 2 7
B. Industry Support Information .................................... 2 9
C. Parts Necessary for Each Airplane ................................. 2 9
1. Kits/Parts ............................................ 2 9
2. Parts and Materials Supplied by the Operator ........................ 4 0
3. Parts Modified and Reidentified ................................ 4 0
4. Parts Removed and Not Replaced .............................. 4 0
D. Parts Necessary to Change Spares ................................. 4 0
E. Special Tooling - Price and Availability ............................... 4 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 1
A. GENERAL INFORMATION ..................................... 4 1
B. WORK INSTRUCTIONS ....................................... 4 2
FIGURE 1: MAIN EQUIPMENT CENTER - SERVICE PANEL - AUTO TRIM TEST SWITCH INSTALLATION
[Group 1-2, 4-5] ......................................... 6 2
FIGURE 2: MAIN EQUIPMENT CENTER - SERVICE PANEL - AUTO TRIM TEST SWITCH INSTALLATION
[Group 3] ............................................ 6 6
FIGURE 3: MAIN EQUIPMENT CENTER - P36 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE W1154 - WIRING ROUTING [Group 1] ................... 7 0
FIGURE 4: MAIN EQUIPMENT CENTER - P36 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE W1154 -WIRING CHANGE [Group 1] .................... 7 2
FIGURE 5: MAIN EQUIPMENT CENTER - P37 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE W1164 - WIRING ROUTING [Group 1] ................... 7 4
FIGURE 6: MAIN EQUIPMENT CENTER - P37 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE W1164 - WIRING CHANGE [Group 1] ................... 7 6
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FIGURE 7: MAIN EQUIPMENT CENTER - E3-1, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE 4501 - WIRING ROUTING [Group 1] ................... 7 8
FIGURE 8: MAIN EQUIPMENT CENTER - E3-1, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE 4501 - WIRING CHANGE [Group 1] .................... 8 3
FIGURE 9: MAIN EQUIPMENT CENTER - E3-3, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4505 - WIRING ROUTING [Group 1] .................. 8 5
FIGURE 10: MAIN EQUIPMENT CENTER - E3-3, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4505 - WIRING CHANGE [Group 1] ................... 9 2
FIGURE 11: MAIN EQUIPMENT CENTER - E3-2, E2-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4503 - WIRING ROUTING [Group 1] .................. 9 4
FIGURE 12: MAIN EQUIPMENT CENTER - E3-2, E2-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4503 - WIRING CHANGE [Group 1] .................. 1 0 1
FIGURE 13: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2060 - WIRING ROUTING [Group 1] . 103
FIGURE 14: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2060 - WIRING CHANGE [Group 1] . 105
FIGURE 15: MAIN EQUIPMENT CENTER - WIRE BUNDLE W4402 - WIRING ROUTING [Group 1] . 107
FIGURE 16: MAIN EQUIPMENT CENTER - WIRE BUNDLE W4402 - WIRING CHANGE [Group 1] . 108
FIGURE 17: MAIN EQUIPMENT CENTER - P36 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE W1260 - WIRING ROUTING [Group 2-5] ................. 1 1 0
FIGURE 18: MAIN EQUIPMENT CENTER - P36 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE W1260 - WIRING CHANGE [Group 2-5] .................. 1 1 1
FIGURE 19: MAIN EQUIPMENT CENTER - P37 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE 1270 - WIRING ROUTING [Group 2-5] .................. 1 1 3
FIGURE 20: MAIN EQUIPMENT CENTER - P37 MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL -
WIRE BUNDLE 1270 - WIRING CHANGE [Group 2-5] ................... 1 1 4
FIGURE 21: MAIN EQUIPMENT CENTER - E2-1, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4471 - WIRING ROUTING [Group 2-3] ................ 1 1 6
FIGURE 22: MAIN EQUIPMENT CENTER - E2-1, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4471 - WIRING CHANGE [Group 2-3] ................. 1 2 4
FIGURE 23: MAIN EQUIPMENT CENTER - E2-3, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4475 - WIRING ROUTING [Group 2-3] ................ 1 2 7
FIGURE 24: MAIN EQUIPMENT CENTER - E2-3, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4475 - WIRING CHANGE [Group 2-3] ................. 1 3 5
FIGURE 25: MAIN EQUIPMENT CENTER - E2-2, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4473 - WIRING ROUTING [Group 2-3] ................ 1 3 8
FIGURE 26: MAIN EQUIPMENT CENTER - E2-2, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4473 - WIRING CHANGE [Group 2-3] ................. 1 4 5
FIGURE 27: MAIN EQUIPMENT CENTER - E2-1, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4471 - WIRING ROUTING [Group 4] .................. 1 4 8
FIGURE 28: MAIN EQUIPMENT CENTER - E2-1, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4471 - WIRING CHANGE [Group 4] .................. 1 5 6
FIGURE 29: MAIN EQUIPMENT CENTER - E2-3, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4475 - WIRING ROUTING [Group 4] .................. 1 5 8
FIGURE 30: MAIN EQUIPMENT CENTER - E2-3, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4475 - WIRING CHANGE [Group 4] .................. 1 6 6
FIGURE 31: MAIN EQUIPMENT CENTER - E2-2, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4473 - WIRING ROUTING [Group 4] .................. 1 6 8
FIGURE 32: MAIN EQUIPMENT CENTER - E2-2, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4473 - WIRING CHANGE [Group 4] .................. 1 7 4
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FIGURE 33: MAIN EQUIPMENT CENTER - E2-1, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4471 - WIRING ROUTING [Group 5] .................. 1 7 6
FIGURE 34: MAIN EQUIPMENT CENTER - E2-1, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4471 - WIRING CHANGE [Group 5] .................. 1 8 4
FIGURE 35: MAIN EQUIPMENT CENTER - E2-3, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4475 - WIRING ROUTING [Group 5] .................. 1 8 6
FIGURE 36: MAIN EQUIPMENT CENTER - E2-3, E3-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4475 - WIRING CHANGE [Group 5] .................. 1 9 4
FIGURE 37: MAIN EQUIPMENT CENTER - E2-2, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4473 - WIRING ROUTING [Group 5] .................. 1 9 6
FIGURE 38: MAIN EQUIPMENT CENTER - E2-2, E4-1 ELECTRONICS SHELVES AND SERVICE PANEL
- WIRE BUNDLE W4473 - WIRING CHANGE [Group 5] .................. 2 0 3
FIGURE 39: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2260 - WIRING ROUTING [Group 2-3] . 206
FIGURE 40: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2260 - WIRING ROUTING [Group 4] . 209
FIGURE 41: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2260 - WIRING ROUTING [Group 5] . 214
FIGURE 42: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2260 - WIRING CHANGE [Group 2-5] . 218
FIGURE 43: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2072 - WIRING ROUTING [Group 2-5] . 220
FIGURE 44: MAIN EQUIPMENT CENTER - WIRE BUNDLE W2072 - WIRING CHANGE [Group 2-5] . 222
APPENDIX A: PART DEMAND INTENT ................................... 2 2 4
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### Page 7

Commercial 
Airplanes
757
Service Bulletin
SPECIAL ATTENTION
SummaryNumber: 757-22-0096Original Issue: March 23, 2015
ATA System: 2212 2222 3209
SUBJECT: AUTOFLIGHT - Automatic Stabilizer Trim System - On-Ground Stabilizer Autotrim
Inhibit System Installation
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will introduce changes to prevent engagement of the automatic stabilizer
trim system while on ground. As a result of uncommanded autopilot engagement, the automatic stabilizer trim
system can be engaged while on the ground and has potential to cause stabilizer movement outside of the
takeoff settings. The root cause of the uncommanded autopilot engagement at airplane takeoffs was not
determined at the time of release of this service bulletin. Any one of multiple possible single failures in the
Autopilot Flight Director System can cause an uncommanded engagement of the autopilot. If this service bulletin
is not accomplished, an on-ground autopilot engagement could cause the stabilizer to be trimmed outside of
the greenband limits, which could increase the possibility of high-speed rejected takeoff (RTO) and/or reduced
controllability of the airplane.
The relays and wiring are modified to open and close the Flight Control Computer (FCC) analog output that
controls the stabilizer trim adjustment. The relays are operated by the air-ground switch and are open when the
air-ground switch is in the on-ground position. A momentary action ground test switch is installed to bypass the
air/ground contacts to allow testing of the Automatic Trim function when the airplane is on the ground. A repeated
interval functional check of the new test switch, given in this service bulletin, will be necessary.
This service bulletin gives instructions to utilize existing relays and install wiring to inhibit the Automatic Stabilizer
Trim Arm discrete when the airplane is on ground. In addition, it also provides instruction to install a two position
momentary contact test switch in the Main Equipment Center to allow for ground testing of the autotrim function.
Boeing Service Related Problem (SRP) 757-SRP-22-0035 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 757 FTD 22-12001 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
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ReferenceAffectedPlanning Data
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer to
Paragraph 1.K., Publications Affected, for affected publications.
The changes in this service bulletin will not change the Engine Indication and Crew Alerting System (EICAS).
Group 1:
1. In the Main Equipment Center, do these changes:
a. At the Service Panel located right and outboard of the E2 equipment rack, install the Test Switch
S70007 and guard.
b. In the P36 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1154.
c. In the P37 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1164.
d. Between the Test Switch S70007 and E3-1 and E4-1 shelf assemblies, change Wire Bundle
W4501.
e. Between the Test Switch S70007 and E3-3 and E4-1 shelf assemblies, change Wire Bundle W4505
f. Between the Test Switch S70007 and E3-2 and E2-1 shelf assemblies, change Wire Bundle
W4503.
g. Between the Test Switch S70007 and the P36 Miscellaneous Electrical Equipment Panel, change
Wire Bundle W2060.
h. Between the Test Switch S70007 and the P37 Miscellaneous Electrical Equipment Panel, change
Wire Bundle W4402.
2. Do a test to make sure the changed Automatic Stabilizer Trim System operates correctly.
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Group 2-5:
1. In the Main Equipment Center, do these changes:
a. At the Service Panel located right and outboard of the E2 equipment rack, install the Test Switch
S70007 and guard.
b. In the P36 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1260.
c. In the P37 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1270.
d. Between the Test Switch S70007 and E2-1 and E3-1 shelf assemblies, change Wire Bundle
W4471.
e. Between the Test Switch S70007 and E2-3 and E3-1 shelf assemblies, change Wire Bundle
W4475.
f. Between the Test Switch S70007 and E2-2 and E4-1 shelf assemblies, change Wire Bundle
W4473.
g. Between the Test Switch S70007 and the P36 Miscellaneous Electrical Equipment Panel, change
Wire Bundle W2260.
h. Between the Test Switch S70007 and the P37 Miscellaneous Electrical Equipment Panel, change
Wire Bundle W2072.
2. Do a test to make sure the changed Automatic Stabilizer Trim System operates correctly.
EFFECTIVITY
757-200/-200CB/-200PF/-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, 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 24 months after the original
issue date of this service bulletin.
Boeing recommends that all airplanes do the Automatic Stabilizer Trim System Operational Test each 1,500
flight hour interval. Refer to Paragraph 3.B., Work Instructions, Step 11, for the test.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
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MANPOWER
Elapsed HoursTotal Task HoursAirplanes
34.7069.45Group 1
41.1082.25Group 2
41.1082.25Group 3
40.1580.35Group 4
38.0576.15Group 5
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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### Page 11 (OCR)

BOEING SERVICE BULLETIN 757-22-0096
INSTALL SWITCH AND CHANGE
WIRING FOR AUTO TRIM INHIBIT
SYSTEM INSTALLATION
MAIN EQUIPMENT CENTER
GROUP 2-5
INSTALL SWITCH AND CHANGE
WIRING FOR AUTO TRIM INHIBIT
SYSTEM INSTALLATION
MAIN EQUIPMENT CENTER  2380460
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### Page 13

Commercial 
Airplanes
757
Service Bulletin
SPECIAL ATTENTION
Number: 757-22-0096
Original Issue: March 23, 2015
ATA System: 2212 2222 3209
SUBJECT: AUTOFLIGHT - Automatic Stabilizer Trim System - On-Ground Stabilizer Autotrim
Inhibit System Installation
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 757-200, 757-200CB, 757-200PF, and 757-300 Airplanes in
5 Groups. The Variable Numbers and Group Information for the applicable airplanes are given
below. Refer to PRR 54530-301RS for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes with different autoflight system wiring configuration changes-1
Airplanes with different autoflight system wiring configuration changes-2
Airplanes with different autoflight system wiring configuration changes
and switch installation
-3
Airplanes with different autoflight system wiring configuration changes-4
Airplanes with different autoflight system wiring configuration changes-5
Airplane Models:
757-200, 757-200CB, 757-200PF, 757-300
GroupVariable Number
1NA001
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GroupVariable Number
2NA002
2NA005
2NA008
2NA021 - NA028
2NA195
2NA197 - NA199
2NA201 - NA213
2NA215 - NA239
2NA301 - NA305
2NA342 - NA344
2NA346 - NA352
2NA392 - NA399
2NA401 - NA408
2NA441 - NA447
2NA502 - NA505
2NA509 - NA510
2NA512 - NA535
2NA537 - NA538
2NA541 - NA546
2NA548 - NA586
2NB001 - NB004
2NB021 - NB023
2NB036 - NB041
2NB052 - NB053
2NB061 - NB068
2NB070 - NB073
2NB079
2NB131 - NB148
2NB161 - NB162
2NB167 - NB168
2NB201 - NB204
2NB221 - NB228
2NB230
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GroupVariable Number
2NB236
2NB239
2NB261 - NB267
2NB291 - NB299
2NB301 - NB302
2NB311 - NB312
2NB321 - NB331
2NB421 - NB424
2NB426 - NB438
2NB446
2NB451 - NB454
2NB501 - NB523
2NB561
2NB571
2NB581 - NB583
2NC001 - NC003
2NC005
2NC008
2NC012 - NC013
2NC017 - NC018
2NC020 - NC022
2NC024
2NC026
2NC029 - NC033
2NC042
2NC051 - NC052
2NC056 - NC062
2NC066 - NC084
2NC091 - NC094
2NC151
2NC161
2NC901 - NC951
2NC971
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GroupVariable Number
2NC973 - NC974
2ND002
2ND004
2ND011 - ND027
2ND029 - ND044
2ND046 - ND059
2ND111 - ND113
2ND161 - ND166
2ND168 - ND199
2ND201 - ND203
2ND221 - ND225
2ND241 - ND248
2ND301 - ND322
2ND401
2ND891
2ND895
2NE001 - NE004
2NE006 - NE008
2NE011 - NE088
2NE092 - NE094
2NE141 - NE150
2NE161 - NE177
2NE201 - NE204
2NE301
2NE311 - NE325
5NJ001 - NJ004
5NJ031 - NJ032
5NJ551 - NJ555
4NL001 - NL002
4NL006 - NL017
5NL101 - NL109
5NL141
5NL601 - NL616
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GroupVariable Number
2NN001 - NN002
2NN051 - NN052
2NP901 - NP904
2NS601 - NS616
2NT001 - NT009
2NT201 - NT202
2NT231 - NT234
2NT237 - NT240
2NT242
2NT245 - NT248
2NT281 - NT289
2NT341 - NT347
2NT351 - NT360
2NT371 - NT373
2NT375 - NT379
2NT381 - NT386
2NT401 - NT409
2NT411 - NT412
2NT426 - NT427
2NT431 - NT432
2NT436 - NT438
2NT441 - NT442
2NT446
2NT701 - NT742
3NT743 - NT750
2NT751 - NT769
2NT791 - NT796
2NT861 - NT862
2NT881 - NT885
2NT901 - NT916
3NT971 - NT983
2NT984 - NT985
2NU031 - NU038
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GroupVariable Number
4NU701 - NU705
4NU721 - NU728
4NU731 - NU732
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will introduce changes to prevent engagement of the automatic
stabilizer trim system while on ground. As a result of uncommanded autopilot engagement, the automatic
stabilizer trim system can be engaged while on the ground and has potential to cause stabilizer
movement outside of the takeoff settings. The root cause of the uncommanded autopilot engagement
at airplane takeoffs was not determined at the time of release of this service bulletin. Any one of multiple
possible single failures in the Autopilot Flight Director System can cause an uncommanded engagement
of the autopilot. If this service bulletin is not accomplished, an on-ground autopilot engagement could
cause the stabilizer to be trimmed outside of the greenband limits, which could increase the possibility
of high-speed rejected takeoff (RTO) and/or reduced controllability of the airplane.
The relays and wiring are modified to open and close the Flight Control Computer (FCC) analog output
that controls the stabilizer trim adjustment. The relays are operated by the air-ground switch and are
open when the air-ground switch is in the on-ground position. A momentary action ground test switch
is installed to bypass the air/ground contacts to allow testing of the Automatic Trim function when the
airplane is on the ground. A repeated interval functional check of the new test switch, given in this
service bulletin, will be necessary.
This service bulletin gives instructions to utilize existing relays and install wiring to inhibit the Automatic
Stabilizer Trim Arm discrete when the airplane is on ground. In addition, it also provides instruction to
install a two position momentary contact test switch in the Main Equipment Center to allow for ground
testing of the autotrim function.
Boeing Service Related Problem (SRP) 757-SRP-22-0035 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 757 FTD 22-12001 is related to this service bulletin.
D. Description
Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer
to Paragraph 1.K., Publications Affected, for affected publications.
The changes in this service bulletin will not change the Engine Indication and Crew Alerting System
(EICAS).
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### Page 19

Group 1:
1. In the Main Equipment Center, do these changes:
a. At the Service Panel located right and outboard of the E2 equipment rack, install the Test
Switch S70007 and guard.
b. In the P36 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1154.
c. In the P37 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1164.
d. Between the Test Switch S70007 and E3-1 and E4-1 shelf assemblies, change Wire Bundle
W4501.
e. Between the Test Switch S70007 and E3-3 and E4-1 shelf assemblies, change Wire Bundle
W4505
f. Between the Test Switch S70007 and E3-2 and E2-1 shelf assemblies, change Wire Bundle
W4503.
g. Between the Test Switch S70007 and the P36 Miscellaneous Electrical Equipment Panel,
change Wire Bundle W2060.
h. Between the Test Switch S70007 and the P37 Miscellaneous Electrical Equipment Panel,
change Wire Bundle W4402.
2. Do a test to make sure the changed Automatic Stabilizer Trim System operates correctly.
Group 2-5:
1. In the Main Equipment Center, do these changes:
a. At the Service Panel located right and outboard of the E2 equipment rack, install the Test
Switch S70007 and guard.
b. In the P36 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1260.
c. In the P37 Miscellaneous Electrical Equipment Panel, change Wire Bundle W1270.
d. Between the Test Switch S70007 and E2-1 and E3-1 shelf assemblies, change Wire Bundle
W4471.
e. Between the Test Switch S70007 and E2-3 and E3-1 shelf assemblies, change Wire Bundle
W4475.
f. Between the Test Switch S70007 and E2-2 and E4-1 shelf assemblies, change Wire Bundle
W4473.
g. Between the Test Switch S70007 and the P36 Miscellaneous Electrical Equipment Panel,
change Wire Bundle W2260.
h. Between the Test Switch S70007 and the P37 Miscellaneous Electrical Equipment Panel,
change Wire Bundle W2072.
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### Page 20

2. Do a test to make sure the changed Automatic Stabilizer Trim System operates correctly.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1, 3:
Affected Maintenance Zones
ZoneModel
119757-200
Group 2:
Affected Maintenance Zones
ZoneModel
119757-200, 757-200CB, 757-
200PF
Group 4:
Affected Maintenance Zones
ZoneModel
119757-300
Group 5:
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 24 months after the
original issue date of this service bulletin.
Boeing recommends that all airplanes do the Automatic Stabilizer Trim System Operational Test each
1,500 flight hour interval. Refer to Paragraph 3.B., Work Instructions, Step 11, for the test.
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### Page 21

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 change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
0.750.751FIGURE 1
2.505.002FIGURE 3 and FIGURE 4
1.252.502FIGURE 5 and FIGURE 6
5.5511.102FIGURE 7 and FIGURE 8
5.2010.402FIGURE 9 and FIGURE 10
7.0514.102FIGURE 11 and FIGURE 12
6.1012.202FIGURE 13 and FIGURE 14
3.507.002FIGURE 15 and FIGURE 16
1.002.002Close Access
0.802.403Test
34.7069.45TOTAL FOR EACH AIRPLANE
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### Page 22

Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
0.750.751FIGURE 1
2.505.002FIGURE 17 and FIGURE 18
1.252.502FIGURE 19 and FIGURE 20
9.3018.602FIGURE 21 and FIGURE 22
9.3018.602FIGURE 23 and FIGURE 24
6.8513.702FIGURE 25 and FIGURE 26
4.759.502FIGURE 39 and FIGURE 42
3.607.202FIGURE 43 and FIGURE 44
1.002.002Close Access
0.802.403Test
41.1082.25TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
0.750.751FIGURE 2
2.505.002FIGURE 17 and FIGURE 18
1.252.502FIGURE 19 and FIGURE 20
9.3018.602FIGURE 21 and FIGURE 22
9.3018.602FIGURE 23 and FIGURE 24
6.8513.702FIGURE 25 and FIGURE 26
4.759.502FIGURE 39 and FIGURE 42
3.607.202FIGURE 43 and FIGURE 44
1.002.002Close Access
0.802.403Test
41.182.25TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
0.750.751FIGURE 1
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Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
2.505.002FIGURE 17 and FIGURE 18
1.252.502FIGURE 19 and FIGURE 20
8.7017.402FIGURE 27 and FIGURE 28
8.7017.402FIGURE 29 and FIGURE 30
7.1014.202FIGURE 31 and FIGURE 32
4.759.502FIGURE 40 and FIGURE 42
3.607.202FIGURE 43 and FIGURE 44
1.002.002Close Access
0.802.403Test
40.1580.35TOTAL FOR EACH AIRPLANE
Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
0.750.751FIGURE 1
2.505.002FIGURE 17 and FIGURE 18
1.252.502FIGURE 19 and FIGURE 20
8.1016.202FIGURE 33 and FIGURE 34
8.1016.202FIGURE 35 and FIGURE 36
6.2012.402FIGURE 37 and FIGURE 38
4.759.502FIGURE 41 and FIGURE 42
3.607.202FIGURE 43 and FIGURE 44
1.002.002Close Access
0.802.403Test
38.0576.15TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 875+ 1.9757-200
+ 875+ 1.9757-200CB
+ 875+ 1.9757-200PF
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### Page 24

Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 570+ 1.9757-300
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 757-SRP-22-0035
b. Service Bulletin Index D624N001
c. Standard Overhaul Practices Manual (SOPM) 20-50-01, 20-50-05
d. Standard Wiring Practices Manual (SWPM) 20-00-13, 20-10-11, 20-10-12, 20-10-19, 20-30-11,
20-30-12, 20-30-16, 20-61-11, 20-74-02, 20-74-11, 20-81-19
e. 757 Aircraft Maintenance Manual (AMM) 06-41-00, 20-10-23, 22-00-02, 24-22-00, 29-11-00
f. 757 Fleet Team Digest (FTD) 22-12001
g. 757 Wiring Diagram Manual (WDM) 22-22-11
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
SERVICE PANEL INSTALLATION - MISCELLANEOUS EQUIPMENT CENTER284N1360
ELECTRICAL CABLE INSTALLATION - P36 MISCELLANEOUS RELAY PANEL288N0104
ELECTRICAL CABLE INSTALLATION - P37 MISCELLANEOUS RELAY PANEL288N0105
ELECTRICAL CABLE INSTALLATION - FLOOR BEAMS STA 297-440288N4151
ELECTRICAL CABLE INSTALLATION - E1 AND E2 ELECTRONIC RACKS288N4329
ELECTRICAL CABLE INSTALLATION - E3 AND E4 ELECTRONIC RACKS288N4330
ELECTRICAL CABLE INSTALLATION - FLOOR BEAMS STA 440-660288N4352
ELECTRICAL CABLE INSTALLATION - LEFT ELECTRONICS BAY STA 395-560288N4361
ELECTRICAL CABLE INSTALLATION - E1 AND E2 ELECTRONIC RACKS288N4362
ELECTRICAL CABLE INSTALLATION - RIGHT ELECTRONICS BAY STA 395-560288N4392
ELECTRICAL CABLE INSTALLATION - LEFT SIDE FLOOR BEAMS STA 440-660288N4397
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### Page 25

TitleDrawing Number
ELECTRICAL CABLE INSTALLATION - RIGHT SIDE FLOOR BEAMS STA 440-660288N4398
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
22-22757 Aircraft Maintenance Manual
22-22757 Wiring Diagram Manual
22-04757 Fault Isolation Manual
34-12757 Illustrated Parts Catalog
22-22757 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.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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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. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Group 1:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
3,155.002907March 1, 2015TOP KIT - RETROFIT
KIT - AUTOTRIM TEST
SWITCH INSTALLA-
TION
012N8929-107
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### Page 28

Group 2-3:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
3,236.0029010March 2, 2015TOP KIT - RETROFIT
KIT - AUTOTRIM TEST
SWITCH INSTALLA-
TION
012N8929-108
10March 16,
2015
10March 30,
2015
10April 13, 2015
10April 27, 2015
20May 26, 2015
20June 23, 2015
20July 22, 2015
20August 19,
2015
30October 1,
2015
30November 12,
2015
30January 6,
2016
30February 17,
2016
30March 30,
2016
30May 11, 2016
40July 8, 2016
40September 2,
2016
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### Page 29

Group 4:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
3,231.0029010March 1, 2015TOP KIT - RETROFIT
KIT - AUTOTRIM TEST
SWITCH INSTALLA-
TION
012N8929-109
5March 16,
2015
Group 5:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
3,231.002907March 1, 2015TOP KIT - RETROFIT
KIT - AUTOTRIM TEST
SWITCH INSTALLA-
TION
012N8929-110
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
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### Page 30

Group 1:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-107
TOP KIT -
RETROFIT KIT -
AUTOTRIM TEST
SWITCH INSTAL-
LATION
-012N8929-107
ASSY W11541280N3376-114
ASSY W11641280N3376-115
ASSY W45011280N3376-116
ASSY W45031280N3376-117
ASSY W45051280N3376-118
ASSY W20601280N3376-119
ASSY W44021280N3376-120
SWITCH GUARD1405-112
(a)CLAMP, LOOP40BACC10DK10
(a)CLAMP, LOOP40BACC10DK3
(a)CLAMP, LOOP40BACC10DK7
(a)CLAMP, LOOP40BACC10GE12
(a)CLAMP, LOOP40BACC10GE20
(a)CLAMP, LOOP40BACC10GE27
(a)CLAMP, LOOP40BACC10GE36
(a)CLAMP, LOOP40BACC10GE44
(a)CLAMP, LOOP40BACC10GE54
(a)BOLT50BACS12HN3-10
(a)BOLT50BACS12HN3-12
(a)STRAP250BACS38K3
SWITCH, TOGGLE1MS24525-26
(a)WASHER50NAS1149D0332J
(a)SPACERS FOR
RIVETS
50NAS42DD6-32FC
(a)SPACERS FOR
RIVETS
50NAS42DD6-64FC
(a) There are more parts than are necessary.
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### Page 31

Group 1:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-119-118-117-116-115-114
ASSY W1154.....-280N3376-114
ASSY W1164....-.280N3376-115
ASSY W4501...-..280N3376-116
ASSY W4503..-...280N3376-117
ASSY W4505.-....280N3376-118
ASSY W2060-.....280N3376-119
WIRE - RAW MA-
TERIAL
.....1280N3376-114W
WIRE - RAW MA-
TERIAL
....1.280N3376-115W
WIRE - RAW MA-
TERIAL
...1..280N3376-116W
WIRE - RAW MA-
TERIAL
..1...280N3376-117W
WIRE - RAW MA-
TERIAL
.1....280N3376-118W
WIRE - RAW MA-
TERIAL
1.....280N3376-119W
ID - SPLICE...1..280N3376-10301
ID - SPLICE...1..280N3376-10302
ID - SPLICE..1...280N3376-10401
ID - SPLICE..1...280N3376-10402
ID - SPLICE.1....280N3376-10501
ID - SPLICE.1....280N3376-10502
TERMINAL1.....324484
CONTACT, PIN.33335BACC47CN1S
CONTACT, SOCK-
ET
5.....BACC47CP1S
CONTACT, SOCK-
ET
....35BACC47ER1
TERMINAL.222..BACT12AR122
SPLICE.222..D-436-37
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Group 1:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-120
ASSY W4402-280N3376-120
WIRE - RAW MA-
TERIAL
1280N3376-120W
CONTACT, SOCK-
ET
3BACC47CP1S
Group 2-3:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-108
TOP KIT -
RETROFIT KIT -
AUTOTRIM TEST
SWITCH INSTAL-
LATION
-012N8929-108
ASSY W12601280N3376-101
ASSY W12701280N3376-102
ASSY W44711280N3376-103
ASSY W44731280N3376-104
ASSY W44751280N3376-105
ASSY W22601280N3376-106
ASSY W20721280N3376-107
SWITCH GUARD1405-112
(a)CLAMP, LOOP40BACC10DK10
(a)CLAMP, LOOP40BACC10DK3
(a)CLAMP, LOOP40BACC10DK7
(a)CLAMP, LOOP40BACC10GE12
(a)CLAMP, LOOP40BACC10GE20
(a)CLAMP, LOOP40BACC10GE27
(a)CLAMP, LOOP40BACC10GE36
(a)CLAMP, LOOP40BACC10GE44
(a)CLAMP, LOOP40BACC10GE54
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### Page 33

Group 2-3:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-108
(a)BOLT50BACS12HN3-10
(a)BOLT50BACS12HN3-12
(a)STRAP250BACS38K3
SWITCH, TOGGLE1MS24525-26
(a)WASHER50NAS1149D0332J
(a)SPACERS FOR
RIVETS
50NAS42DD6-32FC
(a)SPACERS FOR
RIVETS
50NAS42DD6-64FC
(a) There are more parts than are necessary.
Group 2-3:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-106-105-104-103-102-101
ASSY W1260.....-280N3376-101
ASSY W1270....-.280N3376-102
ASSY W4471...-..280N3376-103
ASSY W4473..-...280N3376-104
ASSY W4475.-....280N3376-105
ASSY W2260-.....280N3376-106
WIRE - RAW MA-
TERIAL
.....1280N3376-101W
WIRE - RAW MA-
TERIAL
....1.280N3376-102W
WIRE - RAW MA-
TERIAL
...1..280N3376-103W
WIRE - RAW MA-
TERIAL
..1...280N3376-104W
WIRE - RAW MA-
TERIAL
.1....280N3376-105W
WIRE - RAW MA-
TERIAL
1.....280N3376-106W
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### Page 34

Group 2-3:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-106-105-104-103-102-101
ID - SPLICE...1..280N3376-10301
ID - SPLICE...1..280N3376-10302
ID - SPLICE..1...280N3376-10401
ID - SPLICE..1...280N3376-10402
ID - SPLICE.1....280N3376-10501
ID - SPLICE.1....280N3376-10502
CONTACT, PIN.33335BACC47CN1S
CONTACT, SOCK-
ET
5.....BACC47CP1S
CONTACT, SOCK-
ET
....35BACC47ER1
TERMINAL.222..BACT12AR122
SPLICE.222..D-436-37
Group 2-3:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-107
ASSY W2072-280N3376-107
WIRE - RAW MA-
TERIAL
1280N3376-107W
CONTACT, SOCK-
ET
3BACC47CP1S
Group 4:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-109
TOP KIT -
RETROFIT KIT -
AUTOTRIM TEST
SWITCH INSTAL-
LATION
-012N8929-109
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### Page 35

Group 4:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-109
ASSY W12601280N3376-101
ASSY W12701280N3376-102
ASSY W22601280N3376-106
ASSY W20721280N3376-107
ASSY W44711280N3376-108
ASSY W44731280N3376-109
ASSY W44751280N3376-110
SWITCH GUARD1405-112
(a)CLAMP, LOOP40BACC10DK10
(a)CLAMP, LOOP40BACC10DK3
(a)CLAMP, LOOP40BACC10DK7
(a)CLAMP, LOOP40BACC10GE12
(a)CLAMP, LOOP40BACC10GE20
(a)CLAMP, LOOP40BACC10GE27
(a)CLAMP, LOOP40BACC10GE36
(a)CLAMP, LOOP40BACC10GE44
(a)CLAMP, LOOP40BACC10GE54
(a)BOLT50BACS12HN3-10
(a)BOLT50BACS12HN3-12
(a)STRAP250BACS38K3
SWITCH, TOGGLE1MS24525-26
(a)WASHER50NAS1149D0332J
(a)SPACERS FOR
RIVETS
50NAS42DD6-32FC
(a)SPACERS FOR
RIVETS
50NAS42DD6-64FC
(a) There are more parts than are necessary.
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### Page 36

Group 4:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-109-108-107-106-102-101
ASSY W1260.....-280N3376-101
ASSY W1270....-.280N3376-102
ASSY W2260...-..280N3376-106
ASSY W2072..-...280N3376-107
ASSY W4471.-....280N3376-108
ASSY W4473-.....280N3376-109
WIRE - RAW MA-
TERIAL
.....1280N3376-101W
WIRE - RAW MA-
TERIAL
....1.280N3376-102W
WIRE - RAW MA-
TERIAL
...1..280N3376-106W
WIRE - RAW MA-
TERIAL
..1...280N3376-107W
WIRE - RAW MA-
TERIAL
.1....280N3376-108W
WIRE - RAW MA-
TERIAL
1.....280N3376-109W
ID - SPLICE.1....280N3376-10301
ID - SPLICE.1....280N3376-10302
ID - SPLICE1.....280N3376-10401
ID - SPLICE1.....280N3376-10402
CONTACT, PIN....35BACC47CN1S
CONTACT, SOCK-
ET
..35..BACC47CP1S
CONTACT, SOCK-
ET
....35BACC47ER1
TERMINAL22....BACT12AR122
CONTACT, PIN,
SIZE 20
33....CTA-0166
SPLICE22....D-436-37
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### Page 37

Group 4:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-110
ASSY W4475-280N3376-110
WIRE - RAW MA-
TERIAL
1280N3376-110W
ID - SPLICE1280N3376-10501
ID - SPLICE1280N3376-10502
TERMINAL2BACT12AR122
CONTACT, PIN,
SIZE 20
3CTA-0166
SPLICE2D-436-37
Group 5:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-110
TOP KIT -
RETROFIT KIT -
AUTOTRIM TEST
SWITCH INSTAL-
LATION
-012N8929-110
ASSY W12601280N3376-101
ASSY W12701280N3376-102
ASSY W22601280N3376-106
ASSY W20721280N3376-107
ASSY W44711280N3376-111
ASSY W44731280N3376-112
ASSY W44751280N3376-113
SWITCH GUARD1405-112
(a)CLAMP, LOOP40BACC10DK10
(a)CLAMP, LOOP40BACC10DK3
(a)CLAMP, LOOP40BACC10DK7
(a)CLAMP, LOOP40BACC10GE12
(a)CLAMP, LOOP40BACC10GE20
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### Page 38

Group 5:
Kit 012N8929
NotesExisting Part
Number
NameQTYNew Part Number
-110
(a)CLAMP, LOOP40BACC10GE27
(a)CLAMP, LOOP40BACC10GE36
(a)CLAMP, LOOP40BACC10GE44
(a)CLAMP, LOOP40BACC10GE54
(a)BOLT50BACS12HN3-10
(a)BOLT50BACS12HN3-12
(a)STRAP250BACS38K3
SWITCH, TOGGLE1MS24525-26
(a)WASHER50NAS1149D0332J
(a)SPACERS FOR
RIVETS
50NAS42DD6-32FC
(a)SPACERS FOR
RIVETS
50NAS42DD6-64FC
(a) There are more parts than are necessary.
Group 5:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-112-111-107-106-102-101
ASSY W1260.....-280N3376-101
ASSY W1270....-.280N3376-102
ASSY W2260...-..280N3376-106
ASSY W2072..-...280N3376-107
ASSY W4471.-....280N3376-111
ASSY W4473-.....280N3376-112
WIRE - RAW MA-
TERIAL
.....1280N3376-101W
WIRE - RAW MA-
TERIAL
....1.280N3376-102W
WIRE - RAW MA-
TERIAL
...1..280N3376-106W
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### Page 39

Group 5:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-112-111-107-106-102-101
WIRE - RAW MA-
TERIAL
..1...280N3376-107W
WIRE - RAW MA-
TERIAL
.1....280N3376-111W
WIRE - RAW MA-
TERIAL
1.....280N3376-112W
ID - SPLICE.1....280N3376-10301
ID - SPLICE.1....280N3376-10302
ID - SPLICE1.....280N3376-10401
ID - SPLICE1.....280N3376-10402
CONTACT, PIN....35BACC47CN1S
CONTACT, SOCK-
ET
..35..BACC47CP1S
CONTACT, SOCK-
ET
....35BACC47ER1
CONTACT23....BACC47FJ1A
CONTACT2.....BACC47FJ2A
TERMINAL22....BACT12AR122
SPLICE22....D-436-37
Group 5:
Kit 280N3376
NotesExisting Part
Number
NameQTYNew Part Number
-113
ASSY W4475-280N3376-113
WIRE - RAW MA-
TERIAL
1280N3376-113W
ID - SPLICE1280N3376-10501
ID - SPLICE1280N3376-10502
CONTACT3BACC47FJ1A
TERMINAL2BACT12AR122
SPLICE2D-436-37
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### Page 40

2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesNameQtyPart Number/ Specification
(a) (b)LOCKWIRE1 RollMS20995N32
(a) Can be purchased from: The Boeing Company (CAGE: 81205), 7755 East Marginal Way
South, Seattle, Washington 98108.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
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.
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### Page 41

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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 757 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 757
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 757
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
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### Page 42

7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
8. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
9. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
11. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
12. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
15. All wire routing changes should route with existing wire bundles using existing clamps.
Clamping positions may vary. Replace clamps as necessary. Refer to SWPM 20-10-11
as an accepted procedure.
16. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
B. WORK INSTRUCTIONS
Group 1:
1. Remove electrical power from the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
2. Open access door 119BL to get access to the Main Equipment Center. Refer to 757 AMM 06-41-00
as an accepted procedure.
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### Page 43

3. RC - In the Main Equipment Center, install the Test Switch S70007 and the guard 405-112 to the
Service Panel in accordance with FIGURE 1.
4. RC - In the P36 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1154 in accordance with FIGURE 3 and FIGURE 4.
5. RC - In the P37 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1164 in accordance with FIGURE 5 and FIGURE 6.
6. RC - Between the Test Switch S70007 and E3-1 and E4-1 shelf assemblies, install wires and make
changes to Wire Bundle W4501 in accordance with FIGURE 7 and FIGURE 8.
7. RC - Between the Test Switch S70007 and E3-3 and E4-1 shelf assemblies, install wires and make
changes to Wire Bundle W4505 in accordance with FIGURE 9 and FIGURE 10.
8. RC - Between the Test Switch S70007 and E3-2 and E2-1 shelf assemblies, install wires and make
changes to Wire Bundle W4503 in accordance with FIGURE 11 and FIGURE 12.
9. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P36
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2060
in accordance with FIGURE 13 and FIGURE 14.
10. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P37
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W4402
in accordance with FIGURE 15 and FIGURE 16.
11. RC - Do the Automatic Stabilizer Trim System Operational Test to make sure the changed Automatic
Stabilizer Trim System operates correctly:
a. Supply electrical power to the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES
WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER,
FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES.
INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN
HYDRAULIC POWER IS SUPPLIED.
b. Pressurize the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00 as an
accepted procedure.
c. Make sure that the control column is in the neutral position and not restrained.
d. If the Maintenance Control Display Panel (MCDP) is available for this test, do the steps that
follow:
(1) At the main power distribution panel, P6, open the P6-5 door.
(2) Behind the P6-5 door, remove the dust cover from the Connector D41101J.
(3) Connect the MCDP remote control unit to the Connector D41101J.
(4) At the P11 panel, make sure the Engine Indication and Crew Alerting System (EICAS)
circuit breakers on the P11 panel are closed.
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### Page 44

(5) At the P61 panel, on the EICAS maintenance panel, push the switch CONF/MCDP to
show MCDP data on the EICAS bottom display.
NOTE: The same messages that show on the MCDP in the main equipment center will
show on the EICAS bottom display. The indication "MCDP FLT FAULTS" or
"MCDP GRD TEST" is displayed to identify the MCDP mode.
(6) Make sure EICAS bottom display unit shows the message "MCDP OFF".
e. Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and repeat
the test and applicable corrective actions until the test is passed. Refer to 757 AMM 22-00-02
as an accepted procedure.
f. In the main equipment center, cut and remove the lockwire securing the Test Switch S70007
and hold in the "TEST" position and do the steps that follow:
NOTE: The Test Switch S70007 will need to be held in the "TEST" position during the test.
(1) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(2) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(3) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(4) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(5) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(6) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(7) Make sure that the MCDP shows the message "65 IN PROGRESS".
(8) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure that the MCDP shows the message "65 IN PROGRESS".
(11) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
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(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(12) Make sure that the MCDP shows the message "65 A/P ENG C to CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(13) Make sure that the MCDP shows the message "65 IN PROGRESS'.
(14) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(15) Make sure that the MCDP shows the message "TEST COMPLETE".
g. In the main equipment center, return the Test Switch S70007 to the "NORMAL" position and
do the steps that follow:
(1) Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and
repeat the test and applicable corrective actions until the test is passed. Refer to 757
AMM 22-00-02 as an accepted procedure.
(2) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(3) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(4) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(5) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(6) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(7) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(8) Make sure the MCDP shows "65 STAB TRIM FCC L FAIL", then push the YES/ADV
switch.
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### Page 46

(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure the MCDP shows "65 STAB TRIM FCC R FAIL", then push the YES/ADV
switch.
(11) Make sure that the MCDP shows the message "65 A/P ENG C TO CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(12) Make sure the MCDP shows "65 STAB TRIM FCC C FAIL", then push the YES/ADV
switch.
(13) End of test for the changed Automatic Stabilizer Trim System.
(14) On the Test Switch S70007, install new lockwire in the guarded position.
h. Remove pressure from the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00
as an accepted procedure.
12. Close access door. Refer to 757 AMM 06-41-00 as an accepted procedure.
13. Update the airplane scheduled maintenance program to incorporate functional checks with repeat
intervals not to exceed 1,500 flight hours.
14. Put the airplane back to a serviceable condition.
Group 2:
1. Remove electrical power from the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
2. Open access door 119BL to get access to the Main Equipment Center. Refer to 757 AMM 06-41-00
as an accepted procedure.
3. RC - In the Main Equipment Center, install the Test Switch S70007 and the guard 405-112 to the
Service Panel in accordance with FIGURE 1.
4. RC - In the P36 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1260 in accordance with FIGURE 17 and FIGURE 18.
5. RC - In the P37 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1270 in accordance with FIGURE 19 and FIGURE 20.
6. RC - Between the Test Switch S70007 and E2-1 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4471 in accordance with FIGURE 21 and FIGURE 22.
7. RC - Between the Test Switch S70007 and E2-3 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4475 in accordance with FIGURE 23 and FIGURE 24.
8. RC - Between the Test Switch S70007 and E2-2 and E4-1 shelf assemblies, install wires and make
changes to Wire Bundle W4473 in accordance with FIGURE 25 and FIGURE 26.
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### Page 47

9. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P36
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2260
in accordance with FIGURE 39 and FIGURE 42.
10. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P37
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2072
in accordance with FIGURE 43 and FIGURE 44.
11. RC - Do the Automatic Stabilizer Trim System Operational Test to make sure the changed Automatic
Stabilizer Trim System operates correctly:
a. Supply electrical power to the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES
WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER,
FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES.
INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN
HYDRAULIC POWER IS SUPPLIED.
b. Pressurize the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00 as an
accepted procedure.
c. Make sure that the control column is in the neutral position and not restrained.
d. If the Maintenance Control Display Panel (MCDP) is available for this test, do the steps that
follow:
(1) At the main power distribution panel, P6, open the P6-5 door.
(2) Behind the P6-5 door, remove the dust cover from the Connector D41101J.
(3) Connect the MCDP remote control unit to the Connector D41101J.
(4) At the P11 panel, make sure the Engine Indication and Crew Alerting System (EICAS)
circuit breakers on the P11 panel are closed.
(5) At the P61 panel, on the EICAS maintenance panel, push the switch CONF/MCDP to
show MCDP data on the EICAS bottom display.
NOTE: The same messages that show on the MCDP in the main equipment center will
show on the EICAS bottom display. The indication "MCDP FLT FAULTS" or
"MCDP GRD TEST" is displayed to identify the MCDP mode.
(6) Make sure EICAS bottom display unit shows the message "MCDP OFF".
e. Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and repeat
the test and applicable corrective actions until the test is passed. Refer to 757 AMM 22-00-02
as an accepted procedure.
f. In the main equipment center, cut and remove the lockwire securing the Test Switch S70007
and hold in the "TEST" position and do the steps that follow:
NOTE: The Test Switch S70007 will need to be held in the "TEST" position during the test.
Export Controlled ECCN: 9E991 - BOEING
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### Page 48

(1) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(2) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(3) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(4) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(5) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(6) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(7) Make sure that the MCDP shows the message "65 IN PROGRESS".
(8) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure that the MCDP shows the message "65 IN PROGRESS".
(11) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(12) Make sure that the MCDP shows the message "65 A/P ENG C to CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(13) Make sure that the MCDP shows the message "65 IN PROGRESS'.
(14) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
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### Page 49

(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(15) Make sure that the MCDP shows the message "TEST COMPLETE".
g. In the main equipment center, return the Test Switch S70007 to the "NORMAL" position and
do the steps that follow:
(1) Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and
repeat the test and applicable corrective actions until the test is passed. Refer to 757
AMM 22-00-02 as an accepted procedure.
(2) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(3) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(4) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(5) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(6) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(7) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(8) Make sure the MCDP shows "65 STAB TRIM FCC L FAIL", then push the YES/ADV
switch.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure the MCDP shows "65 STAB TRIM FCC R FAIL", then push the YES/ADV
switch.
(11) Make sure that the MCDP shows the message "65 A/P ENG C TO CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(12) Make sure the MCDP shows "65 STAB TRIM FCC C FAIL", then push the YES/ADV
switch.
(13) End of test for the changed Automatic Stabilizer Trim System.
(14) On the Test Switch S70007, install new lockwire in the guarded position.
h. Remove pressure from the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00
as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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### Page 50

12. Close access door. Refer to 757 AMM 06-41-00 as an accepted procedure.
13. Update the airplane scheduled maintenance program to incorporate functional checks with repeat
intervals not to exceed 1,500 flight hours.
14. Put the airplane back to a serviceable condition.
Group 3:
1. Remove electrical power from the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
2. Open access door 119BL to get access to the Main Equipment Center. Refer to 757 AMM 06-41-00
as an accepted procedure.
3. RC - In the Main Equipment Center, install the Test Switch S70007 and the guard 405-112 to the
Service Panel in accordance with FIGURE 2.
4. RC - In the P36 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1260 in accordance with FIGURE 17 and FIGURE 18.
5. RC - In the P37 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1270 in accordance with FIGURE 19 and FIGURE 20.
6. RC - Between the Test Switch S70007 and E2-1 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4471 in accordance with FIGURE 21 and FIGURE 22.
7. RC - Between the Test Switch S70007 and E2-3 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4475 in accordance with FIGURE 23 and FIGURE 24.
8. RC - Between the Test Switch S70007 and E2-2 and E4-1 shelf assemblies, install wires and make
changes to Wire Bundle W4473 in accordance with FIGURE 25 and FIGURE 26.
9. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P36
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2260
in accordance with FIGURE 39 and FIGURE 42.
10. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P37
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2072
in accordance with FIGURE 43 and FIGURE 44.
11. RC - Do the Automatic Stabilizer Trim System Operational Test to make sure the changed Automatic
Stabilizer Trim System operates correctly:
a. Supply electrical power to the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES
WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER,
FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES.
INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN
HYDRAULIC POWER IS SUPPLIED.
b. Pressurize the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00 as an
accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
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### Page 51

c. Make sure that the control column is in the neutral position and not restrained.
d. If the Maintenance Control Display Panel (MCDP) is available for this test, do the steps that
follow:
(1) At the main power distribution panel, P6, open the P6-5 door.
(2) Behind the P6-5 door, remove the dust cover from the Connector D41101J.
(3) Connect the MCDP remote control unit to the Connector D41101J.
(4) At the P11 panel, make sure the Engine Indication and Crew Alerting System (EICAS)
circuit breakers on the P11 panel are closed.
(5) At the P61 panel, on the EICAS maintenance panel, push the switch CONF/MCDP to
show MCDP data on the EICAS bottom display.
NOTE: The same messages that show on the MCDP in the main equipment center will
show on the EICAS bottom display. The indication "MCDP FLT FAULTS" or
"MCDP GRD TEST" is displayed to identify the MCDP mode.
(6) Make sure EICAS bottom display unit shows the message "MCDP OFF".
e. Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and repeat
the test and applicable corrective actions until the test is passed. Refer to 757 AMM 22-00-02
as an accepted procedure.
f. In the main equipment center, cut and remove the lockwire securing the Test Switch S70007
and hold in the "TEST" position and do the steps that follow:
NOTE: The Test Switch S70007 will need to be held in the "TEST" position during the test.
(1) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(2) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(3) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(4) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(5) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(6) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(7) Make sure that the MCDP shows the message "65 IN PROGRESS".
(8) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
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### Page 52

(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure that the MCDP shows the message "65 IN PROGRESS".
(11) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(12) Make sure that the MCDP shows the message "65 A/P ENG C to CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(13) Make sure that the MCDP shows the message "65 IN PROGRESS'.
(14) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(15) Make sure that the MCDP shows the message "TEST COMPLETE".
g. In the main equipment center, return the Test Switch S70007 to the "NORMAL" position and
do the steps that follow:
(1) Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and
repeat the test and applicable corrective actions until the test is passed. Refer to 757
AMM 22-00-02 as an accepted procedure.
(2) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(3) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
Export Controlled ECCN: 9E991 - BOEING
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### Page 53

(4) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(5) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(6) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(7) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(8) Make sure the MCDP shows "65 STAB TRIM FCC L FAIL", then push the YES/ADV
switch.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure the MCDP shows "65 STAB TRIM FCC R FAIL", then push the YES/ADV
switch.
(11) Make sure that the MCDP shows the message "65 A/P ENG C TO CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(12) Make sure the MCDP shows "65 STAB TRIM FCC C FAIL", then push the YES/ADV
switch.
(13) End of test for the changed Automatic Stabilizer Trim System.
(14) On the Test Switch S70007, install new lockwire in the guarded position.
h. Remove pressure from the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00
as an accepted procedure.
12. Close access door. Refer to 757 AMM 06-41-00 as an accepted procedure.
13. Update the airplane scheduled maintenance program to incorporate functional checks with repeat
intervals not to exceed 1,500 flight hours.
14. Put the airplane back to a serviceable condition.
Group 4:
1. Remove electrical power from the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
2. Open access door 119BL to get access to the Main Equipment Center. Refer to 757 AMM 06-41-00
as an accepted procedure.
3. RC - In the Main Equipment Center, install the Test Switch S70007 and the guard 405-112 to the
Service Panel in accordance with FIGURE 1.
4. RC - In the P36 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1260 in accordance with FIGURE 17 and FIGURE 18.
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: March 23, 2015
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### Page 54

5. RC - In the P37 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1270 in accordance with FIGURE 19 and FIGURE 20.
6. RC - Between the Test Switch S70007 and E2-1 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4471 in accordance with FIGURE 27 and FIGURE 28.
7. RC - Between the Test Switch S70007 and E2-3 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4475 in accordance with FIGURE 29 and FIGURE 30.
8. RC - Between the Test Switch S70007 and E2-2 and E4-1 shelf assemblies, install wires and make
changes to Wire Bundle W4473 in accordance with FIGURE 31 and FIGURE 32.
9. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P36
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2260
in accordance with FIGURE 40 and FIGURE 42.
10. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P37
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2072
in accordance with FIGURE 43 and FIGURE 44.
11. RC - Do the Automatic Stabilizer Trim System Operational Test to make sure the changed Automatic
Stabilizer Trim System operates correctly:
a. Supply electrical power to the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES
WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER,
FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES.
INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN
HYDRAULIC POWER IS SUPPLIED.
b. Pressurize the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00 as an
accepted procedure.
c. Make sure that the control column is in the neutral position and not restrained.
d. If the Maintenance Control Display Panel (MCDP) is available for this test, do the steps that
follow:
(1) At the main power distribution panel, P6, open the P6-5 door.
(2) Behind the P6-5 door, remove the dust cover from the Connector D41101J.
(3) Connect the MCDP remote control unit to the Connector D41101J.
(4) At the P11 panel, make sure the Engine Indication and Crew Alerting System (EICAS)
circuit breakers on the P11 panel are closed.
(5) At the P61 panel, on the EICAS maintenance panel, push the switch CONF/MCDP to
show MCDP data on the EICAS bottom display.
Export Controlled ECCN: 9E991 - BOEING
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### Page 55

NOTE: The same messages that show on the MCDP in the main equipment center will
show on the EICAS bottom display. The indication "MCDP FLT FAULTS" or
"MCDP GRD TEST" is displayed to identify the MCDP mode.
(6) Make sure EICAS bottom display unit shows the message "MCDP OFF".
e. Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and repeat
the test and applicable corrective actions until the test is passed. Refer to 757 AMM 22-00-02
as an accepted procedure.
f. In the main equipment center, cut and remove the lockwire securing the Test Switch S70007
and hold in the "TEST" position and do the steps that follow:
NOTE: The Test Switch S70007 will need to be held in the "TEST" position during the test.
(1) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(2) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(3) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(4) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(5) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(6) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(7) Make sure that the MCDP shows the message "65 IN PROGRESS".
(8) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure that the MCDP shows the message "65 IN PROGRESS".
(11) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
Export Controlled ECCN: 9E991 - BOEING
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### Page 56

(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(12) Make sure that the MCDP shows the message "65 A/P ENG C to CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(13) Make sure that the MCDP shows the message "65 IN PROGRESS'.
(14) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(15) Make sure that the MCDP shows the message "TEST COMPLETE".
g. In the main equipment center, return the Test Switch S70007 to the "NORMAL" position and
do the steps that follow:
(1) Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and
repeat the test and applicable corrective actions until the test is passed. Refer to 757
AMM 22-00-02 as an accepted procedure.
(2) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(3) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(4) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(5) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(6) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(7) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(8) Make sure the MCDP shows "65 STAB TRIM FCC L FAIL", then push the YES/ADV
switch.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
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### Page 57

(10) Make sure the MCDP shows "65 STAB TRIM FCC R FAIL", then push the YES/ADV
switch.
(11) Make sure that the MCDP shows the message "65 A/P ENG C TO CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(12) Make sure the MCDP shows "65 STAB TRIM FCC C FAIL", then push the YES/ADV
switch.
(13) End of test for the changed Automatic Stabilizer Trim System.
(14) On the Test Switch S70007, install new lockwire in the guarded position.
h. Remove pressure from the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00
as an accepted procedure.
12. Close access door. Refer to 757 AMM 06-41-00 as an accepted procedure.
13. Update the airplane scheduled maintenance program to incorporate functional checks with repeat
intervals not to exceed 1,500 flight hours.
14. Put the airplane back to a serviceable condition.
Group 5:
1. Remove electrical power from the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
2. Open access door 119BL to get access to the Main Equipment Center. Refer to 757 AMM 06-41-00
as an accepted procedure.
3. RC - In the Main Equipment Center, install the Test Switch S70007 and the guard 405-112 to the
Service Panel in accordance with FIGURE 1.
4. RC - In the P36 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1260 in accordance with FIGURE 17 and FIGURE 18.
5. RC - In the P37 Miscellaneous Electrical Equipment Panel, install wires and make changes to the
shelf Wire Bundle W1270 in accordance with FIGURE 19 and FIGURE 20.
6. RC - Between the Test Switch S70007 and E2-1 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4471 in accordance with FIGURE 33 and FIGURE 34.
7. RC - Between the Test Switch S70007 and E2-3 and E3-1 shelf assemblies, install wires and make
changes to Wire Bundle W4475 in accordance with FIGURE 35 and FIGURE 36.
8. RC - Between the Test Switch S70007 and E2-2 and E4-1 shelf assemblies, install wires and make
changes to Wire Bundle W4473 in accordance with FIGURE 37 and FIGURE 38.
9. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P36
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2260
in accordance with FIGURE 41 and FIGURE 42.
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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### Page 58

10. RC - In the Right Main Equipment Center, between the Test Switch S70007 and the P37
Miscellaneous Electrical Equipment Panel, install wires and make changes to Wire Bundle W2072
in accordance with FIGURE 43 and FIGURE 44.
11. RC - Do the Automatic Stabilizer Trim System Operational Test to make sure the changed Automatic
Stabilizer Trim System operates correctly:
a. Supply electrical power to the airplane. Refer to 757 AMM 24-22-00 as an accepted procedure.
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES
WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER,
FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES.
INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN
HYDRAULIC POWER IS SUPPLIED.
b. Pressurize the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00 as an
accepted procedure.
c. Make sure that the control column is in the neutral position and not restrained.
d. If the Maintenance Control Display Panel (MCDP) is available for this test, do the steps that
follow:
(1) At the main power distribution panel, P6, open the P6-5 door.
(2) Behind the P6-5 door, remove the dust cover from the Connector D41101J.
(3) Connect the MCDP remote control unit to the Connector D41101J.
(4) At the P11 panel, make sure the Engine Indication and Crew Alerting System (EICAS)
circuit breakers on the P11 panel are closed.
(5) At the P61 panel, on the EICAS maintenance panel, push the switch CONF/MCDP to
show MCDP data on the EICAS bottom display.
NOTE: The same messages that show on the MCDP in the main equipment center will
show on the EICAS bottom display. The indication "MCDP FLT FAULTS" or
"MCDP GRD TEST" is displayed to identify the MCDP mode.
(6) Make sure EICAS bottom display unit shows the message "MCDP OFF".
e. Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and repeat
the test and applicable corrective actions until the test is passed. Refer to 757 AMM 22-00-02
as an accepted procedure.
f. In the main equipment center, cut and remove the lockwire securing the Test Switch S70007
and hold in the "TEST" position and do the steps that follow:
NOTE: The Test Switch S70007 will need to be held in the "TEST" position during the test.
(1) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(2) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
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(3) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(4) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(5) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(6) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(7) Make sure that the MCDP shows the message "65 IN PROGRESS".
(8) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure that the MCDP shows the message "65 IN PROGRESS".
(11) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(12) Make sure that the MCDP shows the message "65 A/P ENG C to CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(13) Make sure that the MCDP shows the message "65 IN PROGRESS'.
(14) Make sure that this sequence of stabilizer indicator and stabilizer movement occurs:
(a) The stabilizer indicator is in the TO CG position.
(b) The indicator and the stabilizer surface move in a nose down (trailing edge down)
direction.
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### Page 60

(c) The indicator and the stabilizer surface move in a nose up (trailing edge up) direction.
(d) The stabilizer indicator moves back into the TO CG position.
(15) Make sure that the MCDP shows the message "TEST COMPLETE".
g. In the main equipment center, return the Test Switch S70007 to the "NORMAL" position and
do the steps that follow:
(1) Do MCDP Power-Up and Self Test. If the test fails, accomplish corrective actions and
repeat the test and applicable corrective actions until the test is passed. Refer to 757
AMM 22-00-02 as an accepted procedure.
(2) Make sure the MCDP shows the message "LAST FLT FAULTS?".
(3) Push the GRD TEST switch and make sure that the GRD TEST mode is engaged.
(4) Use the GRD TEST SEL UP and DOWN switches or the NO/SKIP switch for test selection.
Make sure the display indicates "65- STAB TRIM".
(5) To arm the test, push the YES/ADV switch and make sure that the MCDP shows the
message "65 IN PROGRESS".
(6) Make sure that the MCDP shows the message "65 VFY HYD ON - ADV", then push the
YES/ADV switch.
(7) Make sure that the MCDP shows the message "65 A/P ENG L TO CMD", then push the
L CMD button on the mode control panel on the P55 panel.
(8) Make sure the MCDP shows "65 STAB TRIM FCC L FAIL", then push the YES/ADV
switch.
(9) Make sure that the MCDP shows the message "65 A/P ENG R TO CMD", then push the
R CMD button on the mode control panel on the P55 panel.
(10) Make sure the MCDP shows "65 STAB TRIM FCC R FAIL", then push the YES/ADV
switch.
(11) Make sure that the MCDP shows the message "65 A/P ENG C TO CMD", then push the
C CMD button on the mode control panel on the P55 panel.
(12) Make sure the MCDP shows "65 STAB TRIM FCC C FAIL", then push the YES/ADV
switch.
(13) End of test for the changed Automatic Stabilizer Trim System.
(14) On the Test Switch S70007, install new lockwire in the guarded position.
h. Remove pressure from the left, right, and center hydraulic systems. Refer to 757 AMM 29-11-00
as an accepted procedure.
12. Close access door. Refer to 757 AMM 06-41-00 as an accepted procedure.
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