# Boeing Alert Requirements Bulletin 757-27A0160 RB: No revision named

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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-27A0160 RB
Original Issue: April 01, 2024
ATA System: 2711
SUBJECT: FLIGHT CONTROLS - Aileron and Aileron Trim Control System - Lateral Control Box
Support Assembly Change and Actuator Lateral Control Fitting Replacement
EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations
(EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for
export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per
Supp.1 to Part 740 of the EAR.
9E991ECCN:
Copyright © 2024 The Boeing Company
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: April 01, 2024
757-27A0160 RB
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REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT
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Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
FIGURE 1: MAIN LANDING GEAR WHEEL WELL - LATERAL CONTROL BOX SUPPORT ASSEMBLY
CHANGE [Group 1, 4-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BRACKET INSTALLATION
[Group 1, 4-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
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REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

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REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT
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Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-27A0160 RB
Original Issue: April 01, 2024
ATA System: 2711
SUBJECT: FLIGHT CONTROLS - Aileron and Aileron Trim Control System - Lateral Control Box
Support Assembly Change and Actuator Lateral Control Fitting Replacement
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN
(RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL
TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB
WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. Effectivity
A. Airplanes
This bulletin is applicable to 757-200, 757-200CB, 757-200PF, 757-300 Airplane(s), line number(s)
1-2, 5, 14-15, 42, 46, 56, 74-75, 80, 97, 101-102, 106, 111-115, 117, 123, 127, 130, 132, 139,
141, 143, 145, 147-151, 153, 155, 162-163, 165-167, 169, 173-174, 176, 178, 180-184, 186-187,
189, 191, 193, 195, 197, 199-200, 203-204, 208-209, 211-215, 218-221, 224-232, 235-236,
238-239, 246, 248-250, 255-257, 259, 264-265, 267-268, 270-271, 273-275, 279, 281, 285,
287-288, 291-294, 298, 300-302, 306, 312, 314, 317-319, 322-323, 325-326, 330, 332-335,
339-345, 347-350, 353-355, 359-364, 369-372, 374, 376-379, 382-389, 392-395, 397-400, 402-404,
407, 409-412, 414-418, 421-422, 424-425, 429-430, 432-433, 435-443, 445-446, 448-449, 453,
455, 458-459, 461, 465-466, 470-478, 480-482, 485-486, 489, 493, 495-503, 506, 508, 510-516,
518-519, 521, 523, 525-528, 530-546, 548-549, 551-556, 558-559, 561-571, 573-575, 577-586,
588-590, 592-597, 599, 601-605, 607-619, 622-625, 627-683, 685-707, 709-717, 719, 721, 723-780,
782-800, 802-834, 836-875, 877-888, 890-894, 896-1050 in 5 Group(s). Where the effectivity is
presented with hyphens between line numbers, the airplane applicability means "through" and
"inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive.
The Variable Numbers and Group Information for the applicable airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
757-200 airplanes with Support Box Assembly - Lateral Control Part
Number 251N1264-7 installed.
-1
757-200 airplanes with Support Box Assembly - Lateral Control Part
Number 251N1135-6 installed.
-2
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DESCRIPTIONCONFIGURATIONGROUP
757-200 airplanes with Support Box Assembly - Lateral Control Part
Number 251N1135-1 installed.
-3
757-200, 757-200CB and 757-200PF airplanes with Support Box
Assembly - Lateral Control Part Number 251N1264-8 installed.
-4
757-200, 757-200PF and 757-300 airplanes with Support Box
Assembly - Lateral Control Part Number 251N1264-9 installed.
-5
Airplane Models:
757-200, 757-200CB, 757-200PF, 757-300
GroupVariable Number
3NA001
2NA002
2NA005
1NA021 - NA023
4NA024 - NA028
4NA195
4NA197 - NA199
2NA205
4NA227 - NA228
4NA230
4NA235 - NA239
4NA301 - NA305
4NA343 - NA344
4NA346 - NA352
4NA392 - NA399
2NA401
1NA404
4NA406
4NA441 - NA447
1NA505
1NA519 - NA521
4NA522
GroupVariable Number
4NA549 - NA552
4NA554 - NA555
4NA558 - NA576
4NA578 - NA586
1NB023
1NB037
4NB041
1NB053
4NB062 - NB066
4NB070 - NB073
4NB079
4NB131 - NB148
4NB161 - NB162
4NB167 - NB168
4NB201 - NB202
4NB221 - NB226
5NB227 - NB228
5NB230
4NB236
4NB239
4NB261 - NB267
4NB291 - NB299
GroupVariable Number
4NB301 - NB302
4NB311 - NB312
4NB321 - NB330
4NB421
4NB424
4NB428 - NB431
4NB434 - NB435
4NB437 - NB438
4NB446
4NB451 - NB454
4NB501 - NB523
5NB571
5NB581 - NB583
1NC042
4NC051 - NC052
4NC056 - NC062
4NC066 - NC078
5NC079 - NC084
4NC091
5NC092 - NC094
4NC151
4NC161
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GroupVariable Number
4NC901 - NC951
4NC973 - NC974
4ND004
4ND012
4ND017
4ND032
4ND039 - ND041
4ND044
4ND046
4ND048
4ND052 - ND053
4ND111
4ND161
4ND163 - ND166
4ND169 - ND176
4ND178 - ND188
4ND190 - ND199
4ND201 - ND202
4ND221 - ND225
4ND241 - ND242
4ND244 - ND247
4ND301 - ND317
5ND318 - ND322
5ND401
4ND895
4NE001 - NE003
4NE008
4NE012
4NE017
4NE021 - NE022
4NE025
4NE029
4NE031
GroupVariable Number
4NE036 - NE037
4NE040 - NE041
4NE044
4NE048 - NE051
4NE054 - NE055
4NE067 - NE075
4NE077 - NE081
4NE083 - NE088
4NE092 - NE094
4NE145
4NE147
4NE161 - NE164
4NE166
4NE168
4NE170 - NE172
4NE174 - NE176
4NE201
4NE204
4NE301
4NE311 - NE325
5NJ001 - NJ004
5NJ031 - NJ032
5NJ551 - NJ555
5NL001 - NL002
5NL006 - NL017
5NL101 - NL109
5NL141
5NL601 - NL616
5NN001 - NN002
5NN051 - NN052
5NP901 - NP904
4NS601 - NS610
5NS611 - NS616
GroupVariable Number
5NT001 - NT009
5NT201 - NT202
5NT231 - NT234
5NT237 - NT240
5NT242
5NT245 - NT248
5NT281 - NT284
5NT286 - NT289
5NT341 - NT343
5NT345 - NT347
5NT351 - NT360
5NT371 - NT373
5NT375 - NT379
5NT381 - NT386
5NT401 - NT409
5NT411 - NT412
5NT426 - NT427
5NT431 - NT432
5NT436 - NT438
5NT441 - NT442
5NT446
5NT701 - NT750
5NT752 - NT769
5NT791 - NT796
5NT861 - NT862
5NT881
5NT884 - NT885
5NT901 - NT903
5NT905 - NT916
5NT971 - NT985
5NU031 - NU038
5NU701 - NU705
5NU721 - NU728
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GroupVariable Number
5NU731 - NU732
GroupVariable Number
--
GroupVariable Number
--
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2019-12-13 is related to this service
bulletin. The effective date of AD 2019-12-13 is July 12, 2019.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 757-27A0160 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-27A0160 RB mandatory.
Group 1, 4-5:
Accomplish the required action(s), based on the applicable condition(s) in Table 1, in accordance with
Accomplishment Instructions.
Group 2-3:
Accomplish the required action(s), based on the applicable condition(s) in Table 2, in accordance with
Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that
CONDITION or OPTION.
Group 1, 4-5:
Table 1: Lateral Control Box Support Assembly Change and Aileron Trim Actuator Bracket Installation
Repeat Interval (Not
to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs First)
ActionCondition
-Within 10,000 Flight Hours
(FH) after the Original Is-
sue date of the Require-
ments Bulletin 757-
27A0160 RB.
ACTION 1:
Change the lateral control box
support assembly. (a)
All Airplanes.
ACTION 2:
Install aileron trim actuator
bracket. (a) orWithin 30 Months after the
Original Issue date of the
Requirements Bulletin 757-
27A0160 RB.
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Group 1, 4-5:
Table 1: Lateral Control Box Support Assembly Change and Aileron Trim Actuator Bracket Installation
Repeat Interval (Not
to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs First)
ActionCondition
(a) Accomplishment of ACTION 1 and ACTION 2 terminates the repetitive Aileron Trim Actuator attachment
lug detailed inspection and the Aileron Trim Actuator bearing rotation check specified in Boeing Alert
Requirements Bulletin 757-27A0159 RB.
Group 2-3:
Table 2: Actuator Lateral Control Fitting Replacement
Repeat Interval (Not
to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs First)
ActionCondition
-Within 10,000 Flight Hours
(FH) after the Original Is-
sue date of the Require-
ments Bulletin 757-
27A0160 RB.
Replace existing actuator later-
al control fitting with an aileron
trim actuator bracket. (a)
All Airplanes.
or
Within 30 Months after the
Original Issue date of the
Requirements Bulletin 757-
27A0160 RB
(a) Accomplishment of this action terminates the repetitive Aileron Trim Actuator attachment lug detailed in-
spection and the Aileron Trim Actuator bearing rotation check specified in Boeing Alert Requirements
Bulletin 757-27A0159 RB.
4. APPROVAL
This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this document comply with the applicable regulations and are FAA approved, as well as European
Union Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in this Requirements Bulletin effectivity. This document and its approval were based on the
airplane in its original Boeing delivery configuration or as modified by other Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by
this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this Requirements Bulletin.
In addition, the Manager of the FAA Continued Operational Safety Branch approves accomplishment of
the change defined in this bulletin as an alternative method of compliance to accomplishing the requirements
of paragraph (g) of AD 2019-12-13. All provisions of AD 2019-12-13 that are not specifically referenced in
the above statement remain fully applicable and must be complied with accordingly.
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5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. This is an Enhanced Required for Compliance document. There will be a separate
Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated
by an Airworthiness Directive (AD), then all applicable requirements specified in the
RB must be done. In the RB, the "Refer to the listed procedures..." column of the
table(s) in the Work Instructions is for reference only. The procedures in that column
are not required by the AD and are for guidance only. For the related SB, some
locations are marked RC Start and RC End to identify the requirements that are
restated from the RB. For the related SB, the areas between RC Start and RC End,
including sub-steps and any figures identified between RC Start and RC End, must
be done to comply with the AD. Therefore, an Alternative Method of Compliance
(AMOC) is required for any deviations to steps between RC Start and RC End,
including substeps and identified figures. For the related SB, the steps not between
RC Start and RC End may be deviated from using accepted methods in accordance
with the operator's maintenance or inspection program without obtaining approval
of an AMOC; this is provided that the steps between RC Start and RC End, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition. Figures not required for compliance are omitted
from the RB.
2. This is an Enhanced Required for Compliance document. The Boeing processes
used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure
that the information between "RC Start" and "RC End" in the SB are identical to the
information in the same sections (Compliance, Work Instructions...) of the RB which
the SB refers to as the related document.
3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
4. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
5. 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).
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— 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.
6. 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.
7. 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.
8. 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.
9. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
10. 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.
B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements:
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Group 1, 4-5:
Table 1: Lateral Control Box Support Assembly Change and Aileron Trim Actuator Bracket Installation
Refer to the listed
procedure in SB 757-
27A0160 Original Is-
sue or later approved
revisions as an ac-
cepted procedure
Method of Compli-
ance
ActionCondition
Do PART 1:-ACTION 1:All Airplanes.
PREPARATION.Change the lateral control box
support assembly. (a) -FIGURE 1
-FIGURE 2ACTION 2:
Install aileron trim actuator
bracket. (a)
Do PART 2:-
FEEL AND TRIM
MECHANISM ASSEM-
BLY AND AILERON
TRIM ACTUATOR IN-
STALLATION.
Do PART 3:-
RESTORATION.
Do PART 4:-
FUNCTIONAL TEST.
Do PART 5:-
CLOSE UP.
(a) Accomplishment of ACTION 1 and ACTION 2 terminates the repetitive Aileron Trim Actuator attachment
lug detailed inspection and the Aileron Trim Actuator bearing rotation check specified in Boeing Alert
Requirements Bulletin 757-27A0159 RB.
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Group 2-3:
Table 2: Actuator Lateral Control Fitting Replacement
Refer to the listed
procedures in SB 757-
27A0160 Original Is-
sue or later approved
revisions as an ac-
cepted procedure.
Method of Compli-
ance
ActionCondition
Do PART 1:-Replace existing actuator later-
al control fitting with an aileron
trim actuator bracket. (a)
All Airplanes.
PREPARATION.
-Group 2:
FIGURE 3
Group 3:
FIGURE 4
Do PART 2:-
FEEL AND TRIM
MECHANISM ASSEM-
BLY AND AILERON
TRIM ACTUATOR IN-
STALLATION.
Do PART 3:-
RESTORATION.
Do PART 4:-
FUNCTIONAL TEST.
Do PART 5:-
CLOSE UP.
(a) Accomplishment of this action terminates the repetitive Aileron Trim Actuator attachment lug detailed
inspection and the Aileron Trim Actuator bearing rotation check specified in Boeing Alert Requirements
Bulletin 757-27A0159 RB.
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REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
This Figure applies only to: Group 1, 4-5.
STA
1040
100
LBL  000
15.82
LBL
21.08
3032750
FIGURE 1: MAIN LANDING GEAR WHEEL WELL - LATERAL CONTROL BOX SUPPORT ASSEMBLY
CHANGE
(SHEET 1 OF 2)
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### Page 16

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
USE PROTECTION TO MAKE SURE ADJACENT STRUCTURE IS NOT DAMAGED.
CAUTION
(a)-251N1258-4BOX SUPPORT AS-
SEMBLY
Cut1
USE PROTECTION TO MAKE SURE ADJACENT STRUCTURE IS NOT DAMAGED.
CAUTION
(b)(c)-251N1258-4BOX SUPPORT AS-
SEMBLY
Machine2
(a) Cut the aileron trim actuator attachment lug from the box support assembly.
(b) Machine the cut surface of the trim actuator attachment lug to flush to 0.03 inch maximum with the box
support assembly. The machined surface must be 125 Microinches RA roughness or better.
(c) Do a Portable Method C Penetrant inspection of the machined surface of the lug for any crack. Refer to
SOPM 20-20-02 as an accepted procedure. If any crack is found, contact The Boeing Company for repair
instructions and do the repair.
FIGURE 1: MAIN LANDING GEAR WHEEL WELL - LATERAL CONTROL BOX SUPPORT ASSEMBLY
CHANGE
(SHEET 2 OF 2)
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ALERTALERT

### Page 17 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
This Figure applies only to: Group 1, 4-5.
10 0
AND
LBL
15.82
LBL
21.08
3034930
FIGURE 2: MAIN LANDING GEAR WHEEL WELL- AILERONTRIM ACTUATOR BRACKETINSTALLATION
(SHEET 1 OF 6)
Original Issue: April 01, 2024
Export Controlled ECCN: 9E991  757-27A0160 RB
See page 1 for details  17 of 33

### Page 18 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
LBL
15.82
LBL
21.08
BEFORE
(VIEW LOOKING FORWARD)
A-A
BEFORE  INBD
(VIEW LOOKING DOWN)  B-B  3034931
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BRACKET INSTALLATION
(SHEET 2 OF 6)
Original Issue: April 01, 2024
757-27A0160 RB
Export Controlled ECCN: 9E991
See page 1 for details  18 of 33

### Page 19

FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BRACKET INSTALLATION
(SHEET 3 OF 6)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
19 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 20 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
LBL
15.82
(8 BOLT COLLAR  (4 LOCATIONS)
LBL
21.08
AFTER  INBD
(VIEW LOOKING FORWARD)
C-C
2.33
2.30
VIEW LOOKING DOWN  INBD  3033057
D-D
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BRACKET INSTALLATION
(SHEET 4 OF 6)
Original Issue: April 01, 2024
757-27A0160 RB
Export Controlled ECCN: 9E991
See page 1 for details  20 of 33

### Page 21

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)-TYPE II, CLASS A
(TYPE II, CLASS C op-
tional)
CHEMICAL CONVER-
SION COATING
Apply1
(b)-BMS 10-11, TYPE IPRIMERApply2
(c)-BMS 10-11, TYPE IIENAMELApply3
(d)-251N1020-1PART NUMBERApply4
(e)4-RIVETRemove5
(f)1251N1138-1BRACKET - AILERON
TRIM ACTUATOR
Put / Hold6
(g)4-HOLEDrill / Ream7
(a)(b)4-HOLEDeburr
-1251N1138-1BRACKET - AILERON
TRIM ACTUATOR
Install (New)8
(h)(i)4BACB30NX6K5BOLTInstall (New)
(h)4BACC30BH6COLLARInstall (New)
(j)--PART MARKApply9
(a) Apply chemical conversion coating where the surface finish was removed. Refer to SOPM 20-43-03 as
an accepted procedure.
(b) Apply one coat of primer where chemical conversion coating was applied. Refer to SOPM 20-41-02 as
an accepted procedure.
(c) Apply one coat of enamel top coat, color BAC 702 (White Gloss) where primer was applied. Refer to
SOPM 20-41-02 as an accepted procedure.
(d) Refer to SOPM 20-50-10 Code RH as an accepted procedure.
(e) Refer to 757-200 SRM 51-40-02, or 757-200CB SRM 51-40-02, or 757-200PF SRM 51-40-02, or 757-
300 SRM 51-40-02 as an accepted procedure.
(f) Use the pilot hole, existing fastener hole and dimension to locate the bracket - aileron trim actuator in the
location shown.
(g) Match drill 4 hole locations from the support box assembly to the bracket - aileron trim actuator. Refer to
757-200 SRM 51-40-05, 757-200CB SRM 51-40-05, 757-200PF SRM 51-40-05 or 757-300 SRM 51-40-
05 with transition fit for drill hole size as an accepted procedure. Make sure a 1D minimum edge margin
is kept.
(h) For bolt hole location(s) that is common to the support box assembly and the bracket - aileron trim actuator
and is unable to oversize BACB30NX6K5 (BACB30NX6K5X and BACB30NX6K5Y) for clean-up, use
fastener part number BACB30NX8K5 and collar part number BACC30BH8 as optional.
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BRACKET INSTALLATION
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
21 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 22

More DataQtyIdentificationNameTaskStep
(i) Install fasteners wet with sealant BMS 5-95. Fasteners orientation is optional for access. Refer to 757-
200 SRM 51-40-02, or 757-200CB SRM 51-40-02, or 757-200PF SRM 51-40-02, or 757-300 SRM 51-
40-02 as an accepted procedure.
(j) Part mark as 251N1264-10, if existing part number was 251N1264-7 refer to SOPM 20-50-10 Code RH
as an accepted procedure.
Part mark as 251N1264-11, if existing part number was 251N1264-8 refer to SOPM 20-50-10 Code RH
as an accepted procedure.
Part mark as 251N1264-12, if existing part number was 251N1264-9 refer to SOPM 20-50-10 Code RH
as an accepted procedure.
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BRACKET INSTALLATION
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
22 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 23 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
This Figure applies only to: Group 2.
BEFORE
AFTER
LBL
21.08  15.82
BEFORE
3033037
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 1 OF 5)
Original Issue: April 01, 2024
Export Controlled ECCN: 9E991  757-27A0160 RB
See page 1 for details  23 of 33

### Page 24 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
LBL
15.82
B
INBD
BEFORE
(VIEW LOOKING FORWARD)
A-A
BEFORE
(VIEW LOOKING DOWN)  INBD  3033045
B-B
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 2 OF 5)
Original Issue: April 01, 2024
Export Controlled ECCN: 9E991  757-27A0160 RB
See page 1 for details  24 of 33

### Page 25

FIGURE 3: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 3 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
25 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 26 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
LBL
15.82
COLLAR
COLLAR
COLLAR  INBD
AFTER
(VIEW LOOKING FORWARD)
C-C
2.43
2.41
INBD
AFTER
(VIEW LOOKING DOWN)  D-D  3033040
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 4 OF 5)
Original Issue: April 01, 2024
757-27A0160 RB
Export Controlled ECCN: 9E991
See page 1 for details  26 of 33

### Page 27

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)3-FASTENERRemove1
-1-FITTINGRemove2
(b)1251N1138-2BRACKET - AILERON
TRIM ACTUATOR
Put / Hold3
(c)3-HOLEDrill / Ream4
-3-HOLEDeburr
(d)-TYPE II, CLASS A
(TYPE II, CLASS C op-
tional)
CHEMICAL CONVER-
SION COATING
Apply
(e)-BMS 10-11, TYPE IPRIMERApply
-1251N1138-2BRACKET - AILERON
TRIM ACTUATOR
Install (New)5
(f)1BACB30NX8K41HI-LOKInstall (New)6
-1BACC30BH8COLLARInstall (New)
(f)1BACB30NX8K7BOLT, HEX DRIVEInstall (New)7
-1BACC30BH8COLLARInstall (New)
(f)1BACB30VT8K5BOLTInstall (New)8
-1BACC30BL8COLLARInstall (New)
(g)-251N1135-9PART NUMBERApply9
(a) Refer to 757-200 SRM 51-40-02 as an accepted procedure.
(b) Use the pilot hole and existing fastener holes to locate the bracket - aileron trim actuator in the position
shown.
(c) Match drill 3 hole locations from the support box assembly to the bracket - aileron trim actuator. Refer to
757-200 SRM 51-40-05 with transition fit for drill hole size as an accepted procedure. Make sure a 1D
minimum edge margin is kept.
(d) Apply chemical conversion coating where the surface finish was removed. Refer to SOPM 20-43-03 as
an accepted procedure.
(e) Apply one coat of primer where chemical conversion coating was applied. Refer to SOPM 20-41-02 as
an accepted procedure.
(f) Install fastener wet with sealant BMS 5-95. Refer to 757-200 SRM 51-40-02 as an accepted procedure.
(g) Refer to SOPM 20-50-10 Code RH as an accepted procedure.
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
27 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 28 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
This Figure applies only to: Group 3.
STA
1040
BEFORE
AFTER
LBL
15.82
LBL
21.08
BEFORE
600008
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 1 OF 6)
Original Issue: April 01, 2024
Export Controlled ECCN: 9E991  757-27A0160 RB
See page 1 for details  28 of 33

### Page 29 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
LBL
15.82
B
INBD
BEFORE
(VIEW LOOKING FORWARD)
A-A
BEFORE
(VIEW LOOKING DOWN)  B-B  3033058
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 2 OF 6)
Original Issue: April 01, 2024
Export Controlled ECCN: 9E991  757-27A0160 RB
See page 1 for details  29 of 33

### Page 30

FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 3 OF 6)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
30 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 31 (OCR)

REQUIREMENTS BULLETIN 757-27A0160
ALERT  ALERT
LBL
15.82
COLLAR
COLLAR
COLLAR
INBD
AFTER
(VIEW LOOKING FORWARD)
C-C
2.43
2.41
NBD
AFTER
(VIEW LOOKING DOWN)  D-D  3033044
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 4 OF 6)
Original Issue: April 01, 2024
Export Controlled ECCN: 9E991  757-27A0160 RB
See page 1 for details  31 of 33

### Page 32

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)2-FASTENERRemove1
-1-FITTINGRemove2
(a)1-FASTENERRemove3
(b)1251N1138-3BRACKET - AILERON
TRIM ACTUATOR
Put / Hold4
(c)3-HOLEDrill / Ream5
-3-HOLEDeburr
(d)-TYPE II, CLASS A
(TYPE II, CLASS C op-
tional)
CHEMICAL CONVER-
SION COATING
Apply
(e)-BMS 10-11, TYPE IPRIMERApply
(f)1251N1138-3BRACKET - AILERON
TRIM ACTUATOR
Install (New)6
(g)1BACB30NX8K41HI-LOKInstall (New)7
-1BACC30BH8COLLARInstall (New)
(g)1BACB30NX8K7BOLT, HEX DRIVEInstall (New)8
-1BACC30BH8COLLARInstall (New)
(g)1BACB30VT8K5BOLTInstall (New)9
-1BACC30BL8COLLARInstall (New)
(h)-251N1135-8PART NUMBERApply10
(a) Refer to 757-200 SRM 51-40-02 as an accepted procedure.
(b) Use the pilot hole and existing fastener holes to locate the bracket - aileron trim actuator in the position
shown.
(c) Match drill 3 hole locations from the support box assembly to the bracket - aileron trim actuator. Refer to
757-200 SRM 51-40-05 with transition fit for drill hole size as an accepted procedure. Make sure a 1D
minimum edge margin is kept.
(d) Apply chemical conversion coating where the surface finish was removed. Refer to SOPM 20-43-03 as
an accepted procedure.
(e) Apply one coat of primer where chemical conversion coating was applied. Refer to SOPM 20-41-02 as
an accepted procedure.
(f) Install bracket - aileron trim actuator in the location shown by aligning the fastener holes on the fitting with
existing fastener holes.
(g) Install fastener wet with sealant BMS 5-95. Refer to 757-200 SRM 51-40-02 as an accepted procedure.
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
32 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

### Page 33

More DataQtyIdentificationNameTaskStep
(h) Refer to SOPM 20-50-10 Code RH as an accepted procedure.
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - ACTUATOR LATERAL CONTROL FITTING
REPLACEMENT
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: April 01, 2024
757-27A0160 RB
33 of 33
REQUIREMENTS BULLETIN 757-27A0160
ALERTALERT

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