# Boeing Alert Service Bulletin 757-27A0159: 757-27A0159-00--RB

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2019-0445, the docket of AD 2019-12-13. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 757-27A0159](https://openairdocs.org/service-documents/boeing/757-27a0159.md)
- Title as filed: 757-27A0159-00--RB
- Pages: 19
- PDF: https://openairdocs.org/files/sha256/ce/f6/cef66b7cc5ae3625d745fe42c8ea430620fd31c697ea58767e5594a9c899b1b0
- Page: https://openairdocs.org/service-documents/boeing/757-27a0159/file/cef66b7cc5ae

## Text

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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-27A0159 RB
Original Issue: March 29, 2019
ATA System: 2711
SUBJECT: FLIGHT CONTROLS - Aileron and Aileron Trim Control System - Aileron Trim Actuator
Bearing Rotation Check and Attachment Lug Inspections
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:
Copyright © 2019 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Unpublished Work.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 29, 2019
757-27A0159 RB
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3.0

### Page 2

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REQUIREMENTS BULLETIN 757-27A0159
ALERTALERT
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### Page 3

Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BEARING - ROTATION
CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR ATTACHMENT LUG -
DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR ATTACHMENT LUG -
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . . . . . . . . . . . . . . . 18
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REQUIREMENTS BULLETIN 757-27A0159
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Export Controlled ECCN: 9E991
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REQUIREMENTS BULLETIN 757-27A0159
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-27A0159 RB
Original Issue: March 29, 2019
ATA System: 2711
SUBJECT: FLIGHT CONTROLS - Aileron and Aileron Trim Control System - Aileron Trim Actuator
Bearing Rotation Check and Attachment Lug Inspections
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)
1-1050 in 1 Group(s).
B. Spares Affected
Examine your spares supply for the parts or components identified below. If any parts or components
are found, refer to the Accomplishment Instructions for the recommended action.
NamePart Number
AILERON TRIM ACTUATOR60B80030-3 OR -4 (SHIMADZU PART
NUMBER 732-16810-01 OR -03)
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related
to Requirements Bulletin 757-27A0159 RB. The Airworthiness Directive will make the compliance tasks
and times given in Requirements Bulletin 757-27A0159 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 and 2 in accordance with
the Accomplishment Instructions.
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### Page 6

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.
Table 1: Aileron Trim Actuator Bearing Rotation Check
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 1,760 Flight
Hours after the
original issue date
of the Require-
ments Bulletin 757-
27A0159 RB.
Do an Aileron Trim Actua-
tor bearing rotation check
to make sure it turns
freely. (a)
All Airplanes
-Before further
flight.
Do a HFEC inspection of
the Aileron Trim Actuator
attachment lug for any
crack. (c)
CONDITION 1: BEARING
DOES NOT TURN
FREELY.
-Before further
flight.
CONDITION 1.1 (AC-
TION 1): Contact the
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 1.1: ANY
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG -Before further
flight.
CONDITION 1.1 (AC-
TION 2): Replace the
Aileron Trim Actuator with
a new or serviceable part.
(b)
1,100 Flight Hours.-CONDITION 1.1 (AC-
TION 3): Repeat Aileron
Trim Actuator bearing ro-
tation check to make sure
it turns freely. (a)
-.Before further
flight.
CONDITION 1.2 (AC-
TION 1): Replace the
Aileron Trim Actuator with
a new or serviceable part.
(b)
CONDITION 1.2: NO
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG 1,100 Flight Hours.-CONDITION 1.2 (AC-
TION 2): Repeat Aileron
Trim Actuator bearing ro-
tation check to make sure
it turns freely. (a)
1,100 Flight Hours.-Repeat Aileron Trim Actu-
ator bearing rotation
check to make sure it
turns freely. (a)
CONDITION 2: BEARING
TURNS FREELY.
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### Page 7

Table 1: Aileron Trim Actuator Bearing Rotation Check
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(a) A bearing that turns freely is defined as: A bearing that moves without ratchet, gritty, or
detent like feeling.
(b) The existing Aileron Trim Actuator can be replaced with a new or serviceable Aileron Trim
Actuator. A serviceable Aileron Trim Actuator is one with a bearing that turns freely.
(c) If a HFEC inspection of the Aileron Trim Actuator attachment lug for any crack is found to
be required as an action for both CONDITION 1 and CONDITION 3, the HFEC inspection
is only required to be done once before further flight.
Table 2: Detailed Inspection of the Aileron Trim Actuator Attachment Lug
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 1,760 Flight
Hours after the
original issue date
of the Require-
ments Bulletin 757-
27A0159 RB.
Do a Detailed Inspection
of the Aileron Trim Actua-
tor attachment lug for any
damage and any crack.
(a)
All Airplanes
-Before further
flight.
Do a HFEC inspection of
the Aileron Trim Actuator
attachment lug for any
crack. (b)
CONDITION 3: ANY DAM-
AGE OR ANY CRACK IS
FOUND DURING THE
DETAILED INSPECTION
OF THE AILERON TRIM
ACTUATOR ATTACH-
MENT LUG
-Before further
flight.
CONDITION 3.1 (AC-
TION 1): Contact the
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3.1: ANY
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG 1,100 Flight Hours.-CONDITION 3.1 (AC-
TION 2): Repeat Detailed
Inspection of the Aileron
Trim Actuator attachment
lug for any damage and
any crack. (a)
1,100 Flight Hours.-Repeat Detailed Inspec-
tion of the Aileron Trim
Actuator attachment lug
for any damage and any
crack. (a)
CONDITION 3.2: NO
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG
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### Page 8

Table 2: Detailed Inspection of the Aileron Trim Actuator Attachment Lug
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,100 Flight Hours.-Repeat Detailed Inspec-
tion of the Aileron Trim
Actuator attachment lug
for any damage and any
crack. (a)
CONDITION 4: NO DAM-
AGE AND NO CRACK IS
FOUND DURING THE
DETAILED INSPECTION
OF THE AILERON TRIM
ACTUATOR ATTACH-
MENT LUG
(a) Damage is defined as: Any surface problems, such as scratches or dings, which have
occurred after the part was manufactured.
(b) If a HFEC inspection of the Aileron Trim Actuator attachment lug for any crack is found to
be required as an action for both CONDITION 1 and CONDITION 3, the HFEC inspection
is only required to be done once before further flight.
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 for the airplanes
listed in the service bulletin effectivity. This document 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 Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this Requirements Bulletin.
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### Page 9

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. 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. 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.
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### Page 10

5. 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.
6. 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.
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. The instructions in the Work Instructions and the figures can include operation of
tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and
Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain
data on versions of the tools or test equipment that you can use. It is permitted to
use replaced tools. It is not permitted to use superseded tools.
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. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation or assembly to detect damage, failure or irregularity. This could include
tactile assessment in which a component or assembly can be checked for
tightness/security. Available lighting is normally supplemented with a direct source
of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors
and magnifying lenses may be necessary. Surface cleaning and elaborate access
procedures may be required.
11. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
12. 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.
B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements
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### Page 11

Table 1: Aileron Trim Actuator Bearing Rotation Check
Refer to the listed
procedures in SB
757-27A0159
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure.
Method of Compli-
ance
ActionCondition
Do PART 1:
PREPARATION
-Do an Aileron Trim Actua-
tor bearing rotation check
to make sure it turns
freely. (a)
All Airplanes
-FIGURE 2
-FIGURE 4Do a HFEC inspection of
the Aileron Trim Actuator
attachment lug for any
crack. (c)
CONDITION 1: BEARING
DOES NOT TURN
FREELY
--CONDITION 1.1 (AC-
TION 1): Contact the
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 1.1: ANY
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG Do PART 2:
AILERON TRIM
ACTUATOR RE-
PLACEMENT
-CONDITION 1.1 (AC-
TION 2): Replace the
Aileron Trim Actuator with
a new or serviceable part.
(b)
Do PART 3:
RESTORATION
--
-FIGURE 2CONDITION 1.1 (AC-
TION 3): Repeat Aileron
Trim Actuator bearing ro-
tation check to make sure
it turns freely. (a)
Do PART 2:
AILERON TRIM
ACTUATOR RE-
PLACEMENT
-CONDITION 1.2 (AC-
TION 1): Replace the
Aileron Trim Actuator with
a new or serviceable part.
(b)
CONDITION 1.2: NO
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG Do PART 3:
RESTORATION
--
-FIGURE 2CONDITION 1.2 (AC-
TION 2): Repeat Aileron
Trim Actuator bearing ro-
tation check to make sure
it turns freely. (a)
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### Page 12

Table 1: Aileron Trim Actuator Bearing Rotation Check
Refer to the listed
procedures in SB
757-27A0159
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure.
Method of Compli-
ance
ActionCondition
Do PART 3:
RESTORATION
--CONDITION 2: BEARING
TURNS FREELY
-FIGURE 2Repeat Aileron Trim Actu-
ator bearing rotation
check to make sure it
turns freely. (a)
(a) A bearing that turns freely is defined as: A bearing that moves without ratchet, gritty, or
detent like feeling.
(b) The existing Aileron Trim Actuator can be replaced with a new or serviceable Aileron Trim
Actuator. A serviceable Aileron Trim Actuator is one with a bearing that turns freely.
(c) If a HFEC inspection of the Aileron Trim Actuator attachment lug for any crack is found to
be required as an action for both CONDITION 1 and CONDITION 3, the HFEC inspection
is only required to be done once before further flight.
Table 2: Detailed Inspection of the Aileron Trim Actuator Attachment Lug
Refer to the listed
procedures in SB
757-27A0159
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure.
Method of Compli-
ance
ActionCondition
Do PART 1:
PREPARATION
-Do a Detailed Inspection
of the Aileron Trim Actua-
tor attachment lug for any
damage and any crack.
(a)
All Airplanes
-FIGURE 3
-FIGURE 4Do a HFEC inspection of
the Aileron Trim Actuator
attachment lug for any
crack. (b)
CONDITION 3: ANY DAM-
AGE OR ANY CRACK IS
FOUND DURING THE
DETAILED INSPECTION
OF THE AILERON TRIM
ACTUATOR ATTACH-
MENT LUG
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REQUIREMENTS BULLETIN 757-27A0159
ALERTALERT

### Page 13

Table 2: Detailed Inspection of the Aileron Trim Actuator Attachment Lug
Refer to the listed
procedures in SB
757-27A0159
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure.
Method of Compli-
ance
ActionCondition
--CONDITION 3.1 (AC-
TION 1): Contact the
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3.1: ANY
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG Do PART 3:
RESTORATION
--
-FIGURE 3CONDITION 3.1 (AC-
TION 2): Repeat Detailed
Inspection of the Aileron
Trim Actuator attachment
lug for any damage and
any crack. (a)
Do PART 3:
RESTORATION
--CONDITION 3.2: NO
CRACK IS FOUND DUR-
ING THE HFEC INSPEC-
TION OF THE AILERON
TRIM ACTUATOR AT-
TACHMENT LUG
-FIGURE 3Repeat Detailed Inspec-
tion of the Aileron Trim
Actuator attachment lug
for any damage and any
crack. (a)
Do PART 3:
RESTORATION
--CONDITION 4: NO DAM-
AGE AND NO CRACK IS
FOUND DURING THE
DETAILED INSPECTION
OF THE AILERON TRIM
ACTUATOR ATTACH-
MENT LUG
-FIGURE 3Repeat Detailed Inspec-
tion of the Aileron Trim
Actuator attachment lug
for any damage or any
crack. (a)
(a) Damage is defined as: Any surface problems, such as scratches or dings, which have
occurred after the part was manufactured.
(b) If a HFEC inspection of the Aileron Trim Actuator attachment lug for any crack is found to
be required as an action for both CONDITION 1 and CONDITION 3, the HFEC inspection
is only required to be done once before further flight.
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REQUIREMENTS BULLETIN 757-27A0159
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### Page 14 (OCR)

REQUIREMENTS BULLETIN 757-27A0159
ALERT  ALERT
WL
166.0
INBD
FEEL, CENTERING, AND TRIM MECHANISM
(VIEW LOOKING FORWARD)
2852517
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BEARING - ROTATION
CHECK
(SHEET 1 OF 2)
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### Page 15

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)1-BEARINGTurn1
(a) Gently turn the Aileron Trim Actuator bearing manually to make sure it turns freely. A bearing that turns
freely is defined as: A bearing that moves without ratchet, gritty, or detent like feeling.
FIGURE 2: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR BEARING - ROTATION
CHECK
(SHEET 2 OF 2)
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### Page 16 (OCR)

REQUIREMENTS BULLETIN 757-27A0159
ALERT  ALERT
WL
166.0
INBD
a INSPECTION AREA
FEEL, CENTERING, AND TRIM MECHANISM
(VIEW LOOKING FORWARD)
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR ATTACHMENT LUG -
DETAILED INSPECTION
(SHEET 1 OF 2)
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Copyright © Unpublished
Work - See page 1 for details.  16 of 19

### Page 17

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)(b)1251N1258-4BOX SUPPORT ASSYInspect1
(a) Do a Detailed Inspection of all sides of the Aileron Trim Actuator attachment lug for any damage or any
crack.
(b) Damage is defined as: Any surface problems, such as scratches or dings, which have occurred after the
part was manufactured.
FIGURE 3: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR ATTACHMENT LUG -
DETAILED INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 29, 2019
757-27A0159 RB
17 of 19
REQUIREMENTS BULLETIN 757-27A0159
ALERTALERT

### Page 18 (OCR)

REQUIREMENTS BULLETIN 757-27A0159
ALERT  ALERT
WL
166.0
INBD
INSPECTION AREA
FEEL, CENTERING, AND TRIM MECHANISM
(VIEW LOOKING FORWARD)
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR ATTACHMENT LUG - HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 1 OF 2)
Original Issue: March 29, 2019
Export Controlled ECCN: 9E991  757-27A0159 RB
Copyright © Unpublished
Work - See page 1 for details.  18 of 19

### Page 19

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)1251N1258-4BOX SUPPORT ASSYInspect1
(a) Do a HFEC inspection of all sides of the Aileron Trim Actuator attachment lug for any crack in accordance
with 757 NDT Manual Part 6, 51-00-19.
FIGURE 4: MAIN LANDING GEAR WHEEL WELL - AILERON TRIM ACTUATOR ATTACHMENT LUG - HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 29, 2019
757-27A0159 RB
19 of 19
REQUIREMENTS BULLETIN 757-27A0159
ALERTALERT

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