# Boeing Alert Requirements Bulletin 737-53A1383 RB: Revision 1

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- Document: [Boeing Alert Requirements Bulletin 737-53A1383 RB](https://openairdocs.org/service-documents/boeing/737-53a1383-rb.md)
- Title as filed: 737-53A1383-00-- RB
- Pages: 33
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### Page 1

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1383 RB
Original Issue: May 09, 2019
ATA System: 5313
SUBJECT: FUSELAGE - Structure Around Openings - Forward Galley Door Bear Strap Inspection
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 © 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Unpublished Work.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
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Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
FIGURE 1: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL GENERAL VISUAL INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
FIGURE 3: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL GENERAL VISUAL INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
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Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1383 RB
Original Issue: May 09, 2019
ATA System: 5313
SUBJECT: FUSELAGE - Structure Around Openings - Forward Galley Door Bear Strap Inspection
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 737-600, 737-700, 737-700C, 737-800, 737-900 Airplane(s), line number(s)
1-1762 in 1 Group(s).
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Boeing
Requirements Bulletin 737-53A1383 RB. The Airworthiness Directive will possibly make the compliance
tasks and times given in Boeing Requirements Bulletin 737-53A1383 RB mandatory..
For airplanes which have incorporated Boeing Business Jet (BBJ) Lower Cabin Altitude Supplemental Type
Certificate (STC) ST01697SE (6500 feet maximum cabin altitude in lieu of 8000 feet) as referenced in
Boeing SB 737-21-1149, the flight cycle related compliance times are different from those specified in this
requirements bulletin. All initial compliance times (threshold and grace period) specified in flight cycles must
be reduced to half of those specified in Requirements Bulletin 737-53A1383 RB. All repeat interval compliance
times specified in flight cycles must be reduced to one-quarter of those specified in Requirements Bulletin
737-53A1383 RB.
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Accomplish the required actions, based on the applicable conditions in Table 1 or 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.
All airplanes must do one of the following Options:
– Option 1: Do Table 1 - Internal and External General Visual Inspection and Internal Surface High
Frequency Eddy Current (HFEC) Inspection of the Forward Galley Door Bear Strap.
– Option 2: Do Table 2 - External General Visual Inspection and External Eddy Current Inspections of
the Forward Galley Door Bear Strap.
Table 1: Option 1 - Internal and External General Visual Inspection and Internal Surface High Frequency
Eddy Current (HFEC) Inspection of the Forward Galley Door Bear Strap
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 737-
53A1383 RB.
Before
15,000 total
flight cycles.
Do an internal and external
general visual inspection of
the forward galley door bear
strap, for any repair.
All airplanes
-Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company
for alternative inspection(s) to
the Requirements Bulletin
737-53A1383 RB, and do the
inspection(s) and applicable
on-condition action(s).
ANY REPAIR FOUND.
(a)
-Before further flight.CONDITION 1 (ACTION 2):
Do an internal surface HFEC
inspection of the forward gal-
ley door bear strap, for any
crack at the unrepaired areas.
-Before further flight.CONDITION 1.1 (ACTION 1):CONDITION 1.1:
Contact The Boeing Company
for repair instructions and do
the repair.
ANY CRACK FOUND.
18,000 flight cycles.-CONDITION 1.1 (ACTION 2):
Repeat the internal surface
HFEC inspection of the for-
ward galley door bear strap,
for any crack.
(b)
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Table 1: Option 1 - Internal and External General Visual Inspection and Internal Surface High Frequency
Eddy Current (HFEC) Inspection of the Forward Galley Door Bear Strap
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
18,000 flight cycles.-Repeat the internal surface
HFEC inspection of the for-
ward galley door bear strap,
for any crack.
CONDITION 1.2:
NO CRACK FOUND.
(b)
-Before further flight.Do an internal surface HFEC
inspection of the forward gal-
ley door bear strap, for any
crack.
CONDITION 2:
NO REPAIR FOUND.
-Before further flight.CONDITION 2.1 (ACTION 1):CONDITION 2.1:
Contact The Boeing Company
for repair instructions and do
the repair.
ANY CRACK FOUND.
18,000 flight cycles.-CONDITION 2.1 (ACTION 2):
Repeat the internal surface
HFEC inspection of the for-
ward galley door bear strap,
for any crack.
(b)
18,000 flight cycles.-Repeat the internal surface
HFEC inspection of the for-
ward galley door bear strap,
for any crack.
CONDITION 2.2:
NO CRACK FOUND.
(b)
(a) It is not required to contact Boeing, if one or a combination of the following repairs has been installed.
1. Remove and replace gap cover in accordance with Boeing installation drawings (141A8350),
2. Up to second oversized fastener holes in accordance with 737-600 SRM 51-40-05, or 737-700
SRM 51-40-05, or 737-700CONV SRM 51-40-05, or 737-700IGW (BBJ) SRM 51-40-05, or 737-
800 SRM 51-40-05, or 737-800BCF SRM 51-40-05 or 737-900 SRM 51-40-05.
3. Skin blend out within the 737-600 SRM 53-00-01, or 737-700 SRM 53-00-01, or 737-700CONV
SRM 53-00-01, or 737-700IGW (BBJ) SRM 53-00-01, or 737-800 SRM 53-00-01, or 737-800BCF
SRM 53-00-01, or 737-900 SRM 53-00-01 allowable damage.
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Table 1: Option 1 - Internal and External General Visual Inspection and Internal Surface High Frequency
Eddy Current (HFEC) Inspection of the Forward Galley Door Bear Strap
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
(b) It is not required to do the internal surface HFEC inspection in areas where a repair covers the affected
inspection zone if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 737-
53A1383 RB and installed after the original issue date of Requirements Bulletin 737-53A1383
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 737-
53A1383 RB.
Before
15,000 total
flight cy-
cles.
Do the external general visual in-
spection of the gap cover and skin
in the forward galley door bear
strap eddy current inspection
zones, for any repair.
All airplanes
-Before further flight.Contact The Boeing Company for
alternative inspection(s) to the
Requirements Bulletin 737-
53A1383 RB, and do the inspec-
tion(s) and applicable on-condi-
tion action(s).
CONDITION 3:
ANY EXTERNAL RE-
PAIR FOUND.
(a)
-Before further flight.Do the external LFEC inspection
of the forward galley door bear
strap and external HFEC inspec-
tion of the skin for any crack.
CONDITION 4:
NO EXTERNAL RE-
PAIR FOUND.
-Before further flight.CONDITION 4.1 (ACTION 1):CONDITION 4.1:
Contact The Boeing Company for
repair instructions and do the re-
pair.
ANY CRACK FOUND
DURING THE EXTER-
NAL LFEC AND HFEC
EDDY CURRENT IN-
SPECTIONS. -Before further flight.CONDITION 4.1 (ACTION 2):Do an internal general visual in-
spection of the forward galley
door bear strap, for any repair.
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Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 4.1.1 (ACTION 1):CONDITION 4.1.1:
Contact The Boeing Company for
alternative inspection(s) to the
Requirements Bulletin 737-
53A1383 RB, and do the inspec-
tion(s) and applicable on-condi-
tion action(s).
ANY INTERNAL RE-
PAIR FOUND.
(b)
-Before further flight.CONDITION 4.1.1 (ACTION 2):
Do an internal surface HFEC in-
spection of the forward galley
door bear strap, for any crack at
the unrepaired areas.
-Before further flight.CONDITION 4.1.1.1 (ACTION 1):CONDITION 4.1.1.1:
Contact The Boeing Company for
repair instructions and do the re-
pair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
18,000 flight cycles.-CONDITION 4.1.1.1 (ACTION 2):
Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
(c)
18,000 flight cycles.-Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
CONDITION 4.1.1.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
(c)
-Before further flight.Do an internal surface HFEC in-
spection of the forward galley
door bear strap, for any crack.
CONDITION 4.1.2:
NO INTERNAL RE-
PAIR FOUND.
-Before further flight.CONDITION 4.1.2.1 (ACTION 1):CONDITION 4.1.2.1:
Contact The Boeing Company for
repair instructions and do the re-
pair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
18,000 flight cycles.-CONDITION 4.1.2.1 (ACTION 2):
Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
(c)
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Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
18,000 flight cycles.-Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
CONDITION 4.1.2.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
(c)
-Within 12,000 flight cycles
after the external eddy cur-
rent inspections were done.
Do an internal general visual in-
spection of the forward galley
door bear strap, for any repair.
CONDITION 4.2:
NO CRACK FOUND
DURING EXTERNAL
EDDY CURRENT IN-
SPECTIONS.
(d)
-Before further flight.CONDITION 4.2.1 (ACTION 1):CONDITION 4.2.1:
Contact The Boeing Company for
alternative inspection(s) to the
Requirements Bulletin 737-
53A1383 RB, and do the inspec-
tion(s) and applicable on-condi-
tion action(s).
ANY INTERNAL RE-
PAIR FOUND.
(b)
-Before further flight.CONDITION 4.2.1 (ACTION 2):
Do an internal surface HFEC in-
spection of the forward galley
door bear strap, for any crack at
the unrepaired areas.
-Before further flight.CONDITION 4.2.1.1 (ACTION 1):CONDITION 4.2.1.1:
Contact The Boeing Company for
repair instructions and do the re-
pair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
18,000 flight cycles.-CONDITION 4.2.1.1 (ACTION 2):
Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
(c)
18,000 flight cycles.-Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
CONDITION 4.2.1.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
(c)
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Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Do an internal surface HFEC in-
spection of the forward galley
door bear strap, for any crack.
CONDITION 4.2.2:
NO INTERNAL RE-
PAIR FOUND.
-Before further flight.CONDITION 4.2.2.1 (ACTION 1):CONDITION 4.2.2.1:
Contact The Boeing Company for
repair instructions and do the re-
pair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
18,000 flight cycles.-CONDITION 4.2.2.1 (ACTION 2):
Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
(c)
18,000 flight cycles.-Repeat the internal surface HFEC
inspection of the forward galley
door bear strap, for any crack.
CONDITION 4.2.2.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
(c)
(a) It is not required to contact Boeing, if one or a combination of the following repairs has been installed:
1. Remove and replace gap cover in accordance with Boeing installation drawings (141A8350),
2. Up to second oversized fastener holes in accordance with 737-600 SRM 51-40-05, or 737-700
SRM 51-40-05, or 737-700CONV SRM 51-40-05, or 737-700IGW (BBJ) SRM 51-40-05, or 737-
800 SRM 51-40-05, or 737-800BCF SRM 51-40-05 or 737-900 SRM 51-40-05.
3. Skin blend out within the 737-600 SRM 53-00-01, or 737-700 SRM 53-00-01, or 737-700CONV
SRM 53-00-01, or 737-700IGW (BBJ) SRM 53-00-01, or 737-800 SRM 53-00-01, or 737-800BCF
SRM 53-00-01, or 737-900 SRM 53-00-01 allowable damage.
(b) It is not required to contact Boeing if one or a combination of the following repairs has been installed:
1. Up to second oversized fastener holes in accordance with 737-600 SRM 51-40-05, or 737-700
SRM 51-40-05, or 737-700CONV SRM 51-40-05, or 737-700IGW (BBJ) SRM 51-40-05, or 737-
800 SRM 51-40-05, or 737-800BCF SRM 51-40-05 or 737-900 SRM 51-40-05.
2. Bear strap blend out within the 737-600 SRM 53-00-01, or 737-700 SRM 53-00-01, or 737-
700CONV SRM 53-00-01, or 737-700IGW (BBJ) SRM 53-00-01, or 737-800 SRM 53-00-01, or
737-800BCF SRM 53-00-01, or 737-900 SRM 53-00-01 allowable damage.
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### Page 12

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
(c) It is not required to do the internal surface HFEC inspection in areas where a repair covers the affected
inspection zone if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 737-
53A1383 RB and installed after the original issue date of Requirements Bulletin 737-53A1383
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(d) For airplanes which have incorporated Boeing Business Jet (BBJ) Lower Cabin Altitude Supplemental
Type Certificate (STC) ST01697SE, the first inspection interval should be reduced to one quarter.
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
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
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 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.
This Requirements Bulletin is also approved for airplanes converted into 737-800BCF under project number
TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certification Data Sheet
A16WE.
This Requirements Bulletin is also approved for 737-700/-800/-900 airplanes having FAA Aviation Partners
Boeing (APB) Supplemental Type Certificate (STC) number ST00830SE installed (not including any areas
affected by the split scimitar winglet configuration).
NOTE: THE APPROVAL STATEMENT THAT FOLLOWS IS FOR 737-700C AIRPLANES ONLY.
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 all 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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This Requirements Bulletin is also approved for 737-700C airplanes having FAA Aviation Partners Boeing
(APB) Supplemental Type Certificate (STC) number ST00830SE installed (not including any areas affected
by the split scimitar winglet configuration).
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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. 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 737-SL-51-042, 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 737 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
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 737
Aircraft Maintenance Manual (AMM).
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ALERTALERT

### Page 16

— 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. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance, unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked. Basic cleaning may be
required to ensure appropriate visibility.
11. 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.
B. WORK INSTRUCTIONS
1. Requirements:
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ALERTALERT

### Page 17

Table 1: Option 1 - Internal and External General Visual Inspection and Internal Surface High Frequency
Eddy Current (HFEC) Inspection of the Forward Galley Door Bear Strap
Refer to the listed
procedures in SB
737-53A1383
Original Issue or
later approved re-
visions as an ac-
cepted procedure
Method of ComplianceActionCondition
DO PART 1:-Do an internal and external general vi-
sual inspection of the forward galley
door bear strap, for any repair.
All airplanes
GET ACCESS.
-FIGURE 1 and
FIGURE 3
--CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company for alter-
native inspection(s) to the Require-
ments Bulletin 737-53A1383 RB, and
do the inspection(s) and applicable on-
condition action(s).
ANY REPAIR FOUND.
(a)
-FIGURE 2CONDITION 1 (ACTION 2):
Do an internal surface HFEC inspec-
tion of the forward galley door bear
strap, for any crack at the unrepaired
areas.
DO PART 2:-CONDITION 1.1 (ACTION 1):CONDITION 1.1:
CLOSE ACCESS.Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND.
DO PART 1:-CONDITION 1.1 (ACTION 2):
GET ACCESS.Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack. -FIGURE 2
(b)
DO PART 2:-Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack.
CONDITION 1.2:
NO CRACK FOUND. CLOSE ACCESS.
DO PART 1:-(b) GET ACCESS.
-FIGURE 2
-FIGURE 2Do an internal surface HFEC inspec-
tion of the forward galley door bear
strap, for any crack.
CONDITION 2:
NO REPAIR FOUND.
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### Page 18

Table 1: Option 1 - Internal and External General Visual Inspection and Internal Surface High Frequency
Eddy Current (HFEC) Inspection of the Forward Galley Door Bear Strap
Refer to the listed
procedures in SB
737-53A1383
Original Issue or
later approved re-
visions as an ac-
cepted procedure
Method of ComplianceActionCondition
DO PART 2:-CONDITION 2.1 (ACTION 1):CONDITION 2.1:
CLOSE ACCESS.Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND.
DO PART 1:-CONDITION 2.1 (ACTION 2):
GET ACCESS.Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack. -FIGURE 2
(b)
DO PART 2:-Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack.
CONDITION 2.2:
NO CRACK FOUND. CLOSE ACCESS.
DO PART 1:-(b) GET ACCESS.
-FIGURE 2
(a) It is not required to contact Boeing, do the internal general visual inspection or do the internal surface
HFEC inspection where one or a combination of the following repairs has been installed:
1. Remove and replace gap cover in accordance with Boeing installation drawings (141A8350).
2. Up to second oversized fastener holes in accordance with 737-600 SRM 51-40-05, or 737-700
SRM 51-40-05, or 737-700CONV SRM 51-40-05, or 737-700IGW (BBJ) SRM 51-40-05, or 737-
800 SRM 51-40-05, or 737-800BCF SRM 51-40-05 or 737-900 SRM 51-40-05.
3. Skin blend out within the 737-600 SRM 53-00-01, or 737-700 SRM 53-00-01, or 737-700CONV
SRM 53-00-01, or 737-700IGW (BBJ) SRM 53-00-01, or 737-800 SRM 53-00-01, or 737-800BCF
SRM 53-00-01, or 737-900 SRM 53-00-01 allowable damage.
(b) It is not required to do the internal surface HFEC inspection in areas where a repair covers the affected
inspection zone if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 737-
53A1383 RB and installed after the original issue date of Requirements Bulletin 737-53A1383
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
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ALERTALERT

### Page 19

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Refer to the listed
procedures in SB
737-53A1383
Original Issue or
later approved re-
visions as an ac-
cepted procedure
Method of ComplianceActionCondition
-FIGURE 3Do the external general visual inspec-
tion of the gap cover and skin in the
forward galley door bear strap eddy
current inspection zones, for any re-
pair.
All airplanes
--Contact The Boeing Company for alter-
native inspection(s) to the Require-
ments Bulletin 737-53A1383 RB, and
do the inspection(s) and applicable on-
condition action(s).
CONDITION 3:
ANY EXTERNAL RE-
PAIR FOUND.
(a)
-FIGURE 4Do the external LFEC inspection of the
forward galley door bear strap and ex-
ternal HFEC inspection of the skin for
any crack.
CONDITION 4:
NO EXTERNAL RE-
PAIR FOUND.
--CONDITION 4.1 (ACTION 1):CONDITION 4.1:
Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND
DURING THE EXTER-
NAL LFEC AND HFEC
EDDY CURRENT IN-
SPECTIONS.
DO PART 1:
GET ACCESS.
-CONDITION 4.1 (ACTION 2):
Do an internal general visual inspection
of the forward galley door bear strap,
for any repair. -FIGURE 1
--CONDITION 4.1.1 (ACTION 1):CONDITION 4.1.1:
Contact The Boeing Company for alter-
native inspection(s) to the Require-
ments Bulletin 737-53A1383 RB, and
do the inspection(s) and applicable on-
condition action.
ANY INTERNAL RE-
PAIR FOUND.
(b)
-FIGURE 2CONDITION 4.1.1 (ACTION 2):
Do an internal surface HFEC inspec-
tion of the forward galley door bear
strap, for any crack at the unrepaired
areas.
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### Page 20

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Refer to the listed
procedures in SB
737-53A1383
Original Issue or
later approved re-
visions as an ac-
cepted procedure
Method of ComplianceActionCondition
DO PART 2:-CONDITION 4.1.1.1 (ACTION 1):CONDITION 4.1.1.1:
CLOSE ACCESS.Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
DO PART 1:
GET ACCESS.
-CONDITION 4.1.1.1 (ACTION 2):
Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack. -FIGURE 2
(c)
DO PART 2:-Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack.
CONDITION 4.1.1.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
CLOSE ACCESS.
DO PART 1:
GET ACCESS.
-(c)
-FIGURE 2
-FIGURE 2Do an internal surface HFEC inspec-
tion of the forward galley door bear
strap, for any crack.
CONDITION 4.1.2:
NO INTERNAL RE-
PAIR FOUND.
DO PART 2:-CONDITION 4.1.2.1 (ACTION 1):CONDITION 4.1.2.1:
CLOSE ACCESS.Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
DO PART 1:
GET ACCESS.
-CONDITION 4.1.2.1 (ACTION 2):
Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack. -FIGURE 2
(c)
DO PART 1:-Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack.
CONDITION 4.1.2.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
GET ACCESS.
-FIGURE 2(c)
DO PART 1:-Do an internal general visual inspection
of the forward galley door bear strap,
for any repair.
CONDITION 4.2:
NO CRACK FOUND
DURING EXTERNAL
EDDY CURRENT IN-
SPECTIONS.
GET ACCESS.
-FIGURE 1
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### Page 21

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Refer to the listed
procedures in SB
737-53A1383
Original Issue or
later approved re-
visions as an ac-
cepted procedure
Method of ComplianceActionCondition
--CONDITION 4.2.1 (ACTION 1):CONDITION 4.2.1:
Contact The Boeing Company for alter-
native inspection(s) to the Require-
ments Bulletin 737-53A1383 RB, and
do the inspection(s) and applicable on-
condition action.
ANY INTERNAL RE-
PAIR FOUND.
(b)
-FIGURE 2CONDITION 4.2.1 (ACTION 2):
Do an internal surface HFEC inspec-
tion of the forward galley door bear
strap, for any crack at the unrepaired
areas.
DO PART 2:-CONDITION 4.2.1.1 (ACTION 1):CONDITION 4.2.1.1:
CLOSE ACCESS.Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
DO PART 1:
GET ACCESS.
-CONDITION 4.2.1.1 (ACTION 2):
Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack. -FIGURE 2
(c)
DO PART 2:-Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack.
CONDITION 4.2.1.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
AN INTERNAL REPAIR
FOUND.
CLOSE ACCESS.
DO PART 1:
GET ACCESS.
-(c)
-FIGURE 2
-FIGURE 2Do an internal surface HFEC inspec-
tion of the forward galley door bear
strap, for any crack.
CONDITION 4.2.2:
NO INTERNAL RE-
PAIR FOUND.
DO PART 2:-CONDITION 4.2.2.1 (ACTION 1):CONDITION 4.2.2.1:
CLOSE ACCESS.Contact The Boeing Company for re-
pair instructions and do the repair.
ANY CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
DO PART 1:
GET ACCESS.
-CONDITION 4.2.2.1 (ACTION 2):
Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack. -FIGURE 2
(c)
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### Page 22

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and skin
Refer to the listed
procedures in SB
737-53A1383
Original Issue or
later approved re-
visions as an ac-
cepted procedure
Method of ComplianceActionCondition
DO PART 2:-Repeat the internal surface HFEC in-
spection of the forward galley door
bear strap, for any crack.
CONDITION 4.2.2.2:
NO CRACK FOUND
DURING THE INTER-
NAL SURFACE HFEC
INSPECTION, WITH
NO INTERNAL RE-
PAIR FOUND.
CLOSE ACCESS.
DO PART 1:
GET ACCESS.
-(c)
-FIGURE 2
(a) It is not required to contact Boeing, if one or a combination of the following repairs has been installed:
1. Remove and replace gap cover in accordance with Boeing installation drawings (141A8350).
2. Up to second oversized fastener holes in accordance with 737-600 SRM 51-40-05, or 737-700
SRM 51-40-05, or 737-700CONV SRM 51-40-05, or 737-700IGW (BBJ) SRM 51-40-05, or 737-
800 SRM 51-40-05, or 737-800BCF SRM 51-40-05 or 737-900 SRM 51-40-05.
3. Skin blend out within the 737-600 SRM 53-00-01, or 737-700 SRM 53-00-01, or 737-700CONV
SRM 53-00-01, or 737-700IGW (BBJ) SRM 53-00-01, or 737-800 SRM 53-00-01, or 737-800BCF
SRM 53-00-01, or 737-900 SRM 53-00-01 allowable damage.
(b) It is not required to contact Boeing if one or a combination of the following repairs has been installed:
1. Up to second oversized fastener holes in accordance with 737-600 SRM 51-40-05, or 737-700
SRM 51-40-05, or 737-700CONV SRM 51-40-05, or 737-700IGW (BBJ) SRM 51-40-05, or 737-
800 SRM 51-40-05, or 737-800BCF SRM 51-40-05 or 737-900 SRM 51-40-05.
2. Bear strap blend out within the 737-600 SRM 53-00-01, or 737-700 SRM 53-00-01, or 737-
700CONV SRM 53-00-01, or 737-700IGW (BBJ) SRM 53-00-01, or 737-800 SRM 53-00-01, or
737-800BCF SRM 53-00-01, or 737-900 SRM 53-00-01 allowable damage.
(c) It is not required to do the internal surface HFEC inspection in areas where a repair covers the affected
inspection zone if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 737-
53A1383 RB and installed after the original issue date of Requirements Bulletin 737-53A1383
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
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REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

### Page 23 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA
STA  344
328
STA
294.5
STA 291.5  STA  7- S-5R
→— S-6R
» - S-7R
S-5R -
- S-8R
S-6R -
S-7R -C  - S-9R
S-8R—
→ -S-10R
S-9R-
— S-11R
S-10R -~
S-11R-C  - S-12R
S-12R-
L- S-13R
S-13R -
- S-14R
S-14R -
- S-15R
S-15R -
- S-16R
S-16R-
FORWARD GALLEY DOOR CUTOUT STRUCTURE
(GALLEY, SIDEWALL PANELS AND INSULATION REMOVED)
INSPECTION AREA  FWD  2860810
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.
FIGURE 1: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL GENERAL VISUAL INSPECTION
(SHEET 1 OF 2)
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### Page 24

More DataQtyIdentificationNameTaskStep
(a)--BEAR STRAPInspect1
(a) Do an internal general visual inspection of the forward galley door bear strap, for any repair.
FIGURE 1: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL GENERAL VISUAL INSPECTION
(SHEET 2 OF 2)
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REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

### Page 25 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA
STA  344
328
STA
294.5
ST 291.5  STA  7— S-5R
→- S-6R
» - S-7R
S-5R -
— S-8R
S-6R -
S-7R -C  - S-9R
S-8R-
→—S-10R
S-9R-
- S-11R
S-10R -~
S-11R-C  - S-12R
S-12R-
L- S-13R
S-13R -
- S-14R
S-14R -1
- S-15R
S-15R -
- S-16R
S-16R-
FORWARD GALLEY DOOR CUTOUT STRUCTURE
(GALLEY, SIDEWALL PANELS AND INSULATION REMOVED)
2844324
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION
(SHEET 1 OF 3)
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### Page 26 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  STA
INNER CHORD  291.5  HINGE BOX  294.5  STUB FRAME
STOP FITTING
S-8R -  CRACK
• (TYPICAL)
/ FITTING-LATCH
SKIN
~ BEAR STRAP
S-9R -
1 23 LOCATIONS
• SEAL
DEPRESSOR
HINGE BOX
WD
HFEC INSPECTION AREA
2844326
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION
(SHEET 2 OF 3)
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### 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)--BEAR STRAPInspect1
(b)--BEAR STRAPInspect2
(a) Do an internal surface HFEC inspection of the bear strap, for any crack. Inspect around each fastener in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure 23.
(b) Do an internal surface HFEC inspection of the bear strap, for any crack. Inspect along the path shown in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure 23.
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION
(SHEET 3 OF 3)
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REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

### Page 28 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA
294.5
GAP COVER
FWD
FORWARD GALLEY DOOR
INSPECTION AREA  2860812
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.
FIGURE 3: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL GENERAL VISUAL INSPECTION
(SHEET 1 OF 2)
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### Page 29

More DataQtyIdentificationNameTaskStep
(a)--SKINInspect1
(a)--GAP COVERInspect
(a) Do an external general visual inspection of the forward galley door skin and gap cover, for any repair.
FIGURE 3: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL GENERAL VISUAL INSPECTION
(SHEET 2 OF 2)
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ALERTALERT

### Page 30 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  • GAP COVER
294.5
AND
FWD
FORWARD GALLEY DOOR
2858753
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
(SHEET 1 OF 4)
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### Page 31 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  STA
16 LOCATIONS 2  294.5  291.5
SKIN
CRACK
(TYPICAL)
PROBE SCAN
DIRECTION
GAP COVER,  S-9R
RAIN GUTTER
BEAR STRAP  OUTER CHORD
FWD
LFEC INSPECTION AREA  2858756
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
(SHEET 2 OF 4)
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### Page 32 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  STA
294.5  291.5
SKIN
3 25 LOCATIONS
GAP COVER  S-9R
RAIN GUTTER
BEAR STRAP  OUTER CHORD
FWD
HFEC INSPECTION AREA  2858758
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
(SHEET 3 OF 4)
Original Issue: May 09, 2019
Export Controlled ECCN: 9E991 - BOEING  737-53A1383 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  32 of 33

### Page 33

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)--BEAR STRAPInspect1
(b)--BEAR STRAPInspect2
(c)--SKINInspect3
(a) Do an external subsurface Low Frequency Eddy Current (LFEC) inspection of the bear strap, for any
crack. Use the probe to scan on the outer surface of the skin and in the direction shown between the two
rows of fasteners common to the STA 291.5 frame outer chord in accordance with 737 NDT Manual Part
6, 51-00-26. The gap cover thickness is 0.10 inches. The skin thickness is 0.0710 inches. The bear strap
thickness is 0.10 inches. The outer chord thickness is 0.110 inches.
(b) Do an external subsurface LFEC inspection of the bear strap at each fastener location, for any crack.
Use the probe to scan the outer surface of skin and the gap cover around the fastener heads to the
greatest extent possible while avoiding skin and gap cover edges. Do not let the probe reach the edge
of part during LFEC inspection, it will cause false reading(s). At the locations labeled half circle, only scan
in half circle regions to the greatest extent possible while avoiding skin and gap cover edges. Do the
LFEC inspection(s) in accordance with 737 NDT Manual Part 6, 51-00-26. The gap cover thickness is
0.10 inches. The skin thickness is 0.0710 inches. The bear strap thickness is 0.10 inches. The outer chord
thickness is 0.110 inches.
(c) Do an external surface High Frequency Eddy Current (HFEC) inspection of the skin forward of the galley
door, for any crack. Use the probe to scan on the outer surface of the skin around the fastener heads in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure 23.
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 09, 2019
737-53A1383 RB
33 of 33
REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

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