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

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- Title as filed: RB-737-53A1383RB Rev 01
- Pages: 37
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### Page 1

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1383 RB
Original Issue: May 09, 2019
Revision 1: February 19, 2020
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:
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Unpublished Work.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.
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737-53A1383 RBRevision 1: February 19, 2020
1 of 37
3.0

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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
FIGURE 1: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL GENERAL VISUAL INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
FIGURE 3: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL GENERAL VISUAL INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
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REQUIREMENTS BULLETIN 737-53A1383
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Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Revision Transmittal SheetNumber: 737-53A1383 RBOriginal Issue: May 09, 2019
Revision 1: February 19, 2020
ATA System: 5313
SUBJECT: FUSELAGE - Structure Around Openings - Forward Galley Door Bear Strap Inspection
This revision includes all pages of the requirements bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2019-NM-098-AD, is related to
Requirements Bulletin 737-53A1383 RB.
Effects of this Revision on airplanes on which the Original Issue was previously done:
ActionConditionGroup
The more work is to do as follows:No crack was
found.
All airplanes that have done Option
2, Condition 4 (no external repair
and have done the external Low
Frequency Eddy Current (LFEC) in-
spection of the forward galley door
bear strap and external High Fre-
quency Eddy Current (HFEC) inspec-
tion of the fuselage skin for any
crack).
Do the external LFEC inspection of the forward galley
door bear strap and external HFEC inspection of the
fuselage skin for any crack in accordance with FIG-
URE 4.
Before 15,000 total flight cycles
or
Within 6,000 flight cycles after the original issue date
of Requirements Bulletin 737-53A1383 RB
Whichever occurs later.
REASON FOR REVISION
This revision is sent to correct thickness callouts for the fuselage skin and bear strap.
These sections in the Requirements Bulletin (RB) were changed:
1. In Paragraph 1.A.1. Airplanes, added effectivity variable number tables.
2. In Paragraph 3. COMPLIANCE, added Federal Aviation Administration (FAA) Notice of Proposed Rule
Making 2019-NM-098-AD.
3. In Paragraph 3. COMPLIANCE, B. WORK INSTRUCTIONS and Figures 2-4, changed "skin" to "fuselage
skin".
4. In Figure 4, Footnote (a), changed fuselage skin and bear strap thickness callouts and removed gap
cover thickness.
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5. In Figure 4, Footnote (b), changed fuselage skin and bear strap thickness callouts and removed outer
chord thickness.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
Service BulletinService BulletinRequirement BulletinRequirement Bulletin
737-53A1383737-53A1383737-53A1383 RB737-53A1383 RB
Issue DateIssue Date
May 09, 2019Original Issue:May 09, 2019Original Issue:
February 19, 2020Revision 1:February 19, 2020Revision 1:
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REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

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Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1383 RB
Original Issue: May 09, 2019
Revision 1: February 19, 2020
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). 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.
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900
GroupVariable Number
1YA001 - YA099
1YA101 - YA199
1YA201 - YA211
1YA221
1YA231 - YA242
1YA251 - YA256
1YA271 - YA272
1YA291
1YA301 - YA302
GroupVariable Number
1YA311 - YA314
1YA321 - YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
1YA501 - YA536
1YA541 - YA552
GroupVariable Number
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
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GroupVariable Number
1YA671 - YA672
1YA681 - YA691
1YA701 - YA710
1YA721 - YA722
1YA731 - YA734
1YA751 - YA756
1YA801 - YA803
1YA809
1YA811 - YA814
1YA831 - YA835
1YA841 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA976
1YB001 - YB006
1YB101 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB381
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
1YB561 - YB574
1YB576 - YB577
1YB581 - YB587
GroupVariable Number
1YB601 - YB632
1YB651
1YB656
1YB851 - YB863
1YB871 - YB873
1YB881 - YB888
1YB901 - YB903
1YB911
1YC001 - YC030
1YC051 - YC083
1YC091 - YC094
1YC101 - YC104
1YC111 - YC113
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC178
1YC186 - YC189
1YC201 - YC203
1YC206 - YC207
1YC301 - YC305
1YC321 - YC386
1YC391 - YC394
1YC396
1YC401 - YC417
1YC421 - YC422
1YC426 - YC428
1YC436 - YC437
1YC441 - YC448
1YC451 - YC455
GroupVariable Number
1YC459
1YC461 - YC467
1YC471 - YC499
1YC501 - YC526
1YC571 - YC583
1YC587 - YC589
1YC591 - YC593
1YC601 - YC655
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC741
1YC751 - YC752
1YC761 - YC770
1YC781 - YC793
1YC801 - YC892
1YC901 - YC907
1YC921 - YC922
1YC931 - YC932
1YC941 - YC951
1YC971 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD108
1YD121 - YD126
1YD151 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
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GroupVariable Number
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
1YD391
1YD401 - YD410
1YD412
1YD481 - YD485
1YD491
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD601 - YD612
1YD651 - YD654
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
GroupVariable Number
1YE371
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG092
1YG201
1YG211
1YG501 - YG508
1YG601 - YG602
1YJ001 - YJ004
1YJ011 - YJ013
1YJ021
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ547
1YJ591 - YJ594
1YJ631 - YJ632
1YJ671 - YJ682
1YJ801 - YJ853
1YJ861 - YJ867
1YJ871
1YJ901 - YJ902
1YJ911 - YJ923
1YJ931 - YJ936
1YJ941 - YJ943
GroupVariable Number
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK132
1YK136 - YK137
1YK301 - YK304
1YK321 - YK330
1YK361 - YK366
1YK401 - YK406
1YK426 - YK427
1YK431 - YK432
1YK456 - YK460
1YK480 - YK484
1YK511 - YK512
1YK601
1YM101 - YM103
1YM201 - YM204
1YM251 - YM268
1YM471
1YM481 - YM482
1YM501
1YM521
1YM541
1YM551
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2019-NM-098-AD, is related to
Requirements Bulletin 737-53A1383 RB.
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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.
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 and Fuselage Skin.
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.
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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
-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)
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)
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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
(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. Fuselage 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.
Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and Fuselage 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
fuselage skin in the forward galley
door bear strap eddy current in-
spection 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)
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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 Fuselage Skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Do the external LFEC inspection
of the forward galley door bear
strap and external HFEC inspec-
tion of the fuselage 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.
-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)
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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 Fuselage 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 4.1.2:
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)
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.
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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 Fuselage Skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-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)
-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)
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### Page 16

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and Fuselage Skin
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
(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. Fuselage 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.
(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.
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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.
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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BLANK PAGE

### Page 19

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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— 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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### Page 21

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 22

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. Fuselage 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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### Page 23

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and Fuselage 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 fuselage skin
in the forward galley door bear strap
eddy current inspection zones, for any
repair.
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 fuselage
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 24

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and Fuselage 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 25

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and Fuselage 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 26

Table 2: Option 2 - External General Visual Inspection and External Eddy Current Inspections of the
Forward Galley Door Bear Strap and Fuselage 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. Fuselage 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 27 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA
STA  344
328
STA
294.5
STA 291.5  STA  7- S-5R
→- S-6R
p - S-7R
S-5R -
— S-8R
S-6R -
S-7R -C  - S-9R
S-8R-
3-S-10R
S-9R
— S-11R
S-10R -
S-11R-  - S-12R
S-12R-
1 — 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
FIGURE 1: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL GENERAL VISUAL INSPECTION
(SHEET 1 OF 2)
Original Issue: May 09, 2019
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  737-53A1383 RB
Copyright © Unpublished
Work - See page 1 for details.  27 0f 37

### Page 28

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
(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)
Export Controlled ECCN: 9E991
Copyright © Unpublished
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737-53A1383 RBRevision 1 February 19, 2020
28 of 37
REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

### Page 29 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA
STA  344
328
STA
294.5
STA 291.5  STA  7- S-5R
→- S-6R
p - S-7R
S-5R -
— S-8R
S-6R -
S-7R -1  - S-9R
S-8R~
→-S-10R
S-9R-
— S-11R
S-10R -
S-11R-  - S-12R
S-12R-
1 — 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)
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION
(SHEET 1 OF 3)
Original Issue: May 09, 2019
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  737-53A1383 RB
Copyright © Unpublished
Work - See page 1 for details.  29 of 37

### Page 30 (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)
I FUSELAGE  • FITTING-LATCH
SKIN
- BEAR STRAP
S-9R -
1 23 LOCATIONS
• SEAL
DEPRESSOR
HINGE BOX
ND
HFEC INSPECTION AREA
B
2844326
FIGURE 2: FORWARD GALLEY DOOR BEAR STRAP - INTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION
(SHEET 2 OF 3)
Original Issue: May 09, 2019
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  737-53A1383 RB
Work - See page 1 for details.  Copyright © Unpublished  30 of 37

### Page 31

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)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 09, 2019
737-53A1383 RBRevision 1 February 19, 2020
31 of 37
REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

### Page 32 (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)
Original Issue: May 09, 2019
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  737-53A1383 RB
Copyright © Unpublished
Work - See page 1 for details.  32 of 37

### Page 33

More DataQtyIdentificationNameTaskStep
(a)--FUSELAGE SKINInspect1
(a)--GAP COVERInspect
(a) Do an external general visual inspection of the fuselage skin and gap cover adjacent to the forward galley
door, for any repair.
FIGURE 3: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL GENERAL VISUAL INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
Copyright © Unpublished
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737-53A1383 RBRevision 1 February 19, 2020
33 of 37
REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

### Page 34 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  GAP COVER
294.5
FWD
FORWARD GALLEY DOOR
2858753
FIGURE 4: FORWARD GALLEY DOOR BEAR STRAP - EXTERNAL EDDY CURRENT INSPECTIONS
(SHEET 1 OF 4)
Original Issue: May 09, 2019
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1383 RB
Work - See page 1 for details.  34 of 37

### Page 35 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  STA
16 LOCATIONS (2  294.5  291.5
FUSELAGE
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)
Original Issue: May 09, 2019
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1383 RB
Work - See page 1 for details.  35 of 37

### Page 36 (OCR)

REQUIREMENTS BULLETIN 737-53A1383
ALERT  ALERT
STA  STA
294.5  291.5
FUSELAGE
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
Revision 1 February 19, 2020  Export Controlled ECCN: 9E991  737-53A1383 RB
Copyright © Unpublished
Work - See page 1 for details.  36 of 37

### Page 37

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)--FUSELAGE 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 fuselage 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 fuselage skin thickness is 0.100 inches. The bear strap thickness is 0.090
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 fuselage skin and the gap cover around the fastener heads to
the greatest extent possible while avoiding fuselage 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 fuselage 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 0.100 inches. The fuselage skin thickness is 0.100 inches. The bear strap thickness is 0.090
inches.
(c) Do an external surface High Frequency Eddy Current (HFEC) inspection of the fuselage skin forward of
the galley door, for any crack. Use the probe to scan on the outer surface of the fuselage 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
Copyright © Unpublished
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737-53A1383 RBRevision 1 February 19, 2020
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REQUIREMENTS BULLETIN 737-53A1383
ALERTALERT

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