# Boeing Alert Service Bulletin 737-53A1329: No revision named

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- Title as filed: U.S. DOT/FAA - SB-737-53A1329-00
- Pages: 29
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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1329
Original Issue: June 04, 2013
ATA System: 5330
SUBJECT: FUSELAGE - Skin - Forward Entry Doorway - Lower Corners - Inspection and Repair
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
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9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2013 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
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6.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 4
B. Concurrent Requirements ...................................... 1 4
C. Reason ................................................ 1 4
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F. Approval ............................................... 1 7
G. Manpower .............................................. 1 7
H. Weight and Balance Changes .................................... 1 8
I. Electrical Load Data ......................................... 1 8
J. References .............................................. 1 8
1. Existing Data: ......................................... 1 8
2. Data Supplied with this Service Bulletin: ........................... 1 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9
K. Publications Affected ........................................ 1 9
L. Interchangeability and Intermixability of Parts ........................... 1 9
M. Software Accomplishment Summary ................................ 1 9
2. MATERIAL INFORMATION ........................................ 2 1
A. Material - Price and Availability ................................... 2 1
B. Industry Support Information .................................... 2 1
C. Parts Necessary for Each Airplane ................................. 2 1
1. Kits/Parts ............................................ 2 1
2. Parts and Materials Supplied by the Operator ........................ 2 1
3. Parts Modified and Reidentified ................................ 2 1
4. Parts Removed and Not Replaced .............................. 2 1
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 4
FIGURE 1: FUSELAGE - FORWARD ENTRY DOORWAY - SKIN ASSEMBLY AND BEAR STRAP AT THE
LOWER CORNERS - INSPECTION [Group 2-3] ....................... 2 6
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1329Original Issue: June 04, 2013
ATA System: 5330
SUBJECT: FUSELAGE - Skin - Forward Entry Doorway - Lower Corners - Inspection and Repair
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to inspect the lower corners of the forward entry doorway for cracking on
airplanes that do not have an airstair door cutout. If the work in this service bulletin is not done, continued crack
progression can result in possible rapid decompression.
Boeing has received five reports of cracking in the skin at the lower aft corner of the forward entry doorway on
airplanes that do not have an airstair door cutout. The cracks ranged from 0.25 to 2.0 inches in length. The
airplanes had accumulated between 34,813 and 73,083 total flight cycles. Cracks in the lower corners of the
forward entry doorway are caused by fatigue loads in the skin and bear strap which are magnified by local stress
concentrations due to the door cutout and edge margin effects at fastener locations near the corner radius.
Additionally, cracks can be initiated from impact damage due to high usage rate of the forward entry door.
Accomplishment of the work in this service bulletin will make sure that cracking at the lower corners of the
forward entry doorway on airplanes that do not have an airstair door cutout is detected and a repair installed.
Boeing Service Bulletin 737-53-1083 gives instructions for the inspection, modification and repair of the lower
corners of the forward entry doorway on airplanes that have an airstair door cutout.
Boeing Service Related Problem (SRP) 737-SRP-53-0381 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-11003 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
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ReferenceAffectedPlanning Data
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected
(Flight Crew Operations Manual and/or
FAA Approved Airplane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Group 1:
Contact Boeing to get instructions for the inspections and repairs for this service bulletin 737-53A1329 Original
Issue and do the work instructed by Boeing.
Group 2-3:
Remove the scuff plates at the lower corners of the forward entry doorway.
Group 2:
At the lower corners of the forward entry doorway, do an internal detailed inspection of the skin assembly and
bear strap, an internal High Frequency Eddy Current (HFEC) inspection of the bear strap and an external detailed
and HFEC inspection of the skin assembly for any crack. If any crack is found in the skin assembly or bear strap,
contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, do the repeat
inspections at the intervals given in Paragraph 1.E., Compliance.
Group 3:
At the lower corners of the forward entry doorway, do an internal detailed inspection of the skin assembly and
bear strap, an internal HFEC inspection of the bear strap and an external detailed and HFEC inspection of the
skin assembly for any crack. If any crack is found in the skin assembly or bear strap at the lower aft corner,
install a repair. If any crack is found in the skin assembly or bear strap at the lower forward corner, contact
Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, do the repeat
inspections at the intervals given in Paragraph 1.E., Compliance.
EFFECTIVITY
737-200/-200C/-300/-400/-500 airplanes that do not have an airstair door cutout. Refer to Paragraph 1.A.1.,
Airplanes, for the list of affected airplane(s).
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COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
FAA AD 2008-09-13 is related to this service bulletin.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures
given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
5.005.00Group 2
5.005.00Group 3
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 737-53A1329
ALERT  ALERT
FORWARD
— ENTRY
DOORWAY
SCUFF PLATE
' SKIN
DO AN INTERNAL DETAILED INSPECT  ON OF THE SKIN
ASSEMBLY AND BEAR STRAP, AN INTERNAL HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECT  TION OF THE BEAR STRAP AND
AN EXTERNAL DETAILED AND HFEC INSPECTION OF THE SKIN
ASSEMBLY FOR ANY CRACK. IF ANY CRACK IS FOUND IN THE
SKIN ASSEMBLY OR BEAR STRAP, DO THE REPAIR. IF NO
CRACKING IS FOUND, DO REPEAT INSPECTIONS.  2195345
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### Page 9

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1329
Original Issue: June 04, 2013
ATA System: 5330
SUBJECT: FUSELAGE - Skin - Forward Entry Doorway - Lower Corners - Inspection and Repair
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
737-200C airplanes, line numbers 72 thru 286 that do not have an
airstair door cutout.
-1
737-200/-200C airplanes, line numbers 294 thru 1453 that do not
have an airstair door cutout.
-2
737-300/-400/-500 airplanes, line numbers 1001 thru 3132 that do
not have an airstair door cutout.
-3
Airplane Models:
737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
3PJ301 - PJ302
3PJ551 - PJ561
3PJ601 - PJ615
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GroupVariable Number
3PJ811
2PK041 - PK046
2PK048 - PK050
2PK052 - PK053
2PK431 - PK433
2PK911 - PK938
2PK971 - PK974
2PL101 - PL113
2PL736 - PL747
2PL758
2PN401 - PN420
3PP001 - PP054
3PP102 - PP169
3PP181 - PP199
3PP231 - PP243
3PP281 - PP286
3PP301 - PP305
3PP401 - PP440
3PP471 - PP475
3PP631 - PP634
3PP671 - PP699
3PP701 - PP733
3PP771 - PP779
3PP861 - PP877
3PP961 - PP967
3PP981 - PP991
3PQ001 - PQ016
3PQ026 - PQ041
3PQ051 - PQ092
3PQ101 - PQ199
3PQ201 - PQ202
3PQ231 - PQ237
3PQ292 - PQ297
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GroupVariable Number
3PQ299
3PQ301 - PQ307
3PQ331 - PQ332
3PQ341 - PQ348
3PQ431 - PQ438
3PQ451
3PQ454
3PQ471
3PQ479 - PQ481
3PQ486 - PQ487
3PQ491 - PQ493
3PQ771 - PQ772
3PQ791 - PQ793
3PQ801 - PQ805
3PQ931 - PQ935
3PR031 - PR034
3PR041 - PR045
3PR061 - PR072
3PR077 - PR080
3PR181
3PS643 - PS644
3PS666 - PS669
3PS691 - PS692
3PS701 - PS706
3PS751 - PS799
3PS901 - PS941
3PT001 - PT015
3PT021 - PT031
3PT101 - PT105
3PT186 - PT188
3PT301 - PT309
3PT331 - PT360
3PT381 - PT399
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GroupVariable Number
3PT401 - PT438
3PT561 - PT565
3PT581 - PT586
3PT611 - PT621
3PT641 - PT644
3PT651 - PT656
3PT681 - PT685
3PT701 - PT703
3PT716 - PT717
3PT801 - PT834
3PT851 - PT854
3PT901 - PT930
3PT971 - PT973
3PT981 - PT985
3PU001 - PU025
3PV001 - PV055
3PV201 - PV209
3PV226 - PV229
3PV231 - PV237
3PV271 - PV272
3PV281 - PV287
3PV351
3PW062 - PW068
3PW201 - PW252
3PW401 - PW408
3PW411 - PW418
3PW421 - PW424
3PW431 - PW435
3PW441 - PW450
3PW461 - PW467
3PW511 - PW522
3PW524 - PW550
3PW561 - PW564
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GroupVariable Number
3PW571 - PW576
3PW611 - PW622
3PW631 - PW637
3PW681 - PW683
3PW711 - PW717
3PW761
3PW771
1PX701
1PY001 - PY008
1PY021
2PY022
2PY036 - PY037
2PY046 - PY048
2PY056 - PY057
2PY111 - PY113
2PY131 - PY135
2PY141 - PY143
2PY151 - PY154
2PY156 - PY157
2PY162
2PY166
2PY191
2PY201
2PY241 - PY244
2PY270 - PY275
1PY301 - PY304
2PY401
2PY409 - PY410
2PY421 - PY422
2PY451
2PY461 - PY463
2PY591 - PY595
2PY671 - PY672
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GroupVariable Number
2PY721
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to inspect the lower corners of the forward entry doorway for
cracking on airplanes that do not have an airstair door cutout. If the work in this service bulletin is not
done, continued crack progression can result in possible rapid decompression.
Boeing has received five reports of cracking in the skin at the lower aft corner of the forward entry
doorway on airplanes that do not have an airstair door cutout. The cracks ranged from 0.25 to 2.0
inches in length. The airplanes had accumulated between 34,813 and 73,083 total flight cycles. Cracks
in the lower corners of the forward entry doorway are caused by fatigue loads in the skin and bear strap
which are magnified by local stress concentrations due to the door cutout and edge margin effects at
fastener locations near the corner radius. Additionally, cracks can be initiated from impact damage due
to high usage rate of the forward entry door.
Accomplishment of the work in this service bulletin will make sure that cracking at the lower corners of
the forward entry doorway on airplanes that do not have an airstair door cutout is detected and a repair
installed. Boeing Service Bulletin 737-53-1083 gives instructions for the inspection, modification and
repair of the lower corners of the forward entry doorway on airplanes that have an airstair door cutout.
Boeing Service Related Problem (SRP) 737-SRP-53-0381 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-11003 is related to this service bulletin.
D. Description
Group 1:
Contact Boeing to get instructions for the inspections and repairs for this service bulletin 737-53A1329
Original Issue and do the work instructed by Boeing.
Group 2-3:
Remove the scuff plates at the lower corners of the forward entry doorway.
Group 2:
At the lower corners of the forward entry doorway, do an internal detailed inspection of the skin assembly
and bear strap, an internal High Frequency Eddy Current (HFEC) inspection of the bear strap and an
external detailed and HFEC inspection of the skin assembly for any crack. If any crack is found in the
skin assembly or bear strap, contact Boeing for repair instructions and do the work instructed by Boeing.
If no cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E., Compliance.
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### Page 15

Group 3:
At the lower corners of the forward entry doorway, do an internal detailed inspection of the skin assembly
and bear strap, an internal HFEC inspection of the bear strap and an external detailed and HFEC
inspection of the skin assembly for any crack. If any crack is found in the skin assembly or bear strap
at the lower aft corner, install a repair. If any crack is found in the skin assembly or bear strap at the
lower forward corner, contact Boeing for repair instructions and do the work instructed by Boeing. If no
cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
1-5737-200C
Group 2:
Affected Maintenance Zones
ZoneModel
1-5737-200, 737-200C
Group 3:
Affected Maintenance Zones
ZoneModel
105737-300, 737-400, 737-500
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related
to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in
this service bulletin mandatory.
FAA AD 2008-09-13 is related to this service bulletin.
Group 1:
Contact Boeing to get instructions for the inspections and repairs for this service bulletin 737-53A1329
Original Issue and do the work instructed by Boeing within 120 days after the original issue date of this
service bulletin.
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### Page 16

Group 2:
Table 1: Forward Entry Doorway - Lower Corners Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,500 flight cycles.Within 4,500
flight cycles af-
ter the original
issue date of
this service
bulletin.
Before 27,000
total flight cy-
cles.
At the forward entry doorway lower
aft corner, do an internal detailed
inspection of the skin assembly
and bear strap, an internal High
Frequency Eddy Current (HFEC)
inspection of the bear strap and
an external detailed and HFEC in-
spection of the skin assembly for
any crack in accordance with
Paragraph 3.B., Work Instructions,
PART 2, step 1.a.
All airplanes.
4,500 flight cycles.Within 4,500
flight cycles af-
ter the original
issue date of
this service
bulletin.
Before 27,000
total flight cy-
cles.
At the forward entry doorway lower
forward corner, do an internal de-
tailed inspection of the skin assem-
bly and bear strap, an internal
HFEC inspection of the bear strap
and an external detailed and
HFEC inspection of the skin assem-
bly for any crack in accordance
with Paragraph 3.B., Work Instruc-
tions, PART 2, step 1.b.
-Before further flight.Contact Boeing for repair instruc-
tions and do the work instructed
by Boeing.
If any crack is found
in the skin assembly
or bear strap.
Group 3:
Table 2: Forward Entry Doorway - Lower Corners Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,500 flight cycles.Within 4,500
flight cycles af-
ter the original
issue date of
this service
bulletin.
Before 27,000
total flight cy-
cles.
At the forward entry doorway lower
aft corner, do an internal detailed
inspection of the skin assembly
and bear strap, an internal HFEC
inspection of the bear strap and
an external detailed and HFEC in-
spection of the skin assembly for
any crack in accordance with
Paragraph 3.B., Work Instructions,
PART 2, step 2.a.
All airplanes.
(a)
-Before further flight.Install the repair in accordance
with Paragraph 3.B., Work Instruc-
tions, PART 2, step 2.a.(1).
If any crack is found
in the skin assembly
or bear strap at the
lower aft corner. (a)
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### Page 17

Group 3:
Table 2: Forward Entry Doorway - Lower Corners Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,500 flight cycles.Within 4,500
flight cycles af-
ter the original
issue date of
this service
bulletin.
Before 27,000
total flight cy-
cles.
At the forward entry doorway lower
forward corner, do an internal de-
tailed inspection of the skin assem-
bly and bear strap, an internal
HFEC inspection of the bear strap
and an external detailed and
HFEC inspection of the skin assem-
bly for any crack in accordance
with Paragraph 3.B., Work Instruc-
tions, PART 2, step 2.b.
All airplanes.
-Before further flight.Contact Boeing for repair instruc-
tions and do the work instructed
by Boeing.
If any crack is found
in the skin assembly
or bear strap at the
lower forward cor-
ner.
(a) Accomplishment of the repair in accordance with this service bulletin terminates the repeat inspections
required by this service bulletin in the area common to the repair. Supplemental inspections are provided
in the applicable Structural Repair Manual (SRM).
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
For 737-300/-400/-500 airplanes as required by paragraph (i) of AD 2008-09-13, the repair identified
in this service bulletin has been evaluated to determine if it affects the Boeing Supplemental Structural
Inspection Document D6-82669, Revision New Inspections as required by paragraph (g) and (h) of the
AD. The SRM repair identified in Paragraph 3.B, Work Instructions, Part 2, Step 2.a(1) of this bulletin
may affect certain areas of Significant Structural Item F-13A inspections. Supplemental inspections
are provided in the noted SRM repair.
G. Manpower
The table below shows an estimate of the task hours necessary to do this service bulletin for each
airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with
operator task hour data if necessary. The estimate does not include lost time. These are some examples
of lost time:
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### Page 18

 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Open Access
2.002.001FIGURE 1
1.501.501Close Access
5.005.00TOTAL FOR EACH AIRPLANE (a)
(a) No manpower information is given for the repair.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 737-53-1083
b. Boeing Service Letter 737-SL-51-042
c. Boeing Service Related Problem (SRP) 737-SRP-53-0381
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2008-09-13
e. Service Bulletin Index D6-19567
f. 737 Fleet Team Digest (FTD) 53-11003
g. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00
h. 737-100/200 Aircraft Maintenance Manual (AMM) 52-11-00
i. 737-300/400/500 Aircraft Maintenance Manual (AMM) 52-11-00, 53-13-01
j. 737-300 Structural Repair Manual (SRM) 53-10-01
k. 737-400 Structural Repair Manual (SRM) 53-10-01
l. 737-500 Structural Repair Manual (SRM) 53-10-01
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### Page 19

2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
SKIN AND STRINGER INSTALLATION - SECTION 4165-45800
SKIN AND STRINGER INSTALLATION - FORWARD ENTRY
AND GALLEY DOORS
65C34778
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
53-10737-300 Structural Repair Manual
53-10737-400 Structural Repair Manual
53-10737-500 Structural Repair Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 21

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes, inspection and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
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. 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.
8. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
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### Page 24

9. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
B. WORK INSTRUCTIONS
Group 1:
1. Contact Boeing to get instructions for the inspections and repairs for this service bulletin
737-53A1329 Original Issue and do the work instructed by Boeing.
Group 2-3:
PART 1 - ACCESS
1. Open the forward entry door. Refer to 737-300/400/500 AMM 52-11-00 or 737-100/200 AMM
52-11-00 as an accepted procedure.
2. Remove the forward entry doorway scuff plates and their support structures at the forward entry
doorway. Refer to 737-300/400/500 AMM 53-13-01 as an accepted procedure.
Group 2-3:
PART 2 - INSPECTION
1. Group 2:
a. At the forward entry doorway lower aft corner, do an internal detailed inspection of the skin
assembly and bear strap, an internal High Frequency Eddy Current (HFEC) inspection of the
bear strap and an external detailed and HFEC inspection of the skin assembly for any crack
in accordance with FIGURE 1.
(1) If any crack is found in the skin assembly or bear strap, contact Boeing for repair
instructions and do the work instructed by Boeing.
(2) If no cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E.,
Compliance.
b. At the forward entry doorway lower forward corner, do an internal detailed inspection of the
skin assembly and bear strap, an internal HFEC inspection of the bear strap and an external
detailed and HFEC inspection of the skin assembly for any crack in accordance with FIGURE
1.
(1) If any crack is found in the skin assembly or bear strap, contact Boeing for repair
instructions and do the work instructed by Boeing.
(2) If no cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E.,
Compliance.
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### Page 25

2. Group 3:
a. At the forward entry doorway lower aft corner, do an internal detailed inspection of the skin
assembly and bear strap, an internal HFEC inspection of the bear strap and an external
detailed and HFEC inspection of the skin assembly for any crack in accordance with FIGURE
1.
(1) If any crack is found in the skin assembly or bear strap, do the following:
(a) Install a repair in accordance with applicable 737-300 SRM 53-10-01 Repair 12 or
737-400 SRM 53-10-01 Repair 12 or 737-500 SRM 53-10-01 Repair 12.
NOTE: Installation of the SRM repair terminates the repeat inspection requirements
of this Service Bulletin for the area common to the repair. Supplemental
inspections are provided in the applicable Structural Repair Manual (SRM).
(2) If no cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E.,
Compliance.
b. At the forward entry doorway lower forward corner, do an internal detailed inspection of the
skin assembly and bear strap, an internal HFEC inspection of the bear strap and an external
detailed and HFEC inspection of the skin assembly for any crack in accordance with FIGURE
1.
(1) If any crack is found in the skin assembly or bear strap, contact Boeing for repair
instructions and do the work instructed by Boeing.
(2) If no cracking is found, do the repeat inspections at the intervals given in Paragraph 1.E.,
Compliance.
Group 2-3:
PART 3 - CLOSE ACCESS
1. Install the forward entry doorway scuff plates and their support structures at the forward entry
doorway. Refer to 737-300/400/500 AMM 53-13-01 as an accepted procedure.
2. Close the forward entry door. Refer to 737-300/400/500 AMM 52-11-00 or 737-100/200 AMM
52-11-00 as an accepted procedure.
3. Put the airplane back to a serviceable condition.
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### Page 26 (OCR)

BOEING SERVICE BULLETIN 737-53A1329
ALERT  ALERT
This Figure applies only to: Group 2-3.
FORWARD
ENTRY
DOORWAY
SKIN
2195349
FIGURE 1: FUSELAGE - FORWARD ENTRY DOORWAY - SKIN ASSEMBLY AND BEAR STRAP AT THE
LOWER CORNERS - INSPECTION
(SHEET 1 OF 4)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 737-53A1329
ALERT  ALERT
STA
348.2
CRACKS
(TYPICAL)
STA  328  FWD  STA  351.2  STA
HFEC
INSPECTION ZONE
_I INSPECTION ZONE  • DETAILED
2195353
FIGURE 1: FUSELAGE - FORWARD ENTRY DOORWAY - SKIN ASSEMBLY AND BEAR STRAP AT THE
LOWER CORNERS - INSPECTION
(SHEET 2 OF 4)
Original Issue: June 04, 2013
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 737-53A1329
ALERT  ALERT
mE 00 00  CRACKS
STA  STA  STA
303.9  312  328
HFEC
INSPECTION ZONE
DETAILED
_I INSPECTION ZONE
2195358
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
FIGURE 1: FUSELAGE - FORWARD ENTRY DOORWAY - SKIN ASSEMBLY AND BEAR STRAP AT THE
LOWER CORNERS - INSPECTION
(SHEET 3 OF 4)
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### Page 29

More DataQtyIdentificationNameTaskStep
(a)--Bear StrapInspect1
(b)--Skin AssemblyInspect2
(c)--Skin AssemblyInspect3
(d)--Bear Strap and Skin
Assembly
Inspect4
(a) Do an internal High Frequency Eddy Current (HFEC) inspection of the bear strap for any crack around
the fasteners shown in accordance with 737 NDT Manual Part 6, 51-00-00, Figure 4 or Figure 23.
(b) Do an external detailed inspection of the skin assembly for any crack.
(c) Do an external HFEC inspection of the skin assembly for any crack around the fasteners shown in accor-
dance with 737 NDT Manual Part 6, 51-00-00, Figure 4 or Figure 23.
(d) Do an internal detailed inspection of all the visible surfaces of the bear strap and skin assembly for any
crack.
FIGURE 1: FUSELAGE - FORWARD ENTRY DOORWAY - SKIN ASSEMBLY AND BEAR STRAP AT THE
LOWER CORNERS - INSPECTION
(SHEET 4 OF 4)
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