# Boeing Alert Service Bulletin 737-53A1339: No revision named

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- Document: [Boeing Alert Service Bulletin 737-53A1339](https://openairdocs.org/service-documents/boeing/737-53a1339.md)
- Title as filed: U.S. DOT/FAA - SB-737-53A1339-00
- Pages: 146
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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1339
Original Issue: August 12, 2014
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Upper Frame To Side Frame Splice at STA
360 Between Stringer 13 and Stringer 14 - Inspection, Repair or Optional Preventative
Modification
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 © 2014 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Unpublished Work.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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connection with this document unless provided in writing by Boeing.
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4.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 5
B. Concurrent Requirements ...................................... 1 5
C. Reason ................................................ 1 5
D. Description .............................................. 1 5
E. Compliance .............................................. 1 6
F. Approval ............................................... 1 9
G. Manpower .............................................. 1 9
H. Weight and Balance Changes .................................... 2 0
I. Electrical Load Data ......................................... 2 1
J. References .............................................. 2 1
1. Existing Data: ......................................... 2 1
2. Data Supplied with this Service Bulletin: ........................... 2 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 1
K. Publications Affected ........................................ 2 2
L. Interchangeability and Intermixability of Parts ........................... 2 2
M. Software Accomplishment Summary ................................ 2 2
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary for Each Airplane ................................. 2 3
1. Kits/Parts: ........................................... 2 3
2. Parts and Materials Supplied by the Operator: ........................ 2 3
3. Parts Modified and Reidentified: ............................... 2 7
4. Parts Removed and Not Replaced: .............................. 2 7
D. Parts Necessary to Change Spares ................................. 2 7
E. Special Tooling - Price and Availability ............................... 2 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9
A. GENERAL INFORMATION ..................................... 2 9
B. WORK INSTRUCTIONS ....................................... 3 0
FIGURE 1: LEFT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE ............ 3 6
FIGURE 2: RIGHT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE ........... 3 9
FIGURE 3: LEFT SIDE - CUT FAIL SAFE CHORD ............................ 4 2
FIGURE 4: RIGHT SIDE - CUT FAIL SAFE CHORD ........................... 4 6
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME ................... 5 0
FIGURE 6: RIGHT SIDE - REMOVAL SECTION OF UPPER FRAME .................. 5 6
FIGURE 7: LEFT SIDE - INSPECT FRAME ................................ 6 0
FIGURE 8: RIGHT SIDE - INSPECT FRAME ............................... 6 2
FIGURE 9: LEFT SIDE - MAKE REPLACEMENT SECTION - UPPER FRAME, INTERCOSTAL CLIP AND
REPAIR ANGLES ....................................... 6 4
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FIGURE 10: RIGHT SIDE - MAKE REPLACEMENT SECTION - UPPER FRAME AND REPAIR ANGLES
.................................................. 6 9
FIGURE 11: LEFT SIDE - LOCATE REPLACEMENT FRAME SECTION AND REPAIR ANGLES . . . 73
FIGURE 12: RIGHT SIDE - LOCATE REPLACEMENT FRAME SECTION AND REPAIR ANGLES . . 80
FIGURE 13: LEFT SIDE - INSTALLATION OF REPLACEMENT FRAME SECTION AND REPAIR ANGLES
.................................................. 8 6
FIGURE 14: RIGHT SIDE - INSTALLATION OF REPLACEMENT FRAME SECTION AND REPAIR ANGLES
.................................................. 9 3
FIGURE 15: LEFT SIDE - INSPECT FRAME ................................ 9 8
FIGURE 16: RIGHT SIDE - INSPECT FRAME .............................. 1 0 1
FIGURE 17: LEFT SIDE - MAKE MODIFICATION ANGLE AND INTERCOSTAL CLIP ......... 1 0 3
FIGURE 18: RIGHT SIDE - MAKE MODIFICATION ANGLE ....................... 1 0 6
FIGURE 19: LEFT SIDE - LOCATE MODIFICATION ANGLE AND INTERCOSTAL CLIP ....... 1 0 8
FIGURE 20: RIGHT SIDE - LOCATE MODIFICATION ANGLE ..................... 1 1 3
FIGURE 21: LEFT SIDE - INSTALLATION OF UPPER FRAME TO SIDE FRAME SPLICE, MODIFICATION
ANGLE ............................................ 1 1 6
FIGURE 22: RIGHT SIDE - INSTALLATION OF UPPER FRAME TO SIDE FRAME SPLICE, MODIFICATION
ANGLE ............................................ 1 2 5
FIGURE 23: LEFT SIDE - POST-REPAIR INSPECT UPPER FRAME TO SIDE FRAME SPLICE . . . 129
FIGURE 24: RIGHT SIDE - POST-REPAIR INSPECT UPPER FRAME TO SIDE FRAME SPLICE . . 133
FIGURE 25: LEFT SIDE - POST-PREVENTATIVE MODIFICATION INSPECT UPPER FRAME TO SIDE
FRAME SPLICE ........................................ 1 3 7
FIGURE 26: RIGHT SIDE - POST-PREVENTATIVE MODIFICATION INSPECT UPPER FRAME TO SIDE
FRAME SPLICE ........................................ 1 4 3
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1339Original Issue: August 12, 2014
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Upper Frame To Side Frame Splice at STA
360 Between Stringer 13 and Stringer 14 - Inspection, Repair or Optional Preventative
Modification
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 do an inspection for cracks on the upper frame, originating from the
upper end fastener hole of the frame splice common to the fail safe chord at Station 360, left and right side,
between stringer S-13 and stringer S-14. This service bulletin also gives instructions to do a frame repair or an
optional preventative modification. Undetected cracks in the left or right side upper frame can grow in size and
result in a severed frame. A severed frame combined with fuselage skin chem mill cracks, window corner cutout
skin cracks or skin lap joint cracks can affect the structural integrity of the airplane and lead to an uncontrolled
decompression event. Accomplishment of the inspections in accordance with this service bulletin will make sure
that cracks in the frames are found. Repair of any cracks found will make sure the frame maintains structural
integrity. Installation of the optional preventative modification will prevent cracks from occurring in the frame
splice joints. If not corrected, frame cracks at Station 360 could adversely affect the structural integrity of the
airplane.
Certain line numbers of 737 airplanes have fuselage frame configurations (Station 360 to Station 907 inclusive)
that are prone to cracking at the same location on the upper frame, between stringer S-13 and stringer S-14.
The fuselage frame splice cracks were addressed in Boeing Service Bulletin 737-53A1261 for line numbers 1
to 1919.
Three operators reported cracks at frame Station 360 between stringer S-13 and stringer S-14 on airplanes with
37,826 to 42,986 flight cycles. The reported cracks ranged from 0.35 inches to 1.5 inches in length. This service
bulletin is being released to address fuselage frames at Station 360, for line numbers 1920 to 2565.
Boeing Fleet Team Digest 737 FTD 53-02001 is related to this service bulletin.
Boeing Multi Operator Message (MOM) MOM-12-0937-01B is related to this service bulletin.
Boeing Service Related Problem 737-SRP-53-0387 is related to this service bulletin.
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### Page 6

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
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
On the left and right side fuselage frames, between stringer S-13 and stringer S-14, at Station 360, do a Medium
Frequency Eddy Current (MFEC) inspection or accomplish the optional preventative modification in accordance
with this service bulletin. If any crack is found on the upper frame, originating from the upper end fastener hole
of the frame splice common to the fail safe chord during the MFEC inspection or optional preventative modification,
do the repair in accordance with this service bulletin. If no crack is found, continue with the installation of the
optional preventative modification if you choose to do the optional preventative modification or continue to do
the repeat inspections. The optional preventative modification may be accomplished at any time.
EFFECTIVITY
737-300/400/500 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
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.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection, repair or optional preventative modification given
in this service bulletin.
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MANPOWER
Refer to Paragraph 1.G., Manpower.
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 737-53A1339
ALERT  ALERT
OPPEF  STA
FRAME  360
STA
360
S-13L_
CRACK
(TYPICAL)
S-14L
DO A MEDIUM FREQUENCY EDDY
CURRENT INSPECTION FOR ANY CRACK
ON THE UPPER FRAME AT STATION 360
BETWEEN STRINGER S-13L AND STRINGER
S-14L, ORIGINATING FROM THE UPPER
END FASTENER HOLE OF THE FRAME
SPLICE, COMMON TO THE SIDE FRAME
AND FAIL SAFE CHORD
FAIL SAFE
CHORI
SIDE FRAME
NOTE: DOOR SURROUND
STRUCTURE NOT  2260272
SHOWN FOR CLARITY
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### Page 9 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
STA  UPPER
360  FRAME
- S-13R
CRACK
(TYPICAL)
S-14R
DO A MEDIUM FREQUENCY EDDY
CURRENT INSPECTION FOR ANY CRACK
ON THE UPPER FRAME AT STATION 360,
BETWEEN STRINGER S-13R AND
STRINGER S-14R, ORIGINATING FROM THE
UPPER END FASTENER HOLE OF THE
FRAME SPLICE, COMMON TO THE SIDE
FRAME AND FAIL SAFE CHORD
SIDE FRAME
• FAIL SAFE CHORD  2267939
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BLANK PAGE

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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1339
Original Issue: August 12, 2014
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Upper Frame To Side Frame Splice at STA
360 Between Stringer 13 and Stringer 14 - Inspection, Repair or Optional Preventative
Modification
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 airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP
Line Number 1920 to 2565-1
Airplane Models:
737-300, 737-400, 737-500
GroupVariable Number
1PJ301 - PJ302
1PJ551 - PJ552
1PM393 - PM399
1PM401 - PM417
1PM541 - PM547
1PM551 - PM564
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GroupVariable Number
1PP149 - PP160
1PP511 - PP517
1PP874 - PP875
1PP925 - PP930
1PP988 - PP990
1PQ074 - PQ085
1PQ198 - PQ199
1PQ201 - PQ202
1PQ230
1PQ237
1PQ256 - PQ267
1PQ287 - PQ296
1PQ306 - PQ307
1PQ341 - PQ344
1PQ361 - PQ369
1PQ401 - PQ408
1PQ411 - PQ413
1PQ421
1PQ471 - PQ473
1PQ479 - PQ481
1PQ486 - PQ487
1PQ491 - PQ493
1PQ771
1PQ791 - PQ793
1PQ801 - PQ805
1PQ931 - PQ932
1PS601 - PS616
1PS631
1PS636 - PS638
1PS643 - PS644
1PS651 - PS657
1PS669
1PS691 - PS692
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GroupVariable Number
1PS701 - PS703
1PS751 - PS762
1PT001 - PT011
1PT024 - PT028
1PT041 - PT064
1PT102 - PT105
1PT124 - PT125
1PT147 - PT148
1PT161 - PT170
1PT183 - PT187
1PT214 - PT220
1PT301 - PT306
1PT331 - PT360
1PT381 - PT399
1PT401 - PT438
1PT501 - PT512
1PT561 - PT565
1PT581 - PT584
1PT611 - PT621
1PT641 - PT642
1PT651 - PT655
1PT671 - PT672
1PT701 - PT703
1PU008 - PU025
1PV041 - PV055
1PV201 - PV203
1PV231 - PV237
1PV271 - PV272
1PV281 - PV283
1PW037 - PW050
1PW052 - PW054
1PW064 - PW068
1PW072
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GroupVariable Number
1PW094
1PW101 - PW102
1PW106
1PW118 - PW120
1PW156 - PW157
1PW162 - PW167
1PW201 - PW245
1PW261
1PW265 - PW268
1PW278
1PW281 - PW284
1PW293
1PW296
1PW301 - PW327
1PW461 - PW467
1PW504
1PW519 - PW520
1PW526
1PW536 - PW546
1PW556 - PW557
1PW564
1PW574 - PW576
1PW595 - PW596
1PW616 - PW620
1PW633 - PW634
1PW662
1PW681 - PW683
1PW701 - PW702
1PW711 - PW717
1PW741 - PW742
1PW761
1PW771
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### Page 15

2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to do an inspection for cracks on the upper frame, originating
from the upper end fastener hole of the frame splice common to the fail safe chord at Station 360, left
and right side, between stringer S-13 and stringer S-14. This service bulletin also gives instructions to
do a frame repair or an optional preventative modification. Undetected cracks in the left or right side
upper frame can grow in size and result in a severed frame. A severed frame combined with fuselage
skin chem mill cracks, window corner cutout skin cracks or skin lap joint cracks can affect the structural
integrity of the airplane and lead to an uncontrolled decompression event. Accomplishment of the
inspections in accordance with this service bulletin will make sure that cracks in the frames are found.
Repair of any cracks found will make sure the frame maintains structural integrity. Installation of the
optional preventative modification will prevent cracks from occurring in the frame splice joints. If not
corrected, frame cracks at Station 360 could adversely affect the structural integrity of the airplane.
Certain line numbers of 737 airplanes have fuselage frame configurations (Station 360 to Station 907
inclusive) that are prone to cracking at the same location on the upper frame, between stringer S-13
and stringer S-14. The fuselage frame splice cracks were addressed in Boeing Service Bulletin
737-53A1261 for line numbers 1 to 1919.
Three operators reported cracks at frame Station 360 between stringer S-13 and stringer S-14 on
airplanes with 37,826 to 42,986 flight cycles. The reported cracks ranged from 0.35 inches to 1.5 inches
in length. This service bulletin is being released to address fuselage frames at Station 360, for line
numbers 1920 to 2565.
Boeing Fleet Team Digest 737 FTD 53-02001 is related to this service bulletin.
Boeing Multi Operator Message (MOM) MOM-12-0937-01B is related to this service bulletin.
Boeing Service Related Problem 737-SRP-53-0387 is related to this service bulletin.
D. Description
On the left and right side fuselage frames, between stringer S-13 and stringer S-14, at Station 360, do
a Medium Frequency Eddy Current (MFEC) inspection or accomplish the optional preventative
modification in accordance with this service bulletin. If any crack is found on the upper frame, originating
from the upper end fastener hole of the frame splice common to the fail safe chord during the MFEC
inspection or optional preventative modification, do the repair in accordance with this service bulletin.
If no crack is found, continue with the installation of the optional preventative modification if you choose
to do the optional preventative modification or continue to do the repeat inspections. The optional
preventative modification may be accomplished at any time.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Affected Maintenance Zones
ZoneModel
107737-300, 737-400, 737-500
E. 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.
NOTE: The damage tolerance inspections specified in Table 4 and Table 5 below may be used in
support of compliance with 14 Code of Federal Regulations, Section 121.1109 or 129.109.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Table 1: Inspect Upper Frame to Side Frame Splice at STA 360 Between Stringer 13 and Stringer 14,
Left and Right Side for Cracks.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 5,000
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 30,000
total flight cy-
cles.
Do PART 2: INSPEC-
TION for cracks.
(a) (c)
Airplanes with less than
37,501 total flight cycles on
the original issue date of
this service bulletin.
-Within 2,500 flight cycles after the
original issue date of this service
bulletin.
Do PART 2: INSPEC-
TION for cracks.
(a) (c)
Airplanes with more than
37,500 total flight cycles on
the original issue date of
this service bulletin.
-Before further flight.Do PART 3: REPAIR.CONDITION 1: Any crack
found during PART 2 IN-
SPECTION.
(b)
6,000 flight cycles.-Repeat PART 2: INSPEC-
TION for cracks.
CONDITION 2: No crack
found during PART 2 IN-
SPECTION.
(c)
(a) It is optional to accomplish the preventative modification in accordance with PART 4: PREVENTATIVE
MODIFICATION. Accomplishment of optional PART 4: PREVENTATIVE MODIFICATION is terminating
action for PART 2: INSPECTION at the modification location only. PART 7: POST-PREVENTATIVE
MODIFICATION INSPECTION is provided in Table 5.
(b) Accomplishment of the repair in accordance with PART 3: REPAIR is terminating action for the repeat
PART 2: INSPECTION at the repaired location only. PART 6: POST-REPAIR INSPECTION is provided
in Table 4.
(c) If any Boeing ODA approved repair via FAA Form 8100-9 was installed to eliminate cracking that was
previously found, initial and repeat inspections in accordance with PART 2: INSPECTION are not required
at the repaired location only.
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### Page 17

Table 2: Actions for the Conditions Found During the HFEC Inspection Specified in PART 3: REPAIR,
Left and Right Side
Repeat IntervalCompliance TimeActionCondition
-Before further flight.Contact Boeing to get in-
structions for the repair
and do the work instruct-
ed by Boeing.
CONDITION 3: Any crack
found during PART 3: RE-
PAIR.
-Before further flight.Continue PART 3: RE-
PAIR.
CONDITION 4: No crack
found during PART 3: RE-
PAIR.
Table 3: Actions for the Conditions Found During the HFEC Inspection Specified in Optional PART 4:
PREVENTATIVE MODIFICATION, Left and Right Side
Repeat IntervalCompliance TimeActionCondition
-Before further flight.Do PART 3: REPAIR.CONDITION 5: Any crack
found in the upper frame
originating from the upper
end fastener location of the
frame splice, common to
the fail safe chord during
PART 4: PREVENTATIVE
MODIFICATION
(a)
-Before further flight.Contact Boeing to get in-
structions for the repair
and do the work instruct-
ed by Boeing.
CONDITION 6: Any other
crack found during PART
4: PREVENTATIVE MODI-
FICATION.
-Before further flight.Continue PART 4: PRE-
VENTATIVE MODIFICA-
TION.
CONDITION 7: No crack
found during PART 4:
PREVENTATIVE MODIFI-
CATION (b)
(a) Accomplishment of the repair in accordance with PART 3: REPAIR is terminating action for the repeat
PART 2: INSPECTION at the repaired location only. PART 6: POST-REPAIR INSPECTION is provided
in Table 4.
(b) Accomplishment of optional PART 4: PREVENTATIVE MODIFICATION is terminating action for PART
2: INSPECTION at the modification location only. PART 7: POST-PREVENTATIVE MODIFICATION
INSPECTION is provided in Table 5.
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### Page 18

Table 4: Post-Repair Inspection of the Upper Frame to Side Frame Splice at STA 360 Between Stringer
13 and Stringer 14, Left and Right Side for Cracks
Repeat Interval (Not to
Exceed)
Compliance TimeActionCondition
-Before 75,000 flight cycles
after repair.
Do PART 6: POST-RE-
PAIR INSPECTION for
cracks.
Airplanes that have accom-
plished the repair in accor-
dance with PART 3: RE-
PAIR of this service bul-
letin.
-Before further flight.Contact Boeing to get in-
structions for the repair
and do the work instruct-
ed by Boeing
CONDITION 8: Any crack
found during PART 6:
POST-REPAIR INSPEC-
TION.
6,000 flight cycles.-Repeat PART 6: POST-
REPAIR INSPECTION
for cracks.
CONDITION 9: No crack
found during PART 6:
POST-REPAIR INSPEC-
TION.
Table 5: Post-Preventative Modification Inspection of the Upper Frame to Side Frame Splice at STA 360
Between Stringer 13 and Stringer 14, Left and Right Side for Cracks
Repeat Interval (Not to
Exceed)
Compliance TimeActionCondition
-Before 75,000 flight cycles
after modification.
Do PART 7: POST-PRE-
VENTATIVE MODIFICA-
TION INSPECTION for
cracks.
Airplanes that have accom-
plished the optional preven-
tative modification in accor-
dance with PART 4: PRE-
VENTATIVE MODIFICA-
TION of this service bul-
letin.
-Before further flight.Contact Boeing to get in-
structions for the repair
and do the work instruct-
ed by Boeing.
CONDITION 10: Any crack
found during PART 7:
POST-PREVENTATIVE
MODIFICATION INSPEC-
TION
6,000 flight cycles.-Repeat PART 7: POST-
PREVENTATIVE MODIFI-
CATION INSPECTION
for cracks.
CONDITION 11: No crack
found during PART 7:
POST-PREVENTATIVE
MODIFICATION INSPEC-
TION
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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.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection/repair/modification
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:
 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
3.006.002Open Access
0.750.751FIGURE 1
0.750.751FIGURE 2
0.750.751FIGURE 3
0.750.751FIGURE 4
4.004.001FIGURE 5
4.004.001FIGURE 6
1.251.251FIGURE 7
1.001.001FIGURE 8
(a) (b)(a) (b)-FIGURE 9
(a) (b)(a) (b)-FIGURE 10
3.757.502FIGURE 11
3.607.502FIGURE 12
2.505.002FIGURE 13
4.004.001FIGURE 14
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Elapsed HoursTask HoursNumber of PersonsTask
3.003.001FIGURE 15
2.002.001FIGURE 16
(a) (b)(a) (b)-FIGURE 17
(a) (b)(a) (b)-FIGURE 18
2.502.501FIGURE 19
2.502.501FIGURE 20
3.003.001FIGURE 21
2.002.001FIGURE 22
2.002.001FIGURE 23
2.002.001FIGURE 24
2.002.001FIGURE 25
2.002.001FIGURE 26
3.006.002Close Access
(c)(c)TOTAL FOR EACH AIRPLANE
(a) Time to make parts considered lost time in Boeing estimates.
(b) Refer to Section 1.G., Manpower, lost time statement.
(c) Estimated total time required dependent upon task accomplished.
H. Weight and Balance Changes
PART 3 - REPAIR
Change in Moment (Pound-
Inches)
Change in Weight (Pounds)Airplane
+476+1.70737-300 (Left Side)
+476+1.70737-300 (Right Side)
+354+1.70737-400 (Left Side)
+354+1.70737-400 (Right Side)
+568+1.70737-500 (Left Side)
+568+1.70737-500 (Right Side)
PART 4 - PREVENTATIVE MODIFICATION (Optional)
Change in Moment (Pound-
Inches)
Change in Weight (Pounds)Airplane
+252+0.90737-300 (Left Side)
+252+0.90737-300 (Right Side)
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PART 4 - PREVENTATIVE MODIFICATION (Optional)
Change in Moment (Pound-
Inches)
Change in Weight (Pounds)Airplane
+187+0.90737-400 (Left Side)
+187+0.90737-400 (Right Side)
+301+0.90737-500 (Left Side)
+301+0.90737-500 (Right Side)
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 737-53A1261
b. Boeing Service Letter 737-SL-51-042
c. Boeing Service Related Problem (SRP) 737-SRP-53-0387
d. Service Bulletin Index D6-19567
e. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-41-05, 20-43-03, 20-50-10,
20-50-12, 20-50-19
f. Standard Wiring Practices Manual (SWPM) 20-20-00, 20-20-10
g. 737 Fleet Team Digest (FTD) 53-02001
h. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Procedure 16 , Part 6, 51-00-00
Procedure 4 or Procedure 23, Part 6, 53-30-00, Procedure 7
i. 737-300/400/500 Aircraft Maintenance Manual (AMM) 25-21-31, 25-21-35, 25-21-46, 25-22-00,
25-23-61, 25-24-00, 25-24-31, 25-31-11
j. 737-300/400/500 Structural Repair Manual (SRM) 51-30-01, 51-40-02
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Frame Installation - Body station 36065-58280
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The table above lists the applicable drawing used to prepare this service bulletin. The drawing is
not necessary to make the specified changes, and is not supplied with this service bulletin. The
drawing may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
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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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection, repair or optional preventative modification
given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
The following parts or materials are necessary to do the repair or optional preventative modification
in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References,
can also be necessary. Examine operator part and material supply to make sure all necessary
parts and materials are available.
PART 3 - REPAIR
NotesName / DimensionsQTYPart Number / Specification
Use to make Replacement
Section - Upper Frame, Part
Number 737-53A1339-1R.
0.040 x 12.0 x 11.0 Inches.17075-0 Clad Aluminum Sheet
Or
69-78188-182 (Optional)
(a) (c) (d) (e)
Use to make Inner Repair An-
gle, Part Number 737-53A1339-
2R.
0.045 x 12.0 x 15.0 Inches17075-0 Clad Aluminum Sheet
(a) (d)
Use to make Outer Repair An-
gle, Part Number 737-53A1339-
3R.
0.045 x 12.0 x 15.0 Inches17075-0 Clad Aluminum Sheet
(a) (d)
Use to make Replacement
Section - Upper Frame, Part
Number 737-53A1339-4R.
0.040 x 12.0 x 11.0 Inches.17075-0 Clad Aluminum Sheet
Or
69-78188-182 (Optional)
(b) (c) (d) (e)
Use to make Inner Repair An-
gle, Part Number 737-53A1339-
5R.
0.045 x 12.0 x 15.0 Inches17075-0 Clad Aluminum Sheet
(b) (d)
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PART 3 - REPAIR
NotesName / DimensionsQTYPart Number / Specification
Use to make Outer Repair An-
gle, Part Number 737-53A1339-
6R.
0.045 x 12.0 x 15.0 Inches17075-0 Clad Aluminum Sheet
(b) (d)
Use to make Intercostal Clip,
Part Number 737-53A1339-7.
0.040 x 5.0 x 5.0 Inches17075-0 Clad Aluminum Sheet
(a) (d)
Left Side Only.
(d) (e) (f) (g)Rivet110BACR15BB7AD()C
(e) (f) (g)Rivet3BACR15BB6AD()C
Left Side Only.
(e) (f) (g)Rivet2BACR15BB5AD()C
Left Side Only.
(e) (f) (g)Rivet2BACR15BB4AD()C
Left Side Only.
Only airplanes with the part in-
stalled.
(e) (f) (g)Rivet3BACR15BB5D()C
Left Side Only.
(e) (f) (g)Rivet4BACR15BB6D()C
Left Side Only.
(e) (g)Ground Stud1BACS53B1ES1
Left Side Only.
Only airplanes with the part in-
stalled.
(f)Washer1NAS1149D0316H
Left Side Only.
Only airplanes with the part in-
stalled.
(f) (e)Nut1BACN10YR3CD
Left Side Only.
Only airplanes with the part in-
stalled.
(h) (i)Lining Attachment Stud10P1913-1
Only airplanes with the part in-
stalled.
Or
2045081-1 (Optional)
(j)Primer8ozBMS 10-11, Type 1
(j)Sealant8ozBMS 5-95 Type 1, Class B2
(j)Corrosion Inhibiting Compound8ozBMS 3-23, Type 2, Class 2
Or
BMS 3-35 (Optional)
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PART 3 - REPAIR
NotesName / DimensionsQTYPart Number / Specification
(k)Chemical Conversion Coating8ozType 2, Class A
(l)Adhesive1ozType 89, Type 117, or Type 121
Only airplanes with the part in-
stalled.
(a) Fabricate from 7075-0 Aluminum Alloy, in accordance with FIGURE 9.
(b) Fabricate from 7075-0 Aluminum Alloy, in accordance with FIGURE 10.
(c) Optional part can be used in lieu of making replacement upper frame section.
(d) Quantity indicates excess material which is not required for the repair.
(e) You can get this part from The Boeing Company.
(f) Use the approved fastener substitutions in accordance with SRM Chapter 51.
(g) Fastener grip length to be determined on installation.
(h) You can get Lining Attachment Stud 0P1913-1 from Western Sky Industries a Division Of Atlas Cor-
poration,1280 San Luis Obispo Street, Hayward, California 94544. You can also get 0P1913-1 from
The Boeing Company.
(i) You can get Lining Attachment Stud 2045081-1 from Vickers Electromech, 2600 South Custer, Wichita,
Kansas 67217.
(j) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
(k) Refer to SOPM 20-43-03 for material sources.
(l) Refer to SOPM 20-50-12 for material sources.
PART 4 - PREVENTATIVE MODIFICATION (Optional)
NotesName / DimensionsQTYPart Number / Specification
Use to make Modification Angle,
Part Number 737-53A1339-2M
0.045 x 12.0 x 15.0 Inches17075-0 Clad Aluminum Sheet
(a) (c)
Use to make Intercostal Clip,
Part Number 737-53A1339-7.
0.040 x 5.0 x 5.0 Inches17075-0 Clad Aluminum Sheet
Left Side Only.
(a) (c)
Use to make Modification Angle,
Part Number 737-53A1339-5M.
0.045 x 12.0 x 15.0 Inches17075-0 Clad Aluminum Sheet
(b) (c)
(c) (d) (e) (f)Rivet70BACR15BB7AD()C
(d) (e) (f)Rivet3BACR15BB6AD()C
Left Side Only.
(d) (e) (f)Rivet4BACR15BB6D()C
Left Side Only.
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PART 4 - PREVENTATIVE MODIFICATION (Optional)
NotesName / DimensionsQTYPart Number / Specification
(d) (e) (f)Rivet3BACR15BB5D()C
Left Side Only.
(d) (e) (f)Rivet2BACR15BB4AD()C
Left Side Only.
Only airplanes with the part in-
stalled.
(d) (e) (f)Rivet1BACR15BB10AD()C
Left Side Only.
Only airplanes with the part in-
stalled.
(d) (e) (f)Ground Stud1BACS53B1ES1
Left Side Only.
Only airplanes with the part in-
stalled.
(e)Washer1NAS1149D0316H
Left Side Only.
Only airplanes with the part in-
stalled.
(e) (d)Nut1BACN10YR3CD
Left Side Only.
Only airplanes with the part in-
stalled.
(g) (h)Lining Attachment Stud10P1913-1
Only airplanes with the part in-
stalled.
Or
2045081-1 (Optional)
(i)Primer4ozBMS 10-11, Type 1
(j)Chemical Conversion Coating4ozType 2, Class A
(i)Sealant4ozBMS 5-95 Type 1, Class B2
(i)Corrosion Inhibiting Compound4ozBMS 3-23, Type 2, Class 2
Or
BMS 3-35 (Optional)
(k)Adhesive1ozType 89, Type 117, or Type 121
Only airplanes with the part in-
stalled.
(a) Fabricate from 7075-0 Aluminum Alloy, in accordance with FIGURE 17.
(b) Fabricate from 7075-0 Aluminum Alloy, in accordance with FIGURE 18.
(c) Quantity indicates excess material which is not required for the repair.
(d) You can get this part from The Boeing Company.
(e) Use the approved fastener substitutions in accordance with SRM Chapter 51.
(f) Fastener grip length to be determined on installation.
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PART 4 - PREVENTATIVE MODIFICATION (Optional)
NotesName / DimensionsQTYPart Number / Specification
(g) You can get Lining Attachment Stud 0P1913-1 from Western Sky Industries a Division Of Atlas Cor-
poration,1280 San Luis Obispo Street, Hayward, California 94544. You can also get 0P1913-1 from
The Boeing Company.
(h) You can get Lining Attachment Stud 2045081-1 from Vickers Electromech, 2600 South Custer, Wichita,
Kansas 67217.
(i) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
(j) Refer to SOPM 20-43-03 for material sources.
(k) Refer to SOPM 20-50-12 for material sources.
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 29

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 Values:
— Values for structural fasteners are given in 737 Structural Repair Manual,
Chapter 51.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
6. 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.
7. 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.
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8. 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.
9. 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.
10. 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.
11. 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.
12. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
14. The CONDITIONS, ACTIONS and OPTIONS shown apply to each frame
independently.
15. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
B. WORK INSTRUCTIONS
1. Do PART 1: OPEN ACCESS.
2. Do PART 2: INSPECTION for cracks.
NOTE: It is optional to accomplish the preventative modification in accordance with PART 4:
PREVENTATIVE MODIFICATION. Accomplishment of optional PART 4: PREVENTATIVE
MODIFICATION is terminating action for the PART 2: INSPECTION at the modification
location only.
CONDITION 1: ANY CRACK FOUND DURING PART 2 INSPECTION
a. Do PART 3: REPAIR of the cracked upper frame.
NOTE: Accomplishment of the repair in accordance with PART 3: REPAIR is terminating
action for the repeat PART 2: INSPECTION at the repaired location only.
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CONDITION 2: NO CRACK FOUND DURING PART 2 INSPECTION
a. Repeat PART 2: INSPECTION for cracks at the repeat interval, in accordance with Section
1.E., Compliance.
NOTE: It is optional to accomplish the preventative modification in accordance with PART
4: PREVENTATIVE MODIFICATION. Accomplishment of optional PART 4:
PREVENTATIVE MODIFICATION is terminating action for the PART 2: INSPECTION
at the modification location only.
3. Do PART 5: CLOSE ACCESS.
4. Put the airplane back to a serviceable condition.
PART 1: OPEN ACCESS
1. Remove/keep passenger seats, sidewall panels and sidewall insulation to open access to the left
and right side upper frame to side frame splice at Station 360, above Stringer 14 as follows:
NOTE: It may be necessary to remove/keep partitions and wind screens, panels, passenger
service units, overhead stowage bin, doorway liners, lavatories or galleys.
More DataName
Refer to 737-300/400/500 AMM 25-22-00, as an
accepted procedure.
PASSENGER SEATS - MAINTENANCE
PRACTICES
Refer to 737-300/400/500 AMM 25-21-46, as an
accepted procedure.
SIDEWALL PANELS - REMOVAL/INSTALLA-
TION
Refer to 737-300/400/500 AMM 25-31-11, as an
accepted procedure.
GALLEY NO. 1 - REMOVAL/INSTALLATION
Refer to 737-300/400/500 AMM 25-23-61, as an
accepted procedure.
PASSENGER CABIN PASSENGER SERVICE
UNITS (PSUs) - MAINTENANCE PRACTICES
Refer to 737-300/400/500 AMM 25-24-31, as an
accepted procedure.
OVERHEAD STOWAGE BIN - REMOVAL/IN-
STALLATION
Refer to 737-300/400/500 AMM 25-24-00, as an
accepted procedure.
PARTITIONS AND WIND SCREENS
Refer to 737-300/400/500 AMM 25-21-31 and
737-300/400/500 AMM 25-21-35, as accepted
procedures.
ENTRY DOORWAY LINER AND SERVICE
DOORWAY LINERS
PART 2: INSPECTION
1. RC - Do a Medium Frequency Eddy Current (MFEC) inspection on the upper frame at Station 360,
left and right side, between stringer 13 and stringer 14, for cracks in accordance with the figures
that follow:
Right Side - Station 360Left Side - Station 360
FIGURE 2FIGURE 1
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NOTE: 1. It is optional to accomplish the preventative modification in accordance with
PART 4: PREVENTATIVE MODIFICATION. Accomplishment of optional PART
4: PREVENTATIVE MODIFICATION is terminating action for PART 2:
INSPECTION at the modified location only.
2. If any Boeing ODA approved repair via FAA Form 8100-9 was installed to
eliminate cracking that was previously found, initial and repeat inspections in
accordance with PART 2: INSPECTION are not required at the repaired location
only.
PART 3: REPAIR
1. RC - Do the repair of the cracked upper frame at Station 360, left or right side, between stringer
13 and stringer 14 as follows:
a. Cut the fail safe chord in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 4FIGURE 3
b. Remove the cracked section of the upper frame in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 6FIGURE 5
c. Do open hole High Frequency Eddy Current (HFEC) inspections for cracks in accordance
with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 8FIGURE 7
CONDITION 3: ANY CRACK FOUND DURING PART 3: REPAIR
(1) Contact Boeing to get instructions for the repair and do the work instructed by Boeing.
CONDITION 4: NO CRACK FOUND DURING PART 3: REPAIR
(1) Make a replacement upper frame section, intercostal clip (Left Side), inner repair angle
and outer repair angle, in accordance with the figures below:
NOTE: As an option to making a replacement upper frame section, a preformed and
contoured frame section may be used.
Right Side - Station 360Left Side - Station 360
FIGURE 10FIGURE 9
(2) Locate the replacement upper frame section, inner repair angle, outer repair angle and
intercostal clip (Left Side) into position on the frame in accordance with the figures below:
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### Page 33

Right Side - Station 360Left Side - Station 360
FIGURE 12FIGURE 11
(3) Install the replacement upper frame section, inner repair angle, outer repair angle and
intercostal clip (Left Side), in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 14FIGURE 13
2. Do PART 6: POST-REPAIR INSPECTION for cracks.
PART 4: PREVENTATIVE MODIFICATION (Optional)
1. RC - Do the preventative modification on the upper frame at Station 360, left or right side, between
stringer 13 and stringer 14 as follows:
NOTE: Accomplishment of optional PART 4: PREVENTATIVE MODIFICATION is terminating
action for PART 2: INSPECTION at the modified location only.
a. Do open hole and surface HFEC inspections for cracks in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 16FIGURE 15
CONDITION 5: ANY CRACK FOUND IN THE UPPER FRAME ORIGINATING FROM THE
UPPER END FASTENER LOCATION OF THE FRAME SPLICE, COMMON TO THE FAIL
SAFE CHORD DURING PART 4: PREVENTATIVE MODIFICATION
(1) Do PART 3: REPAIR.
CONDITION 6: ANY OTHER CRACK FOUND DURING PART 4: PREVENTATIVE
MODIFICATION.
(1) Contact Boeing to get instructions for the repair and do the work instructed by Boeing.
CONDITION 7: NO CRACK FOUND DURING PART 4: PREVENTATIVE MODIFICATION
(1) Cut the fail safe chord in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 4FIGURE 3
(2) Make a modification angle and intercostal clip (Left Side), in accordance with the figures
below:
Right Side - Station 360Left Side - Station 360
FIGURE 18FIGURE 17
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### Page 34

(3) Locate the modification angle and intercostal clip (Left Side), in accordance with the
figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 20FIGURE 19
(4) Install the modification angle and intercostal clip (Left Side), in accordance with the figures
below:
Right Side - Station 360Left Side - Station 360
FIGURE 22FIGURE 21
2. Do PART 7: POST-PREVENTATIVE MODIFICATION INSPECTION for cracks.
PART 5: CLOSE ACCESS
1. Install/kept passenger seats, sidewall panels, sidewall insulation, partitions and wind screens,
panels, passenger service units, overhead stowage bin, doorway liners, lavatories and galleys as
follows:
NOTE: Install/kept partitions and wind screens, panels, passenger service units, overhead
stowage bin, doorway liners, lavatories or galleys that may have been removed for access.
More DataName
Refer to 737-300/400/500 AMM 25-22-00, as an
accepted procedure.
PASSENGER SEATS - MAINTENANCE
PRACTICES
Refer to 737-300/400/500 AMM 25-21-46, as an
accepted procedure.
SIDEWALL PANELS - REMOVAL/INSTALLA-
TION
Refer to 737-300/400/500 AMM 25-31-11, as an
accepted procedure.
GALLEY NO. 1 - REMOVAL/INSTALLATION
Refer to 737-300/400/500 AMM 25-23-61, as an
accepted procedure.
PASSENGER CABIN PASSENGER SERVICE
UNITS (PSUs) - MAINTENANCE PRACTICES
Refer to 737-300/400/500 AMM 25-24-31, as an
accepted procedure.
OVERHEAD STOWAGE BIN - REMOVAL/IN-
STALLATION
Refer to 737-300/400/500 AMM 25-24-00, as an
accepted procedure.
PARTITIONS AND WIND SCREENS
Refer to 737-300/400/500 AMM 25-21-31 and
737-300/400/500 AMM 25-21-35, as accepted
procedures.
ENTRY DOORWAY LINER AND SERVICE
DOORWAY LINERS
PART 6: POST-REPAIR INSPECTION
1. Do PART 1: OPEN ACCESS.
NOTE: PART 6: POST-REPAIR INSPECTION is only required at locations where PART 3:
REPAIR has been accomplished.
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### Page 35

2. Do a Detailed Inspection and a HFEC inspection for cracks in the upper frame, side frame, inner
repair angle and outer repair angle, in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 24FIGURE 23
CONDITION 8: ANY CRACK FOUND DURING PART 6: POST-REPAIR INSPECTION
a. RC - Contact Boeing to get instructions for the repair and do the work instructed by Boeing.
CONDITION 9: NO CRACK FOUND DURING PART 6: POST-REPAIR INSPECTION
a. Repeat PART 6: POST-REPAIR INSPECTION for cracks, at the repeat interval, in accordance
with Section 1.E., Compliance.
3. Do PART 5: CLOSE ACCESS.
4. Put the airplane back to a serviceable condition.
PART 7: POST-PREVENTATIVE MODIFICATION INSPECTION
1. Do PART 1: OPEN ACCESS.
NOTE: PART 7: POST-PREVENTATIVE MODIFICATION INSPECTION is only required at
locations where optional PART 4: PREVENTATIVE MODIFICATION has been
accomplished.
2. Do a Detailed Inspection and a HFEC inspection for cracks in the upper frame, side frame, and
modification angle, in accordance with the figures below:
Right Side - Station 360Left Side - Station 360
FIGURE 26FIGURE 25
CONDITION 10: ANY CRACK FOUND DURING PART 7: POST-PREVENTATIVE MODIFICATION
INSPECTION
a. RC - Contact Boeing to get instructions for the repair and do the work instructed by Boeing.
CONDITION 11: NO CRACK FOUND DURING PART 7: POST-PREVENTATIVE MODIFICATION
INSPECTION
a. Repeat PART 7: POST- PREVENTATIVE MODIFICATION INSPECTION for cracks, at the
repeat interval, in accordance with Section 1.E., Compliance.
3. Do PART 5: CLOSE ACCESS
4. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
OPPEF  STA
FRAME  360
STA
360
S-13L_
SRACI
TYPICAL
S-14L
FAIL SAFE
CHORD
SIDE FRAME
NOTE: DOOR SURROUND
STRUCTURE NOT  2261384
SHOWN FOR CLARITY
FIGURE 1: LEFT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE
(SHEET 1 OF 3)
Original Issue: August 12, 2014
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
UPPER FRAME
SIDE WALL
ISOLATOR
MOUNT  - S-13L
FWD
FAIL SAFE
SIDE FRAME  CHORD
B  B
VIEW ROTATED 90° CW
CRACK  B-B
(TYPICAL)
GROUNDING
STUD
FAIL SAFE
CHORD
UPPER FRAME
- S-14L
SIDE FRAME
INBD  A-A  2287692
FIGURE 1: LEFT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE
(SHEET 2 OF 3)
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### Page 38

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 each inspection.
More DataQtyIdentificationNameTaskStep
(a) (b)1-Upper FrameInspect1
(a) Inspect for cracks in the area around the upper end fastener of the frame splice common to the fail safe
chord as shown in Section B-B.
(b) Do MFEC inspection in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 7.
FIGURE 1: LEFT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE
(SHEET 3 OF 3)
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ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
STA  UPPER
360  FRAME
STAI
360
S-13R -
CRACK -
(TYPICAL)
S-14R *
- SIDE FRAME
FAIL SAFE CHORD
FIGURE 2: RIGHT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE
(SHEET 1 OF 3)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
• UPPER FRAME
S-13R-
FAIL SAFE
CHORD  SIDE FRAME
B  B
VIEW ROTATED 90° CCW
B-B
CRACK
(TYPICAL)
FAIL SAFE CHORD
UPPER FRAME
S-14R
SIDE FRAME
A-A  INBD  2288126
FIGURE 2: RIGHT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE
(SHEET 2 OF 3)
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### Page 41

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 each inspection.
More DataQtyIdentificationNameTaskStep
(a) (b)1-Upper FrameInspect1
(a) Inspect for cracks in the area around the upper end fastener of the frame splice common to the fail safe
chord as shown in Section B-B.
(b) Do MFEC inspection in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 7.
FIGURE 2: RIGHT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 737-53A1339
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
OPPEF  STA
FRAME  360
STA
360
S-13L_
S-14L
FAIL SAFE
CHORD
SIDE FRAME
NOTE: DOOR SURROUND
STRUCTURE NOT  2261608
SHOWN FOR CLARITY
FIGURE 3: LEFT SIDE - CUT FAIL SAFE CHORD
(SHEET 1 OF 4)
Original Issue: August 12, 2014
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Work - See page 1 for details.  42 of 146

### Page 43 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
- S-13L
SIDE WALL
ISOLATOR
MOUNT
B
B
SIDE FRAME
C
0.25R
0.44
FAIL SAFE CHORD
UPPER FRAME
- S-14L
INBD  A-A  2261610
FIGURE 3: LEFT SIDE - CUT FAIL SAFE CHORD
(SHEET 2 OF 4)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
SIDE FRAME
INBD
• SHEAR TIE
FAIL SAFE
UPPER  FRAME  B-B  CHORD
0.25
TAO SAFE 0000  CHORD
0.44
THORAFE 234G  CHORD  - SIDE
FRAME
CUT FAIL SAFE CHORD  C-C  FWD >  2288627
FIGURE 3: LEFT SIDE - CUT FAIL SAFE CHORD
(SHEET 3 OF 4)
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### Page 45

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 each repair.
More DataQtyIdentificationNameTaskStep
(a)1-FastenerRemove1
(b)1-Fail Safe ChordCut2
(c)1-Fail Safe ChordClean/Deburr3
(d)-TYPE 2, CLASS AChemical Conversion
Coat
Apply4
(e)-BMS 10-11, TYPE 1PrimerApply5
(a) Remove fastener in accordance with 737-300/400/500 SRM 51-40-02. For PART 4: PREVENTATIVE
MODIFICATION (optional) this fastener will already be removed.
(b) It is recommended to insert a piece of protective steel between the fail safe chord and frame prior to cutting.
Additional fasteners can be removed to insert the steel piece.
(c) Break all sharp edges.
(d) Apply to all bare/cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure.
(e) Apply two coats of primer to all bare/cut surfaces. Refer to SOPM 20-41-02 as an accepted procedure.
FIGURE 3: LEFT SIDE - CUT FAIL SAFE CHORD
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 737-53A1339
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
STA  UPPER
360  FRAME
SIA
360
S-13R
S-14R
- SIDE FRAME
FAIL SAFE CHORD  2261612
FIGURE 4: RIGHT SIDE - CUT FAIL SAFE CHORD
(SHEET 1 OF 4)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
S-13R -
• SIDE FRAME
_ 0.25R
B
0.44  FAIL SAFE CHORD
UPPER FRAME
S-14R -
- SIDE FRAME
A-A  INBD  2261613
FIGURE 4: RIGHT SIDE - CUT FAIL SAFE CHORD
(SHEET 2 OF 4)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
SIDE FRAME
SHEAR TIE•  INBD
FAIL SAFE
CHORD
B-B  FRAME  UPPER
0.25
3345 CHORI  FAIL SAF
0.44
UPPER
FRAME ~
SIDE
FRAME -
FWD  CUT FAIL SAFE CHORD  C-C  2288632
FIGURE 4: RIGHT SIDE - CUT FAIL SAFE CHORD
(SHEET 3 OF 4)
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### Page 49

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 each repair.
More DataQtyIdentificationNameTaskStep
(a)1-FastenerRemove1
(b)1-Fail Safe ChordCut2
(e)1-Fail Safe ChordClean/Deburr3
(c)-TYPE 2, CLASS AChemical Conversion
Coat
Apply4
(d)-BMS 10-11, TYPE 1PrimerApply5
(a) Remove fastener in accordance with 737-300/400/500 SRM 51-40-02. For PART 4: PREVENTATIVE
MODIFICATION (optional) this fastener will already be removed.
(b) It is recommended to insert a piece of protective steel between the fail safe chord and frame prior to cutting.
Additional fasteners can be removed to insert the steel piece.
(c) Apply to all bare/cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure.
(d) Apply two coats of primer to all bare/cut surfaces. Refer to SOPM 20-41-02 as an accepted procedure.
(e) Break all sharp edges.
FIGURE 4: RIGHT SIDE - CUT FAIL SAFE CHORD
(SHEET 4 OF 4)
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ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
OPPEF  STA
FRAME  360
STA
360  B
S-13L_
S-14L.
GROUND STUD 1
(14 LOCATIONS) C  FASTENER
FAIL SAFE
CHORD
SIDE FRAME
NOTE: DOOR SURROUND
STRUCTURE NOT  2261620
SHOWN FOR CLARITY
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 1 OF 6)
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### Page 51 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
CUT LINE
CUT LINE
C 1.30  - S-13L  C 1.30  - S-13L
1.25  1.25
→
STRINGER  •STRINGER
TIE  TIE
UPPER  UPPER
FRAME  FRAME
INBD
- S-14L  • S-14L
SIDE  SIDE
FRAME  FRAME
FAIL SAFE
FAIL SAFE  A-A  CHORD  B-B
CHORD
OFFSET ELECTRICAL STAND-OFF  CENTERED ELECTRICAL STAND-OFF
WITH LINING HOLE  WITH LINING HOLE
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 2 OF 6)
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### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
INTERCOSTAL
TEE
SIDEWALL
ISOLATOR MOUNT  ) 7 LOCATIONS  INTERCOSTAL
STA  WEB
360
2) INTERCOSTAL
CLIP
UPPER FRAME
STRINGER TIE  STRINGER
CHANNEL
S-13L -
•WD
C-C  2261622
VIEW ROTATED 90° CLOCKWISE
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF OPPER FRAME
(SHEET 3 OF 6)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
UPPER  STA
FRAME  360
S-131_
S-14L
FAIL SAFE
CHORD
SIDE FRAME
NOTE: DOOR SURROUND
STRUCTURE NOT  2290056
SHOWN FOR CLARITY
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 4 OF 6)
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### Page 54

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 each repair.
More DataQtyIdentificationNameTaskStep
(a)14-FastenerRemove1
Max quantity provid-
ed.
Some fasteners may
have been removed
during the cutting of
the fail safe chord.
(g)1-Ground Stud AssemblyRemove
Only airplanes with
the part installed.
(a)7-FastenerRemove2
1-Intercostal ClipRemove
(a)2-FastenerRemove3
Only airplanes with
the part installed.
Only airplanes with
the part installed.
1-Electrical Stand-offRemove / Keep
(a)2-FastenerRemove4
1-Sidewall Isolator MountRemove / Keep
Only airplanes with
the part installed.
1-Lining Attachment StudRemove5
(b) (c)1-Upper FrameCut6
1-Upper Frame Section
Cut
Remove7
(d)1-Upper FrameClean/Deburr8
(e)-TYPE 2, CLASS AChemical Conversion
Coat
Apply9
(f)-BMS 10-11, TYPE 1PrimerApply10
(a) Remove fastener in accordance with 737-300/400/500 SRM 51-40-02.
(b) View A-A and View B-B show the edge distance from the cut line to the existing fastener center line
common to the stringer tie. Use View A-A or View B-B depending on the existing location of the Electrical
Stand-off.
(c) Keep at least 0.75 inch dimension between cut line and the center line of nearest fastener hole common
to the electrical stand-off.
(d) Break all sharp edges. Radius the corners to 0.16 inch minimum to 0.19 inch maximum.
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 5 OF 6)
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BOEING SERVICE BULLETIN 737-53A1339
ALERTALERT

### Page 55

More DataQtyIdentificationNameTaskStep
(e) Apply to all bare/cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure.
(f) Apply two coats of primer to all bare/cut surfaces. Refer to SOPM 20-41-02 as an accepted procedure.
(g) Refer to SWPM 20-20-10 as an accepted procedure for removal of the ground stud.
FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 6 OF 6)
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BOEING SERVICE BULLETIN 737-53A1339
ALERTALERT

### Page 56 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
STA  UPPER
360  FRAME
SIA
360'
S-13R
(15 LOCATIONS) 1  FASTENER
S-14R
- SIDE FRAME
FAIL SAFE CHORD  2261644
FIGURE 6: RIGHT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 1 OF 4)
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### Page 57 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
(3) CUT LINE
S-13R -  1:35
- STRINGER
TIE
UPPER FRAME
S-14R -
FAIL SAFE CHORD
- SIDE FRAME
INBD
A-A
FIGURE 6: RIGHT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 2 OF 4)
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### Page 58 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
STA  UPPER
360  FRAME
500
S-13R -
S-14R
→ SIDE FRAME
FAIL SAFE CHORD  2261646
FIGURE 6: RIGHT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 3 OF 4)
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### Page 59

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 each repair.
More DataQtyIdentificationNameTaskStep
(a)15-FastenerRemove1
Max quantity provid-
ed.
Some fasteners may
have been removed
during the cutting of
the fail safe chord.
Only airplanes with
the part installed.
1-Lining Attachment StudRemove2
(b) (c)1-Upper FrameCut3
1-Upper Frame Section
Cut
Remove4
(d)1-Upper FrameClean/Deburr5
(e)-TYPE 2, CLASS AChemical Conversion
Coat
Apply6
(f)-BMS 10-11, TYPE 1PrimerApply7
(a) Remove fastener in accordance with 737-300/400/500 SRM 51-40-02.
(b) View A-A shows the edge distance from the cut line to the existing fastener center line common to the
stringer tie.
(c) Cut to include the removal of the existing lining attachment stud hole.
(d) Break all sharp edges. Radius the corners to 0.16 inch minimum to 0.19 inch maximum.
(e) Apply to all bare/cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure.
(f) Apply two coats of primer to all bare/cut surfaces. Refer to SOPM 20-41-02 as an accepted procedure.
FIGURE 6: RIGHT SIDE - REMOVAL SECTION OF UPPER FRAME
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 12, 2014
737-53A1339
59 of 146
BOEING SERVICE BULLETIN 737-53A1339
ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 737-53A1339
ALERT  ALERT
UPPER  STA
FRAME  360
7 LOCATIONS
STA
360
S-13L
STRINGER  / CHANNE  STRINGER
TIE
S-14L
~ INTERCOSTAL
WEB
15 LOCATIONS  INTERCOSTAL
TEE
TOOLING
HOLE
FAIL SAFE
CHORD
SIDE FRAME
NOTE: DOOR SURROUND
STRUCTURE NOT  SHOWN FOR CLARITY  2288306
FIGURE 7: LEFT SIDE - INSPECT FRAME
(SHEET 1 OF 2)
Original Issue: August 12, 2014
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-53A1339
Work - See page 1 for details.  60 of 146

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