# Boeing Alert Service Bulletin 737-53A1357: No revision named

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- Document: [Boeing Alert Service Bulletin 737-53A1357](https://openairdocs.org/service-documents/boeing/737-53a1357.md)
- Title as filed: SB 737-53A1357
- Pages: 27
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1357
Original Issue: August 09, 2016
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Station 947.5 Frame Between Stringer S-24R
and Stringer S-25R 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
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2016 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: August 09, 2016
737-53A1357
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2.0

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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 17
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 17
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
FIGURE 1: FUSELAGE FRAME - HIGH FREQUENCY EDDY CURRENT INSPECTION . . . . . . . 23
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: FUSELAGE FRAME AT
STATION (STA) 947.5 COMMON TO THE WATER TANK SUPPORT INTERCOSTAL CLIP
LOCATED BETWEEN STRINGER S-24R AND S-25R INSPECTION AND REPAIR . . . 26
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1357Original Issue: August 09, 2016
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Station 947.5 Frame Between Stringer S-24R
and Stringer S-25R Inspection and Repair
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to do a surface High Frequency Eddy Current (HFEC) inspection for any
crack in the fuselage frame at Station (STA) 947.5, right side, common to the water tank support intercostal clip
located between stringer S-24R and stringer S-25R. Any undetected cracks in the frame could grow in size and
result in a severed frame. The off-load due to a severed frame can result in multiple adjacent severed frames.
If not corrected, multiple adjacent severed frames could adversely affect the structural integrity of the airplane.
One operator of 737 Classic airplanes reported cracks on 20 airplanes. Ten of those cracks were on airplanes
with line numbers 292-2565. Cracks on airplanes with line number 292-2565 will be addressed by a different
service action. This service bulletin is being released to address cracking in fuselage frames at STA 947.5 for
line numbers 2566-3132.
Ten cracks have been reported on airplanes with line numbers 2566-3132. These airplanes had accumulated
between 39,400 and 51,745 flight cycles at the time of crack finding. The reported cracks were between 0.184
to 1.125 inch in length. The cause of the cracks was found to be fatigue caused by cyclic loading of the fuselage
and out of plane bending of the frame caused by the water tank loads.
Accomplishment of the inspections in accordance with this service bulletin will make sure that any crack in the
fuselage frame at STA 947.5, common to the water tank support intercostal clip, located between stringer S-24R
and stringer S-25R, is found and repaired. Repair of any crack will make sure the frame maintains its structural
integrity.
Boeing Fleet Team Digest (FTD) 737 FTD 53-15001 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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### Page 6

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
Get access to the aft cargo compartment aft bulkhead. Remove and keep the aft cargo compartment aft bulkhead
lining, sidewall lining and insulation to get access to fuselage frame at STA 947.5. Do a surface High Frequency
Eddy Current (HFEC) inspection of the fuselage frame at STA 947.5 common to the water tank support intercostal
clip located between stringer S-24R and stringer S-25R for any crack. If any crack is found, originating at the
fastener hole in the fuselage frame common to the water tank support intercostal clip, or originating at the frame
adjacent to the water tank support intercostal clip, do the repair in accordance with this service bulletin. If no
crack is found, continue to do the repeat inspections in accordance with this service bulletin.
EFFECTIVITY
737-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
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 and repair procedures given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
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### Page 7 (OCR)

BOEING SERVICE BULLETIN 737-53A1357
ALERT  ALERT
MATERIAL INFORMATION
None.
DO A SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION OF THE
FUSELAGE FRAME AT STA 947.5 COMMON TO
THE WATER TANK SUPPORT INTERCOSTAL CLIP
LOCATED BETWEEN STRINGER S-24R AND
TRINGER S-25R FOR ANY CRACK. IF ANY
CRACK IS FOUND, ORIGINATING AT THE
ASTENER HOLE IN THE FUSELAGE FRAME
COMN  1ON TO THE WATER TANK SUPPORT
TERCOSTAL CLIP  OR ORIGINATING AT THE
FRAME ADJACEN  NATER  TANK
DO THE REPAIR
ORDANCE  SERVICE BULLETIN.
F NO  UND  INUE TO DO THE
REPEAT INSPEC  TONS IN ACCORDANCE WITH
THIS SERVICE BULLETIN.
STA
947.5
FRAME
S-24R
BL
0.0  • INBD
AFT CARGO COMPARTMENT AFT BULKHEAD  2463198
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### Page 9

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1357
Original Issue: August 09, 2016
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Station 947.5 Frame Between Stringer S-24R
and Stringer S-25R Inspection and Repair
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 737-300/-400/-500 Airplanes, line numbers 2566-3132, in 1
Group. The Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
737-300, -400 and -500 airplanes, line numbers 2566-3132.-1
Airplane Models:
737-300, 737-400, 737-500
GroupVariable Number
1PJ553 - PJ561
1PJ601 - PJ615
1PJ811
1PJ816 - PJ817
1PM548 - PM550
1PP518 - PP520
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GroupVariable Number
1PP876 - PP877
1PQ297 - PQ299
1PQ345 - PQ348
1PQ370 - PQ373
1PQ391 - PQ395
1PQ409 - PQ410
1PQ414 - PQ418
1PQ431 - PQ438
1PQ447 - PQ448
1PQ451
1PQ454
1PQ474 - PQ475
1PQ772
1PQ933 - PQ935
1PQ951
1PQ971 - PQ997
1PR001 - PR017
1PR021 - PR034
1PR041 - PR045
1PR061 - PR072
1PR077 - PR082
1PR091 - PR092
1PR096
1PR101
1PR121 - PR122
1PR131 - PR132
1PR141 - PR143
1PR161 - PR172
1PR181
1PS617 - PS630
1PS704 - PS706
1PS763 - PS799
1PS811
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GroupVariable Number
1PS836 - PS837
1PS841 - PS846
1PS851 - PS852
1PS856
1PS861 - PS863
1PS866 - PS868
1PS871 - PS874
1PS896 - PS897
1PS901 - PS941
1PS956 - PS957
1PS961 - PS963
1PS971 - PS978
1PT012 - PT015
1PT029 - PT031
1PT126 - PT138
1PT188
1PT307 - PT309
1PT513 - PT517
1PT585 - PT586
1PT643 - PT644
1PT656
1PT681 - PT685
1PT716 - PT717
1PT721 - PT725
1PT801 - PT834
1PT851 - PT854
1PT871 - PT886
1PT901 - PT930
1PT971 - PT973
1PT981 - PT985
1PT996
1PU301
1PU311 - PU313
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GroupVariable Number
1PV204 - PV209
1PV226 - PV229
1PV284 - PV287
1PV296
1PV301 - PV302
1PV351
1PV356 - PV357
1PW086 - PW088
1PW168 - PW171
1PW246 - PW252
1PW262 - PW264
1PW271 - PW276
1PW285 - PW292
1PW401 - PW408
1PW411 - PW418
1PW421 - PW424
1PW431 - PW435
1PW441 - PW450
1PW521 - PW522
1PW524 - PW525
1PW527 - PW530
1PW547 - PW550
1PW621 - PW622
1PW635 - PW637
1PW831
1PW851 - PW856
2. Spares Affected
None.
B. Concurrent Requirements
None.
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### Page 13

C. Reason
This service bulletin gives instructions to do a surface High Frequency Eddy Current (HFEC) inspection
for any crack in the fuselage frame at Station (STA) 947.5, right side, common to the water tank support
intercostal clip located between stringer S-24R and stringer S-25R. Any undetected cracks in the frame
could grow in size and result in a severed frame. The off-load due to a severed frame can result in
multiple adjacent severed frames. If not corrected, multiple adjacent severed frames could adversely
affect the structural integrity of the airplane.
One operator of 737 Classic airplanes reported cracks on 20 airplanes. Ten of those cracks were on
airplanes with line numbers 292-2565. Cracks on airplanes with line number 292-2565 will be addressed
by a different service action. This service bulletin is being released to address cracking in fuselage
frames at STA 947.5 for line numbers 2566-3132.
Ten cracks have been reported on airplanes with line numbers 2566-3132. These airplanes had
accumulated between 39,400 and 51,745 flight cycles at the time of crack finding. The reported cracks
were between 0.184 to 1.125 inch in length. The cause of the cracks was found to be fatigue caused
by cyclic loading of the fuselage and out of plane bending of the frame caused by the water tank loads.
Accomplishment of the inspections in accordance with this service bulletin will make sure that any crack
in the fuselage frame at STA 947.5, common to the water tank support intercostal clip, located between
stringer S-24R and stringer S-25R, is found and repaired. Repair of any crack will make sure the frame
maintains its structural integrity.
Boeing Fleet Team Digest (FTD) 737 FTD 53-15001 is related to this service bulletin.
D. Description
Get access to the aft cargo compartment aft bulkhead. Remove and keep the aft cargo compartment
aft bulkhead lining, sidewall lining and insulation to get access to fuselage frame at STA 947.5. Do a
surface High Frequency Eddy Current (HFEC) inspection of the fuselage frame at STA 947.5 common
to the water tank support intercostal clip located between stringer S-24R and stringer S-25R for any
crack. If any crack is found, originating at the fastener hole in the fuselage frame common to the water
tank support intercostal clip, or originating at the frame adjacent to the water tank support intercostal
clip, do the repair in accordance with this service bulletin. If no crack is found, continue to do the repeat
inspections in accordance with this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
218737-300, 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.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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### Page 14

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A.
Table 1: Fuselage Frame At Station (STA) 947.5 Common to the Water Tank Support Intercostal Clip
Located Between Stringer S-24R and S-25R Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 6,000
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 34,000
total flight cy-
cles.
Do PART 2: SURFACE
HIGH FREQUENCY ED-
DY CURRENT (HFEC)
INSPECTION for any
crack. (a) (b)
All airplanes.
-Before further flight.Do PART 3: REPAIR. (b)
(c)
CONDITION 1: ANY
CRACK FOUND
12,000 flight cy-
cles.
-Repeat PART 2: SUR-
FACE HIGH FREQUEN-
CY EDDY CURRENT
(HFEC) INSPECTION for
any crack. (a) (b)
CONDITION 2: NO
CRACK FOUND
(a) If any Boeing ODA approved repair via FAA Form 8100-9 was installed to eliminate cracking that was
previously found at the frame at STA 947.5, right side, between stringers S-24R and S-25R, initial and
repeat inspections in accordance with PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION are not required at the repaired location only, if:
a. A repair doubler of thickness 0.063 inch or larger was installed to reinforce the frame, and
b. The repair doubler extends at least one row of fasteners beyond the stringer clip location at S-23R,
between S-22R and S-23R, and at least one row of fasteners beyond the stringer clip location at S-25R,
between S-25R and S-26R.
(b) Accomplishment of the repair in accordance with PART 3: REPAIR is a terminating action for initial and
repeat PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION.
(c) Post-repair inspections are given in Boeing Drawing 692A3001.
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.
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### Page 15

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 and repair 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
0.250.251Open Access
1.001.001FIGURE 1
0.250.251Close Access
1.501.50TOTAL FOR EACH AIRPLANE (a)
(a) Total for each airplane does not include time for repair, if repair is required
additional time should be applied to the total.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches) (a)
Change in Weight
(Pounds) (a)Airplane
+325+0.31737-300
+340+0.31737-400
+312+0.31737-500
(a) Only if the repair is done in accordance with this service bul-
letin.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Service Bulletin Index D6-19567
b. 737 Fleet Team Digest (FTD) 53-15001
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c. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Procedure 4 or Procedure 23.
d. 737-300/400/500 Aircraft Maintenance Manual (AMM) 25-52-73, 25-52-81, 25-52-91
2. Data Supplied with this Service Bulletin:
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
--DWGFRAME REPAIR - STA 947.5, POTABLE
WATER TANK
692A3001
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
FRAME INSTALLATION - BODY STATION 947.565-46560
TANK INSTALLATION - PASSENGER WATER SYSTEM65-49680
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:
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 Boeing Drawing 692A3001 for PART 3: REPAIR.
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
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and 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
a. Inspection:
None.
b. Repair:
Refer to Boeing Drawing 692A3001 for parts and materials that are necessary for the repair.
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.
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 inspection 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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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF 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. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently.
4. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 737 Structural Repair Manual,
Chapter 51.
5. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
6. Refer to APPENDIX A for logic diagram(s). Logic diagrams are provided as an aid
only. Information contained in Paragraph 1.E., Compliance is the primary source for
compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
7. 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.
8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
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9. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
10. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
12. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Do PART 1: ACCESS.
2. RC - Do PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION for
any crack.
NOTE: If any Boeing ODA approved repair via FAA Form 8100-9 was installed to eliminate
cracking that was previously found at the frame at STA 947.5, right side, between stringers
S-24R and S-25R, initial and repeat inspections in accordance with PART 2: SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION are not required at the
repaired location only, if:
1. A repair doubler of thickness 0.063 inch or larger was installed to reinforce the
frame, and
2. The repair doubler extends at least one row of fasteners beyond the stringer
clip location at S-23R, between S-22R and S-23R, and at least one row of
fasteners beyond the stringer clip location at S-25R, between S-25R and S-26R.
NOTE: Accomplishment of the repair in accordance with PART 3: REPAIR is a terminating action
for initial and repeat PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION.
a. CONDITION 1: ANY CRACK FOUND
(1) Do PART 3: REPAIR.
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NOTE: Accomplishment of the repair in accordance with PART 3: REPAIR is a
terminating action for initial and repeat PART 2: SURFACE HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTION.
NOTE: Post-repair inspections are given in Boeing Drawing 692A3001.
b. CONDITION 2: NO CRACK FOUND
(1) Repeat PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
for any crack.
NOTE: If any Boeing ODA approved repair via FAA Form 8100-9 was installed to
eliminate cracking that was previously found at the frame at STA 947.5, right
side, between stringers S-24R and S-25R, initial and repeat inspections in
accordance with PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION are not required at the repaired location only, if:
1. A repair doubler of thickness 0.063 inch or larger was installed to
reinforce the frame, and
2. The repair doubler extends at least one row of fasteners beyond the
stringer clip location at S-23R, between S-22R and S-23R, and at least
one row of fasteners beyond the stringer clip location at S-25R, between
S-25R and S-26R.
NOTE: Accomplishment of the repair in accordance with PART 3: REPAIR is a
terminating action for initial and repeat PART 2: SURFACE HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTION.
3. Do PART 4: CLOSE ACCESS.
4. Put the airplane back to a serviceable condition.
PART 1: ACCESS
1. Get access to the aft cargo compartment.
2. Remove and keep the aft cargo compartment aft bulkhead lining. Refer to 737-300/400/500 AMM
25-52-81 as an accepted procedure.
3. Remove and keep access panel 1547 from the aft bulkhead in the aft cargo compartment.
4. Remove and keep the aft cargo compartment sidewall lining on the right side of the airplane,
between the aft cargo door and the aft cargo compartment aft bulkhead. Refer to 737-300/400/500
AMM 25-52-73 as an accepted procedure.
5. Remove and keep the aft cargo compartment insulation on the right side of the airplane to get
access to the fuselage frame at STA 947.5. Refer to 737-300/400/500 AMM 25-52-91 as an
accepted procedure.
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PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
1. Do Surface High Frequency Eddy Current (HFEC) inspections for any crack in accordance with
FIGURE 1.
PART 3: REPAIR
1. Do the repair of the fuselage frame at STA 947.5 common to the water tank support intercostal
clip located between stringer S-24R and stringer S-25R in accordance with Boeing Drawing
692A3001.
PART 4: CLOSE ACCESS
1. Install the kept aft cargo compartment insulation. Refer to 737-300/400/500 AMM 25-52-91 as an
accepted procedure.
2. Install the kept aft cargo compartment sidewall lining. Refer to 737-300/400/500 AMM 25-52-73
as an accepted procedure.
3. Install the kept access panel 1547 on the aft bulkhead in the aft cargo compartment.
4. Install the kept aft cargo compartment aft bulkhead lining. Refer to 737-300/400/500 AMM 25-52-81
as an accepted procedure.
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BOEING SERVICE BULLETIN 737-53A1357
ALERT  ALERT
STA
947.5
FRAME
S-24R
BL
0.0  INBD
AFT CARGO COMPARTMENT AFT BULKHEAD  (VIEW LOOKING AFT)  2462374
FIGURE 1: FUSELAGE FRAME - HIGH FREQUENCY EDDY CURRENT INSPECTION
(SHEET 1 OF 3)
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 737-53A1357
ALERT  ALERT
FRAME
FAILSAFE
CHORD
• 1.00
0.50
1.40
0.90
- TYPICAL CRACK
S-24R
WATER TANK
SUPPORT
INTERCOSTAL CLIP  PROBE SCAN
DIRECTION
VIEW LOOKING AFT
INSPECTION AREA  S-25R
INBD
FRAME
1.20
1.00
EDGE OF
FAILSAFE
CHORD
'FAILSAFE
INTERCOSTAL  CHORD
STA
947.5
FWD  2462376
A-A
FIGURE 1: FUSELAGE FRAME - HIGH FREQUENCY EDDY CURRENT INSPECTION
(SHEET 2 OF 3)
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### Page 25

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)1-FrameInspect1
(b)1-FrameInspect2
(a) Do a Surface High Frequency Eddy Current (HFEC) inspection on the forward side of fuselage frame at
STA 947.5, as shown in view A and view A-A, for any crack in accordance with 737 NDT Manual Part 6,
51-00-00, Procedure 4 or 23. Scan the HFEC probe in the circumferential direction of the frame web and
index the probe half a probe coil diameter until the entire inspection area has been inspected.
(b) Do a Surface HFEC inspection on the forward side of fuselage frame STA 947.5 around the inboard fas-
tener common to the water tank support intercostal clip between stringer S-24R and S-25R for any crack
in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.
FIGURE 1: FUSELAGE FRAME - HIGH FREQUENCY EDDY CURRENT INSPECTION
(SHEET 3 OF 3)
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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONPART 2
REPAIRPART 3
ANY CRACK FOUNDCONDITION 1
NO CRACK FOUNDCONDITION 2
2. The table below gives the description for the flag notes called out in the logic diagram.
DescriptionFlag Note Letter
If any Boeing ODA approved repair via FAA Form 8100-9 was installed to
eliminate cracking that was previously found at the frame at STA 947.5, right
side, between stringers S-24R and S-25R, initial and repeat inspections in
accordance with PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION are not required at the repaired location only, if:
(a)
1. A repair doubler of thickness 0.063 inch or larger was installed to
reinforce the frame, and
2. The repair doubler extends at least one row of fasteners beyond the
stringer clip location at S-23R, between S-22R and S-23R, and at
least one row of fasteners beyond the stringer clip location at S-25R,
between S-25R and S-26R.
Accomplishment of the repair in accordance with PART 3: REPAIR is a termi-
nating action for initial and repeat PART 2: SURFACE HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTION.
(b)
Post-repair inspections are given in Boeing Drawing 692A3001.(c)
APPENDIX A:  LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: FUSELAGE FRAME
AT STATION (STA) 947.5 COMMON TO THE WATER TANK SUPPORT INTERCOSTAL CLIP LOCATED
BETWEEN STRINGER S-24R AND S-25R INSPECTION AND REPAIR
(SHEET 1 OF 2)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 737-53A1357
ALERT  ALERT
WHICHEVER OCCURS LATER
WITHIN 6,000 FLIGHT
BEFORE 34,000 TOTAL  CYCLES AFTER THE
ORIGINAL ISSUE DATE
FLIGHT CYCLES  OF THIS SERVICE
BULLETIN
(a)  DO PART 2
(b)
CONDITION 1  CONDITION 2
BEFORE FURTHER  NOT TO EXCEED 12,000
FLIGHT  FLIGHT CYCLES
REPEAT PART 2
DO PART 3  2462377
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: FUSELAGE FRAME
AT STATION (STA) 947.5 COMMON TO THE WATER TANK SUPPORT INTERCOSTAL CLIP LOCATED
BETWEEN STRINGER S-24R AND S-25R INSPECTION AND REPAIR
(SHEET 2 OF 2)
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