# Boeing Alert Service Bulletin 757-53A0099: No revision named

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- Document: [Boeing Alert Service Bulletin 757-53A0099](https://openairdocs.org/service-documents/boeing/757-53a0099.md)
- Title as filed: U.S. DOT/FAA - SB-757-53A0099-00
- Pages: 70
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## Text

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### Page 1

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0099
Original Issue: September 18, 2014
ATA System: 5363
SUBJECT: FUSELAGE - Section 43 and 46 - Structure - Inspection for Cracks in Fuselage Frames
at Stringer S-24 and S-25, Left and Right
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Unpublished Work.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
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: September 18, 2014
757-53A0099
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 3
D. Description .............................................. 1 4
E. Compliance .............................................. 1 4
F. Approval ............................................... 2 1
G. Manpower .............................................. 2 2
H. Weight and Balance Changes .................................... 2 4
I. Electrical Load Data ......................................... 2 4
J. References .............................................. 2 4
1. Existing Data: ......................................... 2 4
2. Data Supplied with this Service Bulletin: ........................... 2 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 5
K. Publications Affected ........................................ 2 5
L. Interchangeability and Intermixability of Parts ........................... 2 5
M. Software Accomplishment Summary ................................ 2 5
2. MATERIAL INFORMATION ........................................ 2 7
A. Material - Price and Availability ................................... 2 7
B. Industry Support Information .................................... 2 7
C. Parts Necessary for Each Airplane ................................. 2 7
1. Kits/Parts ............................................ 2 7
2. Parts and Materials Supplied by the Operator ........................ 2 7
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 1
FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS ......................................... 5 4
FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS - SECTION 43 [Group 1-2, 5-6] ....................... 5 9
APPENDIX A: SCOPE OF INSPECTION [Group 1] ............................. 6 4
APPENDIX B: SCOPE OF INSPECTION  [Group 2] ............................. 6 5
APPENDIX C: SCOPE OF INSPECTION  [Group 3] ............................. 6 6
APPENDIX D: SCOPE OF INSPECTION  [Group 4] ............................. 6 7
APPENDIX E: SCOPE OF INSPECTION [Group 5] ............................. 6 8
APPENDIX F: SCOPE OF INSPECTION [Group 6] ............................. 6 9
APPENDIX G: SCOPE OF INSPECTION [Group 7] ............................. 7 0
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Commercial 
Airplanes
757
Service Bulletin
ALERT
SummaryNumber: 757-53A0099Original Issue: September 18, 2014
ATA System: 5363
SUBJECT: FUSELAGE - Section 43 and 46 - Structure - Inspection for Cracks in Fuselage Frames
at Stringer S-24 and S-25, Left and Right
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
One operator has reported a 0.60 inch long crack in the fuselage frame at Station (STA) 1440, stringer S-24L.
The airplane had 36,890 total flight cycles and 78,922 total flight hours. The crack was discovered while doing
unrelated local repairs. An investigation has determined the crack may have been caused by fatigue. The crack
initiated in the fuselage frame at the corner radius of the fuselage frame opening for the stringer. It continued
to the fastener hole common to fuselage frame, splice plate, and fail safe chord. The crack was not visible
because it was completely hidden by the splice plate on one side and the fail safe chord on the other side. If
this service bulletin is not done, such fatigue cracking could adversely affect the structural integrity of the airplane.
Similar design details and stresses exist at multiple fuselage frame stations in Section 43 and Section 46. This
service bulletin gives instructions to inspect for cracks in the fuselage frames at S-24 and S-25, left and right at
multiple fuselage frame stations.
The fuselage frames have been determined to be structure that is susceptible to Widespread Fatigue Damage
(WFD).
Boeing Service Related Problem (SRP) 757-53-0429 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
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ReferenceAffectedPlanning Data
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
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
This service bulletin gives instructions to do detailed and High Frequency Eddy Current (HFEC) inspections for
cracks in the fuselage frames at the identified Station (STA) locations and Stringer (S) locations.
If any crack is found, contact Boeing for repair instructions and do the repair.
EFFECTIVITY
All 757-200, -200CB, -200PF, -300 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 inspections given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
A LEFT SIDE
RIGHT SIDE
SIDE  SIDE
FRAME  DO DETAILED AND HIGH FREQUENCY EDDY  FRAME
CURRENT (HFEC) INSPECTIONS FOR CRACKS
SPLICE  SPLICE
PLATE  PLATE
S-25R  - S-25L
(SECTION 43)  (SECTION 43)
S-24R  S-24L
(SECTION 46)  (SECTION 46)
INBD  INBD
LOWER  LOWER
TYPICAL FUSELAGE FRAME  FRAME  FRAME  TYPICAL FUSELAGE FRAME
(RIGHT SIDE, VIEW LOOKING AFT)  (LEFT SIDE, VIEW LOOKING AFT)
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Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0099
Original Issue: September 18, 2014
ATA System: 5363
SUBJECT: FUSELAGE - Section 43 and 46 - Structure - Inspection for Cracks in Fuselage Frames
at Stringer S-24 and S-25, Left and Right
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
This service bulletin is for the airplane(s) shown below.
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
757-200 Airplanes with 2 Cargo Doors-1
757-200 Airplanes with 3 Cargo Doors-2
757-200PF Airplanes (Freighter)-3
757-200SF Airplanes (Special Freighter Boeing Supplemental Type
Certificate)
-4
757-300 Airplanes with Cargo Net Support Structure Installation (STA
720-STA 740)
-5
757-300 Airplanes without Cargo Net Support Structure Installation
(STA 720-STA 740)
-6
757-200CB Airplane (Convertible)-7
Airplane Models:
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757-200, 757-200CB, 757-200PF, 757-300
GroupVariable Number
1NA001 - NA028
1NA191 - NA199
4NA201 - NA204
2NA205
4NA206 - NA213
2NA214
4NA215 - NA236
1NA237 - NA239
1NA301 - NA305
2NA341 - NA352
2NA391 - NA399
1NA401 - NA408
1NA441 - NA447
1NA501 - NA586
1NB001 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
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GroupVariable Number
1NB321 - NB331
1NB421 - NB438
1NB446
1NB451 - NB454
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
3NC901 - NC951
3NC971 - NC974
1ND001 - ND007
1ND011 - ND059
1ND111 - ND113
1ND161 - ND199
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
7ND895
1NE001 - NE008
1NE011 - NE088
1NE091 - NE094
1NE141 - NE150
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GroupVariable Number
1NE161 - NE177
1NE201 - NE204
1NE301 - NE302
1NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
5NL001 - NL002
6NL006 - NL017
6NL101 - NL109
6NL141
6NL601 - NL616
1NN001 - NN002
1NN051 - NN052
1NP901 - NP904
3NS601 - NS616
3NT001 - NT009
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
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GroupVariable Number
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT916
1NT971 - NT985
1NU031 - NU038
5NU701 - NU705
5NU721 - NU728
5NU731 - NU732
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
One operator has reported a 0.60 inch long crack in the fuselage frame at Station (STA) 1440, stringer
S-24L. The airplane had 36,890 total flight cycles and 78,922 total flight hours. The crack was discovered
while doing unrelated local repairs. An investigation has determined the crack may have been caused
by fatigue. The crack initiated in the fuselage frame at the corner radius of the fuselage frame opening
for the stringer. It continued to the fastener hole common to fuselage frame, splice plate, and fail safe
chord. The crack was not visible because it was completely hidden by the splice plate on one side and
the fail safe chord on the other side. If this service bulletin is not done, such fatigue cracking could
adversely affect the structural integrity of the airplane.
Similar design details and stresses exist at multiple fuselage frame stations in Section 43 and Section
46. This service bulletin gives instructions to inspect for cracks in the fuselage frames at S-24 and
S-25, left and right at multiple fuselage frame stations.
The fuselage frames have been determined to be structure that is susceptible to Widespread Fatigue
Damage (WFD).
Boeing Service Related Problem (SRP) 757-53-0429 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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D. Description
This service bulletin gives instructions to do detailed and High Frequency Eddy Current (HFEC)
inspections for cracks in the fuselage frames at the identified Station (STA) locations and Stringer (S)
locations.
If any crack is found, contact Boeing for repair instructions and do the repair.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1-2, 4:
Affected Maintenance Zones
ZoneModel
119, 121, 122, 153, 154, 161, 162, 165, 166757-200
Group 3:
Affected Maintenance Zones
ZoneModel
119, 121, 122, 153, 154, 161, 162, 165, 166757-200PF
Group 5-6:
Affected Maintenance Zones
ZoneModel
119, 121, 122, 153, 154, 161, 162, 165, 166757-300
Group 7:
Affected Maintenance Zones
ZoneModel
119, 121, 122, 153, 154, 161, 162, 165, 166757-200CB
E. Compliance
1. 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.
2. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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### Page 15

3. Previously Approved Boeing Frame Repairs Common To Inspection Areas:
a. If any Boeing Organization Designation Authorization (ODA) approved repair via FAA Form
8100-9 interferes with the frame inspection areas in this service bulletin, the operator must
contact Boeing for alternate inspection instructions and do the alternate inspection instructions
before or at the Compliance time outlined in this Service Bulletin (SB).
b. If any Boeing ODA approved repair via FAA Form 8100-9 in the frame inspection area does
not impede inspections under the frame flange per this SB, the operator shall perform the SB
inspections as described in this SB.
4. Any Repair Installed as a Result of Accomplishing this Service Bulletin:
a. If any repair is installed as a result of accomplishing this service bulletin, do the post repair
requirements for the affected repair area in accordance with the Boeing ODA approved repair.
Any remaining requirements of this service bulletin remain fully applicable and must be complied
with.
5. 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.
Group 1:
Table 1: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 24,000 total
flight cycles
Do PART 2: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 3: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 4: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 2: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 1: NO
CRACK FOUND
DURING PART 2
INSPECTIONS
Cycles
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Group 1:
Table 1: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
12,000 Flight--Repeat PART 3: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 2: NO
CRACK FOUND
DURING PART 3
INSPECTIONS
Cycles
12,000 Flight--Repeat PART 4: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 3: NO
CRACK FOUND
DURING PART 4
INSPECTIONS
Cycles
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 4:
ANY CRACK
FOUND
Group 2:
Table 2: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 24,000 total
flight cycles
Do PART 5: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 6: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 7: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 5: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 5: NO
CRACK FOUND
DURING PART 5
INSPECTIONS
Cycles
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### Page 17

Group 2:
Table 2: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
12,000 Flight--Repeat PART 6: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 6: NO
CRACK FOUND
DURING PART 6
INSPECTIONS
Cycles
12,000 Flight--Repeat PART 7: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 7: NO
CRACK FOUND
DURING PART 7
INSPECTIONS
Cycles
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 8:
ANY CRACK
FOUND
Group 3:
Table 3: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 8: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 9: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 8: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 9: NO
CRACK FOUND
DURING PART 8
INSPECTIONS
Cycles
12,000 Flight--Repeat PART 9: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 10:
NO CRACK
FOUND DURING
PART 9 INSPEC-
TIONS
Cycles
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Group 3:
Table 3: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 11:
ANY CRACK
FOUND
Group 4:
Table 4: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 10: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 11: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 10: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 12:
NO CRACK
FOUND DURING
PART 10 INSPEC-
TIONS
Cycles
12,000 Flight--Repeat PART 11: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 13:
NO CRACK
FOUND DURING
PART 11 INSPEC-
TIONS
Cycles
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 14:
ANY CRACK
FOUND
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Group 5:
Table 5: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 24,000 total
flight cycles
Do PART 12: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 13: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 14: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 12: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 15:
NO CRACK
FOUND DURING
PART 12 INSPEC-
TIONS
Cycles
12,000 Flight--Repeat PART 13: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 16:
NO CRACK
FOUND DURING
PART 13 INSPEC-
TIONS
Cycles
12,000 Flight--Repeat PART 14: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 17:
NO CRACK
FOUND DURING
PART 14 INSPEC-
TIONS
Cycles
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 18:
ANY CRACK
FOUND
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Group 6:
Table 6: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 24,000 total
flight cycles
Do PART 15: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 16: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 17: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 15: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 19:
NO CRACK
FOUND DURING
PART 15 INSPEC-
TIONS
Cycles
12,000 Flight--Repeat PART 16: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 20:
NO CRACK
FOUND DURING
PART 16 INSPEC-
TIONS
Cycles
12,000 Flight--Repeat PART 17: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 21:
NO CRACK
FOUND DURING
PART 17 INSPEC-
TIONS
Cycles
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 22:
ANY CRACK
FOUND
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Group 7:
Table 7: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 36,000 total
flight cycles
Do PART 18: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
-Within 6,000 flight
cycles after the
original issue date
of this service bul-
letin
Before 50,000 total
flight cycles
Do PART 19: FUSELAGE
FRAMES - DETAILED AND
HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPEC-
TIONS for cracks.
All Airplanes
12,000 Flight--Repeat PART 18: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 23:
NO CRACK
FOUND DURING
PART 18 INSPEC-
TIONS
Cycles
12,000 Flight--Repeat PART 19: FUSE-
LAGE FRAMES - DE-
TAILED AND HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTIONS for
cracks.
CONDITION 24:
NO CRACK
FOUND DURING
PART 19 INSPEC-
TIONS
Cycles
--Before further flightContact Boeing for repair
instructions and do the re-
pair.
CONDITION 25:
ANY CRACK
FOUND
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.
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G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection 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.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
5.75 (a)23.00 (a)4Part 1 (a)
2.252.251Part 2
3.7515.004Part 3
4.9019.604Part 4
5.7523.004Part 20
22.4082.85TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
4.65 (a)18.60 (a)4Part 1 (a)
2.252.251Part 5
4.9019.604Part 6
4.509.002Part 7
4.6518.604Part 20
20.9568.05TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
4.75 (a)19.00 (a)4Part 1 (a)
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Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
5.0520.204Part 8
3.4013.604Part 9
4.7519.004Part 20
17.9571.80TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
4.75 (a)19.00 (a)4Part 1 (a)
6.5526.204Part 10
3.003.001Part 11
4.7519.004Part 20
19.0567.20TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
5.50 (a)22.00 (a)4Part 1 (a)
1.251.251Part 12
3.9515.804Part 13
4.5018.004Part 14
5.5022.004Part 20
20.7079.05TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
5.50 (a)22.00 (a)4Part 1 (a)
2.252.251Part 15
3.9515.804Part 16
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Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
4.5018.004Part 17
5.5022.004Part 20
21.7080.05TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
Group 7:
Elapsed HoursTask HoursNumber of PersonsTask
5.10 (a)20.40 (a)4Part 1 (a)
5.2521.004Part 18
5.2510.502Part 19
5.1020.404Part 20
20.7072.30TOTAL FOR EACH AIRPLANE
(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access
information. More task hours will be required at these locations.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 757-SL-51-022
b. Boeing Service Related Problem (SRP) 757-53-0429
c. Service Bulletin Index D624N001
d. 757 Aircraft Maintenance Manual (AMM) 06-41-00, 25-50-02, 25-50-07
e. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19
f. 757-200 Structural Repair Manual (SRM) 53-30-07, 53-60-07
g. 757-200CB Structural Repair Manual (SRM) 53-30-07, 53-60-07
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h. 757-200PF Structural Repair Manual (SRM) 53-30-07, 53-60-07
i. 757-300 Structural Repair Manual (SRM) 53-30-07, 53-60-07
j. Multi Operator Message, MOM-MOM-13-0823-01B
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Frame Instl Body Station 1440146N1013
Frame Detail - Body Station 1200 - 1440146N1028
Net Support Structure Instl - Fwd Cargo Compartment451N5130
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 but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 27

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspections given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 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 757 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 757
Airplane Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
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7. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
8. Refer to APPENDIX A to APPENDIX G for Scope of Inspection. The diagrams are
provided as aids 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.
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. 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.
14. Refer to Multi Operator Message, MOM-MOM-13-0823-01B, for information on the
Retention of Failed/Discrepant Part for Boeing Evaluation. It is requested that an
operator or repair station retain any failed or discrepant parts for possible examination
or analysis by Boeing when doing this Service Bulletin.
15. Previously Approved Boeing Frame Repairs Common To Inspection Areas:
— If any Boeing Organization Designation Authorization (ODA) approved repair
via FAA Form 8100-9 interferes with the frame inspection areas in this service
bulletin, the operator must contact Boeing for alternate inspection instructions
and do the alternate inspection instructions before or at the Compliance time
outlined in this Service Bulletin (SB).
— If any Boeing ODA approved repair via FAA Form 8100-9 in the frame inspection
area does not impede inspections under the frame flange per this SB, the
operator shall perform the SB inspections as described in this SB.
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16. Any Repair Installed as a Result of Accomplishing this Service Bulletin:
– If any repair is installed as a result of accomplishing this service bulletin, do the
post repair requirements for the affected repair area in accordance with the
Boeing ODA approved repair. Any remaining requirements of this service bulletin
remain fully applicable and must be complied with.
17. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
18. 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.
B. WORK INSTRUCTIONS
The table below defines the PART requirements by Group.
PARTGroup
1, 2, 3, 4, 201
1, 5, 6, 7, 202
1, 8, 9, 203
1, 10, 11, 204
1, 12, 13, 14, 205
1, 15, 16, 17, 206
1, 18, 19, 207
Group 1:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 2: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 3: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
4. RC - Do PART 4: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
5. RC - Based upon the detailed and HFEC inspection results from accomplishing PART 2, PART
3, or PART 4, do the following:
a. CONDITION 1: NO CRACK FOUND DURING PART 2 INSPECTIONS
(1) RC - Repeat PART 2: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
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b. CONDITION 2: NO CRACK FOUND DURING PART 3 INSPECTIONS
(1) RC - Repeat PART 3: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
c. CONDITION 3: NO CRACK FOUND DURING PART 4 INSPECTIONS
(1) RC - Repeat PART 4: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
d. CONDITION 4 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
6. Do PART 20: CLOSE ACCESS.
Group 2:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 5: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 6: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
4. RC - Do PART 7: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
5. RC - Based upon the detailed and HFEC inspection results from accomplishing PART 5, PART
6, or PART 7, do the following:
a. CONDITION 5: NO CRACK FOUND DURING PART 5 INSPECTIONS
(1) RC - Repeat PART 5: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
b. CONDITION 6: NO CRACK FOUND DURING PART 6 INSPECTIONS
(1) RC - Repeat PART 6: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
c. CONDITION 7: NO CRACK FOUND DURING PART 7 INSPECTIONS
(1) RC - Repeat PART 7: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
d. CONDITION 8 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
6. Do PART 20: CLOSE ACCESS.
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Group 3:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 8: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 9: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
4. RC - Based upon the detailed and HFEC inspection results from accomplishing PART 8 or PART
9, do the following:
a. CONDITION 9: NO CRACK FOUND DURING PART 8 INSPECTIONS
(1) RC - Repeat PART 8: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
b. CONDITION 10: NO CRACK FOUND DURING PART 9 INSPECTIONS
(1) RC - Repeat PART 9: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
c. CONDITION 11 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
5. Do PART 20: CLOSE ACCESS.
Group 4:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 10: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 11: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
4. RC - Based upon the inspection results from accomplishing PART 10 or PART 11, do the following:
a. CONDITION 12: NO CRACK FOUND DURING PART 10 INSPECTIONS
(1) RC - Repeat PART 10: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
b. CONDITION 13: NO CRACK FOUND DURING PART 11 INSPECTIONS
(1) RC - Repeat PART 11: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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c. CONDITION 14 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
5. Do PART 20: CLOSE ACCESS.
Group 5:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 12: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 13: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
4. RC - Do PART 14: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
5. RC - Based upon the inspection results from accomplishing PART 12, PART 13, or PART 14, do
the following:
a. CONDITION 15: NO CRACK FOUND DURING PART 12 INSPECTIONS
(1) RC - Repeat PART 12: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
b. CONDITION 16: NO CRACK FOUND DURING PART 13 INSPECTIONS
(1) RC - Repeat PART 13: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
c. CONDITION 17: NO CRACK FOUND DURING PART 14 INSPECTIONS
(1) RC - Repeat PART 14: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
d. CONDITION 18 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
6. Do PART 20: CLOSE ACCESS.
Group 6:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 15: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 16: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
Export Controlled ECCN: 9E991 - BOEING
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### Page 35

4. RC - Do PART 17: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
5. RC - Based upon the inspection results from accomplishing PART 15, PART 16, or PART 17, do
the following:
a. CONDITION 19: NO CRACK FOUND DURING PART 15 INSPECTIONS
(1) RC - Repeat PART 15: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
b. CONDITION 20: NO CRACK FOUND DURING PART 16 INSPECTIONS
(1) RC - Repeat PART 16: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
c. CONDITION 21: NO CRACK FOUND DURING PART 17 INSPECTIONS
(1) RC - Repeat PART 17: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
d. CONDITION 22 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
6. Do PART 20: CLOSE ACCESS.
Group 7:
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 18: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
3. RC - Do PART 19: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS for cracks.
4. RC - Based upon the inspection results from accomplishing PART 18 or PART 19, do the following:
a. CONDITION 23: NO CRACK FOUND DURING PART 18 INSPECTIONS
(1) RC - Repeat PART 18: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
b. CONDITION 24: NO CRACK FOUND DURING PART 19 INSPECTIONS
(1) RC - Repeat PART 19: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTIONS for cracks.
c. CONDITION 25 - ANY CRACK FOUND
(1) RC - Contact Boeing for repair instructions and do the repair.
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### Page 36

5. Do PART 20: CLOSE ACCESS.
PART 1: OPEN ACCESS
1. Get access to the fuselage frame inspection areas as follows:
a. Remove and keep the cargo compartment sidewall linings. Refer to 757 AMM 25-50-02 as
an accepted procedure.
b. Remove and keep the cargo compartment insulation. Refer to 757 AMM 25-50-07 as an
accepted procedure.
c. Open Main Equipment Center (MEC) access door 119BL. Refer to 757 AMM 06-41-00 as an
accepted procedure.
d. An inquiry was done with an operator to obtain additional access information. The results
indicate that operators should consider planning for additional work and time when gaining
access to the following areas:
Access IssueThreshold
(Total Flight Cycles)
LocationGroup
Ducts and Hoses36,000Right Side, STA 1660 to STA 17011-2, 4-7
Electrical Wire Bundles/Ducts50,000Left Side, STA 5001-3, 5-7
Avionics Rack/Equipment50,000Right Side, STA 4404
P36 Electrical Panel50,000Right Side, STA 500 to STA 5201-2, 4
E6 Aft Equipment Rack (a)50,000Right Side, STA 14801,3, 5-7
Ducts and Hoses50,000Right Side, STA 1660 to STA 17013
(a) Depending on customer configuration, the E6 Aft Equipment Rack may not be installed at this location.
Group 1:
PART 2: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 560, S-25LFuselage FrameInspect
Compartment, Left SideSTA 580, S-25L
STA 600, S-25L
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### Page 37

Group 1:
PART 3: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 640, S-25LFuselage FrameInspect
Compartment, Left SideSTA 660, S-25L
STA 680, S-25L
STA 700, S-25L
STA 720, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
Forward Cargo1STA 660, S-25R
Compartment, Right SideSTA 680, S-25R
STA 700, S-25R
STA 720, S-25R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
2 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 620, S-25LFuselage FrameInspect
Compartment, Left Side
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### Page 38

Group 1:
PART 4: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Left Side
1STA 500, S-25LFuselage FrameInspect
Forward Cargo1STA 520, S-25L
Compartment, Left SideSTA 540, S-25L
STA 740, S-25L
STA 760, S-25L
STA 780, S-25L
Bulk Cargo Compartment,
Left Side
1STA 1520, S-24L
STA 1540, S-24L
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Main Equipment Center,
Right Side
1STA 480, S-25R
STA 500, S-25R
Forward Cargo1STA 520, S-25R
Compartment, Right SideSTA 740, S-25R
STA 760, S-25R
STA 780, S-25R
Aft Cargo Compartment,
Right Side
1STA 1480, S-24R
Bulk Cargo Compartment,
Right Side
1STA 1500, S-24R
STA 1520, S-24R
STA 1540, S-24R
STA 1560, S-24R
STA 1580, S-24R
STA 1600, S-24R
STA 1620, S-24R
Export Controlled ECCN: 9E991 - BOEING
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### Page 39

Group 2:
PART 5: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 560, S-25LFuselage FrameInspect
Compartment, Left SideSTA 580, S-25L
STA 600, S-25L
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### Page 40

Group 2:
PART 6: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 640, S-25LFuselage FrameInspect
Compartment, Left SideSTA 660, S-25L
STA 680, S-25L
STA 700, S-25L
STA 720, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
STA 1520, S-24L
STA 1540, S-24L
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
Forward Cargo1STA 660, S-25R
Compartment, Right SideSTA 680, S-25R
STA 700, S-25R
STA 720, S-25R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
Export Controlled ECCN: 9E991 - BOEING
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### Page 41

2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
2 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 620, S-25LFuselage FrameInspect
Compartment, Left Side
Group 2:
PART 7: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Left Side
1STA 500, S-25LFuselage FrameInspect
Forward Cargo1STA 520, S-25L
Compartment, Left SideSTA 540, S-25L
STA 740, S-25L
STA 760, S-25L
STA 780, S-25L
Main Equipment Center,
Right Side
1STA 480, S-25R
STA 500, S-25R
Forward Cargo1STA 520, S-25R
Compartment, Right SideSTA 740, S-25R
STA 760, S-25R
STA 780, S-25R
Export Controlled ECCN: 9E991 - BOEING
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### Page 42

Group 3:
PART 8: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Left Side
1STA 500, S-25LFuselage FrameInspect
Forward Cargo1STA 520, S-25L
Compartment, Left SideSTA 540, S-25L
STA 560, S-25L
STA 580, S-25L
STA 600, S-25L
STA 660, S-25L
STA 680, S-25L
STA 700, S-25L
STA 720, S-25L
STA 740, S-25L
STA 760, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
STA 1520, S-24L
Forward Cargo1STA 660, S-25R
Compartment, Right SideSTA 680, S-25R
STA 700, S-25R
STA 720, S-25R
STA 740, S-25R
STA 760, S-25R
Export Controlled ECCN: 9E991 - BOEING
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### Page 43

Group 3:
PART 9: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Bulk Cargo Compartment,
Left Side
1STA 1540, S-24LFuselage FrameInspect
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
STA 1701, S-24L
Aft Cargo Compartment,
Right Side
1STA 1480, S-24R
Bulk Cargo Compartment,
Right Side
1STA 1500, S-24R
STA 1520, S-24R
STA 1540, S-24R
STA 1560, S-24R
STA 1580, S-24R
STA 1600, S-24R
STA 1620, S-24R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
STA 1701, S-24R
Export Controlled ECCN: 9E991 - BOEING
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### Page 44

Group 4:
PART 10: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 520, S-25LFuselage FrameInspect
Compartment, Left SideSTA 540, S-25L
STA 560, S-25L
STA 580, S-25L
STA 600, S-25L
STA 660, S-25L
STA 680, S-25L
STA 700, S-25L
STA 720, S-25L
STA 740, S-25L
STA 760, S-25L
STA 780, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
STA 1520, S-24L
STA 1540, S-24L
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
Export Controlled ECCN: 9E991 - BOEING
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### Page 45

LocationQtyStation (STA) and Stringer (S)
Location
NameTask
STA 660, S-25R Forward Cargo
Compartment, Right Side
1
STA 680, S-25R
STA 700, S-25R
STA 720, S-25R
STA 740, S-25R
STA 760, S-25R
STA 780, S-25R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
Group 4:
PART 11: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Right Side
1STA 440, S-25RFuselage FrameInspect
STA 480, S-25R
STA 500, S-25R
Forward Cargo1STA 520, S-25R
Compartment, Right Side
Group 5:
PART 12: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 560, S-25LFuselage FrameInspect
Compartment, Left SideSTA 580, S-25L
STA 600, S-25L
Export Controlled ECCN: 9E991 - BOEING
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### Page 46

Group 5:
PART 13: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 640, S-25LFuselage FrameInspect
Compartment, Left SideSTA 660, S-25L
STA 680, S-25L
STA 700, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
STA 1520, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
Forward Cargo1STA 660, S-25R
Compartment, Right SideSTA 680, S-25R
STA 700, S-25R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
2 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 620, S-25LFuselage FrameInspect
Compartment, Left SideSTA 720, S-25L
Forward Cargo1STA 720, S-25R
Compartment, Right Side
Export Controlled ECCN: 9E991 - BOEING
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### Page 47

Group 5:
PART 14: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Left Side
1STA 500, S-25LFuselage FrameInspect
Forward Cargo1STA 520, S-25L
Compartment, Left SideSTA 540, S-25L
STA 740, S-25L
STA 760, S-25L
STA 780, S-25L
STA 780+20, S-25L
Bulk Cargo Compartment,
Left Side
1STA 1540, S-24L
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Forward Cargo1STA 740, S-25R
Compartment, Right SideSTA 760, S-25R
STA 780, S-25R
STA 780+20, S-25R
Aft Cargo Compartment,
Right Side
1STA 1480, S-24R
Bulk Cargo Compartment,
Right Side
1STA 1500, S-24R
STA 1520, S-24R
STA 1540, S-24R
STA 1560, S-24R
STA 1580, S-24R
STA 1600, S-24R
STA 1620, S-24R
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 48

Group 6:
PART 15: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 560, S-25LFuselage FrameInspect
Compartment, Left SideSTA 580, S-25L
STA 600, S-25L
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ALERTALERT

### Page 49

Group 6:
PART 16: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 640, S-25LFuselage FrameInspect
Compartment, Left SideSTA 660, S-25L
STA 680, S-25L
STA 700, S-25L
STA 720, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
STA 1520, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
Forward Cargo1STA 660, S-25R
Compartment, Right SideSTA 680, S-25R
STA 700, S-25R
STA 720, S-25R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
2 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Forward Cargo1STA 620, S-25LFuselage FrameInspect
Compartment, Left Side
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-53A0099
ALERTALERT

### Page 50

Group 6:
PART 17: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Left Side
1STA 500, S-25LFuselage FrameInspect
Forward Cargo1STA 520, S-25L
Compartment, Left SideSTA 540, S-25L
STA 740, S-25L
STA 760, S-25L
STA 780, S-25L
STA 780+20, S-25L
Bulk Cargo Compartment,
Left Side
1STA 1540, S-24L
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Forward Cargo1STA 740, S-25R
Compartment, Right SideSTA 760, S-25R
STA 780, S-25R
STA 780+20, S-25R
Aft Cargo Compartment,
Right Side
1STA 1480, S-24R
Bulk Cargo Compartment,
Right Side
1STA 1500, S-24R
STA 1520, S-24R
STA 1540, S-24R
STA 1560, S-24R
STA 1580, S-24R
STA 1600, S-24R
STA 1620, S-24R
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 18, 2014
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BOEING SERVICE BULLETIN 757-53A0099
ALERTALERT

### Page 51

Group 7:
PART 18: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Main Equipment Center,
Left Side
1STA 500, S-25LFuselage FrameInspect
Forward Cargo1STA 520, S-25L
Compartment, Left SideSTA 540, S-25L
STA 560, S-25L
STA 580, S-25L
STA 600, S-25L
STA 660, S-25L
STA 680, S-25L
STA 700, S-25L
STA 720, S-25L
STA 740, S-25L
STA 760, S-25L
Aft Cargo Compartment,
Left Side
1STA 1360, S-24L
STA 1380, S-24L
STA 1400, S-24L
STA 1420, S-24L
STA 1440, S-24L
STA 1460, S-24L
STA 1480, S-24L
Bulk Cargo Compartment,
Left Side
1STA 1500, S-24L
Area Aft of Bulk Cargo
Compartment, Left Side
1STA 1661, S-24L
Forward Cargo1STA 660, S-25R
Compartment, Right SideSTA 680, S-25R
STA 700, S-25R
STA 720, S-25R
STA 740, S-25R
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: September 18, 2014
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BOEING SERVICE BULLETIN 757-53A0099
ALERTALERT

### Page 52

LocationQtyStation (STA) and Stringer (S)
Location
NameTask
STA 760, S-25R
Area Aft of Bulk Cargo
Compartment, Right Side
1STA 1661, S-24R
Group 7:
PART 19: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE
1 at the Station (STA) and Stringer (S) locations that follow:
LocationQtyStation (STA) and Stringer (S)
Location
NameTask
Bulk Cargo Compartment,
Left Side
1STA 1520, S-24LFuselage FrameInspect
STA 1540, S-24L
STA 1560, S-24L
STA 1580, S-24L
STA 1600, S-24L
STA 1620, S-24L
Aft Cargo Compartment,
Right Side
1STA 1480, S-24R
Bulk Cargo Compartment,
Right Side
1STA 1500, S-24R
STA 1520, S-24R
STA 1540, S-24R
STA 1560, S-24R
STA 1580, S-24R
STA 1600, S-24R
STA 1620, S-24R
PART 20: CLOSE ACCESS
1. Close access to the fuselage frame inspection areas as follows:
a. Install kept cargo compartment insulation. Refer to 757 AMM 25-50-07 as an accepted
procedure.
b. Install kept cargo compartment sidewall linings. Refer to 757 AMM 25-50-02 as an accepted
procedure.
c. Close Main Equipment Center (MEC) access door 119BL. Refer to 757 AMM 06-41-00 as an
accepted procedure.
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ALERTALERT

### Page 53

d. Close up any areas that required additional work to gain access.
2. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: September 18, 2014
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BOEING SERVICE BULLETIN 757-53A0099
ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
SIDE FRAME
LEFT SIDE
RIGHT SIDE
SPLICE PLATE
- S-25L
(SECTION 43)
S-24L
(SECTION 46)
SIDE FRAME
SPLICE PLATE
LOWER FRAME
TYPICAL FUSELAGE FRAME
(LEFT SIDE, VIEW LOOKING AFT)
TYPICAL
CRACK
INBD
LOWER FRAME
FWD
VIEW LOOKING AFT
S-25L
(SECTION 43)  S-24L  2298095
(SECTION 46)
FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
(SHEET 1 OF 5)
Original Issue: September 18, 2014
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  757-53A0099
Work - See page 1 for details.  54 of 70

### Page 55 (OCR)

BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
- FAIL SAFE CHORD
SIDE FRAME
DETAILED AND HFEC
INSPECTION AREA
B
SPLICE PLATE
LOWER FRAME
S-25L
(SECTION 43)
S-24L
(SECTION 46)
INBD
DETAILED  TYPICAL FUSELAGE FRAME
INSPECTION  (LEFT SIDE, VIEW LOOKING FORWARD)
A-A
HFEC INSPECTION ( 1  SPLICE PLATE
A DETAILED AND HFEC  INSPECTION AREA
FAIL SAFE
CHORD
FWD
SIDE FRAME
B-B  2296867
FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
(SHEET 2 OF 5)
Original Issue: September 18, 2014  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  757-53A0099  55 of 70

### Page 56 (OCR)

BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
SIDE FRAME
- SPLICE PLATE
S-25R -
(SECTION 43)
S-24R
(SECTION 46)
SIDE FRAME
SPLICE PLATE
LOWER FRAME
TYPICAL FUSELAGE FRAME
(RIGHT SIDE, VIEW LOOKING AFT)
TYPICAL
CRACK
INBD
LOWER FRAME
FWD
VIEW LOOKING AFT
S-25R
(SECTION 43)  2306511
S-24R
(SECTION 46)
FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
(SHEET 3 OF 5)
Original Issue: September 18, 2014
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  757-53A0099
Work - See page 1 for details.  56 of 70

### Page 57 (OCR)

BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
FAIL SAFE CHORD
SIDE FRAME
DETAILED AND HFEC
INSPECTION AREA
SPLICE PLATE  ·* K
LOWER FRAME
S-25R
(SECTION 43)
S-24R
(SECTION 46)
INBD
TYPICAL FUSELAGE FRAME  DETAILED
(RIGHT SIDE, VIEW LOOKING FORWARD)  INSPECTION
C-C
) HFEC INSPECTION
SPLICE PLATE
• INSPECTION AREA  • DETAILED AND HFEC  FAIL SAFE  NI
CHORD  B
FWD
SIDE FRAME
D-D  2306789
FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
(SHEET 4 OF 5)
Original Issue: September 18, 2014
Export Controlled ECCN: 9E991 - BOEING  757-53A0099
PROPRIETARY - Copyright © Unpublished
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### Page 58

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) (b) (c)--FUSELAGE FRAMEInspect1
(a) Do a Detailed and High Frequency Eddy Current (HFEC) for cracks in accordance with 757 NDT Manual
Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. HFEC inspection is to be done around the fasteners
and on the fuselage frame along the upper edge of the fail safe chord.
(b) For fuselage frame identification in Section 43, refer to 757-200 SRM 53-30-07, 757-200CB SRM 53-30-
07, 757-200PF SRM 53-30-07, 757-300 SRM 53-30-07.
(c) For fuselage frame identification in Section 46, refer to 757-200 SRM 53-60-07, 757-200CB SRM 53-60-
07, 757-200PF SRM 53-60-07, 757-300 SRM 53-60-07.
FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-53A0099
ALERTALERT

### Page 59 (OCR)

BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
This Figure applies only to: Group 1-2, 5-6.
SIDE FRAME
LEFT SIDE
RIGHT SIDE
SPLICE PLATE
S-25L
SIDE FRAME
SPLICE PLATE
LOWER FRAME
tYPICAL FUSELAGE FRAME
LEFT SIDE. VIEW LOOKING AFT
TYPICAL
CRACK
NBD
LOWER FRAME
FWD
VIEW LOOKING AFT
S-25L
1092622
FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS - SECTION 43
(SHEET 1 OF 5)
Original Issue: September 18, 2014
Export Controlled ECCN: 9E991 - BOEING  757-53A0099
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  59 of 70

### Page 60 (OCR)

BOEING SERVICE BULLETIN 757-53A0099
ALERT  ALERT
FAIL SAFE CHORD
SIDE FRAME
• DETAILED AND HFEC
INSPECTION AREA
CARGO NET  SPLICE PLATE
SUPPORT TEE •
B
LOWER FRAME
S-25L
INBD
DETAILED  AND HFEC  TYPICAL FUSELAGE FRAME  (VIEW LOOKING FORWARD)
INSPECTION  A-A
SPLICE PLATE
CARGO NET
SUPPORT TEE  VIA PETECTION A HEEC
FAIL SAFE
D  CHORD
FWD
SIDE FRAME
B-B  2297602
FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTIONS - SECTION 43
(SHEET 2 OF 5)
Original Issue: September 18, 2014
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  757-53A0099
Work - See page 1 for details.  60 of 70

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