# Boeing Alert Service Bulletin 757-53A0115: No revision named

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- Title as filed: 757-53A0115 RB(reducedsizepdf)
- Pages: 290
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## Text

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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0115 RB
Original Issue: January 25, 2022
ATA System: 5333 5363
SUBJECT: FUSELAGE - Sections 43 and 46 - S-13 to S-14 Fuselage Frame Splice Inspection
EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations
(EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for
export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per
Supp.1 to Part 740 of the EAR.
9E991ECCN:
Copyright © 2022 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Unpublished Work.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: January 25, 2022
757-53A0115 RB
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2.0

### Page 2

Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 25, 2022
757-53A0115 RB
2 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60
FIGURE 1: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - LEFT SIDE [Group 1-2] . . . . . . . . . . . . . . . . . . . . 116
FIGURE 2: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - RIGHT SIDE [Group 1-2] . . . . . . . . . . . . . . . . . . . 122
FIGURE 3: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - LEFT SIDE [Group 3] . . . . . . . . . . . . . . . . . . . . . 128
FIGURE 4: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - RIGHT SIDE [Group 3] . . . . . . . . . . . . . . . . . . . . 135
FIGURE 5: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - LEFT SIDE [Group 4] . . . . . . . . . . . . . . . . . . . . . 142
FIGURE 6: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - RIGHT SIDE [Group 4] . . . . . . . . . . . . . . . . . . . . 149
FIGURE 7: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - LEFT SIDE [Group 5] . . . . . . . . . . . . . . . . . . . . . 156
FIGURE 8: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - RIGHT SIDE [Group 5] . . . . . . . . . . . . . . . . . . . . 163
FIGURE 9: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - LEFT SIDE [Group 6] . . . . . . . . . . . . . . . . . . . . . 170
FIGURE 10: GENERAL VISUAL INSPECTION - FUSELAGE FRAME SPLICES BETWEEN S-13 AND S-14
IN SECTIONS 43 AND 46 - RIGHT SIDE [Group 6] . . . . . . . . . . . . . . . . . . . . 176
FIGURE 11: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - UPPER FRAMES AT FUSELAGE
FRAME SPLICES BETWEEN S-13 AND S-14 IN SECTION 43 - LEFT SIDE [Group 1-3] . 182
FIGURE 12: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AT FUSELAGE FRAME SPLICES BETWEEN S-13
AND S-14 IN SECTION 46 - LEFT SIDE [Group 1-2, 6] . . . . . . . . . . . . . . . . . . 186
FIGURE 13: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - UPPER FRAMES AT FUSELAGE
FRAME SPLICES BETWEEN S-13 AND S-14 IN SECTION 43 - RIGHT SIDE [Group 1-3, 5-6]
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 194
FIGURE 14: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AT FUSELAGE FRAME SPLICES BETWEEN S-13
AND S-14 IN SECTION 46 - RIGHT SIDE [Group 1] . . . . . . . . . . . . . . . . . . . . 200
FIGURE 15: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AT FUSELAGE FRAME SPLICES BETWEEN S-13
AND S-14 IN SECTION 46 - RIGHT SIDE [Group 2, 6] . . . . . . . . . . . . . . . . . . . 210
FIGURE 16: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - UPPER FRAMES AT FUSELAGE
FRAME SPLICES BETWEEN S-13 AND S-14 IN SECTION 46 - LEFT SIDE [Group 3, 5] .220
FIGURE 17: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - UPPER FRAMES AT FUSELAGE
FRAME SPLICES BETWEEN S-13 AND S-14 IN SECTION 46 - RIGHT SIDE [Group 3, 5] .225
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Original Issue: January 25, 2022
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REQUIREMENTS BULLETIN 757-53A0115
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FIGURE 18: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AND SPLICE DOUBLER AT FUSELAGE FRAME
SPLICES BETWEEN S-13 AND S-14 IN SECTION 43 - LEFT SIDE [Group 4] . . . . . . 232
FIGURE 19: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AT FUSELAGE FRAME SPLICES BETWEEN S-13
AND S-14 IN SECTION 46 - LEFT SIDE [Group 4] . . . . . . . . . . . . . . . . . . . . . 241
FIGURE 20: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- UPPER FRAMES AT FUSELAGE
FRAME SPLICES BETWEEN S-13 AND S-14 IN SECTION 43 - RIGHT SIDE [Group 4] . 253
FIGURE 21: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AT FUSELAGE FRAME SPLICES BETWEEN S-13
AND S-14 IN SECTION 46 - RIGHT SIDE [Group 4] . . . . . . . . . . . . . . . . . . . . 259
FIGURE 22: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AND SPLICE DOUBLER AT FUSELAGE FRAME
SPLICES BETWEEN S-13 AND S-14 IN SECTION 43 - LEFT SIDE [Group 5] . . . . . . 273
FIGURE 23: HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS - UPPER FRAMES AND SPLICE DOUBLER AT FUSELAGE FRAME
SPLICES BETWEEN S-13 AND S-14 IN SECTION 43 - LEFT SIDE [Group 6] . . . . . . 282
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 25, 2022
757-53A0115 RB
4 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 5

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0115 RB
Original Issue: January 25, 2022
ATA System: 5333 5363
SUBJECT: FUSELAGE - Sections 43 and 46 - S-13 to S-14 Fuselage Frame Splice Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN
(RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL
TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB
WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. Effectivity
A. Airplanes
This bulletin is applicable to 757-200, 757-200CB, 757-200PF Airplane(s), line number(s) 1-803,
805-809, 811-817, 819-838, 840-845, 847-848, 850-854, 856-905, 907-908, 910-911, 913-914,
916-917, 919-922, 924-925, 927-928, 930-959, 961-962, 964-971, 973-975, 977, 979, 981-984,
986-989, 991-994, 996, 998, 1000, 1002, 1005-1006, 1009-1013, 1015-1016, 1026, 1028-1029,
1041, 1044-1050 in 6 Group(s). Where the effectivity is presented with hyphens between line
numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers 1-9 means
line numbers 1 through 9 inclusive.
The Variable Numbers and Group Information for the applicable airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
757-200 Airplanes, with 4 doors and 2 lower cargo doors.- 1
757-200 Airplanes, with 4 doors and 3 lower cargo doors.- 2
757-200 Airplanes, with overwing emergency exits.- 3
757-200PF Airplanes.- 4
757-200CB Airplane.- 5
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DESCRIPTIONCONFIGURATIONGROUP
757-200 Airplanes that have incorporated STC ST00916WI-D (Special
Freighter Conversion).
- 6
Airplane Models:
757-200, 757-200CB, 757-200PF
GroupVariable Number
1NA001 - NA028
1NA191 - NA199
6NA201 - NA204
2NA205
6NA206 - NA213
2NA214
6NA215 - NA236
1NA237 - NA239
1NA301 - NA305
2NA341 - NA352
2NA391 - NA399
1NA401 - NA408
1NA441 - NA447
3NA501 - NA586
3NB001 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
1NB221 - NB228
1NB230
GroupVariable Number
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
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
4NC901 - NC951
4NC971 - NC974
3ND001 - ND007
3ND011 - ND059
GroupVariable Number
3ND111 - ND113
3ND161 - ND199
3ND201 - ND203
3ND221 - ND225
3ND241 - ND248
3ND301 - ND322
3ND401
3ND891
5ND895
3NE001 - NE008
3NE011 - NE088
3NE091 - NE094
3NE141 - NE150
3NE161 - NE177
3NE201 - NE204
3NE301 - NE302
3NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
3NN001 - NN002
3NN051 - NN052
1NP901 - NP904
4NS601 - NS616
4NT001 - NT009
1NT201 - NT202
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GroupVariable Number
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
GroupVariable Number
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
GroupVariable Number
1NT446
3NT701 - NT769
3NT791 - NT796
3NT861 - NT862
3NT881 - NT885
3NT901 - NT916
3NT971 - NT985
3NU031 - NU038
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 757-53A0115 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-53A0115 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 10, in accordance
with Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that
CONDITION or OPTION.
Group 1-2:
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13L and S-
14L in Sections 43 and 46 for
any repair.
All airplanes
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### Page 8

Group 1-2:
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 1 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 1:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 1 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 43 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 1.1 (ACTION 1):CONDITION 1.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 1.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
CONDITION 1.2:
NO CRACK FOUND
IN SECTION 43
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### Page 9

Group 1-2:
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 2 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 2:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 2 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack
in the unrepaired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 2 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 46 for any
crack in the unrepaired frame.
-Before further flight.CONDITION 2.1 (ACTION 1):CONDITION 2.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 2.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
3,000 flight cycles.-CONDITION 2.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
Export Controlled ECCN: 9E991
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Original Issue: January 25, 2022
757-53A0115 RB
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REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 10

Group 1-2:
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 2.2 (ACTION 1):CONDITION 2.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 2.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
CONDITION 3:
NO REPAIR
FOUND IN SEC-
TION 43
-Before further flight.CONDITION 3.1 (ACTION 1):CONDITION 3.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 3.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
CONDITION 3.2:
NO CRACK FOUND
IN SECTION 43
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Original Issue: January 25, 2022
757-53A0115 RB
10 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 11

Group 1-2:
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 4 (ACTION 1):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack.
CONDITION 4:
NO REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 4 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 46 for any
crack.
-Before further flight.CONDITION 4.1 (ACTION 1):CONDITION 4.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 4.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
3,000 flight cycles.-CONDITION 4.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
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Original Issue: January 25, 2022
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### Page 12

Group 1-2:
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 4.2 (ACTION 1):CONDITION 4.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 4.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
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757-53A0115 RB
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ALERTALERT

### Page 13

Group 1-2:
Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13R and S-
14R in Sections 43 and 46 for
any repair.
All airplanes
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 5 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 5:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 5 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 5.1 (ACTION 1):CONDITION 5.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 5.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 5.2:
NO CRACK FOUND
IN SECTION 43
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### Page 14

Group 1-2:
Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 6 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 6:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 6 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack
in the unrepaired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 6 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13R
and S-14R in Section 46 for any
crack in the unrepaired frame.
-Before further flight.CONDITION 6.1 (ACTION 1):CONDITION 6.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 6.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
3,000 flight cycles.-CONDITION 6.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
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### Page 15

Group 1-2:
Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 6.2 (ACTION 1):CONDITION 6.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 6.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack.
CONDITION 7:
NO REPAIR
FOUND IN SEC-
TION 43
-Before further flight.CONDITION 7.1 (ACTION 1):CONDITION 7.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 7.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 7.2:
NO CRACK FOUND
IN SECTION 43
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### Page 16

Group 1-2:
Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 8 (ACTION 1):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack.
CONDITION 8:
NO REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 8 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13R
and S-14R in Section 46 for any
crack.
-Before further flight.CONDITION 8.1 (ACTION 1):CONDITION 8.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 8.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
3,000 flight cycles.-CONDITION 8.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
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### Page 17

Group 1-2:
Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 8.2 (ACTION 1):CONDITION 8.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 8.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Export Controlled ECCN: 9E991
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Original Issue: January 25, 2022
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REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 18

Group 3:
Table 3: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13L and S-
14L in Sections 43 and 46 for
any repair.
All airplanes
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 9 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 9:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 9 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 43 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 9.1 (ACTION 1):CONDITION 9.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 9.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
CONDITION 9.2:
NO CRACK FOUND
IN SECTION 43
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### Page 19

Group 3:
Table 3: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 10 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 10:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 10 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 10.1 (ACTION 1):CONDITION 10.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 10.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
3,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
CONDITION 10.2:
NO CRACK FOUND
IN SECTION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
CONDITION 11:
NO REPAIR
FOUND IN SEC-
TION 43
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### Page 20

Group 3:
Table 3: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 11.1 (ACTION 1):CONDITION 11.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 11.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 43 for
any crack. (a)
CONDITION 11.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack.
CONDITION 12:
NO REPAIR
FOUND IN SEC-
TION 46
-Before further flight.CONDITION 12.1 (ACTION 1):CONDITION 12.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 12.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
3,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
CONDITION 12.2:
NO CRACK FOUND
IN SECTION 46
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### Page 21

Group 3:
Table 3: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 3:
Table 4: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13R and S-
14R in Sections 43 and 46 for
any repair.
All airplanes
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 13 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 13:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 13 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack
in the unrepaired frames.
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ALERTALERT

### Page 22

Group 3:
Table 4: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 13.1 (ACTION 1):CONDITION 13.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 13.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 13.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 14 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 14:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 14 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 14.1 (ACTION 1):CONDITION 14.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 14.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
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### Page 23

Group 3:
Table 4: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
CONDITION 14.2:
NO CRACK FOUND
IN SECTION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack.
CONDITION 15:
NO REPAIR
FOUND IN SEC-
TION 43
-Before further flight.CONDITION 15.1 (ACTION 1):CONDITION 15.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 15.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 15.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack.
CONDITION 16:
NO REPAIR
FOUND IN SEC-
TION 46
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### Page 24

Group 3:
Table 4: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 16.1 (ACTION 1):CONDITION 16.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 16.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
3,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
CONDITION 16.2:
NO CRACK FOUND
IN SECTION 46
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13L and S-
14L in Sections 43 and 46 for
any repair.
All airplanes
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### Page 25

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 17 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 17:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 17 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames and splice
doubler at the frame splices be-
tween S-13L and S-14L in Sec-
tion 43 for any crack in the unre-
paired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 17 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 43 for any
crack in the unrepaired frame.
-Before further flight.CONDITION 17.1 (ACTION 1):CONDITION 17.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 17.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
6,000 flight cycles.-CONDITION 17.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
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### Page 26

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
6,000 flight cycles.-CONDITION 17.2 (ACTION 1):CONDITION 17.2:
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
NO CRACK FOUND
IN SECTION 43
6,000 flight cycles.-CONDITION 17.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 18 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 18:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 18 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack
in the unrepaired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 18 (ACTION 3):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 46 for any
crack in the unrepaired frame.
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### Page 27

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 18.1 (ACTION 1):CONDITION 18.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 18.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
2,700 flight cycles.-CONDITION 18.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
2,700 flight cycles.-CONDITION 18.2 (ACTION 1):CONDITION 18.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
NO CRACK FOUND
IN SECTION 46
2,700 flight cycles.-CONDITION 18.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
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### Page 28

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 19 (ACTION 1):
Do surface HFEC inspections
of the upper frames and splice
doubler at the frame splices be-
tween S-13L and S-14L in Sec-
tion 43 for any crack.
CONDITION 19:
NO REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 19 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 43 for any
crack.
-Before further flight.CONDITION 19.1 (ACTION 1):CONDITION 19.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 19.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
6,000 flight cycles.-CONDITION 19.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
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### Page 29

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
6,000 flight cycles.-CONDITION 19.2 (ACTION 1):CONDITION 19.2:
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
NO CRACK FOUND
IN SECTION 43
6,000 flight cycles.-CONDITION 19.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 20 (ACTION 1):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack.
CONDITION 20:
NO REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 20 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 46 for any
crack.
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ALERTALERT

### Page 30

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 20.1 (ACTION 1):CONDITION 20.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 20.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
2,700 flight cycles.-CONDITION 20.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
2,700 flight cycles.-CONDITION 20.2 (ACTION 1):CONDITION 20.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
NO CRACK FOUND
IN SECTION 46
2,700 flight cycles.-CONDITION 20.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
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757-53A0115 RB
30 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 31

Group 4:
Table 5: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 4:
Table 6: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13R and S-
14R in Sections 43 and 46 for
any repair.
All airplanes
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 21 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 21:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 21 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack
in the unrepaired frames.
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REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 32

Group 4:
Table 6: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 21.1 (ACTION 1):CONDITION 21.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 21.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 21.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 22 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 22:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 22 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack
in the unrepaired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 22 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13R
and S-14R in Section 46 for any
crack in the unrepaired frame.
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757-53A0115 RB
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ALERTALERT

### Page 33

Group 4:
Table 6: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 22.1 (ACTION 1):CONDITION 22.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 22.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
2,700 flight cycles.-CONDITION 22.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
2,700 flight cycles.-CONDITION 22.2 (ACTION 1):CONDITION 22.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
NO CRACK FOUND
IN SECTION 46
2,700 flight cycles.-CONDITION 22.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack.
CONDITION 23:
NO REPAIR
FOUND IN SEC-
TION 43
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### Page 34

Group 4:
Table 6: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 23.1 (ACTION 1):CONDITION 23.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 23.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 23.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 24 (ACTION 1):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack.
CONDITION 24:
NO REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 24 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13R
and S-14R in Section 46 for any
crack.
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Original Issue: January 25, 2022
757-53A0115 RB
34 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 35

Group 4:
Table 6: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 24.1 (ACTION 1):CONDITION 24.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 24.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
2,700 flight cycles.-CONDITION 24.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
2,700 flight cycles.-CONDITION 24.2 (ACTION 1):CONDITION 24.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
NO CRACK FOUND
IN SECTION 46
2,700 flight cycles.-CONDITION 24.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 25, 2022
757-53A0115 RB
35 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 36

Group 4:
Table 6: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 5:
Table 7: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13L and S-
14L in Sections 43 and 46 for
any repair.
All airplanes
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36 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 37

Group 5:
Table 7: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 25 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 25:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 25 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames and splice
doubler at the frame splices be-
tween S-13L and S-14L in Sec-
tion 43 for any crack in the unre-
paired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 25 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 43 for any
crack in the unrepaired frame.
-Before further flight.CONDITION 25.1 (ACTION 1):CONDITION 25.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 25.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
6,000 flight cycles.-CONDITION 25.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
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### Page 38

Group 5:
Table 7: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
6,000 flight cycles.-CONDITION 25.2 (ACTION 1):CONDITION 25.2:
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
NO CRACK FOUND
IN SECTION 43
6,000 flight cycles.-CONDITION 25.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 26 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 26:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 26 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 26.1 (ACTION 1):CONDITION 26.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 26.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
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### Page 39

Group 5:
Table 7: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
2,700 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
CONDITION 26.2:
NO CRACK FOUND
IN SECTION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 27 (ACTION 1):
Do surface HFEC inspections
of the upper frames and splice
doubler at the frame splices be-
tween S-13L and S-14L in Sec-
tion 43 for any crack.
CONDITION 27:
NO REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 27 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 43 for any
crack.
-Before further flight.CONDITION 27.1 (ACTION 1):CONDITION 27.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 27.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
6,000 flight cycles.-CONDITION 27.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
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### Page 40

Group 5:
Table 7: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
6,000 flight cycles.-CONDITION 27.2 (ACTION 1):CONDITION 27.2:
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
NO CRACK FOUND
IN SECTION 43
6,000 flight cycles.-CONDITION 27.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack.
CONDITION 28:
NO REPAIR
FOUND IN SEC-
TION 46
-Before further flight.CONDITION 28.1 (ACTION 1):CONDITION 28.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 28.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
2,700 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
CONDITION 28.2:
NO CRACK FOUND
IN SECTION 46
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### Page 41

Group 5:
Table 7: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 5:
Table 8: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13R and S-
14R in Sections 43 and 46 for
any repair.
All airplanes
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41 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 42

Group 5:
Table 8: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 29 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 29:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 29 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 29.1 (ACTION 1):CONDITION 29.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 29.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 29.2:
NO CRACK FOUND
IN SECTION 43
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REQUIREMENTS BULLETIN 757-53A0115
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### Page 43

Group 5:
Table 8: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 30 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 30:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 30 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack
in the unrepaired frames.
-Before further flight.CONDITION 30.1 (ACTION 1):CONDITION 30.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 30.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
2,700 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
CONDITION 30.2:
NO CRACK FOUND
IN SECTION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack.
CONDITION 31:
NO REPAIR
FOUND IN SEC-
TION 43
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REQUIREMENTS BULLETIN 757-53A0115
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### Page 44

Group 5:
Table 8: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 31.1 (ACTION 1):CONDITION 31.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
6,000 flight cycles.-CONDITION 31.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
6,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 31.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack.
CONDITION 32:
NO REPAIR
FOUND IN SEC-
TION 46
-Before further flight.CONDITION 32.1 (ACTION 1):CONDITION 32.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
2,700 flight cycles.-CONDITION 32.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
2,700 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
CONDITION 32.2:
NO CRACK FOUND
IN SECTION 46
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### Page 45

Group 5:
Table 8: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13L and S-
14L in Sections 43 and 46 for
any repair.
All airplanes
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757-53A0115 RB
45 of 290
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ALERTALERT

### Page 46

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 33 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 33:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 33 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames and splice
doubler at the frame splices be-
tween S-13L and S-14L in Sec-
tion 43 for any crack in the unre-
paired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 33 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 43 for any
crack in the unrepaired frame.
-Before further flight.CONDITION 33.1 (ACTION 1):CONDITION 33.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
5,000 flight cycles.-CONDITION 33.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
5,000 flight cycles.-CONDITION 33.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
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ALERTALERT

### Page 47

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
5,000 flight cycles.-CONDITION 33.2 (ACTION 1):CONDITION 33.2:
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
NO CRACK FOUND
IN SECTION 43
5,000 flight cycles.-CONDITION 33.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 34 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 34:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 34 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack
in the unrepaired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 34 (ACTION 3):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 46 for any
crack in the unrepaired frame.
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Original Issue: January 25, 2022
757-53A0115 RB
47 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 48

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 34.1 (ACTION 1):CONDITION 34.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 34.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
3,000 flight cycles.-CONDITION 34.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
3,000 flight cycles.-CONDITION 34.2 (ACTION 1):CONDITION 34.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 34.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
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ALERTALERT

### Page 49

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 35 (ACTION 1):
Do surface HFEC inspections
of the upper frames and splice
doubler at the frame splices be-
tween S-13L and S-14L in Sec-
tion 43 for any crack.
CONDITION 35:
NO REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 35 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 43 for any
crack.
-Before further flight.CONDITION 35.1 (ACTION 1):CONDITION 35.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
5,000 flight cycles.-CONDITION 35.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
5,000 flight cycles.-CONDITION 35.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
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### Page 50

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
5,000 flight cycles.-CONDITION 35.2 (ACTION 1):CONDITION 35.2:
Repeat the surface HFEC in-
spections of the upper frames
and splice doubler at the frame
splices between S-13L and S-
14L in Section 43 for any crack.
(a)
NO CRACK FOUND
IN SECTION 43
5,000 flight cycles.-CONDITION 35.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 43 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 36 (ACTION 1):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13L and S-
14L in Section 46 for any crack.
CONDITION 36:
NO REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 36 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13L and
S-14L in Section 46 for any
crack.
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### Page 51

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 36.1 (ACTION 1):CONDITION 36.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 36.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
3,000 flight cycles.-CONDITION 36.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
3,000 flight cycles.-CONDITION 36.2 (ACTION 1):CONDITION 36.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13L and S-14L in Section 46 for
any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 36.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13L
and S-14L in Section 46 for any
crack. (b)
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
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51 of 290
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### Page 52

Group 6:
Table 9: Inspections of the Upper Frames and the Splice Doubler at Fuselage Frame Splices between
S-13 and S-14 in Sections 43 and 46, Left Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 6:
Table 10: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do General Visual Inspections
or a maintenance records check
of the upper frames at the frame
splices between S-13R and S-
14R in Sections 43 and 46 for
any repair.
All airplanes
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 37 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 37:
ANY REPAIR
FOUND IN SEC-
TION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 37 (ACTION 2):
Do surface High Frequency Ed-
dy Current (HFEC) inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack
in the unrepaired frames.
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### Page 53

Group 6:
Table 10: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 37.1 (ACTION 1):CONDITION 37.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
5,000 flight cycles.-CONDITION 37.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
5,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 37.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 38 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspec-
tions and applicable corrective
actions.
CONDITION 38:
ANY REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 38 (ACTION 2):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack
in the unrepaired frames.
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 38 (ACTION 3):
Do a sub-surface Low Frequen-
cy Eddy Current (LFEC) inspec-
tion of the upper frame at the
frame splice between S-13R
and S-14R in Section 46 for any
crack in the unrepaired frame.
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### Page 54

Group 6:
Table 10: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 38.1 (ACTION 1):CONDITION 38.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 38.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
3,000 flight cycles.-CONDITION 38.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
3,000 flight cycles.-CONDITION 38.2 (ACTION 1):CONDITION 38.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 38.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 43 for any crack.
CONDITION 39:
NO REPAIR
FOUND IN SEC-
TION 43
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### Page 55

Group 6:
Table 10: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 39.1 (ACTION 1):CONDITION 39.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 43
5,000 flight cycles.-CONDITION 39.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
5,000 flight cycles.-Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 43
for any crack. (a)
CONDITION 39.2:
NO CRACK FOUND
IN SECTION 43
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 40 (ACTION 1):
Do surface HFEC inspections
of the upper frames at the frame
splices between S-13R and S-
14R in Section 46 for any crack.
CONDITION 40:
NO REPAIR
FOUND IN SEC-
TION 46
-Within 2,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0115 RB.
Before 50,000
total flight cy-
cles.
CONDITION 40 (ACTION 2):
Do a sub-surface LFEC inspec-
tion of the upper frame at the
frame splice between S-13R
and S-14R in Section 46 for any
crack.
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REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 56

Group 6:
Table 10: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 40.1 (ACTION 1):CONDITION 40.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND IN SEC-
TION 46
3,000 flight cycles.-CONDITION 40.1 (ACTION 2):
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
3,000 flight cycles.-CONDITION 40.1 (ACTION 3):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
3,000 flight cycles.-CONDITION 40.2 (ACTION 1):CONDITION 40.2:
Repeat the surface HFEC in-
spections of the upper frames
at the frame splices between S-
13R and S-14R in Section 46
for any crack. (a)
NO CRACK FOUND
IN SECTION 46
3,000 flight cycles.-CONDITION 40.2 (ACTION 2):
Repeat the sub-surface LFEC
inspection of the upper frame at
the frame splice between S-13R
and S-14R in Section 46 for any
crack. (b)
(a) It is not required to do the surface HFEC inspection in areas where an approved repair covers the affected
inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 25, 2022
757-53A0115 RB
56 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT

### Page 57

Group 6:
Table 10: Inspections of the Upper Frames at Fuselage Frame Splices between S-13 and S-14 in Sections
43 and 46, Right Side
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) It is not required to do the sub-surface LFEC inspection in areas where an approved repair covers the
affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 757-
53A0115 RB and installed after the original issue date of Requirements Bulletin 757-53A0115
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
4. APPROVAL
This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this document comply with the applicable regulations and are FAA approved, as well as European
Union Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in this Requirements Bulletin effectivity. This document and its approval were based on the
airplane in its original Boeing delivery configuration or as modified by other Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by
this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this Requirements Bulletin.
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### Page 58

Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 25, 2022
757-53A0115 RB
58 of 290
REQUIREMENTS BULLETIN 757-53A0115
ALERTALERT
BLANK PAGE

### Page 59

5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. This is an Enhanced Required for Compliance document. There will be a separate
Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated
by an Airworthiness Directive (AD), then all applicable requirements specified in the
RB must be done. For the related SB, some locations are marked RC Start and RC
End to identify the requirements that are restated from the RB. For the related SB,
the areas between RC Start and RC End, including sub-steps and any figures
identified between RC Start and RC End, must be done to comply with the AD.
Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations
to steps between RC Start and RC End, including substeps and identified figures.
For the related SB, the steps not between RC Start and RC End may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC; this is provided that the
steps between RC Start and RC End, including sub-steps and identified figures, can
still be done as specified, and the airplane can be put back in an airworthy condition.
Figures not required for compliance are omitted from the RB.
2. This is an Enhanced Required for Compliance document. The Boeing processes
used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure
that the information between "RC Start" and "RC End" in the SB are identical to the
information in the same sections (Compliance, Work Instructions...) of the RB which
the SB refers to as the related document.
3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
4. Boeing Service Letter 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.
5. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 757 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 757
Aircraft 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.
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### Page 60

6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance, unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked. Basic cleaning may be
required to ensure appropriate visibility.
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 or an OPTION,
do all of the ACTION numbers for that CONDITION or OPTION.
11. A maintenance records check of the repair at the frame splices can be done provided
an existing repair can be conclusively determined from that check.
B. WORK INSTRUCTIONS
Actions Required For Compliance
1. Requirements
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