# Boeing Alert Requirements Bulletin 757-53A0120 RB: No revision named, part 1 of 2

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- Title as filed: 757-53A0120 RB_Part1
- Pages: 193
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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0120 RB
Original Issue: January 17, 2022
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Fuselage Frame Web at STA 1640 between S-14 and S-15
- Liner Hole 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Unpublished Work.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 17, 2022
757-53A0120 RB
1 of 204
3.0

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757-53A0120 RB
2 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT
BLANK PAGE

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Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72
FIGURE 1: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - GENERAL
VISUAL INSPECTION [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 145
FIGURE 2: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION  [Group 1-2] . . . . . . . . 148
FIGURE 3: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - OPEN
HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION  [Group 1-2] . . . . 151
FIGURE 4: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - ZERO-TIME
THE PLUGGED LINER HOLE  [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . 154
FIGURE 5: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - ZERO-TIME
THE OPEN LINER HOLE [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 158
FIGURE 6: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - FASTENER
INSTALLATION [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 162
FIGURE 7: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - GENERAL
VISUAL INSPECTION [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 166
FIGURE 8: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION  [Group 1-2] . . . . . . . . 169
FIGURE 9: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - OPEN
HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION  [Group 1-2] . . . . 172
FIGURE 10: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - ZERO-TIME
THE PLUGGED LINER HOLE  [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . 175
FIGURE 11: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - ZERO-TIME
THE OPEN LINER HOLE [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 179
FIGURE 12: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - FASTENER
INSTALLATION [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183
FIGURE 13: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - GENERAL
VISUAL INSPECTION [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 187
FIGURE 14: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AROUND A PLUGGED LINER
HOLE [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 190
FIGURE 15: LEFT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AROUND AN OPEN LINER HOLE
[Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 193
FIGURE 16: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - GENERAL
VISUAL INSPECTION [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 196
FIGURE 17: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AROUND A PLUGGED LINER
HOLE [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 199
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REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

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FIGURE 18: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 BETWEEN S-14 AND S-15 - SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AROUND AN OPEN LINER HOLE
[Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202
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REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

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Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0120 RB
Original Issue: January 17, 2022
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Fuselage Frame Web at STA 1640 between S-14 and S-15
- Liner Hole 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, 757-300 Airplane(s), line number(s) 1-138, 140,
142, 144-146, 148, 150-175, 177-180, 182-183, 185, 187-188, 190, 192, 194, 196, 198, 200-236,
238-257, 259-299, 301-313, 315-317, 319-321, 323-325, 327-329, 331-333, 335-339, 341-394,
396-398, 400-402, 404-406, 408-410, 412-476, 478-480, 482-484, 486-488, 490-492, 494-568,
570-572, 574-576, 578, 580, 582-624, 626-627, 629-630, 632-633, 635, 637, 639, 641, 643, 645,
647-648, 650, 652-653, 655, 657-658, 660-674, 676-678, 680-682, 684-686, 688-690, 692-727,
731-732, 735-754, 756-758, 760-762, 764, 766, 768, 770, 772-773, 775, 777, 779-812, 814,
816-822, 824-878, 880-881, 883-1050 in 3 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 and -200CB Airplanes.-1
Airplanes that have not incorporated the SB 757-53-0110 modification
at or before the accomplishment of the first Requirements Bulletin
757-53A0120 RB inspection.
1
Airplanes that have incorporated the SB 757-53-0110 modification
at or before the accomplishment of the first Requirements Bulletin
757-53A0120 RB inspection.
2
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DESCRIPTIONCONFIGURATIONGROUP
757-300 Airplanes.-2
Airplanes that have not incorporated the SB 757-53-0110 modification
at or before the accomplishment of the first Requirements Bulletin
757-53A0120 RB inspection.
1
Airplanes that have incorporated the SB 757-53-0110 modification
at or before the accomplishment of the first Requirements Bulletin
757-53A0120 RB inspection.
2
757-200 airplanes changed to the Special Freighter (SF) configuration
by the Boeing Company in accordance with Supplemental Type
Certificate (STC) ST00916WI-D.
-3
Airplanes that have not incorporated the SB 757-53-0110 modification
at or before the accomplishment of the first Requirements Bulletin
757-53A0120 RB inspection.
1
Airplanes that have incorporated the SB 757-53-0110 modification
at or before the accomplishment of the first Requirements Bulletin
757-53A0120 RB inspection.
2
Airplane Models:
757-200, 757-200CB, 757-300
GroupVariable Number
1NA001 - NA028
1NA191 - NA199
3NA201 - NA204
1NA205
3NA206 - NA213
1NA214
3NA215 - NA236
1NA237 - NA239
1NA301 - NA305
1NA341 - NA352
1NA391 - NA399
1NA401 - NA408
1NA441 - NA447
GroupVariable Number
1NA501 - NA586
1NB001 - 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
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GroupVariable Number
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
1ND001 - ND007
1ND011 - ND059
1ND111 - ND113
1ND161 - ND199
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
1ND895
1NE001 - NE008
1NE011 - NE088
1NE091 - NE094
GroupVariable Number
1NE141 - NE150
1NE161 - NE177
1NE201 - NE204
1NE301 - NE302
1NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
2NL001 - NL002
2NL006 - NL017
2NL101 - NL109
2NL141
2NL601 - NL616
1NN001 - NN002
1NN051 - NN052
1NP901 - NP904
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
GroupVariable Number
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT916
1NT971 - NT985
1NU031 - NU038
2NU701 - NU705
2NU721 - NU728
2NU731 - NU732
--
--
B. Spares Affected
Examine your spares supply for the parts or components identified below. If any parts or components
are found, refer to Work Instructions for the recommended action.
Part Number
653N0001-1
653N0001-2
2. CONCURRENT REQUIREMENTS
None.
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3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 757-53A0120 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-53A0120 RB mandatory.
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.
Accomplish the required action(s), based on the applicable condition(s) in Table 1 through Table 18, in
accordance with Accomplishment Instructions.
Group 1, Configuration 1:
Table 1: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14L and S-15L for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14L and S-
15L for an existing liner hole.
--No further action required.CONDITION 1: NO
LINER HOLE FOUND.
--No further action required.CONDITION 2: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
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Group 1, Configuration 1:
Table 1: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
--No further action required.CONDITION 3: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 4 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 4: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 4 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 4.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
6,000 Flight Cy-
cles.
-CONDITION 4.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
(b)
CONDITION 4.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 4.2 (OPTION 2):
Zero-time the liner hole.
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Group 1, Configuration 1:
Table 1: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 5.Do the actions specified in Ta-
ble 5.
CONDITION 4.3: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
-At the times specified in Table 5.Do the actions specified in Ta-
ble 5.
CONDITION 4.4: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 4.5: DUR-
ING ACCOMPLISH-
MENT OF CONDITION
4 (OPTION 2) OR
CONDITION 4.2 (OP-
TION 2), ANY CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (d)
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Group 1, Configuration 1:
Table 1: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 4.6: DUR-
ING ACCOMPLISH-
MENT OF CONDITION
4 (OPTION 2) OR
CONDITION 4.2 (OP-
TION 2), ANY CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (d)
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 5 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 5: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 5 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 5.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
6,000 Flight Cy-
cles.
-CONDITION 5.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack. (b)
CONDITION 5.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 5.2 (OPTION 2):
Zero-time the liner hole.
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### Page 12

Group 1, Configuration 1:
Table 1: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 5.Do the actions specified in Ta-
ble 5.
CONDITION 5.3: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
-At the times specified in Table 5.Do the actions specified in Ta-
ble 5.
CONDITION 5.4: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 5.5: DUR-
ING ACCOMPLISH-
MENT OF CONDITION
5 (OPTION 2), CONDI-
TION 5.1, OR CONDI-
TION 5.2 (OPTION 2),
ANY CRACK FOUND
BEFORE OR DURING
ZERO-TIME OF LINER
HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (d)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
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REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 13

Group 1, Configuration 1:
Table 1: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 5.6: DUR-
ING ACCOMPLISH-
MENT OF CONDITION
5 (OPTION 2), CONDI-
TION 5.1, OR CONDI-
TION 5.2 (OPTION 2),
ANY CRACK FOUND
BEFORE OR DURING
ZERO-TIME OF LINER
HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (d)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) If Service Bulletin 757-53-0110 modification was incorporated, do the actions in Condition 4.3 or 4.4 (for
a plugged liner hole) or Condition 5.3 or 5.4 (for an open liner hole).
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
(d) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
13 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 14

Group 1, Configuration 1:
Table 2: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14R and S-15R for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14R and S-
15R for an existing liner hole.
--No further action required.CONDITION 6: NO
LINER HOLE FOUND.
--No further action required.CONDITION 7: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
--No further action required.CONDITION 8: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
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Original Issue: January 17, 2022
757-53A0120 RB
14 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 15

Group 1, Configuration 1:
Table 2: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 9 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 9: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 9 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 9.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
6,000 Flight Cy-
cles.
-CONDITION 9.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
(b)
CONDITION 9.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 9.2 (OPTION 2):
Zero-time the liner hole.
-At the times specified in Table 6.Do the actions specified in Ta-
ble 6.
CONDITION 9.3: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
15 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 16

Group 1, Configuration 1:
Table 2: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 6.Do the actions specified in Ta-
ble 6.
CONDITION 9.4: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 9.5: DUR-
ING ACCOMPLISH-
MENT OF CONDITION
9 (OPTION 2) OR
CONDITION 9.2 (OP-
TION 2), ANY CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (d)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 9.6: DUR-
ING ACCOMPLISH-
MENT OF CONDITION
9 (OPTION 2) OR
CONDITION 9.2 (OP-
TION 2), ANY CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (d)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
16 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 17

Group 1, Configuration 1:
Table 2: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 10 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 10: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 10 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 10.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
6,000 Flight Cy-
cles.
-CONDITION 10.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack. (b)
CONDITION 10.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 10.2 (OPTION 2):
Zero-time the liner hole.
-At the times specified in Table 6.Do the actions specified in Ta-
ble 6.
CONDITION 10.3: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
17 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 18

Group 1, Configuration 1:
Table 2: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 6.Do the actions specified in Ta-
ble 6.
CONDITION 10.4: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 10.5:
DURING ACCOM-
PLISHMENT OF CON-
DITION 10 (OPTION 2),
CONDITION 10.1, OR
CONDITION 10.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (d)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 10.6:
DURING ACCOM-
PLISHMENT OF CON-
DITION 10 (OPTION 2),
CONDITION 10.1, OR
CONDITION 10.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (d)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) If Service Bulletin 757-53-0110 modification was incorporated, do the actions in Condition 9.3 or 9.4 (for
a plugged liner hole) or Condition 10.3 or 10.4 (for an open liner hole).
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
18 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 19

Group 1, Configuration 1:
Table 2: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
(d) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
Group 1, Configuration 2:
Table 3: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
or within 6,000
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14L and S-15L for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14L and S-
15L for an existing liner hole.
--No further action required.CONDITION 11: NO
LINER HOLE FOUND.
--No further action required.CONDITION 12: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
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Original Issue: January 17, 2022
757-53A0120 RB
19 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 20

Group 1, Configuration 2:
Table 3: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
--No further action required.CONDITION 13: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
or within 6,000
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 14 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 14: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 14 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 14.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 14.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 14.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 14.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
20 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 21

Group 1, Configuration 2:
Table 3: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 14.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 14 (OPTION 2)
OR CONDITION 14.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 14.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 14 (OPTION 2)
OR CONDITION 14.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (b)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
21 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 22

Group 1, Configuration 2:
Table 3: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
or within 6,000
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 15 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 15: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 15 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 15.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 15.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 15.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 15.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
22 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 23

Group 1, Configuration 2:
Table 3: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 15.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 15 (OPTION 2),
CONDITION 15.1, OR
CONDITION 15.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 15.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 15 (OPTION 2),
CONDITION 15.1, OR
CONDITION 15.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (b)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
23 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 24

Group 1, Configuration 2:
Table 4: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
or within 6,000
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14R and S-15R for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14R and S-
15R for an existing liner hole.
--No further action required.CONDITION 16: NO
LINER HOLE FOUND.
--No further action required.CONDITION 17: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
--No further action required.CONDITION 18: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
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Original Issue: January 17, 2022
757-53A0120 RB
24 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 25

Group 1, Configuration 2:
Table 4: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
or within 6,000
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 19 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 19: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 19 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 19.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 19.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 19.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 19.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
25 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 26

Group 1, Configuration 2:
Table 4: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 19.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 19 (OPTION 2)
OR CONDITION 19.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 19.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 19 (OPTION 2)
OR CONDITION 19.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (b)
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757-53A0120 RB
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REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 27

Group 1, Configuration 2:
Table 4: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 6,000
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
or within 6,000
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 20,000
Total Flight Cy-
cles.
CONDITION 20 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 20: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 20 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 20.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 20.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 20.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 20.2 (OPTION 2):
Zero-time the liner hole.
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Original Issue: January 17, 2022
757-53A0120 RB
27 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 28

Group 1, Configuration 2:
Table 4: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 20.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 20 (OPTION 2),
CONDITION 20.1, OR
CONDITION 20.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 20.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 20 (OPTION 2),
CONDITION 20.1, OR
CONDITION 20.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (b)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
28 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 29

Group 1, Configuration 1:
Table 5: STA 1640 Frame Web between S-14L and S-15L - Surface and Open Hole High Frequency Eddy
Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 12,000 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB surface HFEC
inspection was done.
CONDITION 21 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 21: CON-
DITION 4.3 OR CONDI-
TION 4.4 AIRPLANES.
-Before further flight.CONDITION 21 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 21.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 21.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 21.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 21.2 (OPTION 2):
Zero-time the liner hole.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 21.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 21 (OPTION 2)
OR CONDITION 21.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (a)
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757-53A0120 RB
29 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 30

Group 1, Configuration 1:
Table 5: STA 1640 Frame Web between S-14L and S-15L - Surface and Open Hole High Frequency Eddy
Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 21.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 21 (OPTION 2)
OR CONDITION 21.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (a)
-Within 12,000 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB Open Hole
HFEC inspection was done.
CONDITION 22 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 22: CON-
DITION 5.3 OR CONDI-
TION 5.4 AIRPLANES.
-Before further flight.CONDITION 22 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Zero-time the liner hole.CONDITION 22.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 22.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 22.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 22.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
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Original Issue: January 17, 2022
757-53A0120 RB
30 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 31

Group 1, Configuration 1:
Table 5: STA 1640 Frame Web between S-14L and S-15L - Surface and Open Hole High Frequency Eddy
Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 22.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 22 (OPTION 2),
CONDITION 22.1, OR
CONDITION 22.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (a)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 22.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 22 (OPTION 2),
CONDITION 22.1, OR
CONDITION 22.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (a)
(a) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(b) A fastener could be either a solid rivet or interference fit Hi-Lok.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
31 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 32

Group 1, Configuration 1:
Table 6: STA 1640 Frame Web between S-14R and S-15R - Surface and Open Hole High Frequency Eddy
Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 12,000 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB surface HFEC
inspection was done.
CONDITION 23 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 23: CON-
DITION 9.3 OR CONDI-
TION 9.4 AIRPLANES.
-Before further flight.CONDITION 23 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 23.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 23.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 23.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 23.2 (OPTION 2):
Zero-time the liner hole.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 23.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 23 (OPTION 2)
OR CONDITION 23.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (a)
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Original Issue: January 17, 2022
757-53A0120 RB
32 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 33

Group 1, Configuration 1:
Table 6: STA 1640 Frame Web between S-14R and S-15R - Surface and Open Hole High Frequency Eddy
Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 23.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 23 (OPTION 2)
OR CONDITION 23.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (a)
-Within 12,000 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB Open Hole
HFEC inspection was done.
CONDITION 24 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 24: CON-
DITION 10.3 OR CON-
DITION 10.4 AIR-
PLANES.
-Before further flight.CONDITION 24 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Zero-time the liner hole.CONDITION 24.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
12,000 Flight Cy-
cles.
-CONDITION 24.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 24.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 24.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
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Original Issue: January 17, 2022
757-53A0120 RB
33 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 34

Group 1, Configuration 1:
Table 6: STA 1640 Frame Web between S-14R and S-15R - Surface and Open Hole High Frequency Eddy
Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 24.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 24 (OPTION 2),
CONDITION 24.1, OR
CONDITION 24.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (a)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 24.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 24 (OPTION 2),
CONDITION 24.1, OR
CONDITION 24.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (a)
(a) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(b) A fastener could be either a solid rivet or interference fit Hi-Lok.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
34 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 35

Group 2, Configuration 1:
Table 7: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14L and S-15L for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14L and S-
15L for an existing liner hole.
--No further action required.CONDITION 25: NO
LINER HOLE FOUND.
--No further action required.CONDITION 26: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
--No further action required.CONDITION 27: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
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Original Issue: January 17, 2022
757-53A0120 RB
35 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 36

Group 2, Configuration 1:
Table 7: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 28 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 28: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 28 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 28.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
3,200 Flight Cy-
cles.
-CONDITION 28.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
(b)
CONDITION 28.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 28.2 (OPTION 2):
Zero-time the liner hole.
-At the times specified in Table 11.Do the actions specified in Ta-
ble 11.
CONDITION 28.3: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
36 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 37

Group 2, Configuration 1:
Table 7: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 11.Do the actions specified in Ta-
ble 11.
CONDITION 28.4: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 28.5:
DURING ACCOM-
PLISHMENT OF CON-
DITION 28 (OPTION 2)
OR CONDITION 28.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (d)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 28.6:
DURING ACCOM-
PLISHMENT OF CON-
DITION 28 (OPTION 2)
OR CONDITION 28.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (d)
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Original Issue: January 17, 2022
757-53A0120 RB
37 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 38

Group 2, Configuration 1:
Table 7: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 29 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 29: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 29 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 29.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
3,200 Flight Cy-
cles.
-CONDITION 29.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack. (b)
CONDITION 29.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 29.2 (OPTION 2):
Zero-time the liner hole.
-At the times specified in Table 11.Do the actions specified in Ta-
ble 11.
CONDITION 29.3: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
38 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 39

Group 2, Configuration 1:
Table 7: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 11.Do the actions specified in Ta-
ble 11.
CONDITION 29.4: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 29.5:
DURING ACCOM-
PLISHMENT OF CON-
DITION 29 (OPTION 2),
CONDITION 29.1, OR
CONDITION 29.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (d)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 29.6:
DURING ACCOM-
PLISHMENT OF CON-
DITION 29 (OPTION 2),
CONDITION 29.1, OR
CONDITION 29.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (d)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) If Service Bulletin 757-53-0110 modification was incorporated, do the actions in Condition 28.3 or 28.4
(for a plugged liner hole) or Condition 29.3 or 29.4 (for an open liner hole).
Export Controlled ECCN: 9E991
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Original Issue: January 17, 2022
757-53A0120 RB
39 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 40

Group 2, Configuration 1:
Table 7: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
(d) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
Group 2, Configuration 1:
Table 8: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14R and S-15R for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14R and S-
15R for an existing liner hole.
--No further action required.CONDITION 30: NO
LINER HOLE FOUND.
--No further action required.CONDITION 31: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
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757-53A0120 RB
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ALERTALERT

### Page 41

Group 2, Configuration 1:
Table 8: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
--No further action required.CONDITION 32: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 33 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 33: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 33 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 33.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
3,200 Flight Cy-
cles.
-CONDITION 33.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
(b)
CONDITION 33.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 33.2 (OPTION 2):
Zero-time the liner hole.
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Original Issue: January 17, 2022
757-53A0120 RB
41 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 42

Group 2, Configuration 1:
Table 8: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 12.Do the actions specified in Ta-
ble 12.
CONDITION 33.3: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
-At the times specified in Table 12.Do the actions specified in Ta-
ble 12.
CONDITION 33.4: NO
CRACK FOUND DUR-
ING CURRENT SUR-
FACE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 33.5:
DURING ACCOM-
PLISHMENT OF CON-
DITION 33 (OPTION 2)
OR CONDITION 33.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (d)
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Original Issue: January 17, 2022
757-53A0120 RB
42 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 43

Group 2, Configuration 1:
Table 8: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 33.6:
DURING ACCOM-
PLISHMENT OF CON-
DITION 33 (OPTION 2)
OR CONDITION 33.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (d)
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 34 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 34: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 34 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 34.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
3,200 Flight Cy-
cles.
-CONDITION 34.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack. (b)
CONDITION 34.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 34.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
43 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 44

Group 2, Configuration 1:
Table 8: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in Table 12.Do the actions specified in Ta-
ble 12.
CONDITION 34.3: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 MODIFICA-
TION SINCE THE PRI-
OR INSPECTION.
-At the times specified in Table 12.Do the actions specified in Ta-
ble 12.
CONDITION 34.4: NO
CRACK FOUND DUR-
ING CURRENT OPEN
HOLE HFEC INSPEC-
TION AND HAVE IN-
CORPORATED SER-
VICE BULLETIN 757-
53-0110 AT THE SAME
TIME AS THE CUR-
RENT INSPECTION.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 34.5:
DURING ACCOM-
PLISHMENT OF CON-
DITION 34 (OPTION 2),
CONDITION 34.1, OR
CONDITION 34.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (d)
Export Controlled ECCN: 9E991
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Original Issue: January 17, 2022
757-53A0120 RB
44 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 45

Group 2, Configuration 1:
Table 8: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 34.6:
DURING ACCOM-
PLISHMENT OF CON-
DITION 34 (OPTION 2),
CONDITION 34.1, OR
CONDITION 34.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (d)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) If Service Bulletin 757-53-0110 modification was incorporated, do the actions in Condition 33.3 or 33.4
(for a plugged liner hole) or Condition 34.3 or 34.4 (for an open liner hole).
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
(d) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
Export Controlled ECCN: 9E991
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Original Issue: January 17, 2022
757-53A0120 RB
45 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 46

Group 2, Configuration 2:
Table 9: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done
or within 3,200
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14L and S-15L for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14L and S-
15L for an existing liner hole.
---No further action required.CONDITION 35: NO
LINER HOLE FOUND.
---No further action required.CONDITION 36: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
---No further action required.CONDITION 37: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
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Original Issue: January 17, 2022
757-53A0120 RB
46 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 47

Group 2, Configuration 2:
Table 9: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done
or within 3,200
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 38 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 38: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 38 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 38.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 38.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 38.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 38.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
47 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 48

Group 2, Configuration 2:
Table 9: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 38.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 38 (OPTION 2)
OR CONDITION 38.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 38.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 38 (OPTION 2)
OR CONDITION 38.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (b)
Export Controlled ECCN: 9E991
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Original Issue: January 17, 2022
757-53A0120 RB
48 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 49

Group 2, Configuration 2:
Table 9: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done
or within 3,200
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 39 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 39: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 39 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 39.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 39.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 39.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 39.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
49 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 50

Group 2, Configuration 2:
Table 9: STA 1640 Frame Web between S-14L and S-15L - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 39.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 39 (OPTION 2),
CONDITION 39.1, OR
CONDITION 39.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 39.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 39 (OPTION 2),
CONDITION 39.1, OR
CONDITION 39.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (b)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
50 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 51

Group 2, Configuration 2:
Table 10: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done
or within 3,200
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
OPTION 1:
Do a General Visual Inspection
of the STA 1640 Frame Web
between S-14R and S-15R for
an existing liner hole.
All Airplanes.
OPTION 2:
Do a Maintenance Records
check of the STA 1640 Frame
Web between S-14R and S-
15R for an existing liner hole.
---No further action required.CONDITION 40: NO
LINER HOLE FOUND.
---No further action required.CONDITION 41: LINER
HOLE FOUND - LINER
HOLE WAS ZERO-
TIMED AND PLUGGED
WITH A FASTENER.
(a)
---No further action required.CONDITION 42: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
DURING PRODUC-
TION. (a)
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Original Issue: January 17, 2022
757-53A0120 RB
51 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 52

Group 2, Configuration 2:
Table 10: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done
or within 3,200
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 43 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 43: LINER
HOLE FOUND - LINER
HOLE WAS PLUGGED
WITH A FASTENER
AND THE LINER HOLE
WAS NOT ZERO-
TIMED BEFORE BE-
ING PLUGGED OR
LINER HOLE WAS
PLUGGED WITH A
FASTENER AND THE
ZERO-TIME HISTORY
IS UNKNOWN.
-CONDITION 43 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 43.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 43.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 43.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 43.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
52 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 53

Group 2, Configuration 2:
Table 10: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 43.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 43 (OPTION 2)
OR CONDITION 43.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 43.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 43 (OPTION 2)
OR CONDITION 43.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (b)
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Original Issue: January 17, 2022
757-53A0120 RB
53 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 54

Group 2, Configuration 2:
Table 10: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
Flight Cycles af-
ter the original
issue date of
Requirements
Bulletin 757-
53A0120 RB, or
within 3,200
Flight Cycles af-
ter the last Ser-
vice Bulletin
757-53A0108
Revision 1 eddy
current inspec-
tions were done
or within 3,200
Flight Cycles af-
ter Service Bul-
letin 757-53-
0110 modifica-
tion was done,
whichever oc-
curs later.
Before 10,000
Total Flight Cy-
cles.
CONDITION 44 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 44: LINER
HOLE FOUND - LINER
HOLE IS OPEN OR A
PLASTIC INSULATION
STUD IS INSTALLED. -CONDITION 44 (OPTION 2):
Zero-time the liner hole.
-Before further flightZero-time the liner hole.CONDITION 44.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 44.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 44.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 44.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
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REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 55

Group 2, Configuration 2:
Table 10: STA 1640 Frame Web between S-14R and S-15R - General Visual Inspection and High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(a)
CONDITION 44.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 44 (OPTION 2),
CONDITION 44.1, OR
CONDITION 44.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (b)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 44.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 44 (OPTION 2),
CONDITION 44.1, OR
CONDITION 44.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (b)
(a) A fastener could be either a solid rivet or interference fit Hi-Lok.
(b) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
55 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 56

Group 2, Configuration 1:
Table 11: STA 1640 Frame Web between S-14L and S-15L - Surface and Open Hole High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 7,200 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB surface HFEC
inspection was done.
CONDITION 45 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 45: CON-
DITION 28.3 OR CON-
DITION 28.4 AIR-
PLANES.
-Before further flight.CONDITION 45 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 45.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 45.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 45.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 45.2 (OPTION 2):
Zero-time the liner hole.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 45.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 45 (OPTION 2)
OR CONDITION 45.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
56 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 57

Group 2, Configuration 1:
Table 11: STA 1640 Frame Web between S-14L and S-15L - Surface and Open Hole High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 45.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 45 (OPTION 2)
OR CONDITION 45.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (a)
-Within 7,200 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB Open Hole
HFEC inspection was done.
CONDITION 46 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 46: CON-
DITION 29.3 OR CON-
DITION 29.4 AIR-
PLANES.
-Before further flight.CONDITION 46 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Zero-time the liner hole.CONDITION 46.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 46.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 46.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 46.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
57 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 58

Group 2, Configuration 1:
Table 11: STA 1640 Frame Web between S-14L and S-15L - Surface and Open Hole High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 46.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 46 (OPTION 2),
CONDITION 46.1, OR
CONDITION 46.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK IS RE-
MOVED WITHIN RE-
PAIR LIMITS OR NO
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE. (a)
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 46.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 46 (OPTION 2),
CONDITION 46.1, OR
CONDITION 46.2 (OP-
TION 2), ANY CRACK
FOUND BEFORE OR
DURING ZERO-TIME
OF LINER HOLE AND
THE CRACK CANNOT
BE REMOVED WITHIN
REPAIR LIMITS. (a)
(a) Repair limit is defined as: The crack can be removed after reaming the hole and the final hole size is
0.3735 inch diameter or smaller, after the insurance cut.
(b) A fastener could be either a solid rivet or interference fit Hi-Lok.
(c) Zero-time and plug terminates Requirements Bulletin 757-53A0120 RB repeat inspections for this location.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
58 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 59

Group 2, Configuration 1:
Table 12: STA 1640 Frame Web between S-14R and S-15R - Surface and Open Hole High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 7,200 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB surface HFEC
inspection was done.
CONDITION 47 (OPTION 1):
Do a Surface High Frequency
Eddy Current (HFEC) inspec-
tion of the web around the
fastener (plug) for any crack.
CONDITION 47: CON-
DITION 33.3 OR CON-
DITION 33.4 AIR-
PLANES.
-Before further flight.CONDITION 47 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 47.1: ANY
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 47.2 (OPTION 1):
Repeat the Surface HFEC in-
spection of the web around the
fastener (plug) for any crack.
CONDITION 47.2: NO
CRACK FOUND DUR-
ING SURFACE HFEC
INSPECTION.
-Before further flight.CONDITION 47.2 (OPTION 2):
Zero-time the liner hole.
(c)Before further flight.Install a fastener (plug) at the
zero-time liner hole location.
(b)
CONDITION 47.3:
DURING ACCOM-
PLISHMENT OF CON-
DITION 47 (OPTION 2)
OR CONDITION 47.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK IS REMOVED
WITHIN REPAIR LIM-
ITS OR NO CRACK
FOUND DURING ZE-
RO-TIME OF LINER
HOLE. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
59 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

### Page 60

Group 2, Configuration 1:
Table 12: STA 1640 Frame Web between S-14R and S-15R - Surface and Open Hole High Frequency
Eddy Current (HFEC) Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Before further flight.Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 47.4:
DURING ACCOM-
PLISHMENT OF CON-
DITION 47 (OPTION 2)
OR CONDITION 47.2
(OPTION 2), ANY
CRACK FOUND DUR-
ING ZERO-TIME OF
LINER HOLE AND THE
CRACK CANNOT BE
REMOVED WITHIN
REPAIR LIMITS. (a)
-Within 7,200 Flight Cycles after
the last Requirements Bulletin
757-53A0120 RB Open Hole
HFEC inspection was done.
CONDITION 48 (OPTION 1):
Do an Open Hole HFEC in-
spection of the web for any
crack.
CONDITION 48: CON-
DITION 34.3 OR CON-
DITION 34.4 AIR-
PLANES.
-Before further flight.CONDITION 48 (OPTION 2):
Zero-time the liner hole.
-Before further flight.Zero-time the liner hole.CONDITION 48.1: ANY
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
7,200 Flight Cy-
cles.
-CONDITION 48.2 (OPTION 1):
Repeat the Open Hole HFEC
inspection of the web for any
crack.
CONDITION 48.2: NO
CRACK FOUND DUR-
ING OPEN HOLE
HFEC INSPECTION.
-Before further flight.CONDITION 48.2 (OPTION 2):
Zero-time the liner hole.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 17, 2022
757-53A0120 RB
60 of 204
REQUIREMENTS BULLETIN 757-53A0120
ALERTALERT

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