# Boeing Alert Requirements Bulletin 757-53A0119 RB: No revision named

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- Title as filed: RB-757-53A0119
- Pages: 178
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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0119 RB
Original Issue: October 12, 2022
ATA System: 5300
SUBJECT: FUSELAGE - No 1, No. 2 and No 4 Passenger Entry Door, Crew Entry Door and All
Cargo Door Skin Cutout Lower Corners - Skin and Bear Strap 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Unpublished Work.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: October 12, 2022
757-53A0119 RB
1 of 178
3.0

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Export Controlled ECCN: 9E991
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Original Issue: October 12, 2022
757-53A0119 RB
2 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT
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Table of Contents
1 . E F F E C T I V I T Y  ................................................ 5
A. Airplanes ................................................ 5
B . S p a r e s  A f f e c t e d  ............................................ 7
2. CONCURRENT REQUIREMENTS ..................................... 7
3 . C O M P L I A N C E  ................................................ 7
4. APPROVAL ................................................ 3 7
5. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9
A. General Information ......................................... 3 9
B. Work Instructions ........................................... 4 0
FIGURE 1: SKIN AT THE LOWER CORNERS OF THE NO. 1, NO. 2, AND NO. 4 PASSENGER ENTRY
DOORS, LEFT SIDE - GENERAL VISUAL INSPECTION [Group 1-3, 5-7] ......... 7 5
FIGURE 2: SKIN AT THE LOWER CORNERS OF THE NO. 1, NO. 2, AND NO. 4 PASSENGER ENTRY
DOORS, RIGHT SIDE - GENERAL VISUAL INSPECTION [Group 1-3, 5-7] ........ 7 7
FIGURE 3: SKIN AT THE LOWER CORNERS OF THE NO. 1 AND NO. 2 CARGO DOORS - GENERAL
VISUAL INSPECTION ..................................... 7 9
FIGURE 4: SKIN AT THE LOWER CORNERS OF THE NO. 3 CARGO DOOR - GENERAL VISUAL
INSPECTION [Group 2, 6] ................................... 8 1
FIGURE 5: SKIN AT THE LOWER CORNERS OF THE CREW ENTRY DOOR - GENERAL VISUAL
INSPECTION [Group 4] .................................... 8 3
FIGURE 6: SKIN AT THE LOWER CORNERS OF THE MAIN DECK CARGO DOOR - GENERAL VISUAL
INSPECTION [Group 4-6] ................................... 8 5
FIGURE 7: SKIN AT THE LOWER CORNERS OF THE NO. 1 PASSENGER ENTRY DOOR LEFT SIDE -
HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ........... 8 7
FIGURE 8: SKIN AT THE LOWER CORNERS OF THE NO. 1 PASSENGER ENTRY DOOR RIGHT SIDE
- HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] .......... 9 0
FIGURE 9: SKIN AT THE LOWER CORNERS OF THE NO. 2 PASSENGER ENTRY DOOR LEFT SIDE -
HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ........... 9 3
FIGURE 10: SKIN AT THE LOWER CORNERS OF THE NO. 2 PASSENGER ENTRY DOOR RIGHT SIDE
- HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] .......... 9 6
FIGURE 11: SKIN AT THE LOWER CORNERS OF THE NO. 4 PASSENGER ENTRY DOOR LEFT SIDE -
HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ........... 9 9
FIGURE 12: SKIN AT THE LOWER CORNERS OF THE NO. 4 PASSENGER ENTRY DOOR RIGHT SIDE
- HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ......... 1 0 2
FIGURE 13: SKIN AT THE LOWER CORNERS OF THE NO. 1 CARGO DOOR - HIGH FREQUENCY EDDY
CURRENT INSPECTION ................................... 1 0 5
FIGURE 14: SKIN AT THE LOWER CORNERS OF THE NO. 2 CARGO DOOR - HIGH FREQUENCY EDDY
CURRENT INSPECTION ................................... 1 0 8
FIGURE 15: SKIN AT THE LOWER CORNERS OF THE NO. 3 CARGO DOOR - HIGH FREQUENCY EDDY
CURRENT INSPECTION [Group 2, 6] ............................ 1 1 1
FIGURE 16: SKIN AT THE LOWER CORNERS OF THE CREW ENTRY DOOR - HIGH FREQUENCY EDDY
CURRENT INSPECTION [Group 4] ............................. 1 1 4
FIGURE 17: SKIN AT THE LOWER CORNERS OF THE MAIN DECK CARGO DOOR - HIGH FREQUENCY
EDDY CURRENT INSPECTION [Group 4-6] ........................ 1 1 7
FIGURE 18: SKIN AND BEAR STRAP AT THE LOWER CORNERS OF THE NO. 1 CARGO DOOR - OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION ............... 1 2 0
FIGURE 19: SKIN AND BEAR STRAP AT THE LOWER CORNERS OF THE NO. 2 CARGO DOOR - OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION ............... 1 2 3
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 4

FIGURE 20: SKIN AND BEAR STRAP AT THE LOWER CORNERS OF THE NO. 3 CARGO DOOR - OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 2, 6] ........ 1 2 6
FIGURE 21: SKIN AND BEAR STRAP AT THE LOWER CORNERS OF THE CREW ENTRY DOOR - OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 4] .......... 1 2 9
FIGURE 22: SKIN AND BEAR STRAP AT THE LOWER CORNERS OF THE MAIN DECK CARGO DOOR
- OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 4-6] .... 1 3 2
FIGURE 23: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 1 PASSENGER ENTRY DOOR LEFT
SIDE - LOW FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ...... 1 3 5
FIGURE 24: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 1 PASSENGER ENTRY DOOR RIGHT
SIDE - LOW FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ...... 1 3 9
FIGURE 25: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 2 PASSENGER ENTRY DOOR LEFT
SIDE - LOW FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ...... 1 4 3
FIGURE 26: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 2 PASSENGER ENTRY DOOR RIGHT
SIDE - LOW FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ...... 1 4 7
FIGURE 27: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 4 PASSENGER ENTRY DOOR LEFT
SIDE - LOW FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ...... 1 5 1
FIGURE 28: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 4 PASSENGER ENTRY DOOR RIGHT
SIDE - LOW FREQUENCY EDDY CURRENT INSPECTION [Group 1-3, 5-7] ...... 1 5 5
FIGURE 29: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 1 CARGO DOOR - LOW FREQUENCY
EDDY CURRENT INSPECTION ............................... 1 5 9
FIGURE 30: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 2 CARGO DOOR - LOW FREQUENCY
EDDY CURRENT INSPECTION ............................... 1 6 3
FIGURE 31: BEAR STRAP AT THE LOWER CORNERS OF THE NO. 3 CARGO DOOR - LOW FREQUENCY
EDDY CURRENT INSPECTION [Group 2, 6] ........................ 1 6 7
FIGURE 32: BEAR STRAP AT THE LOWER CORNERS OF THE CREW ENTRY DOOR - LOW FREQUENCY
EDDY CURRENT INSPECTION [Group 4] ......................... 1 7 1
FIGURE 33: BEAR STRAP AT THE LOWER CORNERS OF THE MAIN DECK CARGO DOOR - LOW
FREQUENCY EDDY CURRENT INSPECTION [Group 4-6] ................ 1 7 5
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 5

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0119 RB
Original Issue: October 12, 2022
ATA System: 5300
SUBJECT: FUSELAGE - No 1, No. 2 and No 4 Passenger Entry Door, Crew Entry Door and All
Cargo Door Skin Cutout Lower Corners - Skin and Bear Strap 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, 757-300 Airplane(s), line number(s)
1-1050 in 7 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 are given below.
DESCRIPTIONCONFIGURATIONGROUP
757-200 airplanes with 4 passenger doors each side and 2 cargo
doors.
-1
757-200 airplanes with 4 passenger doors each side and 3 cargo
doors.
-2
757-200 airplanes with overwing emergency exits.-3
757-200 PF airplanes.-4
757-200 CB airplane.-5
757-200 airplanes that have incorporated STC ST00916WI-D (Special
Freighter Conversion).
-6
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### Page 6

DESCRIPTIONCONFIGURATIONGROUP
757-300 airplanes.-7
Airplane Models:
757-200, 757-200CB, 757-200PF, 757-300
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
7NL001 - NL002
7NL006 - NL017
7NL101 - NL109
7NL141
7NL601 - NL616
3NN001 - NN002
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REQUIREMENTS BULLETIN 757-53A0119
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GroupVariable Number
3NN051 - NN052
1NP901 - NP904
4NS601 - NS616
4NT001 - NT009
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
GroupVariable Number
3NT701 - NT769
3NT791 - NT796
3NT861 - NT862
3NT881 - NT885
3NT901 - NT916
3NT971 - NT985
3NU031 - NU038
7NU701 - NU705
7NU721 - NU728
7NU731 - NU732
--
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 757-53A0119 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-53A0119 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 5, in accordance
with Paragraph 3. 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.
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### Page 8

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0119 RB.
Before 30,000
total flight cy-
cles.
Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the No. 1, No. 2, and No. 4
passenger entry door skin
cutouts.
All airplanes.
-Before further flight.CONDITION 1 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 1: ANY
REPAIR FOUND.
Before further flight.CONDITION 1 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack in the unrepaired
areas.
Before further flight.CONDITION 1 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack in the unre-
paired areas.
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757-53A0119 RB
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 9

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 1.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 1.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 1.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
3,000 flight cycles.-CONDITION 1.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
3,000 flight cycles.-CONDITION 1.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
CONDITION 1.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 1.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
Export Controlled ECCN: 9E991
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Original Issue: October 12, 2022
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 10

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION 1):
Do an external surface HFEC
inspection on the skin around
the fastener heads/holes at
the door cutout lower corners
of the No. 1, No. 2, and No.
4 passenger entry doors for
any skin crack.
CONDITION 2: NO
REPAIR FOUND.
Before further flight.CONDITION 2 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack.
-Before further flight.CONDITION 2.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 2.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 2.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
3,000 flight cycles.-CONDITION 2.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
Export Controlled ECCN: 9E991
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 11

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 2.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
CONDITION 2.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 2.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 12

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0119 RB.
Before 30,000
total flight cy-
cles.
Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the No. 1 and No. 2 cargo
door skin cutouts.
All airplanes.
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 13

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 3 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 3: ANY
REPAIR FOUND.
Before further flight.CONDITION 3 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack in the
unrepaired areas.
Before further flight.CONDITION 3 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No.1 and
No. 2 cargo doors for any
bear strap crack in the unre-
paired areas.
Before further flight.CONDITION 3 (ACTION 4):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 1 and No. 2
cargo doors for any skin or
bear strap crack in the unre-
paired areas.
Export Controlled ECCN: 9E991
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Original Issue: October 12, 2022
757-53A0119 RB
13 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 14

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 3.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 3.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 3.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
3,000 flight cycles.-CONDITION 3.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
3,000 flight cycles.-CONDITION 3.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.
2 cargo doors for any skin or
bear strap crack. (c)
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Original Issue: October 12, 2022
757-53A0119 RB
14 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 15

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 3.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
CONDITION 3.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 3.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
3,000 flight cycles.-CONDITION 3.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.
2 cargo doors for any skin or
bear strap crack. (c)
-Before further flight.CONDITION 4 (ACTION 1):
Do an external surface HFEC
inspection on the skin around
the fastener heads at the
door cutout lower corners of
the No. 1 and No. 2 cargo
doors for any skin crack.
CONDITION 4: NO
REPAIR FOUND.
Before further flight.CONDITION 4 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack.
Before further flight.CONDITION 4 (ACTION 3):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 1 and No. 2
cargo doors for any skin or
bear strap crack.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
15 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 16

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 4.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 4.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 4.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
3,000 flight cycles.-CONDITION 4.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
3,000 flight cycles.CONDITION 4.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.
2 cargo doors for any skin or
bear strap crack. (c)
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Original Issue: October 12, 2022
757-53A0119 RB
16 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 17

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 4.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
CONDITION 4.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 4.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
3,000 flight cycles.-CONDITION 4.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.
2 cargo doors for any skin or
bear strap crack. (c)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
17 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 18

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
(c) In a repair affected area, it is not required to repeat the open hole HFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0119 RB.
Before 30,000
total flight cy-
cles.
Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the No. 3 cargo door skin
cutout.
All airplanes.
Export Controlled ECCN: 9E991
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Original Issue: October 12, 2022
757-53A0119 RB
18 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 19

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 5 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 5: ANY
REPAIR FOUND.
Before further flight.CONDITION 5 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack in the unre-
paired areas.
Before further flight.CONDITION 5 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack
in the unrepaired areas.
Before further flight.CONDITION 5 (ACTION 4):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 3 cargo door
for any skin or bear strap
crack in the unrepaired areas.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
19 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 20

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 5.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 5.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 5.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
3,000 flight cycles.-CONDITION 5.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
3,000 flight cycles.-CONDITION 5.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
20 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 21

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 5.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
CONDITION 5.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 5.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
3,000 flight cycles.-CONDITION 5.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
-Before further flight.CONDITION 6 (ACTION 1):
Do an external surface HFEC
on the skin around the fasten-
er heads at the door cutout
lower corners of the No. 3
cargo door for any skin crack.
CONDITION 6: NO
REPAIR FOUND.
Before further flight.CONDITION 6 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
Before further flight.CONDITION 6 (ACTION 3):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 3 cargo door
for any skin or bear strap
crack.
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
21 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 22

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 6.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 6.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 6.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
3,000 flight cycles.-CONDITION 6.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
3,000 flight cycles.-CONDITION 6.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
22 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 23

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 6.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
CONDITION 6.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 6.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
3,000 flight cycles.-CONDITION 6.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
23 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 24

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
(c) In a repair affected area, it is not required to repeat the open hole HFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0119 RB.
Before 30,000
total flight cy-
cles.
Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the crew entry door skin
cutout.
All airplanes.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
24 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 25

Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 7 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 7: ANY
REPAIR FOUND.
Before further flight.CONDITION 7 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener heads at
the door cutout lower corners
of the crew entry door for any
skin crack in the unrepaired
areas.
Before further flight.CONDITION 7 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the crew entry
door for any bear strap crack
in the unrepaired areas.
Before further flight.CONDITION 7 (ACTION 4):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the crew entry door
for any skin or bear strap
crack in the unrepaired areas.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
25 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 26

Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 7.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 7.1: ANY
CRACK FOUND.
12,000 flight cy-
cles.
-CONDITION 7.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the crew entry door for any
skin crack. (a)
12,000 flight cy-
cles.
-CONDITION 7.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the crew entry
door for any bear strap crack.
(b)
12,000 flight cy-
cles.
-CONDITION 7.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the crew entry door
for any skin or bear strap
crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
26 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 27

Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
12,000 flight cy-
cles.
-CONDITION 7.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the crew entry door for any
skin crack. (a)
CONDITION 7.2: NO
CRACK FOUND.
12,000 flight cy-
cles.
-CONDITION 7.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the crew entry
door for any bear strap crack.
(b)
12,000 flight cy-
cles.
-CONDITION 7.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the crew entry door
for any skin or bear strap
crack. (c)
-Before further flight.CONDITION 8 (ACTION 1):
Do an external surface HFEC
inspection on the skin around
the fastener heads at the
door cutout lower corners of
the crew entry door for any
skin crack.
CONDITION 8: NO
REPAIR FOUND.
Before further flight.CONDITION 8 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads at the door cutout low-
er corners of the crew entry
door for any bear strap crack.
Before further flight.CONDITION 8 (ACTION 3):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the crew entry door
for any skin or bear strap
crack.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
27 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 28

Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 8.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 8.1: ANY
CRACK FOUND.
12,000 flight cy-
cles.
-CONDITION 8.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the crew entry door for any
skin crack. (a)
12,000 flight cy-
cles.
-CONDITION 8.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the crew entry
door for any bear strap crack.
(b)
12,000 flight cy-
cles.
-CONDITION 8.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the crew entry door
for any skin or bear strap
crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
28 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 29

Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
12,000 flight cy-
cles.
-CONDITION 8.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the crew entry door for any
skin crack. (a)
CONDITION 8.2: NO
CRACK FOUND.
12,000 flight cy-
cles.
-CONDITION 8.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the crew entry
door for any bear strap crack.
(b)
12,000 flight cy-
cles.
-CONDITION 8.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the crew entry door
for any skin or bear strap
crack. (c)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
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ALERTALERT

### Page 30

Group 4:
Table 4: Inspection of the Skin and Bear Strap at the Lower Corners of the Crew Entry Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
(c) In a repair affected area, it is not required to repeat the open hole HFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0119 RB.
Before 30,000
total flight cy-
cles.
Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the main deck cargo door
skin cutout.
All airplanes.
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ALERTALERT

### Page 31

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 9 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 9: ANY
REPAIR FOUND.
Before further flight.CONDITION 9 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener heads at
the door cutout lower corners
of the main deck cargo door
for any skin crack in the unre-
paired areas.
Before further flight.CONDITION 9 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the main deck
cargo door for any bear strap
crack in the unrepaired areas.
Before further flight.CONDITION 9 (ACTION 4):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the main deck cargo
door for any skin or bear
strap crack in the unrepaired
areas.
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ALERTALERT

### Page 32

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 9.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 9.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 9.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the main deck cargo door
for any skin crack. (a)
3,000 flight cycles.-CONDITION 9.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the main deck
cargo door for any bear strap
crack. (b)
3,000 flight cycles.-CONDITION 9.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the main deck car-
go door for any skin or bear
strap crack. (c)
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### Page 33

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 9.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the main deck cargo door
for any skin crack. (a)
CONDITION 9.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 9.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the main deck
cargo door for any bear strap
crack. (b)
3,000 flight cycles.-CONDITION 9.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the main deck car-
go door for any skin or bear
strap crack. (c)
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### Page 34

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 10 (ACTION 1):
Do an external surface HFEC
inspection on the skin around
the fastener heads at the
door cutout lower corners of
the main deck cargo door for
any skin crack.
CONDITION 10: NO
REPAIR FOUND.
Before further flight.CONDITION 10 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads at the door cutout low-
er corners of the main deck
cargo door for any bear strap
crack.
Before further flight.CONDITION 10 (ACTION 3):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the main deck cargo
door for any skin or bear
strap crack.
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ALERTALERT

### Page 35

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 10.1 (ACTION
1): Contact The Boeing Com-
pany for repair instructions
and do the repair.
CONDITION 10.1: ANY
CRACK FOUND.
3,000 flight cycles.-CONDITION 10.1 (ACTION
2): Repeat the external sur-
face HFEC inspection on the
skin around the fastener
heads at the door cutout low-
er corners of the main deck
cargo door for any skin crack.
(a)
3,000 flight cycles.-CONDITION 10.1 (ACTION
3): Repeat the external sub-
surface LFEC inspection
through the skin around the
fastener heads at the door
cutout lower corners of the
main deck cargo door for any
bear strap crack. (b)
3,000 flight cycles.-CONDITION 10.1 (ACTION
4): Repeat the open hole
HFEC inspection of the fasten-
er holes at the door cutout
lower corners of the main
deck cargo door for any skin
or bear strap crack. (c)
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### Page 36

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-CONDITION 10.2 (ACTION
1): Repeat the external sur-
face HFEC inspection on the
skin around the fastener
heads at the door cutout low-
er corners of the main deck
cargo door for any skin crack.
(a)
CONDITION 10.2: NO
CRACK FOUND.
3,000 flight cycles.-CONDITION 10.2 (ACTION
2): Repeat the external sub-
surface LFEC inspection
through the skin around the
fastener heads at the door
cutout lower corners of the
main deck cargo door for any
bear strap crack. (b)
3,000 flight cycles.-CONDITION 10.2 (ACTION
3): Repeat the open hole
HFEC inspection of the fasten-
er holes at the door cutout
lower corners of the main
deck cargo door for any skin
or bear strap crack. (c)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 37

Group 4-6:
Table 5: Inspection of the Skin and Bear Strap at the Lower Corners of the Main Deck Cargo Door
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
(c) In a repair affected area, it is not required to repeat the open hole HFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
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 38

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38 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT
BLANK PAGE

### Page 39

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. 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 are given in 757 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.
4. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
5. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION or an OPTION,
do all of the ACTION numbers for that CONDITION or OPTION.
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REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 40

6. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
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. Boeing Service Letter 757-SL-51-22, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
9. 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.
10. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
11. 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.
12. A maintenance records check for any existing repair at the door corner area can be
done if any existing repair can be conclusively determined from that check.
B. WORK INSTRUCTIONS
Actions Required for Compliance
1. Requirements
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### Page 41

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 1: SCUFF
PLATE REMOVAL.
-Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the No. 1, No. 2, and No. 4
passenger entry door skin
cutouts.
All airplanes.
-LEFT SIDE: FIGURE 1
and
RIGHT SIDE: FIGURE 2
--CONDITION 1 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 1: ANY
REPAIR FOUND.
-LEFT SIDE: FIGURE 7,
FIGURE 9, FIGURE 11
and
CONDITION 1 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack in the unrepaired
areas.
RIGHT SIDE: FIGURE 8,
FIGURE 10, FIGURE 12
-LEFT SIDE: FIGURE 23,
FIGURE 25, FIGURE 27
and
CONDITION 1 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack in the unre-
paired areas.
RIGHT SIDE: FIGURE 24,
FIGURE 26, FIGURE 28
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### Page 42

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 1.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 1.1: ANY
CRACK FOUND. Do PART 2: SCUFF
PLATE INSTALLATION.
-
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 1.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
-LEFT SIDE: FIGURE 7,
FIGURE 9, FIGURE 11
and
RIGHT SIDE: FIGURE 8,
FIGURE 10, FIGURE 12
-LEFT SIDE: FIGURE 23,
FIGURE 25, FIGURE 27
and
CONDITION 1.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
RIGHT SIDE: FIGURE 24,
FIGURE 26, FIGURE 28
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### Page 43

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 2: SCUFF
PLATE INSTALLATION.
--CONDITION 1.2: NO
CRACK FOUND.
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 1.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
-LEFT SIDE: FIGURE 7,
FIGURE 9, FIGURE 11
and
RIGHT SIDE: FIGURE 8,
FIGURE 10, FIGURE 12
-LEFT SIDE: FIGURE 23,
FIGURE 25, FIGURE 27
and
CONDITION 1.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
RIGHT SIDE: FIGURE 24,
FIGURE 26, FIGURE 28
-LEFT SIDE: FIGURE 7,
FIGURE 9, FIGURE 11
and
CONDITION 2 (ACTION 1):
Do an external surface HFEC
inspection on the skin around
the fastener heads/holes at
the door cutout lower corners
of the No. 1, No. 2, and No.4
passenger entry doors for any
skin crack
CONDITION 2: NO
REPAIR FOUND.
RIGHT SIDE: FIGURE 8,
FIGURE 10, FIGURE 12
-LEFT SIDE: FIGURE 23,
FIGURE 25, FIGURE 27
and
CONDITION 2 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack.
RIGHT SIDE: FIGURE 24,
FIGURE 26, FIGURE 28
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REQUIREMENTS BULLETIN 757-53A0119
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### Page 44

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 2.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 2.1: ANY
CRACK FOUND. Do PART 2: SCUFF
PLATE INSTALLATION.
-
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 2.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
-LEFT SIDE: FIGURE 7,
FIGURE 9, FIGURE 11
and
RIGHT SIDE: FIGURE 8,
FIGURE 10, FIGURE 12
-LEFT SIDE: FIGURE 23,
FIGURE 25, FIGURE 27
and
CONDITION 2.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
RIGHT SIDE: FIGURE 24,
FIGURE 26, FIGURE 28
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757-53A0119 RB
44 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 45

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 2: SCUFF
PLATE INSTALLATION.
--CONDITION 2.2: NO
CRACK FOUND.
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 2.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
skin crack. (a)
-LEFT SIDE: FIGURE 7,
FIGURE 9, FIGURE 11
and
RIGHT SIDE: FIGURE 8,
FIGURE 10, FIGURE 12
-LEFT SIDE: FIGURE 23,
FIGURE 25, FIGURE 27
and
CONDITION 2.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads/holes at the door
cutout lower corners of the
No. 1, No. 2, and No. 4 pas-
senger entry doors for any
bear strap crack. (b)
RIGHT SIDE: FIGURE 24,
FIGURE 26, FIGURE 28
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
45 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 46

Group 1-3, 5-7:
Table 1: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1, No. 2, and No. 4 Pas-
senger Entry Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 1: SCUFF
PLATE REMOVAL.
-Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the No. 1 and No. 2 cargo
door skin cutouts.
All airplanes.
-FIGURE 3
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
46 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 47

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 3 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 3: ANY
REPAIR FOUND.
-FIGURE 13 AND FIGURE
14
CONDITION 3 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack in the
unrepaired areas.
-FIGURE 29 AND FIGURE
30
CONDITION 3 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No.1 and
No. 2 cargo doors for any
bear strap crack in the unre-
paired areas.
-FIGURE 18 AND FIGURE
19
CONDITION 3 (ACTION 4):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 1 and No. 2
cargo doors for any skin or
bear strap crack in the unre-
paired areas.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
47 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 48

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 3.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 3.1: ANY
CRACK FOUND. Do PART 2: SCUFF
PLATE INSTALLATION.
-
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 3.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
-FIGURE 13 AND FIGURE
14
-FIGURE 29 AND FIGURE
30
CONDITION 3.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
-FIGURE 18 AND FIGURE
19
CONDITION 3.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.2
cargo doors for any skin or
bear strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
48 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 49

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 2: SCUFF
PLATE INSTALLATION.
--CONDITION 3.2: NO
CRACK FOUND.
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 3.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
-FIGURE 13 AND FIGURE
14
-FIGURE 29 AND FIGURE
30
CONDITION 3.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
-FIGURE 18 AND FIGURE
19
CONDITION 3.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.
2 cargo doors for any skin or
bear strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
49 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 50

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-FIGURE 13 AND FIGURE
14
CONDITION 4 (ACTION 1):
Do an external surface HFEC
inspection on the skin around
the fastener heads at the
door cutout lower corners of
the No. 1 and No. 2 cargo
doors for any skin crack.
CONDITION 4: NO
REPAIR FOUND.
-FIGURE 29 AND FIGURE
30
CONDITION 4 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack.
-FIGURE 18 AND FIGURE
19
CONDITION 4 (ACTION 3):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 1 and No. 2
cargo doors for any skin or
bear strap crack.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
50 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 51

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 4.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 4.1: ANY
CRACK FOUND. Do PART 2: SCUFF
PLATE INSTALLATION.
-
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 4.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
-FIGURE 13 AND FIGURE
14
-FIGURE 29 AND FIGURE
30
CONDITION 4.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
-FIGURE 18 AND FIGURE
19
CONDITION 4.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.2
cargo doors for any skin or
bear strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
51 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 52

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 2: SCUFF
PLATE INSTALLATION.
--CONDITION 4.2: NO
CRACK FOUND.
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 4.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 1 and No. 2 cargo
doors for any skin crack. (a)
-FIGURE 13 AND FIGURE
14
-FIGURE 29 AND FIGURE
30
CONDITION 4.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 1 and
No. 2 cargo doors for any
bear strap crack. (b)
-FIGURE 18 AND FIGURE
19
CONDITION 4.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 1 and No.2
cargo doors for any skin or
bear strap crack. (c)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
52 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 53

Table 2: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 1 and No. 2 Cargo Doors
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
(c) In a repair affected area, it is not required to repeat the open hole HFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
53 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 54

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 1: SCUFF
PLATE REMOVAL.
-Do a General Visual Inspec-
tion (GVI) or a maintenance
records check for any existing
repair at the lower corners of
the No. 3 cargo door skin
cutout.
All airplanes.
-FIGURE 4
--CONDITION 5 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspection
and corrective action instruc-
tions and do the alternative
inspections and applicable
corrective actions.
CONDITION 5: ANY
REPAIR FOUND.
-FIGURE 15CONDITION 5 (ACTION 2):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack in the unre-
paired areas.
-FIGURE 31CONDITION 5 (ACTION 3):
Do an external sub-surface
Low Frequency Eddy Current
(LFEC) inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack
in the unrepaired areas.
-FIGURE 20CONDITION 5 (ACTION 4):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 3 cargo door
for any skin or bear strap
crack in the unrepaired areas.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
54 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 55

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 5.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 5.1: ANY
CRACK FOUND. Do PART 2: SCUFF
PLATE INSTALLATION.
-
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 5.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
-FIGURE 15
-FIGURE 31CONDITION 5.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
-FIGURE 20CONDITION 5.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
55 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 56

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 2: SCUFF
PLATE INSTALLATION.
--CONDITION 5.2: NO
CRACK FOUND.
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 5.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
-FIGURE 15
-FIGURE 31CONDITION 5.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
-FIGURE 20CONDITION 5.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
56 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 57

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-FIGURE 15CONDITION 6 (ACTION 1):
Do an external surface HFEC
on the skin around the fasten-
er heads at the door cutout
lower corners of the No. 3
cargo door for any skin crack.
CONDITION 6: NO
REPAIR FOUND.
-FIGURE 31CONDITION 6 (ACTION 2):
Do an external sub-surface
LFEC inspection through the
skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
-FIGURE 20CONDITION 6 (ACTION 3):
Do an open hole HFEC in-
spection of the fastener holes
at the door cutout lower cor-
ners of the No. 3 cargo door
for any skin or bear strap
crack.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
57 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 58

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 6.1 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 6.1: ANY
CRACK FOUND. Do PART 2: SCUFF
PLATE INSTALLATION.
-
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 6.1 (ACTION 2):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
-FIGURE 15
-FIGURE 31CONDITION 6.1 (ACTION 3):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
-FIGURE 20CONDITION 6.1 (ACTION 4):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
58 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 59

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 2: SCUFF
PLATE INSTALLATION.
--CONDITION 6.2: NO
CRACK FOUND.
Do PART 1: SCUFF
PLATE REMOVAL.
-CONDITION 6.2 (ACTION 1):
Repeat the external surface
HFEC inspection on the skin
around the fastener heads at
the door cutout lower corners
of the No. 3 cargo door for
any skin crack. (a)
-FIGURE 15
-FIGURE 31CONDITION 6.2 (ACTION 2):
Repeat the external sub-sur-
face LFEC inspection through
the skin around the fastener
heads at the door cutout low-
er corners of the No. 3 cargo
door for any bear strap crack.
(b)
-FIGURE 20CONDITION 6.2 (ACTION 3):
Repeat the open hole HFEC
inspection of the fastener
holes at the door cutout lower
corners of the No. 3 cargo
door for any skin or bear
strap crack. (c)
(a) In a repair affected area, it is not required to repeat the external surface HFEC inspection in accordance
with Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
59 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

### Page 60

Group 2, 6:
Table 3: Inspection of the Skin and Bear Strap at the Lower Corners of the No. 3 Cargo Door
Refer to the listed proce-
dures in SB 757-53A0119
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
(b) In a repair affected area, it is not required to repeat the sub-surface LFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
(c) In a repair affected area, it is not required to repeat the open hole HFEC inspection in accordance with
Requirements Bulletin 757-53A0119 RB, provided the repair and its approval meet all of the following
criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0119 RB.
2. The repair is approved by the Boeing Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area, states the repeat inspection
requirements for the repair affected area, and approves the repeat inspection requirements as
an alternative method of compliance (AMOC).
Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspec-
tions outside of the repair affected area must continue in accordance with this bulletin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 12, 2022
757-53A0119 RB
60 of 178
REQUIREMENTS BULLETIN 757-53A0119
ALERTALERT

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