# Boeing Alert Requirements Bulletin 747-57A2363 RB: No revision named

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- Title as filed: 747-57A2363 RB-00-
- Pages: 61
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### Page 1

Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-57A2363 RB
Original Issue: December 23, 2019
ATA System: 5744 5720
SUBJECT: WINGS - Nacelle Strut Attach Fittings - Inboard and Outboard Engine Struts - Upper
Wing Skin and Diagonal Brace - Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
Copyright © 2019 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Unpublished Work.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: December 23, 2019
747-57A2363 RB
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3.0

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Original Issue: December 23, 2019
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REQUIREMENTS BULLETIN 747-57A2363
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Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
FIGURE 1: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - UPPER WING SKIN - ULTRASONIC
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
FIGURE 2: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS
AND LOWER LINK FITTING - DETAILED AND ULTRASONIC INSPECTION . . . . . . . 41
FIGURE 3: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - UPPER WING SKIN - ULTRASONIC
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
FIGURE 4: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS
AND LOWER LINK FITTING - DETAILED AND ULTRASONIC INSPECTION . . . . . . . 47
FIGURE 5: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - UPPER WING SKIN - ULTRASONIC
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51
FIGURE 6: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS
AND LOWER LINK FITTING - DETAILED AND ULTRASONIC INSPECTION . . . . . . . 53
FIGURE 7: RIGHT WING - OUTBOARD ENGINE STRUT POSITION 4 - UPPER WING SKIN - ULTRASONIC
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57
FIGURE 8: RIGHT WING - OUTBOARD ENGINE STRUT POSITION 4 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS
AND LOWER LINK FITTING - DETAILED AND ULTRASONIC INSPECTION . . . . . . . 58
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REQUIREMENTS BULLETIN 747-57A2363
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Export Controlled ECCN: 9E991
Copyright © Unpublished
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REQUIREMENTS BULLETIN 747-57A2363
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### Page 5

Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-57A2363 RB
Original Issue: December 23, 2019
ATA System: 5744 5720
SUBJECT: WINGS - Nacelle Strut Attach Fittings - Inboard and Outboard Engine Struts - Upper
Wing Skin and Diagonal Brace - 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 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F,
747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR Airplane(s), line number(s) 1-1419 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.
DESCRIPTIONCONFIGURATIONGROUP
747-100/-200B/-200C/-200F/747SP/747SR light wing airplanes with
Pratt & Whitney or General Electric engines
-1
747-100B/-100B SUD/-200B/-200C/-200F/-300/747SP heavy wing
airplanes with Pratt & Whitney engines
-2
747-SR/-200B/-200C/-200F/-300 heavy wing airplanes with General
Electric engines
-3
747-100B/-200B/-200F/-300/747SP airplanes with Rolls Royce
engines
-4
747-400/-400D/-400F airplanes with Pratt & Whitney or General
Electric engines
-5
747-400/-400F airplanes with Rolls Royce engines-6
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DESCRIPTIONCONFIGURATIONGROUP
747-400/-400F extended range airplanes with Pratt & Whitney or
General Electric engines
-7
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SP, 747SR
GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA543
2RA544 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA727
GroupVariable Number
2RA728 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA783
2RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
4RB411 - RB413
2RB421
1RB601 - RB607
3RB681 - RB697
2RB711
2RB721 - RB723
4RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD047
2RD048 - RD059
1RD071 - RD072
2RD081 - RD083
2RD091 - RD092
GroupVariable Number
1RD101 - RD104
1RD121
2RD122 - RD127
4RD131 - RD144
3RD166 - RD167
3RD171 - RD172
3RD181 - RD183
1RD201 - RD203
2RD204
2RD221 - RD227
3RD231 - RD235
2RD241 - RD243
2RD251 - RD262
3RD271 - RD272
3RD291 - RD292
2RD301 - RD302
4RD311
4RD351 - RD358
3RD361 - RD366
3RD381 - RD383
3RD411 - RD414
2RD421 - RD426
2RD431 - RD435
2RD441 - RD442
3RD451 - RD456
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GroupVariable Number
3RD461
4RD471 - RD475
1RD513 - RD514
2RD515 - RD516
4RD517 - RD519
2RD531
4RD532 - RD533
1RD551
2RD561
2RD571
3RD581 - RD583
2RD591 - RD593
3RD601 - RD607
1RD621 - RD623
3RD641 - RD649
3RD651 - RD659
3RD661
1RD671
1RD681 - RD682
3RD691 - RD692
3RD701 - RD702
3RD721 - RD722
2RD741 - RD742
3RD751 - RD755
2RD761
3RD771 - RD775
2RD781 - RD783
3RD791 - RD792
2RE001
7RF001 - RF006
1RG001 - RG009
1RG091
1RG095
GroupVariable Number
1RG101 - RG104
1RG121 - RG126
1RG141 - RG142
2RG161 - RG164
1RG171 - RG174
1RG191 - RG193
1RG211 - RG213
1RG221 - RG222
4RH101 - RH102
4RH111 - RH112
4RH121 - RH122
1RJ131 - RJ133
1RJ151 - RJ152
2RJ301 - RJ303
3RJ321 - RJ322
3RJ331 - RJ333
5RL401 - RL403
5RL411 - RL436
7RL451 - RL456
5RL461 - RL462
5RL471 - RL481
5RL491 - RL492
5RL501 - RL502
7RL511 - RL516
7RL521 - RL522
7RL531 - RL534
6RL551
5RL561 - RL568
7RL571 - RL572
7RL576 - RL577
7RL579
7RL581 - RL586
5RL651 - RL655
GroupVariable Number
7RL671 - RL675
7RL681 - RL684
5RL751 - RL752
5RM001 - RM007
5RM010 - RM013
5RM021 - RM024
5RM026 - RM030
5RM036 - RM045
5RM051 - RM053
5RM071
5RM081 - RM084
5RM091
6RM096 - RM097
5RM116 - RM117
5RM126 - RM132
6RM136 - RM147
5RM156 - RM158
5RM166 - RM177
5RM191 - RM192
5RM231 - RM233
5RM241 - RM246
6RM261 - RM264
5RM316 - RM318
6RM331 - RM333
5RM341
5RM351 - RM355
5RM366 - RM367
5RM401 - RM403
5RM426
5RM431
5RM441 - RM443
5RM445
5RM801 - RM803
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GroupVariable Number
5RM811 - RM813
5RM851 - RM855
6RM856 - RM859
5RM861 - RM863
5RM871 - RM878
7RM879 - RM880
6RM881 - RM890
5RM891 - RM899
5RM901 - RM906
5RM911
1RR001 - RR004
2RR005
2RR021 - RR025
2RR031
1RR201
3RR202 - RR206
2RR221 - RR226
2RR261 - RR267
1RR301
3RR302 - RR310
3RR331 - RR332
2RR336
1RR341 - RR344
2RR345
2RR361 - RR362
2RR421 - RR422
2RR431 - RR432
4RR441 - RR442
2RR451
2RR501 - RR504
2RR521 - RR522
4RR526
4RR531
GroupVariable Number
3RR551 - RR556
3RR561
2RR566
5RR701
5RR721 - RR724
5RR746 - RR748
5RR851 - RR856
5RR861 - RR862
6RR951 - RR952
2RS001 - RS002
3RS201
2RS211 - RS212
2RS221 - RS222
2RS231 - RS241
2RS251 - RS259
2RS263
2RS265 - RS268
4RS271 - RS276
2RS291 - RS292
4RS301 - RS306
4RS311 - RS320
3RS331 - RS333
3RS341 - RS342
2RS699
2RS701 - RS703
3RS711 - RS713
3RS721 - RS722
2RS731 - RS732
2RS741 - RS743
3RS751 - RS752
3RS761 - RS762
2RS771
3RS781 - RS782
GroupVariable Number
2RS786
5RT001 - RT014
5RT021 - RT022
5RT031 - RT035
5RT041 - RT047
5RT061
5RT071 - RT075
5RT101 - RT103
5RT121
5RT131 - RT137
5RT151 - RT152
5RT161 - RT168
5RT401 - RT412
5RT431 - RT447
6RT451 - RT469
6RT471 - RT499
5RT501 - RT535
6RT551 - RT568
5RT571 - RT591
5RT601 - RT657
6RT671 - RT673
5RT681 - RT682
5RT691 - RT699
5RT701 - RT704
5RT711 - RT717
5RT741 - RT757
5RT776 - RT777
6RT781 - RT784
5RT801 - RT803
5RT811 - RT814
5RT831 - RT837
5RT861 - RT864
5RT876 - RT880
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GroupVariable Number
5RT931 - RT932
5RT945 - RT949
5RT951 - RT955
5RT966 - RT967
5RU001 - RU006
GroupVariable Number
5RU016 - RU017
5RU031 - RU032
5RU051 - RU052
5RU059 - RU062
5RU081 - RU083
GroupVariable Number
5RU101 - RU102
6RU121 - RU132
5RU801 - RU809
5RU831 - RU841
--
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 747-57A2363 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements bulletin 747-57A2363 RB mandatory.
Accomplish the required action(s), based on the applicable conditions in Tables 1 to 11 , in accordance
with the Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that
CONDITION or OPTION.
Group 1:
Table 1: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do an Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
All Airplanes
1,000 flight cycles-Repeat Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
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REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 10

Group 1:
Table 1: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
1,000 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at engine strut
positions 1 through 4 for
any crack.
Group 2:
Table 2: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do an Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
All Airplanes
2,000 flight cycles-Repeat Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
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REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 11

Group 2:
Table 2: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
2,000 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at engine strut
positions 1 through 4 for
any crack.
Group 3:
Table 3: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do an Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
All Airplanes
3,000 flight cycles-Repeat Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
Export Controlled ECCN: 9E991
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Original Issue: December 23, 2019
747-57A2363 RB
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REQUIREMENTS BULLETIN 747-57A2363
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### Page 12

Group 3:
Table 3: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
3,000 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at engine strut
positions 1 through 4 for
any crack.
Group 4:
Table 4: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
ACTION 1: Do an Ultra-
sonic inspection of the
upper wing skin at out-
board engine strut posi-
tions 1 and 4 for any
crack.
All Airplanes
-ACTION 2: Do an Ultra-
sonic inspection of the
upper wing skin at in-
board engine strut posi-
tions 2 and 3 for any
crack.
1,000 flight cycles-CONDITION 1 (ACTION
1): Repeat Ultrasonic in-
spection of the upper
wing skin at outboard en-
gine strut positions 1 and
4 for any crack.
CONDITION 1: NO
CRACK FOUND
2,000 flight cycles-CONDITION 1 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at inboard en-
gine strut positions 2 and
3 for any crack.
Export Controlled ECCN: 9E991
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Original Issue: December 23, 2019
747-57A2363 RB
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REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 13

Group 4:
Table 4: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1):Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
1,000 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at outboard en-
gine strut positions 1 and
4 for any crack.
2,000 flight cycles-CONDITION 2 (ACTION
3): Repeat Ultrasonic in-
spection of the upper
wing skin at inboard en-
gine strut positions 2 and
3 for any crack.
Group 5:
Table 5: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,250
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do an Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
All Airplanes
4,500 flight cycles-Repeat Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
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### Page 14

Group 5:
Table 5: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
4,500 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at engine strut
positions 1 through 4 for
any crack.
Group 6:
Table 6: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do an Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
All Airplanes
4,500 flight cycles-Repeat Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
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### Page 15

Group 6:
Table 6: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
4,500 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at engine strut
positions 1 through 4 for
any crack.
Group 7:
Table 7: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,500
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do an Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
All Airplanes
4,500 flight cycles-Repeat Ultrasonic inspec-
tion of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
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### Page 16

Group 7:
Table 7: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
4,500 flight cycles-CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper
wing skin at engine strut
positions 1 through 4 for
any crack.
Group 1-3:
Table 8: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do Detailed and Ultrason-
ic inspections of the strut
lower spar fitting, diago-
nal brace strut end clevis,
diagonal brace wing at-
tach end clevis and de-
tailed inspection of lower
link fitting at engine strut
positions 1 through 4 for
any crack.
All Airplanes
1,000 flight cycles-Repeat Detailed and Ultra-
sonic inspections of the
strut lower spar fitting, di-
agonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at engine
strut positions 1 through
4 for any crack.
CONDITION 1: NO
CRACK FOUND
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### Page 17

Group 1-3:
Table 8: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
1,000 flight cycles-CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at engine
strut positions 1 through
4 for any crack.
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### Page 18

Group 4, 6:
Table 9: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
ACTION 1: Do Detailed
and Ultrasonic inspec-
tions of the strut lower
spar fitting, diagonal
brace strut end clevis, di-
agonal brace wing attach
end clevis and detailed
inspection of lower link
fitting at inboard engine
strut positions 2 and 3 for
any crack.
All Airplanes
-ACTION 2: Do Detailed
and Ultrasonic inspec-
tions of the strut lower
spar fitting, diagonal
brace strut end clevis, di-
agonal brace wing attach
end clevis and detailed
inspection of lower link
fitting at outboard engine
strut positions 1 and 4 for
any crack.
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### Page 19

Group 4, 6:
Table 9: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
1,000 flight cycles-CONDITION 1 (ACTION
1): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at in-
board engine strut posi-
tions 2 and 3 for any
crack.
CONDITION 1: NO
CRACK FOUND
2,000 flight cycles-CONDITION 1 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at out-
board engine strut posi-
tions 1 and 4 for any
crack.
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ALERTALERT

### Page 20

Group 4, 6:
Table 9: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
1,000 flight cycles-CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at in-
board engine strut posi-
tions 2 and 3 for any
crack.
2,000 flight cycles-CONDITION 2 (ACTION
3): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at out-
board engine strut posi-
tions 1 and 4 for any
crack.
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### Page 21

Group 5:
Table 10: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,250
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
ACTION 1: Do Detailed
and Ultrasonic inspec-
tions of the strut lower
spar fitting, diagonal
brace strut end clevis, di-
agonal brace wing attach
end clevis and detailed
inspection of lower link
fitting at outboard engine
strut positions 1 and 4 for
any crack.
All Airplanes
-ACTION 2: Do Detailed
and Ultrasonic inspec-
tions of the strut lower
spar fitting, diagonal
brace strut end clevis, di-
agonal brace wing attach
end clevis and detailed
inspection of lower link
fitting at inboard engine
strut positions 2 and 3 for
any crack.
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### Page 22

Group 5:
Table 10: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
1,250 flight cycles-CONDITION 1 (ACTION
1): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at out-
board engine strut posi-
tions 1 and 4 for any
crack.
CONDITION 1: NO
CRACK FOUND
2,000 flight cycles-CONDITION 1 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at in-
board engine strut posi-
tions 2 and 3 for any
crack.
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### Page 23

Group 5:
Table 10: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
1,250 flight cycles-CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at out-
board engine strut posi-
tions 1 and 4 for any
crack.
2,000 flight cycles-CONDITION 2 (ACTION
3): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at in-
board engine strut posi-
tions 2 and 3 for any
crack.
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ALERTALERT

### Page 24

Group 7:
Table 11: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,500
flight cycles or 2
years after the
original issue
date of Require-
ments bulletin
747-57A2363
RB, whichever
occurs first.
Before 15,000
total flight cy-
cles.
Do Detailed and Ultrason-
ic inspections of the strut
lower spar fitting, diago-
nal brace strut end clevis,
diagonal brace wing at-
tach end clevis and de-
tailed inspection of lower
link fitting at engine strut
positions 1 through 4 for
any crack.
All Airplanes
1,500 flight cycles-Repeat Detailed and Ultra-
sonic inspections of the
strut lower spar fitting, di-
agonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at engine
strut positions 1 through
4 for any crack.
CONDITION 1: NO
CRACK FOUND
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2: ANY
CRACK FOUND
1,500 flight cycles-CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace
wing attach end clevis
and detailed inspection of
lower link fitting at engine
strut positions 1 through
4 for any crack.
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
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service 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.
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REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 25

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 26

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REQUIREMENTS BULLETIN 747-57A2363
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BLANK PAGE

### Page 27

5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. This is an Enhanced Required for Compliance document. There will be a separate
Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated
by an Airworthiness Directive (AD), then all applicable requirements specified in the
RB must be done. For the related SB, some locations are marked RC Start and RC
End to identify the requirements that are restated from the RB. For the related SB,
the areas between RC Start and RC End, including sub-steps and any figures
identified between RC Start and RC End, must be done to comply with the AD.
Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations
to steps between RC Start and RC End, including substeps and identified figures.
For the related SB, the steps not between RC Start and RC End may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC; this is provided that the
steps between RC Start and RC End, including sub-steps and identified figures, can
still be done as specified, and the airplane can be put back in an airworthy condition.
Figures not required for compliance are omitted from the RB.
2. This is an Enhanced Required for Compliance document. The Boeing processes
used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure
that the information between "RC Start" and "RC End" in the SB are identical to the
information in the same sections (Compliance, Work Instructions...) of the RB which
the SB refers to as the related document.
3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
4. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
5. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 747
Aircraft Maintenance Manual (AMM).
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### Page 28

— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
8. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation or assembly to detect damage, failure or irregularity. This could include
tactile assessment in which a component or assembly can be checked for
tightness/security. Available lighting is normally supplemented with a direct source
of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors
and magnifying lenses may be necessary. Surface cleaning and elaborate access
procedures may be required.
9. 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.
B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements:
Group 1-3, 5-7:
Table 1: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 1: PREPARATION-All Airplanes
-FIGURE 1, FIGURE 3,
FIGURE 5, FIGURE 7
Do an Ultrasonic inspec-
tion of the upper wing skin
at engine strut positions 1
through 4 for any crack.
PART 2: RESTORATION-
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### Page 29

Group 1-3, 5-7:
Table 1: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 1: PREPARATION-CONDITION 1: NO
CRACK FOUND -FIGURE 1, FIGURE 3,
FIGURE 5, FIGURE 7
Repeat Ultrasonic inspec-
tion of the upper wing skin
at engine strut positions 1
through 4 for any crack.
PART 2: RESTORATION-
--CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair instruc-
tions and do the repair.
CONDITION 2: ANY
CRACK FOUND
PART 2: RESTORATION-
PART 1: PREPARATION-
-FIGURE 1, FIGURE 3,
FIGURE 5, FIGURE 7
CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper wing
skin at engine strut posi-
tions 1 through 4 for any
crack.
PART 2: RESTORATION-
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### Page 30

Group 4:
Table 2: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 1: PREPARATION-All Airplanes
-FIGURE 1, FIGURE 7ACTION 1: Do an Ultrason-
ic inspection of the upper
wing skin at outboard en-
gine strut positions 1 and
4 for any crack.
-FIGURE 3, FIGURE 5ACTION 2: Do an Ultrason-
ic inspection of the upper
wing skin at inboard en-
gine strut positions 2 and
3 for any crack.
PART 2: RESTORATION-
PART 1: PREPARATION-CONDITION 1: NO
CRACK FOUND -FIGURE 1, FIGURE 7CONDITION 1 (ACTION
1): Repeat Ultrasonic in-
spection of the upper wing
skin at outboard engine
strut positions 1 and 4 for
any crack.
PART 2: RESTORATION-
PART 1: PREPARATION-
-FIGURE 3, FIGURE 5CONDITION 1 (ACTION
2): Repeat Ultrasonic in-
spection of the upper wing
skin at inboard engine strut
positions 2 and 3 for any
crack.
PART 2: RESTORATION-
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### Page 31

Group 4:
Table 2: Left and Right Wing - Inboard and Outboard Engine Struts - Upper Wing Skin - Ultrasonic In-
spection
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
--CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair instruc-
tions and do the repair.
CONDITION 2: ANY
CRACK FOUND
PART 2: RESTORATION-
PART 1: PREPARATION-
-FIGURE 1, FIGURE 7CONDITION 2 (ACTION
2): Repeat Ultrasonic in-
spection of the upper wing
skin at outboard engine
strut positions 1 and 4 for
any crack.
PART 2: RESTORATION-
PART 1: PREPARATION-
-FIGURE 3, FIGURE 5CONDITION 2 (ACTION
3): Repeat Ultrasonic in-
spection of the upper wing
skin at inboard engine strut
positions 2 and 3 for any
crack.
PART 2: RESTORATION-
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### Page 32

Group 1-3, 7:
Table 3: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 3: OPEN ACCESS-All Airplanes
-FIGURE 2, FIGURE 4,
FIGURE 6, FIGURE 8
Do Detailed and Ultrasonic
inspections of the strut
lower spar fitting, diagonal
brace strut end clevis, diag-
onal brace wing attach end
clevis and detailed inspec-
tion of lower link fitting at
engine strut positions 1
through 4 for any crack.
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-CONDITION 1: NO
CRACK FOUND -FIGURE 2, FIGURE 4,
FIGURE 6, FIGURE 8
Repeat Detailed and Ultra-
sonic inspections of the
strut lower spar fitting, diag-
onal brace strut end clevis,
diagonal brace wing attach
end clevis and detailed in-
spection of lower link fitting
at engine strut positions 1
through 4 for any crack.
PART 4: CLOSE ACCESS-
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### Page 33

Group 1-3, 7:
Table 3: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
--CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair instruc-
tions and do the repair.
CONDITION 2: ANY
CRACK FOUND
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 2, FIGURE 4,
FIGURE 6, FIGURE 8
CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at engine strut
positions 1 through 4 for
any crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
33 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 34

Group 4, 6:
Table 4: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 3: OPEN ACCESS-All Airplanes
-FIGURE 4, FIGURE 6ACTION 1: Do Detailed
and Ultrasonic inspections
of the strut lower spar fit-
ting, diagonal brace strut
end clevis, diagonal brace
wing attach end clevis and
detailed inspection of lower
link fitting at inboard en-
gine strut positions 2 and
3 for any crack.
-FIGURE 2, FIGURE 8ACTION 2: Do Detailed
and Ultrasonic inspections
of the strut lower spar fit-
ting, diagonal brace strut
end clevis, diagonal brace
wing attach end clevis and
detailed inspection of lower
link fitting at outboard en-
gine strut positions 1 and
4 for any crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
34 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 35

Group 4, 6:
Table 4: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 3: OPEN ACCESS-CONDITION 1: NO
CRACK FOUND -FIGURE 4, FIGURE 6CONDITION 1 (ACTION
1): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at inboard en-
gine strut positions 2 and
3 for any crack.
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 2, FIGURE 8CONDITION 1 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at outboard en-
gine strut positions 1 and
4 engine locations for any
crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
35 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 36

Group 4, 6:
Table 4: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
--CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair instruc-
tions and do the repair.
CONDITION 2: ANY
CRACK FOUND
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 4, FIGURE 6CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at inboard en-
gine strut positions 2 and
3 for any crack.
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 2, FIGURE 8CONDITION 2 (ACTION
3): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at outboard en-
gine strut positions 1 and
4 for any crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
36 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 37

Group 5:
Table 5: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 3: OPEN ACCESS-All Airplanes
-FIGURE 2, FIGURE 8ACTION 1: Do Detailed
and Ultrasonic inspections
of the strut lower spar fit-
ting, diagonal brace strut
end clevis, diagonal brace
wing attach end clevis and
detailed inspection of lower
link fitting at outboard en-
gine strut positions 1 and
4 for any crack.
-FIGURE 4, FIGURE 6ACTION 2: Do Detailed
and Ultrasonic inspections
of the strut lower spar fit-
ting, diagonal brace strut
end clevis, diagonal brace
wing attach end clevis and
detailed inspection of lower
link fitting at inboard en-
gine strut positions 2 and
3 for any crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
37 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 38

Group 5:
Table 5: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
PART 3: OPEN ACCESS-CONDITION 1: NO
CRACK FOUND -FIGURE 2, FIGURE 8CONDITION 1 (ACTION
1): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at outboard en-
gine strut positions 1 and
4 for any crack.
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 4, FIGURE 6CONDITION 1 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at inboard en-
gine strut positions 2 and
3 engine locations for any
crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
38 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 39

Group 5:
Table 5: Left and Right Wing - Inboard and Outboard Engine Struts - Strut Lower Spar Fitting, Diagonal
Brace Clevis and Lower Link Fitting - Detailed and Ultrasonic Inspections
Refer to the listed proce-
dures in SB 747-57A2363
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
--CONDITION 2 (ACTION
1): Contact The Boeing
Company for repair instruc-
tions and do the repair.
CONDITION 2: ANY
CRACK FOUND
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 2, FIGURE 8CONDITION 2 (ACTION
2): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at outboard en-
gine strut positions 1 and
4 for any crack.
PART 4: CLOSE ACCESS-
PART 3: OPEN ACCESS-
-FIGURE 4, FIGURE 6CONDITION 2 (ACTION
3): Repeat Detailed and
Ultrasonic inspections of
the strut lower spar fitting,
diagonal brace strut end
clevis, diagonal brace wing
attach end clevis and de-
tailed inspection of lower
link fitting at inboard en-
gine strut positions 2 and
3 for any crack.
PART 4: CLOSE ACCESS-
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
39 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--UPPER WING SKINInspect1
(a) Do an Ultrasonic Inspection for any crack in the upper wing skin at the AFT three rows of upper link fitting
fasteners in accordance with 747 NDT Manual Part 4, 57-30-12.
FIGURE 1: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - UPPER WING SKIN - ULTRASONIC
INSPECTION
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
40 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 41

FIGURE 2: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 1 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
41 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 42 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
* DIAGONAL BRACE
DIAGONAL
BRACE STRUT
END CLEVIS
1.2
< 1.0
STRUT LOWER
SPAR FITTING
STRUT POSITION 1 SHOWN
(TYPICAL)
DETAILED AND ULTRASONIC  2894721
INSPECTION
FIGURE 2: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 2 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Copyright © Unpublished
Work - See page 1 for details.  42 of 61

### Page 43 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
DIAGONAL BRACE WING
ATTACH END CLEVIS
1.2
1.0
LOWER LINK
FITTING
DIAGONAL
BRACE
STRUT POSITION 1 SHOWN
DETAILED AND ULTRASONIC  (TYPICAL)
INSPECTION
• DETAILED INSPECTION  2894836
FIGURE 2: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 3 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  Copyright © Unpublished  747-57A2363 RB
Work - See page 1 for details.  43 of 61

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--DIAGONAL BRACE
STRUT END CLEVIS
AND STRUT LOWER
SPAR FITTING
Inspect1
(b)--DIAGONAL BRACE
STRUT END CLEVIS
AND STRUT LOWER
SPAR FITTING
Inspect2
(c)--LOWER LINK FITTINGInspect3
(d)--DIAGONAL BRACE
WING ATTACH END
CLEVIS
Inspect4
(a) Do a detailed inspection of the diagonal brace strut end clevis and strut lower spar fitting for any crack.
(b) Do an ultrasonic inspection of the diagonal brace strut end clevis and strut lower spar fitting for any crack
in accordance with 747 NDT Manual Part 4, 57-40-08.
(c) Do a detailed inspection of the lower link fitting for any crack.
(d) Do a detailed and ultrasonic inspection of the diagonal brace wing attach end clevis for any crack in ac-
cordance with 747 NDT Manual Part 4, 57-40-08.
FIGURE 2: LEFT WING - OUTBOARD ENGINE STRUT POSITION 1 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
44 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 45 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
FRONT SPAR
CENTER LINE
NACELLE RIB  FRONT SPAR
CENTER LINE  CENTER LINE
INBD
UPPER WING SKIN
(TYPICAL)
PTULTRASONIC INSPECTION  2894558
FIGURE 3: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - UPPER WING SKIN - ULTRASONIC
INSPECTION
(SHEET 1 OF 2)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Copyright © Unpublished
Work - See page 1 for details.  45 of 61

### Page 46

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--UPPER WING SKINInspect1
(a) Do an Ultrasonic Inspection for any crack in the upper wing skin at the AFT three rows of upper link fitting
fasteners in accordance with 747 NDT Manual Part 4, 57-30-12.
FIGURE 3: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - UPPER WING SKIN - ULTRASONIC
INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
46 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 47

FIGURE 4: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 1 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
47 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 48 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
* DIAGONAL BRACE
DIAGONAL
BRACE STRUT
1.2  END CLEVIS
→ 1.0
STRUT LOWER
SPAR FITTING
STRUT POSITION 2 SHOWN
(TYPICAL)
DETAILED AND ULTRASONIC  2894708
INSPECTION
FIGURE 4: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 2 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Copyright © Unpublished
Work - See page 1 for details.  48 of 61

### Page 49 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
DIAGONAL BRACE WING
ATTACH END CLEVIS
1.2
I.O  LOWER
LINK FITTING
FIXED FAIRING
DIAGONAL
BRACE
STRUT POSITION 2 SHOWN
(TYPICAL)
DETAILED AND ULTRASONIC
INSPECTION
* DETAILED INSPECTION  2894712
FIGURE 4: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 3 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  Copyright © Unpublished  747-57A2363 RB
Work - See page 1 for details.  49 of 61

### Page 50

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--DIAGONAL BRACE
STRUT END CLEVIS
AND STRUT LOWER
SPAR FITTING
Inspect1
(b)--DIAGONAL BRACE
STRUT END CLEVIS
AND STRUT LOWER
SPAR FITTING
Inspect2
(c)--LOWER LINK FITTINGInspect3
(d)--DIAGONAL BRACE
WING ATTACH END
CLEVIS
Inspect4
(a) Do a detailed inspection of the diagonal brace strut end clevis and strut lower spar fitting for any crack.
(b) Do an ultrasonic inspection of the diagonal brace strut end clevis and strut lower spar fitting for any crack
in accordance with 747 NDT Manual Part 4, 57-40-08.
(c) Do a detailed inspection of the lower link fitting for any crack.
(d) Do a detailed and ultrasonic inspection of the diagonal brace wing attach end clevis for any crack in ac-
cordance with 747 NDT Manual Part 4, 57-40-08.
FIGURE 4: LEFT WING - INBOARD ENGINE STRUT POSITION 2 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
50 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 51 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
FRONT SPAR
CENTER LINE
FRONT SPAR  NACELLE RIB
CENTER LINE  CENTER LINE
INBD
UPPER WING SKIN
(TYPICAL)
•
NULTRASONIC INSPECTION  2895536
FIGURE 5: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - UPPER WING SKIN - ULTRASONIC
INSPECTION
(SHEET 1 OF 2)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Copyright © Unpublished
Work - See page 1 for details.  51 of 61

### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--UPPER WING SKINInspect1
(a) Do an Ultrasonic Inspection for any crack in the upper wing skin at the AFT three rows of upper link fitting
fasteners in accordance with 747 NDT Manual Part 4, 57-30-12.
FIGURE 5: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - UPPER WING SKIN - ULTRASONIC
INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
52 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 53

FIGURE 6: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 1 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
53 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 54 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
DIAGONAL BRACE
DIAGONAL
BRACE STRUT
END CLEVIS  1.2
1.0 %
STRUT LOWER
SPAR FITTING
STRUT POSITION 3 SHOWN
(TYPICAL)
DETAILED AND ULTRASONIC  2895551
INSPECTION
FIGURE 6: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 2 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Copyright © Unpublished
Work - See page 1 for details.  54 of 61

### Page 55 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
DIAGONAL BRACE WING
ATTACH END CLEVIS
1.2
1.0
LOWER LINK
FITTING
FIXED
FAIRING
DIAGONAL
BRACE
STRUT POSITION 3 SHOWN
(TYPICAL)
ZZA INSPECTION ULTRASONIC
A DETAILED INSPECTION  2895943
FIGURE 6: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 3 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  Copyright © Unpublished  747-57A2363 RB
Work - See page 1 for details.  55 of 61

### Page 56

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--DIAGONAL BRACE
STRUT END CLEVIS
AND STRUT LOWER
SPAR FITTING
Inspect1
(b)--DIAGONAL BRACE
STRUT END CLEVIS
AND STRUT LOWER
SPAR FITTING
Inspect2
(c)--LOWER LINK FITTINGInspect3
(d)--DIAGONAL BRACE
WING ATTACH END
CLEVIS
Inspect4
(a) Do a detailed inspection of the diagonal brace strut end clevis and strut lower spar fitting for any crack.
(b) Do an ultrasonic inspection of the diagonal brace strut end clevis and strut lower spar fitting for any crack
in accordance with 747 NDT Manual Part 4, 57-40-08.
(c) Do a detailed inspection of the lower link fitting for any crack.
(d) Do a detailed and ultrasonic inspection of the diagonal brace wing attach end clevis for any crack in ac-
cordance with 747 NDT Manual Part 4, 57-40-08.
FIGURE 6: RIGHT WING - INBOARD ENGINE STRUT POSITION 3 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
56 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--UPPER WING SKINInspect1
(a) Do an Ultrasonic Inspection for any crack in the upper wing skin at the AFT three rows of upper link fitting
fasteners in accordance with 747 NDT Manual Part 4, 57-30-12.
FIGURE 7: RIGHT WING - OUTBOARD ENGINE STRUT POSITION 4 - UPPER WING SKIN - ULTRASONIC
INSPECTION
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
57 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 58

FIGURE 8: RIGHT WING - OUTBOARD ENGINE STRUT POSITION 4 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 1 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 23, 2019
747-57A2363 RB
58 of 61
REQUIREMENTS BULLETIN 747-57A2363
ALERTALERT

### Page 59 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
DIAGONAL BRACE
DIAGONAL BRACE
STRUT END CLEVIS  1.2
1.0s
STRUT LOWER
SPAR FITTING
STRUT POSITION 4 SHOWN
(TYPICAL)
| DETAILED AND ULTRASONIC  2895869
INSPECTION
FIGURE 8: RIGHT WING - OUTBOARD ENGINE STRUT POSITION 4 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 2 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Copyright © Unpublished
Work - See page 1 for details.  59 of 61

### Page 60 (OCR)

REQUIREMENTS BULLETIN 747-57A2363
ALERT  ALERT
DIAGONAL BRACE
WING ATTACH END
CLEVIS
LOWER LINK
FITTING
1.00  1.2
DIAGONAL
STRUT POSITION 4 SHOWN
DETAILED AND ULTRASONIC  (TYPICAL)
INSPECTION
* DETAILED INSPECTION  2895580
FIGURE 8: RIGHT WING - OUTBOARD ENGINE STRUT POSITION 4 - STRUT LOWER SPAR FITTING,
DIAGONAL BRACE STRUT END CLEVIS, DIAGONAL BRACE WING ATTACH END CLEVIS AND LOWER
LINK FITTING - DETAILED AND ULTRASONIC INSPECTION
(SHEET 3 OF 4)
Original Issue: December 23, 2019
Export Controlled ECCN: 9E991  747-57A2363 RB
Work - See page 1 for details.  Copyright © Unpublished  60 of 61

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