# Boeing Alert Requirements Bulletin 737-53A1407 RB: No revision named

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- Title as filed: RB 737-53A1407 R0
- Pages: 63
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## Text

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### Page 1

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1407 RB
Original Issue: December 20, 2022
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Forward Galley Door Cutout - Forward Upper Corner Fuselage
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Unpublished Work.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: December 20, 2022
737-53A1407 RB
1 of 63
3.0

### Page 2

Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
2 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
FIGURE 1: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL GENERAL VISUAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . 34
FIGURE 2: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
FIGURE 3: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN AND
BEAR STRAP - EXTERNAL HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION. 40
FIGURE 4: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER BEAR STRAP -
EXTERNAL LOW FREQUENCY EDDY CURRENT (LFEC) CURRENT INSPECTION . . 43
FIGURE 5: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
FIGURE 6: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITH A QUADRUPLER REPAIR. 49
FIGURE 7: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
FIGURE 8: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITH A QUADRUPLER REPAIR. 55
FIGURE 9: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - INTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION . . . . . . . . . . . . . . . . . . . 58
FIGURE 10: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - INTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION . . . . . . . . . . . . . . . . . . . 61
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
3 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
4 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1407 RB
Original Issue: December 20, 2022
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Forward Galley Door Cutout - Forward Upper Corner Fuselage
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 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
Airplane(s), line number(s) 1-2598, 2600-2721, 2723-2813, 2815-2930, 2932-3068, 3070-3323,
3325-3425, 3427-3521, 3523-3611, 3613-3701, 3703-3791, 3793-3878, 3880-3915, 3917-3968,
3970-4013, 4015-4054, 4056-4098, 4100-4140, 4142-4180, 4182-4218, 4220-4255, 4257-4293,
4295-4330, 4332-4365, 4367-4398, 4400-4444, 4446-4480, 4482-4546, 4548-4608, 4610-4672,
4674-4727, 4729-4767, 4769-4812, 4814-4858, 4860-4897, 4899-4937, 4939-4977, 4979-5019,
5021-5057, 5059-5097, 5099-5137, 5139-5177, 5179-5217, 5219-5261, 5263-5297, 5299-5337,
5339-5367, 5369-5397, 5399-5427, 5429-5457, 5459-5477, 5479-5509, 5511-5541, 5543-5566,
5568-5586, 5588-5601, 5603-5622, 5624-5655, 5657-5667, 5669-5679, 5681-5711, 5713-5727,
5729-5739, 5741-5764, 5766-5787, 5789-5795, 5797-5822, 5824-5850, 5853-5879, 5881-5901,
5904-5935, 5937-5947, 5949-5962, 5964-5991, 5994-6019, 6021-6033, 6035-6047, 6049-6073,
6075, 6077-6103, 6105-6113, 6115-6131, 6133-6153, 6155-6159, 6161-6187, 6190-6215,
6217-6221, 6223-6243, 6245-6249, 6251-6271, 6274-6289, 6291-6299, 6301-6307, 6309-6325,
6327, 6329-6343, 6345-6355, 6357-6359, 6361-6371, 6373-6383, 6386-6395, 6397-6407,
6409-6411, 6413-6419, 6421-6429, 6431-6439, 6442-6447, 6449-6455, 6457-6463, 6465-6467,
6469-6471, 6473-6480, 6482-6489, 6491, 6493-6498, 6500-6507, 6509-6514, 6516-6520,
6522-6527, 6529-6531, 6533-6534, 6536-6541, 6543-6547, 6549-6554, 6556-6559, 6561,
6563-6568, 6570-6574, 6576-6581, 6583-6588, 6590-6593, 6596-6597, 6599-6602, 6604-6606,
6608-6611, 6613-6615, 6617-6620, 6622, 6624, 6626-6629, 6631-6633, 6635-6638, 6640-6642,
6644-6647, 6649-6651, 6653-6656, 6659-6660, 6662-6665, 6667-6671, 6673-6676, 6678-6680,
6682-6685, 6688-6689, 6691-6694, 6696-6698, 6700-6703, 6705-6707, 6709-6712, 6714-6716,
6718-6719, 6721, 6723-6725, 6727-6730, 6732-6734, 6736-6739, 6741-6743, 6745-6748,
6751-6752, 6754-6757, 6759-6761, 6763-6766, 6768-6770, 6772-6775, 6777-6779, 6781-6782,
6786-6788, 6790-6791, 6793, 6795, 6797, 6799-6802, 6804, 6806, 6808-6809, 6811, 6813, 6815,
6817-6818, 6820, 6822-6824, 6826-6827, 6829, 6831-6833, 6835-6836, 6838, 6840, 6842,
6844-6845, 6847, 6849, 6851, 6853-6854, 6856-6858, 6860, 6862-6863, 6865, 6867, 6869-6871,
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
5 of 63

### Page 6

6873-6874, 6878-6880, 6882-6883, 6885, 6887-6889, 6891-6892, 6894, 6896, 6898, 6900-6903,
6905, 6907, 6910, 6912-6914, 6916, 6918-6919, 6921, 6923-6925, 6927-6928, 6930, 6932-6934,
6936-6937, 6939, 6943, 6945-6948, 6950, 6952, 6954-6955, 6957-6959, 6961-6962, 6964,
6966-6967, 6969, 6971-6972, 6977, 6979, 6981-6982, 6984, 6986-6987, 6989, 6992, 6994,
6996-6997, 6999, 7001-7002, 7007, 7009, 7011-7012, 7014, 7016-7017, 7019, 7021-7022, 7024,
7026, 7029, 7031-7032, 7034, 7036-7037, 7039, 7041, 7046-7047, 7049, 7051-7052, 7054,
7056-7057, 7059, 7061, 7063, 7066-7067, 7069, 7071-7072, 7076, 7078, 7081-7082, 7084,
7086-7087, 7089, 7091-7092, 7094, 7097, 7099, 7101-7102, 7104, 7106-7107, 7109, 7112,
7116-7117, 7119, 7121-7122, 7124, 7126-7127, 7129, 7131, 7134, 7136-7137, 7139, 7141-7142,
7146, 7149, 7151-7152, 7154, 7156-7157, 7159, 7161-7162, 7164, 7167, 7169, 7171-7172, 7174,
7176-7177, 7179, 7182, 7187, 7189, 7191, 7194, 7197, 7199, 7202, 7204, 7206, 7209, 7212,
7214, 7217, 7221, 7224, 7227, 7229, 7232, 7234-7235, 7239, 7242, 7244, 7247, 7249, 7251,
7257, 7259, 7262, 7264, 7266, 7269, 7272, 7274, 7277, 7279-7280, 7284, 7287, 7292, 7294,
7297, 7299, 7302, 7304, 7307, 7309, 7312, 7314, 7317, 7319, 7322, 7327, 7329, 7332, 7334,
7337, 7339, 7342, 7344, 7347, 7349, 7352, 7354, 7357, 7362, 7364, 7367, 7369, 7372, 7374,
7377, 7379, 7382, 7387, 7397, 7402, 7407, 7412, 7417, 7422, 7432, 7437, 7442, 7447, 7452,
7457, 7467, 7472, 7477, 7482, 7487, 7492, 7502, 7507, 7512, 7517, 7522, 7527, 7537, 7547,
7552, 7557, 7562, 7572, 7577, 7582, 7587, 7592, 7597, 8592, 9103-99999 in 1 Group(s). Where
the effectivity is presented with hyphens between line numbers, the airplane applicability means
"through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive.
The Variable Numbers and Group Information for the applicable airplanes is given below.
NOTE: The Variable Number table below includes affected airplanes available as of the issue
date of this bulletin. Affected airplane Variable Numbers added to MyBoeingFleet.com
after the issue date of this bulletin will be shown using the Maintenance Performance
Toolbox EFFECTIVITY search function result.
DESCRIPTIONCONFIGURATIONGROUP
737-600/-700/-700C/-800/-900 and -900ER Airplanes.-1
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
1YA001 - YA099
1YA101 - YA199
1YA201 - YA211
1YA221
1YA231 - YA242
1YA251 - YA256
1YA271 - YA272
1YA291
GroupVariable Number
1YA301 - YA302
1YA311 - YA314
1YA321 - YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
GroupVariable Number
1YA501 - YA536
1YA541 - YA552
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
6 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 7

GroupVariable Number
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
1YA671 - YA672
1YA681 - YA691
1YA701 - YA710
1YA721 - YA722
1YA731 - YA734
1YA751 - YA756
1YA801 - YA803
1YA809
1YA811 - YA814
1YA831 - YA835
1YA841 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA978
1YB001 - YB006
1YB101 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB392
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
GroupVariable Number
1YB561 - YB598
1YB601 - YB636
1YB651
1YB656
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
1YB901 - YB903
1YB911
1YB961 - YB975
1YB981
1YB986 - YB998
1YC001 - YC030
1YC051 - YC084
1YC091 - YC095
1YC101 - YC104
1YC111 - YC113
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC179
1YC186 - YC190
1YC201 - YC203
1YC206 - YC207
1YC301 - YC305
1YC321 - YC387
1YC391 - YC394
1YC396
1YC401 - YC417
GroupVariable Number
1YC421 - YC422
1YC426 - YC428
1YC436 - YC439
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
1YC471 - YC499
1YC501 - YC526
1YC571 - YC583
1YC587 - YC589
1YC591 - YC593
1YC601 - YC655
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC752
1YC761 - YC770
1YC781 - YC793
1YC801 - YC892
1YC901 - YC907
1YC921 - YC922
1YC931 - YC932
1YC941 - YC951
1YC971 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD117
1YD121 - YD126
1YD151 - YD159
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
7 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 8

GroupVariable Number
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
1YD391
1YD401 - YD410
1YD412 - YD424
1YD481 - YD485
1YD491 - YD499
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD601 - YD612
1YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YF001 - YF011
1YF021 - YF049
1YF051 - YF080
GroupVariable Number
1YF086 - YF087
1YF106 - YF107
1YF111 - YF114
1YF116 - YF119
1YF121 - YF132
1YF176 - YF178
1YF191 - YF192
1YF201 - YF276
1YF401 - YF402
1YF431 - YF432
1YF436 - YF437
1YF441 - YF442
1YF451 - YF460
1YF501 - YF599
1YF601 - YF685
1YF691 - YF695
1YF701 - YF707
1YF801 - YF805
1YF831 - YF832
1YF836 - YF838
1YF871 - YF872
1YF901 - YF905
1YF921 - YF928
1YF951 - YF954
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG104
1YG111 - YG114
1YG116 - YG149
1YG201 - YG205
1YG211 - YG214
GroupVariable Number
1YG221 - YG224
1YG251 - YG252
1YG501 - YG517
1YG601 - YG602
1YG701
1YG711
1YG721 - YG722
1YH001 - YH012
1YH031 - YH055
1YH071 - YH080
1YH101 - YH132
1YH201 - YH202
1YH206 - YH207
1YH301 - YH307
1YH321 - YH322
1YH501 - YH542
1YH551 - YH594
1YH601 - YH606
1YH611 - YH620
1YH631 - YH632
1YH636 - YH637
1YH641
1YH681 - YH686
1YH701 - YH755
1YH801 - YH899
1YH901 - YH908
1YH911 - YH915
1YH951 - YH952
1YJ001 - YJ013
1YJ021
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ579
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
8 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 9

GroupVariable Number
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
1YJ931 - YJ937
1YJ941 - YJ956
1YJ961
1YJ976 - YJ977
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK133
1YK136 - YK139
1YK141 - YK142
1YK146 - YK148
1YK151 - YK154
1YK161 - YK167
1YK171
1YK176 - YK177
1YK186
1YK191
1YK196
1YK201 - YK202
1YK301 - YK314
1YK321 - YK340
1YK361 - YK378
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
GroupVariable Number
1YK456 - YK467
1YK471 - YK473
1YK476
1YK478
1YK480 - YK487
1YK491 - YK493
1YK495 - YK499
1YK511 - YK516
1YK521 - YK530
1YK551 - YK571
1YK576 - YK577
1YK580 - YK585
1YK601 - YK602
1YK606 - YK607
1YK611 - YK616
1YK621 - YK634
1YK641 - YK644
1YK651 - YK665
1YK671 - YK672
1YK676 - YK677
1YK681 - YK686
1YK691
1YK695 - YK699
1YK701 - YK713
1YK716 - YK719
1YK721 - YK741
1YK751 - YK770
1YK776 - YK778
1YK781 - YK785
1YK791 - YK792
1YK796 - YK797
1YK801 - YK899
1YK901 - YK912
GroupVariable Number
1YK918 - YK919
1YK921 - YK929
1YK941 - YK999
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL137
1YL201 - YL237
1YL241 - YL242
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL314
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL551
1YL561 - YL579
1YL591 - YL598
1YL601 - YL606
1YL611 - YL612
1YL616 - YL617
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### Page 10

GroupVariable Number
1YL621
1YL626
1YL631 - YL634
1YL636 - YL637
1YL661 - YL664
1YL676 - YL691
1YL696 - YL697
1YL701 - YL707
1YL731
1YL751 - YL752
1YL756 - YL757
1YL761 - YL780
1YL796 - YL797
1YL801 - YL815
1YL901 - YL910
1YL921 - YL940
1YL951 - YL968
1YM101 - YM103
1YM201 - YM244
1YM251 - YM299
1YM301 - YM399
1YM401 - YM415
1YM471
1YM481 - YM484
1YM501 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
1YM631 - YM634
1YM641 - YM652
GroupVariable Number
1YM671 - YM674
1YM691 - YM699
1YM701 - YM710
1YM761 - YM765
1YM771 - YM779
1YN001 - YN016
1YN021 - YN024
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN126
1YN201 - YN202
1YN211 - YN219
1YN231 - YN236
1YN261
1YN501
1YN531 - YN534
1YN551 - YN566
1YN581 - YN585
1YN591 - YN593
1YN601 - YN606
1YN651 - YN653
1YN661 - YN663
1YN666 - YN667
1YN671 - YN674
1YN701 - YN702
1YN741 - YN746
1YN756 - YN758
1YQ001 - YQ003
1YQ011 - YQ021
1YQ026 - YQ029
GroupVariable Number
1YQ036 - YQ045
1YQ201 - YQ207
1YQ231
1YQ241 - YQ251
1YQ281 - YQ284
1YQ291 - YQ296
1YQ301 - YQ302
1YQ321 - YQ324
1YQ331 - YQ334
1YQ346 - YQ347
1YQ351 - YQ367
1YQ371
1YQ401 - YQ403
1YQ451 - YQ454
1YQ456
1YQ461
1YQ471
1YQ501 - YQ520
1YQ601 - YQ606
1YQ610 - YQ614
1YR001 - YR098
1YR101 - YR105
1YR111 - YR124
1YR126 - YR144
1YR166 - YR182
1YR186 - YR198
1YR201 - YR215
1YR231 - YR294
1YR296 - YR297
1YR301 - YR334
1YR338 - YR341
1YR361 - YR366
1YR371 - YR373
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GroupVariable Number
1YR376 - YR377
1YR381 - YR382
1YR386 - YR388
1YR391
1YR396 - YR399
1YR401 - YR405
1YR411 - YR413
1YR416 - YR418
1YR421 - YR424
1YR426 - YR455
1YR457 - YR499
1YR501 - YR506
1YR511 - YR520
1YR526 - YR544
1YR546 - YR551
1YR556 - YR562
1YR571 - YR582
1YR591 - YR592
1YR601 - YR605
1YR616 - YR658
1YR661 - YR663
1YR671 - YR673
1YR676 - YR678
1YR681 - YR682
1YR701 - YR769
1YR771 - YR799
1YR801 - YR827
1YR831 - YR838
1YR841 - YR899
1YR901 - YR903
1YR931 - YR934
1YR938 - YR944
1YR951 - YR998
GroupVariable Number
1YS001 - YS002
1YS006 - YS009
1YS031 - YS032
1YS051 - YS073
1YS101 - YS120
1YS126 - YS142
1YS146 - YS160
1YS166 - YS194
1YS196 - YS197
1YS201 - YS209
1YS221 - YS225
1YS231 - YS236
1YS271 - YS288
1YS295 - YS296
1YS301 - YS348
1YS351 - YS378
1YS381 - YS386
1YS393 - YS395
1YS401
1YS451
1YS456 - YS457
1YS462 - YS465
1YS467
1YS501 - YS502
1YS506
1YS511 - YS518
1YS531
1YS536 - YS538
1YS541 - YS542
1YS546
1YS551 - YS556
1YS561 - YS578
1YS581 - YS595
GroupVariable Number
1YS601 - YS690
1YS701 - YS716
1YS721 - YS762
1YS771 - YS780
1YS806 - YS810
1YS816 - YS818
1YS823 - YS825
1YS851 - YS863
1YS876
1YS881 - YS884
1YS891 - YS894
1YS896 - YS897
1YS901 - YS909
1YS911 - YS957
1YS961 - YS974
1YS976 - YS977
1YS981 - YS987
1YS991 - YS998
1YT001 - YT004
1YT006
1YT026 - YT027
1YT031 - YT032
1YT036 - YT038
1YT061 - YT068
1YT101 - YT138
1YT176 - YT185
1YT191
1YT196 - YT199
1YT201
1YT206 - YT207
1YT211 - YT213
1YT251 - YT299
1YT301 - YT307
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GroupVariable Number
1YT311 - YT312
1YT321 - YT355
1YT371 - YT372
1YT381
1YT391 - YT396
1YT401 - YT403
1YT411 - YT417
1YT427
1YT461 - YT477
1YT491 - YT492
1YT501 - YT521
1YT551 - YT552
1YT556 - YT563
1YT565
1YT571 - YT578
1YT601 - YT606
1YT701 - YT708
1YT723 - YT726
1YT761 - YT781
1YT791 - YT794
1YT796 - YT797
1YT801 - YT804
1YT811 - YT813
1YT826 - YT827
1YT831 - YT832
1YT841 - YT852
1YT856 - YT863
1YT885 - YT887
1YT891 - YT895
1YT901 - YT998
1YU001 - YU060
1YU201 - YU218
1YU301 - YU329
GroupVariable Number
1YU901 - YU931
1YV001 - YV012
1YV021 - YV023
1YV030 - YV034
1YV037 - YV042
1YV045 - YV047
1YV051 - YV059
1YV081
1YV083 - YV084
1YV097 - YV099
1YV101 - YV154
1YV201 - YV203
1YV251 - YV252
1YV256 - YV257
1YV301 - YV312
1YV351 - YV368
1YV381 - YV388
1YV391 - YV394
1YV401
1YV411 - YV413
1YV431 - YV433
1YV441 - YV454
1YV461 - YV464
1YV467 - YV470
1YV501 - YV512
1YV521
1YV571 - YV586
1YV596
1YV601 - YV605
1YV651 - YV674
1YV676
1YV695 - YV696
1YV701 - YV702
GroupVariable Number
1YV711
1YV722 - YV731
1YV741 - YV794
1YV801 - YV820
1YV831 - YV848
1YV881 - YV883
1YV901 - YV915
1YV923 - YV926
1YV971 - YV983
1YW001
1YW011 - YW099
1YW101 - YW164
1YW201 - YW212
1YW226 - YW240
1YW245 - YW261
1YW263
1YW267 - YW281
1YW283 - YW285
1YW292 - YW299
1YW351
1YW356 - YW358
1YW361 - YW366
1YW371 - YW399
1YW401 - YW430
1YW441 - YW445
1YW451 - YW452
1YW471 - YW472
1YW491 - YW498
1YW531 - YW536
1YW541 - YW545
1YW551 - YW580
1YW585 - YW591
1YW595 - YW596
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### Page 13

GroupVariable Number
1YW601
1YW610 - YW613
1YW616 - YW623
1YW666
1YW696 - YW699
1YW701 - YW715
GroupVariable Number
1YW726 - YW731
1YW766 - YW775
1YW801 - YW803
1YW811 - YW813
1YW821
1YW831
GroupVariable Number
1YW881
1YW891 - YW893
1YW906 - YW910
1YW916 - YW918
1YW921 - YW925
1YW971 - YW976
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 737-53A1407 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 737-53A1407 RB mandatory.
For airplanes which have incorporated Boeing Business Jet (BBJ) Lower Cabin Altitude Supplemental Type
Certificate (STC) ST01697SE (6500 feet maximum cabin altitude in lieu of 8000 feet) as referenced in
Boeing SB 737-21-1149, the flight cycle related compliance times are different from those specified in this
service bulletin. All initial compliance times (thresholds) specified in flight cycles must be reduced to half of
those specified in Requirements Bulletin 737-53A1407 RB. All repeat interval compliance times specified
in flight cycles must be reduced to one-quarter of those specified in Requirements Bulletin 737-53A1407
RB.
Accomplish the required actions, based on the applicable conditions in Table 1, Table 2, Table 3 and Table
4 in accordance with Work 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.
Table 1: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin and Bear Strap Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000 flight
cycles after the origi-
nal issue date of Re-
quirements Bulletin
737-53A1407 RB.
Before 30,000 total
flight cycles.
Do an external General
Visual Inspection (GVI)
of the fuselage skin at
the forward galley door
cutout forward upper
corner for any repair.
All Airplanes.
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### Page 14

Table 1: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin and Bear Strap Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended Compliance Time
(Whichever Occurs Later)
ActionCondition
-At the time specified in Table 3.Do the actions specified
in Table 3.
CONDITION 1:
ANY REPAIR
FOUND.
-Within 3,000 flight
cycles after the origi-
nal issue date of Re-
quirements Bulletin
737-53A1407 RB.
Before 30,000 total
flight cycles.
OPTION 1: Do an exter-
nal surface detailed in-
spection of the fuselage
skin at the forward galley
door cutout forward up-
per corner for any crack.
CONDITION 2: NO
REPAIR FOUND.
-Within 3,000 flight
cycles after the origi-
nal issue date of Re-
quirements Bulletin
737-53A1407 RB.
Before 30,000 total
flight cycles.
OPTION 2 (ACTION 1):
Do an external surface
High Frequency Eddy
Current (HFEC) inspec-
tion of the fuselage skin
at the specified fastener
locations, and the fuse-
lage skin and bear strap
along the edge of door
corner radius for any
crack.
OPTION 2 (ACTION 2):
Do an external subsur-
face Low Frequency Ed-
dy Current (LFEC) inspec-
tion of the bear strap at
the specified fastener lo-
cations at the forward
galley door cutout for-
ward upper corner for
any crack.
-Before further flight.Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 2.1:
ANY CRACK
FOUND.
-At the time specified in Table 2.Do the actions specified
in Table 2.
CONDITION 2.2:
NO CRACK
FOUND.
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### Page 15

Table 2: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Repeat In-
spection
Repeat Interval (Not
to Exceed)
Boeing Recommended Com-
pliance Time
ActionCondition
-Within 3,000 flight cycles after
the OPTION 1 inspection.
Do an external General
Visual Inspection (GVI) of
the fuselage skin at the
forward galley door cutout
forward upper corner for
any repair.
AIRPLANES WITH NO
CRACK FOUND AS A
RESULT OF OPTION 1
INSPECTION.
-Within 12,000 flight cycles after
the OPTION 2 inspection.
Do an external General
Visual Inspection (GVI) of
the fuselage skin at the
forward galley door cutout
forward upper corner for
any repair.
AIRPLANES WITH NO
CRACK FOUND AS A
RESULT OF OPTION 2
INSPECTION.
-At the time specified in Table 4.Do the actions specified in
Table 4.
CONDITION 3: ANY RE-
PAIR FOUND.
-Within 3,000 flight cycles if the
last inspection was OPTION 1
or OPTION 2.
OPTION 1: Do an external
surface detailed inspection
of the fuselage skin at the
forward galley door cutout
forward upper corner for
any crack.
CONDITION 4: NO RE-
PAIR FOUND.
-Within 3,000 flight cycles if the
last inspection was OPTION 1.
OPTION 2 (ACTION 1):
Do an external surface
HFEC inspection of the
fuselage skin at the speci-
fied fastener locations, and
the fuselage skin and bear
strap along the edge of
door corner radius for any
crack.
OR
Within 12,000 flight cycles if the
last inspection was OPTION 2.
OPTION 2 (ACTION 2):
Do an external subsurface
LFEC inspection of the
bear strap at the specified
fastener locations at the
forward galley door cutout
forward upper corner for
any crack.
-Before further flight.Contact The Boeing Com-
pany for repair instructions
and do the repair.
CONDITION 4.1: ANY
CRACK FOUND.
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### Page 16

Table 2: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Repeat In-
spection
Repeat Interval (Not
to Exceed)
Boeing Recommended Com-
pliance Time
ActionCondition
3,000 flight cycles.-Repeat the external GVI
at the forward upper cor-
ner of the forward galley
door cutout fuselage skin,
for any repair and applica-
ble on-condition actions.
CONDITION 4.2: NO
CRACK FOUND AS A
RESULT OF OPTION 1
INSPECTION.
12,000 flight cycles.-Repeat the external GVI
at the forward upper cor-
ner of the forward galley
door cutout fuselage skin,
for any repair and applica-
ble on-condition actions.
CONDITION 4.3: NO
CRACK FOUND AS A
RESULT OF OPTION 2
INSPECTION.
Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Inter-
val (Not to Ex-
ceed)
Boeing Recommended Compliance
Time (Whichever Occurs Later)
ActionCondition
-Within 3,000 flight
cycles after the orig-
inal issue date of
Requirements Bul-
letin 737-53A1407
RB.
Before 30,000 total
flight cycles.
Contact The Boeing Compa-
ny for alternative inspection,
do the inspection and appli-
cable on-condition correc-
tive action. (a)
AIRPLANES WITH
REPAIR FOUND AS
A RESULT OF THE
INITIAL EXTERNAL
GVI OF THE FUSE-
LAGE SKIN AND
THE REPAIR
FOUND WAS NOT
DONE IN ACCOR-
DANCE WITH
737NG SRM 53-10-
01 REPAIR 6 DAT-
ED MARCH 10,
2020.
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### Page 17

Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Inter-
val (Not to Ex-
ceed)
Boeing Recommended Compliance
Time (Whichever Occurs Later)
ActionCondition
-Within 24,000 flight cycles after SRM 53-
10-01 Repair 6 dated March 10, 2020 was
done.
ACTION 1: Do an external
surface HFEC inspection of
the exposed repair part at
the specified fastener loca-
tions, and the fuselage skin,
bear strap, and repair parts
along the edge of door cor-
ner radius for any crack.
(b)(c)
AIRPLANES WITH
REPAIR FOUND AS
A RESULT OF THE
INITIAL EXTERNAL
GVI OF THE FUSE-
LAGE SKIN AND
THE REPAIR
FOUND WAS DONE
IN ACCORDANCE
WITH 737NG SRM
53-10-01 REPAIR 6
DATED MARCH 10,
2020 WITH OR
WITHOUT A
QUADRUPLER RE-
PAIR.
Within 24,000 flight cycles after SRM 53-
10-01 Repair 6 dated March 10, 2020 was
done.
ACTION 2: Do an external
subsurface LFEC inspection
at the specified fastener lo-
cation for the skin and at
other specified fastener lo-
cations for the repair parts
at the forward galley door
cutout forward upper corner
for any crack. (b)(c)
Within 24,000 flight cycles after SRM 53-
10-01 Repair 6 dated March 10, 2020 was
done.
ACTION 3: Do an internal
surface HFEC inspection of
the bear strap at the speci-
fied location at the forward
galley door cutout forward
upper corner for any crack.
(b)
Within 24,000 flight cycles after SRM 53-
10-01 Repair 6 dated March 10, 2020 was
done.
ACTION 4: Do an internal
subsurface LFEC inspection
of the fuselage skin and
bear strap at specified fas-
tener locations and do an
internal subsurface LFEC
inspection of the fuselage
skin at the specified location
at the forward galley door
cutout forward upper corner
for any crack. (b)
-Before further flight.Contact The Boeing Compa-
ny for repair instructions
and do the repair.
CONDITION 5: ANY
CRACK FOUND.
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### Page 18

Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Inter-
val (Not to Ex-
ceed)
Boeing Recommended Compliance
Time (Whichever Occurs Later)
ActionCondition
24,000 flight
cycles.
--CONDITION 6 (ACTION 1):
Repeat the external surface
HFEC inspection of the ex-
posed repair part at the
specified fastener locations,
and the fuselage skin, bear
strap, and repair parts along
the edge of door corner ra-
dius for any crack. (b)(c)
CONDITION 6: NO
CRACK FOUND.
CONDITION 6 (ACTION 2):
Repeat the external subsur-
face LFEC inspection at the
specified fastener location
for the skin and at other
specified fastener locations
for the repair parts at the
forward galley door cutout
forward upper corner for
any crack. (b)(c)
CONDITION 6 (ACTION 3):
Repeat the internal surface
HFEC inspection of the
bear strap at the specified
location at the forward gal-
ley door cutout forward up-
per corner for any crack. (b)
CONDITION 6 (ACTION 4):
Repeat the internal subsur-
face LFEC inspection of the
fuselage skin and bear
strap at specified fastener
locations and repeat the in-
ternal subsurface LFEC in-
spection of the fuselage
skin at the specified location
at the forward galley door
cutout forward upper corner
for any crack. (b)
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### Page 19

Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Inter-
val (Not to Ex-
ceed)
Boeing Recommended Compliance
Time (Whichever Occurs Later)
ActionCondition
(a) It is not required to contact The Boeing Company for alternative inspection, where a repair covers the af-
fected inspection area if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack conditions identified in Requirements Bulletin 737-
53A1407 RB and installed after the Original Issue date of Requirements Bulletin 737-53A1407
RB, and
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) These inspections do not replace the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020, but are in addition to the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020.
(c) The text "repair part" and "repair parts" refers to doublers, triplers, and quadruplers, as applicable, as
specified in the figures for each action.
Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Interval (Not to
Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 3,000 flight cycles
after the last OPTION 1
inspection.
Contact The Boeing Compa-
ny for alternative inspection,
do the inspection and appli-
cable on-condition correc-
tive action. (a)
REPAIR FOUND NOT
DONE IN ACCORDANCE
WITH 737NG SRM 53-10-
01 REPAIR 6 DATED
MARCH 10, 2020 AND
THE LAST INSPECTION
WAS AN OPTION 1 IN-
SPECTION.
-Within 12,000 flight cycles
after the last OPTION 2
inspection.
Contact The Boeing Compa-
ny for alternative inspection,
do the inspection and appli-
cable on-condition correc-
tive action. (a)
REPAIR FOUND NOT
DONE IN ACCORDANCE
WITH 737NG SRM 53-10-
01 REPAIR 6 DATED
MARCH 10, 2020 AND
THE LAST INSPECTION
WAS AN OPTION 2 IN-
SPECTION.
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### Page 20

Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Interval (Not to
Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 24,000 flight cycles
after SRM 53-10-01 Repair
6 dated March 10, 2020
was done.
ACTION 1: Do an external
surface HFEC inspection of
the exposed repair part at
the specified fastener loca-
tions, and the fuselage skin,
bear strap, and repair parts
along the edge of door cor-
ner radius for any crack.
(b)(c)
REPAIR FOUND DONE IN
ACCORDANCE WITH
737NG SRM 53-10-01
REPAIR 6 DATED
MARCH 10, 2020 WITH
OR WITHOUT A
QUADRUPLER REPAIR.
ACTION 2: Do an external
subsurface LFEC inspection
at the specified fastener lo-
cation for the skin and at
other specified fastener lo-
cations for the repair parts
at the forward galley door
cutout forward upper corner
for any crack. (b)(c)
ACTION 3: Do an internal
surface HFEC inspection of
the bear strap at the speci-
fied location at the forward
galley door cutout forward
upper corner for any crack.
(b)
ACTION 4: Do an internal
subsurface LFEC inspection
of the fuselage skin and
bear strap at specified fas-
tener locations and do an
internal subsurface LFEC
inspection of the fuselage
skin at the specified location
at the forward galley door
cutout forward upper corner
for any crack. (b)
-Before further flight.Contact The Boeing Compa-
ny for repair instructions
and do the repair.
CONDITION 7: ANY
CRACK FOUND.
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Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Interval (Not to
Exceed)
Boeing Recommended
Compliance Time
ActionCondition
24,000 flight cycles.-CONDITION 8 (ACTION 1):CONDITION 8: NO
CRACK FOUND. Repeat the external surface
HFEC inspection of the ex-
posed repair part at the
specified fastener locations,
and the fuselage skin, bear
strap, and repair parts along
the edge of door corner ra-
dius for any crack. (b)(c)
CONDITION 8 (ACTION 2):
Repeat the external subsur-
face LFEC inspection at the
specified fastener location
for the skin and at other
specified fastener locations
for the repair parts at the
forward galley door cutout
forward upper corner for
any crack. (b)(c)
CONDITION 8 (ACTION 3):
Repeat the internal surface
HFEC inspection of the
bear strap at the specified
location at the forward gal-
ley door cutout forward up-
per corner for any crack. (b)
CONDITION 8 (ACTION 4):
Repeat the internal subsur-
face LFEC inspection of the
fuselage skin and bear
strap at specified fastener
locations and repeat the in-
ternal subsurface LFEC in-
spection of the fuselage
skin at the specified location
at the forward galley door
cutout forward upper corner
for any crack. (b)
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Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Repeat Interval (Not to
Exceed)
Boeing Recommended
Compliance Time
ActionCondition
(a) It is not required to contact The Boeing Company for alternative inspection, where a repair covers the af-
fected inspection area if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack conditions identified in Requirements Bulletin 737-
53A1407 RB and installed after the Original Issue date of Requirements Bulletin 737-53A1407
RB, and
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) These inspections do not replace the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020, but are in addition to the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020.
(c) The text "repair part" and "repair parts" refers to doublers, triplers, and quadruplers, as applicable, as
specified in the figures for each action.
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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5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF
METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE
BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES
CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION
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 737-SL-51-042, 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 737 Structural Repair Manual,
Chapter 51.
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— Values for airframe maintenance tasks are included in Chapter 20 of 737
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 737
Aircraft Maintenance Manual (AMM).
— 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. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
10. 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.
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. 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:
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Table 1: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-FIGURE 1Do an external General Visu-
al Inspection (GVI) of the
fuselage skin at the forward
galley door cutout forward
upper corner for any repair.
All Airplanes.
--Do the actions specified in
Table 3.
CONDITION 1: ANY RE-
PAIR FOUND.
-FIGURE 2OPTION 1: Do an external
surface detailed inspection
of the fuselage skin at the
forward galley door cutout
forward upper corner for any
crack.
CONDITION 2: NO RE-
PAIR FOUND.
-FIGURE 3OPTION 2 (ACTION 1):
Do an external surface High
Frequency Eddy Current
(HFEC) inspection of the
fuselage skin at the speci-
fied fastener locations, and
the fuselage skin and bear
strap along the edge of door
corner radius for any crack.
-FIGURE 4OPTION 2 (ACTION 2):
Do an external subsurface
Low Frequency Eddy Cur-
rent (LFEC) inspection of the
bear strap at the specified
fastener locations at the for-
ward galley door cutout for-
ward upper corner for any
crack.
--Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 2.1: ANY
CRACK FOUND.
--Do the actions specified in
Table 2.
CONDITION 2.2: NO
CRACK FOUND.
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Table 2: Forward Galley Door Cutout - Forward Upper Corner Bear Fuselage Skin And Bear Strap Repeat
Inspection
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-FIGURE 1Do an external General Visu-
al Inspection (GVI) of the
fuselage skin at the forward
galley door cutout forward
upper corner for any repair.
AIRPLANES WITH NO
CRACK FOUND AS A
RESULT OF OPTION 1
INSPECTION.
-FIGURE 1Do an external General Visu-
al Inspection (GVI) of the
fuselage skin at the forward
galley door cutout forward
upper corner for any repair.
AIRPLANES WITH NO
CRACK FOUND AS A
RESULT OF OPTION 2
INSPECTION.
--Do the actions specified in
Table 4.
CONDITION 3: ANY RE-
PAIR FOUND.
-FIGURE 2OPTION 1: Do an external
surface detailed inspection
of the fuselage skin at the
forward galley door cutout
forward upper corner for any
crack.
CONDITION 4: NO RE-
PAIR FOUND.
-FIGURE 3OPTION 2 (ACTION 1): Do
an external surface HFEC
inspection of the fuselage
skin at the specified fastener
locations, and the fuselage
skin and bear strap along
the edge of door corner ra-
dius for any crack.
-FIGURE 4OPTION 2 (ACTION 2): Do
an external subsurface
LFEC inspection of the bear
strap at the specified fasten-
er locations at the forward
galley door cutout forward
upper corner for any crack.
--Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 4.1: ANY
CRACK FOUND.
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Table 2: Forward Galley Door Cutout - Forward Upper Corner Bear Fuselage Skin And Bear Strap Repeat
Inspection
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-FIGURE 1Repeat the external GVI at
the forward upper corner of
the forward galley door
cutout fuselage skin, for any
repair and applicable on-
condition actions.
CONDITION 4.2: NO
CRACK FOUND AS A
RESULT OF OPTION 1
INSPECTION.
-FIGURE 1Repeat the external GVI at
the forward upper corner of
the forward galley door
cutout fuselage skin, for any
repair and applicable on-
condition actions.
CONDITION 4.3: NO
CRACK FOUND AS A
RESULT OF OPTION 2
INSPECTION.
Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--Contact The Boeing Compa-
ny for alternative inspection,
do the inspection and appli-
cable on-condition corrective
action. (a)
AIRPLANES WITH RE-
PAIR FOUND AS A RE-
SULT OF THE INITIAL
EXTERNAL GVI OF THE
FUSELAGE SKIN AND
THE REPAIR FOUND
WAS NOT DONE IN AC-
CORDANCE WITH 737NG
SRM 53-10-01 REPAIR 6
DATED MARCH 10, 2020.
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Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-Airplanes without a
quadrupler repair, do
FIGURE 5.
ACTION 1: Do an external
surface HFEC inspection of
the exposed repair part at
the specified fastener loca-
tions, and the fuselage skin,
bear strap, and repair parts
along the edge of door cor-
ner radius for any crack.
(b)(c)
AIRPLANES WITH RE-
PAIR FOUND AS A RE-
SULT OF THE INITIAL
EXTERNAL GVI OF THE
FUSELAGE SKIN AND
THE REPAIR FOUND
WAS DONE IN ACCOR-
DANCE WITH 737NG
SRM 53-10-01 REPAIR 6
DATED MARCH 10, 2020
WITH OR WITHOUT A
QUADRUPLER REPAIR.
Airplanes with a quadru-
pler repair, do FIGURE
6.
-Airplanes without a
quadrupler repair, do
FIGURE 7.
ACTION 2: Do an external
subsurface LFEC inspection
at the specified fastener lo-
cation for the skin and at
other specified fastener loca-
tions for the repair parts at
the forward galley door
cutout forward upper corner
for any crack. (b)(c)
Airplanes with a quadru-
pler repair, do FIGURE
8.
DO PART 1: GET AC-
CESS.
-ACTION 3: Do an internal
surface HFEC inspection of
the bear strap at the speci-
fied location at the forward
galley door cutout forward
upper corner for any crack.
(b)
-FIGURE 9
-FIGURE 10ACTION 4: Do an internal
subsurface LFEC inspection
of the fuselage skin and
bear strap at specified fas-
tener locations and do an
internal subsurface LFEC
inspection of the fuselage
skin at the specified location
at the forward galley door
cutout forward upper corner
for any crack. (b)
DO PART 2: CLOSE AC-
CESS.
-
--Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 5: ANY
CRACK FOUND.
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Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-Airplanes without a
quadrupler repair, do
FIGURE 5.
CONDITION 6 (ACTION 1):
Repeat the external surface
HFEC inspection of the ex-
posed repair part at the
specified fastener locations,
and the fuselage skin, bear
strap, and repair parts along
the edge of door corner ra-
dius for any crack. (b)(c)
CONDITION 6: NO
CRACK FOUND.
Airplanes with a quadru-
pler repair, do FIGURE
6.
-Airplanes without a
quadrupler repair, do
FIGURE 7.
CONDITION 6 (ACTION 2):
Repeat the external subsur-
face LFEC inspection at the
specified fastener location
for the skin and at other
specified fastener locations
for the repair parts at the
forward galley door cutout
forward upper corner for any
crack. (b)(c)
Airplanes with a quadru-
pler repair, do FIGURE
8.
DO PART 1: GET AC-
CESS.
-CONDITION 6 (ACTION 3):
Repeat the internal surface
HFEC inspection of the bear
strap at the specified loca-
tion at the forward galley
door cutout forward upper
corner for any crack. (b)
-FIGURE 9
-FIGURE 10CONDITION 6 (ACTION 4):
Repeat the internal subsur-
face LFEC inspection of the
fuselage skin and bear strap
at specified fastener loca-
tions and repeat the internal
subsurface LFEC inspection
of the fuselage skin at the
specified location at the for-
ward galley door cutout for-
ward upper corner for any
crack. (b)
DO PART 2: CLOSE AC-
CESS.
-
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Table 3: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
(a) It is not required to contact The Boeing Company for alternative inspection, where a repair covers the af-
fected inspection area if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack conditions identified in Requirements Bulletin 737-
53A1407 RB and installed after the Original Issue date of Requirements Bulletin 737-53A1407
RB, and
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) These inspections do not replace the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020, but are in addition to the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020.
(c) The text "repair part" and "repair parts" refers to doublers, triplers, and quadruplers, as applicable, as
specified in the figures for each action.
Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--Contact The Boeing Compa-
ny for alternative inspection,
do the inspection and appli-
cable on-condition corrective
action. (a)
REPAIR FOUND NOT
DONE IN ACCORDANCE
WITH 737NG SRM 53-10-
01 REPAIR 6 DATED
MARCH 10, 2020 AND
THE LAST INSPECTION
WAS AN OPTION 1 IN-
SPECTION.
--Contact The Boeing Compa-
ny for alternative inspection,
do the inspection and appli-
cable on-condition corrective
action. (a)
REPAIR FOUND NOT
DONE IN ACCORDANCE
WITH 737NG SRM 53-10-
01 REPAIR 6 DATED
MARCH 10, 2020 AND
THE LAST INSPECTION
WAS AN OPTION 2 IN-
SPECTION.
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Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-Airplanes without a
quadrupler repair, do
FIGURE 5.
ACTION 1: Do an external
surface HFEC inspection of
the exposed repair part at
the specified fastener loca-
tions, and the fuselage skin,
bear strap, and repair parts
along the edge of door cor-
ner radius for any crack.
(b)(c)
REPAIR FOUND DONE IN
ACCORDANCE WITH
737NG SRM 53-10-01
REPAIR 6 DATED
MARCH 10, 2020 WITH
OR WITHOUT A
QUADRUPLER REPAIR.
Airplanes with a quadru-
pler repair, do FIGURE
6.
-Airplanes without a
quadrupler repair, do
FIGURE 7.
ACTION 2: Do an external
subsurface LFEC inspection
at the specified fastener loca-
tion for the skin and at other
specified fastener locations
for the repair parts at the
forward galley door cutout
forward upper corner for any
crack. (b)(c)
Airplanes with a quadru-
pler repair, do FIGURE
8.
DO PART 1: GET AC-
CESS.
-ACTION 3: Do an internal
surface HFEC inspection of
the bear strap at the speci-
fied location at the forward
galley door cutout forward
upper corner for any crack.
(b)
-FIGURE 9
-FIGURE 10ACTION 4: Do an internal
subsurface LFEC inspection
of the fuselage skin and bear
strap at specified fastener
locations and do an internal
subsurface LFEC inspection
of the fuselage skin at the
specified location at the for-
ward galley door cutout for-
ward upper corner for any
crack. (b)
DO PART 2: CLOSE AC-
CESS.
-
--Contact The Boeing Compa-
ny for repair instructions and
do the repair.
CONDITION 7: ANY
CRACK FOUND.
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Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
-Airplanes without a
quadrupler repair, do
FIGURE 5.
CONDITION 8 (ACTION 1):
Repeat the external surface
HFEC inspection of the ex-
posed repair part at the
specified fastener locations,
and the fuselage skin, bear
strap, and repair parts along
the edge of door corner ra-
dius for any crack. (b)(c)
CONDITION 8: NO
CRACK FOUND.
Airplanes with a quadru-
pler repair, do FIGURE
6.
-Airplanes without a
quadrupler repair, do
FIGURE 7.
CONDITION 8 (ACTION 2):
Repeat the external subsur-
face LFEC inspection at the
specified fastener location
for the skin and at other
specified fastener locations
for the repair parts at the
forward galley door cutout
forward upper corner for any
crack. (b)(c)
Airplanes with a quadru-
pler repair, do FIGURE
8.
DO PART 1: GET AC-
CESS.
-CONDITION 8 (ACTION 3):
Repeat the internal surface
HFEC inspection of the bear
strap at the specified loca-
tion at the forward galley
door cutout forward upper
corner for any crack. (b)
-FIGURE 9
-FIGURE 10CONDITION 8 (ACTION 4):
Repeat the internal subsur-
face LFEC inspection of the
fuselage skin and bear strap
at specified fastener loca-
tions and repeat the internal
subsurface LFEC inspection
of the fuselage skin at the
specified location at the for-
ward galley door cutout for-
ward upper corner for any
crack. (b)
DO PART 2: CLOSE AC-
CESS.
-
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### Page 33

Table 4: Forward Galley Door Cutout - Forward Upper Corner Fuselage Skin And Bear Strap Inspection
With An Existing Repair
Refer to the listed proce-
dures in SB 737-53A1407
original issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
(a) It is not required to contact The Boeing Company for alternative inspection, where a repair covers the af-
fected inspection area if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack conditions identified in Requirements Bulletin 737-
53A1407 RB and installed after the Original Issue date of Requirements Bulletin 737-53A1407
RB, and
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
(b) These inspections do not replace the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020, but are in addition to the inspections required by 737NG SRM 53-10-01 Repair 6 dated March
10, 2020.
(c) The text "repair part" and "repair parts" refers to doublers, triplers, and quadruplers, as applicable, as
specified in the figures for each action.
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### Page 34 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3003930
FIGURE 1: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL GENERAL VISUAL INSPECTION
(SHEET 1 OF 3)
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### Page 35 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FUSELAGE
STA  312  SKIN  291.5  STA  BEAR STRAP
¿ *
- S-6R
UPPER  - S-8R
REVEAL  STUB
FRAME
COVER  I S-9R
GENERAL VISUAL INSPECTION  3003931
FIGURE 1: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL GENERAL VISUAL INSPECTION
(SHEET 2 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  35 of 63

### Page 36

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)-141A3312-()FUSELAGE SKINInspect1
(a) Do an external general visual inspection of the fuselage skin at the forward galley door cutout forward
upper corner for any repair.
FIGURE 1: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL GENERAL VISUAL INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
36 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 37 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3003932
FIGURE 2: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL DETAILED INSPECTION
(SHEET 1 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  37 of 63

### Page 38 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FUSELAGE
STA  SKIN  STA
312  291.5  BEAR STRAP
†— S-6R
UPPER  - S-8R
REVEAL  STUB
FRAME
GAP  S-9R
COVER
FWD
DETAILED INSPECTION  3003933
FIGURE 2: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL DETAILED INSPECTION
(SHEET 2 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  38 of 63

### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)-141A3312-()FUSELAGE SKINInspect1
(a) Do an external surface detailed inspection of the fuselage skin at the forward galley door cutout forward
upper corner for any crack.
FIGURE 2: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN -
EXTERNAL DETAILED INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
39 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 40 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3003934
FIGURE 3: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN AND
BEAR STRAP - EXTERNAL HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 1 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  40 of 63

### Page 41 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FUSELAGE  STA
SKIN  RAIN GUTTER  291.5  BEAR STRAP
• S-6R
3 zONE 1
UPPER
REVEAL
-S-8R
FWD  (3) ZONE 1 L
STUB
FRAME  ) 11 LOCATIONS
FUSELAGE SKIN
(3) ZONE 1 L
BEAR STRAP
ROTATED 90° CW
UPPER REVEAL OMITTED FOR CLARITY
HFEC INSPECTION AREA  A-A
ZONE 1 L  HFEC INSPECTION OF FUSELAGE SKIN AND BEAR  3003935
STRAP EDGES ALONG DOOR CORNER RADIUS
FIGURE 3: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN AND
BEAR STRAP - EXTERNAL HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 2 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  41 of 63

### Page 42

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)-141A3312-()FUSELAGE SKINInspect1
(a)(b)-141A3312-()FUSELAGE SKINInspect2
(c)-141A3312-()FUSELAGE SKINInspect3
(c)-141A3313-()BEAR STRAPInspect
(a) Do an external surface High Frequency Eddy Current (HFEC) inspection of the fuselage skin for any crack
at each fastener location. Use the probe to scan on the outer surface of the fuselage skin around the
fastener heads in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure 23. The
fuselage skin thickness is 0.100 inch.
(b) Rain Gutter removal is not required. Do an external surface High Frequency Eddy Current (HFEC) around
the accessible area of the fastener.
(c) Do an external surface HFEC inspection of the fuselage skin and bear strap along the edge of door corner
radius for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure
23. The fuselage skin and bear strap thicknesses are 0.100 inch and 0.090 inch respectively.
FIGURE 3: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER FUSELAGE SKIN AND
BEAR STRAP - EXTERNAL HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
42 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 43 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3004843
FIGURE 4: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER BEAR STRAP - EXTERNAL
LOW FREQUENCY EDDY CURRENT (LFEC) CURRENT INSPECTION
(SHEET 1 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  Export Controlled ECCN: 9E991  43 of 63

### Page 44 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FUSELAGE  SKIN  RAIN GUTTER  291.5  STA  BEAR STRAP
— S-6R
UPPER
REVEAL  -S-8R
11 LOCATIONS (
STUB
FRAME
FWD
LFEC INSPECTION AREA
3003936
FIGURE 4: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER BEAR STRAP - EXTERNAL
LOW FREQUENCY EDDY CURRENT (LFEC) CURRENT INSPECTION
(SHEET 2 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  44 of 63

### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)-141A3313-()BEAR STRAPInspect1
(a)(b)-141A3313-()BEAR STRAPInspect2
(a) Do an external subsurface Low Frequency Eddy Current (LFEC) inspection of the bear strap for any crack
at each fastener location. Use the probe to scan on the outer surface of the bear strap around the fastener
heads in accordance with 737 NDT Manual Part 6, 51-00-26. The fuselage skin and bear strap thicknesses
are 0.100 inch and 0.090 inch respectively.
(b) Rain Gutter removal is not required. Do an external subsurface Low Frequency Eddy Current (LFEC) in-
spection around the accessible area of the fastener.
FIGURE 4: FORWARD GALLEY DOOR CUTOUT - FORWARD UPPER CORNER BEAR STRAP - EXTERNAL
LOW FREQUENCY EDDY CURRENT (LFEC) CURRENT INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
45 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 46 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3003937
FIGURE 5: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
(SHEET 1 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  46 of 63

### Page 47 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FUSELAGE  TRIPLER  STA
FLAT  SKIN  291.5  1) 11 LOCATIONS
SHIM  DOUBLER
BEAR STRAP
RAIN
GUTTER
TAPERED  3) ZONE 1
SHIM
UPPER  — S-8R
REVEAL
3) ZONE 1
STUL
FRAME
• S-9R
TRIPLER
DOUBLER
3) ZONE 1
FUSELAGE SKIN
BEAR STRAP
FILLER  - S-10R
ROTATED 90° CW
UPPER REVEAL OMITTED FOR CLARITY  RAIN
A-A  GUTTER
HFEC INSPECTION AREA
ZONE 1  HFEC INSPECTION OF TRIPLER, DOUBLER, FUSELAGE SKIN  3003938
AND BEAR STRAP EDGES ALONG DOOR CORNER RADIUS
FIGURE 5: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
(SHEET 2 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  47 of 63

### Page 48

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)--TRIPLERInspect1
(a)(b)--TRIPLERInspect2
(c)--TRIPLERInspect3
(c)--DOUBLERInspect
(c)-141A3312-()FUSELAGE SKINInspect
(c)-141A3313-()BEAR STRAPInspect
(a) Do an external surface High Frequency Eddy Current (HFEC) inspection of the tripler for any crack at
each fastener location. Use the probe to scan on the outer surface of the tripler around the fastener heads
in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure 23. The tripler, doubler,
fuselage skin and bear strap thicknesses are 0.063 inch, 0.100 inch, 0.100 inch and 0.090 inch respec-
tively.
(b) Rain Gutter removal is not required. Do an external surface High Frequency Eddy Current (HFEC) inspec-
tion around the accessible area of the fastener.
(c) Do an external surface HFEC inspection of the tripler, doubler, fuselage skin and bear strap along the
edge of door corner radius for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure
4, or Procedure 23. The tripler, doubler, fuselage skin and bear strap thicknesses are 0.063 inch, 0.100
inch, 0.100 inch and 0.090 inch respectively.
FIGURE 5: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
48 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 49 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3004886
FIGURE 6: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITH A QUADRUPLER REPAIR
(SHEET 1 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  49 of 63

### Page 50 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
SHIM  FLAT  SKIN  FUSELAGE  DOUBLER  TRIPLER  QUADRUPLER  291.5  STA  BEAR STRAP
RAIN
GUTTER
TAPERED  3) ZONE 1
SHIM
UPPER  • S-8R
REVEAL
3) ZONE 1
STUB
QUADRUPLER  FRAME
• S-9R
TRIPLER
DOUBLER
(3) ZONE 1
BEAR STRAP  FUSELAGE SKIN
ROTATED 90° CW  FILLER  -S-10R
UPPER REVEAL OMITTED FOR CLARITY
RAIN
A-A  GUTTER
1) 11 LOCATIONS
HFEC INSPECTION AREA
ZONE 1 L  HFEC INSPECTION OF QUADRUPLER, TRIPLER,  DOUBLER, FUSELAGE SKIN AND BEAR STRAP  3003946
EDGES ALONG DOOR CORNER RADIUS
FIGURE 6: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITH A QUADRUPLER REPAIR
(SHEET 2 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  50 of 63

### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)--QUADRUPLERInspect1
(a)(b)--QUADRUPLERInspect2
(c)--QUADRUPLERInspect3
(c)--TRIPLERInspect
(c)--DOUBLERInspect
(c)-141A3312-()FUSELAGE SKINInspect
(c)-141A3313-()BEAR STRAPInspect
(a) Do an external surface High Frequency Eddy Current (HFEC) inspection of the quadrupler for any crack
at each fastener location. Use the probe to scan on the outer surface of the quadrupler around the fastener
heads in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4, or Procedure 23. The
quadrupler, tripler, doubler, fuselage skin and bear strap thicknesses are 0.063 inch, 0.063 inch, 0.100
inch, 0.100 inch and 0.090 inch respectively.
(b) Rain Gutter removal is not required. Do an external surface High Frequency Eddy Current (HFEC) inspec-
tion around the accessible area of the fastener.
(c) Do external surface HFEC inspection of the quadrupler, tripler, doubler, fuselage skin and bear strap
along the edge of door corner radius for any crack in accordance with 737 NDT Manual Part 6, 51-00-00,
Procedure 4, or Procedure 23. The quadrupler, tripler, doubler, fuselage skin and bear strap thicknesses
are 0.063 inch, 0.063 inch, 0.100 inch, 0.100 inch and 0.090 inch respectively.
FIGURE 6: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION WITH A QUADRUPLER REPAIR
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
51 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 52 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3004723
FIGURE 7: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
(SHEET 1 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  52 of 63

### Page 53 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
STA
FLAT  SHIM  SKIN  FUSELAGE  DOUBLER  TRIPLER  291.5  BEAR STRAP
RAIN
GUTTER
TAPERED
SHIM
UPPER  - S-8R
REVEAL
10 LOCATIONS
STUE
FRAME
- S-9R
- S-10R
FILLER
RAIN
GUTTER
FWD
LFEC INSPECTION AREA  3003944
FIGURE 7: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOV
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
(SHEET 2 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  53 of 63

### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)--DOUBLERInspect1
(b)--DOUBLERInspect2
(b)-141A3312-()FUSELAGE SKINInspect
(a)(c)--DOUBLERInspect3
(a) Do an external subsurface Low Frequency Eddy Current (LFEC) inspection of the doubler for any crack
at each fastener location. Use the probe to scan on the outer surface of the doubler around the fastener
heads in accordance with 737 NDT Manual Part 6, 51-00-26. The tripler, doubler and fuselage skin
thicknesses are 0.063 inch, 0.100 inch and 0.100 inch respectively.
(b) Do an external subsurface Low Frequency Eddy Current (LFEC) inspection of the doubler and fuselage
skin for any crack at the fastener location. Use the probe to scan on the outer surface of the doubler
around the fastener head in accordance with 737 NDT Manual Part 6, 51-00-26. The tripler, doubler and
fuselage skin thicknesses are 0.063 inch, 0.100 inch and 0.100 inch respectively.
(c) Rain Gutter removal is not required. Do an external subsurface Low Frequency Eddy Current (LFEC) in-
spection around the accessible area of the fastener.
FIGURE 7: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITHOUT A QUADRUPLER REPAIR
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
54 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 55 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FWD
FORWARD GALLEY DOOR
3004875
FIGURE 8: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITH A QUADRUPLER REPAIR
(SHEET 1 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  55 of 63

### Page 56 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
FUSELAGE  TRIPLER  STA
SKIN  291.5  BEAR STRAP
FLAT  DOUBLER  QUADRUPLER
SHIM
RAIN
GUTTER
TAPERED
SHIM  UPPER
REVEAL  - S-8R
10 LOCATIONS
STUB
FRAME
• S-9R
FILLER
- S-10R
RAIN
GUTTER
LFEC INSPECTION AREA  3003975
FIGURE 8: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITH A QUADRUPLER REPAIR
(SHEET 2 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  56 of 63

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)--TRIPLERInspect1
(a)--DOUBLERInspect
(b)--TRIPLERInspect2
(b)--DOUBLERInspect
(b)-141A3312-()FUSELAGE SKINInspect
(a)(c)--TRIPLERInspect3
(a)(c)--DOUBLERInspect
(a) Do an external subsurface Low Frequency Eddy Current (LFEC) inspection of the tripler and doubler for
any crack at each fastener location. Use the probe to scan on the outer surface of the tripler around the
fastener heads in accordance with 737 NDT Manual Part 6, 51-00-26. The quadrupler, tripler, doubler
and fuselage skin thicknesses are 0.063 inch, 0.063 inch, 0.100 inch and 0.100 inch respectively.
(b) Do an external subsurface Low Frequency Eddy Current (LFEC) inspection of the tripler, doubler and
fuselage skin for any crack at the fastener location. Use the probe to scan on the outer surface of the
tripler around the fastener head in accordance with 737 NDT Manual Part 6, 51-00-26. The quadrupler,
tripler, doubler and fuselage skin thicknesses are 0.063 inch, 0.063 inch, 0.100 inch and 0.100 inch re-
spectively.
(c) Rain Gutter removal is not required. Do an external subsurface Low Frequency Eddy Current (LFEC)
around the accessible area of the fastener.
FIGURE 8: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - EXTERNAL LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION WITH A QUADRUPLER REPAIR
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
57 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

### Page 58 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
STA
STA  344
STA  STA  328
294.5  312
SIA  277  291.5  STA  7- S-5R
=- S-6R
— S-7R
→ S-8R
— S-9R
→— S-10R
S-9R-
- S-11R
S-12R
S-12R-
‚— S-13R
S-13R -
1- S-14R
- S-15R
S-15R -C
I- S-16R
S-16R-
FORWARD GALLEY DOOR CUTOUT STRUCTURE
FWD  (GALLEY, SIDEWALL PANELS AND INSULATION REMOVED)  3003978
FIGURE 9: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - INTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 1 OF 3)
Original Issue: December 20, 2022
737-53A1407 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  58 of 63

### Page 59 (OCR)

REQUIREMENTS BULLETIN 737-53A1407
ALERT  ALERT
BEAR STRAP  FUSELAGE
SKIN
UPPER  REVEAL  UPPER MAIN  SEAL
STUB
FRAME
SEAL
DEPRESSOR
HFEC INSPECTION AREA  3003979
FIGURE 9: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - INTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 2 OF 3)
Original Issue: December 20, 2022
Export Controlled ECCN: 9E991  737-53A1407 RB
Copyright © Unpublished Work - See page 1 for details.  59 of 63

### Page 60

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a)--BEAR STRAPInspect1
(a) Do an internal surface High Frequency Eddy Current (HFEC) inspection of the bear strap for any crack .
Use the probe to scan around the fastener head in the half circle area shown. Do not let the probe reach
the edge of part during HFEC inspection. Do the HFEC inspection in accordance with 737 NDT Manual
Part 6, 51-00-00, Procedure 4, or Procedure 23. The bear strap thickness is 0.090 inch.
FIGURE 9: FORWARD GALLEY DOOR CUTOUT FORWARD UPPER CORNER - INTERNAL HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 20, 2022
737-53A1407 RB
60 of 63
REQUIREMENTS BULLETIN 737-53A1407
ALERTALERT

The text continues at https://openairdocs.org/service-documents/boeing/737-53a1407-rb/file/eb7e418ae4d3.md?from=61

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