# Boeing Alert Requirements Bulletin 737-57A1359 RB: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2026-2725; AD 2026-21-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Requirements Bulletin 737-57A1359 RB](https://openairdocs.org/service-documents/boeing/737-57a1359-rb.md)
- Title as filed: 737-57A1359 RB
- Pages: 42
- PDF: https://openairdocs.org/files/sha256/7d/82/7d82d2fd78d91ae387161a569124cdfe213b8663e81961434680f6f7432757c8
- Page: https://openairdocs.org/service-documents/boeing/737-57a1359-rb/file/7d82d2fd78d9

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-57A1359 RB
Original Issue: October 03, 2025
ATA System: 5741
SUBJECT: WINGS - Wing Leading Edge - Engine Fuel Shutoff Valve Access Panel Inspection
and Test
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 © 2025 The Boeing Company
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: October 03, 2025
737-57A1359 RB
1 of 42
4.0

### Page 2

Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
2 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
FIGURE 1: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET) . . . . . . . . . . . . . . . . . . . . . . . . . . 17
FIGURE 2: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET) . . . . . . . . . . . . . . . . . . . . . . . . . . 20
FIGURE 3: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
FIGURE 4: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
APPENDIX A: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST . 33
APPENDIX B: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST. 38
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
3 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
4 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-57A1359 RB
Original Issue: October 03, 2025
ATA System: 5741
SUBJECT: WINGS - Wing Leading Edge - Engine Fuel Shutoff Valve Access Panel Inspection
and Test
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
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 737-700, 737-700C, 737-800, 737-900ER Airplane(s), line number(s)
1981, 2093, 3834-3878, 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, 6873-6874, 6878-6880, 6882-6883, 6885,
6887-6889, 6891-6892, 6894, 6896, 6898, 6900-6903, 6905, 6907, 6910, 6912-6914, 6916,
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
5 of 42

### Page 6

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 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.
DESCRIPTIONCONFIGURATIONGROUP
737-700, -700C, -800, -900ER Airplanes-1
Airplane Models:
737-700, 737-700C, 737-800, 737-900ER
GroupVariable Number
1YB636
1YD418 - YD424
1YF068 - YF080
1YF132
1YF634 - YF685
1YF691 - YF695
1YF871 - YF872
1YG134 - YG149
1YG513 - YG517
1YG721 - YG722
1YH001 - YH002
1YH307
GroupVariable Number
1YH512 - YH542
1YH552 - YH594
1YH603 - YH606
1YH613 - YH620
1YH632
1YH636 - YH637
1YH641
1YH681 - YH686
1YH701 - YH755
1YH801 - YH899
1YH901 - YH908
1YH911 - YH915
GroupVariable Number
1YH951 - YH952
1YK478
1YK493
1YK499
1YK695 - YK699
1YK999
1YL231 - YL237
1YM414 - YM415
1YN126
1YN552 - YN566
1YN581 - YN585
1YN591 - YN593
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
6 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 7

GroupVariable Number
1YN602 - YN606
1YN651 - YN653
1YN661 - YN663
1YN666 - YN667
1YN671 - YN674
1YN741 - YN746
1YN756 - YN758
1YQ020 - YQ021
1YQ045
1YQ203 - YQ207
1YQ283 - YQ284
1YQ321 - YQ324
1YQ331 - YQ334
1YQ346 - YQ347
1YQ351 - YQ367
1YQ371
1YQ456
1YQ461
1YQ471
1YQ501 - YQ520
1YQ601 - YQ606
1YQ610 - YQ614
1YR014 - YR050
1YR057 - YR098
1YR103 - YR105
1YR117 - YR124
1YR130 - YR140
1YR143 - YR144
1YR173 - YR182
1YR186 - YR198
1YR205 - YR215
1YR246 - YR270
1YR279 - YR285
GroupVariable Number
1YR287 - YR290
1YR312 - YR334
1YR338 - YR341
1YR363 - YR366
1YR371 - YR373
1YR376 - YR377
1YR382
1YR386 - YR388
1YR391
1YR396 - YR399
1YR411 - YR413
1YR416 - YR418
1YR423 - YR424
1YR426 - YR430
1YR432 - YR450
1YR454 - YR455
1YR457 - YR499
1YR504 - YR506
1YR513 - YR515
1YR519 - YR520
1YR527 - YR544
1YR546 - YR551
1YR556 - YR562
1YR571 - YR582
1YR591 - YR592
1YR618 - YR650
1YR653 - YR655
1YR657 - YR658
1YR661 - YR663
1YR671 - YR673
1YR676 - YR678
1YR681 - YR682
1YR714 - YR769
GroupVariable Number
1YR771 - YR799
1YR807 - YR827
1YR831 - YR838
1YR841 - YR850
1YR854 - YR899
1YR901 - YR903
1YR931 - YR934
1YR938 - YR944
1YR952 - YR998
1YS002
1YS006 - YS009
1YS031 - YS032
1YS053 - 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
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
7 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 8

GroupVariable Number
1YS506
1YS511 - YS518
1YS531
1YS536 - YS538
1YS541 - YS542
1YS546
1YS551 - YS556
1YS561 - YS578
1YS581 - YS595
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
GroupVariable Number
1YT101 - YT138
1YT176 - YT185
1YT191
1YT196 - YT199
1YT201
1YT206 - YT207
1YT211 - YT213
1YT251 - YT299
1YT301 - YT307
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
GroupVariable Number
1YT831 - YT832
1YT841 - YT852
1YT856 - YT863
1YT885 - YT887
1YT891 - YT895
1YT901 - YT998
1YU001 - YU060
1YU201 - YU218
1YU301 - YU329
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
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
8 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 9

GroupVariable Number
1YV501 - YV512
1YV521
1YV571 - YV586
1YV596
1YV601 - YV605
1YV651 - YV674
1YV676
1YV695 - YV696
1YV701 - YV702
1YV711
1YV722 - YV731
1YV741 - YV794
1YV801 - YV820
1YV831 - YV848
1YV881 - YV883
1YV901 - YV915
1YV923 - YV926
1YV971 - YV983
1YW001
1YW011 - YW099
GroupVariable Number
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
GroupVariable Number
1YW585 - YW591
1YW595 - YW596
1YW601
1YW610 - YW613
1YW616 - YW623
1YW666
1YW696 - YW699
1YW701 - YW715
1YW726 - YW731
1YW766 - YW775
1YW801 - YW803
1YW811 - YW813
1YW821
1YW831
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 737-57A1359 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 737-57A1359 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Table 1 and Table 2, in accordance
with Accomplishment Instructions.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
9 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 10

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that
CONDITION or OPTION.
Table 1: Form-in-Place (FiP) Gasket Detailed Inspection (DET) and Fluid Leak Test, Left Wing
Repeat Inter-
val (Not to
Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 36 months after
the Original Issue date of
Requirements Bulletin
737-57A1359 RB.
Do a DET of the FiP gasket at
the engine fuel shutoff valve
access panel for correct
sealant installation. (a)
All Airplanes.
-Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Replace the FiP gasket.INCORRECT SEALANT
INSTALLATION FOUND. CONDITION 1 (ACTION 2):
Do a fluid leak test of the en-
gine fuel shutoff valve access
panel for any leak. If any leak
is found, do all applicable on-
condition corrective action(s)
and repeat the leak test until
no leak is found.
-Before further flight.Do a fluid leak test of the en-
gine fuel shutoff valve access
panel for any leak. If any leak
is found, do all applicable on-
condition corrective action(s)
and repeat the leak test until
no leak is found.
CONDITION 2:
CORRECT SEALANT IN-
STALLATION FOUND.
(a) Correct sealant installation is defined as:
1. No structure is visible in the FiP gasket area.
2. The sealing surface is smooth.
3. No sealant touch-up is added after the original sealant application. It is identified by
irregular, smeared, or thicker regions with different texture or appearance from the
surrounding gasket, often with visible brush or tool marks.
4. Any small cavity or depression in the sealing surface which are less than or equal to
1/4 inch in width, and 1/8 inch in length, are permitted if the cavities or depressions
do not extend across the full width of the sealed surface and maintain a minimum
sealing surface of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the
main track rib assembly and attach strap.
6. The gasket is adhered to the underlying surface and is not loose.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
10 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 11

Table 2: Form-in-Place (FiP) Gasket Detailed Inspection (DET) and Fluid Leak Test, Right Wing
Repeat Inter-
val (Not to
Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Within 36 months after
the Original Issue date of
Requirements Bulletin
737-57A1359 RB.
Do a DET of the FiP gasket at
the engine fuel shutoff valve
access panel for correct
sealant installation. (a)
All Airplanes.
-Before further flight.CONDITION 3 (ACTION 1):CONDITION 3:
Replace the FiP gasket.INCORRECT SEALANT
INSTALLATION FOUND. CONDITION 3 (ACTION 2):
Do a fluid leak test of the en-
gine fuel shutoff valve access
panel for any leak. If any leak
is found, do all applicable on-
condition corrective action(s)
and repeat the leak test until
no leak is found.
-Before further flight.Do a fluid leak test of the en-
gine fuel shutoff valve access
panel for any leak. If any leak
is found, do all applicable on-
condition corrective action(s)
and repeat the leak test until
no leak is found.
CONDITION 4:
CORRECT SEALANT IN-
STALLATION FOUND.
(a) Correct sealant installation is defined as:
1. No structure is visible in the FiP gasket area.
2. The sealing surface is smooth.
3. No sealant touch-up is added after the original sealant application. It is identified by
irregular, smeared, or thicker regions with different texture or appearance from the
surrounding gasket, often with visible brush or tool marks.
4. Any small cavity or depression in the sealing surface which are less than or equal to
1/4 inch in width, and 1/8 inch in length, are permitted if the cavities or depressions
do not extend across the full width of the sealed surface and maintain a minimum
sealing surface of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the
main track rib assembly and attach strap.
6. The gasket is adhered to the underlying surface and is not loose.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
11 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 12

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) approved for all EASA 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.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
12 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 13

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. In the RB, the "Refer to the listed procedures..." column of the
table(s) in the Work Instructions is for reference only. The procedures in that column
are not required by the AD and are for guidance only. 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. 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.
— 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.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
13 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 14

5. 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.
6. 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.
7. 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.
8. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
9. A Detailed Inspection (DET) 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.
10. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION or an OPTION,
do all of the ACTION numbers for that CONDITION or OPTION.
11. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
12. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
B. WORK INSTRUCTIONS
Actions Required for Compliance
1. Requirements.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
14 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 15

Table 1: Form-in-Place (FiP) Gasket Detailed Inspection (DET) and Fluid Leak Test, Left Wing
Refer to the listed
procedures in SB
737-57A1359 Origi-
nal Issue or later
approved revi-
sions as an accept-
ed procedure
Method of Compli-
ance
ActionCondition
PART 1: LEFT
WING OPEN AC-
CESS
-Do a DET of the FiP gasket at
the engine fuel shutoff valve
access panel for correct sealant
installation. (a)
All Airplanes.
-FIGURE 1
-FIGURE 3CONDITION 1 (ACTION 1):CONDITION 1:
Replace the FiP gasket.INCORRECT
SEALANT INSTALLA-
TION FOUND. -APPENDIX ACONDITION 1 (ACTION 2):Do a fluid leak test of the engine
fuel shutoff valve access panel
for any leak. If any leak is found,
do all applicable on-condition
corrective action(s) and repeat
the leak test until no leak is
found.
PART 3: LEFT
WING CLOSE AC-
CESS
-
-APPENDIX ADo a fluid leak test of the engine
fuel shutoff valve access panel
for any leak. If any leak is found,
do all applicable on-condition
corrective action(s) and repeat
the leak test until no leak is
found.
CONDITION 2:
CORRECT SEALANT
INSTALLATION
FOUND.
PART 3: LEFT
WING CLOSE AC-
CESS
-
(a) Correct sealant installation is defined as:
1. No structure is visible in the FiP gasket area.
2. The sealing surface is smooth.
3. No sealant touch-up is added after the original sealant application. It is identified by irreg-
ular, smeared, or thicker regions with different texture or appearance from the surrounding
gasket, often with visible brush or tool marks.
4. Any small cavity or depression in the sealing surface which are less than or equal to 1/4
inch in width, and 1/8 inch in length, are permitted if the cavities or depressions do not
extend across the full width of the sealed surface and maintain a minimum sealing surface
of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the
main track rib assembly and attach strap.
6. The gasket is adhered to the underlying surface and is not loose.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
15 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 16

Table 2: Form-in-Place (FiP) Gasket Detailed Inspection (DET) and Fluid Leak Test, Right Wing
Refer to the listed
procedures in SB
737-57A1359 Origi-
nal Issue or later
approved revi-
sions as an accept-
ed procedure
Method of Compli-
ance
ActionCondition
PART 2: RIGHT
WING OPEN AC-
CESS
-Do a DET of the FiP gasket at
the engine fuel shutoff valve
access panel for correct sealant
installation. (a)
All Airplanes.
-FIGURE 2
-FIGURE 4CONDITION 3 (ACTION 1):CONDITION 3:
Replace the FiP gasket.INCORRECT
SEALANT INSTALLA-
TION FOUND. -APPENDIX BCONDITION 3 (ACTION 2):Do a fluid leak test of the engine
fuel shutoff valve access panel
for any leak. If any leak is found,
do all applicable on-condition
corrective action(s) and repeat
the leak test until no leak is
found.
PART 4: RIGHT
WING CLOSE AC-
CESS
-
-APPENDIX BDo a fluid leak test of the engine
fuel shutoff valve access panel
for any leak. If any leak is found,
do all applicable on-condition
corrective action(s) and repeat
the leak test until no leak is
found.
CONDITION 4:
CORRECT SEALANT
INSTALLATION
FOUND.
PART 4: RIGHT
WING CLOSE AC-
CESS
-
(a) Correct sealant installation is defined as:
1. No structure is visible in the FiP gasket area.
2. The sealing surface is smooth.
3. No sealant touch-up is added after the original sealant application. It is identified by irreg-
ular, smeared, or thicker regions with different texture or appearance from the surrounding
gasket, often with visible brush or tool marks.
4. Any small cavity or depression in the sealing surface which are less than or equal to 1/4
inch in width, and 1/8 inch in length, are permitted if the cavities or depressions do not
extend across the full width of the sealed surface and maintain a minimum sealing surface
of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the
main track rib assembly and attach strap.
6. The gasket is adhered to the underlying surface and is not loose.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
16 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 17 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
36.02
cA:
SEAL RIB  SLAT STA  MAIN TRACK
ASSEMBLY  36.02  • UPPER SKIN PANEL  RIB ASSEMBLY
LOWER SKIN  ATTACH
PANEL  STRAP
ENGINE FUEL SHUTOFF VALVE
DETAILED INSPECTION  ACCESS PANEL IS NOT SHOWN  (VIEW IN THE UP DIRECTION)  NB  3087334
AREA  A-A
FIGURE 1: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET)
(SHEET 1 OF 3)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  17 of 42

### Page 18 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
MAIN TRACK
RIB ASSEMBLY
ATTACH
STRAP
INB
ENGINE FUEL SHUTOFF VALVE
ACCESS PANEL IS NOT SHOWN
DETAILED INSPECTION  3087465
AREA
FIGURE 1: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET)
(SHEET 2 OF 3)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  18 of 42

### Page 19

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)(b)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANT (FORM-IN-
PLACE GASKET)
Inspect1
(c)(d)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANTInspect2
(a) Correct sealant installation is defined as:
1. No structure is visible in the FiP gasket area.
2. The sealing surface is smooth.
3. No sealant touch-up is added after the original sealant application. It is identified by irregular,
smeared, or thicker regions with different texture or appearance from the surrounding gasket,
often with visible brush or tool marks.
4. Any small cavity or depression in the sealing surface which are less than or equal to 1/4 inch in
width, and 1/8 inch in length, are permitted if the cavities or depressions do not extend across
the full width of the sealed surface and maintain a minimum sealing surface of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the main track
rib assembly and attach strap.
6. The gasket is adhered to the underlying surface and is not loose.
(b) Do a DET of the FiP gasket on the seal rib assembly, attach strap, and main track rib assembly in areas
which contact the engine fuel shutoff valve access panel for correct sealant installation.
(c) Do a DET of the sealant on the main track rib assembly adjacent to the attach strap to make sure that it
seals the space between the main track rib assembly and attach strap, is attached to the rib's surface,
and is flush with adjacent surfaces.
(d) Correct sealant installation in the FiP gasket area of the engine fuel shutoff valve access panel also in-
cludes:
1. The outboard aft corner of the gasket area is sealed and attached to the flange of the main track
rib assembly and attach strap.
FIGURE 1: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET)
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
19 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 20 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
36.02
MAIN TRACK  SLAT STA  SEAL RIB
RIB ASSEMBLY  UPPER SKIN PANEL  36.02  ASSEMBLY
ATTACH  LOWER SKIN
STRAP  PANEL
ENGINE FUEL SHUTOFF ACCESS
DETAILED INSPECTION  (VIEW IN THE UP DIRECTION)  PANEL IS NOT SHOWN  3087613
AREA  A-A
FIGURE 2: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET)
(SHEET 1 OF 3)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  20 of 42

### Page 21 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
MAIN TRACK
RIB ASSEMBLY
ATTACH
STRAP
ENGINE FUEL SHUTOFF VALVE
ACCESS PANEL IS NOT SHOWN
• DETAILED INSPECTION  3088510
AREA
FIGURE 2: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET)
(SHEET 2 OF 3)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  21 of 42

### Page 22

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)(b)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANT (FORM-IN-
PLACE GASKET)
Inspect1
(c)(d)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANTInspect2
(a) Correct sealant installation is defined as:
1. No structure is visible in the FiP gasket area.
2. The sealing surface is smooth.
3. No sealant touch-up is added after the original sealant application. It is identified by irregular,
smeared, or thicker regions with different texture or appearance from the surrounding gasket,
often with visible brush or tool marks.
4. Any small cavity or depression in the sealing surface which are less than or equal to 1/4 inch in
width, and 1/8 inch in length, are permitted if the cavities or depressions do not extend across
the full width of the sealed surface and maintain a minimum sealing surface of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the main track
rib assembly and attach strap.
6. The gasket is adhered to the underlying surface and is not loose.
(b) Do a DET of the FiP gasket on the seal rib assembly, attach strap, and main track rib assembly in areas
which contact the engine fuel shutoff valve access panel for correct sealant installation.
(c) Do a DET of the sealant on the main track rib assembly adjacent to the attach strap to make sure that it
seals the space between the main track rib assembly and attach strap, is attached to the rib's surface,
and is flush with adjacent surfaces.
(d) Correct sealant installation in the FiP gasket area of the engine fuel shutoff valve access panel also in-
cludes:
1. The outboard aft corner of the gasket area is sealed and attached to the flange of the main track
rib assembly and attach strap.
FIGURE 2: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET DETAILED INSPECTION (DET)
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
22 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 23 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
36.02
SEAL RIB  ASSEMBLY  SLAT STA  36.02  UPPER SKIN PANEL  MAIN TRACK  RIB ASSEMBLY
LOWER SKIN  PANEL  20€60U  D450U  ATTACH
STRAP
ENGINE FUEL SHUTOFF VALVE
ACCESS PANEL IS NOT SHOWN
(VIEW IN THE UP DIRECTION)
APPLICATION AREA  FORM-IN-PLACE GASKET  A-A
FORM-IN-PLACE GASKET AND  3087587
SEALANT APPLICATION AREA
FIGURE 3: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 1 OF 5)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  23 of 42

### Page 24 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
MAIN TRACK
RIB ASSEMBLY
14€01
З4€Đ00
- ATTACH STRAP
ANED
ENGINE FUEL SHUTOFF VALVE ACCESS
PANEL IS SHOWN IN CLOSED POSITION
FORM-IN-PLACE GASKET
APPLICATION AREA
FORM-IN-PLACE GASKET AND  3087591
SEALANT APPLICATION AREA
FIGURE 3: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 2 OF 5)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  24 of 42

### Page 25

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)(b)--SEALANT (FORM-IN-
PLACE GASKET)
Remove1
(b)(c)--SEALANTRemove2
(b)(d)--SEALANTRemove3
(e)--CORROSION INHIBIT-
ING COMPOUND
Remove4
(f)(g)--SURFACEClean5
(h)(i)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANTApply6
(h)(j)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANTApply7
(k)(l)(m)-FREKOTE 710-NCPARTING AGENTApply8
(n)(o)-BMS 5-45, CLASS B-
1/2
SEALANT (FORM-IN-
PLACE GASKET)
Apply9
(p)(q)1521BBENGINE FUEL SHUT-
OFF VALVE ACCESS
PANEL
Open10
(b)(r)1521BBENGINE FUEL SHUT-
OFF VALVE ACCESS
PANEL
Clean11
(b)(r)(s)--SURFACEClean
(b)(t)-BMS 5-45, CLASS B-
1/2
SEALANTRemove12
(a) Remove the existing FiP gasket on the seal rib assembly, main track rib assembly, and attach strap.
(b) Use a non-metallic tool and make sure not to damage the surface of the metal or protective coating. Refer
to SOPM 20-50-19 as an accepted procedure.
(c) Remove existing sealant in the space between the seal rib assembly and adjacent attach strap.
(d) Remove existing sealant in the space between the main track rib assembly and adjacent attach strap.
Make sure all sealant is removed from the surround structure at the aft outboard side of the engine fuel
shutoff valve access panel. Remove sealant located on the underside of the main track rib assembly
flange and attach strap.
(e) Remove existing corrosion inhibiting compound from the shown surfaces where a FiP gasket or sealant
was applied. Refer to SOPM 20-50-19 as an accepted procedure.
(f) Clean the surfaces of the seal rib assembly, main track rib assembly, and attach strap which have had
the FiP gasket or sealant removed. Refer to SOPM 20-50-19 as an accepted procedure.
FIGURE 3: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 3 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
25 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 26

More DataQtyIdentificationNameTaskStep
(g) If the surface finish on the structure in the shown area is cracked or shows signs of abrasion, repair
chemical and solvent resistant finish. Refer to SOPM 20-41-02 as an accepted procedure.
(h) BMS 5-45 shrinks when it cures, make sure that the sealant stays attached to the structure(s) after it
cures. It is optional to co-cure the sealant with the FiP gasket. Refer to SOPM 20-50-19 as an accepted
procedure.
(i) Fill the space between the seal rib assembly and adjacent attach strap flush with sealant.
(j) At the aft outboard side of the engine fuel shutoff valve access panel surround structure, build up the
sealant flush to fill the space between the flange of the main track rib assembly and adjacent attach strap.
It is permitted to apply sealant to the underside of these parts to secure the sealant. Refer to Boeing
Service Bulletin 737-57A1359 APPENDIX E for example application of main track rib assembly attach
strap space sealant on the right wing engine fuel shutoff valve access panel.
(k) Do not apply parting agent to the surround structure of the engine fuel shutoff valve access panel.
(l) Frekote 710-NC is permitted to be used as a parting agent.
(m) If Frekote 710-NC is used as a parting agent, do as follows:
– Apply two coats to the surfaces of the engine fuel shutoff valve access panel which are in contact
with the surround structure. Apply parting agent to the access panel only. Allow 5 to 10 minutes be-
tween each application. Allow 20 minutes after the second application before closing the access
panel. Extend the application area of parting agent to be more than 2 inch larger than the fay surface
area to allow for the squeeze out. Parting agent can be applied to the entire surface of the engine
fuel shutoff valve access panel. Do not touch applied parting agent.
(n) Make a FiP gasket. Apply sealant smooth and flat at the fay surface of the engine fuel shutoff valve access
panel surround structure. Enough sealant should be applied to achieve continuous squeeze-out along
the edges of the panel. After the access panel has latched close, continue to press up on the panel with
the same force used to latch the panel. Continue this pressure for 15 seconds to allow excess sealant to
squeeze out fully. Do not press up with more force than required to latch the panel or voids will be created
in the FiP gasket and the fluid leak test will fail.
(o) After closing the engine fuel shutoff valve access panel, while the FiP gasket sealant is still wet, remove
the sealant from the spaces between the edges of both the access panel and surrounding structure, except
for the sealant at the aft edge of the engine fuel shutoff valve access panel. Allow the sealant to cure.
Refer to SOPM 20-50-19 as an accepted procedure.
(p) After the sealant has cured, cycle the engine fuel shutoff valve access panel to break it free from the
sealant. If necessary, use a skin wedge to break the panel free. After cycling the panel, it should open
without assistance. Make sure that the sealant bonds to the access panel surround structure and not the
access panel. Trim excess cured sealant from door structure as required.
(q) After sealant has cured and door has been re-opened, remove and apply new parting agent. Refer to
SOPM 20-50-19 as an accepted procedure. In lieu of subsequent re-applications of parting agent every
time the door is re-opened, petrolatum that meets VV-P-236 specification or Krytox 240AC can be applied
to the panel as a post-cure lubricant. If petrolatum is applied to the panel after the sealant has cured, it
must be wiped off with a lint-free rag leaving behind a thin film. If Krytox is used, it does not have to be
wiped off.
FIGURE 3: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
26 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 27

More DataQtyIdentificationNameTaskStep
(r) Remove any sealant adhering to the access panel or excess sealant squeeze that extends into the panel
opening from the surround structure.
(s) The FiP gasket and sealant must be removed and applied again if the sealing surface on the surround
structure of the engine fuel shutoff valve access panel does not meet all the conditions that follow:
1. No structure is visible in the FiP gasket area.
2. All sealant is evenly distributed.
3. No sealant is added after the initial sealant application time expires.
4. Any small cavity or depression in the sealing surface which are less than or equal to 1/4 inch in
width, and 1/8 inch in length, are permitted if the cavities or depressions do not extend across
the full width of the sealed surface and maintain a minimum sealing surface of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the main track
rib assembly and attach strap.
(t) Remove any excess FiP gasket sealant from the notch at the aft edge of the engine fuel shutoff valve
access panel and forward of the lower skin panel.
FIGURE 3: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
27 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 28 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
36.02
MAIN TRACK  UPPER SKIN PANEL SO A  SEAL RIB
RIB ASSEMBLY  ASSEMBLY
STRAP  ATTACH  04G0U  24500U  LOWER SKIN  PANEL
ENGINE FUEL SHUTOFF VALVE
ACCESS PANEL IS NOT SHOWN  (VIEW IN THE UP DIRECTION)  INBD
FORM-IN-PLACE GASKET  APPLICATION AREA  A-A
FORM-IN-PLACE GASKET AND  6192808
SEALANT APPLICATION AREA
FIGURE 4: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 1 OF 5)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  28 of 42

### Page 29 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
MAIN TRACK
RIB ASSEMBLY
4€0U
14600U
ATTACH STRAP -
ENGINE FUEL SHUTOFF VALVE ACCESS
PANEL IS SHOWN IN CLOSED POSITION
FORM-IN-PLACE GASKET
APPLICATION AREA
FORM-IN-PLACE GASKET AND  3087620
SEALANT APPLICATION AREA
FIGURE 4: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 2 OF 5)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  29 of 42

### Page 30

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)(b)--SEALANT (FORM-IN-
PLACE GASKET)
Remove1
(b)(c)--SEALANTRemove2
(b)(d)--SEALANTRemove3
(e)--CORROSION INHIBIT-
ING COMPOUND
Remove4
(f)(g)--SURFACEClean5
(h)(i)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANTApply6
(h)(j)-BMS 5-45, CLASS B-
1/2 OR B-2
SEALANTApply7
(k)(l)(m)-FREKOTE 710-NCPARTING AGENTApply8
(n)(o)-BMS 5-45, CLASS B-
1/2
SEALANT (FORM-IN-
PLACE GASKET)
Apply9
(p)(q)1621BBENGINE FUEL SHUT-
OFF VALVE ACCESS
PANEL
Open10
(b)(r)1621BBENGINE FUEL SHUT-
OFF VALVE ACCESS
PANEL
Clean11
(b)(r)(s)--SURFACEClean
(b)(t)-BMS 5-45, CLASS B-
1/2
SEALANTRemove12
(a) Remove the existing FiP gasket on the seal rib assembly, main track rib assembly, and attach strap.
(b) Use a non-metallic tool and make sure not to damage the surface of the metal or protective coating. Refer
to SOPM 20-50-19 as an accepted procedure.
(c) Remove existing sealant in the space between the seal rib assembly and adjacent attach strap.
(d) Remove existing sealant in the space between the main track rib assembly and adjacent attach strap.
Make sure all sealant is removed from the surround structure at the aft outboard side of the engine fuel
shutoff valve access panel. Remove sealant located on the underside of the main track rib assembly
flange and attach strap.
(e) Remove existing corrosion inhibiting compound from the shown surfaces where a FiP gasket or sealant
was applied. Refer to SOPM 20-50-19 as an accepted procedure.
(f) Clean the surfaces of the seal rib assembly, main track rib assembly, and attach strap which have had
the FiP gasket or sealant removed. Refer to SOPM 20-50-19 as an accepted procedure.
FIGURE 4: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 3 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
30 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 31

More DataQtyIdentificationNameTaskStep
(g) If the surface finish on the structure in the shown area is cracked or shows signs of abrasion, repair
chemical and solvent resistant finish. Refer to SOPM 20-41-02 as an accepted procedure.
(h) BMS 5-45 shrinks when it cures, make sure that the sealant stays attached to the structure(s) after it
cures. It is optional to co-cure the sealant with the FiP gasket. Refer to SOPM 20-50-19 as an accepted
procedure.
(i) Fill the space between the seal rib assembly and adjacent attach strap flush with sealant.
(j) At the aft outboard side of the engine fuel shutoff valve access panel surround structure, build up the
sealant flush to fill the space between the flange of the main track rib assembly and adjacent attach strap.
It is permitted to apply sealant to the underside of these parts to secure the sealant. Refer to Boeing
Service Bulletin 737-57A1359 APPENDIX E for example application of main track rib assembly attach
strap space sealant on the right wing engine fuel shutoff valve access panel.
(k) Do not apply parting agent to the surround structure of the engine fuel shutoff valve access panel.
(l) Frekote 710-NC is permitted to be used as a parting agent.
(m) If Frekote 710-NC is used as a parting agent, do as follows:
– Apply two coats to the surfaces of the engine fuel shutoff valve access panel which are in contact
with the surround structure. Apply parting agent to the access panel only. Allow 5 to 10 minutes be-
tween each application. Allow 20 minutes after the second application before closing the access
panel. Extend the application area of parting agent to be more than 2 inch larger than the fay surface
area to allow for the squeeze out. Parting agent can be applied to the entire surface of the engine
fuel shutoff valve access panel. Do not touch applied parting agent.
(n) Make a FiP gasket. Apply sealant smooth and flat at the fay surface of the engine fuel shutoff valve access
panel surround structure. Enough sealant should be applied to achieve continuous squeeze-out along
the edges of the panel. After the access panel has latched close, continue to press up on the panel with
the same force used to latch the panel. Continue this pressure for 15 seconds to allow excess sealant to
squeeze out fully. Do not press up with more force than required to latch the panel or voids will be created
in the FiP gasket and the fluid leak test will fail.
(o) After closing the engine fuel shutoff valve access panel, while the FiP gasket sealant is still wet, remove
the sealant from the spaces between the edges of both the access panel and surrounding structure, except
for the sealant at the aft edge of the engine fuel shutoff valve access panel. Allow the sealant to cure.
Refer to SOPM 20-50-19 as an accepted procedure.
(p) After the sealant has cured, cycle the engine fuel shutoff valve access panel to break it free from the
sealant. If necessary, use a skin wedge to break the panel free. After cycling the panel, it should open
without assistance. Make sure that the sealant bonds to the access panel surround structure and not the
access panel. Trim excess cured sealant from door structure as required.
(q) After sealant has cured and door has been re-opened, remove and apply new parting agent. Refer to
SOPM 20-50-19 as an accepted procedure. In lieu of subsequent re-applications of parting agent every
time the door is re-opened, petrolatum that meets VV-P-236 specification or Krytox 240AC can be applied
to the panel as a post-cure lubricant. If petrolatum is applied to the panel after the sealant has cured, it
must be wiped off with a lint-free rag leaving behind a thin film. If Krytox is used, it does not have to be
wiped off.
FIGURE 4: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
31 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 32

More DataQtyIdentificationNameTaskStep
(r) Remove any sealant adhering to the access panel or excess sealant squeeze that extends into the panel
opening from the surround structure.
(s) The FiP gasket and sealant must be removed and applied again if the sealing surface on the surround
structure of the engine fuel shutoff valve access panel does not meet all the conditions that follow:
1. No structure is visible in the FiP gasket area.
2. All sealant is evenly distributed.
3. No sealant is added after the initial sealant application time expires.
4. Any small cavity or depression in the sealing surface which are less than or equal to 1/4 inch in
width, and 1/8 inch in length, are permitted if the cavities or depressions do not extend across
the full width of the sealed surface and maintain a minimum sealing surface of 1/4 inch.
5. The outboard aft corner of the gasket area is sealed and attached to the flange of the main track
rib assembly and attach strap.
(t) Remove any excess FiP gasket sealant from the notch at the aft edge of the engine fuel shutoff valve
access panel and forward of the lower skin panel.
FIGURE 4: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FORM-IN-PLACE (FIP)
GASKET REPLACEMENT
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
32 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 33

Do the following fluid leak test for the left side of the airplane:
1. Insert a 3/8 inch (9mm) inner diameter flexible plastic tube attached to a funnel into the space between
the engine fuel shutoff valve access panel and internal structure(s). Use one of the two options that
follow:
a. Option 1
(1) If closed, open engine fuel shutoff valve access panel (521BB). Refer to 737-600/700/800/900
AMM 57-41-02 as an accepted procedure.
(2) Insert plastic tube between the space in the slats and the leading edge, and thru the lightening
hole of the leading edge nose beam. Refer to Figure A.1 as an aid illustration.
NOTE: Make sure there is a minimum 2 feet of tubing from the funnel to either the leading
edge nose beam or the main track rib assembly.
b. Option 2
(1) If closed, open engine fuel shutoff valve access panel (521BB). Refer to 737-600/700/800/900
AMM 57-41-02 as an accepted procedure.
(2) If installed, remove and keep lower leading edge access panel - slat station 53.95 (521CB).
Refer to 737-600/700/800/900 AMM 57-41-02 as an accepted procedure.
(3) Insert plastic tube into lower leading edge access panel - slat station 53.95 (521CB) and thru
the space between the thermal anti-icing duct and the hole in the main track rib assembly.
Refer to Figure A.2 as an aid illustration.
NOTE: Make sure there is a minimum 2 feet of tubing from the funnel to either the leading
edge nose beam or the main track rib assembly.
APPENDIX A:  LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 1 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
33 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 34 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
SLAT STA  53.95
36.02
WATER
LEADING EDGE
NOSE BEAM
SLAT STA
36.02
PLASTIC
TUBE
FUNNEL  SLAT STA
53.95
ANTI-ICING DUCT
MAIN TRACK
RIB ASSEMBLY
FIGURE A.1
ENGINE FUEL SHUTOFF VALVE AND LOWER  LEADING EDGE-SLAT STA 53.95 ACCESS  3087797
PANELS, AND SLATS ARE NOT SHOWN
APPENDIX A: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 2 OF 5)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  34 of 42

### Page 35 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA SLAT STA  53.95
36.02
WATER
SLAT STA
36.02
PLASTIC  TUBE  • FUNNEL
SLAT STA
53.95
ANTI-ICING DUCT
MAIN TRACK
RIB ASSEMBLY
FIGURE A.2
ENGINE FUEL SHUTOFF VALVE AND LOWER  I LEADING EDGE-SLAT STA 53.95 ACCESS  3087818
PANELS, AND SLATS ARE NOT SHOWN
APPENDIX A: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 3 OF 5)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  35 of 42

### Page 36 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
2. Make sure the end of the tube is in the down and aft direction, and extends no more than 2 inches
inboard from the main track rib assembly. Refer to Figure A.3 below as an aid illustration.
SLAT STA
36.02
ENGINE FUEL SHUTOFF VALVE  SLAT STA  36.02  INBOARD EDGE OF MAIN END OF PLASTIC TUBE
ACCESS PANEL HINGE  TRACK RIB ASSEMBLY
ANTI-ICING DUCT  EDGE OF  2.00  MAX
ATTACH STRIP
FIGURE A.3
ENGINE FUEL SHUTOFF VALVE AND LOWER
LEADING EDGE-SLAT STA 53.95 ACCESS
PANELS, AND SLATS ARE NOT SHOWN
(VIEW IN THE UP DIRECTION)  3087819
A-A
APPENDIX A: LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 4 OF 5)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  36 of 42

### Page 37

3. Close engine fuel shutoff valve access panel (521BB). Refer to 737-600/700/800/900 AMM 57-41-02
as an accepted procedure.
4. Pour 32 ounces (1 liter) of water in less than 15 seconds through the funnel onto the engine fuel shutoff
valve access panel.
NOTE: It is recommended to prepare a bucket or container to catch the drained 32 ounces (1 liter)
of water from the strut drain tube.
a. If water does not drain through the strut drain tube, clean the drain path and repeat the fluid leak
test.
b. If any water leaks from the engine fuel shutoff valve access panel in less than two minutes, the
fluid leak test has failed.
c. If water drains only through the strut drain tube, and no water leaks from the engine fuel shutoff
valve access panel for more than two minutes, the fluid leak test is successful and complete.
NOTE: The fluid leak test can result in a leak from the adjacent blowout door. Refer to
737-600/700/800/900 AMM 57-41-02 as an accepted procedure to repair this leak.
APPENDIX A:  LEFT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
37 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 38

Do the following fluid leak test for the right side of the airplane:
1. Insert a 3/8 inch (9mm) inner diameter flexible plastic tube attached to a funnel into the space between
the engine fuel shutoff valve access panel and internal structure(s). Use one of the two options that
follow:
a. Option 1
(1) If closed, open engine fuel shutoff valve access panel (621BB). Refer to 737-600/700/800/900
AMM 57-41-02 as an accepted procedure.
(2) Insert plastic tube between the space in the slats and the leading edge, and thru the lightening
hole of the leading edge nose beam. Refer to Figure B.1 as an aid illustration.
NOTE: Make sure there is a minimum 2 feet of tubing from the funnel to either the leading
edge nose beam or the main track rib assembly.
b. Option 2
(1) If closed, open engine fuel shutoff valve access panel (621BB). Refer to 737-600/700/800/900
AMM 57-41-02 as an accepted procedure.
(2) If installed, remove and keep lower leading edge access panel - slat station 53.95 (621CB).
Refer to 737-600/700/800/900 AMM 57-41-02 as an accepted procedure.
(3) Insert plastic tube into lower leading edge access panel - slat station 53.95 (621CB) and thru
the space between the thermal anti-icing duct and the hole in the main track rib assembly.
Refer to Figure B.2 as an aid illustration.
NOTE: Make sure there is a minimum 2 feet of tubing from the funnel to either the leading
edge nose beam or the main track rib assembly.
APPENDIX B:  RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 1 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
38 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

### Page 39 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
53.95  SLAT STA
36.02
WATER
LEADING EDGE
NOSE BEAN
SLAT STA
36.02
PLASTIC
• TUBE
SLAT STA  FUNNEL
53.95
ANTI-ICING DUCT
MAIN TRACK
RIB ASSEMBLY
FIGURE B.1
ENGINE FUEL SHUTOFF VALVE AND LOWER  I LEADING EDGE-SLAT STA 53.95 ACCESS  3087858
PANELS, AND SLATS ARE NOT SHOWN
APPENDIX B: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 2 OF 5)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  39 of 42

### Page 40 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
SLAT STA
53.95  SLAT STA
36.02
WATER
SLAT STA
36.02
FUNNEL  PLASTIC  •TUBE
SLAT STA
53.95
ANTI-ICING DUCT
MAIN TRACK
RIB ASSEMBLY
FIGURE B.2
ENGINE FUEL SHUTOFF VALVE AND LOWER  LEADING EDGE-SLAT STA 53.95 ACCESS  3087859
PANELS, AND SLATS ARE NOT SHOWN
APPENDIX B: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 3 OF 5)
Original Issue: October 03, 2025
Export Controlled ECCN: 9E991  737-57A1359 RB
See page 1 for details  40 of 42

### Page 41 (OCR)

REQUIREMENTS BULLETIN 737-57A1359
ALERT  ALERT
2. Make sure the end of the tube is in the down and aft direction, and extends no more than 2 inches
inboard from the main track rib assembly. Refer to Figure B.3 below as an aid illustration.
SLAT STA
36.02
INBOARD EDGE OF MAIN
END OF PLASTIC TUBE  TRACK RIB ASSEMBLY  SLAT STA  ENGINE FUEL SHUTOFF VALVE
36.02  ACCESS PANEL HINGE
MAX  2.00  ANTI-ICING DUCT
EDGE OF
ATTACH STRIP
INBD
FIGURE B.3
ENGINE FUEL SHUTOFF VALVE AND LOWER
LEADING EDGE-SLAT STA 53.95 ACCESS
PANELS, AND SLATS ARE NOT SHOWN
(VIEW IN THE UP DIRECTION)  3087861
A-A
APPENDIX B: RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 4 OF 5)
Original Issue: October 03, 2025
737-57A1359 RB
Export Controlled ECCN: 9E991
See page 1 for details  41 of 42

### Page 42

3. Close engine fuel shutoff valve access panel (621BB). Refer to 737-600/700/800/900 AMM 57-41-02
as an accepted procedure.
4. Pour 32 ounces (1 liter) of water in less than 15 seconds through the funnel onto the engine fuel shutoff
valve access panel.
NOTE: It is recommended to prepare a bucket or container to catch the drained 32 ounces (1 liter)
of water from the strut drain tube.
a. If water does not drain through the strut drain tube, clean the drain path and repeat the fluid leak
test.
b. If any water leaks from the engine fuel shutoff valve access panel in less than two minutes, the
fluid leak test has failed.
c. If water drains only through the strut drain tube, and no water leaks from the engine fuel shutoff
valve access panel for more than two minutes, the fluid leak test is successful and complete.
NOTE: The fluid leak test can result in a leak from the adjacent blowout door. Refer to
737-600/700/800/900 AMM 57-41-02 as an accepted procedure to repair this leak.
APPENDIX B:  RIGHT WING - ENGINE FUEL SHUTOFF VALVE ACCESS PANEL - FLUID LEAK TEST
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: October 03, 2025
737-57A1359 RB
42 of 42
REQUIREMENTS BULLETIN 737-57A1359
ALERTALERT

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.