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Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-53A0112 RB Original Issue: November 16, 2018 Revision 1: June 17, 2022 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14 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 © 2018 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Unpublished Work.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: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 1 of 90
4.0
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 2 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
1. EFFECTIVITY7
A. Airplanes7
B. Spares Affected9
2. CONCURRENT REQUIREMENTS9
3. COMPLIANCE9
4. APPROVAL43
5. ACCOMPLISHMENT INSTRUCTIONS45
A. General Information45
B. Work Instructions46
FIGURE 1: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME GENERAL VISUAL INSPECTION
.73
FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME GENERAL VISUAL
INSPECTION76
FIGURE 3: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME OPEN HOLE HFEC INSPECTION
.79
FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME OPEN HOLE HFEC
INSPECTION82
FIGURE 5: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME FASTENER RE-INSTALLATION
.85
FIGURE 6: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME FASTENER RE-INSTALLATION
.88
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 3 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 4 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
BLANK PAGE
Commercial Airplanes 757 Requirements Bulletin ALERT Revision Transmittal SheetNumber: 757-53A0112 RBOriginal Issue: November 16, 2018 Revision 1: June 17, 2022 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14 This revision includes all pages of the requirements bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2019-23-06 is related to this service bulletin.
The effective date of AD 2019-23-06 is January 13, 2020.
Effects of this Revision on airplanes on which Original Issue was previously done:
None.
REASON FOR REVISION This revision is sent to change the compliance time for Group 1 airplanes that have accomplished Service Bulletin 757-53A0108 with no crack found, but have not accomplished Service Bulletin 757-53A0112. The repeat inspection interval for Group 2 airplanes has also been changed.
These sections were changed:
- In Compliance, added new Airworthiness Directive (AD) related to this service bulletin. Changed grace period, and added and changed compliance table, initial conditions for Group 1 airplanes. Changed repeat inspection period, and added and changed compliance table, initial conditions for Group 2 airplanes. Changed compliance table, initial conditions for Group 3, Group 4 and Group 5 airplanes.
- In Work Instructions, added and changed work instruction table, initial conditions for Group 1 airplanes. Added and changed work instruction table, initial conditions for Group 2 airplanes. Changed work instruction table, initial conditions for Group 3, Group 4 and Group 5 airplanes.
- In Figure 5 and 6, updated illustrations.
Operators are suggested to review changes to the compliance times and adopt it into their maintenance program as applicable.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes.
Pages with no vertical lines have no changes.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 5 of 90
REVISION HISTORY Service BulletinService BulletinRequirement BulletinRequirement Bulletin 757-53A0112757-53A0112757-53A0112 RB757-53A0112 RB Issue DateIssue Date November 16, 2018Original Issue:November 16, 2018Original Issue:
June 17, 2022Revision 1:June 17, 2022Revision 1:
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 6 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-53A0112 RB Original Issue: November 16, 2018 Revision 1: June 17, 2022 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. Effectivity A. Airplanes This bulletin is applicable to 757-200, 757-200CB, 757-300 Airplane(s), line number(s) 1-138, 140, 142, 144-146, 148, 150-175, 177-180, 182-183, 185, 187-188, 190, 192, 194, 196, 198, 200-236, 238-257, 259-299, 301-313, 315-317, 319-321, 323-325, 327-329, 331-333, 335-339, 341-394, 396-398, 400-402, 404-406, 408-410, 412-476, 478-480, 482-484, 486-488, 490-492, 494-568, 570-572, 574-576, 578, 580, 582-624, 626-627, 629-630, 632-633, 635, 637, 639, 641, 643, 645, 647-648, 650, 652-653, 655, 657-658, 660-674, 676-678, 680-682, 684-686, 688-690, 692-727, 731-732, 735-754, 756-758, 760-762, 764, 766, 768, 770, 772-773, 775, 777, 779-812, 814, 816-822, 824-878, 880-881, 883-1050 in 5 Group(s). Where the effectivity is presented with hyphens between line numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive.
DESCRIPTIONCONFIGURATIONGROUP 757-200 and -200CB airplanes that have a long inner chord strap at the Body Station (STA) 1640 fuselage frame. Line numbers 45 and subsequent .
-1 757-200 airplanes changed to the Special Freighter (SF) configuration by the Boeing Company in accordance with Supplemental Type Certificate (STC) ST00916WI-D that have a long inner chord strap at the Body Station (STA) 1640 fuselage frame. Line numbers 50, 52, 54, 58, 63, 77-78, 81, 89-90, 93, 98, 123, 145, 160, 166, 168, 175, 179, 210-211, and 214.
-2 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 7 of 90
DESCRIPTIONCONFIGURATIONGROUP 757-300 airplanes that have a long inner chord strap at the Body Station (STA) 1640 fuselage frame.
-3 757-200 airplanes that have a short inner chord strap at the Body Station (STA) 1640 fuselage frame. Line Numbers 1-8, 12, 14-15, 17-22, 26-28, 31, and 34-44.
-4 757-200 airplanes changed to the Special Freighter (SF) configuration by the Boeing Company in accordance with Supplemental Type Certificate (STC) ST00916WI-D that have a short inner chord strap at the Body Station (STA) 1640 fuselage frame. Line numbers 9-11, 13, 16, 23-25, 29-30, and 32-33.
-5 Airplane Models:
757-200, 757-200CB, 757-300 GroupVariable Number 4NA001 - NA021 1NA022 - NA028 4NA191 1NA192 - NA199 5NA201 - NA204 4NA205 5NA206 - NA213 4NA214 2NA215 - NA236 1NA237 - NA239 1NA301 - NA305 1NA341 - NA352 1NA391 - NA399 4NA401 - NA403 1NA404 - NA408 1NA441 - NA447 4NA501 - NA504 1NA505 - NA586 4NB001 GroupVariable Number 1NB002 - NB004 1NB021 - NB023 1NB036 - NB041 1NB051 - NB053 1NB061 - NB073 1NB079 1NB131 - NB148 1NB161 - NB162 1NB166 - NB168 1NB201 - NB204 1NB221 - NB228 1NB230 1NB236 1NB239 1NB261 - NB267 1NB291 - NB299 1NB301 - NB302 1NB311 - NB312 1NB321 - NB331 GroupVariable Number 1NB421 - NB438 1NB446 1NB451 - NB454 1NB501 - NB523 1NB561 1NB571 1NB581 - NB583 1NC001 - NC033 1NC041 - NC042 1NC051 - NC052 1NC056 - NC062 1NC066 - NC084 1NC091 - NC094 1NC151 1NC161 1ND001 - ND007 1ND011 - ND059 1ND111 - ND113 1ND161 - ND199 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 8 of 90 REQUIREMENTS BULLETIN 757-53A0112
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GroupVariable Number 1ND201 - ND203 1ND221 - ND225 1ND241 - ND248 1ND301 - ND322 1ND401 1ND891 1ND895 1NE001 - NE008 1NE011 - NE088 1NE091 - NE094 1NE141 - NE150 1NE161 - NE177 1NE201 - NE204 1NE301 - NE302 1NE311 - NE325 1NJ001 - NJ004 1NJ031 - NJ032 1NJ551 - NJ555 GroupVariable Number 3NL001 - NL002 3NL006 - NL017 3NL101 - NL109 3NL141 3NL601 - NL616 1NN001 - NN002 1NN051 - NN052 1NP901 - NP904 1NT201 - NT202 1NT231 - NT234 1NT237 - NT240 1NT242 1NT245 - NT248 1NT281 - NT289 1NT341 - NT347 1NT351 - NT360 1NT371 - NT373 1NT375 - NT379 GroupVariable Number 1NT381 - NT386 1NT401 - NT409 1NT411 - NT412 1NT426 - NT427 1NT431 - NT432 1NT436 - NT438 1NT441 - NT442 1NT446 1NT701 - NT769 1NT791 - NT796 1NT861 - NT862 1NT881 - NT885 1NT901 - NT916 1NT971 - NT985 1NU031 - NU038 3NU701 - NU705 3NU721 - NU728 3NU731 - NU732 B. Spares Affected None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2019-23-06 is related to this service bulletin. The effective date of AD 2019-23-06 is January 13, 2020.
Accomplish the required action(s), based on the applicable condition(s) in Tables 1 through 10 in accordance with the Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION. When more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 9 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body Station (STA) 1640 Fuselage Frame at S-14L Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 500 flight cycles after the Revision 1 date of Requirements Bulletin 757- 53A0112 RB.
Before 20,000 total flight cycles.
Do a general visual inspection for any reinforcing repair or local frame replacement on the STA 1640 fuselage frame at the stringer S-14L intercostal area.
Airplanes with less than 32,000 total flight cycles at the Revision 1 date of Requirements Bulletin 757- 53A0112 RB that have not accomplished the inspections in accordance with the original issue of Service Bulletin 757-53A0108, the Revision 1 of Service Bulletin 757-53A0108, or the original issue of Requirements Bulletin 757- 53A0112 RB.
-Within 30 days of the Revision 1 date of Requirements Bulletin 757-53A0112 RB.
Before 32,500 total flight cycles.
Do a general visual inspection for any reinforcing repair or local frame replacement on the STA 1640 fuselage frame at the stringer S-14L intercostal area.
Airplanes with 32,000 total flight cycles or more at the Revision 1 date of Requirements Bulletin 757- 53A0112 RB that have not accomplished the inspections in accordance with the original issue of Service Bulletin 757-53A0108, the Revision 1 of Service Bulletin 757-53A0108, or the original issue of Requirements Bulletin 757- 53A0112 RB.
-Within 500 flight cycles after the Revision 1 date of Requirements Bulletin 757- 53A0112 RB not to exceed 5,600 flight cycles after the last inspection done in accordance with the Original Issue or the Revision 1 of Service Bulletin 757- 53A0108.
Within 2,900 flight cycles after the last inspection done in accordance with the original issue or the Revision 1 of Service Bulletin 757- 53A0108.
Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14L intercostal tee clip for any crack.
Airplanes with less than 39,500 total flight cycles at the Revision 1 date of Requirements Bulletin 757- 53A0112 RB that have accomplished the inspections in accordance with the original issue or the Revision 1 of Service Bulletin 757-53A0108 with no crack found and have not accomplished the inspections in the original issue of Requirements Bulletin 757- 53A0112 RB.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 10 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body Station (STA) 1640 Fuselage Frame at S-14L Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before 40,000 total flight cycles or, within 30 days of the Revision 1 date of Requirements Bulletin 757- 53A0112 RB, whichever occurs later.
Within 2,900 flight cycles after the last inspection done in accordance with the original issue or the Revision 1 of Service Bulletin 757- 53A0108.
Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14L intercostal tee clip for any crack.
Airplanes with 39,500 total flight cycles or more at the Revision 1 date of Requirements Bulletin 757- 53A0112 RB that have accomplished the inspections in accordance with the original issue or the Revision 1 of Service Bulletin 757-53A0108 with no crack found and have not accomplished the inspections in the original issue of Requirements Bulletin 757- 53A0112 RB.
-Within 12,000 flight cycles after the installation of the local frame replacement or within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
Within 16,000 flight cycles after the installation of the local frame replacement or before 50,000 total flight cycles.
Whichever occurs first.
Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14L intercostal tee clip for any crack.
Airplanes that have accomplished the inspections in accordance with the original issue or the Revision 1 of Service Bulletin 757- 53A0108 and have installed a local frame replacement in the S-14L intercostal area that is Boeing Organization Designation Authorization (ODA) approved via an FAA form 8100-9 and the frame web common to the tee clip fastener holes at stringer S-14L has been replaced.
Whichever occurs later.
--Within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable.
Airplanes that have accomplished the inspections in accordance with the original issue or the Revision 1 of Service Bulletin 757- 53A0108 and have installed a local frame replacement in the S-14L intercostal area that is not Boeing ODA approved.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 11 of 90 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body Station (STA) 1640 Fuselage Frame at S-14L Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition --Within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable.
Airplanes that have accomplished the inspections in accordance with the original issue or the Revision 1 of Service Bulletin 757- 53A0108 and have installed a reinforcing repair in the S-14L intercostal area.
--Within 12,000 flight cycles after the last Requirements Bulletin 757-53A0112 RB inspections.
Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14L intercostal tee clip for any crack.
Airplanes that have accomplished the inspections in accordance with the original issue of Requirements Bulletin 757-53A0112 RB with no crack found.
-Before further flight.Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE STRINGER S-14L INSPEC- TION AREA.
-Before further flight.Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN THE STRINGER S-14L
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA FORM 8100-9.
-Within 12,000 flight cycles after the installation of the local frame replacement or within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
Within 16,000 flight cycles after the installation of the local frame replacement or before 50,000 total flight cycles.
Whichever occurs first.
Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14L intercostal tee clip for any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN THE STRINGER S-14L
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT STRINGER S-14L HAS BEEN REPLACED. Whichever occurs later.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RBRevision 1: June 17, 2022 12 of 90 REQUIREMENTS BULLETIN 757-53A0112