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Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-53A0112 RB Original Issue: November 16, 2018 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14 Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
Copyright © 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Unpublished Work.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 RB 1 of 76
2.0
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 2 of 76 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
BLANK PAGE
Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected6
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL37
5. ACCOMPLISHMENT INSTRUCTIONS39
A. General Information39
B. Work Instructions40
FIGURE 1: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME GENERAL VISUAL INSPECTION
.59
FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME GENERAL VISUAL
INSPECTION62
FIGURE 3: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME OPEN HOLE HFEC INSPECTION
.65
FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME OPEN HOLE HFEC
INSPECTION68
FIGURE 5: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME FASTENER RE-INSTALLATION
.71
FIGURE 6: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME FASTENER RE-INSTALLATION
.74
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 3 of 76 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 4 of 76 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
BLANK PAGE
Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-53A0112 RB Original Issue: November 16, 2018 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 RB 5 of 76
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 B. Spares Affected None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to Requirements Bulletin 757-53A0112 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 757-53A0112 RB mandatory.
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 RB 6 of 76 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 1,300 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB or before 32,500 total flight cycles.
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 original issue date of Requirements Bulletin 757- 53A0112 RB that have not accomplished inspections in accordance with the original issue of Service Bulletin 757-53A0108.
Whichever occurs first.
--Within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
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 original issue date of Requirements Bulletin 757- 53A0112 RB that have not accomplished inspections in accordance with the original issue of Service Bulletin 757-53A0108.
-Within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
Within 5,600 flight cycles after the last Service Bulletin 757- 53A0108 inspection.
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 Service Bulletin 757-53A0108 with no crack found.
-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 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.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 7 of 76 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 of Service Bulletin 757-53A0108 and have installed a local frame replacement in the S-14L intercostal area that is not Boeing ODA approved.
--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 of Service Bulletin 757-53A0108 and have installed a reinforcing repair in the S-14L intercostal area.
-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.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 8 of 76 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 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.
-Before further flight.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 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND IN THE STRINGER S-14L INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Company for repair instructions and do the repair.
ANY CRACK FOUND.
12,000-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S-14L intercostal tee clip for any crack. (a) -Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to the frame web and S-14L intercostal tee clip.
NO CRACK FOUND.
12,000-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S-14L intercostal tee clip for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 9 of 76 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
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin 757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Requirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112 RB inspections in the repair area.
Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body Station (STA) 1640 Fuselage Frame at S-14R Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,300 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB or before 32,500 total flight cycles.
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-14R intercostal area.
Airplanes with less than 32,000 total flight cycles at the original issue date of Requirements Bulletin 757- 53A0112 RB that have not accomplished inspections in accordance with the original issue of Service Bulletin 757-53A0108.
Whichever occurs first.
--Within 500 flight cycles after the original issue date of Requirements Bulletin 757-53A0112 RB.
Do a general visual inspection for any reinforcing repair or local frame replacement on the STA 1640 fuselage frame at the stringer S-14R intercostal area.
Airplanes with 32,000 total flight cycles or more at the original issue date of Requirements Bulletin 757- 53A0112 RB that have not accomplished inspections in accordance with the original issue of Service Bulletin 757-53A0108.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 10 of 76 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body Station (STA) 1640 Fuselage Frame at S-14R 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.
Within 5,600 flight cycles after the last Service Bulletin 757- 53A0108 inspection.
Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14R intercostal tee clip for any crack.
Airplanes that have accomplished the inspections in accordance with the original issue of Service Bulletin 757-53A0108 with no crack found.
-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- 14R intercostal tee clip for any crack.
Airplanes that have accomplished the inspections in accordance with the original issue of Service Bulletin 757-53A0108 and have installed a local frame replacement in the S-14R 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-14R 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 of Service Bulletin 757-53A0108 and have installed a local frame replacement in the S-14R intercostal area that is not Boeing ODA approved.
--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 of Service Bulletin 757-53A0108 and have installed a reinforcing repair in the S-14R intercostal area.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 11 of 76 REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body Station (STA) 1640 Fuselage Frame at S-14R Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -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-14R IN- SPECTION 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-14R
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- 14R intercostal tee clip for any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN THE STRINGER S-14R
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-14R HAS BEEN REPLACED. Whichever occurs later.
-Before further flight.Do an open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S- 14R intercostal tee clip for any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND IN THE STRINGER S-14R INSPECTION AREA.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018 757-53A0112 RB 12 of 76 REQUIREMENTS BULLETIN 757-53A0112