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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-53A1375 RB Original Issue: March 12, 2018 ATA System: 5313 SUBJECT: FUSELAGE - Body Station 303.9 Frame - Inspection of Frame Web and Doubler at Stringer 16 Left 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Unpublished Work.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: March 12, 2018 737-53A1375 RB 1 of 26
3.0
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 2 of 26 REQUIREMENTS BULLETIN 737-53A1375
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected6
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL10
5. ACCOMPLISHMENT INSTRUCTIONS11
A. General Information11
B. Work Instructions12
FIGURE 1: LEFT SIDE - STA 303.9 FRAME - SURFACE HFEC INSPECTIONS OF FRAME WEB AND
DOUBLER AT THE STOP FITTING AT S-16L [Group 2, Configuration 2]15
FIGURE 2: LEFT SIDE - STA 303.9 FRAME - SURFACE HFEC INSPECTIONS OF FRAME WEB AND
DOUBLER AT THE STOP FITTING AT S-16L [Group 3, Configuration 2]18
FIGURE 3: LEFT SIDE - STA 303.9 FRAME - SURFACE HFEC INSPECTIONS OF FRAME WEB AND
DOUBLER AT THE STOP FITTING AT S-16L [Group 4, Configuration 2]21
FIGURE 4: LEFT SIDE - STA 303.9 FRAME - SURFACE HFEC INSPECTIONS OF FRAME WEB AND
DOUBLER AT THE STOP FITTING AT S-16L [Group 5]24
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 3 of 26 REQUIREMENTS BULLETIN 737-53A1375
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 4 of 26 REQUIREMENTS BULLETIN 737-53A1375
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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-53A1375 RB Original Issue: March 12, 2018 ATA System: 5313 SUBJECT: FUSELAGE - Body Station 303.9 Frame - Inspection of Frame Web and Doubler at Stringer 16 Left
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. EFFECTIVITY A. Airplanes This bulletin is applicable to 737-100/200/200C/300/400/500 Airplanes, line numbers 1-3132.
DESCRIPTIONCONFIGURATIONGROUP 737-100/200/200C Airplanes, line numbers 1 thru 291.-1 737-200/300/400/500 Airplanes, line numbers 292 thru 2349 and 2351 thru 2437.
-2 Airplanes without any modification or repair installed on the STA
303.9 frame at S-16L.
1 Airplanes with doubler modification or repair installed in accordance with SB 737-53A1197.
2 Airplanes with doubler modification or repair installed on STA 303.9 frame at S-16L that was not installed in accordance with SB 737-53A1197.
3 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 5 of 26
DESCRIPTIONCONFIGURATIONGROUP All 737-200C Airplanes.-3 Airplanes without any modification or repair installed on the STA
303.9 frame at S-16L.
1 Airplanes with doubler modification or repair installed in accordance with SB 737-53A1197.
2 Airplanes with doubler modification or repair installed on STA 303.9 frame at S-16L that was not installed in accordance with SB 737-53A1197.
3 737-300/400/500 Airplanes, line numbers 2350 and 2438 thru 2765.-4 Airplanes without any modification or repair installed on the STA
303.9 frame at S-16L, or airplanes with a short doubler modification or a short doubler repair installed in accordance with SB 737-53A1188 Original Issue or Revision 1.
1 Airplanes with a long doubler modification or a long doubler repair installed in accordance with SB 737-53A1188 Revision 2 or Revision
3.
2 Airplanes with doubler modification or repair installed on STA 303.9 frame at S-16L that was not installed in accordance with SB 737-53A1188.
3 737-300/400/500 Airplanes, line numbers 2766 thru 3132.-5 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 737-53A1375 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 737-53A1375 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 4, in accordance with the Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 6 of 26 REQUIREMENTS BULLETIN 737-53A1375
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Group 1:
Boeing endorses the FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line numbers 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Group 2-4, Configuration 1:
No work is necessary.
Group 2-3, Configuration 2:
Table 1: Surface High Frequency Eddy Current (HFEC) inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles after the original issue date of Requirements Bulletin 737- 53A1375 RB.
Within 15,000 flight cycles after the installation of the modification or repair in accordance with Boeing Service Bulletin (SB) 737- 53A1197.
Do surface HFEC inspections of the STA 303.9 frame web and doubler at the stop fitting at S-16L for any crack. (a) All Airplanes -Before further flight.CONDITION 1 (ACTION
1): Contact The Boeing Company for repair instructions and do the repair.
CONDITION 1: ANY
CRACK FOUND 4,500 flight cycles.-CONDITION 1 (ACTION
2): Repeat the surface HFEC inspections of the STA 303.9 frame web and doubler at the stop fitting at S-16L for any crack. (a) 4,500 flight cycles.-Repeat the surface HFEC inspections of the STA
303.9 frame web and doubler at the stop fitting at S-16L for any crack.
(a) CONDITION 2: NO
CRACK FOUND Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 7 of 26 REQUIREMENTS BULLETIN 737-53A1375
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Group 2-3, Configuration 2:
Table 1: Surface High Frequency Eddy Current (HFEC) inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1375 RB in areas where an existing repair covers the inspection area and meets the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 737-53A1375 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 of which contains a repeat inspection program for the subject area.
Group 4, Configuration 2:
Table 2: Surface High Frequency Eddy Current (HFEC) inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles after the original issue date of Requirements Bulletin 737- 53A1375 RB.
Within 15,000 flight cycles after the installation of the modification or repair in accordance with Boeing Service Bulletin (SB) 737- 53A1188 Revision 2 or Revision 3.
Do surface HFEC inspections of the STA 303.9 frame web and doubler at the stop fitting at S-16L for any crack. (a) All Airplanes -Before further flight.CONDITION 1 (ACTION
1): Contact The Boeing Company for repair instructions and do the repair.
CONDITION 1: ANY
CRACK FOUND 12,000 flight cycles.
-CONDITION 1 (ACTION
2): Repeat the surface HFEC inspections of the STA 303.9 frame web and doubler at the stop fitting at S-16L for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Group 4, Configuration 2:
Table 2: Surface High Frequency Eddy Current (HFEC) inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 12,000 flight cycles.
-Repeat the surface HFEC inspections of the STA
303.9 frame web and doubler at the stop fitting at S-16L for any crack.
(a) CONDITION 2: NO
CRACK FOUND
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1375 RB in areas where an existing repair covers the inspection area and meets the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 737-53A1375 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 of which contains a repeat inspection program for the subject area.
Group 2-4, Configuration 3:
Table 3: Inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles after the original issue date of Requirements Bulletin 737- 53A1375 RB.
Before 15,000 total flight cycles.
Contact The Boeing Company for alternative inspection instruction and do the inspection and any corrective actions as applicable.
All Airplanes Group 5:
Table 4: Surface High Frequency Eddy Current (HFEC) inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles after the original issue date of Requirements Bulletin 737- 53A1375 RB.
Before 15,000 total flight cycles.
Do surface HFEC inspections of the STA 303.9 frame web and doubler at the stop fitting at S-16L for any crack. (a) All Airplanes Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 9 of 26 REQUIREMENTS BULLETIN 737-53A1375
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Group 5:
Table 4: Surface High Frequency Eddy Current (HFEC) inspections of the Body Station (STA) 303.9 frame web and doubler at the stop fitting at stringer 16 left (S-16L) for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 1 (ACTION
1): Contact The Boeing Company for repair instructions and do the repair.
CONDITION 1: ANY
CRACK FOUND 12,000 flight cycles.
-CONDITION 1 (ACTION
2): Repeat the surface HFEC inspections of the STA 303.9 frame web and doubler at the stop fitting at S-16L for any crack. (a) 12,000 flight cycles.
-Repeat the surface HFEC inspections of the STA
303.9 frame web and doubler at the stop fitting at S-16L for any crack.
(a) CONDITION 2: NO
CRACK FOUND
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1375 RB in areas where an existing repair covers the inspection area and meets the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 737-53A1375 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 of which contains a repeat inspection program for the subject area.
4. APPROVAL This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this document comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This document and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other Boeing changes.
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 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 10 of 26 REQUIREMENTS BULLETIN 737-53A1375
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5. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION NOTE: 6. 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.
7. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.
8. 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.
9. The instructions in the Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools.
10. 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.
11. 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.
12. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 11 of 26 REQUIREMENTS BULLETIN 737-53A1375
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13. This is an Enhanced Required for Compliance document. There will be a separate Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated by an Airworthiness Directive (AD), then all applicable requirements specified in the RB must be done. For the related SB, some locations are marked RC Start and RC End to identify the requirements that are restated from the RB. For the related SB, the areas between RC Start and RC End, including sub-steps and any figures identified between RC Start and RC End, must be done to comply with the AD.
Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations to steps between RC Start and RC End, including substeps and identified figures.
For the related SB, the steps not between RC Start and RC End may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC; this is provided that the steps between RC Start and RC End, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.
Figures not required for compliance are omitted from the RB.
14. 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.
B. WORK INSTRUCTIONS Actions Required for Compliance:
1. Requirements Group 1:
Boeing endorses the FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line numbers 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR
121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Group 2-4, Configuration 1:
No work is necessary.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 12, 2018 737-53A1375 RB 12 of 26 REQUIREMENTS BULLETIN 737-53A1375