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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-53A1371 RB Original Issue: January 19, 2018 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Fuselage Frame Webs at Overwing Emergency Exits Between Stringer-7 and Stringer-8, Left and Right Side - Inspection 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Unpublished Work.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: January 19, 2018 737-53A1371 RB 1 of 81
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Table of Contents
1 . E F F E C T I V I T Y5
A. Airplanes5
B . S p a r e s A f f e c t e d6
2. CONCURRENT REQUIREMENTS6
3 . C O M P L I A N C E6
4. APPROVAL9
5. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 1 A. General Information ......................................... 1 1 B. Work Instructions ........................................... 1 2 FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE [Group 2, Configuration 1] ............................ 1 6 FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE [Group 2, Configuration 2] .................. 2 1 FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- RIGHT SIDE [Group 2, Configuration 1] ........................... 2 5 FIGURE 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE [Group 2, Configuration 2] .................. 3 0 FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE [Group 3, Configuration 1] ............................ 3 4 FIGURE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE [Group 3, Configuration 2] .................. 4 0 FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- RIGHT SIDE [Group 3, Configuration 1] ........................... 4 4 FIGURE 8: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE [Group 3, Configuration 2] .................. 5 0 FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE [Group 4, Configuration 1] .................. 5 4 FIGURE 10: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE [Group 4, Configuration 2] ............ 6 2 FIGURE 11: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE [Group 4, Configuration 1] .................. 6 8 FIGURE 12: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE [Group 4, Configuration 2] ........... 7 6 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-53A1371 RB Original Issue: January 19, 2018 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Fuselage Frame Webs at Overwing Emergency Exits Between Stringer-7 and Stringer-8, Left and Right Side - Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. EFFECTIVITY A. Airplanes This bulletin is applicable to all 737-100/-200/-200C/-300/-400/-500 airplanes. The Variable Numbers and Group Information for the applicable airplanes are given below.
DESCRIPTIONCONFIGURATIONGROUP 737-100/-200/-200C airplanes. Line numbers 1-291.-1 737-200/-200C airplanes.-2 737-200/-200C airplanes on which a support bracket between S-7 and S-8 for stowage bins was installed.
1 737-200/-200C airplanes on which a support bracket between S-7 and S-8 for stowage bins was not installed.
2 737-300/-500 airplanes.-3 737-300/-500 airplanes on which a support bracket between S-7 and S-8 for stowage bins was installed.
1 737-300/-500 airplanes on which a support bracket between S-7 and S-8 for stowage bins was not installed.
2 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 19, 2018 737-53A1371 RB 5 of 81
DESCRIPTIONCONFIGURATIONGROUP 737-400 airplanes.-4 737-400 airplanes on which a support bracket between S-7 and S-8 for stowage bins was installed.
1 737-400 airplanes on which a support bracket between S-7 and S-8 for stowage bins was not installed.
2 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 737-53A1371 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 737-53A1371 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 3, in accordance with the Accomplishment Instructions.
When more than one ACTION is given for a CONDITION number, do all of the ACTION numbers for that CONDITION number.
Group 1:
The Boeing Company 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, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 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:
Table 1: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and STA 639 Between S-7 and S-8, Left and Right Side Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles after the original issue date of Requirements Bulletin 737- 53A1371 RB.
Before 12,000 total flight cycles.
Do an HFEC inspection of the fuselage frame webs at STA 616 and STA 639 between S-7 and S-8, left and right side for any crack. (a) All airplanes.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 19, 2018 737-53A1371 RB 6 of 81 REQUIREMENTS BULLETIN 737-53A1371
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Group 2:
Table 1: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and STA 639 Between S-7 and S-8, Left and Right Side Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company for repair instructions and do the repair.
ANY CRACK FOUND.
6,000 flight cycles.-CONDITION 1 (ACTION 2):
Repeat an HFEC inspection of the fuselage frame webs at STA 616 and STA 639 between S-7 and S-8, left and right side for any crack. (a) 6,000 flight cycles.-Repeat an HFEC inspection of the fuselage frame webs at STA 616 and STA 639 between S-7 and S-8, left and right side for any crack. (a) CONDITION 2:
NO CRACK FOUND.
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9.
Group 3:
Table 2: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and STA 639 Between S-7 and S-8, Left and Right Side Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles after the original issue date of Requirements Bulletin 737- 53A1371 RB.
Before 12,000 total flight cycles.
Do an HFEC inspection of the fuselage frame webs at STA 616 and STA 639 between S-7 and S-8, left and right side for any crack. (a) All airplanes.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 19, 2018 737-53A1371 RB 7 of 81 REQUIREMENTS BULLETIN 737-53A1371
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Group 3:
Table 2: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and STA 639 Between S-7 and S-8, Left and Right Side Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company for repair instructions and do the repair.
ANY CRACK FOUND.
9,000 flight cycles.-CONDITION 1 (ACTION 2):
Repeat an HFEC inspection of the fuselage frame webs at STA 616 and STA 639 between S-7 and S-8, left and right side for any crack. (a) 9,000 flight cycles.-Repeat an HFEC inspection of the fuselage frame webs at STA 616 and STA 639 between S-7 and S-8, left and right side for any crack. (a) CONDITION 2:
NO CRACK FOUND.
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9.
Group 4:
Table 3: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 578, STA 601, STA 616 and STA 639 Between S-7 and S-8, Left and Right Side Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles after the original issue date of Requirements Bulletin 737- 53A1371 RB.
Before 12,000 total flight cycles.
Do an HFEC inspection of the fuselage frame webs at STA 578, STA 601, STA 616 and STA 639 between S-7 and S-8, left and right side for any crack.
(a) All airplanes.
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Original Issue: January 19, 2018 737-53A1371 RB 8 of 81 REQUIREMENTS BULLETIN 737-53A1371
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Group 4:
Table 3: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 578, STA 601, STA 616 and STA 639 Between S-7 and S-8, Left and Right Side Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company for repair instructions and do the repair.
ANY CRACK FOUND.
9,000 flight cycles.-CONDITION 1 (ACTION 2):
Repeat an HFEC inspection of the fuselage frame webs at STA 578, STA 601, STA 616 and STA 639 between S-7 and S-8, left and right side for any crack.
(a) 9,000 flight cycles.-Repeat an HFEC inspection of the fuselage frame webs at STA 578, STA 601, STA 616 and STA 639 between S-7 and S-8, left and right side for any crack.
(a) CONDITION 2:
NO CRACK FOUND.
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9.
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: January 19, 2018 737-53A1371 RB 9 of 81 REQUIREMENTS BULLETIN 737-53A1371
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5. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION NOTE: 1. 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.
2. 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.
3. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided.
4. 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.
5. 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.
6. When more than one ACTION is given for a CONDITION number, do all of the ACTION numbers for that CONDITION number.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 19, 2018 737-53A1371 RB 11 of 81 REQUIREMENTS BULLETIN 737-53A1371
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7. 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.
8. 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.
9. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
B. WORK INSTRUCTIONS Actions Required for Compliance:
1. Requirements Group 1:
The Boeing Company 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, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV.
Airplanes in Group 1 (line number 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.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 19, 2018 737-53A1371 RB 12 of 81 REQUIREMENTS BULLETIN 737-53A1371