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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-52A1180 RB Original Issue: January 24, 2020 ATA System: 5211 SUBJECT: DOORS - Forward Entry Door - Stop Fitting Assembly 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 © 2020 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Unpublished Work.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.
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected7
2. CONCURRENT REQUIREMENTS7
3. COMPLIANCE7
4. APPROVAL8
5. ACCOMPLISHMENT INSTRUCTIONS11
A. General Information11
B. Work Instructions12
FIGURE 1: FORWARD ENTRY DOOR - STOP FITTING ASSEMBLY - INSPECTION14
FIGURE 2: FORWARD ENTRY DOOR - STOP FITTING ASSEMBLY - MEASUREMENT16
FIGURE 3: FORWARD ENTRY DOOR - STOP FITTING ASSEMBLY - REMOVAL18
FIGURE 4: FORWARD ENTRY DOOR - UPPER BEAM - MODIFICATION20
FIGURE 5: FORWARD ENTRY DOOR - STOP FITTING ASSEMBLY - INSTALLATION23
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.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: 737-52A1180 RB Original Issue: January 24, 2020 ATA System: 5211 SUBJECT: DOORS - Forward Entry Door - Stop Fitting Assembly 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 737-600, 737-700, 737-700C, 737-800, 737-900 Airplane(s), line number(s) 1-1075 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.
DESCRIPTIONCONFIGURATIONGROUP 737-600/-700/-700C/-800/-900 Airplanes.-1 Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900 GroupVariable Number 1YA001 - YA099 1YA101 - YA118 1YA201 - YA210 1YA231 - YA242 1YA251 - YA256 1YA271 - YA272 GroupVariable Number 1YA291 1YA301 - YA302 1YA311 - YA314 1YA321 - YA323 1YA336 - YA340 1YA351 GroupVariable Number 1YA356 1YA366 1YA501 - YA536 1YA541 - YA551 1YA571 - YA578 1YA601 - YA615 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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GroupVariable Number 1YA621 - YA622 1YA626 - YA629 1YA635 1YA645 - YA647 1YA656 - YA657 1YA681 - YA690 1YA701 - YA706 1YA721 - YA722 1YA731 - YA734 1YA751 - YA756 1YA801 - YA803 1YA809 1YA811 - YA814 1YA831 - YA834 1YA841 - YA856 1YA881 - YA882 1YA891 - YA892 1YA961 - YA966 1YB001 - YB006 1YB101 - YB112 1YB151 - YB153 1YB161 - YB162 1YB171 - YB172 1YB181 - YB183 1YB201 - YB205 1YB271 1YB276 1YB301 - YB305 1YB501 - YB502 1YB521 1YC001 - YC028 1YC051 - YC082 1YC101 - YC104 GroupVariable Number 1YC111 - YC113 1YC121 1YC126 - YC127 1YC136 - YC141 1YC146 - YC147 1YC151 - YC156 1YC166 - YC167 1YC171 1YC301 - YC303 1YC321 - YC382 1YC391 - YC392 1YC396 1YC401 - YC414 1YC416 - YC417 1YC421 1YC426 1YC441 - YC448 1YC451 - YC455 1YC459 1YC461 - YC467 1YC471 - YC490 1YC501 - YC525 1YC571 - YC581 1YC587 - YC589 1YC591 - YC593 1YC601 - YC654 1YC681 - YC696 1YC701 - YC715 1YC720 - YC725 1YC727 - YC738 1YC751 - YC752 1YC761 - YC770 1YC781 - YC793 GroupVariable Number 1YC801 - YC882 1YC901 - YC907 1YC931 - YC932 1YC941 - YC948 1YC971 - YC976 1YC981 - YC983 1YD001 - YD005 1YD021 - YD025 1YD041 - YD054 1YD081 - YD084 1YD101 - YD107 1YD121 - YD126 1YD151 - YD153 1YD171 - YD172 1YD201 - YD203 1YD206 - YD207 1YD251 1YD301 - YD316 1YD401 - YD408 1YD501 - YD506 1YD531 - YD534 1YD541 - YD542 1YD601 - YD611 1YE001 - YE020 1YE051 1YE101 - YE109 1YE151 - YE157 1YE171 - YE172 1YE201 - YE203 1YG001 - YG042 1YG061 - YG064 1YG066 - YG083 1YG501 - YG505 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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GroupVariable Number 1YG601 - YG602 GroupVariable Number 1YJ471 GroupVariable Number 1YJ501 - YJ514 B. Spares Affected Examine your spares supply for the parts or components identified below. If any parts or components are found, refer to the Work Instructions for the recommended action.
Part Number 141A6150-1 141A6150-2 141A6100 - 678
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 737-52A1180 RB. The Airworthiness Directive will make the compliance tasks and times given in the Requirements Bulletin 737-52A1180 RB mandatory.
For airplanes which have incorporated Boeing Business Jet (BBJ) Lower Cabin Altitude Supplemental Type Certificate (STC) ST01697SE (6500 feet maximum cabin altitude in lieu of 8000 feet) as referenced in Boeing SB 737-21-1149, the flight cycle related compliance times are different from those specified in this bulletin. All initial compliance times (thresholds) specified in flight cycles must be reduced to half of those specified in this bulletin. All repeat interval compliance times specified in flight cycles must be reduced to one-quarter of those specified in this bulletin.
Accomplish the required actions, based on the applicable conditions in Table 1, 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 or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
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Table 1: Forward Entry Door Number 7 Stop Fitting Assembly Inspection Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 5,000 forward entry door flight cycles after the Original Issue date of Requirements Bulletin 737- 52A1180 RB.
Before 10,000 total flight cycles on the forward entry door.
OPTION 1:
Do a review of maintenance records of the upper aft corner door stop fitting assembly to determine part number.
(a) All Airplanes OPTION 2:
Do an inspection of the upper aft corner door stop fitting assembly to determine part number.
OPTION 3:
Do measurement of the stop fitting lug outer diameter to determine part number.
-Within 5,000 forward entry door flight cycles after the Original Issue date of Requirements Bulletin 737- 52A1180 RB.
Before 10,000 total flight cycles on the forward entry door.
Replace with Part Number 141A6104-21.
CONDITION 1:
PART NUMBER 141A6104-3 FOUND ---No further action is required.
CONDITION 2:
PART NUMBER 141A6104-3 IS
NOT FOUND
(a) A review of the maintenance or delivery records can be used if the part number of the installed aft corner door stop fitting assembly can be positively determined.
4. APPROVAL Note: The approval statement that follows is valid for all affected airplanes, except 737-700C airplanes.
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.
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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.
Note: The approval statement that follows is valid for 737-700C airplanes only.
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 for 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.
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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. 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. 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.
5. 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.
— Non-standard torque values for maintenance tasks are included in the applicable installation step.
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6. 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.
7. 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.
8. 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.
9. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.
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. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin.
B. WORK INSTRUCTIONS Actions Required for Compliance:
1. Requirements:
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