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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2899 RB Original Issue: April 05, 2019 ATA System: 5313 SUBJECT: FUSELAGE - Tail Section - Body Station 2598 Bulkhead Left Side and Right Side Upper Splice Fitting 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 © 2019 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Unpublished Work.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: April 05, 2019 747-53A2899 RB 1 of 36
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 05, 2019 747-53A2899 RB 2 of 36 REQUIREMENTS BULLETIN 747-53A2899
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected5
2. CONCURRENT REQUIREMENTS5
3. COMPLIANCE6
4. APPROVAL9
5. ACCOMPLISHMENT INSTRUCTIONS11
A. General Information11
B. Work Instructions13
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE [Group 1, 3] . . 21 FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE [Group 1, 3] . 25 FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE [Group 2] . . . 29 FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE [Group 2] . . 33 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 05, 2019 747-53A2899 RB 3 of 36 REQUIREMENTS BULLETIN 747-53A2899
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 05, 2019 747-53A2899 RB 4 of 36 REQUIREMENTS BULLETIN 747-53A2899
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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2899 RB Original Issue: April 05, 2019 ATA System: 5313 SUBJECT: FUSELAGE - Tail Section - Body Station 2598 Bulkhead Left Side and Right Side Upper Splice Fitting 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 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR Airplane(s), line number(s) 1-1419 in 3 Group(s).
DESCRIPTIONCONFIGURATIONGROUP 747-100/-100B/-100B SUD /-200B/-200C/-200F/-300/-400/-400D/-400F/ 747SR airplanes that have upper splice fittings 65B02539 -1/-2 or -3/-4 or -11/-12 installed.
-1 747-400/ 747SP airplanes that have upper splice fittings 65B02539 -1/-2 or -3/-4 or -11/-12 installed.
-2 747-400/-400F airplanes that have upper splice fittings 65B02539 -7/-8 installed.
-3 B. Spares Affected None.
2. CONCURRENT REQUIREMENTS None.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 05, 2019 747-53A2899 RB 5 of 36
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 747-53A2899 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2899 RB mandatory.
Accomplish the required actions, based on the applicable condition in Tables 1, 2, 3, and 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.
Group 1, 3:
Table 1: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Left Upper Splice Fitting at the STA 2598 Bulkhead Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs later) ActionCondition -Within 2,000 flight cycles after the original issue date of Requirements Bulletin 747- 53A2899 RB.
Before 20,000 total flight cycles.
Do a detailed inspection and open hole HFEC inspection of the left upper splice fitting at the STA 2598 bulkhead for any crack.
All Airplanes.
3,000 flight cycles-Repeat the detailed inspection and open hole HFEC inspection of the left upper splice fitting at the STA 2598 bulkhead for any crack.
CONDITION 1:
NO CRACK FOUND.
-Before further flight.CONDITION 2 (ACTION 1):CONDITION 2:
Contact The Boeing Company for repair instructions, and do the repair.
ANY CRACK FOUND.
3,000 flight cycles-CONDITION 2 (ACTION 2):
Repeat the detailed inspection and open hole HFEC inspection of the left upper splice fitting at the STA 2598 bulkhead for any crack.
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Original Issue: April 05, 2019 747-53A2899 RB 6 of 36 REQUIREMENTS BULLETIN 747-53A2899
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Group 1, 3:
Table 2: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Right Upper Splice Fitting at the STA 2598 Bulkhead Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs later) ActionCondition -Within 2,000 flight cycles after the original issue date of Requirements Bulletin 747- 53A2899 RB.
Before 20,000 total flight cycles.
Do a detailed inspection and open hole HFEC inspection of the right upper splice fitting at the STA 2598 bulkhead for any crack.
All Airplanes.
3,000 flight cycles-Repeat the detailed inspection and open hole HFEC inspection of the right upper splice fitting at the STA 2598 bulkhead for any crack.
CONDITION 3:
NO CRACK FOUND.
-Before further flight.CONDITION 4 (ACTION 1):CONDITION 4:
Contact The Boeing Company for repair instructions, and do the repair.
ANY CRACK FOUND.
3,000 flight cycles-CONDITION 4 (ACTION 2):
Repeat the detailed inspection and open hole HFEC inspection of the right upper splice fitting at the STA 2598 bulkhead for any crack.
Group 2:
Table 3: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Left Upper Splice Fitting at the STA 2598 Bulkhead Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs later) ActionCondition -Within 1,500 flight cycles after the original issue date of Requirements Bulletin 747- 53A2899 RB.
Before 12,000 total flight cycles.
Do a detailed inspection and open hole HFEC inspection of the left upper splice fitting at the STA 2598 bulkhead for any crack.
All Airplanes.
1,500 flight cycles.-Repeat the detailed inspection and open hole HFEC inspection of the left upper splice fitting at the STA 2598 bulkhead for any crack.
CONDITION 5:
NO CRACK FOUND.
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Original Issue: April 05, 2019 747-53A2899 RB 7 of 36 REQUIREMENTS BULLETIN 747-53A2899
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Group 2:
Table 3: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Left Upper Splice Fitting at the STA 2598 Bulkhead Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs later) ActionCondition -Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Contact The Boeing Company for repair instructions, and do the repair.
ANY CRACK FOUND.
1,500 flight cycles.-CONDITION 6 (ACTION 2):
Repeat the detailed inspection and open hole HFEC inspection of the left upper splice fitting at the STA 2598 bulkhead for any crack.
Group 2:
Table 4: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Right Upper Splice Fitting at the STA 2598 Bulkhead Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs later) ActionCondition -Within 1,500 flight cycles after the original issue date of Requirements Bulletin 747- 53A2899 RB.
Before 12,000 total flight cycles.
Do a detailed inspection and open hole HFEC inspection of the right upper splice fitting at the STA 2598 bulkhead for any crack.
All Airplanes.
1,500 flight cycles.-Repeat the detailed inspection and open hole HFEC inspection of the right upper splice fitting at the STA 2598 bulkhead for any crack.
CONDITION 7:
NO CRACK FOUND.
-Before further flight.CONDITION 8 (ACTION 1):CONDITION 8:
Contact The Boeing Company for repair instructions, and do the repair.
ANY CRACK FOUND.
1,500 flight cycles.-CONDITION 8 (ACTION 2):
Repeat the detailed inspection and open hole HFEC inspection of the right upper splice fitting at the STA 2598 bulkhead for any crack.
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Original Issue: April 05, 2019 747-53A2899 RB 8 of 36 REQUIREMENTS BULLETIN 747-53A2899
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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 for the 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 approved 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. 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 747 Structural Repair Manual, Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747 Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM).
— Non-standard torque values for maintenance tasks are included in the applicable installation step.
2. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.
3. 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.
4. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.
5. 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.
6. Boeing Service Letter 747-SL-51-048, 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.
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7. The instructions in Paragraph 3.B., 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.
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. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems.
10. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information.
11. 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.
12. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
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 process 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.
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