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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2900 RB Original Issue: April 11, 2019 ATA System: 5300 SUBJECT: FUSELAGE - Section 42 - Underwing Longeron and Fuselage Skin 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Unpublished Work.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 11, 2019 747-53A2900 RB 1 of 29
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 2 of 29 REQUIREMENTS BULLETIN 747-53A2900
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected5
2. CONCURRENT REQUIREMENTS5
3. COMPLIANCE5
4. APPROVAL9
5. ACCOMPLISHMENT INSTRUCTIONS11
A. General Information11
B. Work Instructions12
FIGURE 1: LEFT SIDE - UNDERWING LONGERON FUSELAGE SKIN - DETAILED INSPECTION . 18 FIGURE 2: LEFT SIDE - FUSELAGE SKIN - ULTRASONIC AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION20
FIGURE 3: LEFT SIDE - UNDERWING LONGERON - ULTRASONIC INSPECTION22
FIGURE 4: RIGHT SIDE - UNDERWING LONGERON FUSELAGE SKIN - DETAILED INSPECTION . 24 FIGURE 5: RIGHT SIDE - FUSELAGE SKIN - ULTRASONIC AND HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION26
FIGURE 6: RIGHT SIDE - UNDERWING LONGERON - ULTRASONIC INSPECTION28
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 3 of 29 REQUIREMENTS BULLETIN 747-53A2900
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 4 of 29 REQUIREMENTS BULLETIN 747-53A2900
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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2900 RB Original Issue: April 11, 2019 ATA System: 5300 SUBJECT: FUSELAGE - Section 42 - Underwing Longeron and Fuselage Skin 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 747-400, 747-400F Airplane(s), line number(s) 1308, 1313, 1315-1419 in 1 Group(s).
B. Spares Affected None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to the Boeing Requirements Bulletin 747-53A2900 RB. The Airworthiness Directive will make the compliance tasks and times given in the Boeing Requirements Bulletin 747-53A2900 RB mandatory.
Accomplish the required action(s), based on the applicable conditions in Table 1 and Table 2, 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.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 5 of 29
TABLE 1: LEFT SIDE UNDERWING LONGERON AND FUSELAGE SKIN INSPECTIONS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 2,600 flight cycles after the original issue date of Requirements Bulletin 747- 53A2900 RB.
Before 6,600 total flight cycles.
Do a detailed inspection of the underwing longeron and the adjacent fuselage skin at STA 1000, S-38 on the left side of the airplane for any crack.
All Airplanes Do an ultrasonic and High Frequency Eddy Current (HFEC) inspection of the fuselage skin at STA 1000, S-38 on the left side of the airplane for any crack.
Do an ultrasonic inspection of the underwing longeron at STA 1000, S- 38 on the left side of the airplane for any crack.
2,600 flight cycles.-ACTION 1: Repeat the detailed inspection of the underwing longeron and the adjacent fuselage skin at STA 1000, S-38 on the left side of the airplane for any crack.
CONDITION 1:
NO CRACK FOUND -ACTION 2: Repeat the ultrasonic and High Frequency Eddy Current (HFEC) inspection of the fuselage skin at STA 1000, S-38 on the left side of the airplane for any crack.
-ACTION 3: Repeat the ultrasonic inspection of the underwing longeron at STA 1000, S-38 on the left side of the airplane for any crack.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 6 of 29 REQUIREMENTS BULLETIN 747-53A2900
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TABLE 1: LEFT SIDE UNDERWING LONGERON AND FUSELAGE SKIN INSPECTIONS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
CONDITION 2:
ANY CRACK FOUND 2,600 flight cycles.-ACTION 2: Repeat the detailed inspection of the underwing longeron and the adjacent fuselage skin at STA 1000, S-38 on the left side of the airplane for any crack.
-ACTION 3: Repeat the ultrasonic and High Frequency Eddy Current (HFEC) inspection of the fuselage skin at STA 1000, S-38 on the left side of the airplane for any crack.
-ACTION 4: Repeat the ultrasonic inspection of the underwing longeron at STA 1000, S-38 on the left side of the airplane for any crack.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 7 of 29 REQUIREMENTS BULLETIN 747-53A2900
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TABLE 2: RIGHT SIDE UNDERWING LONGERON AND FUSELAGE SKIN INSPECTIONS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 2,600 flight cycles from the release of the original issue of Requirements Bulletin 747-53A2900 RB.
Before 6,600 total flight cycles.
Do a detailed inspection of the underwing longeron and the adjacent fuselage skin at STA 1000, S-38 on the right side of the airplane for any crack.
All Airplanes Do an ultrasonic and High Frequency Eddy Current (HFEC) inspection of the fuselage skin at STA 1000, S-38 on the right side of the airplane for any crack.
Do an ultrasonic inspection of the underwing longeron at STA 1000, S- 38 on the right side of the airplane for any crack.
2,600 flight cycles.-ACTION 1: Repeat the detailed inspection of the underwing longeron and the adjacent fuselage skin at STA 1000, S-38 on the right side of the airplane for any crack.
CONDITION 3:
NO CRACK FOUND -ACTION 2: Repeat the ultrasonic and High Frequency Eddy Current (HFEC) inspection of the fuselage skin at STA 1000, S-38 on the right side of the airplane for any crack.
-ACTION 3: Repeat the ultrasonic inspection of the underwing longeron at STA 1000, S-38 on the right side of the airplane for any crack.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 8 of 29 REQUIREMENTS BULLETIN 747-53A2900
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TABLE 2: RIGHT SIDE UNDERWING LONGERON AND FUSELAGE SKIN INSPECTIONS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
CONDITION 4:
ANY CRACK FOUND 2,600 flight cycles.-ACTION 2: Repeat the detailed inspection of the underwing longeron and the adjacent fuselage skin at STA 1000, S-38 on the right side of the airplane for any crack.
-ACTION 3: Repeat the ultrasonic and High Frequency Eddy Current (HFEC) inspection of the fuselage skin at STA 1000, S-38 on the right side of the airplane for any crack.
-ACTION 4: Repeat the ultrasonic inspection of the underwing longeron at STA 1000, S-38 on the right side of the airplane for any crack.
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.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 9 of 29 REQUIREMENTS BULLETIN 747-53A2900
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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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. 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).
— Values for engine maintenance tasks are included in Chapter 70 of 747 Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the applicable installation step.
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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. 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.
7. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.
8. A Detailed Inspection is defined as: An intensive examination of a specific item, installation or assembly to detect damage, failure or irregularity. This could include tactile assessment in which a component or assembly can be checked for tightness/security. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors and magnifying lenses may be necessary. Surface cleaning and elaborate access procedures may be required.
9. 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.
10. The instructions in 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.
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
1. Requirements Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 11, 2019 747-53A2900 RB 12 of 29 REQUIREMENTS BULLETIN 747-53A2900