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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2906 RB Original Issue: July 16, 2021 ATA System: 5300 SUBJECT: FUSELAGE STRUCTURE - Center Section - Crown Stringer Inspection and Repair 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 © 2021 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Unpublished Work.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: July 16, 2021 747-53A2906 RB 1 of 23
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected6
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL8
5. ACCOMPLISHMENT INSTRUCTIONS9
A. General Information9
B. Work Instructions10
FIGURE 1: LEFT SIDE FUSELAGE - CROWN STRINGER AT S-7L TO S-12L BETWEEN STA 740 AND
STA 1000 - DETAILED INSPECTION14
FIGURE 2: RIGHT SIDE FUSELAGE - CROWN STRINGER AT S-7R TO S-12R BETWEEN STA 740 AND
STA 1000 - DETAILED INSPECTION16
FIGURE 3: LEFT SIDE FUSELAGE - CROWN STRINGER AT S-7L TO S-12L BETWEEN STA 740 AND STA 1000 - SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . . 18 FIGURE 4: RIGHT SIDE FUSELAGE - CROWN STRINGER AT S-7R TO S-12R BETWEEN STA 740 AND STA 1000 - SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . . 21 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 16, 2021 747-53A2906 RB 3 of 23 REQUIREMENTS BULLETIN 747-53A2906
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 16, 2021 747-53A2906 RB 4 of 23 REQUIREMENTS BULLETIN 747-53A2906
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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2906 RB Original Issue: July 16, 2021 ATA System: 5300 SUBJECT: FUSELAGE STRUCTURE - Center Section - Crown Stringer Inspection and Repair
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 747-8F Airplane(s), line number(s) 1420-1433, 1436-1438, 1441-1442, 1444-1445, 1447-1448, 1450, 1452, 1454-1455, 1457-1458, 1460-1465, 1467, 1469, 1471, 1473-1474, 1476, 1478-1479, 1481-1491, 1493, 1496, 1501-1502, 1504-1505, 1516, 1520-1522, 1526, 1528, 1530, 1532-1536, 1540-1574 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.
The Variable Numbers and Group Information for the applicable airplanes is given below.
NOTE: The Variable Number table below includes all affected airplanes up to Line Number 1571.
Affected airplanes after Line Number 1571 will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet Profile Page.
DESCRIPTIONCONFIGURATIONGROUP 747-8F Airplanes.-1 Airplane Models:
747-8F Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 16, 2021 747-53A2906 RB 5 of 23
GroupVariable Number 1RC501 - RC514 1RC521 - RC528 1RC531 - RC541 1RC546 - RC566 GroupVariable Number 1RC571 - RC582 1RC601 - RC610 1RC641 - RC644 1RC651 - RC652 GroupVariable Number 1RC661 1RC671 - RC674 1RC681 - RC696 1RC701 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 747-53A2906 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2906 RB mandatory.
Accomplish the required action(s), based on the applicable conditions in Table 1 and Table 2 in accordance with 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.
Table 1: Crown Stringers Detailed Inspection for Any Crack Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,600 flight cycles or 36 months after the original issue date of Requirements Bulletin 747- 53A2906 RB, whichever occurs first.
Before 9,600 total flights cycles.
Do a detailed inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack.
All Airplanes.
9,600 flight cycles.-Repeat the detailed inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack.
CONDITION 1: NO CRACK FOUND.
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Table 1: Crown Stringers Detailed Inspection for Any Crack Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 2 (ACTION 1):CONDITION 2: ANY CRACK FOUND. Repair in accordance with Structural Repair Manual (SRM) 747-8F SRM 53-20-03.
9,600 flight cycles.-CONDITION 2 (ACTION 2):
Repeat the detailed inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack.
At the times specified in Table 2.CONDITION 2 (ACTION 3): Do the actions specified in Table
2.
Table 2: Crown Stringers Surface High Frequency Eddy Current (HFEC) Inspection for Any Crack at Repaired Areas Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,600 flight cycles or 36 months after the original issue date of Requirements Bulletin 747- 53A2906 RB, whichever occurs first.
Before 9,600 total flights cycles.
Do a surface High Frequency Eddy Current (HFEC) inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack at repaired areas. (a) Airplanes with repair(s) not done in accordance with 747- 53A2906 RB. (a) -Within 9,600 flight cycles after repair.
Do a surface HFEC inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack at repaired areas.
(a) Airplanes with repair(s) done in accordance with 747- 53A2906 RB. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Table 2: Crown Stringers Surface High Frequency Eddy Current (HFEC) Inspection for Any Crack at Repaired Areas Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition 9,600 flight cycles.-Repeat the surface HFEC inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack at repaired areas. (a) CONDITION 1: NO CRACK FOUND.
-Before further flight.CONDITION 2 (ACTION 1):CONDITION 2: ANY CRACK FOUND. Repair in accordance with Structural Repair Manual (SRM) 747-8F SRM 53-20-03.
9,600 flight cycles.-CONDITION 2 (ACTION 2):
Repeat the surface HFEC inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack at repaired areas. (a)
(a) A repaired area includes Structural Repair Manual (SRM) repairs, Boeing approved unpublished repairs, or rework accomplished during production identified in the Significant Rework Log (SRL) provided with each individual aircraft at delivery.
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 Union Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in this Requirements 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 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.
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 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.
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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. 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.
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 or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
B. WORK INSTRUCTIONS Actions Required for Compliance
1. Requirements Table 1: Crown Stringers Detailed Inspection for Any Crack Refer to the listed procedures in SB 747-53A2906 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 1: OPEN ACCESS.
-Do a detailed inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack.
All Airplanes.
-LEFT SIDE: FIGURE 1 and RIGHT SIDE: FIGURE 2.
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Table 1: Crown Stringers Detailed Inspection for Any Crack Refer to the listed procedures in SB 747-53A2906 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 2:
CLOSE ACCESS.
-Repeat the detailed inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack.
CONDITION 1: NO CRACK FOUND.
-LEFT SIDE: FIGURE 1 and RIGHT SIDE: FIGURE 2.
-747-8F SRM 53-20-03-2R-1 orCONDITION 2 (ACTION 1):CONDITION 2: ANY CRACK FOUND. 747-8F SRM 53-20-03-2R-2 orRepair in accordance with Structural Repair Manual (SRM) 747-8F SRM 53-20-03.
747-8F SRM 53-20-03-2R-3 or 747-8F SRM 53-20-03-2R-4.
Do PART 2:
CLOSE ACCESS - -LEFT SIDE: FIGURE 1CONDITION 2 (ACTION 2):
andRepeat the detailed inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack.
RIGHT SIDE: FIGURE 2.
--CONDITION 2 (ACTION 3):
Do the actions specified in Table 2.
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Table 2: Crown Stringers Surface High Frequency Eddy Current (HFEC) Inspection for Any Crack at Repaired Areas Refer to the listed procedures in SB 747-53A2906 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 1: OPEN ACCESS.
-Do a surface High Frequency Eddy Current (HFEC) inspection at repaired areas of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack. (a) Airplanes with repair(s) not done in accordance with 747- 53A2906 RB.(a) -LEFT SIDE: FIGURE 3and RIGHT SIDE: FIGURE 4.
Do PART 1: OPEN ACCESS.
-Do a surface HFEC inspection at repaired areas of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack. (a) Airplanes with repair(s) done in accordance with 747- 53A2906 RB.(a) -LEFT SIDE: FIGURE 3and RIGHT SIDE: FIGURE 4.
Do PART 2:
CLOSE ACCESS.
-Repeat the surface HFEC inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack at repaired areas. (a) CONDITION 1: NO CRACK FOUND.
-LEFT SIDE: FIGURE 3 and RIGHT SIDE: FIGURE 4.
-747-8F SRM 53-20-03-2R-1 orCONDITION 2 (ACTION 1):CONDITION 2: ANY CRACK FOUND. 747-8F SRM 53-20-03-2R-2 orRepair in accordance with Structural Repair Manual (SRM) 747-8F SRM 53-20-03.
747-8F SRM 53-20-03-2R-3 or 747-8F SRM 53-20-03-2R-4.
Do PART 2:
CLOSE ACCESS.
- -LEFT SIDE: FIGURE 3CONDITION 2 (ACTION 2):
andRepeat the surface HFEC inspection of the left and right side crown stringers located at S-7, S-8, S-9, S-10, S-11, and S-12 between STA 740 and STA 1000 for any crack at repaired areas. (a) RIGHT SIDE: FIGURE 4.
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