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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2909 RB Original Issue: September 21, 2022 ATA System: 5312 5305 SUBJECT: FUSELAGE - AFT Section - Stringers and End Stringer Splice Assemblies Between STA 2285 and STA 2300, From S-17 To S-25 Inspection EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations (EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per Supp.1 to Part 740 of the EAR.
9E991ECCN:
Copyright © 2022 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Unpublished Work.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: September 21, 2022 747-53A2909 RB 1 of 41
5.0
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 2 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
BLANK PAGE
Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected5
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL14
5. ACCOMPLISHMENT INSTRUCTIONS15
A. General Information15
B. Work Instructions16
FIGURE 1: LEFT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17L TO S-25L - DETAILED INSPECTION
.26
FIGURE 11: LEFT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION30
FIGURE 12: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17R TO S-25R - DETAILED
INSPECTION34
FIGURE 22: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION38
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 3 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 4 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
BLANK PAGE
Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2909 RB Original Issue: September 21, 2022 ATA System: 5312 5305 SUBJECT: FUSELAGE - AFT Section - Stringers and End Stringer Splice Assemblies Between STA 2285 and STA 2300, From S-17 To S-25 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 747-8 Airplane(s), line number(s) 1434-1435, 1439-1440, 1443, 1446, 1449, 1451, 1453, 1456, 1459, 1466, 1468, 1470, 1472, 1475, 1477, 1480, 1492, 1494-1495, 1497-1500, 1503, 1506-1515, 1517-1519, 1523-1525, 1527, 1529, 1531, 1537-1539 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.
DESCRIPTIONCONFIGURATIONGROUP 747-8 Airplanes.-1 Airplane Models:
747-8 GroupVariable Number 1RC001 - RC009 1RC021 - RC040 GroupVariable Number 1RC051 - RC060 1RC066 - RC072 GroupVariable Number 1RC076 - RC077 -- B. Spares Affected None.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 5 of 41
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 747-53A2909 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2909 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 and 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: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17L to S-25L Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 30 months after the original issue date of Requirements Bulletin 747- 53A2909 RB.
Before 4,000 total flight cycles, or within 8 years after the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, whichever occurs first.
Do a detailed inspection of the stringers and the end stringer splice assemblies at S-17L to S-25L from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack and any shim between stringer and bear strap and any gap within fastener joint at stringer to bear strap joint.
All airplanes -Before further flight.CONDITION 1 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 1: ANY
CRACK FOUND -At the times specified in Table 3.CONDITION 1 (ACTION 2):
Do the actions specified in Table 3. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 6 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Table 1: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17L to S-25L Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 2 (ACTION 1):
Do a detailed inspection of the affected stringer and the end stringer splice fitting for any crack.
CONDITION 2: NO
CRACK FOUND
AND ANY GAP
FOUND OR NO
SHIM FOUND -Before further flight.CONDITION 2 (ACTION 2):
Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin common to the end stringer splice fitting for any crack.
-Before further flight.CONDITION 2.1 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 2.1:
ANY CRACK FOUND -At the times specified in Table 3.CONDITION 2.1 (ACTION 2):
Do the actions specified in Table 3. (a) -At the times specified in Table 3.Do the actions specified in Table 3.
CONDITION 2.2: NO
CRACK FOUND -At the times specified in Table 3.CONDITION 3 (OPTION 1):
Do the actions specified in Table 3. (a) CONDITION 3: NO
CRACK FOUND
AND NO GAP
FOUND AND ANY SHIM FOUND -Within 4,000 flight cycles or 8 years,whichever occurs first.CONDITION 3 (OPTION 2)(ACTION 1): Do a detailed inspection of the affected stringer and the end stringer splice fitting for any crack. (b) -Within 4,000 flight cycles or 8 years, whichever occurs first.
CONDITION 3 (OPTION 2) (ACTION 2): Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin common to the end stringer splice fitting for any crack. (b) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 7 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Table 1: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17L to S-25L Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 3.1 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 3.1:
ANY CRACK
FOUND AS A RE- SULT OF OPTION 2 INSPECTIONS -At the times specified in Table 3.CONDITION 3.1 (ACTION 2):
Do the actions specified in Table 3. (a) -At the times specified in Table 3.Do the actions specified in Table 3.
CONDITION 3.2: NO
CRACK FOUND AS
A RESULT OF OP- TION 2 INSPEC- TIONS
(a) It is not required to do the detailed inspection for any crack in any affected stringer where an approved repair was accomplished at the affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2909 RB and installed after the original issue date of Requirements Bulletin 747-53A2909
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
(b) Doing the detailed and High Frequency Eddy Current (HFEC) inspections and finding no crack as a result of the inspection is terminating action to Requirements Bulletin 747-53A2909 RB for that affected end stringer splice assembly.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 8 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Table 2: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17R to S-25R Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 30 months after the original issue date of Requirements Bulletin 747- 53A2909 RB.
Before 4,000 total flight cycles, or within 8 years after the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, whichever occurs first.
Do a detailed inspection of the stringers and the end stringer splice assemblies at S-17R to S-25R from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack and any shim between stringer and bear strap and any gap within fastener joint at stringer to bear strap joint.
All airplanes -Before further flight.CONDITION 4 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 4: ANY
CRACK FOUND -At the times specified in Table 4.CONDITION 4 (ACTION 2):
Do the actions specified in Table 4. (a) -Before further flight.CONDITION 5 (ACTION 1):
Do a detailed inspection of the affected stringer and the end stringer splice fitting for any crack.
CONDITION 5: NO
CRACK FOUND
AND ANY GAP
FOUND OR NO
SHIM FOUND -Before further flight.CONDITION 5 (ACTION 2):
Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin common to the end stringer splice fitting for any crack.
-Before further flight.CONDITION 5.1 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 5.1:
ANY CRACK FOUND -At the times specified in Table 4.CONDITION 5.1 (ACTION 2):
Do the actions specified in Table 4. (a) -At the times specified in Table 4.Do the actions specified in Table 4.
CONDITION 5.2: NO
CRACK FOUND Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 9 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Table 2: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17R to S-25R Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -At the times specified in Table 4.CONDITION 6 (OPTION 1):
Do the actions specified in Table 4. (a) CONDITION 6: NO
CRACK FOUND
AND NO GAP
FOUND AND ANY SHIM FOUND -Within 4,000 flight cycles or 8 years,whichever occurs first.CONDITION 6 (OPTION 2)(ACTION 1): Do a detailed inspection of the affected stringer and the end stringer splice fitting for any crack. (b) -Within 4,000 flight cycles or 8 years, whichever occurs first.
CONDITION 6 (OPTION 2) (ACTION 2): Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin common to the end stringer splice fitting for any crack. (b) -Before further flight.CONDITION 6.1 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 6.1:
ANY CRACK
FOUND AS A RE- SULT OF OPTION 2 INSPECTIONS -At the times specified in Table 4.CONDITION 6.1 (ACTION 2):
Do the actions specified in Table 4. (a) -At the times specified in Table 4.Do the actions specified in Table 4.
CONDITION 6.2: NO
CRACK FOUND AS
A RESULT OF OP- TION 2 INSPEC- TIONS
(a) It is not required to do the detailed inspection for any crack in any affected stringer where an approved repair was accomplished at the affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2909 RB and installed after the original issue date of Requirements Bulletin 747-53A2909
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
(b) Doing the detailed and High Frequency Eddy Current (HFEC) inspections and finding no crack as a result of the inspection is terminating action to Requirements Bulletin 747-53A2909 RB for that affected end stringer splice assembly.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 10 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Table 3: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17L to S-25L Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,000 flight cycles or 8 years after the last detailed inspection was done.
Do a detailed inspection of the stringers and the end stringer splice assemblies at S-17L to S-25L from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack. (a) All airplanes -Before further flight.CONDITION 7 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 7: ANY
CRACK FOUND 4,000 flight cycles or 8 years, whichever occurs first.
-CONDITION 7 (ACTION 2):
Repeat the detailed inspection of the stringers and the end stringer splice assemblies at S-17L to S-25L from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack. (a) 4,000 flight cycles or 8 years, whichever occurs first.
-CONDITION 8 (OPTION 1):
Repeat the detailed inspection of the stringers and the end stringer splice assemblies at S-17L to S-25L from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack. (a) CONDITION 8: NO
CRACK FOUND -Within 4,000 flight cycles or 8 years, whichever occurs first.
CONDITION 8 (OPTION 2) (ACTION 1): Do a detailed inspection of the affected stringer and the end stringer splice fitting for any crack. (b) -Within 4,000 flight cycles or 8 years, whichever occurs first.
CONDITION 8 (OPTION 2) (ACTION 2): Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin common to the end stringer splice fitting for any crack. (b) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 11 of 41 REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
Table 3: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA 2285 and STA 2300, S-17L to S-25L Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 8.1 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 8.1:
ANY CRACK
FOUND AS A RE- SULT OF OPTION 2 INSPECTIONS 4,000 flight cycles or 8 years, whichever occurs first.
-CONDITION 8.1 (ACTION 2):
Repeat the detailed inspection of the stringers and the end stringer splice assemblies at S-17L to S-25L from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack. (a) 4,000 flight cycles or 8 years, whichever occurs first.
-Repeat the detailed inspection of the stringers and the end stringer splice assemblies at S-17L to S-25L from STA 2285 to STA 2300 Main Entry Door #5 cutout aft edge frame for any crack. (b) CONDITION 8.2: NO
CRACK FOUND AS
A RESULT OF OP- TION 2 INSPEC- TIONS
(a) It is not required to do the detailed inspection for any crack in any affected stringer where an approved repair was accomplished at the affected inspection zone, if the repair meets the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2909 RB and installed after the original issue date of Requirements Bulletin 747-53A2909
RB, AND
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
(b) Doing the detailed and High Frequency Eddy Current (HFEC) inspections and finding no crack as a result of the inspection is terminating action to Requirements Bulletin 747-53A2909 RB for that affected end stringer splice assembly.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022 747-53A2909 RB 12 of 41 REQUIREMENTS BULLETIN 747-53A2909