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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2907 RB Original Issue: March 03, 2022 ATA System: 5312 SUBJECT: FUSELAGE STRUCTURE - Center Section - Stringers at Stringer Splice at STA 1000, STA 1140, STA 1660, STA 1740, STA 1960, and STA 2180 - 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:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET 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Unpublished Work.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: March 03, 2022 747-53A2907 RB 1 of 243
4.0
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Original Issue: March 03, 2022 747-53A2907 RB 2 of 243 REQUIREMENTS BULLETIN 747-53A2907
ALERTALERT
BLANK PAGE
Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected6
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL14
5. ACCOMPLISHMENT INSTRUCTIONS15
A. General Information15
B. Work Instructions16
FIGURE 1: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L
AT STA 2180 - GENERAL VISUAL INSPECTION [Group 1]25
FIGURE 3: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 1 OPTION 1 [Group 1]
.38
FIGURE 4: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 1 OPTION 2 [Group 1]
.46
FIGURE 5: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L
AT STA 2180 - RADIUS FILLER INSTALLATION [Group 1]54
FIGURE 6: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L
AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 2 [Group 1]68
FIGURE 7: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO
S-12R AT STA 2180 - GENERAL VISUAL INSPECTION [Group 1]76
FIGURE 9: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 3 OPTION 3 [Group
1]89
FIGURE 10: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 3 OPTION 4 [Group
1]97
FIGURE 11: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO
S-12R AT STA 2180 - RADIUS FILLER INSTALLATION [Group 1]105
FIGURE 12: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 4 [Group 1] . 119 FIGURE 13: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - GENERAL VISUAL INSPECTION [Group 2]
.127
FIGURE 15: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION -
CONDITION 5 OPTION 5 [Group 2]141
FIGURE 16: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION -
CONDITION 5 OPTION 6 [Group 2]150
FIGURE 17: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - RADIUS FILLER INSTALLATION [Group 2]
.159
FIGURE 18: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION -
CONDITION 6 [Group 2]174
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FIGURE 19: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - GENERAL
VISUAL INSPECTION [Group 2]183
FIGURE 21: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER
DETAILED INSPECTION - CONDITION 7 OPTION 7 [Group 2]198
FIGURE 22: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER
DETAILED INSPECTION - CONDITION 7 OPTION 8 [Group 2]208
FIGURE 23: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - RADIUS
FILLER INSTALLATION [Group 2]218
FIGURE 24: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER
DETAILED INSPECTION - CONDITION 8 [Group 2]234
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Original Issue: March 03, 2022 747-53A2907 RB 4 of 243 REQUIREMENTS BULLETIN 747-53A2907
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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2907 RB Original Issue: March 03, 2022 ATA System: 5312 SUBJECT: FUSELAGE STRUCTURE - Center Section - Stringers at Stringer Splice at STA 1000, STA 1140, STA 1660, STA 1740, STA 1960, and STA 2180 - 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, 747-8F Airplane(s), line number(s) 1420-1563 in 2 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 747-8 Airplanes.- 1 747-8F Airplanes.- 2 Airplane Models:
747-8, 747-8F GroupVariable Number 1RC001 - RC009 1RC021 - RC040 1RC051 - RC060 1RC066 - RC072 1RC076 - RC077 GroupVariable Number 2RC501 - RC514 2RC521 - RC528 2RC531 - RC541 2RC546 - RC566 2RC571 - RC582 GroupVariable Number 2RC601 - RC610 2RC641 - RC644 2RC651 - RC652 2RC661 2RC671 - RC674 Export Controlled ECCN: 9E991
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GroupVariable Number 2RC681 - RC689 GroupVariable Number -- GroupVariable Number -- 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 747-53A2907 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2907 RB mandatory.
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.
Group 1:
Accomplish the required action(s), based on the applicable condition(s) in Table 1 and Table 2 in accordance with Paragraph 3. Accomplishment Instructions.
Group 2:
Accomplish the required action(s), based on the applicable condition(s) in Table 3 and Table 4 in accordance with Paragraph 3. Accomplishment Instructions.
Group 1:
Table 1: Stringer Splice Inspection of Stringers S-8L to S-16L at STA 1740, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Requirements Bulletin 747-53A2907 RB.
Before 12,000 total flights cycles.
Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
All Airplanes.
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Group 1:
Table 1: Stringer Splice Inspection of Stringers S-8L to S-16L at STA 1740, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 1 (ACTION 1): Remove radius fillers at each free flange of the stringer with two or more fastener locations.
CONDITION 1:
FOUND TWO OR
MORE RADIUS
FILLERS AT ANY
FREE FLANGE OF THE STRINGER. Before further flight.OPTION 1 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
Before further flight.OPTION 2: Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
-Before further flight.CONDITION 1.1 (ACTION 1):
Contact the Boeing Company for repair instructions and do the repair.
CONDITION 1.1: ANY
CRACK FOUND AS
A RESULT OF OP- TION 1 INSPECTION.
-Within 9,600 flight cycles after the last detailed inspection.
CONDITION 1.1 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Before further flight.CONDITION 1.2 (ACTION 1):
Install radius fillers.
CONDITION 1.2: NO
CRACK FOUND AS
A RESULT OF OP- TION 1 INSPECTION. -.Within 9,600 flight cycles after thelast detailed inspection.CONDITION 1.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Before further flight.CONDITION 1.3 (ACTION 1):
Contact the Boeing Company for repair instructions and do the repair.
CONDITION 1.3: ANY
CRACK FOUND AS
A RESULT OF OP- TION 2 INSPECTION.
-Within 4,600 flight cycles after the last detailed inspection.
CONDITION 1.3 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
Export Controlled ECCN: 9E991
BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 03, 2022 747-53A2907 RB 7 of 243 REQUIREMENTS BULLETIN 747-53A2907
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Group 1:
Table 1: Stringer Splice Inspection of Stringers S-8L to S-16L at STA 1740, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection.
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
CONDITION 1.4: NO
CRACK FOUND AS
A RESULT OF OP- TION 2 INSPECTION.
-Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
CONDITION 2:
FOUND NO MORE
THAN ONE RADIUS
FILLER AT ANY
FREE FLANGE OF THE STRINGER.
-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.
-Within 9,600 flight cycles after the last detailed inspection.
CONDITION 2.1 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Within 9,600 flight cycles after the last detailed inspection.
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
CONDITION 2.2: NO CRACK FOUND.
Group 1:
Table 2: Stringer Splice Inspection of Stringers S-8R to S-16R at STA 1740, S-1R to S-12R at STA 1960 and S-1R to S-12R at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Requirements Bulletin 747-53A2907 RB.
Before 12,000 total flights cycles.
Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
All Airplanes.
Export Controlled ECCN: 9E991
BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 03, 2022 747-53A2907 RB 8 of 243 REQUIREMENTS BULLETIN 747-53A2907
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Group 1:
Table 2: Stringer Splice Inspection of Stringers S-8R to S-16R at STA 1740, S-1R to S-12R at STA 1960 and S-1R to S-12R at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 3 (ACTION 1): Remove radius fillers at each free flange of the stringer with two or more fastener locations.
CONDITION 3:
FOUND TWO OR
MORE RADIUS
FILLERS AT ANY
FREE FLANGE OF THE STRINGER. Before further flight.OPTION 3 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
Before further flight.OPTION 4: Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
-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 RESULT OF OP- TION 3 INSPECTION.
-Within 9,600 flight cycles after the last detailed inspection.
CONDITION 3.1 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Before further flight.CONDITION 3.2 (ACTION 1):
Install radius fillers.
CONDITION 3.2: NO
CRACK FOUND AS
A RESULT OF OP- TION 3 INSPECTION. -Within 9,600 flight cycles after thelast detailed inspection.CONDITION 3.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Before further flight.CONDITION 3.3 (ACTION 1):
Contact the Boeing Company for repair instructions and do the repair.
CONDITION 3.3: ANY
CRACK FOUND AS
A RESULT OF OP- TION 4 INSPECTION.
-Within 4,600 flight cycles after the last detailed inspection.
CONDITION 3.3 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
Export Controlled ECCN: 9E991
BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 03, 2022 747-53A2907 RB 9 of 243 REQUIREMENTS BULLETIN 747-53A2907
ALERTALERT
Group 1:
Table 2: Stringer Splice Inspection of Stringers S-8R to S-16R at STA 1740, S-1R to S-12R at STA 1960 and S-1R to S-12R at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection.
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
CONDITION 3.4: NO
CRACK FOUND AS
A RESULT OF OP- TION 4 INSPECTION.
-Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
CONDITION 4:
FOUND NO MORE
THAN ONE RADIUS
FILLER AT ANY
FREE FLANGE OF THE STRINGER.
-Before further flight.CONDITION 4.1 (ACTION 1):
Contact the Boeing Company for repair instructions and do the repair.
CONDITION 4.1: ANY CRACK FOUND.
-Within 9,600 flight cycles after the last detailed inspection.
CONDITION 4.1 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Within 9,600 flight cycles after the last detailed inspection.
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
CONDITION 4.2: NO CRACK FOUND.
Group 2:
Table 3: Stringer Splice Inspection of Stringers S-7L to S-12L at STA 1000, S-13L to S-16L at STA 1140, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Requirements Bulletin 747-53A2907 RB.
Before 12,000 total flights cycles.
Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
All Airplanes.
Export Controlled ECCN: 9E991
BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 03, 2022 747-53A2907 RB 10 of 243 REQUIREMENTS BULLETIN 747-53A2907
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Group 2:
Table 3: Stringer Splice Inspection of Stringers S-7L to S-12L at STA 1000, S-13L to S-16L at STA 1140, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 5 (ACTION 1): Remove radius fillers at each free flange of the stringer with two or more fastener locations.
CONDITION 5:
FOUND TWO OR
MORE RADIUS
FILLERS AT ANY
FREE FLANGE OF THE STRINGER. Before further flight.OPTION 5 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
Before further flight.OPTION 6: Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation 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 AS
A RESULT OF OP- TION 5 INSPECTION.
-Within 9,600 flight cycles after the last detailed inspection.
CONDITION 5.1 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Before further flight.CONDITION 5.2 (ACTION 1):
Install radius fillers.
CONDITION 5.2: NO
CRACK FOUND AS
A RESULT OF OP- TION 5 INSPECTION. -Within 9,600 flight cycles after thelast detailed inspection.CONDITION 5.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Before further flight.CONDITION 5.3 (ACTION 1):
Contact the Boeing Company for repair instructions and do the repair.
CONDITION 5.3: ANY
CRACK FOUND AS
A RESULT OF OP- TION 6 INSPECTION.
-.Within 4,600 flight cycles after the last detailed inspection.
CONDITION 5.3 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
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Group 2:
Table 3: Stringer Splice Inspection of Stringers S-7L to S-12L at STA 1000, S-13L to S-16L at STA 1140, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection.
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
CONDITION 5.4: NO
CRACK FOUND AS
A RESULT OF OP- TION 6 INSPECTION.
-Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
CONDITION 6:
FOUND NO MORE
THAN ONE RADIUS
FILLER AT ANY
FREE FLANGE OF THE STRINGER.
-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.
-.Within 9,600 flight cycles after the last detailed inspection.
CONDITION 6.1 (ACTION 2):
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
-Within 9,600 flight cycles after the last detailed inspection.
Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
CONDITION 6.2: NO CRACK FOUND.
Group 2:
Table 4: Stringer Splice Inspection of Stringers S-7R to S-12R at STA 1000, S-13R to S-16R at STA 1140, S-7R to S-11R at STA 1660, S-1R to S-12R at STA 1960 and S-1R to S-12R at STA 2180.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Requirements Bulletin 747-53A2907 RB.
Before 12,000 total flights cycles.
Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations.
All Airplanes.
Export Controlled ECCN: 9E991
BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 03, 2022 747-53A2907 RB 12 of 243 REQUIREMENTS BULLETIN 747-53A2907