# Boeing Alert Requirements Bulletin 747-53A2909 RB: No revision named

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- Title as filed: 747-53A2909-00 RB
- Pages: 41
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### Page 1

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Unpublished Work.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
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5.0

### Page 2

Export Controlled ECCN: 9E991
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Original Issue: September 21, 2022
747-53A2909 RB
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REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT
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Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
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 INSPECTION . . . . . . . . . . . . . . . . . . . 30
FIGURE 12: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17R TO S-25R - DETAILED
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
FIGURE 22: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION . . . . . . . . . . . . . . . . . . . 38
Export Controlled ECCN: 9E991
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Original Issue: September 21, 2022
747-53A2909 RB
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REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 4

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

### Page 5

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.
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Original Issue: September 21, 2022
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### Page 6

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 Compli-
ance Time (Whichever Occurs
Later)
ActionCondition
-Within 30 months
after the original
issue date of Re-
quirements Bul-
letin 747-
53A2909 RB.
Before 4,000 total
flight cycles, or
within 8 years af-
ter the date of is-
suance of the
original certificate
of airworthiness
or the original ex-
port 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
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Original Issue: September 21, 2022
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REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 7

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 Compli-
ance 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 Frequen-
cy Eddy Current (HFEC) in-
spection 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 in-
spection 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 fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
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Original Issue: September 21, 2022
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REQUIREMENTS BULLETIN 747-53A2909
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### Page 8

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 Compli-
ance 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

### Page 9

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 Compli-
ance Time (Whichever Occurs
Later)
ActionCondition
-Within 30 months
after the original
issue date of Re-
quirements Bul-
letin 747-
53A2909 RB.
Before 4,000 total
flight cycles, or
within 8 years af-
ter the date of is-
suance of the
original certificate
of airworthiness
or the original ex-
port 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 Frequen-
cy Eddy Current (HFEC) in-
spection 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
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### Page 10

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 Compli-
ance 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 in-
spection 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 fas-
tener holes of the skin com-
mon 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

### Page 11

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 Compli-
ance 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 in-
spection 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 fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
Export Controlled ECCN: 9E991
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Original Issue: September 21, 2022
747-53A2909 RB
11 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 12

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 Compli-
ance 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
ALERTALERT

### Page 13

Table 4: 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 Compli-
ance 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-17R to
S-25R from STA 2285 to STA
2300 Main Entry Door #5
cutout aft edge frame for any
crack. (a)
All airplanes
-Before further flight.CONDITION 9 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 9: ANY
CRACK FOUND
4,000 flight cycles
or 8 years,
whichever occurs
first.
-CONDITION 9 (ACTION 2):
Repeat the 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. (a)
4,000 flight cycles
or 8 years,
whichever occurs
first.
-CONDITION 10 (OPTION 1):
Repeat the 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. (a)
CONDITION 10: NO
CRACK FOUND
-Within 4,000 flight cycles or 8 years,
whichever occurs first.
CONDITION 10 (OPTION 2)
(ACTION 1): Do a detailed in-
spection 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 10 (OPTION 2)
(ACTION 2): Do an open hole
High Frequency Eddy Current
(HFEC) inspection of the fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
Export Controlled ECCN: 9E991
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Original Issue: September 21, 2022
747-53A2909 RB
13 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 14

Table 4: 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 Compli-
ance Time (Whichever Occurs
Later)
ActionCondition
-Before further flight.CONDITION 10.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 10.1:
ANY CRACK
FOUND AS A RE-
SULT OF OPTION 2
INSPECTIONS 4,000 flight cycles
or 8 years,
whichever occurs
first.
-CONDITION 10.1 (ACTION 2):
Repeat the 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. (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-17R to S-25R from STA
2285 to STA 2300 Main Entry
Door #5 cutout aft edge frame
for any crack. (b)
CONDITION 10.2:
NO CRACK FOUND
AS A RESULT OF
OPTION 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.
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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### Page 15

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).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
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### Page 16

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
DO NOT REMOVE STRINGER FASTENERS AND END STRINGER SPLICE
ASSEMBLIES AT TWO ADJACENT LOCATIONS, AS THIS CAN CAUSE
STRUCTURAL MISALIGNMENT. IT IS ACCEPTABLE TO REMOVE STRINGER
FASTENERS AND END STRINGER SPLICE ASSEMBLIES EVERY OTHER
STRINGER UP TO MAXIMUM OF FOUR STRINGER LOCATIONS ON EACH
SIDE OF THE AIRPLANE AT A TIME.
CAUTION
1. Requirements.
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### Page 17

Table 1: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17L to S-25L
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 1: GET ACCESS-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
-FIGURE 1
--CONDITION 1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 1: ANY
CRACK FOUND Do PART 2: CLOSE ACCESS-
--CONDITION 1 (ACTION 2):
Do the actions specified in
Table 3. (a)
Do PART 3: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - RE-
MOVAL
-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 -FIGURE 11
-FIGURE 11CONDITION 2 (ACTION 2):
Do an open hole High Frequen-
cy Eddy Current (HFEC) in-
spection of the fastener holes
of the skin common to the end
stringer splice fitting for any
crack.
--CONDITION 2.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 2.1:
ANY CRACK
FOUND Do PART 2: CLOSE ACCESS-
--CONDITION 2.1 (ACTION 2):
Do the actions specified in
Table 3. (a)
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### Page 18

Table 1: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17L to S-25L
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 4: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-Do the actions specified in
Table 3.
CONDITION 2.2: NO
CRACK FOUND
--
Do PART 2: CLOSE ACCESS-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
--
Do PART 3: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - RE-
MOVAL
-CONDITION 3 (OPTION 2)
(ACTION 1): Do a detailed in-
spection of the affected
stringer and the end stringer
splice fitting for any crack. (b) -FIGURE 11
-FIGURE 11CONDITION 3 (OPTION 2)
(ACTION 2): Do an open hole
High Frequency Eddy Current
(HFEC) inspection of the fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
--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
INSPECTION
Do PART 2: CLOSE ACCESS-
--CONDITION 3.1 (ACTION 2):
Do the actions specified in
Table 3. (a)
Do PART 4: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-Do the actions specified in
Table 3.
CONDITION 3.2: NO
CRACK FOUND AS
A RESULT OF OP-
TION 2 INSPEC-
TION --
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### Page 19

Table 1: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17L to S-25L
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
(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.
Table 2: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17R to S-25R
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 1: GET ACCESS-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
-FIGURE 12
--CONDITION 4 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 4: ANY
CRACK FOUND Do PART 2: CLOSE ACCESS-
--CONDITION 4 (ACTION 2):
Do the actions specified in
Table 4. (a)
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### Page 20

Table 2: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17R to S-25R
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 5: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - RE-
MOVAL
-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 -FIGURE 22
-FIGURE 22CONDITION 5 (ACTION 2):
Do an open hole High Frequen-
cy Eddy Current (HFEC) in-
spection of the fastener holes
of the skin common to the end
stringer splice fitting for any
crack.
--CONDITION 5.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 5.1:
ANY CRACK
FOUND Do PART 2: CLOSE ACCESS-
--CONDITION 5.1 (ACTION 2):
Do the actions specified in
Table 4. (a)
Do PART 6: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-Do the actions specified in
Table 4.
CONDITION 5.2: NO
CRACK FOUND
--
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### Page 21

Table 2: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17R to S-25R
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 2: CLOSE ACCESS-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
--
Do PART 5: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - RE-
MOVAL
-CONDITION 6 (OPTION 2)
(ACTION 1): Do a detailed in-
spection of the affected
stringer and the end stringer
splice fitting for any crack. (b) -FIGURE 22
-FIGURE 22CONDITION 6 (OPTION 2)
(ACTION 2): Do an open hole
High Frequency Eddy Current
(HFEC) inspection of the fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
--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
INSPECTION
Do PART 2: CLOSE ACCESS-
--CONDITION 6.1 (ACTION 2):
Do the actions specified in
Table 4. (a)
Do PART 6: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-Do the actions specified in
Table 4.
CONDITION 6.2: NO
CRACK FOUND AS
A RESULT OF OP-
TION 2 INSPEC-
TION --
(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.
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### Page 22

Table 3: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17L to S-25L
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 1: GET ACCESS-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
-FIGURE 1
--CONDITION 7 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 7: ANY
CRACK FOUND Do PART 2: CLOSE ACCESS-
-FIGURE 1CONDITION 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)
Do PART 2: CLOSE ACCESS-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 -FIGURE 1
Do PART 3: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - RE-
MOVAL
-CONDITION 8 (OPTION 2)
(ACTION 1): Do a detailed in-
spection of the affected
stringer and the end stringer
splice fitting for any crack. (b) -FIGURE 11
-FIGURE 11CONDITION 8 (OPTION 2)
(ACTION 2): Do an open hole
High Frequency Eddy Current
(HFEC) inspection of the fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
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### Page 23

Table 3: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17L to S-25L
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
--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
Do PART 2: CLOSE ACCESS-
Do PART 4: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-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)
-FIGURE 1
Do PART 4: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-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 -FIGURE 1
Do PART 2: CLOSE ACCESS-
(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.
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REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 24

Table 4: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17R to S-25R
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
Do PART 1: GET ACCESS-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. (a)
All airplanes
-FIGURE 12
--CONDITION 9 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 9: ANY
CRACK FOUND Do PART 2: CLOSE ACCESS-
-FIGURE 12CONDITION 9 (ACTION 2):
Repeat the 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. (a)
Do PART 2: CLOSE ACCESS-CONDITION 10 (OPTION 1):
Repeat the 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. (a)
CONDITION 10: NO
CRACK FOUND -FIGURE 12
Do PART 5: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - RE-
MOVAL
-CONDITION 10 (OPTION 2)
(ACTION 1): Do a detailed in-
spection of the affected
stringer and the end stringer
splice fitting for any crack. (b) -FIGURE 22
-FIGURE 22CONDITION 10 (OPTION 2)
(ACTION 2): Do an open hole
High Frequency Eddy Current
(HFEC) inspection of the fas-
tener holes of the skin com-
mon to the end stringer splice
fitting for any crack. (b)
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### Page 25

Table 4: Detailed Inspection of the Stringers and End Stringer Splice Assemblies Located Between STA
2285 and STA 2300, S-17R to S-25R
Refer to the listed proce-
dures in SB 747-53A2909
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of ComplianceActionCondition
--CONDITION 10.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 10.1:
ANY CRACK
FOUND AS A RE-
SULT OF OPTION 2
INSPECTIONS
Do PART 2: CLOSE ACCESS-
Do PART 6: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-CONDITION 10.1 (ACTION 2):
Repeat the 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. (a)
-FIGURE 12
Do PART 6: FASTENERS
AND END STRINGER
SPLICE ASSEMBLY - INSTAL-
LATION
-Repeat the 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. (b)
CONDITION 10.2:
NO CRACK FOUND
AS A RESULT OF
OPTION 2 INSPEC-
TIONS -FIGURE 12
Do PART 2: CLOSE ACCESS.-
(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
25 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 26 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA  STA
2300  2285
S-17
S-25  STA
2285  STA
2300
S-17L-
S-25L -
FWD
VIEW LOOKING OUTBOARD
DETAILED INSPECTION  2989003
FIGURE 1: LEFT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17L TO S-25L - DETAILED INSPECTION
(SHEET 1 OF 4)
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### Page 27

FIGURE 1: LEFT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17L TO S-25L - DETAILED INSPECTION
(SHEET 2 OF 4)
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REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 28 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
SIA
2285
DOOR STOP
SPLICE FITTING 3  END STRINGER
STRINGER (
FRAME CHORD
TAPERED  BEAR STRAP
SKIN  FILLER
2) SHIM
TYPICAL CRACK
FWD
VIEW LOOKING UP
(TYPICAL, 9 LOCATIONS)
A-A
/ DETAILED INSPECTION
2989025
FIGURE 1: LEFT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17L TO S-25L - DETAILED INSPECTION
(SHEET 3 OF 4)
Original Issue: September 21, 2022
747-53A2909 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  28 of 41

### Page 29

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for figure.
More DataQtyIdentificationNameTaskStep
(a)(b)9S-17L TO S-25LSTRINGERInspect1
(c)--SHIMInspect2
(d)9-END STRINGER
SPLICE FITTING
Inspect3
(a) Do a detailed inspection of stringers located between STA 2285 and STA 2300 and from S-17L to S-25L
for any crack. Inspect all visible areas of the stringer.
(b) If structure attached to the stringer covers an area that is inspected, it is only necessary to inspect the
area of the stringer that is visible. It is not necessary to remove structure attached to the stringer to do
the inspection.
(c) Do a detailed inspection of the end stringer splice assembly between the bear strap and the stringer for
any shim and any gap.
(d) Do a detailed inspection of the end stringer splice fitting located at each stringer between STA 2285 and
STA 2300 for any crack. Inspect all visible areas of the end stringer splice fitting.
FIGURE 1: LEFT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17L TO S-25L - DETAILED INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022
747-53A2909 RB
29 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 30 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA  STA
2300  2285
S-17
S-25  STA
2285  STA
2300
S-17L -
S-25L -
FWD
VIEW LOOKING OUTBOARD
FIGURE 11: LEFT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 1 OF 4)
Original Issue: September 21, 2022
Export Controlled ECCN: 9E991  747-53A2909 RB
Copyright © Unpublished Work - See page 1 for details.  30 of 41

### Page 31 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA  STA
2300  BEAR STRAP  2285
STRINGER  SKIN FLANGE  STRINGER  -WD  FRAME CHORD
DETAILED INSPECTION
VIEW LOOKING OUTBOARD
(TYPICAL, 9 LOCATIONS)
2989071
FIGURE 11: LEFT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 2 OF 4)
Original Issue: September 21, 2022
Export Controlled ECCN: 9E991  747-53A2909 RB
Copyright © Unpublished Work - See page 1 for details.  31 of 41

### Page 32 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
DOOR STOP
END STRINGER
SPLICE FITTING
STRINGER
FRAME CHORD
TYPICAL
SKIN  CRACK  TYPICAL  CRACK  TAPERED  2) FASTENER  HOLES  BEAR STRAP
FILLER
FASTENER
HOLES
B
D
FWD
DETAILED INSPECTION
VIEW LOOKING UP
(TYPICAL, 9 LOCATIONS)
A-A
3009502
FIGURE 11: LEFT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 3 OF 4)
Original Issue: September 21, 2022
Export Controlled ECCN: 9E991  747-53A2909 RB
Copyright © Unpublished Work - See page 1 for details.  32 of 41

### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for figure.
More DataQtyIdentificationNameTaskStep
(a)1-STRINGERInspect1
(b)--FASTENER HOLESInspect2
(c)--END STRINGER
SPLICE FITTING
Inspect3
(a) Do a detailed inspection of the stringer at the stringer end assembly for any crack. Inspect around the
stringer fastener holes and the stringer fillet radius in the area of the removed end stringer splice fitting
and door stop.
(b) Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin within
the footprint of the end stringer splice fitting common to the stringer. Inspect the fastener holes in accor-
dance with 747 NDT Manual Part 6, 51-00-00, Procedure 16.
(c) Do a detailed inspection of the end stringer splice fitting. Inspect all surfaces.
FIGURE 11: LEFT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022
747-53A2909 RB
33 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 34 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA  STA
2285  2300
• S-17
STA  • S-25
STA  2285
2300
- - S-17R
= -S-25R
FWD
VIEW LOOKING OUTBOARD
DETAILED INSPECTION  2989573
FIGURE 12: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17R TO S-25R - DETAILED INSPECTION
(SHEET 1 OF 4)
Original Issue: September 21, 2022
747-53A2909 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  34 of 41

### Page 35

FIGURE 12: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17R TO S-25R - DETAILED INSPECTION
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022
747-53A2909 RB
35 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 36 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA
2285
DOOR STOP
(3) SPLICE FITTING  END STRINGER
1) STRINGER
FRAME CHORD
BEAR STRAP  SHIM (  TAPERED  FILLER  SKIN
TYPICAL CRACK
FWD
VIEW LOOKING UP
(TYPICAL, 9 LOCATIONS)
A-A
DETAILED INSPECTION  2989575
FIGURE 12: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17R TO S-25R - DETAILED INSPECTION
(SHEET 3 OF 4)
Original Issue: September 21, 2022
747-53A2909 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  36 of 41

### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for figure.
More DataQtyIdentificationNameTaskStep
(a)(b)9S-17R TO S-25RSTRINGERInspect1
(c)--SHIMInspect2
(d)9-END STRINGER
SPLICE FITTING
Inspect3
(a) Do a detailed inspection of stringers located between STA 2285 and STA 2300 and from S-17R to S-25R
for any crack. Inspect all visible areas of the stringer.
(b) If structure attached to the stringer covers an area that is inspected, it is only necessary to inspect the
area of the stringer that is visible. It is not necessary to remove structure attached to the stringer to do
the inspection.
(c) Do a detailed inspection of the end stringer splice assembly between the bear strap and the stringer for
any shim and any gap.
(d) Do a detailed inspection of the end stringer splice fitting located at each stringer between STA 2285 and
STA 2300 for any crack. Inspect all visible areas of the end stringer splice fitting.
FIGURE 12: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGERS S-17R TO S-25R - DETAILED INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022
747-53A2909 RB
37 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

### Page 38 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA
2300
'S-17
STA  S-25
STA  2285
2300
- S-17R
= -S-25R
FWD
VIEW LOOKING OUTBOARD
2989576
FIGURE 22: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 1 OF 4)
Original Issue: September 21, 2022
Export Controlled ECCN: 9E991  747-53A2909 RB
Copyright © Unpublished Work - See page 1 for details.  38 of 41

### Page 39 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA  STA
2285  BEAR STRAP  2300
FRAME CHORD  STRINGER  STRINGER
SKIN FLANGE
DETAILED INSPECTION
VIEW LOOKING OUTBOARD
(TYPICAL, 9 LOCATIONS)
2989577
FIGURE 22: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 2 OF 4)
Original Issue: September 21, 2022
Export Controlled ECCN: 9E991  747-53A2909 RB
Copyright © Unpublished Work - See page 1 for details.  39 of 41

### Page 40 (OCR)

REQUIREMENTS BULLETIN 747-53A2909
ALERT  ALERT
STA
2285
DOOR STOP
3) SPLICE FITTING  END STRINGER
1 STRINGER
FRAME CHORD
TYPICAL
BEAR STRAP  FASTENER 2  CRACK  TYPICAL SKIN
HOLES  TAPERED  CRACK
FILLER
2 FASTENER  HOLES
FWD
VIEW LOOKING UP
(TYPICAL, 9 LOCATIONS)
A-A
DETAILED INSPECTION
3009503
FIGURE 22: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 3 OF 4)
Original Issue: September 21, 2022
747-53A2909 RB
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.  40 of 41

### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for figure.
More DataQtyIdentificationNameTaskStep
(a)1-STRINGERInspect1
(b)--FASTENER HOLESInspect2
(c)--END STRINGER
SPLICE FITTING
Inspect3
(a) Do a detailed inspection of the stringer at the stringer end assembly for any crack. Inspect around the
stringer fastener holes and the stringer fillet radius in the area of the removed end stringer splice fitting
and door stop.
(b) Do an open hole High Frequency Eddy Current (HFEC) inspection of the fastener holes of the skin within
the footprint of the end stringer splice fitting common to the stringer. Inspect the fastener holes in accor-
dance with 747 NDT Manual Part 6, 51-00-00, Procedure 16.
(c) Do a detailed inspection of the end stringer splice fitting. Inspect all surfaces.
FIGURE 22: RIGHT SIDE - STA 2285 TO STA 2300 - STRINGER AND END STRINGER SPLICE - DETAILED
INSPECTION AND OPEN HOLE HFEC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 21, 2022
747-53A2909 RB
41 of 41
REQUIREMENTS BULLETIN 747-53A2909
ALERTALERT

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