# Boeing Alert Requirements Bulletin 747-53A2913 RB: No revision named

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- Document: [Boeing Alert Requirements Bulletin 747-53A2913 RB](https://openairdocs.org/service-documents/boeing/747-53a2913-rb.md)
- Title as filed: 747-53A2913-00 RB (12)
- Pages: 22
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## Text

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### Page 1

Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-53A2913 RB
Original Issue: December 19, 2025
ATA System: 5300 5305 5312
SUBJECT: FUSELAGE - Fuselage Skin Between STA 1350 and STA 1480 at S-23L and S-23R
- Lap Splice 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 © 2025 The Boeing Company
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: December 19, 2025
747-53A2913 RB
1 of 22
3.0

### Page 2

Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
2 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
3 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
4 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-53A2913 RB
Original Issue: December 19, 2025
ATA System: 5300 5305 5312
SUBJECT: FUSELAGE - Fuselage Skin Between STA 1350 and STA 1480 at S-23L and S-23R
- Lap Splice Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
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, 1517-1518, 1524-1525, 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 Passenger Airplanes-1
Airplane Models:
747-8
GroupVariable Number
1RC001 - RC009
1RC021 - RC040
GroupVariable Number
1RC051 - RC060
1RC066 - RC072
GroupVariable Number
--
--
B. Spares Affected
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
5 of 22

### Page 6

None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 747-53A2913 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 747-53A2913 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) 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: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23L for any crack.
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Before 20,000 total flight cycles.Do an external surface HFEC
inspection of the upper fasten-
er row of the fuselage skin lap
splice for any crack.
All Airplanes.
3,600 flight cycles.-Repeat the external surface
HFEC inspection of the upper
fastener row of the fuselage
skin lap splice for any crack.
(a)
CONDITION 1: NO
CRACK FOUND
-Before further flight.CONDITION 2 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 2: ANY
CRACK FOUND
3,600 flight cycles.-CONDITION 2 (ACTION 2):
Repeat the external surface
HFEC inspection of the upper
fastener row of the fuselage
skin lap splice for any crack.
(a)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
6 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 7

Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23L for any crack.
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin
747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747-
53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913
RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Table 2: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23R for any crack.
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
ActionCondition
-Before 20,000 total flight cycles.Do an external surface HFEC
inspection of the upper fasten-
er row of the fuselage skin lap
splice for any crack.
All Airplanes.
3,600 flight cycles.-Repeat the external surface
HFEC inspection of the upper
fastener row of the fuselage
skin lap splice for any crack.
(a)
CONDITION 3: NO
CRACK FOUND
-Before further flight.CONDITION 4 (ACTION 1):
Contact The Boeing Company
for repair instructions and do
the repair.
CONDITION 4: ANY
CRACK FOUND
3,600 flight cycles.-CONDITION 4 (ACTION 2):
Repeat the external surface
HFEC inspection of the upper
fastener row of the fuselage
skin lap splice for any crack.
(a)
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin
747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747-
53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913
RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
7 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 8

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) approved for all EASA 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.
Export Controlled ECCN: 9E991
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Original Issue: December 19, 2025
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REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 9

5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF
METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE
BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES
CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION
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. In the RB, the "Refer to the listed procedures..." column of the
table(s) in the Work Instructions is for reference only. The procedures in that column
are not required by the AD and are for guidance only. For the related SB, some
locations are marked RC Start and RC End to identify the requirements that are
restated from the RB. For the related SB, the areas between RC Start and RC End,
including sub-steps and any figures identified between RC Start and RC End, must
be done to comply with the AD. Therefore, an Alternative Method of Compliance
(AMOC) is required for any deviations to steps between RC Start and RC End,
including substeps and identified figures. For the related SB, the steps not between
RC Start and RC End may be deviated from using accepted methods in accordance
with the operator's maintenance or inspection program without obtaining approval
of an AMOC; this is provided that the steps between RC Start and RC End, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition. Figures not required for compliance are omitted
from the RB.
2. This is an Enhanced Required for Compliance document. The Boeing processes
used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure
that the information between "RC Start" and "RC End" in the SB are identical to the
information in the same sections (Compliance, Work Instructions...) of the RB which
the SB refers to as the related document.
3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
4. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
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Original Issue: December 19, 2025
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REQUIREMENTS BULLETIN 747-53A2913
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### Page 10

— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
5. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
6. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
7. 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.
8. 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.
12. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
B. WORK INSTRUCTIONS
Actions Required for Compliance
1. Requirements
Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23L for any crack.
Refer to the listed proce-
dures in SB 747-53A2913
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 1: OPEN AC-
CESS - LEFT SIDE.
-Do an external surface
HFEC inspection of the up-
per fastener row of the
fuselage skin lap splice for
any crack.
All Airplanes.
-FIGURE 1
Do PART 2: CLOSE AC-
CESS - LEFT SIDE.
-Repeat the external surface
HFEC inspection of the up-
per fastener row of the
fuselage skin lap splice for
any crack. (a)
CONDITION 1: NO
CRACK FOUND
-FIGURE 1
Export Controlled ECCN: 9E991
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Original Issue: December 19, 2025
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REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 11

Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23L for any crack.
Refer to the listed proce-
dures in SB 747-53A2913
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
CONDITION 2: ANY
CRACK FOUND Do PART 2: CLOSE AC-
CESS - LEFT SIDE.
-
Do PART 1: OPEN AC-
CESS - LEFT SIDE.
-CONDITION 2 (ACTION 2):
Repeat the external surface
HFEC inspection of the up-
per fastener row of the
fuselage skin lap splice for
any crack. (a)
-FIGURE 1
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin
747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747-
53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913
RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Table 2: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23R for any crack.
Refer to the listed proce-
dures in SB 747-53A2913
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
Do PART 3: OPEN AC-
CESS - RIGHT SIDE.
-Do an external surface
HFEC inspection of the up-
per fastener row of the
fuselage skin lap splice for
any crack.
All Airplanes.
-FIGURE 2
Do PART 4: CLOSE AC-
CESS - RIGHT SIDE.
-Repeat the external surface
HFEC inspection of the up-
per fastener row of the
fuselage skin lap splice for
any crack. (a)
CONDITION 3: NO
CRACK FOUND
-FIGURE 2
Export Controlled ECCN: 9E991
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Original Issue: December 19, 2025
747-53A2913 RB
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REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 12

Table 2: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspec-
tions Between STA 1350 and STA 1480 at S-23R for any crack.
Refer to the listed proce-
dures in SB 747-53A2913
Original Issue or later
approved revisions as an
accepted procedure.
Method of ComplianceActionCondition
--CONDITION 4 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
CONDITION 4: ANY
CRACK FOUND Do PART 4: CLOSE AC-
CESS - RIGHT SIDE.
-
Do PART 3: OPEN AC-
CESS - RIGHT SIDE.
-CONDITION 4 (ACTION 2):
Repeat the external surface
HFEC inspection of the up-
per fastener row of the
fuselage skin lap splice for
any crack. (a)
-FIGURE 2
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin
747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747-
53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913
RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
12 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 13 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
STA
1480
* STA
1350
STA  STA  STA  STA  STA  STA  STA
1350  1372  1394  1416  1438  1460  1480
- S-23L
VIEW LOOKING INBOARD  (TYPICAL)  3098313
A-A
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION
(SHEET 1 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991  747-53A2913 RB
See page 1 for details  13 of 22

### Page 14 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
UPPER
SKIN
PANEL
S-23L-
LOWER,
•SKIN
PANEL
VIEW LOOKING INBOARD
1350  STA  FWD  (TYPICAL)  17 LOCATIONS  1372  STA
UPPER
SKIN
PANEL
S-23L
LOWER
• SKIN
PANEL
VIEW LOOKING INBOARD
1372  STA  - WD  (TYPICAL)  18 LOCATIONS  1394  STA
A INSPECTION AREA  3098404
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION
(SHEET 2 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991  747-53A2913 RB
See page 1 for details  14 of 22

### Page 15 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
UPPER
SKIN
PANEL
S-23L -
LOWER
SKIN
PANEL
VIEW LOOKING INBOARD
STA  (TYPICAL)  STA
1394  17 LOCATIONS  1416
UPPER
• SKIN
PANEL
S-23L
LOWER
• SKIN
PANEL
VIEW LOOKING INBOARD
1416  STA  - WD  (TYPICAL)  17 LOCATIONS  1438  STA
I INSPECTION AREA  3098396
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION
(SHEET 3 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991  747-53A2913 RB
See page 1 for details  15 of 22

### Page 16 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
UPPER
SKIN
PANEL
TYPICAL
CRACK
0000024000
S-23L
LOWER
SKIN
PANEL
VIEW LOOKING INBOARD
1438  STA  17 LOCATIONS  (TYPICAL)  WD  1460  STA
UPPER
SKIN
PANEL
S-23L
-- .
LOWER
SKIN
PANEL
VIEW LOOKING INBOARD
1460  STA  FWD  16 LOCATIONS  (TYPICAL)  TYPICAL  CRACK  1480  STA
A INSPECTION AREA  3098418
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION
(SHEET 4 OF 5)
Original Issue: December 19, 2025
747-53A2913 RB
Export Controlled ECCN: 9E991
See page 1 for details  16 of 22

### Page 17

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 this figure.
More DataQtyIdentificationNameTaskStep
(a)102-FUSELAGE SKINInspect1
(a) Do an external surface High Frequency Eddy Current (HFEC) inspection around the fasteners of the
fuselage skin lap splice, in accordance with 747 NDT Manual Part 6, 51-00-00 Procedure 23, for any
crack.
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION
(SHEET 5 OF 5)
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Original Issue: December 19, 2025
747-53A2913 RB
17 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

### Page 18 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
STA
1480
STA
1350
STA  STA  STA  SIA  STA  STA  STA
1480  1460  1438  1416  1394  1372  1350
S-23R
FWD
VIEW LOOKING INBOARD
3098421
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION
(SHEET 1 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991
See page 1 for details  18 of 22

### Page 19 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
UPPER
SKIN
PANEL
- S-23R
LOWER
SKIN
PANEL
VIEW LOOKING INBOARD
1480  STA  TYPICAL  CRACK  (TYPICAL)  16 LOCATIONS  1460  STA
UPPER
TYPICAL  SKIN
CRACK  PANEL
- S-23R
LOWER
SKIN
PANEL
VIEW LOOKING INBOARD
STA  (TYPICAL)  STA
1460  WD  17 LOCATIONS  1438
A INSPECTION AREA  3098440
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION
(SHEET 2 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991  747-53A2913 RB
See page 1 for details  19 of 22

### Page 20 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
UPPER SKIN
PANEL
00000001
- S-23R
LOWER
SKIN
PANEL
VIEW LOOKING INBOARD
1438  STA  17 LOCATIONS  (TYPICAL)  FWD  STA  1416
UPPER SKIN
PANEL
- S-23R
LOWER
• SKIN
PANEL
STA  VIEW LOOKING INBOARD  STA
1416  17 LOCATIONS  (TYPICAL)  FWD  1394
A INSPECTION AREA  3098437
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION
(SHEET 3 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991  747-53A2913 RB
See page 1 for details  20 of 22

### Page 21 (OCR)

REQUIREMENTS BULLETIN 747-53A2913
ALERT  ALERT
UPPER SKIN
PANEL
- S-23R
LOWER
SKIN
PANEL
FWD
STA  STA
1394  18 LOCATIONS  1372
VIEW LOOKING INBOARD
(TYPICAL)
UPPER SKIN
PANEL
-S-23R
LOWER-
SKIN
PANEL
STA  FWD  STA
1372  17 LOCATIONS  1350
VIEW LOOKING INBOARD
(TYPICAL)
VIA INSPECTION AREA  3098433
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION
(SHEET 4 OF 5)
Original Issue: December 19, 2025
Export Controlled ECCN: 9E991  747-53A2913 RB
See page 1 for details  21 of 22

### Page 22

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 this figure.
More DataQtyIdentificationNameTaskStep
(a)102-FUSELAGE SKINInspect1
(a) Do an external surface High Frequency Eddy Current (HFEC) inspection around the fasteners of the
fuselage skin lap splice, in accordance with 747 NDT Manual Part 6, 51-00-00 Procedure 23, for any
crack.
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: December 19, 2025
747-53A2913 RB
22 of 22
REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT

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