# Boeing Alert Service Bulletin 747-53A2899: Revision 1

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- Document: [Boeing Alert Service Bulletin 747-53A2899](https://openairdocs.org/service-documents/boeing/747-53a2899.md)
- Title as filed: 747-53A2899-00--RB
- Pages: 36
- PDF: https://openairdocs.org/files/sha256/0e/86/0e861657be307865edb4c5401e6ec0a2dcbf3f1a59df59a1b8a230f4fd8af190
- Page: https://openairdocs.org/service-documents/boeing/747-53a2899/file/0e861657be30

## Text

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### Page 1

Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-53A2899 RB
Original Issue: April 05, 2019
ATA System: 5313
SUBJECT: FUSELAGE - Tail Section - Body Station 2598 Bulkhead Left Side and Right Side
Upper Splice Fitting Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
Copyright © 2019 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Unpublished Work.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: April 05, 2019
747-53A2899 RB
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4.0

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REQUIREMENTS BULLETIN 747-53A2899
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Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE [Group 1, 3] . . 21
FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE  [Group 1, 3] . 25
FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE  [Group 2] . . . 29
FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE  [Group 2] . . 33
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ALERTALERT
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Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-53A2899 RB
Original Issue: April 05, 2019
ATA System: 5313
SUBJECT: FUSELAGE - Tail Section - Body Station 2598 Bulkhead Left Side and Right Side
Upper Splice Fitting 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 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F,
747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR Airplane(s), line number(s) 1-1419 in 3 Group(s).
DESCRIPTIONCONFIGURATIONGROUP
747-100/-100B/-100B SUD
/-200B/-200C/-200F/-300/-400/-400D/-400F/ 747SR airplanes that
have upper splice fittings 65B02539 -1/-2 or -3/-4 or -11/-12 installed.
-1
747-400/ 747SP airplanes that have upper splice fittings 65B02539
-1/-2 or -3/-4 or -11/-12 installed.
-2
747-400/-400F airplanes that have upper splice fittings 65B02539
-7/-8 installed.
-3
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
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3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 747-53A2899 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 747-53A2899 RB mandatory.
Accomplish the required actions, based on the applicable condition in Tables 1, 2, 3, and 4 in accordance
with the 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 number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Group 1, 3:
Table 1: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Left Upper
Splice Fitting at the STA 2598 Bulkhead
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs later)
ActionCondition
-Within 2,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 747-
53A2899 RB.
Before 20,000
total flight cy-
cles.
Do a detailed inspection and
open hole HFEC inspection
of the left upper splice fitting
at the STA 2598 bulkhead
for any crack.
All Airplanes.
3,000 flight cycles-Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the left upper
splice fitting at the STA 2598
bulkhead for any crack.
CONDITION 1:
NO CRACK FOUND.
-Before further flight.CONDITION 2 (ACTION 1):CONDITION 2:
Contact The Boeing Compa-
ny for repair instructions, and
do the repair.
ANY CRACK FOUND.
3,000 flight cycles-CONDITION 2 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the left upper
splice fitting at the STA 2598
bulkhead for any crack.
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REQUIREMENTS BULLETIN 747-53A2899
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### Page 7

Group 1, 3:
Table 2: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Right Upper
Splice Fitting at the STA 2598 Bulkhead
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs later)
ActionCondition
-Within 2,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 747-
53A2899 RB.
Before 20,000
total flight cy-
cles.
Do a detailed inspection and
open hole HFEC inspection
of the right upper splice fit-
ting at the STA 2598 bulk-
head for any crack.
All Airplanes.
3,000 flight cycles-Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the right upper
splice fitting at the STA 2598
bulkhead for any crack.
CONDITION 3:
NO CRACK FOUND.
-Before further flight.CONDITION 4 (ACTION 1):CONDITION 4:
Contact The Boeing Compa-
ny for repair instructions, and
do the repair.
ANY CRACK FOUND.
3,000 flight cycles-CONDITION 4 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the right upper
splice fitting at the STA 2598
bulkhead for any crack.
Group 2:
Table 3: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Left Upper
Splice Fitting at the STA 2598 Bulkhead
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs later)
ActionCondition
-Within 1,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 747-
53A2899 RB.
Before 12,000
total flight cy-
cles.
Do a detailed inspection and
open hole HFEC inspection
of the left upper splice fitting
at the STA 2598 bulkhead
for any crack.
All Airplanes.
1,500 flight cycles.-Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the left upper
splice fitting at the STA 2598
bulkhead for any crack.
CONDITION 5:
NO CRACK FOUND.
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Group 2:
Table 3: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Left Upper
Splice Fitting at the STA 2598 Bulkhead
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs later)
ActionCondition
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Contact The Boeing Compa-
ny for repair instructions, and
do the repair.
ANY CRACK FOUND.
1,500 flight cycles.-CONDITION 6 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the left upper
splice fitting at the STA 2598
bulkhead for any crack.
Group 2:
Table 4: Detailed and Open Hole High Frequency Eddy Current (HFEC) Inspection of the Right Upper
Splice Fitting at the STA 2598 Bulkhead
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs later)
ActionCondition
-Within 1,500
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 747-
53A2899 RB.
Before 12,000
total flight cy-
cles.
Do a detailed inspection and
open hole HFEC inspection
of the right upper splice fit-
ting at the STA 2598 bulk-
head for any crack.
All Airplanes.
1,500 flight cycles.-Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the right upper
splice fitting at the STA 2598
bulkhead for any crack.
CONDITION 7:
NO CRACK FOUND.
-Before further flight.CONDITION 8 (ACTION 1):CONDITION 8:
Contact The Boeing Compa-
ny for repair instructions, and
do the repair.
ANY CRACK FOUND.
1,500 flight cycles.-CONDITION 8 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC in-
spection of the right upper
splice fitting at the STA 2598
bulkhead for any crack.
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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 for the airplanes
listed in the service bulletin effectivity. This document and its approval were based on the airplane in its
original Boeing delivery configuration or as modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by
this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this Requirements Bulletin.
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5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
2. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
3. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
4. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
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. 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.
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7. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
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. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
10. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
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 number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
12. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
13. 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.
14. This is an Enhanced Required for Compliance document. The Boeing process 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.
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B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements:
Group 1, 3:
Table 1: Detailed and Open Hole High Frequency Eddy Current Inspection of the Left Upper Splice Fitting
at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
DO PART 1: GET AC-
CESS
-Do a detailed inspection
and open hole HFEC inspec-
tion of the left upper splice
fitting at the STA 2598
bulkhead, for any crack.
All Airplanes.
DO FIGURE 1: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL - LEFT
SIDE
-FIGURE 2
DO FIGURE 3: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
LEFT SIDE
-
DO PART 2: CLOSE AC-
CESS
DO PART 1: GET AC-
CESS
-Repeat the detailed inspec-
tion and open hole HFEC
inspection of the left upper
splice fitting at the STA
2598 bulkhead for any
crack.
CONDITION 1: NO
CRACK FOUND.
DO FIGURE 1: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL - LEFT
SIDE
-FIGURE 2
DO FIGURE 3: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
LEFT SIDE
-
DO PART 2: CLOSE AC-
CESS
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### Page 14

Group 1, 3:
Table 1: Detailed and Open Hole High Frequency Eddy Current Inspection of the Left Upper Splice Fitting
at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
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 1: GET AC-
CESS
-CONDITION 2 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC
inspection of the left upper
splice fitting at the STA
2598 bulkhead for any
crack.
DO FIGURE 1: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL - LEFT
SIDE
-FIGURE 2
DO FIGURE 3: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
LEFT SIDE
-
DO PART 2: CLOSE AC-
CESS
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Group 1, 3:
Table 2: Detailed and Open Hole High Frequency Eddy Current Inspection of the Right Upper Splice
Fitting at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
DO PART 1: GET AC-
CESS
-Do a detailed inspection
and open hole HFEC inspec-
tion of the right upper splice
fitting at the STA 2598
bulkhead, for any crack.
All Airplanes.
DO FIGURE 4: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL -
RIGHT SIDE
-FIGURE 5
DO FIGURE 6: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
RIGHT SIDE
-
DO PART 2: CLOSE AC-
CESS
DO PART 1: GET AC-
CESS
-Repeat the detailed inspec-
tion and open hole HFEC
inspection of the right upper
splice fitting at the STA
2598 bulkhead for any
crack.
CONDITION 3: NO
CRACK FOUND.
DO FIGURE 4: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL -
RIGHT SIDE
-FIGURE 5
DO FIGURE 6: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
RIGHT SIDE
-
DO PART 2: CLOSE AC-
CESS
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Group 1, 3:
Table 2: Detailed and Open Hole High Frequency Eddy Current Inspection of the Right Upper Splice
Fitting at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
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 4: ANY
CRACK FOUND
DO PART 1: GET AC-
CESS
-CONDITION 2 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC
inspection of the right upper
splice fitting at the STA
2598 bulkhead for any
crack.
DO FIGURE 4: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL -
RIGHT SIDE
-FIGURE 5
DO FIGURE 6: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
RIGHT SIDE
-
DO PART 2: CLOSE AC-
CESS
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### Page 17

Group 2:
Table 3: Detailed and Open Hole High Frequency Eddy Current Inspection of the Left Upper Splice Fitting
at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
DO PART 1: GET AC-
CESS
-Do a detailed inspection
and open hole HFEC inspec-
tion of the left upper splice
fitting at the STA 2598
bulkhead, for any crack.
All Airplanes.
DO FIGURE 7: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL - LEFT
SIDE
-FIGURE 8
DO FIGURE 9: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
LEFT SIDE
-
DO PART 2: CLOSE AC-
CESS
DO PART 1: GET AC-
CESS
-Repeat the detailed inspec-
tion and open hole HFEC
inspection of the left upper
splice fitting at the STA
2598 bulkhead for any
crack.
CONDITION 1: NO
CRACK FOUND.
DO FIGURE 7: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL - LEFT
SIDE
-FIGURE 8
DO FIGURE 9: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
LEFT SIDE
-
DO PART 2: CLOSE AC-
CESS
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
17 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 18

Group 2:
Table 3: Detailed and Open Hole High Frequency Eddy Current Inspection of the Left Upper Splice Fitting
at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
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 1: GET AC-
CESS
-CONDITION 2 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC
inspection of the left upper
splice fitting at the STA
2598 bulkhead for any
crack.
DO FIGURE 7: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL - LEFT
SIDE
-FIGURE 8
DO FIGURE 9: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
LEFT SIDE
-
DO PART 2: CLOSE AC-
CESS
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
18 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 19

Group 2:
Table 4: Detailed and Open Hole High Frequency Eddy Current Inspection of the Right Upper Splice
Fitting at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
Original Issue or later
approved revisions as an
accepted procedure
Method of ComplianceActionCondition
DO PART 1: GET AC-
CESS
-Do a detailed inspection
and open hole HFEC inspec-
tion of the right upper splice
fitting at the STA 2598
bulkhead, for any crack.
All Airplanes.
DO FIGURE 10: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL -
RIGHT SIDE
-FIGURE 11
DO FIGURE 12: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
RIGHT SIDE
-
DO PART 2: CLOSE AC-
CESS
DO PART 1: GET AC-
CESS
-Repeat the detailed inspec-
tion and open hole HFEC
inspection of the right upper
splice fitting at the STA
2598 bulkhead for any
crack.
CONDITION 3: NO
CRACK FOUND.
DO FIGURE 10: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL -
RIGHT SIDE
-FIGURE 11
DO FIGURE 12: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
RIGHT SIDE
-
DO PART 2: CLOSE AC-
CESS
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
19 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 20

Group 2:
Table 4: Detailed and Open Hole High Frequency Eddy Current Inspection of the Right Upper Splice
Fitting at the STA 2598 Bulkhead
Refer to the listed proce-
dures in SB 747-53A2899
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 4: ANY
CRACK FOUND
DO PART 1: GET AC-
CESS
-CONDITION 2 (ACTION 2):
Repeat the detailed inspec-
tion and open hole HFEC
inspection of the right upper
splice fitting at the STA
2598 bulkhead for any
crack.
DO FIGURE 10: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER REMOVAL -
RIGHT SIDE
-FIGURE 11
DO FIGURE 12: STA 2598
BULKHEAD - UPPER
SPLICE FITTING - FAS-
TENER INSTALLATION -
RIGHT SIDE
-
DO PART 2: CLOSE AC-
CESS
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
20 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 21 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
This Figure applies only to: Group 1, 3.
STA
2598
' S-11L
' S-11R
2826003
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 1 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  21 of 36

### Page 22 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
****  STRINGER FITTING
* %  - S-10L
UPPER LONGERON
SPLICE FITTING
- S-11L
LOWER LONGERON
SPLICE FITTING
INBD  A-A  NILE
INSPECTION AREA  2826004
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 2 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.

### Page 23 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STA
2598
UPPER
SPLICE
FITTING
UPPER SPLICE
STA  FITTING
2598  (2) 4 LOCATIONS
FWD  B-B
UPPER LONGERON
SPLICE FITTING
- S-11L
LOWER LONGERON
SPLICE FITTING
INSPECTION AREA  C-C  FWD
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 3 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.  23 of 36

### Page 24

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)(b)1-UPPER SPLICE FIT-
TING
Inspect1
(c)4-HOLEInspect2
(a) Do a detailed inspection of the upper splice fitting at the STA 2598 bulkhead, for any crack.
(b) If structure or systems hardware attached to the skin covers a structural detail that is inspected, then it
is only necessary to inspect the area of the structural detail that is visible. It is not necessary to remove
structure or systems hardware attached to the skin to do the inspection.
(c) Do an open hole HFEC inspection at hole locations where fasteners were removed in the upper splice
fitting, for any crack in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16.
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
24 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 25 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
This Figure applies only to: Group 1, 3.
STA
2598
' S-11L
' S-11R
2826380
FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 1 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  25 of 36

### Page 26 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STRINGER FITTING
S-10R
UPPER LONGERON
SPLICE FITTING
S-11R
LOWER LONGERON
SPLICE FITTING
C
UPPER SPLICE 1
FITTING  A-A  INBD
INSPECTION AREA
FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 2 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.

### Page 27 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STA
2598
UPPER
SPLICE
‚FITTING
UPPER SPLICE
FITTING
STA
2598
4 LOCATIONS 2
B-B  FWD
UPPER LONGERON
SPLICE FITTING
S-11R -
LOWER LONGERON
SPLICE FITTING
FWD  2833576
INSPECTION AREA
C-C
FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 3 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  27 of 36

### Page 28

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)(b)1-UPPER SPLICE FIT-
TING
Inspect1
(c)4-HOLEInspect2
(a) Do a detailed inspection of the upper splice fitting at the STA 2598 bulkhead for any crack.
(b) If structure or systems hardware attached to the skin covers a structural detail that is inspected, then it
is only necessary to inspect the area of the structural detail that is visible. It is not necessary to remove
structure or systems hardware attached to the skin to do the inspection.
(c) Do an open hole HFEC inspection at hole locations where fasteners were removed in the upper splice
fitting, for any crack in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16.
FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
28 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 29 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
This Figure applies only to: Group 2.
STA
2598
S-11L
S-11R
2829213
FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 1 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  29 of 36

### Page 30 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
*****  STRINGER FITTING
* %  - S-10L
UPPER LONGERON
SPLICE FITTING
- S-11L
LOWER LONGERON
SPLICE FITTING
INBD  A-A  NILE
INSPECTION AREA  2829219
FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 2 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.

### Page 31 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STA
2598
UPPER
SPLICE
FITTING
UPPER SPLICE
STA  FITTING
2598
(2) 4 LOCATIONS
FWD  B-B
UPPER LONGERON
SPLICE FITTING
- S-11L
LOWER LONGERON
SPLICE FITTING
INSPECTION AREA  C-C  FWD  2834216
FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 3 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  31 of 36

### Page 32

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)(b)1-UPPER SPLICE FIT-
TING
Inspect1
(c)4-HOLEInspect2
(a) Do a detailed inspection of the upper splice fitting at the STA 2598 bulkhead, for any crack.
(b) If structure or systems hardware attached to the skin covers a structural detail that is inspected, then it
is only necessary to inspect the area of the structural detail that is visible. It is not necessary to remove
structure or systems hardware attached to the skin to do the inspection.
(c) Do an open hole HFEC inspection at hole locations where fasteners were removed in the upper splice
fitting, for any crack in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16.
FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
32 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 33 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
This Figure applies only to: Group 2.
STA
2598
' S-11L
' S-11R
2829223
FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 1 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  33 of 36

### Page 34 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STRINGER FITTING
S-10R
UPPER LONGERON
SPLICE FITTING
S-11R
LOWER LONGERON
SPLICE FITTING
FITTING  UPPER SPLICE (  A-A  INBD
INSPECTION AREA  2829224
FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 2 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.  SO DE

### Page 35 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STA  UPPER
2598  SPLICE
FITTING
UPPER SPLICE STA
FITTING  2598
4 LOCATIONS 2
B-B  FWD
UPPER LONGERON
SPLICE FITTING
S-11R -
LOWER LONGERON
SPLICE FITTING
C-C  INSPECTION AREA  2834253
FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 3 OF 4)
Original Issue: April 05, 2019
Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  35 of 36

### Page 36

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)(b)1-UPPER SPLICE FIT-
TING
Inspect1
(c)4-HOLESInspect2
(a) Do a detailed inspection of the upper splice fitting at the STA 2598 bulkhead, for any crack.
(b) If structure or systems hardware attached to the skin covers a structural detail that is inspected, then it
is only necessary to inspect the area of the structural detail that is visible. It is not necessary to remove
structure or systems hardware attached to the skin to do the inspection.
(c) Do an open hole HFEC inspection at hole locations where fasteners were removed in the upper splice
fitting, for any crack in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16.
FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2019
747-53A2899 RB
36 of 36
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

---
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