# Boeing Alert Requirements Bulletin 747-53A2899 RB: Revision 1

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- Title as filed: 747-53A2899-RB-01--
- Pages: 40
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### Page 1

Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-53A2899 RB
Original Issue: April 05, 2019
Revision 1: April 07, 2020
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Unpublished Work.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 RBRevision 1: April 07, 2020
1 of 40
3.0

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ALERTALERT
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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
FIGURE 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE [Group 1, 3] . . 25
FIGURE 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE [Group 1, 3] . 29
FIGURE 8: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE [Group 2] . . . 33
FIGURE 11: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN
HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE [Group 2] . . 37
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ALERTALERT
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Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Revision Transmittal SheetNumber: 747-53A2899 RBOriginal Issue: April 05, 2019
Revision 1: April 07, 2020
ATA System: 5313
SUBJECT: FUSELAGE - Tail Section - Body Station 2598 Bulkhead Left Side and Right Side
Upper Splice Fitting Inspection
This revision includes all pages of the requirements bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2019-NM-122-AD, is related to
this service bulletin.
Effects of this revision on Airplanes on which Original Issue was previously done:
None.
REASON FOR REVISION
This revision is sent to correct the Approval statement in the Requirements Bulletin (RB) and to provide Notice
of Proposed Rule Making (NPRM) information.
These sections were changed:
- In Compliance, added NPRM information.
- In Approval of the Requirements Bulletin, added EASA/JAA approval statement.
- In Effectivity, Group Applicability table clarified to specify Group 2 description as 747-400 (Large Cargo
Freighter)/747SP airplanes.
Vertical lines are put on the left edge of each page, except in Effectivity and format changes, to show the location
of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
Service BulletinService BulletinRequirement BulletinRequirement Bulletin
747-53A2899747-53A2899747-53A2899 RB747-53A2899 RB
Issue DateIssue Date
April 05, 2019Original Issue:April 05, 2019Original Issue:
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April 07, 2020Revision 1:April 07, 2020Revision 1:
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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

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Commercial 
Airplanes
747
Requirements Bulletin
ALERT
Number: 747-53A2899 RB
Original Issue: April 05, 2019
Revision 1: April 07, 2020
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). Where the effectivity is presented with hyphens between line numbers, the airplane
applicability means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through
9 inclusive.
DESCRIPTIONCONFIGURATIONGROUP
747-100/-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 (Large Cargo Freighter)/ 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
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SP, 747SR
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GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
GroupVariable Number
1RB411 - RB413
1RB421
1RB601 - RB607
1RB681 - RB697
1RB711
1RB721 - RB723
1RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD144
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD227
1RD231 - RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
1RD301 - RD302
1RD311
1RD351 - RD358
1RD361 - RD366
1RD381 - RD383
1RD411 - RD414
1RD421 - RD426
GroupVariable Number
1RD431 - RD435
1RD441 - RD442
1RD451 - RD456
1RD461
1RD471 - RD475
1RD513 - RD519
1RD531 - RD533
1RD551
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD601 - RD607
1RD621 - RD623
1RD641 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
3RF001 - RF006
2RG001 - RG009
2RG091
2RG095
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GroupVariable Number
2RG101 - RG104
2RG121 - RG126
2RG141 - RG142
2RG161 - RG164
2RG171 - RG174
2RG191 - RG193
2RG211 - RG213
2RG221 - RG222
2RH101 - RH102
2RH111 - RH112
2RH121 - RH122
1RJ131 - RJ133
1RJ151 - RJ152
1RJ301 - RJ303
1RJ321 - RJ322
1RJ331 - RJ333
1RL401 - RL402
3RL403
1RL411 - RL419
3RL420 - RL436
3RL451 - RL456
3RL461 - RL462
3RL471 - RL481
3RL491 - RL492
3RL501 - RL502
3RL511 - RL516
3RL521 - RL522
3RL531 - RL534
3RL551
3RL561 - RL568
3RL571 - RL572
3RL576 - RL577
3RL579
GroupVariable Number
3RL581 - RL586
1RL651 - RL654
3RL655
3RL671 - RL675
3RL681 - RL684
1RL751
3RL752
1RM001 - RM007
1RM010 - RM013
1RM021 - RM024
1RM026 - RM029
3RM030
1RM036 - RM045
1RM051 - RM052
3RM053
1RM071
1RM081 - RM084
1RM091
1RM096 - RM097
1RM116 - RM117
1RM126 - RM132
1RM136 - RM147
1RM156 - RM158
1RM166 - RM177
1RM191 - RM192
1RM231 - RM233
1RM241 - RM246
1RM261 - RM264
1RM316 - RM318
1RM331 - RM333
1RM341
1RM351 - RM355
1RM366 - RM367
GroupVariable Number
3RM401 - RM403
3RM426
3RM431
3RM441 - RM443
3RM445
1RM801 - RM803
1RM811 - RM813
1RM851 - RM858
3RM859
1RM861 - RM862
3RM863
1RM871 - RM876
3RM877 - RM880
1RM881 - RM886
3RM887 - RM890
1RM891 - RM899
1RM901 - RM905
3RM906
1RM911
1RR001 - RR005
1RR021 - RR025
1RR031
1RR201 - RR206
1RR221 - RR226
1RR261 - RR267
1RR301 - RR310
1RR331 - RR332
1RR336
1RR341 - RR345
1RR361 - RR362
1RR421 - RR422
1RR431 - RR432
1RR441 - RR442
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GroupVariable Number
1RR451
1RR501 - RR504
1RR521 - RR522
1RR526
1RR531
1RR551 - RR556
1RR561
1RR566
1RR701
1RR721 - RR724
1RR746 - RR748
1RR851 - RR856
1RR861 - RR862
1RR951 - RR952
1RS001 - RS002
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
GroupVariable Number
1RS711 - RS713
1RS721 - RS722
1RS731 - RS732
1RS741 - RS743
1RS751 - RS752
1RS761 - RS762
1RS771
1RS781 - RS782
1RS786
1RT001 - RT014
1RT021 - RT022
1RT031 - RT035
1RT041 - RT047
1RT061
1RT071 - RT075
1RT101 - RT103
1RT121
1RT131 - RT137
1RT151 - RT152
1RT161 - RT168
1RT401 - RT412
1RT431 - RT447
1RT451 - RT469
1RT471 - RT499
1RT501 - RT535
1RT551 - RT568
1RT571 - RT591
1RT601 - RT630
2RT631 - RT632
1RT633 - RT657
GroupVariable Number
1RT671 - RT673
1RT681 - RT682
1RT691 - RT699
1RT701 - RT704
1RT711 - RT717
1RT741 - RT742
2RT743
1RT744 - RT757
1RT776 - RT777
1RT781 - RT784
1RT801 - RT803
1RT811 - RT814
1RT831 - RT837
1RT861 - RT864
2RT876
1RT877 - RT880
1RT931 - RT932
1RT945 - RT949
1RT951 - RT955
1RT966 - RT967
1RU001 - RU006
1RU016 - RU017
1RU031 - RU032
1RU051 - RU052
1RU059 - RU062
1RU081 - RU083
1RU101 - RU102
1RU121 - RU132
1RU801 - RU809
1RU831 - RU841
B. Spares Affected
None.
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2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2019-NM-122-AD, is related
to this service bulletin.
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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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, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the 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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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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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 16

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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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 17

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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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 18

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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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 19

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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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 20

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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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 21

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
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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 22

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
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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 23

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
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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 24

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
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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
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
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Copyright © Unpublished
Work - See page 1 for details.  25 of 40

### Page 26 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STRINGER FITTING
- S-10L
UPPER LONGERON
SPLICE FITTING
- S-11L
LOWER LONGERON
SPLICE FITTING
C
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
Revision 1 April 07, 2020  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
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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished
Work - See page 1 for details.  27 of 40

### 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 2: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - LEFT SIDE
(SHEET 4 OF 4)
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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 29 (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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  29 of 40

### Page 30 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STRINGER FITTING
S-10R
UPPER LONGERON
SPLICE FITTING
S-11R
LOWER LONGERON
SPLICE FITTING
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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished
Work - See page 1 for details.  ON NO CE

### Page 31 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STA
2598
UPPER
SPLICE
FITTING
OPPER 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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished  747-53A2899 RB
Work - See page 1 for details.  31 of 40

### 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 5: STA 2598 BULKHEAD - UPPER SPLICE FITTING - DETAILED INSPECTION AND OPEN HOLE
HIGH FREQUENCY EDDY CURRENT INSPECTION - RIGHT SIDE
(SHEET 4 OF 4)
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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
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
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Work - See page 1 for details.  33 of 40

### Page 34 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STRINGER FITTING
- S-10L
UPPER LONGERON
SPLICE FITTING
- S-11L
LOWER LONGERON
SPLICE FITTING
C
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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished
Work - See page 1 for details.  TO DE

### Page 35 (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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished
Work - See page 1 for details.

### 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-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)
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REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

### Page 37 (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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  747-53A2899 RB
Copyright © Unpublished
Work - See page 1 for details.  37 of 40

### Page 38 (OCR)

REQUIREMENTS BULLETIN 747-53A2899
ALERT  ALERT
STRINGER FITTING
S-10R
UPPER LONGERON
SPLICE FITTING
S- 11R •
LOWER LONGERON
SPLICE FITTING
UPPER SPLICE 1  FITTING  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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished
Work - See page 1 for details.

### Page 39 (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
Revision 1 April 07, 2020  Export Controlled ECCN: 9E991  Copyright © Unpublished  747-53A2899 RB
Work - See page 1 for details.  + 10 68

### Page 40

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 RBRevision 1 April 07, 2020
40 of 40
REQUIREMENTS BULLETIN 747-53A2899
ALERTALERT

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