# Boeing Alert Service Bulletin 747-53A2499: Revision 3

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- Document: [Boeing Alert Service Bulletin 747-53A2499](https://openairdocs.org/service-documents/boeing/747-53a2499.md)
- Title as filed: SB-747-53A2499-03
- Pages: 378
- PDF: https://openairdocs.org/files/sha256/dd/0c/dd0cad58d0a8c8047f6800d3c9944f12cb6ee98510fc9daaba9262e54dac300e
- Page: https://openairdocs.org/service-documents/boeing/747-53a2499/file/dd0cad58d0a8

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2499
Original Issue: August 11, 2005
Revision 3: July 15, 2014
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 41, 42, and 46 Body Skin Lap Joint Inspections and
Modifications
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:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2005 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Unpublished Work.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: August 11, 2005
747-53A2499Revision 3: July 15, 2014
1 of 378
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Table of Contents
Revision Transmittal Sheet ............................................ 7
Summary ..................................................... 1 1
1. PLANNING INFORMATION ........................................ 1 5
A. Effectivity ............................................... 1 5
1. Airplanes ............................................ 1 5
2. Spares Affected ........................................ 2 2
B. Concurrent Requirements ...................................... 2 2
C. Reason ................................................ 2 3
D. Description .............................................. 2 4
E. Compliance .............................................. 2 8
F. Approval ............................................... 3 7
G. Manpower .............................................. 4 0
H. Weight and Balance Changes .................................... 4 3
I. Electrical Load Data ......................................... 4 3
J. References .............................................. 4 3
1. Existing Data: ......................................... 4 3
2. Data Supplied with this Service Bulletin: ........................... 4 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 7
K. Publications Affected ........................................ 4 7
L. Interchangeability and Intermixability of Parts ........................... 4 7
M. Software Accomplishment Summary ................................ 4 7
2. MATERIAL INFORMATION ........................................ 4 9
A. Material - Price and Availability ................................... 4 9
B. Industry Support Information .................................... 5 0
C. Parts Necessary for Each Airplane ................................. 5 0
1. Kits/Parts: ........................................... 5 0
2. Parts and Materials Supplied by the Operator: ........................ 6 6
3. Parts Modified and Reidentified: ............................... 6 6
4. Parts Removed and Not Replaced: .............................. 6 6
D. Parts Necessary to Change Spares ................................. 6 6
E. Special Tooling - Price and Availability ............................... 6 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 6 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 7
A. GENERAL INFORMATION ..................................... 6 7
B. WORK INSTRUCTIONS ....................................... 7 1
FIGURE 1: LOGIC DIAGRAM (DELETED - REVISION 1) ........................ 7 9
FIGURE 2: LAP JOINT INSPECTION [Group 1, 16-18] .......................... 8 0
FIGURE 3: LAP JOINT INSPECTION [Group 2] .............................. 9 1
FIGURE 4: LAP JOINT INSPECTION [Group 3] ............................. 1 0 7
FIGURE 5: LAP JOINT INSPECTION [Group 4, 19] ........................... 1 2 1
FIGURE 6: LAP JOINT INSPECTION [Group 5] ............................. 1 3 7
FIGURE 7: LAP JOINT INSPECTION [Group 6] ............................. 1 5 1
FIGURE 8: LAP JOINT INSPECTION [Group 7] ............................. 1 6 7
FIGURE 9: LAP JOINT INSPECTION [Group 8] ............................. 1 8 3
FIGURE 10: LAP JOINT INSPECTION [Group 9] ............................. 1 9 7
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FIGURE 11: LAP JOINT INSPECTION [Group 10] ............................ 2 0 9
FIGURE 12: LAP JOINT INSPECTION [Group 11] ............................ 2 2 3
FIGURE 13: LAP JOINT INSPECTION [Group 12] ............................ 2 3 7
FIGURE 14: LAP JOINT INSPECTION [Group 13] ............................ 2 5 1
FIGURE 15: LAP JOINT INSPECTION [Group 14] ............................ 2 6 6
FIGURE 16: SECTION 41, STRINGER 6 - LAP JOINT MODIFICATION [Group 1-15, 19] ....... 2 7 9
FIGURE 17: SECTION 41, STRINGER 23 - LAP JOINT MODIFICATION [Group 1, 14-18] ...... 2 8 3
FIGURE 18: SECTION 41, STRINGER 23 - LAP JOINT MODIFICATION [Group 2-12, 19] ...... 2 8 5
FIGURE 19: SECTION 41, STRINGER 23 - LAP JOINT MODIFICATION [Group 13] ......... 2 8 7
FIGURE 20: SECTION 41, STRINGER 44 - LAP JOINT MODIFICATION [Group 1-15, 19] ...... 2 8 9
FIGURE 21: SECTION 42, STRINGER 44 - LAP JOINT MODIFICATION [Group 1, 13-15] ...... 2 9 2
FIGURE 22: SECTION 42, STRINGER 44 - LAP JOINT MODIFICATION [Group 2-12, 19] ...... 2 9 4
FIGURE 23: LAP JOINT INSPECTION [Group 15] ............................ 2 9 6
FIGURE 24: SECTION 41, STRINGER 6 - LAP JOINT MODIFICATION [Group 16-18] ........ 3 0 9
FIGURE 25: SECTION 41, STRINGER 44 - LAP JOINT MODIFICATION [Group 16-18] ........ 3 1 1
FIGURE 26: SECTION 41, STRINGER 6 - LAP JOINT POST-MODIFICATION INSPECTION [Group 1, 14-15]
................................................. 3 1 3
FIGURE 27: SECTION 41, STRINGER 6 - LAP JOINT POST-MODIFICATION INSPECTION [Group 2-13,
19] ............................................... 3 1 7
FIGURE 28: SECTION 41, STRINGER 6 - LAP JOINT POST-MODIFICATION INSPECTION [Group 16-18]
................................................. 3 2 2
FIGURE 29: SECTION 41, STRINGER 23 - LAP JOINT POST-MODIFICATION INSPECTION [Group 1,
14-18] ............................................. 3 2 6
FIGURE 30: SECTION 41, STRINGER 23 - LAP JOINT POST-MODIFICATION INSPECTION [Group 2-13,
19] ............................................... 3 3 0
FIGURE 31: SECTION 41, STRINGER 44 - LAP JOINT POST-MODIFICATION INSPECTION [Group 1,
14-15] ............................................. 3 3 4
FIGURE 32: SECTION 41, STRINGER 44 - LAP JOINT POST-MODIFICATION INSPECTION [Group 2-13,
19] ............................................... 3 3 7
FIGURE 33: SECTION 41, STRINGER 44 - LAP JOINT POST-MODIFICATION INSPECTION [Group 16-18]
................................................. 3 4 0
FIGURE 34: SECTION 42, STRINGER 44 - LAP JOINT POST-MODIFICATION INSPECTION [Group 1,
13-15] ............................................. 3 4 3
FIGURE 35: SECTION 42, STRINGER 44 - LAP JOINT POST-MODIFICATION INSPECTION [Group 2-12,
19] ............................................... 3 4 6
FIGURE 36: SECTION 41, STRINGER 6 - POST-MODIFICATION INSPECTION OF LAP JOINT
MODIFICATION INSTALLED BETWEEN STA 340 AND STA 400 AS GIVEN IN SERVICE
BULLETIN 747-53-2272 - EXTERNAL LFEC AND DETAILED INSPECTIONS OF SKIN - LEFT
SIDE [Group 6, 11, 19] .................................... 3 4 9
FIGURE 37: SECTION 41, STRINGER 6 - POST-MODIFICATION INSPECTION OF LAP JOINT
MODIFICATION INSTALLED BETWEEN STA 340 AND STA 400 AS GIVEN IN SERVICE
BULLETIN 747-53-2272 - EXTERNAL LFEC AND DETAILED INSPECTIONS OF SKIN - RIGHT
SIDE [Group 6, 11, 19] .................................... 3 5 3
FIGURE 38: SECTION 41, STRINGER 6 - POST-MODIFICATION INSPECTION OF LAP JOINT
MODIFICATION INSTALLED BETWEEN STA 340 AND STA 400 AS GIVEN IN SERVICE
BULLETIN 747-53-2272 - EXTERNAL HFEC INSPECTION OF DOUBLER - LEFT SIDE [Group
6, 11, 19] ............................................ 3 5 7
FIGURE 39: SECTION 41, STRINGER 6 - POST-MODIFICATION INSPECTION OF LAP JOINT
MODIFICATION INSTALLED BETWEEN STA 340 AND STA 400 AS GIVEN IN SERVICE
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BULLETIN 747-53-2272 - EXTERNAL HFEC INSPECTION OF DOUBLER - RIGHT SIDE [Group
6, 11, 19] ............................................ 3 6 0
FIGURE 40: SECTION 41, STRINGER 6 - POST-MODIFICATION INSPECTION OF LAP JOINT
MODIFICATION INSTALLED BETWEEN STA 340 AND STA 400 AS GIVEN IN SERVICE
BULLETIN 747-53-2272 - INTERNAL DETAILED AND HFEC INSPECTIONS OF THE SKIN -
LEFT SIDE [Group 6, 11, 19] ................................. 3 6 3
FIGURE 41: SECTION 41, STRINGER 6 - POST-MODIFICATION INSPECTION OF LAP JOINT
MODIFICATION INSTALLED BETWEEN STA 340 AND STA 400 AS GIVEN IN SERVICE
BULLETIN 747-53-2272 - INTERNAL DETAILED AND HFEC INSPECTIONS OF THE SKIN -
RIGHT SIDE [Group 6, 11, 19] ................................ 3 6 7
Appendix A: REDUCED EDGE MARGIN PROCEDURES ........................ 3 7 1
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-53A2499Original Issue: August 11, 2005
Revision 3: July 15, 2014
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 41, 42, and 46 Body Skin Lap Joint Inspections and
Modifications
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
More work is necessary on airplanes that had lap joint modifications accomplished as given in previous revisions
of this service bulletin before 20,000 total flight cycles. Post-modification inspections will be required within
15,000 flight cycles after modification in order to allow continued operation to the Limit of Validity (LOV) of 35,000
total flight cycles.
In addition, more work is necessary on airplane line numbers 604 - 685 that had external doublers installed as
given in Service Bulletin 747-53-2272 at Stringer 6 from Station 340 to Station 400. Post-modification inspection
at Stringer 6 from Station 340 to Station 400 is now required as given in this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-26-10 is related to this service bulletin.
REASON FOR REVISION
This revision is sent to add modification instructions and compliance information for Large Cargo Freighter (LCF)
airplanes and to add post-modification inspections for all airplanes. This revision is also sent to add
post-modification inspections for Group 6, 11 and 19 airplanes with stringer 6 lap joint modification installed
between STA 340 and STA 400 as given in Service Bulletin 747-53-2272. These airplanes have upper skin
gage of 0.056 inch and are not covered by the post-modification inspections given in Service Bulletin 747-53-2253.
These sections were changed:
1. In the Summary: Added Widespread Fatigue Damage (WFD) statement. Added Planning Table and
new SRP and FTD references. Updated the Action section, related Airworthiness Directives, and
summary illustration.
2. In Paragraph 1.A., Effectivity: RT526, RT530, RT578, RT579, RT654, RT691 and RT692 are moved
from Group 1 to Group 15. Airplane RT631 is moved from Group 16 to new Group 17. Airplane RT632
is moved from Group 16 to new Group 18. Airplanes RR204, RR551, RR552 and RR553 are moved
from Group 4 to new Group 19. Revised some Group descriptions in the Group/Configuration table.
3. In Paragraph 1.C., Reason: Added reason for Revision 3, added WFD statement, and new SRP and
FTD references.
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4. In Paragraph 1.D., Description: Added instructions for post-modification inspections. Added "more
work" statements for Revision 3. Clarified lap joints affected for reference Service Bulletin 747-53A2312.
Removed AD references from related service bulletin table. Added reference Service Bulletin
747-53A2487.
5. In Paragraph 1.E., Compliance: Updated related AD information. Updated compliance Tables 1 and 2
so that existing compliance times are based from the effective dates of related Airworthiness Directives
where applicable. Updated compliance Table 3 to clarify the action and compliance information. Added
compliance tables for Group 16-18 modifications and for Group 1-19 post-modification inspections.
Added information for post-repair inspection requirements.
6. In Paragraph 1.F., Approval: Updated Alternative Method of Compliance (AMOC) statements to reflect
new compliance tables. Added new AMOC statements for AD 2010-26-10, AD 2012-10-03, and AD
2013-16-24. Deleted AMOC statements for ADs that have been superseded.
7. In Paragraph 1.G., Manpower: Revised manpower estimates for modification of some configurations.
Added manpower estimates for post-modification inspections of all Groups.
8. In Paragraph 1.J.1., Existing Data, updated the reference list.
9. In Paragraph 1.K., Publications Affected: Added "or in existing documents" to the Damage Tolerance
Inspection statement.
10. In Paragraph 1.M., Software Accomplishment Summary: This new service bulletin section has been
added.
11. In Paragraph 3.A., General Information: Updated existing general notes and added some new notes
to reflect current standards and requirements. Removed note regarding inspection threshold for skin
panels that have been replaced, this information is now in Paragraph 1.E., Compliance.
12. In Paragraph 3.B., Work Instructions: Updated Group applicability to reflect new Groups. Added
modification instructions for Group 16-18 airplanes. Changed modification and inspection instructions
for Groups 6, 11, 19 airplanes. Added post-repair and post-modification inspection instructions for all
airplanes.
13. In Figures 5, 7, 8-9 and 11-14: Added note for airplanes with doubler installed as given in Service
Bulletin 747-53A2487.
14. In Figure 15: View L reference is clarified. Added note for airplanes with doubler installed during BCF
conversion. Added note for airplanes with doubler installed as given in Service Bulletin 747-53A2487.
15. In Figure 17: Group 16-18 airplanes are added.
16. In Figure 23: Added View M with associated Step 5 and footnote (e) for inspection at Stringer 4L, STA
1960 to STA 2000. Added footnote (f) for airplanes with doubler installed during BCF conversion. Added
footnote (g) for airplanes with doubler installed as given in Service Bulletin 747-53A2487.
17. Figures 24-25: These new figures are added for lap joint modifications for LCF airplanes.
18. Figures 26-35: These new figures are added for post-modification inspections of all Groups.
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19. Figures 36-41: New figures are added for Group 6, 11, 19, airplanes for post-modification inspections
of stringer 6 lap joint modification doublers installed between STA 340 and STA 400 as given in Service
Bulletin 747-53-2272.
20. Revised "cracks found" and "no cracks found" conditions to "any crack found" and "no crack found",
respectively, throughout the service bulletin. Also, added acceptable service bulletin revision levels
when referencing work to be done as given in Service Bulletin 747-53A2817.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
August 11, 2005Original Issue:
October 30, 2008Revision 1:
August 12, 2010Revision 2:
July 15, 2014Revision 3:
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2499Original Issue: August 11, 2005
Revision 3: July 15, 2014
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 41, 42, and 46 Body Skin Lap Joint Inspections and
Modifications
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives data for the inspection and repair of certain fuselage skin longitudinal lap joints. These
inspections and repairs are necessary for safe operation of airplanes past the design goal for economic usage.
Boeing has completed extended pressure fatigue tests on a 747-100SR and a 747-400 fuselage test article.
Analysis of these test results have identified areas of the fuselage lap joints where fatigue cracks can occur.
Boeing has also used updated analysis methods on the 747 skin longitudinal lap joints. Inspection and repair
of these areas is necessary for safe operation of airplanes past the design goal for economic usage.
The inspections in this service bulletin will make sure that fatigue cracks in the overlapping skin at the upper
row of fasteners in certain fuselage lap joints are found and repaired before they become critical. Skin cracks
not detected prior to reaching critical crack length may result in the inability to withstand current regulatory
fail-safe loads, in-flight depressurization of the airplane or loss of structural integrity.
Revision 1: Subsequent to the release of the original issue of this service bulletin, a review of all lap joints was
accomplished for the affected airplanes. It was determined that all lap joints with an upper skin thickness of
0.090 inches or less should be inspected at the times given in Paragraph 1.E., Compliance. In addition, a review
of all service bulletins which recommend repeat inspections was accomplished to determine if the inspections
were appropriate on aging airplanes. This review indicated that certain lap joints where the skin thickness is
less than or equal to 0.071 inches should be modified at the times given in Paragraph 1.E., Compliance.
The skin lap joints affected by this service bulletin have been determined to be structure that is susceptible to
Widespread Fatigue Damage (WFD). For more information about WFD, refer to 747-SL-53-088.
Boeing Service Related Problem (SRP) 747-SRP-53-0211, 747-OP-SRP-53-0279 and 747-SRP-53-0434  are
related to this service bulletin.
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Boeing Fleet Team Digest (FTD) 747 FTD 53-13001 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 85901-91RS)
Lap joint inspection
Do external High Frequency Eddy Current (HFEC) inspections of certain lap joints for cracks. These lap joints
are in Section 41, Section 42, and Section 46. In addition, do internal and external Low Frequency Eddy Current
(LFEC) inspections at certain doublers common to these lap joints. If no crack is found, do the inspection again
at the time shown in this service bulletin. If any crack is found, remove the fastener in the cracked hole and
sufficient adjacent fasteners and do open hole HFEC inspections to find the crack length. Repair before any
more flights. Repair as given in the structural repair manual or ask Boeing for repair data. As part of the repair,
do open-hole HFEC inspections of the skin at all existing fastener locations common to the repair.
Lap joint modification
Do eddy current inspections of the lap joints in sections 41 and 42 that will be modified. If any crack is found,
repair the crack and contact Boeing for lap joint modification instructions. For areas where no crack is found,
do the lap joint modifications.
Lap joint post-modification inspections
Do internal surface HFEC inspections for any crack in the skin or internal doubler at the perimeter fasteners
common to the modification and repeat the inspections. If any crack is found contact Boeing for repair instructions
and do the work instructed by Boeing.
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Group 6, 11, 19:
In addition, at stringer 6 lap joint modification, installed between STA 340 and STA 400, do internal HFEC,
external LFEC and detail inspections for any crack in the skin at perimeter fastener locations common to the
modification. Do external HFEC and detailed inspections for any crack in the external doubler common to the
lap joint. If any crack is found contact Boeing for repair instructions and do the work instructed by Boeing.
EFFECTIVITY
747-200C, 747-200F, 747-400, 747-400D, and 747-400F airplanes. Refer to Paragraph 1.A.1., Airplanes for
the list of affected airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
Federal Aviation Administration (FAA) Airworthiness Directives AD 90-06-06, AD 94-15-17, AD 2004-07-22 R1,
AD 2005-08-01, AD 2006-20-02, AD 2006-22-09, AD 2006-24-02, AD 2006-24-05, AD 2007-15-07, AD
2008-16-14, AD 2009-04-16, AD 2010-26-10, AD 2012-10-03 and AD 2013-16-24 are related to this service
bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection, repair, or modification procedures given in this
service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-53A2499
ALERT  ALERT
DO EXTERNAL SURFACE HFEC INSPECTIONS OF THE SKIN
AROUND THE UPPER ROW OF FASTENERS IN CERTAIN LAP
JOINTS IN SECTION 41, 42 AND 46. IF CRACKS ARE
FOUND, REPAIR BEFORE ANY MORE FLIGHTS AS GIVEN
IN THE SRM.
DO STRUCTURAL MODIFICATIONS AND POST MODIFICATION
INSPECTIONS AS APPLICABLE ON SPECIFIED LAP JOINTS
AT STRINGERS 6 AND 23 IN SECTION 41 AND AT STRINGER 44 IN  SECTIONS 41 AND 42.  W49253
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### Page 15

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2499
Original Issue: August 11, 2005
Revision 3: July 15, 2014
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 41, 42, and 46 Body Skin Lap Joint Inspections and
Modifications
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplanes shown below. Refer to PRR85901-44RS and
PRR85901-91RS for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
747-400 and 747-400D airplanes, line numbers 696 through 1358,
except airplanes modified to Boeing Converted Freighter (BCF)
configuration as of May 31, 2013.
-1
747-200F airplanes, line numbers 242 through 347, that have a main
deck side cargo door.
-2
747-200F airplanes, line numbers 315 through 343, that do not have
a main deck side cargo door.
-3
747-200F airplanes, line numbers 354 through 571, that have a main
deck side cargo door.
-4
747-200F airplane line number 382. This airplane has a main deck
side cargo door.
-5
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DESCRIPTIONCONFIGURATIONGROUP
747-200F airplanes, line numbers 654 through 684.-6
747-200F airplanes, line numbers 687 through 886.-7
747-200C airplane line numbers 287 and 289. These airplanes have
a main deck side cargo door.
-8
747-200C airplanes, line numbers 209 through 327, that do not have
a main deck side cargo door.
-9
747-200C airplane line numbers 416, 438, 524, and 565.-10
747-200C airplane line number 669.-11
747-200C airplane line number 712.-12
747-400F airplanes, line numbers 968 through 1419.-13
747-400 airplanes, line numbers 735 through 1302, that have a main
deck side cargo door, including airplanes modified to BCF
configuration.
-14
747-400 airplanes, line numbers 717 through 1188, that have been
modified to BCF configuration as of May 31, 2013.
-15
747-400 airplane line numbers 904 and 932 that have been modified
to Large Cargo Freighter.
-16
747-400 airplane line number 766 that has been modified to Large
Cargo Freighter.
-17
747-400 airplane line number 778 that has been modified to Large
Cargo Freighter.
-18
747-200F airplanes, line numbers 604 through 625, that have a main
deck side cargo door.
-19
Airplane Models:
747-200C, 747-200F, 747-400, 747-400D, 747-400F
GroupVariable Number
1RF001 - RF006
9RJ131 - RJ133
9RJ151 - RJ152
8RJ301 - RJ302
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GroupVariable Number
10RJ303
11RJ321
12RJ322
10RJ331 - RJ333
13RL401 - RL403
13RL411 - RL436
13RL451 - RL456
13RL461 - RL462
13RL471 - RL481
13RL491 - RL492
13RL501 - RL502
13RL511 - RL516
13RL521 - RL522
13RL531 - RL534
13RL551
13RL561 - RL568
13RL571 - RL572
13RL576 - RL577
13RL579
13RL581 - RL586
13RL651 - RL655
13RL671 - RL675
13RL681 - RL684
13RL751 - RL752
1RM001 - RM007
1RM010 - RM013
1RM021 - RM024
1RM026 - RM030
1RM036 - RM045
1RM051 - RM053
1RM071
1RM081 - RM084
1RM091
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GroupVariable Number
1RM096 - RM097
1RM116 - RM117
1RM126 - RM127
15RM128
1RM129 - RM132
1RM136 - RM147
1RM156 - RM158
1RM166 - RM177
1RM191 - RM192
1RM231 - RM233
1RM241 - RM246
1RM261 - RM264
1RM316 - RM318
1RM331 - RM333
1RM341
1RM351 - RM355
1RM366 - RM367
1RM401 - RM403
1RM426
1RM431
1RM441 - RM443
1RM445
14RM801 - RM803
14RM811 - RM813
13RM851 - RM859
13RM861 - RM863
13RM871 - RM899
13RM901 - RM906
13RM911
3RR001 - RR004
4RR005
4RR021 - RR023
7RR024 - RR025
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GroupVariable Number
4RR031
2RR202
4RR203
19RR204
6RR205
7RR206
2RR221 - RR222
4RR223 - RR226
2RR261
5RR262
4RR263 - RR265
6RR266 - RR267
2RR301 - RR303
4RR304 - RR306
7RR307 - RR310
2RR331
4RR332
4RR336
2RR341 - RR344
4RR345
4RR361 - RR362
4RR421 - RR422
6RR431 - RR432
7RR441 - RR442
7RR451
4RR501 - RR504
4RR521
7RR522
7RR526
4RR531
19RR551 - RR553
7RR554 - RR556
4RR561
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GroupVariable Number
7RR566
13RR701
13RR721 - RR724
13RR746 - RR748
13RR851 - RR856
13RR861 - RR862
13RR951 - RR952
14RT001 - RT014
14RT021 - RT022
14RT031 - RT035
14RT041 - RT047
14RT061
14RT071 - RT075
14RT101 - RT103
14RT121
14RT131 - RT137
14RT151 - RT152
14RT161 - RT168
1RT401 - RT412
1RT431 - RT447
1RT451 - RT455
15RT456
1RT457 - RT460
15RT461
1RT462 - RT469
1RT471 - RT499
15RT501
1RT502 - RT505
15RT506 - RT510
1RT511 - RT512
15RT513
1RT514 - RT515
15RT516
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GroupVariable Number
1RT517
15RT518 - RT520
1RT521 - RT523
15RT524
1RT525
15RT526
1RT527
15RT528
1RT529
15RT530
1RT531 - RT535
1RT551 - RT568
1RT571
15RT572 - RT579
1RT580 - RT591
1RT601 - RT630
17RT631
18RT632
1RT633 - RT641
15RT642
1RT643 - RT653
15RT654 - RT657
1RT671 - RT673
1RT681 - RT682
15RT691 - RT692
1RT693 - RT699
1RT701 - RT704
1RT711 - RT717
1RT741 - RT742
16RT743
1RT744 - RT750
15RT751 - RT752
1RT753 - RT757
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GroupVariable Number
1RT776 - RT777
15RT781 - RT782
1RT783 - RT784
1RT801 - RT803
1RT811 - RT814
1RT831 - RT836
15RT837
1RT861 - RT864
16RT876
1RT877 - RT880
1RT931 - RT932
1RT945 - RT949
1RT951 - RT952
14RT953 - RT954
1RT955
1RT966
15RT967
1RU001 - RU006
1RU016 - RU017
1RU031 - RU032
1RU051 - RU052
1RU059 - RU062
1RU081 - RU083
1RU101 - RU102
1RU121 - RU132
1RU801 - RU809
1RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
This service bulletin gives data for the inspection and repair of certain fuselage skin longitudinal lap
joints. These inspections and repairs are necessary for safe operation of airplanes past the design goal
for economic usage.
Boeing has completed extended pressure fatigue tests on a 747-100SR and a 747-400 fuselage test
article. Analysis of these test results have identified areas of the fuselage lap joints where fatigue cracks
can occur. Boeing has also used updated analysis methods on the 747 skin longitudinal lap joints.
Inspection and repair of these areas is necessary for safe operation of airplanes past the design goal
for economic usage.
The inspections in this service bulletin will make sure that fatigue cracks in the overlapping skin at the
upper row of fasteners in certain fuselage lap joints are found and repaired before they become critical.
Skin cracks not detected prior to reaching critical crack length may result in the inability to withstand
current regulatory fail-safe loads, in-flight depressurization of the airplane or loss of structural integrity.
The skin lap joints affected by this service bulletin have been determined to be structure that is
susceptible to Widespread Fatigue Damage (WFD). For more information about WFD, refer to
747-SL-53-088.
Boeing Service Related Problem (SRP) 747-SRP-53-0211, 747-OP-SRP-53-0279 and 747-SRP-53-0434
are related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 53-13001 is related to this service bulletin.
Revision 1: Subsequent to the release of the original issue of this service bulletin, a review of all lap
joints was accomplished for the affected airplanes. It was determined that all lap joints with an upper
skin thickness of 0.090 inches or less should be inspected at the times given in Paragraph 1.E.,
Compliance. In addition, a review of all service bulletins which recommend repeat inspections was
accomplished to determine if the inspections were appropriate on aging airplanes. This review indicated
that certain lap joints where the skin thickness is less than or equal to 0.071 inches should be modified
at the times given in Paragraph 1.E., Compliance.
Revision 1 is sent to expand the eddy current inspection areas and to add lap joint modifications for
specific lap joints. A detailed list of changes is given in the Revision Transmittal Sheet section of
Revision 1.
Revision 2 is sent to revise the modification drawings that are specified for stringer 6 lap joint
modification. New Groups 15 and 16 have also been created for airplanes modified by Boeing to Boeing
Converted Freighter (BCF), and airplanes modified to Large Cargo Freighter (LCF). BCF airplanes
have unique inspection requirements. A detailed list of changes is given in the Revision Transmittal
Sheet section of Revision 2.
Revision 3 is sent to add modification instructions and compliance information for Large Cargo Freighter
(LCF) airplanes and to add post-modification inspections for all airplanes. This revision is also sent to
add post-modification inspections for Group 6, 11 and 19 airplanes with stringer 6 lap joint modification
installed between STA 340 and STA 400 as given in Service Bulletin 747-53-2272. These airplanes
have upper skin gage of 0.056 inch and are not covered by the post-modification inspections given in
Service Bulletin 747-53-2253.
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D. Description
Lap joint inspection
Do external High Frequency Eddy Current (HFEC) of certain lap joints for cracks. These lap joints are
in Section 41, Section 42, and Section 46. In addition, do internal and external Low Frequency Eddy
Current (LFEC) inspections at certain doublers common to these lap joints. If no crack is found, do the
inspection again at the time shown in this service bulletin. If any crack is found, remove the fastener
in the cracked hole and sufficient adjacent fasteners and do open hole HFEC inspections to find the
crack length. Repair before any more flights. Repair as given in the structural repair manual or ask
Boeing for repair data. As part of the repair, do open-hole HFEC inspections of the skin at all existing
fastener locations common to the repair.
Lap joint modification
Do eddy current inspections of the lap joints in sections 41 and 42 that will be modified. If any crack is
found, repair the crack and contact Boeing for lap joint modification instructions. For areas where no
crack is found, do the lap joint modifications.
Lap joint post-modification inspections
Do internal surface HFEC inspections for any crack in the skin or internal doubler at the perimeter
fasteners common to the modification and repeat the inspections. If any crack is found contact Boeing
for repair instructions and do the work instructed by Boeing.
Group 6, 11, 19:
In addition, at stringer 6 lap joint modification, installed between STA 340 and STA 400, do internal
HFEC, external LFEC and detail inspections for any crack in the skin at perimeter fastener locations
common to the modification. Do external HFEC and detailed inspections for any crack in the external
doubler common to the lap joint. If any crack is found contact Boeing for repair instructions and do the
work instructed by Boeing.
Effectivity is divided into 19 groups due to configuration differences.
Revision 1 - More work is necessary on airplanes changed as given in the initial release of this service
bulletin. The eddy current inspection areas have been expanded and lap joint modifications are necessary
in specific areas at the time given in Paragraph 1.E., Compliance.
Revision 2 - No more work is necessary on airplanes changed as given in the original issue or Revision
1 of this service bulletin.
Revision 3 - More work is necessary on airplanes that had lap joint modifications accomplished as
given in previous revisions of this service bulletin before 20,000 total flight cycles. Post-modification
inspections will be required within 15,000 flight cycles after modification in order to allow continued
operation to the Limit of Validity (LOV) of 35,000 total flight cycles.
Revision 3 - In addition, more work is necessary on airplane line numbers 604 - 685 that had external
doublers installed as given in Service Bulletin 747-53-2272 at Stringer 6 from Station 340 to Station
400. Post-modification inspection at Stringer 6 from Station 340 to Station 400 is now required as given
in this service bulletin.
NOTE: The related service bulletin for 747-100, 747-200B, 747-300, 747SP, and 747SR
airplanes is 747-53A2367.
1.
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2. If the external skin panel of an affected lap joint has been replaced, start to do the
inspections of that lap joint 22,000 full pressure flight cycles after the skin panel was
replaced.
3. At all lap joints not covered by the lap joint modification given in this service bulletin,
additional inspections and/or a lap joint modification must be accomplished at 35,000
total flight cycles. Boeing is not planning to provide inspection methods and
engineering drawings for the modification.
4. Because of the extent of the work required to accomplish the modification in this
Service Bulletin, jacking and support of the airplane will be necessary. Boeing can
provide a jacking plan for the incorporation of the bulletin. To have Boeing assist in
developing jacking/support recommendations the following is required:
— A list of structures related Service Bulletins to be incorporated.
— The exact airplane configuration including weight and center of gravity.
— Whether the following will be installed or removed: landing gear, flaps, engines,
pylons and interiors.
— The airplane identification (line number or variable number).
— List the lap joints to be modified and lap the joints that require repair (if possible).
— Provide the planned incorporation date for the bulletin modification. Provide
adequate time for Boeing to develop the necessary data and for any required
contacts or agreements to be developed.
5. Some of the lap joints shown in this service bulletin are also affected by other Service
Bulletins as shown in the tables that follow. The information in these tables is for
reference only, and no prior or concurrent work is required for this service bulletin.
Lap Joints AffectedEffectivitySubjectService Bul-
letin Number
S-34, S-39, and S-44 from
STA 741 to STA 841 and S-
34, S-40 and S-46 from STA
1641 to STA 1741 (Lower lobe
lap splices at the wing to body
fairings.)
All 747s line number 201 - 814Fuselage - Skin - Lap Splice
Upper Countersunk Fastener
Row Inspection Repair and
Modification at Wing-To Body
Fairing
747-53A2312
S-12, from STA 520 to STA
740
All 747s line number 201 - 230Fuselage - Skin - Body Skin
Lap Joint Inspection and Fas-
tener Replacement at Stringer
12 From Body Station 520 to
741.1
747-53-2366
S-6, from STA 340 to STA 520All 747sFuselage - Skin - Inspection
for Cracks at Multiple Sites in
Fuselage Skin Lap Joints
747-53A2501
S-6, from STA 340 to 400747 airplanes, line numbers 1
- 603
Fuselage - Nose Section -
Station 340 to 400 Stringer 6
Inspection and Modification
747-53-2253
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Lap Joints AffectedEffectivitySubjectService Bul-
letin Number
S-6, from STA 400 to 520747 airplanes, line numbers 1
- 628
Fuselage - Nose Section -
Station 400 to 520 Stringer
Lap Splice Inspection, Repair
and Modification
747-53A2303
S-6, from STA 340 to 400747 airplanes, line numbers 1
- 603
Fuselage - Skin - Fuselage
Skin at Stringer 6, from STA
340 to STA 400 - Inspection,
Repair, and Modification
747-53A2748
S-34L, from STA 1640 to STA
1740
All 747 airplanes with a Main
Deck Side Cargo Door (MD-
SCD), including airplanes that
have been modified by Boeing
to add a MDSCD.
Fuselage - Section 46 - Sta-
tion 1640 to 1740 Left Side at
Stringer 34 - Skin Panel In-
spection for Cracking
747-53A2487
All Section 41 lap jointsAll 747-SP, 747-SR, 747-100,
747-100B, 747-100BSUD,
747-200B, 747-200C, 747-
200F and 747-300 airplanes
line number 1 through 685,
686, 688, 690 - 695.
Fuselage - Nose Section 41
Body Frame Structure Re-
placement and Reinforcement
747-53-2272
NOTE: The service bulletin that follows includes a repair and a modification that affects the lap joint
at S-44L from STA 560 to STA 580. This service bulletin provides the appropriate inspection
instructions for affected airplanes that have been repaired or modified as given in Service
Bulletin 747-53-2386.
Lap Joints AffectedEffectivitySubjectService Bul-
letin Number
S-44L, from STA 560 to STA
580
All 747s line number 1 - 886,
except 747-400s
Fuselage - Skin - Skin Inspec-
tion, Repair, and Modification
at the Body Station 570
Equipment Cooling Outlet
747-53-2386
NOTE: Boeing recommends that Service Bulletin 747-53A2563, "Fuselage - Skin - Inspections of the
Fuselage Skin and Butt Joint Splice Straps for Scribe Lines" be done prior to installation of
any modification doublers as given in this service bulletin. If the scribe line inspections are
not done prior to installation of modification doublers, it may be necessary to remove the
doublers at a later time to do scribe line inspections.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 115, 116, 117, 118, 121, 122,
123, 124, 125, 126, 127, 128, 141, 142, 143,
144, 145, 146, 147, 148, 151, 152, 211, 212,
221, 222, 223, 224, 225, 226, 231, 232, 241,
242, 243, 244, 251, 252, 253, 254, 261, 262,
263, 264, 271, 272, 273, 274
747-400, 747-400D
Group 2-7, 19:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 115, 116, 117, 118, 121, 122,
123, 124, 125, 126, 127, 128, 141, 142, 143,
144, 145, 146, 147, 148, 151, 152, 211, 212,
221, 222, 223, 224, 225, 226, 231, 232, 233,
234, 241, 242, 243, 244, 251, 252, 253, 254,
261, 262, 263, 264, 271, 272, 273, 274
747-200F
Group 8-12:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 115, 116, 117, 118, 121, 122,
123, 124, 125, 126, 127, 128, 141, 142, 143,
144, 145, 146, 147, 148, 151, 152, 211, 212,
221, 222, 223, 224, 225, 226, 231, 232, 233,
234, 241, 242, 243, 244, 251, 252, 253, 254,
261, 262, 263, 264, 271, 272, 273, 274
747-200C
Group 13:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 115, 116, 117, 118, 121, 122,
123, 124, 125, 126, 127, 128, 141, 142, 143,
144, 145, 146, 147, 148, 151, 152, 211, 212,
221, 222, 223, 224, 225, 226, 231, 232, 233,
234, 241, 242, 243, 244, 251, 252, 253, 254,
261, 262, 263, 264, 271, 272, 273, 274
747-400F
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Group 14-15:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 115, 116, 117, 118, 121, 122,
123, 124, 125, 126, 127, 128, 141, 142, 143,
144, 145, 146, 147, 148, 151, 152, 211, 212,
221, 222, 223, 224, 225, 226, 231, 232, 241,
242, 243, 244, 251, 252, 253, 254, 261, 262,
263, 264, 271, 272, 273, 274
747-400
Group 16-18:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 115, 116, 117, 118, 211, 212,
221, 222, 223, 224, 225, 121A, 122A, 125A,
126A
747-400
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directives AD 90-06-06, AD 94-15-17, AD
2004-07-22 R1, AD 2005-08-01, AD 2006-20-02, AD 2006-22-09, AD 2006-24-02, AD 2006-24-05,
AD 2007-15-07, AD 2008-16-14, AD 2009-04-16, AD 2010-26-10, AD 2012-10-03 and AD 2013-16-24
are related to this service bulletin.
The effective date of AD 2006-05-09 is April 13, 2006.
The effective date of AD 2010-26-10 is February 1, 2011.
Group 2-5, 8-10:
For airplanes that have Stringer 6, Station 340 - 400, external doublers installed as given in Service
Bulletin 747-53-2272 or Service Bulletin 747-53-2253: No action is required by this service bulletin at
Stringer 6, Station 340 - 400. Do post-modification inspections as given in Service Bulletin 747-53-2253.
Group 2-5, 8-10, 19:
For airplanes that have Stringer 6, Station 400 - 520, external doublers installed as given in Service
Bulletin 747-53A2303: No action is required by this service bulletin at Stringer 6, Station 400 - 520. Do
post-modification inspections as given in Service Bulletin 747-53A2303.
Group 6, 11, 19:
For airplanes that have Stringer 6, Station 340 - 400, external doublers installed as given in Service
Bulletin 747-53-2272: Modification is not required by this service bulletin at Stringer 6, Station 340 -
400. Do post-modification inspections as given in this service bulletin.
For areas where a lap joint SRM repair was installed and the repair doubler(s) is greater than or equal
to 40 inches long, refer to Table 1.
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For areas where a lap joint SRM repair was installed and the repair doubler(s) is less than 40 inches
long, refer to the applicable SRM or Boeing 747 RAG (Document D6-36181, "Repair Assessment
Guidelines - Model 747") for inspection requirements (including inspection method and compliance
time).
Group 1-15, 19:
Table 1 - Lap Joint Inspection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs Later)ActionCondition
-Within 1,000
flight cycles af-
ter the effective
date of AD
2006-05-09.
Within 3,000
flight cycles af-
ter the last
HFEC inspec-
tion of the area
as given in the
SSID.
Before
22,000 total
flight cycles.
(h)
Do the Area 1 eddy
current inspections
for cracks in the
skin as given in
Paragraph 3.B.,
Work Instructions,
PART 1.
All airplanes
(c)
-Within 1,000
flight cycles af-
ter the effective
date of AD
2010-26-10.
Within 3,000
flight cycles af-
ter the last
HFEC inspec-
tion of the area
as given in the
SSID.
Before
22,000 total
flight cycles.
(h)
Do the Area 2 eddy
current inspections
for cracks in the
skin as given in
Paragraph 3.B.,
Work Instructions,
PART 2.
All airplanes
(c)
-Before further flight.Repair the lap joint
as given in Para-
graph 3.B., Work
Instructions, PART
1 or PART 2.
Any crack found.
(g)
1,500 flight cy-
cles
Within 1,000
flight cycles af-
ter the Revision
3 date of this
service bulletin.
Within 1,500 flight cycles after
the last inspection.
Repeat the inspec-
tion for cracks as
given in Paragraph
3.B., Work Instruc-
tions, PART 1 and
PART 2
No crack is found, at
Stringer 4 left, be-
tween STA 1720 and
STA 1740, and be-
tween STA 1960 and
STA 1980
(b) (f)
2,400 flight cy-
cles, or 1,500
flight cycles for
airplanes with
more than
30,000 total flight
cycles.
Within 1,000
flight cycles af-
ter the Revision
3 date of this
service bulletin.
Within 2,400 flight cycles after
the last inspection, or within
1,500 flight cycles after the
last inspection for airplanes
with more than 30,000 total
flight cycles.
Repeat the inspec-
tion for cracks as
given in Paragraph
3.B., Work Instruc-
tions, PART 1 and
PART 2
No crack is found, in
the area covered by
external doublers in-
stalled in accordance
with Boeing Service
Bulletin 747-53-2386.
(a) (b) (f)
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Group 1-15, 19:
Table 1 - Lap Joint Inspection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs Later)ActionCondition
3,000 flight cy-
cles, or 1,500
flight cycles for
airplanes with
more than
30,000 total flight
cycles.
Within 3,000 flight cycles after the last inspec-
tion, or within 1,500 flight cycles after the last
inspection for airplanes with more than 30,000
total flight cycles.
Repeat the inspec-
tion for cracks as
given in Paragraph
3.B., Work Instruc-
tions, PART 1 and
PART 2.
Any areas where no
crack is found, except
at Stringer 4 left, be-
tween STA 1720 and
STA 1740, and be-
tween STA 1960 and
STA 1980 and in the
area covered by exter-
nal doublers installed
in accordance with
Boeing Service Bul-
letin 747-53-2386.
(a) (b) (f)
3,000 flight cy-
cles, or 1,500
flight cycles for
airplanes with
more than
30,000 total flight
cycles.
Within 15,000 flight cycles after the repair was
installed.
Accomplish internal
HFEC inspections
for cracks as given
in the applicable
747 SRM or D6-
36181, "Repair As-
sessment Guide-
lines - Model 747."
Areas where a lap
joint repair was in-
stalled as given in
Paragraph 3.B., Work
Instructions of this
service bulletin, and
the repair doubler is
greater than or equal
to 40 inches long.(g)
(a) (b) (e) (f)
(a) For laps joints specified in Paragraph 3.B., Work Instructions, PART 3: On airplanes with more than 30,000
total flight cycles, reduce the inspection interval to 1,500 flight cycles until the lap joint modification given
in Paragraph 3.B., Work Instructions, PART 3 is accomplished.
(b) Accomplishment of a lap joint modification as given in Paragraph 3.B., Work Instructions, PART 3 terminates
the repeat inspections as given in Paragraph 3.B., Work Instructions, PART 1 and PART 2 for the length
of the lap joint that is modified.
(c) The Supplemental Structural Inspection Document (SSID) D6-35022, Revision G for SSI's F-25G, F-25H,
and F-25I provides inspection options for the subject lap joints. Only the HFEC inspection will allow this
compliance time.
(d) This information is deleted.
(e) At tear straps and frame shear ties, where skin is not inspectable for less than 4 inches, HFEC inspection
is not required.
(f) This inspection is for cracks in the upper skin under the external doubler(s).
(g) Until the structural modification as given in Paragraph 3.B., Work Instructions, PART 3 is installed, any
inspection or replacement requirements as given in the applicable 747 SRM must be accomplished.
(h) If a skin panel requiring inspection has been replaced, the threshold for the inspections of that skin panel
can be calculated from the time when the skin panel was replaced.
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Group 1-15, 19:
Table 2 - Lap Joint Modification.
Compliance Time (Whichever Occurs Later)ActionCondition
Within 3,000 flight cycles
after the effective date of
AD 2010-26-10.
Before 30,000 total
flight cycles.
(f)
Do the lap joint modification as given
in Paragraph 3.B., Work Instructions,
PART 3.
All airplanes.
(a) (b) (c) (d) (e)
(a) Accomplishment of a lap joint modification as given in Paragraph 3.B., Work Instructions, PART 3 terminates
the repeat inspections required by Compliance Table 1 for the length of the lap joint that is modified.
(b) For lap joints specified in Paragraph 3.B., Work Instructions, PART 3: On airplanes with more than 30,000
total flight cycles, the repeat inspection intervals in Compliance Table 1 must be reduced to 1,500 flight
cycles until the lap joint modification is accomplished.
(c) The external modification doubler installation as given in Service Bulletin 747-53A2499, Revision 1 or
Revision 2 meets the requirements of the modification as given in this service bulletin revision.
(d) It is not necessary to accomplish this modification between STA 340 and STA 400 at the Stringer 6 lap
joints if an external doubler modification has already been installed as given in Service Bulletin 747-53-
2272 or Service Bulletin 747-53-2253. For airplane line numbers 201 through 685, the requirement to install
external doublers at the Stringer 6 lap joints between STA 340 and STA 400 at or before 20,000 total flight
cycles, as given in Service Bulletin 747-53-2272 or Service Bulletin 747-53-2253, remains applicable.
(e) It is not necessary to accomplish this modification between STA 400 and STA 520 at the Stringer 6 lap
joints if an external doubler modification has already been installed as given in Service Bulletin 747-
53A2303. For airplane line numbers 201 through 628, the requirement to install external doublers at the
Stringer 6 lap joints between STA 400 and STA 520 at or before 23,000 total flight cycles, as given in
Service Bulletin 747-53A2303 (AD 90-06-06), remains applicable.
(f) Any Airworthiness Directive having an earlier compliance time for modification should be complied with
instead of the compliance time stated in this table.
Group 16-18:
Table 3 - Lap Joint Inspection.
Compliance TimeActionCondition
As given in Service Bulletin 747-53A2817, Original
Issue, Revision 1
Do the inspections of lap joints as
given in Service Bulletin 747-
53A2817, Original Issue, Revision
1
All airplanes.
(a)
(a) If a skin panel requiring inspection has been replaced, the threshold for the inspections of that skin panel
can be calculated from the time when the skin panel was replaced.
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### Page 32

Group 16:
Table 4 - Lap Joint Modification.
Compliance Time (Whichever Occurs Later)ActionCondition
Within 1,000
flight cycles af-
ter the Revi-
sion 3 date of
this service
bulletin.
Before 25,000 total flight cycles.Do the lap joint modification as giv-
en in Paragraph 3.B., Work Instruc-
tions, PART 3
(a)
All airplanes.
(a) Accomplishment of a lap joint modification as given in Paragraph 3.B., Work Instructions, PART 3 termi-
nates the inspections required by Compliance Table 3 for the length of the lap joint that is modified.
Group 17:
Table 5 - Lap Joint Modification.
Compliance Time (Whichever Occurs Later)ActionCondition
Within 1,000
flight cycles af-
ter the Revi-
sion 3 date of
this service
bulletin.
Before 30,000 total flight cyclesDo the lap joint modification as giv-
en in Paragraph 3.B., Work Instruc-
tions, PART 3.
(a)
All airplanes.
(a) Accomplishment of a lap joint modification as given in Paragraph 3.B., Work Instructions, PART 3 termi-
nates the inspections required by Compliance Table 3 for the length of the lap joint that is modified.
Group 18:
Table 6 - Lap Joint Modification.
Compliance Time (Whichever Occurs Later)ActionCondition
Within 1,000
flight cycles af-
ter the Revi-
sion 3 date of
this service
bulletin.
Before 26,000 total flight cycles.Do the lap joint modification as giv-
en in Work Instructions Paragraph
3.B.3., PART 3.
(a)
All airplanes.
(a) Accomplishment of a lap joint modification as given in Paragraph 3.B., Work Instructions, PART 3 termi-
nates the inspections required by Compliance Table 3 for the length of the lap joint that is modified.
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Group 2-5, 8-10:
Table: 7 - Lap Joint Post-Modification Inspection - Areas with External Doublers installed as given in
this Service Bulletin (Stringer 6, Stringer 23 and Stringer 44).
Repeat Inter-
val (Not to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 10,000 flight
cycles after accom-
plishing the modifica-
tion at Stringer 6, be-
tween STA 340 and
STA 400 as given in
Paragraph 3.B.,
Work Instructions,
PART 3.
Do internal detailed and surface
HFEC inspections for any crack
in the skin or internal doubler
along the edge fastener rows of
the modification at Stringer 6,
between STA 340 and STA 400
as given in Paragraph 3.B.,
Work Instructions, PART 4.
(a) (c)
Airplanes with lap
joints modified as
given in Paragraph
3.B., Work Instruc-
tions, PART 3.
AND
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 15,000 flight
cycles after accom-
plishing the modifica-
tion at Stringer 6, be-
tween STA 400 and
STA 520; at Stringer
23; and at Stringer
44 as given in Para-
graph 3.B., Work In-
structions, PART 3.
Do internal detailed and surface
HFEC inspections for any crack
in the skin or internal doubler
along the edge fastener rows of
the modification at Stringer 6,
between STA 400 and STA 520;
at Stringer 23; and at Stringer
44 as given in Paragraph 3.B.,
Work Instructions, PART 4.
(b) (c)
-Before further flight.Contact Boeing for repair instruc-
tions and do the repair.
Any crack found.
3,000 flight cy-
cles.
--In unrepaired areas: Repeat the
internal detailed and surface
HFEC inspections for cracks in
the skin or internal doubler
along the edge fastener rows of
the modification as given in
Paragraph 3.B., Work Instruc-
tions, PART 4.
No crack found.
(a) This action is only required if external doublers were installed as given in this service bulletin at Stringer
6, between STA 340 and STA 400, as an alternative method of compliance to AD 90-06-06 or AD 2013-
16-24. If external doublers were already installed as given in Service Bulletin 747-53-2272 or Service
Bulletin 747-53-2253, then do the post-modification inspections as given in Service Bulletin 747-53-2253.
(b) This action is only required at Stringer 6, between STA 400 and STA 520, if doublers were installed as
given in this service bulletin as an alternative method of compliance to AD 90-06-06. If external doublers
were already installed as given in Service Bulletin 747-53A2303, then do the post-modification inspections
as given in Service Bulletin 747-53A2303.
(c) If lap joints were modified at different times, each modified area must be inspected within the specified
number of flight since that area was modified.
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Group 6, 11, 19:
Table 8 - Post-Modification Inspections of Stringer 6 Lap Joint Modification Installed Between STA 340
and STA 400 as given in Service Bulletin 747-53-2272.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 10,000 flight cy-
cles after installation of
the Stringer 6 Skin Lap
Splice Modification
Doubler Between STA
340 and STA 400 as
given in Service Bulletin
747-53-2272.
Do external detailed and
LFEC inspections of the up-
per and lower skin panels for
cracking at locations around
the perimeter of the doublers
as given in Paragraph 3.B.,
Work Instructions, PART 5,
Step a.
All airplanes
(a)
(a) (b)(c)
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 10,000 flight cy-
cles after installation of
the Stringer 6 Skin Lap
Splice Modification
Doubler Between STA
340 and STA 400 as
given in Service Bulletin
747-53-2272.
Do external detailed and
HFEC inspections of the ex-
ternal doubler for cracking at
locations common to the S-
6 lap joint as given in Para-
graph 3.B., Work Instruc-
tions, PART 5, Step b.
(c)
(a)
(a) (b)
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 15,000 flight cy-
cles after installation of
the Stringer 6 Skin Lap
Splice Modification
Doubler Between STA
340 and STA 400 as
given in Service Bulletin
747-53-2272.
Do internal detailed and
HFEC inspections of the up-
per and lower skin panels for
cracking at locations around
the perimeter of the doublers
as given in Paragraph 3.B.,
Work Instructions, PART 5,
Step c.
(a)
(a) (b)(c)
-Before further flight.Contact Boeing for repair in-
structions and do the repair.
Any crack found.
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### Page 35

Group 6, 11, 19:
Table 8 - Post-Modification Inspections of Stringer 6 Lap Joint Modification Installed Between STA 340
and STA 400 as given in Service Bulletin 747-53-2272.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
1,000 flight cy-
cles.
Within 1,000 flight cycles after the previ-
ous inspection of the skin as given in
Paragraph 3.B., Work Instructions, PART
5, Step a.
In unrepaired areas: Repeat
the external detailed and
LFEC inspections of the up-
per and lower skin panels for
cracking at locations around
the perimeter of the doublers
as given in Paragraph 3.B.,
Work Instructions, PART 5,
Step a.
No crack found.
(a)
(a)
3,000 flight cy-
cles.
Within 3,000 flight cycles after the previ-
ous inspection of the doubler as given in
Paragraph 3.B., Work Instructions, PART
5, Step b.
In unrepaired areas: Repeat
the external detailed and
HFEC inspections of the ex-
ternal doubler for cracking at
locations common to the S-
6 lap joint as given in Para-
graph 3.B., Work Instruc-
tions, PART 5, Step b.
(a)
(a)
3,000 flight cy-
cles.
Within 3,000 flight cycles after the previ-
ous inspection of the skin as given in
Paragraph 3.B., Work Instructions, PART
5, Step c.
In unrepaired areas: Repeat
the internal detailed and
HFEC inspections of the up-
per and lower skin panels for
cracking at locations around
the perimeter of the doublers
as given in Paragraph 3.B.,
Work Instructions, PART 5,
Step c.
(a)
(a)
(a) 35,000 total flight cycles is the Limit Of Validity (LOV) for model 747 airplanes.
(b) If the left and right side modifications were installed at different times, each modification must be inspected
within the specified number of flight cycles since that modification was installed.
(c) Also do inspections of Stringer 6 from STA 400 to STA 520, Stringer 23, and Stringer 44 as given in
compliance Table 9.
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Group 6, 11, 19:
Table: 9 - Lap Joint Post-Modification Inspection - Areas with External Doublers installed as given in
this Service Bulletin (Stringer 6, Stringer 23 and Stringer 44).
Repeat Inter-
val (Not to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 10,000 flight
cycles after accom-
plishing the modifica-
tion at Stringer 6, be-
tween STA 340 and
STA 400 as given in
Paragraph 3.B.,
Work Instructions,
PART 3.
Do internal detailed and surface
HFEC inspections for any crack
in the skin or internal doubler
along the edge fastener rows of
the modification at Stringer 6,
between STA 340 and STA 400
as given in Paragraph 3.B.,
Work Instructions, PART 4.
(a) (c)
Airplanes with lap
joints modified as
given in Paragraph
3.B., Work Instruc-
tions, PART 3.
AND
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 15,000 flight
cycles after accom-
plishing the modifica-
tion at Stringer 6, be-
tween STA 400 and
STA 520; at Stringer
23; and at Stringer
44 as given in Para-
graph 3.B., Work In-
structions, PART 3.
Do internal detailed and surface
HFEC inspections for any crack
in the skin or internal doubler
along the edge fastener rows of
the modification at Stringer 6,
between STA 400 and STA 520;
at Stringer 23; and at Stringer
44 as given in Paragraph 3.B.,
Work Instructions, PART 4.
(b) (c)
-Before further flight.Contact Boeing for repair instruc-
tions and do the repair.
Any crack found.
3,000 flight cy-
cles.
--In unrepaired areas: Repeat the
internal detailed and surface
HFEC inspections for cracks in
the skin or internal doubler
along the edge fastener rows of
the modification as given in
Paragraph 3.B., Work Instruc-
tions, PART 4.
No crack found.
(a) This action is only required if external doublers were installed as given in this service bulletin at Stringer
6, between STA 340 and STA 400. If external doublers were already installed as given in Service Bulletin
747-53-2272, then do the post-modification inspections of Stringer 6, between STA 340 and STA 400 as
given in compliance Table 8.
(b) For Group 19 airplanes (line numbers 604 - 628), this action is only required at Stringer 6, between STA
400 and STA 520, if doublers were installed as given in this service bulletin as an alternative method of
compliance to AD 90-06-06. If external doublers were already installed as given in Service Bulletin 747-
53A2303, then do the post-modification inspections as given in Service Bulletin 747-53A2303.
(c) If lap joints were modified at different times, each modified area must be inspected within the specified
number of flight since that area was modified.
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Group 1, 7, 12-18:
Table 10 - Lap Joint Post-Modification Inspection.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 1,000
flight cycles after
the Revision 3
date of this ser-
vice bulletin.
Within 15,000 flight cy-
cles after accomplish-
ing the modification as
given in Paragraph
3.B., Work Instructions,
PART 3.
Do internal detailed and sur-
face HFEC inspections for
any crack in the skin or inter-
nal doubler along the edge
fastener rows of the modifica-
tion as given in Paragraph
3.B., Work Instructions,
PART 4.
Airplanes with lap
joints modified as
given in Paragraph
3.B., Work Instruc-
tions, PART 3.
(a)
(a)
-Before further flight.Contact Boeing for repair in-
structions and do the repair.
Any crack found.
3,000 flight cy-
cles (a)
Within 3,000 flight cycles after the previ-
ous inspection. (a)
In unrepaired areas: Repeat
the internal detailed and
surface HFEC inspections
for any crack in the skin or
internal doubler along the
edge fastener rows of the
modification as given in
Paragraph 3.B., Work Instruc-
tions, PART 4.
No crack found.
(a) 35,000 total flight cycles is the Limit Of Validity (LOV) for model 747 airplanes.
F. Approval
This Service Bulletin (SB) was examined by the Federal Aviation Administration (FAA). The changes
specified in this SB 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 SB effectivity. This SB 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 SB, the operator is responsible for obtaining appropriate regulatory agency approval before
incorporating this SB.
This SB has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification
Office (ACO) approves the accomplishment of the inspection, repair, and modification procedures with
the corresponding compliance times specified in Tables 1 - 10 under paragraph 1.E., "Compliance",
of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the inspections and repairs
required by paragraphs (h) and (i) of AD 2004-07-22 R1, for the inspection of Structural Significant
Items (SSI) F-25G, F-25H, and F-25I of Supplemental Structural Inspection Document (SSID) 06-35022,
Revision G. This AMOC only applies to the areas inspected by this SB. When this SB specifies contacting
Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with
paragraph (l) of the AD. All provisions of AD 2004-07-22 R1 that are not specifically referenced in this
paragraph, including the initial inspection threshold and repeat intervals per paragraph (h) and (i) of
AD 2004-07-22 R1, remain fully applicable and must be complied with accordingly until the inspections
in this SB begin.
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In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4-10 under paragraph 1.E.,
"Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the inspections
and repairs required by paragraphs (h), and (i) of AD 2004-07-22 R1, for the inspection of SSI F-25K
of SSID D6-35022, Revision G. This AMOC only applies to the areas modified by this SB. When this
SB specifies contacting Boeing for repair instructions, the repair instructions must be approved by the
FAA in accordance with paragraph (l) of the AD. All provisions of AD 2004-07-22 R1 that are not
specifically referenced in this paragraph, including the initial inspection threshold and repeat intervals
per paragraph (h) and (i) of AD 2004-07-22 R1, remain fully applicable and must be complied with
accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the inspection
procedures with the corresponding compliance times specified in Tables 1 and 3 (as applicable), under
paragraph 1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment
of the post-modification inspection requirements with the corresponding compliance times required by
paragraph (p) of AD 2008-16-14. This AMOC is only for areas where inspections are done in accordance
with this SB. When this SB specifies contacting Boeing for repair instructions, the repair instructions
must be approved by the FAA in accordance with paragraph (v) of the AD. All provisions of AD
2008-16-14 that are not specifically referenced in this paragraph remain fully applicable and must be
complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the inspection and
repair procedures with the corresponding compliance times specified in Table I, under paragraph 1.E.,
"Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the
post-modification inspection and repair requirements with the corresponding compliance times required
by paragraph (c) of AD 94-15-17. This AMOC is only for areas where inspections are done in accordance
with this SB. When this SB specifies contacting Boeing for repair instructions, the repair instructions
must be approved by the FAA in accordance with paragraph (d) of the AD. All provisions of AD 94-15-17
that are not specifically referenced in this paragraph remain fully applicable and must be complied with
accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures with the corresponding compliance times specified in
Tables 2, 4- 10 (as applicable) under paragraph 1.E., "Compliance", of SB 747-53A2499, Revision 3,
as an AMOC to the accomplishment of the inspection requirements with the corresponding compliance
times required by paragraph (g) of AD 2006-22-09. This AMOC is only for areas where modification
doublers have been installed in accordance with this SB. When this SB specifies contacting Boeing
for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph
(j) of the AD. All provisions of AD 2006-22-09 that are not specifically referenced in this paragraph
remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO also approves the accomplishment of the modification
and post-modification inspection procedures with corresponding compliance times specified in Tables
2, 4- 10 (as applicable) under paragraph 1.E., "Compliance", of SB 747-53A2499, Revision 3, as an
AMOC to the accomplishment of the modification and post-modification inspections required by
paragraphs (m), and (n) of AD 2013-16-24. This AMOC is only for areas where Stringer 6 external
doublers are installed in accordance with this SB. This AMOC is not valid for the modification threshold.
The modification threshold given in AD 2013-16-24, paragraphs (m) remains in effect. When this SB
specifies contacting Boeing for repair instructions, the repair instructions must be approved by the FAA
in accordance with paragraph (q) of the AD. All provisions of AD 2013-16-24 that are not specifically
referenced in this paragraph remain fully applicable and must be complied with accordingly.
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In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4- 10 (as applicable), under paragraph
1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the
inspection and modification required by paragraphs (g), (i), (j) and (o) of AD 2012-10-03. This AMOC
is valid only for areas where the external doublers are installed in accordance with SB 747-53A2499.
When this SB specifies contacting Boeing for repair instructions, the repair instructions must be approved
by the FAA in accordance with paragraph (q) of the AD 2012-10-03. All provisions of AD 2012-10-03
that are not specifically referenced in this paragraph including the compliance time for modification
remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4- 10 (as applicable) under paragraph
1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the
inspection and modification required by paragraphs (g), (i), and (j) of AD 2009-04-16. This AMOC is
valid only for areas where the external doublers are installed in accordance with SB 747-53A2499,
Revision 3. When this SB specifies contacting Boeing for repair instructions, the repair instructions
must be approved by the FAA in accordance with paragraph (k) of the AD. All provisions of AD
2009-04-16 that are not specifically referenced in this paragraph including the compliance time for
modification remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures with the corresponding compliance times specified in
Tables 2, 4- 10 (as applicable) under paragraph 1.E., "Compliance", of SB 747-53A2499, Revision 3,
as an AMOC to the accomplishment of the inspection procedures with the corresponding compliance
times specified in Table 1, under paragraph 1.E., "Compliance", of SB 747-53A2675, dated October
12, 2006, required by paragraph (f) of AD 2006-24-05. This AMOC is only for areas where stringer 6
modification doublers have been installed in accordance with this SB. When this SB specifies contacting
Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with
paragraph (j) of the AD. All provisions of AD 2006-24-05 that are not specifically referenced in this
paragraph remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures with the corresponding compliance times specified in
Tables 2, 4- 10 (as applicable) under paragraph 1.E., "Compliance", of SB 747-53A2499, Revision 3,
as an AMOC to the accomplishment of the inspection requirements with the corresponding compliance
times required by paragraph (f) and (k) of AD 2006-24-02. This AMOC is only for areas where stringer
6 modification doublers have been installed in accordance with this SB. When this SB specifies contacting
Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with
paragraph (n) of the AD. All provisions of AD 2006-24-02 that are not specifically referenced in this
paragraph remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4 - 10 (as applicable) under paragraph
1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the Zone
1 external doubler modification requirement aft of body station (STA) 340, at Stringer 6, with the
corresponding compliance time for SB 747-53-2272, SB 747-53-2253, and SB 747-53A2303, specified
in Section 3 of the Aging Airplane SB Structural Modification and Inspection Program Document
D6-35999, dated March 31, 1989 required by paragraph A. of AD 90-06-06. This AMOC is only for
areas where the external doublers are installed in accordance with SB 747-53A2499, Revision 2 or
Revision 3. When this SB specifies contacting Boeing for repair instructions, the repair instructions
must be approved by the FAA in accordance with paragraph C. of the AD. All provisions of AD 90-06-06
that are not specifically referenced in this paragraph, including the compliance times for modification
remain fully applicable and must be complied with accordingly.
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In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4 - 10 (as applicable) under paragraph
1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the
modification required by paragraph (s) of AD 2005-08-01. This AMOC is only for areas on the skin
where stringer 6 modification doublers have been installed aft of BS 340 in accordance with this SB.
When this SB specifies contacting Boeing for repair instructions, the repair instructions must be approved
by the FAA in accordance with paragraph (t) of the AD. All provisions of AD 2005-08-01 that are not
specifically referenced in this paragraph, including the compliance time for modification remain fully
applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4 - 10 (as applicable) under paragraph
1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the
inspection and modification requirements specified in Tables 1 and 2, under paragraph 1.E.,
"Compliance", of SB 747-53A2542, dated February 16, 2006 required by paragraphs (f) and (h) of AD
2007-15-07. When this SB specifies contacting Boeing for repair instructions, the repair instructions
must be approved by the FAA in accordance with paragraph (i) of the AD. All provisions of AD
2007-15-07 that are not specifically referenced in this paragraph, including the compliance time for
modification remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the modification
and post-modification inspection procedures specified in Tables 2, 4 - 10 (as applicable) under paragraph
1.E., "Compliance", of SB 747-53A2499, Revision 3, as an AMOC to the accomplishment of the
inspection required by paragraphs (f) and (h) of AD 2006-20-02. This AMOC is only for areas where
modification doublers have been installed in accordance with this SB. When this SB specifies contacting
Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with
paragraph (k) of the AD. All provisions of AD 2006-20-02 that are not specifically referenced in this
paragraph remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the inspection, repair
and modification procedures with the corresponding compliance times specified in Tables 1 - 10 (as
applicable) under paragraph 1.E.,"Compliance" of SB 747-53A2499, Revision 3, as an AMOC to the
accomplishment of the inspection, repair and modification procedures required by paragraph (g), (h),
(i), (j) and (k) of AD 2010-26-10. All provisions of AD 2010-26-10 that are not specifically referenced
in the above statement remain fully applicable and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the task-hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
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Group 1-15, 19:
Lap Joint Inspections - Area 1
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.5010.004Prepare
21.0084.004Examine Section 41
40.00160.004Examine Section 42
74.25297.004Examine Section 46
137.50551.00 (a)TOTAL FOR EACH AIRPLANE
(a) More time will be necessary for repairs if cracks are found.
Group 1-15, 19:
Lap Joint Inspections - Area 1 and Area 2
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.5010.004Prepare
21.0084.004Examine Section 41
47.50190.004Examine Section 42
97.75391.004Examine Section 46
168.75675.00 (a)TOTAL FOR EACH AIRPLANE
(a) More time will be necessary for repairs if cracks are found.
Group 1-5, 7-10, 12-15, 19:
Lap Joint Modifications
Elapsed HoursTask-HoursNumber of Per-
sons
Task
287.754604.0016Modify Section 41
303.751215.004Modify Section 42
591.55819.00TOTAL FOR EACH AIRPLANE
Group 2-6, 8-11, 19:
Lap Joint Modifications
Elapsed HoursTask-HoursNumber of Per-
sons
Task
116.001856.0016Modify Section 41
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Group 2-6, 8-11, 19:
Lap Joint Modifications
Elapsed HoursTask-HoursNumber of Per-
sons
Task
303.751215.004Modify Section 42
419.753071.00TOTAL FOR EACH AIRPLANE
Group 16-18:
Lap Joint Modifications
Elapsed HoursTask-HoursNumber of Per-
sons
Task
239.003824.0016Modify Section 41
239.003824.00TOTAL FOR EACH AIRPLANE
Group 1-5, 7-10, 12-15, 19:
Lap Joint Post-Modification Inspections
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Prepare
16.7567.004Inspect Section 41
7.0028.004Inspect Section 42
26.25105.00TOTAL FOR EACH AIRPLANE
Group 6, 11, 19:
Lap Joint Post-Modification Inspections
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Prepare
7.2529.004Inspect Section 41
7.0028.004Inspect Section 42
16.7567.00TOTAL FOR EACH AIRPLANE
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Group 16-18:
Lap Joint Post-Modification Inspections
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.008.004Prepare
14.5058.004Inspect Section 41
16.5066.00TOTAL FOR EACH AIRPLANE
Group 6, 11, 19:
Post-Modification Inspections of Stringer 6 Lap Joint Modification Installed
Between STA 340 and STA 400 as given in Service Bulletin 747-53-2272
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.008.004Prepare
14.5058.004Inspect Section 41
16.5066.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Installation of lap joint repairs and modifications given in this service bulletin will affect the weight and
balance of the airplane. Determination of these changes is necessary, once the configuration of the
lap joint repairs and modifications are defined.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 85901-91RS
b. Boeing Service Bulletin 747-53-2253, 747-53-2272, 747-53-2305, 747-53-2366, 747-53-2386,
747-53-2487, 747-53A2303, 747-53A2312, 747-53A2367, 747-53A2487, 747-53A2499,
747-53A2501, 747-53A2563, 747-53A2675, 747-53A2748, 747-53A2817
c. Boeing Service Letter 747-SL-51-048, 747-SL-53-088
d. Boeing Service Related Problem (SRP) 747-OP-SRP-53-0279, 747-SRP-53-0211,
747-SRP-53-0434
e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-07-22 R1, 2005-08-01,
2006-05-09, 2006-20-02, 2006-22-09, 2006-24-02, 2006-24-05, 2007-15-07, 2008-16-14,
2009-04-16, 2010-26-10, 2012-10-03, 2013-16-24, 90-06-06, 94-15-17
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f. Service Bulletin Index D6-30300
g. Standard Overhaul Practices Manual (SOPM) 20-41-01, 20-50-11
h. 747 Fleet Team Digest (FTD) 53-13001
i. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 53-30-00, Part 6, 53-30-02
or 53-30-06
j. 747 Repair Assessment Guidelines (RAG)
k. 747-100/200/300 Structural Repair Manual (SRM) 51-10-06
l. 747-100/-200/-300 Structural Repair Manual (SRM) 51-30-08
m. 747-100/200/300 Structural Repair Manual (SRM) 51-70-00, 51-70-03, 53-10-04, 53-30-03
n. 747-400 Structural Repair Manual (SRM) 51-10-01, 51-10-03, 51-20-05, 51-40-08, 53-00-01
o. 747-400F Structural Repair Manual (SRM) 51-10-01, 51-10-03, 51-20-05, 51-40-08, 53-00-01
p. 747-400LCF Structural Repair Manual (SRM) 51-10-01, 51-10-03, 51-20-05, 51-40-08
q. 747-400SF Structural Repair Manual (SRM) 53-00-01
2. Data Supplied with this Service Bulletin:
a. Drawings:
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### Page 45

ADCNDCN/REVSheetTitleDrawing No
--1Kit - Lap Splice Modification, S-6, Sta 340
Sta 520
141U0008
--10
--11
--12
-A13
-A14
-A15
--2
--3
--4
--5
--6
--7
--8
-A9
-APSDLKit - Lap Splice Modification, S-6, Sta 340
Sta 520
141U0008#DL
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### Page 46

ADCNDCN/REVSheetTitleDrawing No
--1Kit - Lap Splice Modification, S-6, Sta 340
- 520
141U0059
-A10
-A11
-A12
-A13
-A14
-A15
-A16
-A17
-A18
-A19
-A2
-A3
-A4
-A5
-A6
-A7
-A8
-A9
--PSDLKit - Lap Splice Modification, S-6, Sta 340
- 520
141U0059#DL
-B2747 WFD U-1 Section 41, S-23 Skin Rein-
forcement - STA 220 - 400
691U1050
--3
--4
--5
-CPSDL747 WFD U-1 Section 41, S-23 Skin Rein-
forcement - STA 220 - 400
691U1050#DL
-A1747 WFD U-1 Section 41, S-44 Skin Rein-
forcement - STA 420 - 520
691U1051
-CPSDL747 WFD U-1 Section 41, S-44 Skin Rein-
forcement - STA 420 - 520
691U1051#DL
-A1Lap Splice Reinforcement, Stringer 44, Sta
520 - Sta 471
691U1052
--2
-A3
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ADCNDCN/REVSheetTitleDrawing No
-CPSDLLap Splice Reinforcement, Stringer 44, Sta
520 - Sta 471
691U1052#DL
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin or in existing documents.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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BLANK PAGE

### Page 49

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane, as shown
below. Alternatively, operators can fabricate their own parts. If there is a limit to the quantity (QTY) of
available kits, a supply sequence is given by Spares. More kits become available as given in the Reorder
Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
Unit Price thru
Jan 31/11
ROLT
(Weeks)
QTYDateNameKit Number
$5001.00431Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-1
$4887.00433Dec 08/09Kit - Lap Splice Modifica-
tion
141U0059-2
$5004.00432Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-3
$4333.00433Dec 08/09Kit - Lap Splice Modifica-
tion
141U0059-4
$6787.00431Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-5
$6880.00433Dec 08/09Kit - Lap Splice Modifica-
tion
141U0059-6
$6708.00432Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-7
$6645.00434Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-8
$5898.00431Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-9
$5465.00432Dec 08/09Kit - Lap Splice Modifica-
tion
141U0059-10
$7586.00431Jan 21/10Kit - Lap Splice Modifica-
tion
141U0059-11
$6961.00432Dec 08/09Kit - Lap Splice Modifica-
tion
141U0059-12
Unit Price thru
Jan 31/11
ROLT
(Weeks)
QTYDateNameKit Number
$3135.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-1
$3121.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-2
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### Page 50

Unit Price thru
Jan 31/11
ROLT
(Weeks)
QTYDateNameKit Number
$3135.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-3
$3122.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-4
$2990.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-5
$2990.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-6
$3096.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-7
$2948.00(a)(a)(a)Kit - Lap Splice Modifica-
tion
141U0008-8
(a) These kits are were not available at the time of release of Revision 2 of this service bulletin.
Boeing recommends that operators submit a purchase order 18 months in advance of performing
the modification.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection, repair, or modification procedures given
in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
NOTE: The kits shown below are for lap splice modification at stringer 6. See Drawing 141U0008,
Sheet 1 and Drawing 141U0059, Sheet 1 for kit applicability. The kits below can be
ordered from Boeing, or the equivalent parts can be supplied by the operator.
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-1-2-3-4-5-6
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
-.....141U0008-1
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
.-....141U0008-2
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
..-...141U0008-3
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### Page 51

Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-1-2-3-4-5-6
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
...-..141U0008-4
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
....-.141U0008-5
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
.....-141U0008-6
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
1.....141U0008-11
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
.1....141U0008-12
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
..1...141U0008-13
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
...1..141U0008-14
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
....11141U0008-15
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
1.....141U0008-41
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
.1....141U0008-42
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
..1...141U0008-43
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
...1..141U0008-44
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
....1.141U0008-45
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Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-1-2-3-4-5-6
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
.....1141U0008-46
Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-7-8-11-12-13-14
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
-.....141U0008-7
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
520
.-....141U0008-8
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
..-...141U0008-11
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
...-..141U0008-12
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
....-.141U0008-13
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
.....-141U0008-14
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
11....141U0008-17
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
1.....141U0008-47
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
.1....141U0008-48
(a)BOLT, 100 DEG HEX DR..21212121BACB30NW6K5X
(a)BOLT, 100 DEG HEX DR..4444BACB30NW6K8X
COLLAR..25252525BACC30M6
(a)RIVET, 100 DEG....48BACR15GF6D10
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Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-7-8-11-12-13-14
(a)RIVET, 100 DEG..578571..BACR15GF6D4
(a)RIVET..421385947947BACR15GF6D5
(a)RIVET, 100 DEG..688583675546BACR15GF6D6
(a)RIVET, 100 DEG..473405492422BACR15GF6D7
(a)RIVET, 100 DEG..159162221200BACR15GF6D8
(a)RIVET, 100 DEG..15192522BACR15GF6D9
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-15-17-41-42-43-44
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
-.....141U0008-15
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 520
.-....141U0008-17
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
..-...141U0008-41
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
...-..141U0008-42
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
....-.141U0008-43
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
.....-141U0008-44
EXTERNAL DOUBLER..1...141U0035-1
EXTERNAL DOUBLER...1..141U0035-2
EXTERNAL DOUBLER..1...141U0035-3
EXTERNAL DOUBLER...1..141U0035-4
EXTERNAL DOUBLER....1.141U0035-5
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
53 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 54

Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-15-17-41-42-43-44
EXTERNAL DOUBLER.....1141U0035-6
STRUCTURAL FILLER....1.141U0035-7
STRUCTURAL FILLER.....1141U0035-8
(a)BOLT, 100 DEG HEX DR2.....BACB30NW6K3X
(a)BOLT, 100 DEG HEX DR62....BACB30NW6K4X
(a)BOLT, 100 DEG HEX DR.6....BACB30NW6K5X
(a)BOLT, 100 DEG HEX DR4.....BACB30YP6K4
(a)BOLT, 100 DEG HEX DR24....BACB30YP6K5
(a)BOLT, 100 DEG HEX DR.2....BACB30YP6K6
COLLAR66....BACC30BL6
COLLAR88....BACC30M6
(a)RIVET, UNIVERSAL HD195130....BACR15BB6D4C
(a)RIVET, UNIVERSAL HD1017....BACR15BB6D6C
(a)RIVET, UNIVERSAL HD69....BACR15BB6D7C
(a)RIVET, 100 DEG579.....BACR15GF6D4
(a)RIVET959646....BACR15GF6D5
(a)RIVET, 100 DEG22987....BACR15GF6D6
(a)RIVET, 100 DEG300367....BACR15GF6D7
(a)RIVET, 100 DEG9228....BACR15GF6D8
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-45-46-47-48
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
-...141U0008-45
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
.-..141U0008-46
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
54 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 55

Kit 141U0008
NotesExisting
Part
Number
NameQTYNew Part Number
-45-46-47-48
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
..-.141U0008-47
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 520
...-141U0008-48
EXTERNAL DOUBLER1...141U0035-9
EXTERNAL DOUBLER.1..141U0035-10
STRUCTURAL FILLER1...141U0035-11
STRUCTURAL FILLER.1..141U0035-12
EXTERNAL DOUBLER..1.141U0035-13
EXTERNAL DOUBLER...1141U0035-14
STRUCTURAL FILLER..1.141U0035-15
STRUCTURAL FILLER...1141U0035-16
Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-1-2-3-4-5-6
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
400
-.....141U0059-1
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
400
.-....141U0059-2
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
400
..-...141U0059-3
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
400
...-..141U0059-4
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 400 - STA
520
....-.141U0059-5
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 400 - STA
520
.....-141U0059-6
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
55 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 56

Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-1-2-3-4-5-6
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
1.....141U0059-21
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
.1....141U0059-22
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
....1.141U0059-23
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
.....1141U0059-24
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 400
.1....141U0059-31
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 400
...1..141U0059-32
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 400 - STA 520
....11141U0059-33
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 400
1.....141U0059-37
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 400
..1...141U0059-38
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
..1...141U0059-41
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
...1..141U0059-42
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
56 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 57

Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-7-8-9-10-11-12
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 400 - STA
520
-.....141U0059-7
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 400 - STA
520
.-....141U0059-8
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
400
..-...141U0059-9
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 340 - STA
400
...-..141U0059-10
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 400 - STA
520
....-.141U0059-11
KIT - LAP SPLICE MODIFICA-
TION, S-6, STA 400 - STA
520
.....-141U0059-12
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
..1...141U0059-25
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
...1..141U0059-26
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
....1.141U0059-27
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
.....1141U0059-28
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 400 - STA 520
11....141U0059-34
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 400
...1..141U0059-35
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 400 - STA 520
....11141U0059-36
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
57 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 58

Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-7-8-9-10-11-12
KIT - FASTENERS, LAP
SPLICE MODIFICATION, S-
6, STA 340 - STA 400
..1...141U0059-39
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
1.....141U0059-43
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
.1....141U0059-44
Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-21-22-23-24-25-26
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
-.....141U0059-21
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
.-....141U0059-22
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
..-...141U0059-23
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
...-..141U0059-24
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
....-.141U0059-25
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
340 - STA 400
.....-141U0059-26
STRINGER FILLER11..11141U0060-2
TEAR STRAP DOUBLER11..11141U0060-4
TEAR STRAP FILLER11..11141U0060-6
FLAT FILLER11..11141U0060-8
TAPERED FILLER1...1.141U0060-9
TAPERED FILLER.1...1141U0060-10
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
58 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 59

Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-21-22-23-24-25-26
STRINGER FILLER..11..141U0060-12
TEAR STRAP DOUBLER..11..141U0060-14
TEAR STRAP FILLER..11..141U0060-16
FLAT FILLER..11..141U0060-18
TAPERED FILLER..1...141U0060-19
TAPERED FILLER...1..141U0060-20
STRINGER FILLER..11..141U0060-22
TEAR STRAP DOUBLER..22..141U0060-24
TEAR STRAP FILLER..33..141U0060-28
EXTERNAL DOUBLER1...1.141U0060-37
EXTERNAL DOUBLER.1...1141U0060-38
SKIN EXTENSION..1...141U0060-39
SKIN EXTENSION...1..141U0060-40
EXTERNAL DOUBLER1.....141U0060-41
EXTERNAL DOUBLER.1....141U0060-42
EXTERNAL DOUBLER..1...141U0060-43
EXTERNAL DOUBLER...1..141U0060-44
EXTERNAL DOUBLER....1.141U0060-45
EXTERNAL DOUBLER.....1141U0060-46
FILLER11..11141U0060-52
STRINGER FILLER11..11141U0060-56
FILLER11..11141U0060-60
FILLER..11..BACF3F008J032NN
FILLER11..11BACF3F010L035NN
SHIM, LAMINATED..33..BACF3F011J015NN
FILLER, FLAT..11..BACF3F011J017NN
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
59 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

### Page 60

Kit 141U0059
NotesExisting
Part
Number
NameQTYNew Part Number
-27-28-31-32-33-34
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
-.....141U0059-27
KIT - PARTS, LAP SPLICE
MODIFICATION, S-6, STA
400 - STA 520
.-....141U0059-28
KIT - FASTENERS, LAP
SPLICE MODIFICATION,
S-6, STA 340 - STA 400
..-...141U0059-31
KIT - FASTENERS, LAP
SPLICE MODIFICATION,
S-6, STA 340 - STA 400
...-..141U0059-32
KIT - FASTENERS, LAP
SPLICE MODIFICATION,
S-6, STA 400 - STA 520
....-.141U0059-33
KIT - FASTENERS, LAP
SPLICE MODIFICATION,
S-6, STA 400 - STA 520
.....-141U0059-34
STRINGER FILLER11....141U0060-12
TEAR STRAP DOUBLER11....141U0060-14
TEAR STRAP FILLER11....141U0060-16
FLAT FILLER11....141U0060-18
TAPERED FILLER1.....141U0060-19
TAPERED FILLER.1....141U0060-20
STRINGER FILLER11....141U0060-22
TEAR STRAP DOUBLER22....141U0060-24
TEAR STRAP FILLER33....141U0060-28
SKIN EXTENSION1.....141U0060-39
SKIN EXTENSION.1....141U0060-40
EXTERNAL DOUBLER1.....141U0060-47
EXTERNAL DOUBLER.1....141U0060-48
(a)HI-LOK.....2BACB30MY8K4
(a)BOLT.....2BACB30MY8K5
(a)BOLT, HEX DRIVE.....12BACB30MY8K6
(a)BOLT, PROTRUDING HD.....4BACB30MY8K6Y
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 11, 2005
747-53A2499Revision 3: July 15, 2014
60 of 378
BOEING SERVICE BULLETIN 747-53A2499
ALERTALERT

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