# Boeing Alert Service Bulletin 747-53A2682: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-0461; AD 2013-23-15 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 747-53A2682](https://openairdocs.org/service-documents/boeing/747-53a2682.md)
- Title as filed: U.S. DOT/FAA - SB-747-53A2682-01
- Pages: 83
- PDF: https://openairdocs.org/files/sha256/d5/97/d5972d0a243215edfd943cc5ab80e88a413f4dd8194f1837924494da4ef5fce8
- Page: https://openairdocs.org/service-documents/boeing/747-53a2682/file/d5972d0a2432

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2682
Original Issue: May 08, 2008
Revision 1: May 24, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 42 Fuselage Frame Shear Tie End Fasteners - External
Skin Crack Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2008 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Unpublished Work.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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, 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. BOEING is a trademark of Boeing Management
Company.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
1 of 83
3.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
2 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 0
B. Concurrent Requirements ...................................... 2 0
C. Reason ................................................ 2 1
D. Description .............................................. 2 1
E. Compliance .............................................. 2 2
F. Approval ............................................... 2 8
G. Manpower .............................................. 2 9
H. Weight and Balance Changes .................................... 2 9
I. Electrical Load Data ......................................... 2 9
J. References .............................................. 2 9
1. Existing Data: ......................................... 2 9
2. Data Supplied with this Service Bulletin: ........................... 3 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 0
K. Publications Affected ........................................ 3 1
L. Interchangeability and Intermixability of Parts ........................... 3 1
M. Software Accomplishment Summary ................................ 3 1
2. MATERIAL INFORMATION ........................................ 3 3
A. Material - Price and Availability ................................... 3 3
B. Industry Support Information .................................... 3 3
C. Parts Necessary for Each Airplane ................................. 3 3
1. Kits/Parts: ........................................... 3 3
2. Parts and Materials Supplied by the Operator: ........................ 3 3
3. Parts Modified and Reidentified: ............................... 3 3
4. Parts Removed and Not Replaced: .............................. 3 3
D. Parts Necessary to Change Spares ................................. 3 3
E. Special Tooling - Price and Availability ............................... 3 3
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5
A. GENERAL INFORMATION ..................................... 3 5
B. WORK INSTRUCTIONS ....................................... 3 6
FIGURE 1: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - LEFT SIDE -
EXTERNAL SKIN INSPECTION [Group 1-2, 4] ........................ 4 0
FIGURE 2: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION ................................ 4 5
FIGURE 3: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE -
EXTERNAL SKIN INSPECTION [Group 1-2, 4] ........................ 5 0
FIGURE 4: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION ................................ 5 5
FIGURE 5: STATION 540 TO 980, BELOW STRINGER 39 LEFT TO BELOW STRINGER 39 RIGHT -
EXTERNAL SKIN INSPECTION ................................ 6 0
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
3 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 4

FIGURE 6: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 28 - LEFT SIDE -
EXTERNAL SKIN INSPECTION  [Group 3] .......................... 6 5
FIGURE 7: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE -
EXTERNAL SKIN INSPECTION  [Group 3] .......................... 6 9
FIGURE 8: INSPECTION OF SKIN AT DOUBLER LOCATIONS WHERE THE UPPER OR LOWER
FASTENER ROW OF THE DOUBLER IS COMMON TO A SHEAR TIE END FASTENER . 72
FIGURE 9: INSPECTION OF SKIN AT DOUBLER LOCATIONS WHERE THE UPPER OR LOWER
FASTENER ROW OF THE DOUBLER IS COMMON TO A SHEAR TIE END FASTENER [Group
3 ]  ................................................ 7 6
APPENDIX A: DOUBLER EXAMPLES THAT REQUIRE INSPECTION OF SKIN NEXT TO THE SHEAR TIE
END FASTENER ....................................... 8 1
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
4 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 5

Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-53A2682Original Issue: May 08, 2008
Revision 1: May 24, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 42 Fuselage Frame Shear Tie End Fasteners - External
Skin Crack Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplane(s) inspected or repaired in accordance with the original issue of this
service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-02 is related to this service bulletin.
Airplane line numbers 758 through 1419 (except Large Cargo Freighter airplanes) were added to this Service
Bulletin effectivity as new Groups 3 and 4.
REASON FOR REVISION
This Alert revision is sent to add airplane line numbers 758 through 1419 to the service bulletin effectivity (except
Large Cargo Freighter airplanes).
These sections were changed:
1. In the Summary: Updated Background and Action information, added reference to Service Related
Problem 747-SRP-53-0352 and Fleet Team Digest article 747-FTD-53-09006, added reference to FAA
AD 2009-06-02, and added new Groups 3 and 4 to Manpower table.
2. In Paragraph 1.A.1., Airplanes: Revised description for Group 1 and added description for new Groups
3 and 4.
3. In Paragraph 1.C., Reason: Updated Reason information, added references to Service Related Problem
747-SRP-53-0352 and Fleet Team Digest article 747-FTD-53-09006.
4. In Paragraph 1.D., Description: Inspection area description changed, "No more work" statement is
added, and Affected Maintenance Zones are added.
5. In Paragraph 1.E., Compliance: Related AD statement is added. Compliance information in Table 1 is
updated, and footnote (b) was deleted. Table 2 is added for Group 2 airplanes. Table 3 is added for
new Groups 3 and 4. Tables 4 and 5 are added for inspection at shear tie end fasteners that are
common to an upper or lower fastener row of a repair doubler.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
5 of 83

### Page 6

6. In Paragraph 1.F., Approval: Alternative Method of Compliance (AMOC) statement is added relating
to FAA AD 2009-06-02.
7. In Paragraph 1.K.2., Publication Affected: "Damage Tolerance Structural Inspections" statement is
added.
8. In Paragraph 1.J.1., References: Document references and installation drawings are updated.
9. In Paragraph 3.B., Work Instructions: Group applicability is updated. Instructions for inspection of Group
3 and 4 airplanes is added. PART 3 - Skin Crack Repair steps are clarified. New PART 4 is added for
inspection at shear tie end fasteners that are common to an upper or lower fastener row of a repair
doubler.
10. In Figures 1 through 5: Previous flag note 1 is now footnote (a), and the flag note table was deleted.
Section view A-A is corrected. L-shaped shear tie is identified. Group applicability is also updated for
Group 4.
11. In Figure 2: Stringer identifications are corrected.
12. In Figures 3, 4, and 5: Added footnote (b).
13. Figures 6 and 7: These new figures have been added for Group 3.
14. Figures 8 and 9: These new figures have been added for inspection of the skin at repair doublers where
the upper or lower fastener row of the repair doubler is common to a shear tie end fastener.
15. Appendix A: This new appendix has been added to identify external repair doubler configurations where
the skin should be inspected next to the shear tie end fastener.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
May 08, 2008Original Issue:
May 24, 2012Revision 1:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
6 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 7

Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2682Original Issue: May 08, 2008
Revision 1: May 24, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 42 Fuselage Frame Shear Tie End Fasteners - External
Skin Crack Inspection
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 instructions to do external inspections of the Section 42 skin for cracks at fuselage
frame shear tie end fastener locations. Cracks in the fuselage skin can propagate and become large, resulting
in a loss of structural integrity and a sudden decompression of the airplane in-flight.
Fuselage frame shear ties are an integral part of the load bearing airframe structure, and are located between
longitudinal stringers.
The inspection for skin cracks at fuselage frame shear tie end fastener locations as given in this service bulletin
is between Station 540 to 980 (STA 780 on 747SP airplanes), Stringer 23 to 47 left and right side. This issue is
a part of the wide-spread fatigue damage (WFD) assessment for the model 747 airplanes. It is one of the
structural details that have been determined by analysis and fleet history to be susceptible to WFD and requires
service action in the form of inspections and/or modification.
Since the release of the original issue of this service bulletin, one operator has reported finding three skin cracks
at fastener holes common to STA 540 frame shear tie between S-23L and S-25L. The affected airplane had
T-shaped shear ties in the inspection area and was not in the effectivity of the original issue of this service
bulletin. Based on these reports of cracks in T-shaped shear ties, airplane line numbers 758 through 1419
(except Large Cargo Freighter airplanes) have been added to the bulletin effectivity.
Boeing Service Related Problems (SRP) 747-SRP-53-0299 and 747-SRP-53-0352 are related to this service
bulletin.
Boeing Fleet Team Digest (FTD) 747-FTD-53-09006 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
7 of 83

### Page 8

ACTION
Station 540 to 980 (STA 780 on 747SP series airplanes), Stringers 23 to 47, left and right sides, do an external
detailed inspection or external high frequency eddy current (HFEC) inspection for skin cracks at fuselage frame
shear tie end fastener locations. If an external repair doubler exists in the inspection area and the upper or lower
fastener row of the doubler is common to a shear tie end fastener, do an internal HFEC inspection of the skin
next to the shear tie.
If no cracks are found, repeat inspections are required. See Paragraph 1.E., Compliance. If cracks are found,
repair as given in the applicable 747 Structural Repair Manual (SRM).
EFFECTIVITY
747-100/-100B/-100B SUD/-200B/-200C/-200F/-300/-400/400D/-400F/SP/SR Airplanes. Refer to Paragraph
1.A.1 Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-02 is related to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release another Airworthiness Directive related to this
service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service
bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service
bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
25.7591.00Group 1, 2, 3, and 4
Refer to Paragraph 1.G., Manpower .
MATERIAL INFORMATION
None.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
8 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 9 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
SECTION 42
1000
000  • 0  0 0 0 0
000000  0000  0000000  00000
DO AN EXTERNAL DETAILED INSPECTION
OR HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION FOR SKIN CRACKS AT FUSELAGE
FRAME SHEAR TIE END FASTENER LOCATIONS.
STRETCHED UPPER DECK 747 SHOWN  1371677
OTHER AFFECTED AIRPLANES SIMILAR
Original Issue: May 08, 2008
Revision 1: May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  9 of 83

### Page 10

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
10 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT
BLANK PAGE

### Page 11

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2682
Original Issue: May 08, 2008
Revision 1: May 24, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Section 42 Fuselage Frame Shear Tie End Fasteners - External
Skin Crack Inspection
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 Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
747 airplanes, line numbers 1 through 757, except 747SP airplanes.
This Group includes airplanes modified to Boeing Special Freighter.
-1
747SP airplanes.-2
747-300/-400/-400D, airplanes, line numbers 758 through 1419,
except Large Cargo Freighter airplanes. This Group includes airplanes
modified to Boeing Converted Freighter.
-3
747-200F/400F airplanes, line numbers 758 through 1419.-4
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SP, 747SR
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
11 of 83

### Page 12

GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
12 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 13

GroupVariable Number
1RB101 - RB102
1RB411 - RB413
1RB421
1RB601 - RB607
1RB681 - RB697
1RB711
1RB721 - RB723
1RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD144
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD227
1RD231 - RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
1RD301 - RD302
1RD311
1RD351 - RD358
1RD361 - RD366
1RD381 - RD383
1RD411 - RD414
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
13 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 14

GroupVariable Number
1RD421 - RD426
1RD431 - RD435
1RD441 - RD442
1RD451 - RD456
1RD461
1RD471 - RD475
1RD513 - RD519
1RD531 - RD533
1RD551
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD601 - RD607
1RD621 - RD623
1RD641 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
3RF001 - RF006
2RG001 - RG009
2RG091
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
14 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 15

GroupVariable Number
2RG095
2RG101 - RG104
2RG121 - RG126
2RG141 - RG142
2RG161 - RG164
2RG171 - RG174
2RG191 - RG193
2RG211 - RG213
2RG221 - RG222
2RH101 - RH102
2RH111 - RH112
2RH121 - RH122
1RJ131 - RJ133
1RJ151 - RJ152
1RJ301 - RJ303
1RJ321 - RJ322
1RJ331 - RJ333
4RL401 - RL403
4RL411 - RL436
4RL451 - RL456
4RL461 - RL462
4RL471 - RL481
4RL491 - RL492
4RL501 - RL502
4RL511 - RL516
4RL521 - RL522
4RL531 - RL534
4RL551
4RL561 - RL568
4RL571 - RL572
4RL576 - RL577
4RL579
4RL581 - RL586
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
15 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 16

GroupVariable Number
4RL651 - RL655
4RL671 - RL675
4RL681 - RL684
4RL751 - RL752
3RM001 - RM007
3RM010 - RM013
3RM021 - RM024
3RM026 - RM030
3RM036 - RM045
3RM051 - RM053
3RM071
3RM081 - RM084
3RM091
3RM096 - RM097
3RM116 - RM117
3RM126 - RM132
3RM136 - RM147
3RM156 - RM158
3RM166 - RM177
3RM191 - RM192
3RM231 - RM233
3RM241 - RM246
3RM261 - RM264
3RM316 - RM318
3RM331 - RM333
3RM341
3RM351 - RM355
3RM366 - RM367
3RM401 - RM403
3RM426
3RM431
3RM441 - RM443
3RM445
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
16 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 17

GroupVariable Number
3RM801 - RM803
3RM811 - RM813
4RM851 - RM859
4RM861 - RM863
4RM871 - RM899
4RM901 - RM906
4RM911
1RR001 - RR005
1RR021 - RR025
1RR031
1RR201 - RR206
1RR221 - RR226
1RR261 - RR267
1RR301 - RR307
4RR308 - RR310
1RR331 - RR332
1RR336
1RR341 - RR345
1RR361 - RR362
1RR421 - RR422
1RR431 - RR432
1RR441
4RR442
4RR451
1RR501 - RR504
1RR521 - RR522
1RR526
1RR531
1RR551 - RR554
4RR555 - RR556
1RR561
1RR566
4RR701
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
17 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 18

GroupVariable Number
4RR721 - RR724
4RR746 - RR748
4RR851 - RR856
4RR861 - RR862
4RR951 - RR952
1RS001 - RS002
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
1RS711 - RS713
1RS721 - RS722
1RS731 - RS732
1RS741 - RS743
1RS751 - RS752
1RS761
3RS762
1RS771
1RS781 - RS782
1RS786
1RT001 - RT002
3RT003 - RT014
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
18 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 19

GroupVariable Number
1RT021 - RT022
1RT031
3RT032 - RT035
1RT041 - RT043
3RT044 - RT047
3RT061
3RT071 - RT075
3RT101 - RT103
3RT121
3RT131 - RT137
3RT151 - RT152
3RT161 - RT168
1RT401 - RT406
3RT407 - RT412
1RT431 - RT433
3RT434 - RT447
1RT451 - RT452
3RT453 - RT469
1RT471 - RT475
3RT476 - RT499
1RT501 - RT504
3RT505 - RT530
1RT531 - RT532
3RT533 - RT535
1RT551 - RT553
3RT554 - RT568
1RT571 - RT573
3RT574 - RT590
1RT591
1RT601 - RT602
3RT603 - RT630
3RT633 - RT657
1RT671
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
19 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 20

GroupVariable Number
3RT672 - RT673
3RT681 - RT682
3RT691 - RT699
3RT701 - RT704
3RT711 - RT717
3RT741 - RT742
3RT744 - RT757
3RT776 - RT777
3RT781 - RT784
3RT801 - RT803
3RT811 - RT814
3RT831 - RT837
3RT861 - RT864
3RT877 - RT880
3RT931 - RT932
3RT945 - RT949
3RT951 - RT955
3RT966 - RT967
3RU001 - RU006
3RU016 - RU017
3RU031 - RU032
3RU051 - RU052
3RU059 - RU062
3RU081 - RU083
3RU101 - RU102
3RU121 - RU132
3RU801 - RU809
3RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
20 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 21

C. Reason
This service bulletin gives instructions to do external inspections of the Section 42 skin for cracks at
fuselage frame shear tie end fastener locations. Cracks in the fuselage skin can propagate and become
large, resulting in a loss of structural integrity and a sudden decompression of the airplane in-flight.
Fuselage frame shear ties are an integral part of the load bearing airframe structure, and are located
between longitudinal stringers.
The inspection for skin cracks at fuselage frame shear tie end fastener locations as given in this service
bulletin is between Station 540 to 980 (STA 780 on 747SP airplanes), Stringer 23 to 47 left and right
side. This issue is a part of the wide-spread fatigue damage (WFD) assessment for the model 747
airplanes. It is one of the structural details that have been determined by analysis and fleet history to
be susceptible to WFD and requires service action in the form of inspections and/or modification.
Since the release of the original issue of this service bulletin, one operator has reported finding three
skin cracks at fastener holes common to STA 540 frame shear tie between S-23L and S-25L. The
affected airplane had T-shaped shear ties in the inspection area and was not in the effectivity of the
original issue of this service bulletin. Based on these reports of cracks in T-shaped shear ties, airplane
line numbers 758 through 1419 (except Large Cargo Freighter airplanes) have been added to the
bulletin effectivity.
Boeing Service Related Problems (SRP) 747-SRP-53-0299 and 747-SRP-53-0352 are related to this
service bulletin.
Boeing Fleet Team Digest (FTD) 747-FTD-53-09006 is related to this service bulletin.
Revision 1 is sent to add airplane line numbers 758 through 1419 to the service bulletin effectivity
(except Large Cargo Freighter airplanes). Refer to the Revision Transmittal Sheet section of Revision
1 for a detailed list of changes.
D. Description
Station 540 to 980 (STA 780 on 747SP series airplanes), Stringers 23 to 47, left and right sides, do an
external detailed inspection or external high frequency eddy current (HFEC) inspection for skin cracks
at fuselage frame shear tie end fastener locations. If an external repair doubler exists in the inspection
area and the upper or lower fastener row of the doubler is common to a shear tie end fastener, do an
internal HFEC inspection of the skin next to the shear tie.
If no cracks are found, repeat inspections are required. See Paragraph 1.E., Compliance. If cracks are
found, repair as given in the applicable 747 Structural Repair Manual (SRM).
Revision 1 - No more work is necessary on the airplane(s) inspected or repaired as given in the original
issue of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
21 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 22

Group 1:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 127, 128, 129,
191, 192, 291, 292
747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C,
747-200F, 747-300, 747-400,
747SR
Group 2:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 127, 128, 129,
191, 192, 291, 292
747SP
Group 3:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 127, 128, 129,
191, 192, 291, 292
747-300, 747-400, 747-400D
Group 4:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 127, 128, 129,
191, 192, 291, 292
747-200F, 747-400F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-02 is related to this service
bulletin.
The Federal Aviation Administration (FAA) will possibly release another Airworthiness Directive related
to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in
this service bulletin mandatory.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
22 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 23

Group 1:
Table 1: Station 540 to 980, Stringer 23 to 47 Left and Right Side, External Skin Crack Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
flight cycles af-
ter the effective
date of AD
2009-06-02.
Before 22,000
total flight cy-
cles.
Do an external detailed
inspection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
All airplanes
or
-Do an external high fre-
quency eddy current
(HFEC) inspection for
skin cracks at fuselage
frame shear tie end fas-
tener locations as given
in paragraph 3.B., Work
Instructions, PART 1 and
PART 2.
3,000 flight cycles.Within 3,000 flight cycles after the
initial inspection.
Do an external detailed
inspection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
No skin crack(s) found. (a)
or
6,000 flight cycles.Within 6,000 flight cycles after the
initial inspection.
Do an external HFEC in-
spection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
-Before further flight.Install a skin crack repair
as given in paragraph
3.B., Work Instructions,
PART 3.
Any skin crack found.
--No action required by this
service bulletin at that
doubler location. (b)
Any existing external repair
doubler in the inspection
area where the upper and
lower fastener rows of the
repair doubler ARE NOT
common to a shear tie end
fastener.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
23 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 24

Group 1:
Table 1: Station 540 to 980, Stringer 23 to 47 Left and Right Side, External Skin Crack Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
Refer to Compliance Table 4.Any existing external repair
doubler in the inspection
area where the upper or
lower fastener row of the re-
pair doubler IS common to
a shear tie end fastener.
(a) Do repeat inspections at intervals specified for the given inspection method.
(b) Post-repair inspections required by the applicable 747 SRM, or 747 RAG, or other FAA approved repair
instructions, are still necessary.
Group 2:
Table 2: Station 540 to 780, Stringer 23 to 47 Left and Right Side, External Skin Crack Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
flight cycles af-
ter the effective
date of AD
2009-06-02.
Before 22,000
total flight cy-
cles.
Do an external detailed
inspection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
All airplanes
or
-Do an external HFEC in-
spection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
24 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 25

Group 2:
Table 2: Station 540 to 780, Stringer 23 to 47 Left and Right Side, External Skin Crack Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.Within 3,000 flight cycles after the
initial inspection.
Do an external detailed
inspection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
No skin crack(s) found. (a)
or
6,000 flight cycles.Within 6,000 flight cycles after the
initial inspection.
Do an external HFEC in-
spection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
-Before further flight.Install a skin crack repair
as given in paragraph
3.B., Work Instructions,
PART 3.
Any skin crack found.
--No action required by this
service bulletin at that
doubler location. (b)
Any existing external repair
doubler in the inspection
area where the upper and
lower fastener rows of the
repair doubler ARE NOT
common to a shear tie end
fastener.
Refer to Compliance Table 4.Any existing external repair
doubler in the inspection
area where the upper or
lower fastener row of the re-
pair doubler IS common to
a shear tie end fastener.
(a) Do repeat inspections at intervals specified for the given inspection method.
(b) Post-repair inspections required by the applicable 747 SRM, or 747 RAG, or other FAA approved repair
instructions, are still necessary.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
25 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 26

Group 3-4:
Table 3: Station 540 to 980, Stringer 23 to 47 Left and Right Side, External Skin Crack Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,000
flight cycles af-
ter the revision
1 date of this
service bulletin.
Before 22,000
total flight cy-
cles.
Do an external detailed
inspection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
All airplanes
or
-Do an external HFEC in-
spection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
3,000 flight cycles.Within 3,000 flight cycles after the
initial inspection.
Do an external detailed
inspection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
No skin crack(s) found. (a)
or
6,000 flight cycles.Within 6,000 flight cycles after the
initial inspection.
Do an external HFEC in-
spection for skin cracks
at fuselage frame shear
tie end fastener locations
as given in paragraph
3.B., Work Instructions,
PART 1 and PART 2.
-Before further flight.Install a skin crack repair
as given in paragraph
3.B., Work Instructions,
PART 3.
Any skin crack found.
--No action required by this
service bulletin at that
doubler location. (b)
Any existing external repair
doubler in the inspection
area where the upper and
lower fastener rows of the
repair doubler ARE NOT
common to a shear tie end
fastener.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
26 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 27

Group 3-4:
Table 3: Station 540 to 980, Stringer 23 to 47 Left and Right Side, External Skin Crack Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
Refer to Compliance Table 4 or Table 5, as applicable.Any existing external repair
doubler in the inspection
area where the upper or
lower fastener row of the re-
pair doubler IS common to
a shear tie end fastener.
(a) Do repeat inspections at intervals specified for the given inspection method.
(b) Post-repair inspections required by the applicable 747 SRM, or 747 RAG, or other FAA approved repair
instructions, are still necessary.
Group 1-2, 4:
Table 4: Post Repair (or Prior Existing Repair) Inspection of Skin at Doubler Locations Where the Upper
or Lower Fastener Row of the Doubler is Common to a Shear Tie End Fastener.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Do an internal HFEC in-
spection for cracks in the
skin next to the shear tie
as given in paragraph
3.B., Work Instructions,
PART 4.
Existing external repair dou-
bler installed in the inspec-
tion area where the upper or
lower fastener row of the re-
pair doubler IS common to
a shear tie end fastener.
6,000 flight cycles.-Repeat the internal HFEC
inspection for cracks in
the skin next to the shear
tie as given in paragraph
3.B., Work Instructions,
PART 4. (a)
No skin crack(s) found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any skin crack found.
(a) Post-repair inspections required by the applicable 747 SRM, or 747 RAG, or other FAA approved repair
instructions, are still necessary.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
27 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 28

Group 3:
Table 5: Post Repair (or Prior Existing Repair) Inspection of Skin at Doubler Locations Where the Upper
or Lower Fastener Row of the Doubler is Common to a Shear Tie End Fastener.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Do an internal HFEC in-
spection for cracks in the
skin next to the shear tie
as given in paragraph
3.B., Work Instructions,
PART 4.
Existing external repair dou-
bler installed in the inspec-
tion area where the upper or
lower fastener row of the re-
pair doubler IS common to
a shear tie end fastener.
6,000 flight cycles
at L-shaped shear
tie locations.
-Repeat the internal HFEC
inspection for cracks in
the skin next to the shear
tie as given in paragraph
3.B., Work Instructions,
PART 4. (a)
No skin crack(s) found.
or
4,500 flight cycles
at T-shaped shear
tie locations.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any skin crack found.
(a) Post-repair inspections required by the applicable 747 SRM, or 747 RAG, or other FAA approved repair
instructions, are still necessary.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin 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 service bulletin effectivity. This service bulletin 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 service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Seattle Aircraft Certification Office (ACO) approves the inspection
and repair procedures with corresponding compliance times specified in Tables 1, 2, and 4 (groups 1
and 2 only) under paragraph 1.E., "Compliance" of Service Bulletin 747-53A2682, Revision 1, as an
alternative method of compliance (AMOC) to the inspection and repair procedures with corresponding
compliance times specified in Table 1 under paragraph 1.E., "Compliance" of Service Bulletin
747-53A2682, original issue, dated May 8, 2008, required by paragraph (f) of AD 2009-06-02 . When
this service bulletin 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 2009-06-02 that
are not specifically referenced in this paragraph remain fully applicable and must be complied with
accordingly.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
28 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 29

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 inspect the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Elapsed HoursTask HoursNumber of Per-
sons
Task
3.006.002Open Access
7.5030.004Inspect - Detailed Visual
12.2549.004Inspect - HFEC
3.006.002Close Access
25.7591.00TOTAL FOR EACH AIRPLANE
Note: Additional time will be required if skin cracks are found and a repair is installed.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 747-SL-51-048 .
b. Boeing Service Related Problem (SRP) 747-SRP-53-0299, 747-SRP-53-0352.
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2009-06-02 .
d. Standard Overhaul Practices Manual (SOPM) 20-30-03.
e. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00
f. 747-100/200/300 Structural Repair Manual (SRM) 53-30-03.
g. 747-100/200/300 Aircraft Maintenance Manual (AMM) 53-51-01
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
29 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 30

h. 747-400 Aircraft Maintenance Manual (AMM) 53-51-01.
i. 747-400 Structural Repair Manual (SRM) 53-00-01.
j. 747-400F Structural Repair Manual (SRM) 53-00-01
k. 747-400SF Structural Repair Manual (SRM) 53-00-01 .
l. 747-SP Structural Repair Manual (SRM) 53-39-01.
m. Boeing Fleet Team Digest 747-FTD-53-09006.
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
SKIN PANEL INSTL - STA 520 TO STA 741.10,
S-23L TO S-34L
65B04104
SKIN PANEL INSTL - STA 520 TO STA 741.10,
S-34L TO S-39L
65B04105
SKIN PANEL INSTL - STA 520 TO STA 741.10,
S-39L TO S-44L
65B04106
SKIN PANEL INSTL - STA 520 TO STA 741.10,
S-44L TO S-44R
65B04107
SKIN PANEL INSTL65B04108
SKIN PANEL INSTL65B04109
SKIN PANEL INSTL65B04110
SKIN PANEL INSTL65B04115
SKIN PANEL INSTL65B04116
SKIN PANEL INSTL65B04117
SKIN PANEL INSTL65B04118
SKIN PANEL INSTL - STA 520 TO STA 1000,
S-23L TO S-34L
65B18624
SKIN PANEL INSTL - STA 520 TO STA 1000,
S-23R TO S-34R
65B18625
SKIN PANEL INSTL - STA 520 TO FRONT
SPAR BLKD, S-34L TO S-39L
65B18626
SKIN PANEL INSTL - STA 520 TO FRONT
SPAR BLKD, S-34R TO S-39R
65B18627
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
30 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 31

TitleDrawing Number
SKIN PANEL INSTL - STA 520 TO FRONT
SPAR BHD, STGR 39L TO STGR 44L
65B18628
SKIN PANEL INSTL - STA 520 TO FRONT
SPAR BLKD, S-44L TO S-44R
65B18629
SKIN PANEL INSTL - STA 520 TO FRONT
SPAR BLKD, S-39R TO S-44R
65B18696
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
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. DTI requirements for the structure affected are contained in Paragraph
1.E., Compliance of this service bulletin.
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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
31 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 32

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
32 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT
BLANK PAGE

### Page 33

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
None.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
33 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 34

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
34 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT
BLANK PAGE

### Page 35

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
— Linear dimensions are in inches
— Torque limits to tighten nuts and bolts are given in 747 SRM, Chapter 51.
4. Use the approved fastener and process material substitutions as given in SRM
Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length as given in SRM Chapter 51.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "as
given in" are included in the instruction, the procedure in the Boeing document must
be used.
8. Boeing Service Letter 747-SL-51-048 Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
9. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
35 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 36

10. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
B. WORK INSTRUCTIONS
PART 1 - External Skin Access and Inspection
1. Remove wing to body fairing panels as necessary. Refer to 747-100/200/300 AMM 53-51-01 or
747-400 AMM 53-51-01 as an accepted procedure.
2. Group 1, 3-4:
Station 540 to 980, do an external detailed inspection or surface high frequency eddy current
(HFEC) inspection for skin cracks in areas without existing repair doublers as given in PART 2 -
Inspection.
a. Condition 1 - No crack found, repeat external Detailed or HFEC skin inspections. See Paragraph
1.E., Compliance.
b. Condition 2 - Crack found, go to PART 3 - Skin Crack Repair.
3. Group 2:
Station 540 to 780, do an external detailed inspection or surface high frequency eddy current
(HFEC) inspection for skin crack in areas without existing repair doublers as given in PART 2 -
Inspection.
a. Condition 1 - No crack found, repeat external Detailed or HFEC skin inspections. See Paragraph
1.E., Compliance.
b. Condition 2 - Crack found, go to PART 3 - Skin Crack Repair.
4. If there are any shear tie locations where detailed or HFEC inspection cannot be done due to an
existing external doubler installed in the inspection area, determine if the upper or lower fastener
row of the doubler is common to a shear tie end fastener. Refer to APPENDIX A for examples.
a. For any existing external repair doubler in the inspection area where the upper and lower
fastener rows of the repair doubler ARE NOT common to a shear tie end fastener, no action
is required by this service bulletin at that doubler location. Post-repair instructions required
by the applicable 747 SRM, or 747 RAG, or other FAA approved repair instructions, are still
necessary.
b. For doubler locations where the upper or lower fastener row of the repair doubler is common
to a shear tie end fastener, do a HFEC inspection of the skin next to the shear tie as given in
PART 4 - Inspection of Skin at Doubler Locations Where the Upper or Lower Fastener Row
of the Doubler is Common to a Shear Tie End Fastener.
PART 2 - Inspection
1. Group 1-2, 4:
Below Stringer 23 to above Stringer 26, left side, do an external detailed inspection or external
high frequency eddy current (HFEC) inspection for skin cracks at fuselage frame L-shaped shear
tie end fastener locations as given in FIGURE 1.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
36 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 37

2. Group 3:
Below Stringer 23 to above Stringer 28, left side, do an external detailed inspection or external
HFEC inspection for skin cracks at fuselage frame T-shaped and L-shaped shear tie end fastener
locations as given in FIGURE 6 .
3. Below Stringer 23 to above Stringer 26, right side, do an external detailed inspection or external
high frequency eddy current (HFEC) inspection for skin cracks at fuselage frame L-shaped shear
tie end fastener locations as given in FIGURE 2.
4. Group 1-2, 4:
Below Stringer 26 to above Stringer 39, left side, do an external detailed inspection or an external
HFEC inspection for skin cracks at fuselage frame L-shaped shear tie end fastener locations as
given in FIGURE 3.
5. Group 3:
Below Stringer 26 to above Stringer 39, left side, do an external detailed inspection or an external
HFEC inspection for skin cracks at fuselage frame L-shaped shear tie end fastener locations as
given in FIGURE 7.
6. Below Stringer 26 to above Stringer 39, right side, do an external detailed inspection or an external
HFEC inspection for skin cracks at fuselage frame L-shaped shear tie end fastener locations as
given in FIGURE 4.
7. Below Stringer 39 left to below Stringer 39 right, do an external detailed inspection or external high
frequency eddy current (HFEC) inspection for skin cracks at fuselage frame L-shaped shear tie
end fastener locations as given in FIGURE 5.
PART 3 - Skin Crack Repair
1. Below Stringers 23, 34, 39 and 44 left and right side, at skin lap locations repair crack(s) as given
in 747-SP SRM 53-39-01 Figure 43, or 747-100/200/300 SRM 53-30-03 Figure 46, or 747-400
SRM 53-00-01 Repair 13, or 747-400F SRM 53-00-01 Repair 13, or 747-400SF SRM 53-00-01
Repair 13, as applicable.
2. Left and right side, above Stringer 24 to above Stringer 34, above Stringer 35 to above Stringer
39, above Stringer 40 to above Stringer 44 and above Stringer 45 to Stringer 47, at skin locations
that is not a skin lap, repair crack(s) as given in 747-SP SRM 53-39-01 Figure 1, or 747-100/200/300
SRM 53-30-03 Figure 1, or 747-400 SRM 53-00-01 Repair 1, or 747-400F SRM 53-00-01 Repair
1, or 747-400SF SRM 53-00-01 Repair 1, as applicable.
3. Install wing to body fairing panels as necessary. Refer to 747-100/200/300 AMM 53-51-01 or
747-400 AMM 53-51-01 as an accepted procedure.
PART 4 - Inspection of Skin at Doubler Locations Where the Upper or Lower Fastener Row of
the Doubler is Common to a Shear Tie End Fastener.
1. Remove equipment that follows as necessary, and as applicable, for access to the inspection area.
Refer to the following procedures, as necessary.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
37 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 38

AMM SubjectEquipment
747-400 AMM 25-21-
04
747-100/200/300
AMM 25-21-04
Sidewall and Insulation
747-400 AMM 25-25-
01
747-100/200/300
AMM 25-25-01
Passenger Seat
747-400 AMM 25-59-
01
747-100/200/300
AMM 25-59-01
Main Deck Cargo Compartment Sidewall Lining
747-400 AMM 25-59-
05
747-100/200/300
AMM 25-59-05
Main Deck Cargo Compartment Sidewall Insulation
747-400 AMM 25-52-
01
747-100/200/300
AMM 25-52-01
Cargo Compartment Sidewall Lining
747-400 AMM 25-52-
03
747-100/200/300
AMM 25-52-03
Preformed Lining Panels
747-400 AMM 25-52-
04
747-100/200/300
AMM 25-52-04
Cargo Compartment Insulation
747-400 AMM 25-53-
15
747-100/200/300
AMM 25-53-15
Ball Transfer Panels
2. Group 1-2, 4:
Do an internal HFEC inspection for cracks in the skin next to the shear tie as give in FIGURE 8.
3. Group 3:
If the shear tie is L-shaped, do an internal HFEC inspection for cracks in the skin next to the shear
tie as given in FIGURE 8. If the shear tie is T-shaped, do an internal HFEC inspection for cracks
in the skin next to the shear tie as given in FIGURE 9.
4. Group 1-2, 4:
If no crack is found, repeat the internal HFEC inspection for cracks in the skin next to the shear
tie as given in FIGURE 8 at the interval given in Paragraph 1.E., Compliance.
5. Group 3:
If no crack is found, repeat the internal HFEC inspection for cracks in the skin as given in FIGURE
8 or FIGURE 9, as applicable, at the interval given in Paragraph 1.E., Compliance.
6. If any crack is found, contact Boeing for repair instructions and do the repair.
7. Re-install removed equipment as necessary, and as applicable, and return the airplane to a
serviceable condition. Refer to the following procedures, as necessary.
AMM SubjectEquipment
747-400 AMM 25-21-
04
747-100/200/300
AMM 25-21-04
Sidewall and Insulation
747-400 AMM 25-25-
01
747-100/200/300
AMM 25-25-01
Passenger Seat
747-400 AMM 25-59-
01
747-100/200/300
AMM 25-59-01
Main Deck Cargo Compartment Sidewall Lining
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
38 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 39

AMM SubjectEquipment
747-400 AMM 25-59-
05
747-100/200/300
AMM 25-59-05
Main Deck Cargo Compartment Sidewall Insulation
747-400 AMM 25-52-
01
747-100/200/300
AMM 25-52-01
Cargo Compartment Sidewall Lining
747-400 AMM 25-52-
03
747-100/200/300
AMM 25-52-03
Preformed Lining Panels
747-400 AMM 25-52-
04
747-100/200/300
AMM 25-52-04
Cargo Compartment Insulation
747-400 AMM 25-53-
15
747-100/200/300
AMM 25-53-15
Ball Transfer Panels
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1: May 24, 2012
39 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
This Figure applies only to: Group 1-2, 4.
STA
1000
STA
520
• SEE DOO
STA
540
STA  STA
520  STA  600  STA  700  STA  800  900  STA  980  000 L
- S-6L
J 0
FOR TYPICAL
SHEAR TIE  - S-12L
SEE
FOR TYPICAL
CRACK LOCATIONS  - S-19L
SEE  •o•c  o o
• S-23L
S-26L
- S-34L
- S-39L
- S-44L
• S-47L
UP  LEFT SIDE PASSENGER
(TYPICAL)
FWD <  1372576
FIGURE 1: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 1 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  40 of 83

### Page 41 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
520  STA  600  STA  700  STA  STA  980  STA
800  900  1000
1S-0
- S-6L
FOR TYPICAL  - S-12L
SHEAR TIE
SEE O
FOR TYPICAL  • S-19L
CRACK LOCATIONS
SEE  S-23L
• S-26L
S-34L
S-39L
• S-44L
S-47L
UP  LEFT  SIDE-FREIGHTERS
WITH A  NOSE CARGO DOOR
FWD <  (TYPICAL)
FIGURE 1: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 2 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  41 of 83

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
520  STA  580  STA  620  680  STA  740  STA  780  STA  1000
1— s-0
- S-6L
FOR TYPICAL  - S-12L
SHEAR TIE
SEE (D)
FOR TYPICAL  - S-19L
CRACK LOCATIONS
SEE  S-23L
S-26L
S-34L
- S-39L
S-44L
S-47L
UP  LEFT SIDE PASSENGER - SP
(TYPICAL)
FWD <  1498784
FIGURE 1: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 3 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  42 of 83

### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
+_+  - S-23L
-S-24L  L-SHAPED
SHEAR TIE  ' FASTENER
(TYPICAL)  HEAD
- S-25L
TYPICAL CRACK
FWDE
- INSPECTION AREA 0.10
(TYPICAL ALL LOCATIONS)
FASTENER
HEAD
L-SHAPED  • REINFORCING
SHEAR TIE  CHORD
(TYPICAL)  TYPICAL SHEAR
TIE, FASTENED
+++  OR INTEGRAL
• FRAME
• FOR TYPICAL
CRACK (S) LOCATION  FWD C
SEE (E  Л
INBD
A-A  1372845
FIGURE 1: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 4 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  43 of 83

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-30-03 as an accepted
procedure.
--SKINClean1
External detailed inspection or external high
frequency eddy current (HFEC) inspection as
given in 747 NDT, Part 6, 51-00-00 Figure 4
or 23, for skin cracks at fuselage frame shear
tie end fastener locations. (a)
--SKINInspect
(a) Skin fastener locations at "T" cross section shear ties are not required to be inspected.
FIGURE 1: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1 May 24, 2012
44 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
1000
STA
520
SEE ADO
STA
540
STA  STA
STA
1000  STA  980  STA  900  800  STA  700  STA  600  520
s-0-
S-6R-
•
S-12R -
S-19R -
S-23R
S-26R
FOR TYPICAL
SHEAR TIE
S-34R -  SEE O
FOR TYPICAL
S-39R -  CRACK LOCATIONS
SEE E
S-44R
S-47R
RIGHT SIDE PASSENGER  UP
(TYPICAL)
→ FWD  1373795
FIGURE 2: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 1 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  45 of 83

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
STA
STA  980  STA  STA  STA  700  600  520
1000  900  800
S-6R -
S-12R -
S-19R -
S-23R
S-26R
FOR TYPICAL
SHEAR TIE
S-34R  SEE
FOR TYPICAL
S-39R  CRACK LOCATIONS
SEE
S-44R
S-47R
RIGHT SIDE-FREIGHTERS  UP
WITH A NOSE CARGO DOOR
(TYPICAL)  → FWD
1373944
FIGURE 2: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 2 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  46 of 83

### Page 47 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  • STA
780  STA
STA  520
STA  580
STA  STA  620
1000  740  680
s-0-
S-6R -
S-12R -
S-19R -
S-23R -
S-26R
FOR TYPICAL
SHEAR TIE
S-34R -  SEE O
FOR TYPICAL
S-39R  CRACK LOCATIONS
SEE
S-44R-
S-47R
UP
RIGHT SIDE PASSENGER - SP
(TYPICAL)  → FWD
1500541
FIGURE 2: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 3 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  47 of 83

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
+77.
S-23R -  + + +
*+++
L-SHAPED  S-24R
FASTENER
SHEAR TIE
HEAD
(TYPICAL)
S-25R
TYPICAL CRACK
> FWD
INSPECTION AREA 0.10
(TYPICAL ALL LOCATIONS)
FASTENER
HEAD
REINFORCING  L-SHAPED
CHORD  SHEAR TIE
TYPICAL SHEAR  (TYPICAL)
TIE, FASTENED
OR INTEGRAL
FRAME -
FOR TYPICAL
• F WD  CRACK (S) LOCATION
SEE
INBD  A-A  1373960
FIGURE 2: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 4 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  48 of 83

### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-30-03 as an accepted
procedure.
--SKINClean1
External detailed inspection or external high
frequency eddy current (HFEC) inspection as
given in 747 NDT, Part 6, 51-00-00 Figure 4
or 23, for skin cracks at fuselage frame shear
tie end fastener locations. (a)
--SKINInspect
(a) Skin fastener locations at "T" cross section shear ties are not required to be inspected.
FIGURE 2: STATION 540 TO 980, BELOW STRINGER 23 TO ABOVE STRINGER 26 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1 May 24, 2012
49 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
This Figure applies only to: Group 1-2, 4.
STA
1000
STA
520
• SEE DOO
STA
540
STA  STA
520  STA  600  STA  700  STA  800  900  STA  980  • STA  1000
- S-6L
O
- S-12L
FOR TYPICAL
SHEAR TIE  — S-19L
SEE  o
FOR TYPICAL  - S-23L
CRACK LOCATIONS  S-26L
SEE
- S-34L
S-39L
- S-44L
S-47L
UP  LEFT SIDE PASSENGER
(TYPICAL)
1374002
FIGURE 3: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 1 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  50 of 83

### Page 51 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
520  STA  600  STA  700  STA  STA  980  STA
800  900  1000
- s-0
- S-6L
- S-12L
FOR TYPICAL
SHEAR TIE  - S-19L
SEE
FOR TYPICAL  • S-23L
CRACK LOCATIONS  S-26L
SEE
• S-34L
S-39L
- S-44L
S-47L
UP  LEFT SIDE-FREIGHTERS
WITH A NOSE CARGO DOOR
FWD <  (TYPICAL)
1374016
FIGURE 3: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 2 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  51 of 83

### Page 52 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
520  STA  580  STA  620  680  STA  740  STA  780  STA  1000
1— s-0
- S-6L
- S-12L
FOR TYPICAL
SHEAR TIE  - S-19L
SEE
- S-23L
FOR TYPICAL
• S-26L
CRACK LOCATIONS
SEE
S-34L
S-39L
S-44L
S-47L
UP  LEFT SIDE PASSENGER - SP
(TYPICAL)
FWD <  1500542
FIGURE 3: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 3 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  52 of 83

### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
- STR IX"
- STR "X"  L-SHAPED  SHEAR TIE  FASTENER
(TYPICAL)  HEAD
- STR 'X"
TYPICAL CRACK
FWDE
- INSPECTION AREA 0.10
(TYPICAL ALL LOCATIONS)
FASTENER
HEAD
L-SHAPED  - REINFORCING
SHEAR TIE  CHORD
(TYPICAL)  TYPICAL SHEAR
TIE, FASTENED
- -  OR INTEGRAL
→ FRAME
• FOR TYPICAL
CRACK (S) LOCATION  FWD C
SEE (E)
INBD
A-A  1374173
FIGURE 3: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 4 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  53 of 83

### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-30-03 as an accepted
procedure.
--SKINClean1
External detailed inspection or external high
frequency eddy current (HFEC) inspection as
given in 747 NDT, Part 6, 51-00-00 Figure 4
or 23, for skin cracks at fuselage frame shear
tie end fastener locations. (a) (b)
--SKINInspect
(a) Skin fastener locations at "T" cross section shear ties are not required to be inspected.
(b) Inspection of the skin under the wing to body fairing attachment brackets is not required.
FIGURE 3: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - LEFT SIDE - EXTERNAL
SKIN INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1 May 24, 2012
54 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
1000
STA
520
SEE AOO
STA
540
STA  • STA
STA
STA  980  STA  STA  700  STA  600  520
1000  900
s-0-
S-6R -
S-12R -
S-19R -
S-23R
S-26R
FOR TYPICAL
S-34R
SHEAR TIE
SEE  S-39R
FOR TYPICAL
CRACK LOCATIONS  S-44R
SEE
S-47R
RIGHT SIDE PASSENGER  UP
(TYPICAL)
→ FWD  1374200
FIGURE 4: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 1 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  55 of 83

### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
STA  980  STA  STA  STA  700  600  STA  520
1000  900  800
S-O—!
S-6R -
S-12R -
S-19R -
S-23R
S-26R
FOR TYPICAL
S-34R
SHEAR TIE
SEE  S-39R
FOR TYPICAL
CRACK LOCATIONS  S-44R
SEE
S-47R
RIGHT SIDE-FREIGHTERS  UP
WITH A NOSE CARGO DOOR
(TYPICAL)  → FWD
1374212
FIGURE 4: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 2 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  56 of 83

### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
540
STA  STA
STA  780  STA  STA  STA  620  580  STA  520
1000  740  680
S-0-
S-6R -
S-12R -
S-19R -
S-23R-
S-26R
S-34R
• FOR TYPICAL
SHEAR TIE
S-39R
SEE
S-44R  FOR TYPICAL
CRACK LOCATIONS
S-47R  SEE
UP
RIGHT SIDE PASSENGER - SP
(TYPICAL)  → FWD
1500544
FIGURE 4: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 3 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  57 of 83

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
+7+
STR "X"
FASTENER  L-SHAPED  STR "X"-
HEAD  SHEAR TIE
(TYPICAL)
STR "X"
TYPICAL CRACK
> FWD
INSPECTION AREA 0.10
(TYPICAL ALL LOCATIONS)
FASTENER
HEAD
REINFORCING  L-SHAPED
CHORD  SHEAR TIE
TYPICAL SHEAR  (TYPICAL)
TIE, FASTENED
OR INTEGRAL  ++1
FRAME ~
FOR TYPICAL
• FWD  CRACK (S) LOCATION
SEE
INBD  A-A  1374215
FIGURE 4: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 4 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  58 of 83

### Page 59

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-30-03 as an accepted
procedure.
--SKINClean1
External detailed inspection or external high
frequency eddy current (HFEC) inspection as
given in 747 NDT, Part 6, 51-00-00 Figure 4
or 23, for skin cracks at fuselage frame shear
tie end fastener locations. (a) (b)
--SKINInspect
(a) Skin fastener locations at "T" cross section shear ties are not required to be inspected.
(b) Inspection of the skin under the wing to body fairing attachment brackets is not required.
FIGURE 4: STATION 540 TO 980, BELOW STRINGER 26 TO ABOVE STRINGER 39 - RIGHT SIDE -
EXTERNAL SKIN INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 08, 2008
747-53A2682Revision 1 May 24, 2012
59 of 83
BOEING SERVICE BULLETIN 747-53A2682
ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-53A2682
ALERT  ALERT
STA
1000
STA
520
SEE ADO
STA
540
STA  STA
STA
520  600  700  STA  STA  STA  980  STA
800  900  1000
- s-0
- S-6L
J
- S-12L
- S-19L
U
- S-23L
FOR TYPICAL  S-26L
SHEAR TIE
SEE D
FOR TYPICAL  S-34L
CRACK LOCATIONS
SEE E  S-39L
S-44L
S-47L
• S-39R
UP  PASSENGER
(TYPICAL)
FWD C
FIGURE 5: STATION 540 TO 980, BELOW STRINGER 39 LEFT TO BELOW STRINGER 39 RIGHT -
EXTERNAL SKIN INSPECTION
(SHEET 1 OF 5)
Original Issue: May 08, 2008
Revision 1 May 24, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2682
Work - See page 1 for details.  60 of 83

The text continues at https://openairdocs.org/service-documents/boeing/747-53a2682/file/d5972d0a2432.md?from=61

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.