# Boeing Alert Service Bulletin 747-51A2060: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0718; AD 2010-05-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 747-51A2060](https://openairdocs.org/service-documents/boeing/747-51a2060.md)
- Title as filed: Boeing Service Bulletin
- Pages: 196
- PDF: https://openairdocs.org/files/sha256/b8/b6/b8b6611b3bbd47b9d87438cc0a9c02a7659ed57cca8efe2b93b546bd22d125e4
- Page: https://openairdocs.org/service-documents/boeing/747-51a2060/file/b8b6611b3bbd

## Text

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### Page 1

Commercial        
Airplane
Group 
 747
Service Bulletin
ALERT
Number: 747-51A2060
Date: October 30, 2008
ATA System: 5100 5331 5500 5730
SUBJECT: STRUCTURES - Structures - Wing Side of Body Joint, Horizontal Stabilizer Side of
Body Joint, and Fuselage Circumferential Splice Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P .O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery 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.
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Table of Contents
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 0
D. Description .............................................. 2 1
E. Compliance .............................................. 2 3
F . Approval ............................................... 2 8
G. Manpower .............................................. 2 8
H. Weight and Balance Changes .................................... 3 0
I. Electrical Load Data ......................................... 3 0
J. References .............................................. 3 0
1. Existing Data: .......................................... 3 0
2. Data supplied with this Service Bulletin: ........................... 3 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 1
K. Publications Affected ......................................... 3 3
L. Interchangeability and Intermixability of Parts ........................... 3 3
2. MATERIAL INFORMATION ........................................ 3 5
A. Material - Price and Availability ................................... 3 5
B. Industry Support Information .................................... 3 5
C. Parts Necessary For Each Airplane ................................. 3 5
1. Kits/Parts: ............................................ 3 5
2. Parts and Materials Supplied by the Operator: ........................ 3 5
3. Parts Modified and Reidentified: ................................ 3 5
4. Parts Removed and Not Replaced: .............................. 3 5
D. Parts Necessary to Change Spares ................................. 3 5
E. Special Tooling - Price and Availability ............................... 3 5
F . Special Tooling Necessary to do this Service Bulletin ....................... 3 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 7
A. GENERAL INFORMATION ..................................... 3 7
B. WORK INSTRUCTIONS ....................................... 3 9
FIGURE 1: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - LEFT SIDE .... 4 8
FIGURE 2: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - RIGHT SIDE .... 5 1
FIGURE 3: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - LEFT
SIDE .............................................. 5 4
FIGURE 4: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - RIGHT
SIDE .............................................. 5 8
FIGURE 5: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (MIDDLE) UPPER SURFACE - LEFT
SIDE .............................................. 6 2
FIGURE 6: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (MIDDLE) UPPER SURFACE - RIGHT
SIDE .............................................. 6 5
FIGURE 7: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (FORWARD) UPPER SURFACE -
LEFT SIDE ........................................... 6 8
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FIGURE 8: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (FORWARD) UPPER SURFACE -
RIGHT SIDE .......................................... 7 1
FIGURE 9: DETAILED INSPECTION OF WING SOB JOINT LOWER SURFACE - LEFT SIDE .... 7 4
FIGURE 10: DETAILED INSPECTION OF WING SOB JOINT LOWER SURFACE - RIGHT SIDE . . . 78
FIGURE 11: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) LOWER SURFACE - LEFT
SIDE .............................................. 8 2
FIGURE 12: OPEN-HOLE INSPECTION OF WING SOB JOINT (AFT) LOWER SURFACE - RIGHT SIDE
.................................................. 8 5
FIGURE 13: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (MIDDLE) LOWER SURFACE - LEFT
SIDE .............................................. 8 8
FIGURE 14: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (MIDDLE) LOWER SURFACE -
RIGHT SIDE .......................................... 9 1
FIGURE 15: DETAILED INSPECTION OF HORIZONTAL STABILIZER SOB JOINT - LEFT SIDE . . . 94
FIGURE 16: DETAILED INSPECTION OF HORIZONTAL STABILIZER SOB JOINT - RIGHT SIDE . . 102
FIGURE 17: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT UPPER HINGE
FITTING - LEFT SIDE .................................... 1 1 0
FIGURE 18: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT UPPER HINGE
FITTING - RIGHT SIDE .................................... 1 1 3
FIGURE 19: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT LOWER HINGE
FITTING - LEFT SIDE .................................... 1 1 6
FIGURE 20: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT LOWER HINGE
FITTING - RIGHT SIDE .................................... 1 1 9
FIGURE 21: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
UPPER CHORD AND TERMINAL FITTING - LEFT SIDE ................. 1 2 2
FIGURE 22: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
UPPER CHORD AND TERMINAL FITTING - RIGHT SIDE ................ 1 2 6
FIGURE 23: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
LOWER CHORD AND TERMINAL FITTING - LEFT SIDE ................. 1 3 0
FIGURE 24: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
LOWER CHORD AND TERMINAL FITTING - RIGHT SIDE ................ 1 3 3
FIGURE 25: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
UPPER CHORD AND OUTBOARD SKIN - LEFT SIDE .................. 1 3 6
FIGURE 26: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
UPPER CHORD AND OUTBOARD SKIN - RIGHT SIDE .................. 1 3 9
FIGURE 27: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
UPPER CHORD AND CENTER SECTION SKIN - LEFT SIDE .............. 1 4 2
FIGURE 28: OPEN-HOLE HFEC INSPECTION OF HORIZONTAL STABILIZER SOB JOINT REAR SPAR
UPPER CHORD AND CENTER SECTION SKIN - RIGHT SIDE .............. 1 4 5
FIGURE 29: DETAILED INSPECTION OF THE FUSELAGE SKIN, STRINGERS, AND STRINGER SPLICE
FITTINGS (NON-SUD AIRPLANES). [Group 1, 5] ..................... 1 4 8
FIGURE 30: DETAILED INSPECTION OF THE FUSELAGE SKIN, STRINGERS, AND STRINGER SPLICE
FITTINGS (SP AIRPLANES). [Group 2] ........................... 1 5 6
FIGURE 31: DETAILED INSPECTION OF THE FUSELAGE SKIN, STRINGERS, AND STRINGER SPLICE
FITTINGS (SUD AIRPLANES). [Group 3-4] ......................... 1 6 4
FIGURE 32: OPEN-HOLE HFEC INSPECTION OF FUSELAGE CIRCUMFERENTIAL SPLICES (NON-SUD
AIRPLANES). [Group 1, 5] .................................. 1 7 1
FIGURE 33: OPEN-HOLE HFEC INSPECTION OF FUSELAGE CIRCUMFERENTIAL SPLICES (SP
AIRPLANES). [Group 2] ................................... 1 7 5
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FIGURE 34: OPEN-HOLE HFEC INSPECTION OF FUSELAGE CIRCUMFERENTIAL SPLICES (SUD
AIRPLANES). [Group 3-4] .................................. 1 7 9
FIGURE 35: SURFACE HFEC INSPECTION OF FUSELAGE SKIN (NON-SUD AIRPLANES). [Group 1, 5]
................................................. 1 8 3
FIGURE 36: SURFACE HFEC INSPECTION OF FUSELAGE SKIN (SP AIRPLANES). [Group 2] . . . 188
FIGURE 37: SURFACE HFEC INSPECTION OF FUSELAGE SKIN (SUD AIRPLANES). [Group 3-4] . 193
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Commercial        
Airplane
Group 
 747
Service Bulletin
ALERT
SummaryNumber: 747-51A2060Date: October 30, 2008
ATA System: 5100 5331 5500 5730
SUBJECT: STRUCTURES - Structures - Wing Side of Body Joint, Horizontal Stabilizer Side of
Body Joint, and Fuselage Circumferential Splice 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
Accomplishment of the inspections in this service bulletin will find fatigue cracks in the wing side-of-body (SOB)
joint upper and lower surfaces, horizontal stabilizer SOB joint upper and lower surfaces, and the fuselage skin
and circumferential splices. The cracks could occur at multiple adjacent locations in the inspection areas and
join together to form large cracks. The cracks that are not found and repaired could compromise the structural
integrity and lead to loss of controllability and a rapid decompression of the airplane.
Boeing’s analysis shows that the 747 wing SOB joint splices, horizontal stabilizer SOB joint splices, fuselage
skin and circumferential splices are susceptible to fatigue cracks. The fatigue cracks are due to high cyclic loads
on the airplane.
The accomplishment instructions in this service bulletin provide additional structural maintenance
recommendations to support operation of airplanes and preclude possible fatigue cracks in the inspection areas
up to the Initial Operational Limit (IOL). The current IOL is 35,000 total flight cycles or 135,000 total flight hours
(165,000 total flight hours for the 747-400, 747-400D, and 747-400F airplanes).
The inspections in this service bulletin will make sure that fatigue cracks are found and repaired in the wing SOB
joint upper and lower surfaces, horizontal stabilizer SOB joint upper and lower surfaces, and the fuselage skin
and circumferential splices. Evaluation of the inspection reports will allow Boeing to determine if additional
inspections are necessary. The area of the inspection may change with the inspection findings reported to
Boeing.
Boeing Service Related Problem (SRP) 747-SRP-51-0014 is related to this service bulletin.
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ACTION
As the inspections given in this service bulletin are developed to find fatigue cracking of airplanes that are near
the IOL, Boeing recommends that the inspections not be done earlier than the times given in Paragraph 1.E.,
Compliance.
Do the following as given in Paragraph 1.E., Compliance:
— Wing SOB Joint
— Do a Detailed Inspection of the wing SOB joint upper and lower surfaces for any crack.
— Do an Open-Hole High Frequency Eddy Current (HFEC) Inspection of the wing SOB joint upper and
lower surfaces for any crack.
— Horizontal Stabilizer SOB Joint
— Do a Detailed Inspection of the horizontal stabilizer SOB joint surfaces for any crack.
— Do Surface and Open-Hole HFEC Inspections of the horizontal stabilizer SOB joint upper and lower
surfaces for any crack.
— Fuselage Skin and Circumferential Splices
— Do a Detailed Inspection of the fuselage skin, stringers, and stringer splice fittings for any crack. Do a
repetitive Detailed Inspection of the circumferential skin, stringers, and stringer splice fittings for any
crack.
— Do Surface and Open-Hole HFEC Inspections of the fuselage skin and circumferential splices for any
crack.
Contact Boeing with any crack finding for repair instructions. Repair any crack found as given by Boeing.
EFFECTIVITY
All 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F , 747-300, 747-400, 747-400D, 747-400F ,
747SP , and 747SR airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Federal Aviation Administration (FAA) Airworthiness Directives FAA AD 2004-07-22 R1, FAA AD 2004-03-09,
and FAA AD 2006-10-16 are related to this service bulletin.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures
given in this service bulletin.
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MANPOWER
Elapsed HoursTotal Task HoursAirplanes
520.752658All
MATERIAL INFORMATION
None.
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BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
STA
1961
STA
1350
STA
1000
DO A DETAILED, SURFACE HFEC, AND
OPEN HOLE HFEC INSPECTIONS OF
THE WING SIDE OF BODY JOINT,
HORIZONTAL STABILIZER SIDE OF BODY
JOINT, AND FUSELAGE SKIN AND
CIRCUMFERENTIAL SPLICES FOR ANY
CRACK. IF ANY CRACK IS FOUND, CONTACT
BOEING FOR REPAIR INSTRUCTIONS. REPAIR
ANY CRACK FOUND AS GIVEN BY BOEING.
1572773
October 30, 2008
747-51A2060
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Commercial        
Airplane
Group 
 747
Service Bulletin
ALERT
Number: 747-51A2060
Date: October 30, 2008
ATA System: 5100 5331 5500 5730
SUBJECT: STRUCTURES - Structures - Wing Side of Body Joint, Horizontal Stabilizer Side of
Body Joint, and Fuselage Circumferential Splice 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.
NOTE: 747-8 and 747-8F series airplanes are not affected by this service bulletin.
NOTE: This Service Bulletin is for the airplanes identified below. The Effectivity list shown below
is complete for airplanes through line number 1419. Airplanes after line number 1419 are
also affected by this service bulletin, and are in Group(s): 1,2,3,4,5
DESCRIPTIONCONFIGURATIONGROUP
747-100/100B/200B/200C/200F/SR airplanes (Non-SUD).-1
747-SP airplanes.-2
747-100B SUD/300 and 747-100/200B Boeing-Modified Streched
Upper Deck Modification airplanes.
-3
747-400/400D airplanes (SUD).-4
747-400F airplanes (Non-SUD).-5
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DESCRIPTIONCONFIGURATIONGROUP
747-400LCF airplanes.-6
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
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
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GroupVariable Number
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
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
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GroupVariable Number
1RD311
1RD351 - RD358
1RD361 - RD366
3RD381 - RD383
1RD411 - RD414
1RD421 - RD426
1RD431 - RD435
1RD441 - RD442
1RD451 - RD456
1RD461
1RD471 - RD475
1RD513 - RD519
1RD531 - RD533
1RD551
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD621 - RD623
1RD641 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
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GroupVariable Number
4RF001 - RF006
2RG001 - RG009
2RG091
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
5RL401 - RL403
5RL411 - RL436
5RL451 - RL456
5RL461 - RL462
5RL471 - RL481
5RL491 - RL492
5RL501 - RL502
5RL511 - RL516
5RL521 - RL522
5RL531 - RL534
5RL551
5RL561 - RL568
5RL571 - RL572
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GroupVariable Number
5RL576 - RL577
5RL579
5RL581 - RL586
5RL651 - RL655
5RL671 - RL675
5RL681 - RL684
5RL751 - RL752
4RM001 - RM007
4RM010 - RM013
4RM021 - RM024
4RM026 - RM030
4RM036 - RM045
4RM051 - RM053
4RM071
4RM081 - RM084
4RM091
4RM096 - RM097
4RM116 - RM117
4RM126 - RM132
4RM136 - RM147
4RM156 - RM158
4RM166 - RM177
4RM191 - RM192
4RM231 - RM233
4RM241 - RM246
4RM261 - RM264
4RM316 - RM318
4RM331 - RM333
4RM341
4RM351 - RM355
4RM366 - RM367
4RM401 - RM403
4RM426
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GroupVariable Number
4RM431
4RM441 - RM443
4RM445
4RM801 - RM803
4RM811 - RM813
5RM851 - RM859
5RM861 - RM863
5RM871 - RM899
5RM901 - RM906
5RM911
1RR001 - RR005
1RR021 - RR025
1RR031
1RR201 - RR206
1RR221 - RR226
1RR261 - RR267
1RR301 - RR310
1RR331 - RR332
1RR336
1RR341 - RR345
1RR361 - RR362
1RR421 - RR422
1RR431 - RR432
1RR441 - RR442
1RR451
1RR501 - RR504
1RR521 - RR522
1RR526
1RR531
1RR551 - RR556
1RR561
1RR566
5RR701
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GroupVariable Number
5RR721 - RR724
5RR746 - RR748
5RR851 - RR856
5RR861 - RR862
5RR951 - RR952
3RS001 - RS002
3RS201
3RS211 - RS212
3RS221 - RS222
3RS231 - RS241
3RS251 - RS259
3RS263
3RS265 - RS268
3RS271 - RS276
3RS291 - RS292
3RS301 - RS306
3RS311 - RS320
3RS331 - RS333
3RS341 - RS342
3RS699
3RS701 - RS703
3RS711 - RS713
3RS721 - RS722
3RS731 - RS732
3RS741 - RS743
3RS751 - RS752
3RS761 - RS762
3RS771
3RS781 - RS782
3RS786
4RT001 - RT014
4RT021 - RT022
4RT031 - RT035
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GroupVariable Number
4RT041 - RT047
4RT061
4RT071 - RT075
4RT101 - RT103
4RT121
4RT131 - RT137
4RT151 - RT152
4RT161 - RT168
4RT401 - RT412
4RT431 - RT447
4RT451 - RT469
4RT471 - RT499
4RT501 - RT535
4RT551 - RT568
4RT571 - RT591
4RT601 - RT630
6RT631 - RT632
4RT633 - RT657
4RT671 - RT673
4RT681 - RT682
4RT691 - RT699
4RT701 - RT704
4RT711 - RT717
4RT741 - RT742
6RT743
4RT744 - RT757
4RT776 - RT777
4RT781 - RT784
4RT801 - RT803
4RT811 - RT814
4RT831 - RT837
4RT861 - RT864
6RT876
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GroupVariable Number
4RT877 - RT880
4RT931 - RT932
4RT945 - RT949
4RT951 - RT955
4RT966 - RT967
4RU001 - RU006
4RU016 - RU017
4RU031 - RU032
4RU051 - RU052
4RU059 - RU062
4RU081 - RU083
4RU101 - RU102
4RU121 - RU132
4RU801 - RU809
4RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None
C. Reason
Accomplishment of the inspections in this service bulletin will find fatigue cracks in the wing side-of-body
(SOB) joint upper and lower surfaces, horizontal stabilizer SOB joint upper and lower surfaces, and
the fuselage skin and circumferential splices. The cracks could occur at multiple adjacent locations in
the inspection areas and join together to form large cracks. The cracks that are not found and repaired
could compromise the structural integrity and lead to loss of controllability and a rapid decompression
of the airplane.
Boeing’s analysis shows that the 747 wing SOB joint splices, horizontal stabilizer SOB joint splices,
fuselage skin and circumferential splices are susceptible to fatigue cracks. The fatigue cracks are due
to high cyclic loads on the airplane.
The accomplishment instructions in this service bulletin provide additional structural maintenance
recommendations to support operation of airplanes and preclude possible fatigue cracks in the inspection
areas up to the Initial Operational Limit (IOL). The current IOL is 35,000 total flight cycles or 135,000
total flight hours (165,000 total flight hours for the 747-400, 747-400D, and 747-400F airplanes).
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The inspections in this service bulletin will make sure that fatigue cracks are found and repaired in the
wing SOB joint upper and lower surfaces, horizontal stabilizer SOB joint upper and lower surfaces, and
the fuselage skin and circumferential splices. Evaluation of the inspection reports will allow Boeing to
determine if additional inspections are necessary. The area of the inspection may change with the
inspection findings reported to Boeing.
Boeing Service Related Problem (SRP) 747-SRP-51-0014 is related to this service bulletin.
D. Description
As the inspections given in this service bulletin are developed to find fatigue cracking of airplanes that
are near the IOL, Boeing recommends that the inspections not be done earlier than the times given in
Paragraph 1.E., Compliance.
Do the following as given in Paragraph 1.E., Compliance:
— Wing SOB Joint
— Do a Detailed Inspection of the wing SOB joint upper and lower surfaces for any crack.
— Do an Open-Hole High Frequency Eddy Current (HFEC) Inspection of the wing SOB joint
upper and lower surfaces for any crack.
— Horizontal Stabilizer SOB Joint
— Do a Detailed Inspection of the horizontal stabilizer SOB joint for any crack.
— Do Surface and Open-Hole HFEC Inspections of the horizontal stabilizer SOB joint upper and
lower surfaces for any crack.
— Fuselage Skin and Circumferential Splices
— Do a Detailed Inspection of the fuselage skin, stringers, and stringer splice fittings for any
crack. Do a repetitive Detailed Inspection of the fuselage skin, stringers, and stringer splice
fittings for any crack.
— Do Surface and Open-Hole HFEC Inspections of the fuselage skin and circumferential splices
for any crack.
Contact Boeing with any crack finding for repair instructions. Repair any crack found as given by Boeing.
NOTE: Service Bulletins 747-57-2071, 747-57A2309, 747-57-2110, 747-57A2314, and 747-55A2050
provide additional access and inspection information for some of the areas described in this
service bulletin.
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
131, 132, 191, 192, 233, 234, 241, 242, 243,
244, 251, 252, 253, 254, 263, 264, 291, 292,
313, 314, 333, 334, 338, 343, 344, 348, 541,
544, 641, 644
747-100, 747-100B, 747-200B,
747-200C, 747-200F , 747SR
Group 2:
Affected Maintenance Zones
ZoneModel
131, 132, 191, 192, 241, 242, 243, 244, 253,
254, 291, 292, 313, 314, 333, 338, 343, 348,
541, 544, 641, 644
747SP
Group 3:
Affected Maintenance Zones
ZoneModel
131, 132, 191, 192, 233, 234, 241, 242, 243,
244, 251, 252, 253, 254, 263, 264, 291, 292,
313, 314, 333, 334, 338, 343, 344, 348, 541,
544, 641, 644
747-200B
Group 3:
Affected Maintenance Zones
ZoneModel
131, 132, 191, 192, 225, 226, 241, 242, 243,
244, 251, 252, 253, 254, 263, 264, 291, 292,
313, 314, 333, 334, 338, 343, 344, 348, 541,
544, 641, 644
747-100B SUD, 747-300
Group 4:
Affected Maintenance Zones
ZoneModel
131, 132, 191, 192, 225, 226, 241, 242, 243,
244, 251, 252, 253, 254, 263, 264, 291, 292,
313, 314, 334, 335, 338, 339, 344, 345, 348,
349, 541, 544, 641, 644
747-400, 747-400D
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Group 5:
Affected Maintenance Zones
ZoneModel
131, 132, 191, 192, 233, 234, 241, 242, 243,
244, 251, 252, 253, 254, 261, 262, 263, 264,
291, 292, 313, 314, 334, 335, 338, 339, 344,
345, 348, 349, 541, 544, 641, 644
747-400F
Group 6:
Affected Maintenance Zones
ZoneModel
131, 132, 191, 192, 291, 292, 313, 314, 334,
335, 338, 339, 344, 345, 348, 349, 541, 544,
641, 644
747-400
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin.The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Federal Aviation Administration (FAA) Airworthiness Directives FAA AD 2004-07-22 R1, FAA AD
2004-03-09, and FAA AD 2006-10-16 are related to this service bulletin.
Group 1-5:
Table 1: Detailed Inspection of Fuselage Circumferential Splices.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1 year
after the date on
this service
bulletin.
Before 25,000
total flight
cycles.
Do a Detailed Inspection
of the fuselage skin,
stringers, and stringer
splice fittings for any
crack as given in PART 4
of Paragraph 3.B., Work
Instructions.
All airplanes.
6,000 flight cycles.Within 6,000 flight cycles from
previous inspection.
Do a Detailed Inspection
of the fuselage skin,
stringers, and stringer
splice fittings for any
crack as given in PART 4
of Paragraph 3.B., Work
Instructions.
No crack found.
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Group 1-5:
Table 1: Detailed Inspection of Fuselage Circumferential Splices.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Report any crack finding
to Boeing as given in
PART 5 of Paragraph
3.B., Work Instructions.
Repair any crack found
as given by Boeing.
Any crack found.
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Group 1-3:
Table 2: Inspection of Wing SOB Joint, Horizontal Stabilizer SOB Joint, and Fuselage Circumferential
Splices for Group 1-3.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1 year
after the date on
this service
bulletin.
Before 30,000
total flight cycles
or 115,000 total
flight hours;
whichever
occurs first. Do
not accomplish
the inspections
unless the
airplane has at
least
accumulated
either 28,500
total flight cycles
or 110,000 total
flight hours.
Do a Detailed Inspection
of the wing SOB joint
upper and lower surfaces
for any crack as given in
PART 2 of Paragraph
3.B., Work
Instructions.(a)
All airplanes
Do an Open-Hole HFEC
Inspection of the wing
SOB joint upper and
lower surfaces for any
crack as given in PART 2
of Paragraph 3.B., Work
Instructions.(a)
Do a Detailed Inspection
of the horizontal stabilizer
SOB joint for any crack
as given in PART 3 of
Paragraph 3.B., Work
Instructions.
Do a Surface and
Open-Hole HFEC
Inspection of the
horizontal stabilizer SOB
joint upper and lower
surfaces for any crack as
given in PART 3 of
Paragraph 3.B., Work
Instructions.
Do a Surface and
Open-Hole HFEC
Inspection of the fuselage
skin and circumferential
splices for any crack as
given in PART 4 of
Paragraph 3.B., Work
Instructions.
--No more action is
necessary.
No crack found.
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Group 1-3:
Table 2: Inspection of Wing SOB Joint, Horizontal Stabilizer SOB Joint, and Fuselage Circumferential
Splices for Group 1-3.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Report any crack finding
to Boeing as given in
PART 5 of Paragraph
3.B., Work Instructions.
Repair any crack found
as given by Boeing.
Any crack found.
(a) If the modification was accomplished as given in Service Bulletin 747-57A2314, the inspection of the
affected area of the modification can be deferred until the post modification inspection period as given
in Service Bulletin 747-57A2314.
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Group 4-6:
Table 3: Inspection of Wing SOB Joint, Horizontal Stabilizer SOB Joint, and Fuselage Circumferential
Splices for Group 4-6.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1 year
after the date on
this service
bulletin.
Before 30,000
total flight cycles
or 135,000 total
flight hours;
whichever
occurs first. Do
not accomplish
the inspections
unless the
airplane has at
least
accumulated
either 28,500
total flight cycles
or 130,000 total
flight hours.
Do a Detailed Inspection
of the wing SOB joint
upper and lower surfaces
for any crack as given in
PART 2 of Paragraph
3.B., Work Instructions.
All airplanes.
Do an Open-Hole HFEC
Inspection of the wing
SOB joint upper and
lower surfaces for any
crack as given in PART 2
of Paragraph 3.B., Work
Instructions.
Do a Detailed Inspection
of the horizontal stabilizer
SOB joint for any crack
as given in PART 3 of
Paragraph 3.B., Work
Instructions.
Do a Surface and
Open-Hole HFEC
Inspection of the
horizontal stabilizer SOB
joint upper and lower
surfaces for any crack as
given in PART 3 of
Paragraph 3.B., Work
Instructions.
Do a Surface and
Open-Hole HFEC
Inspection of the fuselage
skin and circumferential
splices for any crack as
given in PART 4 of
Paragraph 3.B., Work
Instructions.(a)
--No more action is
necessary.
No crack found.
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Group 4-6:
Table 3: Inspection of Wing SOB Joint, Horizontal Stabilizer SOB Joint, and Fuselage Circumferential
Splices for Group 4-6.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Report any crack finding
to Boeing as given in
PART 5 of Paragraph
3.B., Work Instructions.
Repair any crack found
as given by Boeing.
Any crack found.
(a) The instructions for Group 6 will require unique drawings for fuselage circumferential splices. It is suggested
that operators contact Boeing with requests for data at least one year before the data will be needed.
The airplane is not to be operated without this inspection beyond the compliance time given in this table.
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.
This service bulletin has been approved by the FAA. In addition, The Manager of the FAA Seattle ACO
approves the accomplishment of the applicable open-hole HFEC inspection procedures of this service
bulletin as an alternative method of compliance (AMOC) to the corresponding inspection requirements
of paragraphs (h) and (i) of FAA AD 2004-07-22 R1 for SSI E-3 (A-F), E-9 (A-E), W-18 (A-C), W-19
(A-B) and F-26 (A, C, and E) of Supplemental Structural Inspection Document (SSID) D6-35022,
Revision G, dated December 2000. This AMOC only applies to the areas inspected as given in this
service bulletin. No further inspection as given in SSID is required for the areas after the open-hole
HFEC inspections. All provisions of AD 2004-07-22 R1 that are not specifically referenced in the
preceding statement, including the initial inspection threshold per paragraph (i) of AD 2004-07-22 R1,
remain fully applicable and must be complied with.
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. The estimate does not include
additional time that may be necessary for additional inspections, repairs as a result of your reported
inspection findings to Boeing and subsequent additional work, and restoration. Adjust the estimate with
operator task hour data if necessary.The estimate does not include lost time.These are some examples
of lost time:
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 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
Persons
Task
6.7554.008PART 1 - ACCESS
(Wing SOB Joint,
Horizontal Stabilizer
SOB Joint, and
Fuselage)
5.5022.004PART 2 -
INSPECTION OF
WING SOB JOINT
(FIGURE 1 and
FIGURE 2)
2.259.004PART 2 (FIGURE 3
and FIGURE 4)
3.006.002PART 2 (FIGURE 5
and FIGURE 6)
3.006.002PART 2 (FIGURE 7
and FIGURE 8)
7.5030.004PART 2 (FIGURE 9
and FIGURE 10)
4.0016.004PART 2 (FIGURE
11 and FIGURE 12)
4.0016.004PART 2 (FIGURE
13 and FIGURE 14)
9.5038.004PART 3 -
INSPECTION OF
HORIZONTAL
STABILIZER SOB
JOINT (FIGURE 15
and FIGURE 16)
124.00496.004PART 3 (FIGURE
17 and FIGURE 18)
32.00128.004PART 3 (FIGURE
19 and FIGURE 20)
32.00128.004PART 3 (FIGURE
21 and FIGURE 22)
36.00144.004PART 3 (FIGURE
23 and FIGURE 24)
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Elapsed HoursTask HoursNumber of
Persons
Task
30.00120.004PART 3 (FIGURE
25 and FIGURE 26)
32.00128.004PART 3 (FIGURE
27 and FIGURE 28)
20.7583.004PART 4 -
INSPECTION OF
FUSELAGE SKIN
AND
CIRCUMFERENTIAL
SPLICES (FIGURE
29, FIGURE 30, or
FIGURE 31)
140.001120.008PART 4 (FIGURE
32, FIGURE 33, or
FIGURE 34)
28.50114.004PART 4 (FIGURE
35, FIGURE 36, or
FIGURE 37)
520.752658.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None
I. Electrical Load Data
None.
J. References
1. Existing Data:
a. Boeing Service Bulletin 747-55A2050, 747-57-2071, 747-57-2110, 747-57A2309, 747-57A2314
b. Boeing Service Letter 747-SL-51-048
c. Boeing Service Related Problem (SRP) 747-SRP-51-0014
d. Federal Aviation Administration (FAA) Airworthiness Directive 2004-03-09, 2004-07-22 R1,
2006-10-16
e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-05, 20-50-19
f. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Figure 1, 11, or 16, Part 6,
51-00-00, Figure 4 or 23
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g. 747 Supplemental Structural Inspection Document (SSID) Vol 1E-3, Vol 1E-9, Vol 1F-26, Vol
1W-18, Vol 1W-19
h. 747-100/200/300 Aircraft Maintenance Manual (AMM) 12-09-00, 20-11-05, 24-22-00, 25-21-01,
25-21-04, 25-22-04, 25-28-01, 25-28-02, 28-11-02, 28-26-00, 29-11-00, 51-31-00, 53-51-01,
57-31-00
i. 747-100/200/300 Structural Repair Manual (SRM) 51-30
j. 747-400 Aircraft Maintenance Manual (AMM) 06-09-00, 20-11-05, 24-22-00, 25-21-01,
25-21-04, 25-28-01, 25-28-02, 28-11-02, 28-11-19, 28-26-00, 29-11-00, 51-31-00, 53-51-01,
57-31-00
k. 747-400 Structural Repair Manual (SRM) 51-40
l. 747-400F Structural Repair Manual (SRM) 51-40
m. 747-400LCF Structural Repair Manual (SRM) 51-40
n. 747-400SF Structural Repair Manual (SRM) 51-40
o. 747-SP Structural Repair Manual (SRM) 51-30
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TABLE 1: WING SOB JOINT
TitleDrawing Number
WING STUB ASSY - FRONT AND REAR SPAR BBL 127.5065B07822
WING STUB ASSY - FRONT AND REAR SPAR BBL 127.5065B14492
WING STUB ASSY - FRONT AND REAR SPAR BBL 127.5065B15270
WING STUB ASSY - FRONT AND REAR SPAR BBL 127.5065B15272
WING STUB INSTL - FRONT AND REAR SPAR BBL 127.50112U5010
SPLICE INSTL - BODY BL 127.50, UPPER SURFACE, SECTION
12
65B01113
SPLICE INSTL - BODY BL 127.50, UPPER SURFACE, SECTION
12
65B14589
SPLICE INSTL - BODY BL 127.50, UPPER SURFACE, SECTION
12
112U3010
SPLICE INSTL - BODY BL 127.50, LOWER SURFACE, SECTION
12
65B01115
SPLICE INSTL - BODY BL 127.50, LOWER SURFACE, SECTION
12
65B14591
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TABLE 1: WING SOB JOINT
TitleDrawing Number
SPLICE INSTL - BODY BL 127.50, LOWER SURFACE, SECTION
12
65B16651
SPLICE INSTL - BODY BL 127.50, LOWER SURFACE, SECTION
12
65B17108
SPLICE INSTL - BODY BL 127.50, LOWER SURFACE, SECTION
12
112U4010
TABLE 2: HORIZONTAL STABILIZER SOB JOINT
TitleDrawing Number
RIB INSTL - HING, HORIZONTAL STABILIZER65B03560
REAR SPAR INSTL - CENTER SECTION, HORIZONTAL
STABILIZER
65B03595
UPPER SKIN INSTL - CENTER SECTION, HORIZONTAL
STABILIZER
65B03599
SPAR INSTL, REAR - HORIZONTAL STABILIER65B03641
TABLE 3: FUSELAGE SKIN AND CIRCUMFERENTIAL SPLICES (SECTION 42)
TitleDrawing Number
SKIN PANEL INSTL - STA 520 TO STA 741.10, S-0 TO S-665B25601
SKIN PANEL INSTL - STRETCHED UPPER DECK - STA 741.10
TO STA 1000, S-0 TO S-6
65B25604
SKIN PANEL INSTL - STA 520 TO STA 741.10, S-0 TO S-665B04100
SKIN PANEL INSTL - STA 741.10 TO STA 1000, S-0 TO S-665B04111
SKIN PANEL INSTL - STA 520 TO STA 1000, S-0 TO S-665B18620
TABLE 4: FUSELAGE SKIN AND CIRCUMFERENTIAL SPLICES (SECTION 44)
TitleDrawing Number
SKIN PANEL INSTL - STA 1000 TO STA 1241, S-4L TO S-4R65B04119
SKIN PANEL INSTL - STA 1000 TO STA 1241, S-4 TO S-1265B04120
SKIN PANEL INSTL - STA 1000 TO STA 1241, S-12 TO S-1965B04121
SKIN PANEL INSTL - STA 1241 TO STA 1480, S-4L TO S-4R65B04123
SKIN PANEL INSTL - STA 1241 TO STA 1480, S-4 TO S-1265B04124
SKIN PANEL INSTL - STA 1350.10 TO STA 1480, S-12 TO S-1965B04125
SKIN PANEL INSTL - STA 1000 TO STA 1200, S-0 TO S-665B18630
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TABLE 4: FUSELAGE SKIN AND CIRCUMFERENTIAL SPLICES (SECTION 44)
TitleDrawing Number
SKIN PANEL INSTL - STA 1000 TO STA 1200, S-6 TO S-1265B18631
SKIN PANEL INSTL - STA 1200 TO STA 1241, S-12L TO S-12R65B18632
SKIN PANEL INSTL - STA 1241 TO STA 1350, S-12 TO S-1965B18633
SKIN PANEL INSTL - STA 1000 TO STA 1220, S-0 TO S-665B25726
SKIN PANEL INSTL - STA 1000 TO STA 1288, S-6 TO S-1265B25727
SKIN PANEL INSTL - STA 1220 TO STA 1283, S-6L TO S-6R65B25729
SKIN PANEL INSTL - STA 1283 TO STA 1480, S-4L TO S-4R65B25730
TABLE 5: FUSELAGE SKIN AND CIRCUMFERENTIAL SPLICES (SECTION 46)
TitleDrawing Number
SKIN PANEL INSTL - STA 1480 TO STA 1741.10 S-4L TO S-4R65B04127
SKIN PANEL INSTL - STA 1480 TO STA 1741.10, S-4 TO S-1265B04128
SKIN PANEL INSTL - STA 1480 TO STA 1741.10, S-12 TO S-1965B04129
SKIN PANEL INSTL - STA 1741.10 TO STA 1961.10, S-4L TO
S-4R
65B04135
SKIN PANEL INSTL - STA 1741.10 TO STA 1961.10, S-4 TO S-1265B04136
SKIN PANEL INSTL - STA 1741.10 TO STA 1961.10, S-12 TO
S-19
65B04137
SKIN PANEL INSTL - STA 1741.10 TO STA 1961.10, S-4L TO
S-12L, SIDE CARGO DOOR
65B17652
SKIN PANEL INSTL - STA 1480 TO STA 1741.10, S-4L TO S-4R65B18636
SKIN PANEL INSTL - STA 1480 TO STA 1741.10, S-4 TO S-1265B18637
SKIN PANEL INSTL - STA 1480 TO STA 1741.10, S-12 TO S-1965B18638
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
None.
L. Interchangeability and Intermixability of Parts
None.
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### Page 35

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes 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:
Additional oversized fasteners may be necessary during the inspection for temporary installation
to prevent the mis-alignment of the parts. Refer to Paragraph 1.J.3., Installation Drawings Used
in the Preparation of this Service Bulletin, for the original fastener type, diameter, and grip length.
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.
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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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. The work instructions are divided into work packages.Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower.Y ou can do each work
package independently.
5. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Hole dimensions for standard solid rivets are given in 747 SRM, Chapter 51
– Torque limits to tighten nuts and bolts are given in 747 SRM, Chapter 51
6. For approved fastener and process material substitutions, refer to 747 SRM, Chapter
51. Alternate fasteners are given in 747 SRM Chapter 51 and Boeing Drawing
012W6100.
7. If the length of any fastener necessary to accomplish 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.
8. 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.
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– For the Detailed Inspection area that is also for the Open-Hole High Frequency
Eddy Current (HFEC) Inspection, sealants and corrosion inhibiting compounds
should be removed.
– Refer to 747-100/200/300 AMM 51-31-00 or 747-400 AMM 51-31-00 as an
accepted procedure for general sealant application of the airplane structure.
Refer to SOPM 20-30-03, SOPM 20-41-05, and SOPM 20-50-19 as an
acceptable procedures for additional information on general cleaning; and
removal and application of sealants and corrosion inhibiting compounds.
9. 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.
10. The Detailed, Surface High Frequency Eddy Current (HFEC), and Open-Hole HFEC
Inspections are necessary at the following three areas of the airplane: wing
side-of-body (SOB) joint, horizontal stabilizer SOB joint, and fuselage. A typical
configuration is shown in the figures to show a description of each inspection for the
three areas. In each area the following locations are inspected:
– Wing SOB Joint Area
– Upper surface location: Wing SOB aft joint.
– Upper surface location: Wing SOB middle joint.
– Upper surface location: Wing SOB forward joint.
– Lower surface location: Wing SOB aft joint.
– Lower surface location: Wing SOB middle joint.
– Horizontal Stabilizer SOB Joint Area
– Location: Upper hinge fitting.
– Location: Lower hinge fitting.
– Location: Rear spar upper chord and terminal fitting.
– Location: Rear spar lower chord and terminal fitting.
– Location: Rear spar upper chord and outboard skin.
– Location: Rear spar upper chord and center section skin.
– Fuselage Area: Skin and circumferential splices in the crown location from body
station (STA) 741 to STA 1961.
11. Fastener removal for Open-Hole HFEC Inspection is necessary in three areas of the
airplane: wing SOB joint, horizontal stabilizer SOB joint, and fuselage. These areas
and both (left and right) sides of each area can be inspected concurrently with the
following limitations:
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– For the wing SOB and horizontal stabilizer SOB joints, the Open-Hole HFEC
Inspection is acceptable in one location at a time on both left and right side of
the airplane.
– For the fuselage, Open-Hole HFEC Inspection in multiple body stations that are
not adjacent body station is acceptable.Within each body station, it is acceptable
to remove fasteners in two stringer bays at a time.
12. Alternate the removal and inspection of the fasteners for each inspection location
as given in Paragraph 3.B., Work Instructions. Only the specified fasteners may be
removed prior to removing any other fasteners for that inspection location. Removal
of all of the fasteners at one time may result in the mis-alignment of the parts.
– Keep and mark the heads of the removed fasteners for an easy identification.
– Additional oversized fasteners may be necessary during the inspection for
temporary installation to prevent the mis-alignment of the parts.
13. For fastener installation requirements, refer to the drawings listed in Paragraph 1.J.3.,
Installation Drawings Used in the Preparation of this Service Bulletin. For the hole
locations where the diameter is within the tolerance as given in Paragraph 1.J.3.,
Installation Drawings Used in the Preparation of this Service Bulletin, a maximum of
1/64-inch over size is acceptable to clean up a hole for the Open-Hole HFEC
Inspection as given in 747 NDT Part 6, 51-00-00, Figure 1, 11, or 16. Additional
over-sizing of the hole will be evaluated on a case-by-case basis when the inspection
results are submitted to Boeing.
B. WORK INSTRUCTIONS
PART 1 - ACCESS
1. Access for Wing SOB Joint Upper and Lower Surfaces.
a. De-fuel the airplane (all tanks). Refer to 747-100/200/300 AMM 28-26-00 or 747-400 AMM
28-26-00 as an accepted procedure.
b. Remove the wing fuel tank access panels and wing-to-body fairing panels.
(1) Remove the wing fuel tank access panels 544AB and 644AB. Refer to 747-100/200/300
AMM 28-11-02 or 747-400 AMM 28-11-02 as an accepted procedure.
(2) Remove the wing-to-body fairing panels in maintenance zone 191, 192, 291, and 292.
Refer to 747-100/200/300 AMM 53-51-01 or 747-400 AMM 53-51-01 as an accepted
procedure.
(3) For access information, refer to 747-100/200/300 AMM 12-09-00 or 747-400 AMM
06-09-00 as an accepted procedure.
c. Get access inside the fuel tanks as necessary during accomplishment of this service bulletin.
Refer to 747-100/200/300 AMM 57-31-00 or 747-400 AMM 57-31-00 as an accepted procedure
for the fuel tank access opening information.
d. Remove and keep the pressure barrier installed on the outboard flange of the wing rear spar
to center section upper external splice fitting.
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NOTE: The pressure barrier is bonded to the fitting and structure with a silicone adhesive.
Use care not to damage the pressure barrier when removing.
2. Access for Horizontal Stabilizer SOB Joint Upper and Lower Surfaces.
a. Remove hydraulic power. Refer to 747-100/200/300 AMM 29-11-00 or 747-400 AMM 29-11-00
as an accepted procedure.
b. Remove electrical power. Refer to 747-100/200/300 AMM 24-22-00 or 747-400 AMM 24-22-00
as an accepted procedure.
c. De-fuel the horizontal stabilizer fuel tanks as applicable. Refer to 747-400 AMM 28-26-00 as
an accepted procedure.
d. Open the following access doors:
(1) Group 1-3:
Refer to 747-100/200/300 AMM 12-09-00 as an accepted procedure for the access
information.
(a) Open the access doors 312AR and 315AL.
(b) Open the access doors 333JZ and 343JZ on the horizontal stabilizer center section.
(c) Open the access door 334GBAL and 344GBAR on the horizontal stabilizer lower
surface just outboard of the fuselage.
(2) Group 4-6:
Refer to 747-400 AMM 06-09-00 as an accepted procedure for the access information.
(a) Open the access doors 312AR and 315AL.
(b) Open the access door 339AZ and 349AZ.
(c) Open the access door 338AZ, if installed, on horizontal stabilizer center section.
Refer to 747-400 AMM 28-11-19 as an accepted procedure.
(d) Open the access doors 334GAL and 334GAR on the horizontal stabilizer lower
surface just outboard of the fuselage.
e. Disconnect and remove the hydraulic tubes in the inspection area as necessary. Refer to
747-100/200/300 AMM 20-11-05 or 747-400 AMM 20-11-05 as an accepted procedure.
f. For airplanes with horizontal stabilizer fuel tank, remove fasteners attaching fiberglass shield
to gain access to the inspection area.
3. Group 1-5:
Access for Fuselage Skin and Circumferential Splices
NOTE: In the areas to be inspected as given in PART 4 - INSPECTION OF FUSELAGE SKIN
AND CIRCUMFERENTIAL SPLICES, remove the following components to gain access
for the inspection.
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a. Remove the sidewall panels. Refer to 747-100/200/300 AMM 25-21-01 or 747-400 AMM
25-21-01 as an accepted procedure.
b. Remove the ceiling panels. Refer to 747-100/200/300 AMM 25-22-04 or 747-100/200/300
AMM 25-28-01 or 747-400 AMM 25-28-01 or as an accepted procedure.
c. Remove the center overhead stowage bins. Refer to 747-100/200/300 AMM 25-28-02 or
747-400 AMM 25-28-02 as an accepted procedure.
d. Remove the insulation. Refer to 747-100/200/300 AMM 25-21-04 or 747-400 AMM 25-21-04
as an accepted procedure.
PART 2 - INSPECTION OF WING SOB JOINT
1. Get access to the inspection area as specified in PART 1 - ACCESS.
2. Do the following inspections of the wing SOB joint upper surface as follows:
a. Do a Detailed Inspection of the wing SOB joint upper surface for any crack as given in FIGURE
1 and FIGURE 2, left and right side respectively.
b. Do an Open-Hole HFEC Inspection of the wing SOB joint (aft) upper surface for any crack as
given in FIGURE 3 and FIGURE 4, left and right side respectively.
c. Do an Open-Hole HFEC Inspection of the wing SOB joint (middle) upper surface for any crack
as given in FIGURE 5 and FIGURE 6, left and right side respectively.
d. Do an Open-Hole HFEC Inspection of the wing SOB joint (forward) upper surface for any
crack as given in FIGURE 7 and FIGURE 8, left and right side respectively.
3. Do the following inspections of the wing SOB joint lower surface as follows:
a. Do a Detailed Inspection of the wing SOB joint lower surface for any crack as given in FIGURE
9 and FIGURE 10, left and right side respectively.
b. Do an Open-Hole HFEC Inspection of the wing SOB joint (aft) lower surface for any crack as
given in FIGURE 11 and FIGURE 12, left and right side respectively.
c. Do an Open-Hole HFEC Inspection of the wing SOB joint (middle) lower surface for any crack
as given in FIGURE 13 and FIGURE 14, left and right side respectively.
PART 3 - INSPECTION OF HORIZONTAL STABILIZER SOB JOINT
1. Get access to the inspection area as specified in PART 1 - ACCESS.
2. Do the following inspections of the horizontal stabilizer SOB joint as follows:
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a. Do a Detailed Inspection of the horizontal stabilizer SOB joint for any crack as given in FIGURE
15 and FIGURE 16, left and right side respectively.
b. Do an Open-Hole HFEC Inspection of the horizontal stabilizer SOB joint upper hinge fitting
for any crack as given in FIGURE 17 and FIGURE 18, left and right side respectively.
c. Do an Open-Hole HFEC Inspection of the horizontal stabilizer SOB joint lower hinge fitting
for any crack as given in FIGURE 19 and FIGURE 20, left and right side respectively.
d. Do an Open-Hole HFEC Inspection of the horizontal stabilizer SOB joint rear spar upper chord
and terminal fitting for any crack as given in FIGURE 21 and FIGURE 22, left and right side
respectively.
e. Do an Open-Hole HFEC Inspection of the horizontal stabilizer SOB joint rear spar lower chord
and terminal fitting for any crack as given in FIGURE 23 and FIGURE 24, left and right side
respectively.
f. Do an Open-Hole HFEC Inspection of the horizontal stabilizer SOB joint rear spar upper chord
and outboard skin for any crack as given in FIGURE 25 and FIGURE 26, left and right side
respectively.
g. Do an Open-Hole HFEC Inspection of the horizontal stabilizer SOB joint rear spar upper chord
and center section skin for any crack as given in FIGURE 27 and FIGURE 28, left and right
side respectively.
Group 1-5:
PART 4 - INSPECTION OF FUSELAGE SKIN AND CIRCUMFERENTIAL SPLICES
1. Get access to the inspection area as specified in PART 1 - ACCESS.
2. Detailed Inspection of the Fuselage Skin, Stringers, and Stringer Splice Fittings
a. Group 1, 5:
Do a Detailed Inspection of the fuselage skin, stringers, and stringer splice fittings for any
crack as given in FIGURE 29 for the following locations:
TABLE 1: INSPECTION LOCATION FOR NON-SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
S-6L to S-6R741
S-6L to S-6R1000(a)
S-16L to S-16R1241
S-12L to S-16L and S-12R to S-16R1350
S-16L to S-16R1480
S-12L to S-12R1741
S-8L to S-8R1961
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TABLE 1: INSPECTION LOCATION FOR NON-SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
(a) An external doubler is installed on STA 1000, approximately from S-4L to S-4R. Do a Detailed Inspection
of the doubler in this area.
b. Group 2:
Do a Detailed Inspection of the fuselage skin, stringers, and stringer splice fittings for any
crack as given in FIGURE 30 for the following locations:
TABLE 2: INSPECTION LOCATION FOR SP AIRPLANES
Stringer (S) LocationBody Station (STA)
S-6L to S-6R800
S-6L to S-6R1141
S-12L to S-12R1200(a)
S-16L to S-16R1241
S-12L to S-16L and S-12R to S-16R1350
S-16L to S-16R1640
S-12L to S-12R1741
S-8L to S-8R1961
(a) An external doubler is installed on STA 1200, approximately from S-4L to S-4R. Do a Detailed Inspection
of the doubler in this area.
c. Group 3-4:
Do a Detailed Inspection of the fuselage skin, stringers, and stringer splice fittings for any
crack as given in FIGURE 31 for the following locations:
TABLE 3: INSPECTION LOCATION FOR SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
S-6L to S-6R741
S-6L to S-6R1000
S-6L to S-6R1220
S-12L to S-12R1283(a)
S-12L to S-16L and S-12R to S-16R1350
S-16L to S-16R1480
S-12L to S-12R1741
S-8L to S-8R1961
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TABLE 3: INSPECTION LOCATION FOR SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
(a) An external doubler is installed on STA 1283, approximately from S-4L to S-4R. Do a Detailed Inspection
of the doubler in this area.
3. Open-Hole HFEC Inspection of the Fuselage Circumferential Splices
a. Group 1, 5:
Do an Open-Hole HFEC Inspection of the fuselage circumferential splices for any crack as
given in FIGURE 32 for the following locations:
TABLE 4: OPEN-HOLE HFEC INSPECTION LOCATION FOR NON-SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-1R741
S-1L to S-1R1000
S-13L to S-15L and S-13R to S-15R1241
S-13L to S-15L and S-13R to S-15R1350
S-8L to S-10L and S-8R to S-10R1480
S-1L to S-1R1741
S-1L to S-1R1961
b. Group 2:
Do an Open-Hole HFEC Inspection of the fuselage circumferential splices for any crack as
given in FIGURE 33 for the following locations:
TABLE 5: OPEN-HOLE HFEC INSPECTION LOCATION FOR SP AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-1R800
S-1L to S-1R1141
S-1L to S-1R1200
S-13L to S-15L and S-13R to S-15R1241
S-13L to S-15L and S-13R to S-15R1350
S-8L to S-10L and S-8R to S-10R1640
S-1L to S-1R1741
S-1L to S-1R1961
c. Group 3-4:
Do an Open-Hole HFEC Inspection of the fuselage circumferential splices for any crack as
given in FIGURE 34 for the following locations:
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TABLE 6: OPEN-HOLE HFEC INSPECTION LOCATION FOR SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-1R741
S-1L to S-1R1000
S-1L to S-1R1220
S-1L to S-1R1283
S-13L to S-15L and S-13R to S-15R1350
S-8L to S-10L and S-8R to S-10R1480
S-1L to S-1R1741
S-1L to S-1R1961
4. Surface HFEC Inspection of the Fuselage Skin
a. Group 1, 5:
Do a Surface HFEC Inspection of the fuselage skin for any crack as given in FIGURE 35 for
the following locations:
TABLE 7: SURFACE HFEC INSPECTION LOCATION FOR NON-SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-6L and S-1R to S-6R741
S-1L to S-6L and S-1R to S-6R1000(a)
S-15L to S-16L and S-13L to S-13R and S-15R to
S-16R
1241
S-12L to S-13L and S-15L to S-16L and S-12R to
S-13R and S-15R to S-16R
1350
S-10L to S-16L and S-8L to S-8R and S-10R to S-16R1480
S-1L to S-12L and S-1R to S-12R1741
S-1L to S-8L and S-1R to S-8R1961
(a) An external doubler is installed on STA 1000, approximately from S-4L to S-4R. Surface HFEC Inspection
of the skin is not necessary in this location.
b. Group 2:
Do a Surface HFEC Inspection of the fuselage skin for any crack as given in FIGURE 36 for
the following locations:
TABLE 8: SURFACE HFEC INSPECTION LOCATION FOR SP AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-6L and S-1R to S-6R800
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TABLE 8: SURFACE HFEC INSPECTION LOCATION FOR SP AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-6L and S-1R to S-6R1141
S-1L to S-12L and S-1R to S-12R1200(a)
S-15L to S-16L and S-13L to S-13R and S-15R to
S-16R
1241
S-12L to S-13L and S-15L to S-16L and S-12R to
S-13R and S-15R to S-16R
1350
S-10L to S-16L and S-8L to S-8R and S-10R to S-16R1640
S-1L to S-12L and S-1R to S-12R1741
S-1L to S-8L and S-1R to S-8R1961
(a) An external doubler is installed on STA 1200, approximately from S-4L to S-4R. Surface HFEC Inspection
of the skin is not necessary in this location.
c. Group 3-4:
Do a Surface HFEC Inspection of the fuselage skin for any crack as given in FIGURE 37 for
the following locations:
TABLE 9: SURFACE HFEC INSPECTION LOCATION FOR SUD AIRPLANES
Stringer (S) LocationBody Station (STA)
S-1L to S-6L and S-1R to S-6R741
S-1L to S-6L and S-1R to S-6R1000
S-1L to S-6L and S-1R to S-6R1220
S-1L to S-12L and S-1R to S-12R1283(a)
S-12L to S-13L and S-15L to S-16L and S-12R to
S-13R and S-15R to S-16R
1350
S-10L to S-16L and S-8L to S-8R and S-10R to S-16R1480
S-1L to S-12L and S-1R to S-12R1741
S-1L to S-8L and S-1R to S-8R1961
(a) An external doubler is installed on STA 1283, approximately from S-4L to S-4R. Surface HFEC Inspection
of the skin is not necessary in this location.
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PART 5 - REPAIR AND INSPECTION RESULTS REPORTING GUIDELINES
1. Report any crack finding to Boeing. Repair any crack found as given by Boeing at the time given
in Paragraph 1.E., Compliance.
2. For the inspection area with crack(s), refer to Boeing Service Letter 747-SL-51-048 as a
recommended guidelines for reporting the inspection results. A complete and accurate inspection
report will help expedite the response time to the operators.
3. If no crack is found, proceed to PART 6 - RESTORE.
PART 6 - RESTORE
1. Install kept and/or oversized fasteners as given in 747-100/200/300 SRM 51-30, 747-400 SRM
51-40, 747-400F SRM 51-40, 747-400LCF SRM 51-40, 747-400SF SRM 51-40, or 747-SP SRM
51-30 as applicable where the fasteners were removed for Open-Hole HFEC Inspection. Refer to
SOPM 20-50-19, Method 2 as an accepted procedure for general sealing of fasteners during
installation.
2. Apply sealants and corrosion inhibiting compounds to surfaces where previously removed for
inspection. Refer to 747-100/200/300 AMM 51-31-00 or 747-400 AMM 51-31-00 as an accepted
procedure for general sealant application.
3. Reinstall all equipment and access panels/doors that were removed for access; and restore
hydraulic and electrical power.
4. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
BBL
127.50
FRONT
SPAR
REAR
SPAR
FWD
1568977
FIGURE 1: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - LEFT SIDE
(SHEET 1 OF 3)
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### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do an External
Detailed Inspection
of the wing skin
along BBL 127.5 for
any crack. Inspect
the area within 10
inches from BBL
127.5 between rear
spar and S-28.
--WING SKINInspect1
FIGURE 1: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - LEFT SIDE
(SHEET 2 OF 3)
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MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do an Internal
Detailed Inspection
of the flanges of the
upper rib chord for
any crack. Inspect
between rear spar
and S-28.
--WING UPPER RIB
CHORD
Inspect2
Do an Internal
Detailed Inspection
of the entire splice
fitting from S-1 to
S-28 for any crack.
--WING SPLICE
FITTING
Inspect3
Do an Internal
Detailed Inspection
of the stringer at the
splice fitting
attachment from S-1
to S-28 for any
crack.
--WING STRINGERInspect4
FIGURE 1: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - LEFT SIDE
(SHEET 3 OF 3)
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ALERTALERT

### Page 51 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
000000
BBL
127.50
FRONT
SPAR
REAR
SPAR
FWD
1569661
FIGURE 2: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - RIGHT SIDE
(SHEET 1 OF 3)
October 30, 2008
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### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do an External
Detailed Inspection
of the wing skin
along BBL 127.5 for
any crack. Inspect
the area within 10
inches from BBL
127.5 between rear
spar and S-28.
--WING SKINInspect1
FIGURE 2: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - RIGHT SIDE
(SHEET 2 OF 3)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 30, 2008
747-51A2060
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ALERTALERT

### Page 53

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do an Internal
Detailed Inspection
of the flanges of the
upper rib chord for
any crack. Inspect
between rear spar
and S-28.
--WING UPPER RIB
CHORD
Inspect2
Do an Internal
Detailed Inspection
of the entire splice
fitting from S-1 to
S-28 for any crack.
--WING SPLICE
FITTING
Inspect3
Do an Internal
Detailed Inspection
of the stringer at the
splice fitting
attachment from S-1
to S-28 for any
crack.
--WING STRINGERInspect4
FIGURE 2: DETAILED INSPECTION OF WING SOB JOINT UPPER SURFACE - RIGHT SIDE
(SHEET 3 OF 3)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 30, 2008
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53 of 196
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ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
000000
00000 0  STA
1000
STA
1140
STA
1241
STA
1350
EXTERNAL
LONGERON
FITTING
WING -
1241  STA  STA 1241
BODY SPLICE
EXTERNAL
LONGERON
FITTING
00000
0•00
SPLICE  000000
FITTING
PRESSURE  WING REAR SPAR
FWD
1570201
FIGURE 3: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - LEFT SIDE
(SHEET 1 OF 4)
October 30, 2008
747-51A2060
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### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
EXTERNAL
LONGERON
FITTING
• BODY SKIN
S-2
OUTBOARD
HORIZONTAL
FLANGE
S-1
B
WING SKIN
INBD
10 LOCATIONS (1)2
TYPICAL CONFIGURATION
A-A
BODY  SHIM
SKIN •
EXTERNAL
LONGERON  • INTERNAL
FITTING  LONGERON
FITTING
EXTERNAL  SPLICE  FITTING  MOISTURE  DRAIN TUBE  FILLER
FILLER
WING SKIN
WING REAR  SECTION  CENTER
SPAR CHORD  SKIN
INBD  (TYPICAL)  BUSHING  REPAIR  FITTING  SPLICE  INTERNAL  CHORD  SPAR  REAR
TYPICAL CONFIGURATION  1570212
B-B
FIGURE 3: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - LEFT SIDE
(SHEET 2 OF 4)
October 30, 2008
747-51A2060
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### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
SHIM
BODY SKIN  INTERNAL
LONGERON
EXTERNAL  FITTING
LONGERON
FITTING
FILLER
EXTERNAL SPLICE FITTING
WING SKIN
• FILLER
UPPER RIB CHORD •
CENTER
SECTION
SKIN
INTERNAL
STRINGER NO. 1  SPLICE
FITTING
SPLICE FITTING
INBD
TYPICAL CONFIGURATION
C-C
WING SKIN
STRINGER NO. 1 AND 2-
SPLICE FITTING
INBD
UPPER
RIB
CHORD
TYPICAL CONFIGURATION  1570263
D-D
FIGURE 3: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - LEFT SIDE
(SHEET 3 OF 4)
October 30, 2008
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  56 of 196

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--BOLTRemove / Keep1
--WASHERRemove / Keep
--NUTRemove / Keep
Do an Open-Hole
HFEC Inspection of
all the components
in the stack up for
any crack as given
in 747 NDT Part 6,
51-00-00, Figure 1,
11, or 16.(b)
--HOLESInspect2
(a) It is acceptable to remove one group of fasteners at one time as follows: Group A= Bolts 1-3, Group B=
Bolts 4-5, Group C= Bolts 6-8, and Group D= Bolts 9-10.
(b) Repair bushings may be installed as given in Service Bulletin 747-57-2110, Service Bulletin 747-57A2314,
or by prior repairs at the hole locations. Contact Boeing for inspection instructions at hole locations with
a repair bushing.
FIGURE 3: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - LEFT SIDE
(SHEET 4 OF 4)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 30, 2008
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ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
000000
STA  00000
1000
STA
1140
STA
1241  EWD
STA
1350
EXTERNAL
LONGERON
FITTING
WING
BODY SPLICE  STA 1241  STA  1241
EXTERNAL
ONGFRON
FITTING
90000001  •  000000000  SPLICE
FITTING
WING REAR SPAR  PRESSURE  BARRIER
FWD
1570270
FIGURE 4: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - RIGHT SIDE
(SHEET 1 OF 4)
October 30, 2008
747-51A2060
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### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
EXTERNAL
LONGERON
FITTING
10
BODY SKIN  ==
B
OUTBOARD
- HORIZONTAL
FLANGE
S-1
B
WING SKIN
INBD
2)  10 LOCATIONS
TYPICAL CONFIGURATION
A-A
SHIM  BODY
SKIN
EXTERNAL
INTERNAL  LONGERON
LONGERON  FITTING
FITTING
MOISTURE  EXTERNAL
FILLER  DRAIN TUBE  FITTING  SPLICE
FILLER
WING SKIN
SKIN  SECTION  CENTER  WING REAR  SPAR CHORD
SPAR  REAR  CHORD  SPLICE  FITTING  INTERNAL  BUSHING  (TYPICAL)  REPAIR  INBD
TYPICAL CONFIGURATION  1570288
B-B
FIGURE 4: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - RIGHT SIDE
(SHEET 2 OF 4)
October 30, 2008
747-51A2060
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  59 of 196

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-51A2060
ALERT  ALERT
SHIM
BODY SKIN
INTERNAL
LONGERON  EXTERNAL
FITTING  LONGERON
FITTING
FILLER
/ EXTERNAL SPLICE FITTING
- WING SKIN
FILLER •
~ UPPER RIB CHORD
CENTER
SECTION
SKIN
INTERNAL
SPLICE
FITTING  STRINGER NO. 1
SPLICE FITTING
INBD
TYPICAL CONFIGURATION
C-C
- WING SKIN
- STRINGER NO. 1 AND 2
SPLICE FITTING
INBD
UPPER
RIB
CHORD
TYPICAL CONFIGURATION  1570296
D-D
FIGURE 4: OPEN-HOLE HFEC INSPECTION OF WING SOB JOINT (AFT) UPPER SURFACE - RIGHT SIDE
(SHEET 3 OF 4)
October 30, 2008
747-51A2060
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  60 of 196

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