# Boeing Alert Service Bulletin 747-53A2751: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0553; AD 2009-24-17 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 747-53A2751](https://openairdocs.org/service-documents/boeing/747-53a2751.md)
- Title as filed: Airworthiness Directive - Boeing Service Bulletin - 2009-NM-111
- Pages: 111
- PDF: https://openairdocs.org/files/sha256/79/cd/79cde51f0e63a481c626e44f768ea509884f147164b921ca59163d56ed1d7f11
- Page: https://openairdocs.org/service-documents/boeing/747-53a2751/file/79cde51f0e63

## Text

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### Page 1

Commercial        
Airplane
Group 
 747
Service Bulletin
ALERT
Number: 747-53A2751
Date: October 09, 2008
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Inspection of Non-Stretched Upper Deck Airplanes for
Installation of Fasteners at the Stringer to Stringer Clip Joint.
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Unpublished Work - All Rights Reserved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, 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.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
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3.0

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### Page 3

Table of Contents
Summary ..................................................... 5
1. PLANNING INFORMATION ......................................... 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 6
B. Concurrent Requirements ...................................... 1 6
C. Reason ................................................ 1 6
D. Description .............................................. 1 7
E. Compliance .............................................. 1 8
F . Approval ............................................... 1 9
G. Manpower .............................................. 1 9
H. Weight and Balance Changes .................................... 2 1
I. Electrical Load Data ......................................... 2 1
J. References .............................................. 2 1
1. Existing Data .......................................... 2 1
2. Data supplied with this Service Bulletin ............................ 2 1
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 1
K. Publications Affected ......................................... 2 2
L. Interchangeability and Intermixability of Parts ........................... 2 2
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts ............................................ 2 3
2. Parts and Materials Supplied by the Operator ........................ 2 3
3. Parts Modified and Reidentified ................................ 2 3
4. Parts Removed and Not Replaced .............................. 2 3
D. Parts Necessary to Change Spares ................................. 2 3
E. Special Tooling - Price and Availability ............................... 2 3
F . Special Tooling Necessary to do this Service Bulletin ....................... 2 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5
A. GENERAL INFORMATION ..................................... 2 5
B. WORK INSTRUCTIONS ....................................... 2 6
FIGURE 1: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS (LEFT
SIDE) .............................................. 3 2
FIGURE 2: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS
(RIGHT SIDE) ......................................... 3 5
FIGURE 3: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO FRAME SPLICE ON
TYPICAL FRAME (LEFT SIDE) ................................ 3 8
FIGURE 4: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO FRAME SPLICE ON
TYPICAL FRAME (RIGHT SIDE) ............................... 4 2
FIGURE 5: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (LEFT SIDE)
.................................................. 4 6
FIGURE 6: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (RIGHT SIDE)
.................................................. 5 1
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FIGURE 7: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE
(LEFT SIDE) [Group 4-6] .................................... 5 6
FIGURE 8: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE
(RIGHT SIDE) [Group 4-6] ................................... 6 1
FIGURE 9: INSPECTION OF FRAME AND SKIN STRUCTURE - MIDDLE OF SHORT FRAME SPLICE
(LEFT SIDE) [Group 1-3, 7] .................................. 6 6
FIGURE 10: INSPECTION OF FRAME AND SKIN STRUCTURE - MIDDLE OF SHORT FRAME SPLICE
(RIGHT SIDE) [Group 1-3, 7] ................................. 7 0
FIGURE 11: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO END OF LONG FRAME
SPLICE - INBOARD (LEFT SIDE) ............................... 7 4
FIGURE 12: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO END OF LONG FRAME
SPLICE - INBOARD (RIGHT SIDE) .............................. 7 8
FIGURE 13: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO END OF LONG STEPPED
FRAME SPLICE - INBOARD (LEFT SIDE) [Group 4-6] ................... 8 2
FIGURE 14: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO END OF LONG STEPPED
FRAME SPLICE - INBOARD (RIGHT SIDE) [Group 4-6] .................. 8 7
FIGURE 15: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO END OF LONG FRAME
SPLICE - OUTBOARD (LEFT SIDE) ............................. 9 2
FIGURE 16: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO END OF LONG FRAME
SPLICE - OUTBOARD (RIGHT SIDE) ............................ 9 6
FIGURE 17: INSPECTION OF FRAME AND SKIN STRUCTURE - TYPICAL FRAME (LEFT SIDE) . . 100
FIGURE 18: INSPECTION OF FRAME AND SKIN STRUCTURE - TYPICAL FRAME (RIGHT SIDE) . 103
FIGURE 19: INSTALLATION OF MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS
(LEFT SIDE) .......................................... 1 0 6
FIGURE 20: INSTALLATION OF MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS
(RIGHT SIDE) ......................................... 1 0 9
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Commercial        
Airplane
Group 
 747
Service Bulletin
ALERT
SummaryNumber: 747-53A2751Date: October 09, 2008
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Inspection of Non-Stretched Upper Deck Airplanes for
Installation of Fasteners at the Stringer to Stringer Clip Joint.
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 work given in this Service Bulletin will make sure that necessary fasteners are installed at
stringer to stringer clip joints. These fasteners are located on the left and right side of Stringer (S)-10, S-10A,
and S-11 at Body Station (STA) 760 through 940 frames. If the fasteners are not installed, fatigue cracking can
occur in the adjacent shear ties. The cracks in the shear ties can cause skin cracks and a rapid in-flight
decompression.
The stringers are structurally connected to the body frames by stringer clips. The skin is attached to the frame
and stringers and shear ties are installed to the skin and frame. Adjacent to S-10, S-10A, and S-11 at STA 760
through 940 frames, there are tension ties that connect the left and right sides of the body structure aft of the
upper deck floor.
During a routine maintenance of 747-200F airplanes, two operators reported findings of broken and cracked
shear ties on STA 820 frame between S-10AL and S-11L. Also cracks were found on the frame doubler and
frame web near S-11L. More inspection showed missing fasteners at the stringer to stringer clip joint on S-10L
at STA 820 frame. The cracks and missing fasteners were found on airplanes that had 16,087 and 16,421 total
flight cycles.
Boeing analysis shows that the cracks were caused by increased load on the shear ties because of the missing
fasteners in the stringer to stringer clip joint. Boeing investigation shows that a similar cracking could occur in
the frames adjacent to the tensions ties if the stringer clip fasteners are not installed.
Accomplishment of the inspection in this Service Bulletin will make sure that the necessary fasteners are installed
at the stringer to stringer clip joints at S-10, S-10A, and S-11 at STA 760 through 940 frames.
Boeing Service Related Problem (SRP) 747-SRP-53-0317 is related to this service bulletin.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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### Page 6

ACTION
Do a General Visual Inspection to make sure that the fasteners are installed at the stringer to stringer clip joints
on S-10, S-10A, and S-11 at STA 760 through 940 frames. If the fasteners are installed, then no more work is
necessary. If the fasteners are missing, then do Detailed and Surface High Frequency Eddy Current (HFEC)
Inspections of the adjacent frame and skin structure for a crack. If no crack is found, then install the missing
fasteners. If a crack is found, then do the repair(s) as given in the Structural Repair Manual (SRM) and install
the missing fasteners. After the SRM repair(s) do a repetitive Detailed Inspection of the repaired area(s) as
given in Paragraph 1.E., Compliance.
EFFECTIVITY
Refer to Service Bulletin Paragraph 1.A., Effectivity.
COMPLIANCE
Refer to Paragraph 1.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.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service
bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Paragraph 2.C.2., Parts and Materials Supplied by the Operator
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### Page 7 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
STA
940
STA
760
SLOPING SHEAR WEB
(2 LOCATIONS)
TENSION TIE
(TYPICAL)
_ FRAME (TYPICAL)
S-9R  S-9L
S-10L
S-10R
S-10AR  S-10AL
S-11R  S-11L
— STA
760
FWD
STA
940
HORIZONTAL SHEAR WEB  (2 LOCATIONS)  1495226
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BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
FRAME
(TYPICAL)
STRINGER
(TYPICAL)
DO A GENERAL VISUAL INSPECTION
FOR MISSING FASTENERS
(4 LOCATIONS) AT EACH STRINGER TO
STRINGER CLIP JOINTS ON LEFT AND
RIGHT SIDES OF S-10, S-10A AND S-11
AT STA 760 THROUGH 940.
STRINGER CLIP
(TYPICAL)
1495231
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### Page 9

Commercial        
Airplane
Group 
 747
Service Bulletin
ALERT
Number: 747-53A2751
Date: October 09, 2008
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Inspection of Non-Stretched Upper Deck Airplanes for
Installation of Fasteners at the Stringer to Stringer Clip Joint.
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.
DESCRIPTIONCONFIGURATIONGROUP
747-100/-200B airplanes with a short splice frame at STA 760 and
STA 780. This excludes Boeing-Modified Special Freighter and
Boeing-Modified CRAF airplanes.
-1
Boeing-Modified Special Freighter airplanes with a short splice frame
at STA 760 and STA 780.
-2
Boeing-Modified CRAF airplanes with a short splice frame at STA
760 and STA 780.
-3
In passenger configuration1
In freighter configuration2
747-100/-100B/-200B/-SR airplanes with a long splice frame at STA
760 and STA 780. This excludes Boeing-Modified Special Freighter
and Boeing-Modified Special CRAF airplanes.
-4
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DESCRIPTIONCONFIGURATIONGROUP
Boeing-Modified Special Freighter airplanes with a long splice frame
at STA 760 and STA 780.
-5
747-200C (Convertible) and Boeing-Modified CRAF airplanes with
a long splice frame at STA 760 and STA 780.
-6
In passenger configuration1
In freighter configuration2
747-200F airplanes with a long splice frame at STA 760 and short
splice frame at STA 780.
-7
Airplane Models:
747-100, 747-100B, 747-200B, 747-200C, 747-200F , 747SR
GroupVariable Number
1RA001
3RA002
1RA003 - RA005
3RA006
1RA007 - RA010
3RA011
1RA012 - RA014
3RA015
1RA016 - RA025
2RA026
1RA027
3RA028
2RA029
3RA030
1RA031 - RA032
2RA033
1RA034
2RA101 - RA103
1RA104 - RA110
2RA111 - RA112
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GroupVariable Number
1RA113 - RA115
2RA161 - RA162
5RA163
4RA164
1RA201 - RA203
1RA216
4RA217
1RA245
4RA246
1RA251 - RA255
4RA256 - RA266
1RA301 - RA306
4RA307 - RA318
1RA351 - RA360
1RA369 - RA371
4RA372 - RA373
6RA401 - RA405
4RA406 - RA418
1RA501 - RA502
1RA521 - RA523
5RA524
4RA525 - RA528
1RA532 - RA534
4RA535 - RA548
1RA551 - RA552
1RA559 - RA560
4RA561
1RA581 - RA582
4RA585
1RA601 - RA602
3RA631
2RA632
3RA633
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GroupVariable Number
5RA634 - RA635
1RA651 - RA652
1RA671 - RA674
4RA675 - RA677
1RA701
4RA702
1RA721 - RA722
4RA723 - RA731
1RA741 - RA743
4RA744 - RA745
4RA749 - RA750
1RA761 - RA762
1RA781
4RA782 - RA783
6RA784
5RA901 - RA902
4RA903 - RA909
5RA910 - RA916
4RB001 - RB016
2RB041
1RB042
2RB043
1RB044
4RB071 - RB075
1RB101 - RB102
4RB411 - RB413
4RB421
4RB601 - RB603
5RB604 - RB605
4RB606
5RB607
4RB681 - RB695
5RB696
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GroupVariable Number
4RB697
4RB711
4RB721 - RB723
4RB741 - RB748
4RD001 - RD004
4RD021 - RD022
5RD041
6RD042
5RD043 - RD044
4RD045 - RD054
5RD055
4RD056 - RD059
4RD071 - RD072
4RD081
5RD082 - RD083
4RD091 - RD092
4RD101 - RD104
4RD121 - RD127
4RD131 - RD141
5RD142
4RD143
5RD144
4RD166 - RD167
4RD171 - RD172
4RD181 - RD183
4RD201 - RD204
4RD221 - RD224
5RD225
4RD226
5RD227
4RD231 - RD232
5RD233 - RD235
4RD241 - RD243
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GroupVariable Number
4RD251 - RD262
4RD271 - RD272
4RD291 - RD292
5RD301 - RD302
4RD311
4RD351 - RD357
5RD358
5RD361 - RD366
5RD411 - RD412
4RD413 - RD414
4RD421 - RD426
4RD431 - RD435
5RD441 - RD442
4RD451 - RD456
5RD461
4RD471 - RD475
4RD513 - RD519
4RD531 - RD533
5RD551
4RD561
4RD571
5RD581 - RD583
4RD591 - RD593
4RD621
5RD622 - RD623
5RD641 - RD643
4RD644 - RD645
5RD646
4RD647 - RD649
4RD651 - RD659
4RD661
4RD671
4RD681 - RD682
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GroupVariable Number
5RD691
4RD692
4RD701 - RD702
4RD741 - RD742
4RD751
5RD752
4RD753 - RD755
4RD761
4RD771 - RD775
4RD781 - RD783
4RD791 - RD792
4RE001
6RJ131 - RJ133
6RJ151 - RJ152
6RJ301 - RJ303
6RJ321 - RJ322
6RJ331 - RJ333
7RR001 - RR005
7RR021 - RR025
7RR031
7RR201 - RR206
7RR221 - RR226
7RR261 - RR267
7RR301 - RR310
7RR331 - RR332
7RR336
7RR341 - RR345
7RR361 - RR362
7RR421 - RR422
7RR431 - RR432
7RR441 - RR442
7RR451
7RR501 - RR504
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GroupVariable Number
7RR521 - RR522
7RR526
7RR531
7RR551 - RR556
7RR561
7RR566
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of work given in this Service Bulletin will make sure that necessary fasteners are
installed at stringer to stringer clip joints.These fasteners are located on the left and right side of Stringer
(S)-10, S-10A, and S-11 at Body Station (STA) 760 through 940 frames. If the fasteners are not installed,
fatigue cracking can occur in the adjacent shear ties.The cracks in the shear ties can cause skin cracks
and a rapid in-flight decompression.
The stringers are structurally connected to the body frames by stringer clips. The skin is attached to
the frame and stringers and shear ties are installed to the skin and frame. Adjacent to S-10, S-10A,
and S-11 at STA 760 through 940 frames, there are tension ties that connect the left and right sides
of the body structure aft of the upper deck floor.
During a routine maintenance of 747-200F airplanes, two operators reported findings of broken and
cracked shear ties on STA 820 frame between S-10AL and S-11L. Also cracks were found on the frame
doubler and frame web near S-11L. More inspection showed missing fasteners at the stringer to stringer
clip joint on S-10L at STA 820 frame. The cracks and missing fasteners were found on airplanes that
had 16,087 and 16,421 total flight cycles.
Boeing analysis shows that the cracks were caused by increased load on the shear ties because of
the missing fasteners in the stringer to stringer clip joint. Boeing investigation shows that a similar
cracking could occur in the frames adjacent to the tensions ties if the stringer clip fasteners are not
installed.
Accomplishment of the inspection in this Service Bulletin will make sure that the necessary fasteners
are installed at the stringer to stringer clip joints at S-10, S-10A, and S-11 at STA 760 through 940
frames.
Boeing Service Related Problem (SRP) 747-SRP-53-0317 is related to this service bulletin.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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### Page 17

D. Description
Do a General Visual Inspection to make sure that the fasteners are installed at the stringer to stringer
clip joints on S-10, S-10A, and S-11 at STA 760 through 940 frames. If the fasteners are installed, then
no more work is necessary. If the fasteners are missing, then do Detailed and Surface High Frequency
Eddy Current (HFEC) Inspections of the adjacent structure for a crack. If no crack is found, then install
the missing fasteners. If a crack is found, then do the repair(s) as given in the Structural Repair Manual
(SRM) and install the missing fasteners. After the SRM repair(s) do a repetitive Detailed Inspection of
the repaired area(s) as given in Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
233, 234, 241, 242, 243, 244747-100, 747-200B
Group 2-3:
Affected Maintenance Zones
ZoneModel
233, 234, 241, 242, 243, 244747-100
Group 4:
Affected Maintenance Zones
ZoneModel
233, 234, 241, 242, 243, 244747-100, 747-100B, 747-200B,
747SR
Group 5:
Affected Maintenance Zones
ZoneModel
233, 234, 241, 242, 243, 244747-100, 747-200B, 747SR
Group 6:
Affected Maintenance Zones
ZoneModel
233, 234, 241, 242, 243, 244747-100, 747-200B, 747-200C
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### Page 18

Group 7:
Affected Maintenance Zones
ZoneModel
233, 234, 241, 242, 243, 244747-200F
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.
Table 1: Inspect for Missing Fasteners at Stringer to Stringer Clip Joints
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 3,000 flight
cycles after the
date on this service
bulletin.
Do a General Visual
Inspection to make sure
that the fasteners are
installed at the stringer to
stringer clip joints on
S-10, S-10A and S-11 at
STA 760 through 940
frames as given in PART
2 of Paragraph 3.B.,
Work Instructions.
All airplanes.
--No more work is
necessary.
No fasteners are missing.
-Before further
flight.
Do Detailed and Surface
HFEC Inspections of the
adjacent frame and skin
structure for a crack as
given in PART 3 of
Paragraph 3.B., Work
Instructions.
Fasteners are missing.
-Before further
flight.
Install the missing
fasteners as given in
PART 4 of Paragraph
3.B., Work Instructions.
No crack found.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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### Page 19

Table 1: Inspect for Missing Fasteners at Stringer to Stringer Clip Joints
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Repair the shear ties,
frame web, and/or skin as
given in PART 3 of
Paragraph 3.B., Work
Instructions.
Crack found in the shear
ties, frame web, and/or
skin.
-Before further
flight.
Install the missing
fasteners as given in
PART 4 of Paragraph
3.B., Work Instructions.
3,000 flight cycles.Before 20,000 total
flight cycles
Do a Detailed Inspection
of the repair(s) and the
adjacent structure within
10 inches of the
repairs(s) for a crack.
Repair(s) installed for the
shear ties, frame web,
and/or skin as given in
PART 3 of Paragraph 3.B.,
Work Instructions.
or
within 3,000 flight
cycles from the
repair installation,
whichever occurs
later.
Before further
flight.
Contact Boeing for
alternative repair
instructions and do the
repair.
Crack found in the repair(s)
or in the adjacent structure
other than shear ties, frame
web, and skin.
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.
G. Manpower
The tables below show 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
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 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Table 1: Manpower Estimates for Initial Inspection
Elapsed HoursTask HoursNumber of
Persons
Task
3.5014.004Open Access
2.002.001FIGURE 1
2.002.001FIGURE 2
3.5014.004Close Access
11.0032.00TOTAL FOR EACH AIRPLANE (a)
(a) If the fasteners are missing, more time will be necessary for additional
inspections and possible repairs. Refer to Table 2 below for more information.
Table 2: Manpower Estimates for Additional Inspection
Elapsed HoursTask HoursNumber of
Persons
Task
2.752.751FIGURE 3 (a) (b)
2.752.751FIGURE 4 (a) (b)
3.753.751FIGURE 5 (a) (b)
3.753.751FIGURE 6 (a) (b)
2.752.751FIGURE 7 (a) (b)
2.752.751FIGURE 8 (a) (b)
3.503.501FIGURE 9 (a) (b)
3.503.501FIGURE 10 (a) (b)
3.753.751FIGURE 11 (a) (b)
3.753.751FIGURE 12 (a) (b)
3.003.001FIGURE 13 (a) (b)
3.003.001FIGURE 14 (a) (b)
3.503.501FIGURE 15 (a) (b)
3.503.501FIGURE 16 (a) (b)
3.253.251FIGURE 17 (a) (b)
3.253.251FIGURE 18 (a) (b)
0.400.401FIGURE 19 (a)
0.400.401FIGURE 20 (a)
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Table 2: Manpower Estimates for Additional Inspection
Elapsed HoursTask HoursNumber of
Persons
Task
(a) Estimates given are per location affected. Multiply affected areas by the time
given.
(b) If cracks are found, more time will be necessary for repairs.
H. Weight and Balance Changes
None.
I. Electrical Load Data
None.
J. References
1. Existing Data
a. Boeing Service Bulletin 747-53-2502
b. Boeing Service Related Problem (SRP) 747-SRP-53-0317
c. Standard Overhaul Practices Manual (SOPM) 20-41-05
d. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00 Figure 4 or 23
e. 747-100/200/300 Aircraft Maintenance Manual (AMM) 25-21-01, 25-21-04, 25-22-04, 25-25-01,
25-52-01, 25-52-04
f. 747-100/200/300 Structural Repair Manual (SRM) 51-30-05, 53-10-04, 53-30-03
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Frame Installation - Station 76065B01731
Frame Installation - Station 78065B01732
Frame Installation - Station 80065B01733
Frame Installation - Station 82065B01734
Frame Installation - Station 84065B01735
Frame Installation - Station 86065B01736
Frame Installation - Station 88065B01737
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TitleDrawing Number
Frame Installation - Station 90065B01738
Frame Installation - Station 92065B01739
Frame Installation - Station 94065B01740
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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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repairs given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
(a) (b)Bolt4BACB30MY6K2
(a) (b)Collar4BACC30M6
(a) Refer to 747 Structural Repair Manual Chapter 51 for alternative fasteners.
(b) Quantities are for one stringer to stringer clip joint.The actual quantity will vary and depend
on the inspection results.
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, may 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. 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
5. 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.
6. 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.
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7. 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.
8. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to ensure visual access to all surfaces in the
inspection area. This level of inspection is made under normal available lighting
conditions such as daylight, hangar lighting, flashlight or drop-light and may require
removal or opening of access panels or doors. Stands, ladders or platforms may be
required to gain proximity to the area being checked.
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.
B. WORK INSTRUCTIONS
PART 1: ACCESS
1. Group 1; Group 3, Configuration 1; Group 4; Group 6, Configuration 1:
Get Access to the Stringer to Stringer Clip Joints.
a. Remove seats between Body Station (STA) 760 and 940 frames. Refer to 747-100/200/300
AMM 25-25-01 as an accepted procedure.
b. Remove the sidewall and ceiling panels to get access to the stringer to stringer clip joints.
Refer to 747-100/200/300 AMM 25-21-01 and 747-100/200/300 AMM 25-22-04, respectively
as accepted procedures.
c. Remove insulation to get access to the stringer to stringer clip joints. Refer to 747-100/200/300
AMM 25-21-04 as an accepted procedure.
d. After getting access, do PART 2: INSPECTION FOR MISSING FASTENERS.
2. Group 2; Group 3, Configuration 2; Group 5; Group 6, Configuration 2; Group 7:
Get Access to the Stringer to Stringer Clip Joint.
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a. Remove the sidewall and ceiling linings to get access to the stringer to stringer clip joints.
Refer to 747-100/200/300 AMM 25-52-01 as an accepted procedure.
b. Remove the insulation to get access to the stringer to stringer clip joints. Refer to
747-100/200/300 AMM 25-52-04 as an accepted procedure.
c. After getting access, do PART 2: INSPECTION FOR MISSING FASTENERS.
PART 2: INSPECTION FOR MISSING FASTENERS
1. Do a General Visual Inspection for missing fasteners (left side) as given in FIGURE 1.
a. If the fasteners are installed, then do PART 5: CLOSE ACCESS.
b. If the fasteners are missing, then do PART 3: INSPECTION FOR DAMAGE.
2. Do a General Visual Inspection for missing fasteners (right side) as given in FIGURE 2.
a. If the fasteners are installed, then do PART 5: CLOSE ACCESS.
b. If the fasteners are missing, then do PART 3: INSPECTION FOR DAMAGE.
PART 3: INSPECTION FOR DAMAGE
1. Group 1-3:
Do Detailed and Surface High Frequency Eddy Current (HFEC) Inspections of the frame and skin
structure adjacent to all of the missing fastener locations as given in the following table:
TABLE 1: INSPECTION LAYOUT FOR STRINGER AND FRAME LOCATIONS
S-11RS-11LS-10ARS-10ALS-10RS-10L
FIGURE 6FIGURE 5FIGURE 4FIGURE 3FIGURE 18FIGURE 17STA 760
FIGURE 10FIGURE 9FIGURE 6FIGURE 5FIGURE 4FIGURE 3STA 780
FIGURE 16FIGURE 15FIGURE 12FIGURE 11FIGURE 6FIGURE 5STA 800
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 820
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 840
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 860
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 880
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 900
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 920
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 940
Note: Multiple locations from STA 760 through 940 may be affected by the missing fasteners. Adjacent stringer
locations on a frame may overlap in inspection areas. If the overlap of the inspection areas occur, then it is
necessary to inspect once from one end of the inspection area to the other end.
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a. If no crack is found, then do PART 4: INSTALL MISSING FASTENERS.
b. If a crack is found, then do the following:
(1) Do the following repair(s):
(a) For a crack in the shear ties, do the repair as given in 747-100/200/300 SRM 53-10-04
Figures 3, 3A, or 4 as applicable.
(b) For a crack in the frame web, do the repair as given in 747-100/200/300 SRM
53-10-04, Figures 132 through 138 as applicable.
(c) For a crack in the skin, do the repair as given in 747-100/200/300 SRM 53-30-03 as
applicable.
(2) Do a repetitive Detailed Inspection of the repair(s) and the adjacent structure within 10
inches of the repair(s) for a crack at the time as given in Paragraph 1.E., Compliance.
(3) If a crack is found in the repair(s) or in the adjacent structure other than the shear ties,
frame web, and skin; contact Boeing for alternative repair instructions. Do the repair at
the time as given in Paragraph 1.E., Compliance.
(4) After doing all the necessary repairs, do PART 4: INSTALL MISSING FASTENERS.
2. Group 4-6:
Do Detailed and Surface HFEC Inspections of the frame and skin structure adjacent to all of the
missing fastener locations as given in the following table:
TABLE 2: INSPECTION LAYOUT FOR STRINGER AND FRAME LOCATIONS
S-11RS-11LS-10ARS-10ALS-10RS-10L
FIGURE 14FIGURE 13FIGURE 8FIGURE 7FIGURE 18FIGURE 17STA 760
FIGURE 12FIGURE 11FIGURE 6FIGURE 5FIGURE 4FIGURE 3STA 780
FIGURE 16FIGURE 15FIGURE 12FIGURE 11FIGURE 6FIGURE 5STA 800
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 820
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 840
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 860
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 880
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 900
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 920
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 940
Note: Multiple locations from STA 760 through 940 may be affected by the missing fasteners. Adjacent stringer
locations on a frame may overlap in inspection areas. If the overlap of the inspection areas occur, then it is
necessary to inspect once from one end of the inspection area to the other end.
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a. If no crack is found, then do PART 4: INSTALL MISSING FASTENERS.
b. If a crack is found, then do the following:
(1) Do the following repair(s):
(a) For a crack in the shear ties, do the repair as given in 747-100/200/300 SRM 53-10-04
Figures 3, 3A, or 4 as applicable.
(b) For a crack in the frame web, do the repair as given in 747-100/200/300 SRM
53-10-04, Figures 132 through 138 as applicable.
(c) For a crack in the skin, do the repair as given in 747-100/200/300 SRM 53-30-03 as
applicable.
(2) Do a repetitive Detailed Inspection of the repair(s) and the adjacent structure within 10
inches of the repair(s) for a crack at the time as given in Paragraph 1.E., Compliance.
(3) If a crack is found in the repair(s) or in the adjacent structure other than the shear ties,
frame web, and skin; contact Boeing for alternative repair instructions. Do the repair at
the time as given in Paragraph 1.E., Compliance.
(4) After doing all the necessary repairs, do PART 4: INSTALL MISSING FASTENERS.
3. Group 7:
Do Detailed and Surface HFEC Inspections of the frame and skin structure adjacent to all of the
missing fastener locations as given in the following table:
TABLE 3: INSPECTION LAYOUT FOR STRINGER AND FRAME LOCATIONS
S-11RS-11LS-10ARS-10ALS-10RS-10L
FIGURE 12FIGURE 11FIGURE 6FIGURE 5FIGURE 4FIGURE 3STA 760
FIGURE 10FIGURE 9FIGURE 6FIGURE 5FIGURE 4FIGURE 3STA 780
FIGURE 16FIGURE 15FIGURE 12FIGURE 11FIGURE 6FIGURE 5STA 800
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 820
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 840
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 860
FIGURE 18FIGURE 17FIGURE 18FIGURE 17FIGURE 18FIGURE 17STA 880
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 900
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 920
FIGURE 18FIGURE 17N/AN/AFIGURE 18FIGURE 17STA 940
Note: Multiple locations from STA 760 through 940 may be affected by the missing fasteners. Adjacent stringer
locations on a frame may overlap in inspection areas. If the overlap of the inspection areas occur, then it is
necessary to inspect once from one end of the inspection area to the other end.
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a. If no crack is found, then do PART 4: INSTALL MISSING FASTENERS.
b. If a crack is found, then do the following:
(1) Do the following repair(s):
(a) For a crack in the shear ties, do the repair as given in 747-100/200/300 SRM 53-10-04
Figures 3, 3A, or 4 as applicable.
(b) For a crack in the frame web, do the repair as given in 747-100/200/300 SRM
53-10-04, Figures 132 through 138 as applicable.
(c) For a crack in the skin, do the repair as given in 747-100/200/300 SRM 53-30-03 as
applicable.
(2) Do a repetitive Detailed Inspection of the repair(s) and the adjacent structure within 10
inches of the repair(s) for a crack at the time as given in Paragraph 1.E., Compliance.
(3) If a crack is found in the repair(s) or in the adjacent structure other than the shear ties,
frame web, and skin; contact Boeing for alternative repair instructions. Do the repair at
the time as given in Paragraph 1.E., Compliance.
(4) After doing all the necessary repairs, do PART 4: INSTALL MISSING FASTENERS.
PART 4: INSTALL MISSING FASTENERS
1. Install the missing fasteners at stringer to stringer clip joints (left side) as given in FIGURE 19.
a. Keep a minimum of 2D edge margin from edge of any structure during the installation of the
fasteners.
b. After installing the fasteners, do Part 5: CLOSE ACCESS.
2. Install the missing fasteners at stringer to stringer clip joints (right side) as given in FIGURE 20.
a. Keep a minimum of 2D edge margin from edge of any structure during the installation of the
fasteners.
b. After installing the fasteners, do Part 5: CLOSE ACCESS.
PART 5: CLOSE ACCESS
1. Group 1; Group 3, Configuration 1; Group 4; Group 6, Configuration 1:
Close access and put back into serviceable condition.
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a. Apply BMS 3-23, Type II, Corrosion Inhibiting Compound to all areas where fasteners were
removed, and where repairs were done. Refer to Boeing Standard Overhaul Practices Manual,
SOPM 20-41-05.
b. Install the insulation. Refer to 747-100/200/300 AMM 25-21-04 as an accepted procedure.
c. Install the sidewall and ceiling panels. Refer to 747-100/200/300 AMM 25-21-01 and
747-100/200/300 AMM 25-22-04, respectively as accepted procedures.
d. Install the seats between STA 760 and 940 frames. Refer to 747-100/200/300 AMM 25-25-01
as an accepted procedure.
2. Group 2; Group 3, Configuration 2; Group 5; Group 6, Configuration 2; Group 7:
Close access and put back into serviceable condition.
a. Apply BMS 3-23, Type II, Corrosion Inhibiting Compound to all areas where fasteners were
removed, and where repairs were done. Refer to SOPM 20-41-05.
b. Install the insulation. Refer to 747-100/200/300 AMM 25-52-04 as an accepted procedure.
c. Install the sidewall and ceiling linings. Refer to 747-100/200/300 AMM 25-52-01 as an accepted
procedure.
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BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
STA
940
STA
760
_S-O
_ S-10L
• S-10AL
S-11L
‚→ S-12L
STA
760
STA
STA  780
800
820
STA
840
STA
860
STA
880
STA
900
STA
STA  920  1494880
940
FIGURE 1: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS (LEFT
SIDE)
(SHEET 1 OF 3)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
FRAME
(TYPICAL)
STRINGER
(TYPICAL)
STRINGER CLIP
(TYPICAL)
1495139
FIGURE 1: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS (LEFT
SIDE)
(SHEET 2 OF 3)
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### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The stringer
clip shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a General Visual
Inspection to make
sure that the
fasteners are
installed on the
stringer to stringer
clip joints (a) (b)
--STRINGER TO
STRINGER CLIP
JOINTS
Inspect1
(a) For STA 760, 780, 800, 820, 840, 860, and 880 inspect S-10L, S-10AL, and S-11L.
(b) For STA 900, 920 and 940 inspect S-10L and S-11L.
FIGURE 1: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS (LEFT
SIDE)
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
STA
940 STA
760
5-0 -
S-9R
S-10R
S-10AR
S-11R
S-12R
STA
800
820
STA
840
STA
860
STA
FWD  880
STA
900
STA
920  STA  1495143
940
FIGURE 2: INSPECTION FOR MISSING FASTENERS AT STRINGERTO STRINGER CLIP JOINTS (RIGHT
SIDE)
(SHEET 1 OF 3)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
FRAME
(TYPICAL)
• STRINGER
(TYPICAL)
STRINGER CLIP
(TYPICAL)
1495142
FIGURE 2: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS (RIGHT
SIDE)
(SHEET 2 OF 3)
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### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The stringer
clip shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a General Visual
Inspection to make
sure that the
fasteners are
installed on the
stringer to stringer
clip joints (a) (b)
--STRINGER TO
STRINGER CLIP
JOINTS
Inspect1
(a) For STA 760, 780, 800, 820, 840, 860, and 880 inspect S-10R, S-10AR, and S-11R.
(b) For STA 900, 920 and 940 inspect S-10R and S-11R.
FIGURE 2: INSPECTION FOR MISSING FASTENERS AT STRINGER TO STRINGER CLIP JOINTS (RIGHT
SIDE)
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
STA
940
STA
760
S-10L
S- 10AL
S-11L
TYPICAL STRINGER
WITH MISSING
FASTENERS
TYPICAL FRAME
FWD
1541004
FIGURE 3: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENTTO FRAME SPLICE ONTYPICAL
FRAME (LEFT SIDE)
(SHEET 1 OF 4)
October 09, 2008
747-53A2751
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### Page 39

FIGURE 3: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO FRAME SPLICE ON TYPICAL
FRAME (LEFT SIDE)
(SHEET 2 OF 4)
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October 09, 2008
747-53A2751
39 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
TYPICAL FRAME STRINGER CUTOUT
B-B
TOP EDGE SURFACE (4
ALONG THE RADIUS
(4 CORNERS)
TYPICAL FRAME SPLICE STRINGER CUTOUT
1544188
FIGURE 3: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENTTO FRAME SPLICE ONTYPICAL
FRAME (LEFT SIDE)
(SHEET 3 OF 4)
October 09, 2008
747-53A2751
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### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The location
shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a Detailed
Inspection for a
crack in the shear
ties, frame web, and
skin adjacent to the
missing fastener
location.(a)
--FRAME AND SKIN
STRUCTURE
Inspect1
Do a Surface HFEC
Inspection for a
crack along the
radius as given in
747 NDT Part 6,
51-00-00 Figure 4 or
23.(b)
--SHEAR TIESInspect2
Do a Surface HFEC
Inspection for a
crack at the stringer
cutout radius as
given in 747 NDT
Part 6, 51-00-00
Figure 4 or 23.(c) (d)
--FRAMEInspect3
Do a Surface HFEC
Inspection for a
crack along the
radius and edge
surface of the flange
intersection as given
in 747 NDT Part 6,
51-00-00 Figure 4 or
23.
--FRAME SPLICEInspect4
(a) Inspect the structure within 10 inches of each missing fastener location on the frame.
(b) Inspect the Single, Double, or "T" Flange shear ties as applicable.
(c) Inspect the edges of all components at the stringer cutout radius.
(d) Inspect the surface and around the fasteners adjacent to the stringer cutout radius.
FIGURE 3: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO FRAME SPLICE ON TYPICAL
FRAME (LEFT SIDE)
(SHEET 4 OF 4)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
41 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
STA
940
STA
760
S-10L
S-10AL
S-11L
FASTENERS GER
TYPICAL FRAME
FWD
1541768
FIGURE 4: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENTTO FRAME SPLICE ONTYPICAL
FRAME (RIGHT SIDE)
(SHEET 1 OF 4)
October 09, 2008
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

### Page 43

FIGURE 4: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO FRAME SPLICE ON TYPICAL
FRAME (RIGHT SIDE)
(SHEET 2 OF 4)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
43 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
TYPICAL FRAME STRINGER CUTOUT
B-B
(4) TOP EDGE SURFACE
ALONG THE RADIUS 4
(4 CORNERS)
TYPICAL FRAME SPLICE STRINGER CUTOUT
1544260
FIGURE 4: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENTTO FRAME SPLICE ONTYPICAL
FRAME (RIGHT SIDE)
(SHEET 3 OF 4)
October 09, 2008
747-53A2751
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  44 of 111

### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The location
shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a Detailed
Inspection for a
crack in the shear
ties, frame web, and
skin adjacent to the
missing fastener
location.(a)
--FRAME AND SKIN
STRUCTURE
Inspect1
Do a Surface HFEC
Inspection for a
crack along the
radius as given in
747 NDT Part 6,
51-00-00 Figure 4 or
23.(b)
--SHEAR TIESInspect2
Do a Surface HFEC
Inspection for a
crack at the stringer
cutout radius as
given in 747 NDT
Part 6, 51-00-00
Figure 4 or 23.(c) (d)
--FRAMEInspect3
Do a Surface HFEC
Inspection for a
crack along the
radius and edge
surface of the flange
intersection as given
in 747 NDT Part 6,
51-00-00 Figure 4 or
23.
--FRAME SPLICEInspect4
(a) Inspect the structure within 10 inches of each missing fastener location on the frame.
(b) Inspect the Single, Double, or "T" Flange shear ties as applicable.
(c) Inspect the edges of all components at the stringer cutout radius.
(d) Inspect the surface and around the fasteners adjacent to the stringer cutout radius.
FIGURE 4: INSPECTION OF FRAME AND SKIN STRUCTURE - ADJACENT TO FRAME SPLICE ON TYPICAL
FRAME (RIGHT SIDE)
(SHEET 4 OF 4)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
45 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
SIA
940
. S-10L
S-10AL
S-11L
TYPICAL STRINGER
WITH MISSING
FASTENERS
TYPICAL
FRAME
FWD  1541981
FIGURE 5: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (LEFT SIDE)
(SHEET 1 OF 5)
October 09, 2008
747-53A2751
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### Page 47

FIGURE 5: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (LEFT SIDE)
(SHEET 2 OF 5)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
47 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
OR
FWD  WD
SHEAR TIE
SINGLE FLANGE
B-B
TYPICAL FRAME STRINGER CUTOUT
C-C  1544365
FIGURE 5: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (LEFT SIDE)
(SHEET 3 OF 5)
October 09, 2008
747-53A2751
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
TOP EDGE SURFACE (4
4) ALONG THE RADIUS
(4 CORNERS)
TYPICAL FRAME SPLICE STRINGER CUTOUT
TYPICAL FRAME SPLICE FLANGE
1544349
FIGURE 5: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (LEFT SIDE)
(SHEET 4 OF 5)
October 09, 2008
747-53A2751
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  49 of 111

### Page 50

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The location
shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a Detailed
Inspection for a
crack in the shear
ties, frame web, and
skin adjacent to the
missing fastener
location.(a)
--FRAME AND SKIN
STRUCTURE
Inspect1
Do a Surface HFEC
Inspection for a
crack along the
radius as given in
747 NDT Part 6,
51-00-00 Figure 4 or
23.(b)
--SHEAR TIESInspect2
Do a Surface HFEC
Inspection for a
crack at the stringer
cutout radius as
given in 747 NDT
Part 6, 51-00-00
Figure 4 or 23.(c) (d)
--FRAMEInspect3
Do a Surface HFEC
Inspection for a
crack along the
radius and edge
surface of the flange
intersection as given
in 747 NDT Part 6,
51-00-00 Figure 4 or
23.
--FRAME SPLICEInspect4
(a) Inspect the structure within 10 inches of each missing fastener location on the frame.
(b) Inspect the Single, Double, "L", or "T" Flange shear ties as applicable.
(c) Inspect the edges of all components at the stringer cutout radius.
(d) Inspect the surface and around the fasteners adjacent to the stringer cutout radius.
FIGURE 5: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (LEFT SIDE)
(SHEET 5 OF 5)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
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50 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 51 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
STA
940
S-10L
S-10AL
S-11L
TYPICAL STRINGER
WITH MISSING
FASTENERS
TYPICAL
FRAME
FWD  1542258
FIGURE 6: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (RIGHT SIDE)
(SHEET 1 OF 5)
October 09, 2008
747-53A2751
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### Page 52

FIGURE 6: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (RIGHT SIDE)
(SHEET 2 OF 5)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
52 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
OR
FWD  FWD
V
SHEAR TIE  SHEAR TIE
I L FLANGE  SINGLE FLANGE
B-B
TYPICAL FRAME STRINGER CUTOUT
C-C  1544455
FIGURE 6: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (RIGHT SIDE)
(SHEET 3 OF 5)
October 09, 2008
747-53A2751
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### Page 54 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
4) TOP EDGE SURFACE
ALONG THE RADIUS (4
(4 CORNERS)
TYPICAL FRAME SPLICE STRINGER CUTOUT
TYPICAL FRAME SPLICE FLANGE
1544475
FIGURE 6: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (RIGHT SIDE)
(SHEET 4 OF 5)
October 09, 2008
747-53A2751
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  54 of 111

### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The location
shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a Detailed
Inspection for a
crack in the shear
ties, frame web, and
skin adjacent to the
missing fastener
location.(a)
--FRAME AND SKIN
STRUCTURE
Inspect1
Do a Surface HFEC
Inspection for a
crack along the
radius as given in
747 NDT Part 6,
51-00-00 Figure 4 or
23.(b)
--SHEAR TIESInspect2
Do a Surface HFEC
Inspection for a
crack at the stringer
cutout radius as
given in 747 NDT
Part 6, 51-00-00
Figure 4 or 23.(c) (d)
--FRAMEInspect3
Do a Surface HFEC
Inspection for a
crack along the
radius and edge
surface of the flange
intersection as given
in 747 NDT Part 6,
51-00-00 Figure 4 or
23.
--FRAME SPLICEInspect4
(a) Inspect the structure within 10 inches of each missing fastener location on the frame.
(b) Inspect the Single, Double, "L", or "T" Flange shear ties as applicable.
(c) Inspect the edges of all components at the stringer cutout radius.
(d) Inspect the surface and around the fasteners adjacent to the stringer cutout radius.
FIGURE 6: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF FRAME SPLICE (RIGHT SIDE)
(SHEET 5 OF 5)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
55 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
This Figure applies only to: Group 4-6.
STA
940
STA
760
•S-10L
• S-10AL
S-11L
TYPICAL STRINGER
WITH MISSING
FASTENERS
TYPICAL FRAME
FWD
FIGURE 7: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE (LEFT
SIDE)
(SHEET 1 OF 5)
October 09, 2008
747-53A2751
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### Page 57

FIGURE 7: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE (LEFT
SIDE)
(SHEET 2 OF 5)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
57 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
OR
FWD  -WD
SHEAR TIE
SINGLE FLANGE
B-B
TYPICAL FRAME STRINGER CUTOUT
C-C  1544542
FIGURE 7: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE (LEFT
SIDE)
(SHEET 3 OF 5)
October 09, 2008
747-53A2751
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### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-53A2751
ALERT  ALERT
TOP EDGE SURFACE (4
4) ALONG THE RADIUS
(4 CORNERS)
TYPICAL FRAME SPLICE STRINGER CUTOUT
TYPICAL FRAME SPLICE FLANGE
1544526
FIGURE 7: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE (LEFT
SIDE)
(SHEET 4 OF 5)
October 09, 2008
747-53A2751
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  59 of 111

### Page 60

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The location
shown is typical for each stringer to stringer clip joint.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a Detailed
Inspection for a
crack in the shear
ties, frame web, and
skin adjacent to the
missing fastener
location.(a)
--FRAME AND SKIN
STRUCTURE
Inspect1
Do a Surface HFEC
Inspection for a
crack along the
radius as given in
747 NDT Part 6,
51-00-00 Figure 4 or
23.(b)
--SHEAR TIESInspect2
Do a Surface HFEC
Inspection for a
crack at the stringer
cutout radius as
given in 747 NDT
Part 6, 51-00-00
Figure 4 or 23.(c) (d)
--FRAMEInspect3
Do a Surface HFEC
Inspection for a
crack along the
radius and edge
surface of the flange
intersection as given
in 747 NDT Part 6,
51-00-00 Figure 4 or
23.
--FRAME SPLICEInspect4
(a) Inspect the structure within 10 inches of each missing fastener location on the frame.
(b) Inspect the Single, Double, "L", or "T" Flange shear ties as applicable.
(c) Inspect the edges of all components at the stringer cutout radius.
(d) Inspect the surface and around the fasteners adjacent to the stringer cutout radius.
FIGURE 7: INSPECTION OF FRAME AND SKIN STRUCTURE - END OF STEPPED FRAME SPLICE (LEFT
SIDE)
(SHEET 5 OF 5)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
October 09, 2008
747-53A2751
60 of 111
BOEING SERVICE BULLETIN 747-53A2751
ALERTALERT

The text continues at https://openairdocs.org/service-documents/boeing/747-53a2751/file/79cde51f0e63.md?from=61

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