# Boeing Alert Service Bulletin 747-53A2605: Revision 1

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- Document: [Boeing Alert Service Bulletin 747-53A2605](https://openairdocs.org/service-documents/boeing/747-53a2605.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 
SB-747-53A2605-01
- Pages: 158
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2605
Original Issue: October 08, 2009
Revision 1: May 27, 2010
ATA System: 5312
SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and 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 © 2009 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Unpublished Work - All Rights Reserved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, KC-10, KDC-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
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 9
B. Concurrent Requirements ...................................... 1 9
C. Reason ................................................ 1 9
D. Description .............................................. 1 9
E. Compliance .............................................. 2 1
F. Approval ............................................... 2 3
G. Manpower .............................................. 2 4
H. Weight and Balance Changes .................................... 3 2
I. Electrical Load Data ......................................... 3 2
J. References .............................................. 3 2
1. Existing Data: ......................................... 3 2
2. Data supplied with this Service Bulletin: ........................... 3 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 6
K. Publications Affected ........................................ 3 6
L. Interchangeability and Intermixability of Parts ........................... 3 6
2. MATERIAL INFORMATION ........................................ 3 7
A. Material - Price and Availability ................................... 3 7
B. Industry Support Information .................................... 3 8
C. Parts Necessary For Each Airplane ................................. 3 8
1. Kits/Parts: ........................................... 3 8
2. Parts and Materials Supplied by the Operator: ....................... 1 4 5
3. Parts Modified and Reidentified: ............................... 1 4 5
4. Parts Removed and Not Replaced: ............................. 1 4 5
D. Parts Necessary to Change Spares ................................ 1 4 5
E. Special Tooling - Price and Availability .............................. 1 4 5
F. Special Tooling Necessary to do this Service Bulletin ...................... 1 4 6
3. ACCOMPLISHMENT INSTRUCTIONS ................................. 1 4 7
A. GENERAL INFORMATION .................................... 1 4 7
B. WORK INSTRUCTIONS ...................................... 1 4 8
APPENDIX A: TENSION TIE DISCONNECTION METHODS ....................... 1 5 7
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-53A2605Original Issue: October 08, 2009
Revision 1: May 27, 2010
ATA System: 5312
SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.
More airplanes were added to the service bulletin effectivity. Airplanes RR561 and RR566 were added to Group
8.
REASON FOR REVISION
This revision is sent to add more airplanes to the service bulletin effectivity and add Appendix A to give information
on methods for disconnecting tension ties.
These sections were changed:
1. In Paragraph 1.A., Effectivity, added airplanes RR561 and RR566 to Group 8.
2. In Paragraph 1.C., Reason, and Paragraph 1.D., Description, added revision information.
3. In Paragraph 1.J.2, Data Supplied with this Service Bulletin, updated drawing list. Drawing number,
142U0101#DL Revision B, is sent with this revision of the service bulletin.
4. In Paragraph 2.A., Material - Price and Availability, updated pricing of the kits.
5. Appendix A was added to give information on methods for disconnecting tension ties.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
October 08, 2009Original Issue:
May 27, 2010Revision 1:
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2605Original Issue: October 08, 2009
Revision 1: May 27, 2010
ATA System: 5312
SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions for modification of upper deck tension ties and adjacent frame structure
on non stretched upper deck (Non-SUD) airplanes. The tension ties have been determined to be structure that
is susceptible to Widespread Fatigue Damage (WFD). WFD can cause tension ties to become severed or
disconnected from the frames. Severed or disconnected Tension Ties and/or Frames at multiple locations could
result in rapid in-flight decompression.
For more information about WFD, refer to Boeing Service Letter 747-SL-53-088B.
Service Bulletin 747-53A2502 recommends initial and repeat inspection of Non-SUD airplane tension ties from
body station (STA) 760 to STA 940. Service Bulletin 747-53-2502 was issued to address multiple reports of
cracks found in tension ties and adjacent frame structure. Accomplishment of the modification in this service
bulletin terminates the repeat inspection requirement of Service Bulletin 747-53-2502.
Federal Aviation Administration (FAA) Airworthiness Directives 2004-07-22 R1 and 2006-01-07 are related to
this service bulletin.
Boeing Service Related Problem (SRP) 747-SRP-53-0200 is related to this service bulletin.
ACTION (PRR 85901-68RS)
Get access to the Frame to Tension Tie joints at STA 720 through STA 940 or STA 840 through STA 940
depending on the group. At each station, disconnect and remove a section of the tension tie between the frame
and approximate Buttock Line (BL) 36. For each frame, remove a specified section of the frame above and
below the tension tie attach point. After the existing frame and tension tie structure has been removed and
discarded, install new frame and tension tie structure. Do the modification on both sides of the airplane.
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After modification, do initial and repeat inspections of the unmodified areas of the tension ties at the compliance
time specified in paragraph 1.E., Compliance. Also, if the airplane will be operated past the post-modification
inspection compliance time specified in paragraph 1.E., then contact Boeing for post-modification inspection
instructions and do initial and repeat inspections of the modified tension tie and frame structure.
EFFECTIVITY
747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, and 747SR airplanes. Refer to paragraph 1.A.,
Effectivity, for the list of affected 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 2004-07-22 R1 and 2006-01-07 are related to
this service bulletin.
Refer to paragraph 1.E, Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the modification and inspections given in this service bulletin.
MANPOWER
Refer to paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-53A2605
ALERT  ALERT
SIA
STA  940
720
FRAME (TYPICAL)
TENSION TIE (TYPICAL)
STA
720
MODIFY /INSPECT
TENSION TIES AND
FRAMES
FWD  STA
940  1732168
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Revision 1: May 27, 2010  747-53A2605
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  9 of 158

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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2605
Original Issue: October 08, 2009
Revision 1: May 27, 2010
ATA System: 5312
SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and 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
This service bulletin is for the airplanes shown below. Refer to PRR 85901-68RS for data about
this change.
Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
NOTE: This service bulletin is for the airplanes identified below.
DESCRIPTIONCONFIGURATIONGROUP
747-100/-200B airplanes. Contains 142U0102-233 Tension Tie Mod.
Kit.
-1
747-100 airplanes. Contains 142U0102-233 Tension Tie Mod. Kit.-2
747-100/-200B airplanes.-3
747-100/-100B/-200B and 747SR airplanes.-4
747-200B and 747SR airplanes.-5
747-100/-100B/-200B and 747SR airplanes.-6
747-200B and 747SR airplanes.-7
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DESCRIPTIONCONFIGURATIONGROUP
747-200F Freighter airplanes.-8
747-200C airplanes.-9
747-400F Freighter airplanes.-10
747-100 airplanes. Contains 142U0102-233 Tension Tie Mod. Kit.-11
747-100 airplanes.-12
747-100 airplanes. Contains 142U0102-232 Tension Tie Mod. Kit.-13
747-100 airplanes. Contains 142U0102-232 Tension Tie Mod. Kit.-14
747-100 airplanes. Contains 142U0102-232 Tension Tie Mod. Kit.-15
Airplane Models:
747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR
GroupVariable Number
13RA001 - RA025
11RA026
1RA027 - RA028
11RA029
1RA030 - RA032
11RA033
1RA034
15RA101 - RA103
14RA104 - RA110
11RA111 - RA112
2RA113 - RA115
11RA161 - RA162
12RA163
3RA164
14RA201 - RA203
1RA216
3RA217
1RA245
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GroupVariable Number
4RA246
13RA251 - RA254
1RA255
3RA256 - RA266
13RA301 - RA303
1RA304 - RA306
3RA307 - RA313
4RA314 - RA317
6RA318
13RA351 - RA355
1RA356 - RA360
1RA369 - RA371
3RA372 - RA373
14RA401 - RA403
2RA404 - RA412
3RA413
4RA414 - RA418
1RA501 - RA502
13RA521 - RA523
12RA524
3RA525 - RA528
1RA532 - RA534
3RA535 - RA543
4RA544 - RA548
13RA551 - RA552
1RA559 - RA560
3RA561
1RA581 - RA582
3RA585
1RA601 - RA602
1RA631
11RA632
1RA633
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GroupVariable Number
12RA634 - RA635
1RA651 - RA652
1RA671 - RA674
3RA675 - RA677
1RA701
3RA702
1RA721 - RA722
3RA723 - RA724
4RA725 - RA731
1RA741 - RA743
3RA744 - RA745
4RA749 - RA750
1RA761 - RA762
1RA781
4RA782 - RA784
15RA901 - RA902
14RA903 - RA904
2RA905 - RA909
11RA910 - RA916
4RB001 - RB016
15RB041
14RB042
15RB043
2RB044
3RB071 - RB075
1RB101 - RB102
6RB411 - RB413
4RB421
4RB601 - RB603
5RB604 - RB605
4RB606
5RB607
6RB681 - RB695
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GroupVariable Number
7RB696
6RB697
6RB711
4RB721 - RB723
4RB741 - RB748
4RD001 - RD004
4RD021 - RD022
5RD041
4RD042
5RD043 - RD044
4RD045 - RD054
5RD055
4RD056 - RD059
4RD071 - RD072
4RD081
7RD082 - RD083
6RD091 - RD092
4RD101 - RD104
4RD121
6RD122 - RD127
6RD131 - RD141
7RD142
6RD143
7RD144
6RD166 - RD167
4RD171 - RD172
6RD181 - RD183
6RD201 - RD204
6RD221 - RD224
7RD225
6RD226
7RD227
6RD231 - RD232
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GroupVariable Number
7RD233 - RD235
6RD241 - RD243
4RD251 - RD262
6RD271 - RD272
6RD291 - RD292
7RD301 - RD302
6RD311
6RD351 - RD357
7RD358
7RD361 - RD366
7RD411 - RD412
6RD413 - RD414
6RD421 - RD426
4RD431 - RD435
7RD441 - RD442
6RD451 - RD456
7RD461
6RD471 - RD475
6RD513 - RD519
6RD531 - RD533
5RD551
6RD561
4RD571
7RD581 - RD583
6RD591 - RD593
4RD621
5RD622 - RD623
7RD641 - RD643
6RD644 - RD645
7RD646
6RD647 - RD649
6RD651 - RD659
6RD661
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GroupVariable Number
4RD671
6RD681 - RD682
7RD691
6RD692
6RD701 - RD702
6RD741 - RD742
6RD751
7RD752
6RD753 - RD755
6RD761
6RD771 - RD775
6RD781 - RD783
6RD791 - RD792
6RE001
9RJ131 - RJ133
9RJ151 - RJ152
9RJ301 - RJ303
9RJ321 - RJ322
9RJ331 - RJ333
10RL401 - RL403
10RL411 - RL436
10RL451 - RL456
10RL461 - RL462
10RL471 - RL481
10RL491 - RL492
10RL501 - RL502
10RL511 - RL516
10RL521 - RL522
10RL531 - RL534
10RL551
10RL561 - RL568
10RL571 - RL572
10RL576 - RL577
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GroupVariable Number
10RL579
10RL581 - RL586
10RL651 - RL655
10RL671 - RL675
10RL681 - RL684
10RL751 - RL752
10RM851 - RM859
10RM861 - RM863
10RM871 - RM899
10RM901 - RM906
10RM911
8RR001 - RR005
8RR021 - RR025
8RR031
8RR201 - RR206
8RR221 - RR226
8RR261 - RR267
8RR301 - RR310
8RR331 - RR332
8RR336
8RR341 - RR345
8RR361 - RR362
8RR421 - RR422
8RR431 - RR432
8RR441 - RR442
8RR451
8RR501 - RR504
8RR521 - RR522
8RR526
8RR531
8RR551 - RR556
8RR561
8RR566
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GroupVariable Number
10RR701
10RR721 - RR724
10RR746 - RR748
10RR851 - RR856
10RR861 - RR862
10RR951 - RR952
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions for modification of upper deck tension ties and adjacent frame
structure on non stretched upper deck (Non-SUD) airplanes. The tension ties have been determined
to be structure that is susceptible to Widespread Fatigue Damage (WFD). WFD can cause tension ties
to become severed or disconnected from the frames. Severed or disconnected Tension Ties and/or
Frames at multiple locations could result in rapid in-flight decompression.
For more information about WFD, refer to Boeing Service Letter 747-SL-53-088B.
Service Bulletin 747-53-2502 recommends initial and repeat inspection of Non-SUD airplane tension
ties from body station (STA) 760 to STA 940. Service Bulletin 747-53-2502 was issued to address
multiple reports of cracks found in tension ties and adjacent frame structure. Accomplishment of the
modification in this service bulletin terminates the repeat inspection requirement of Service Bulletin
747-53-2502.
Federal Aviation Administration (FAA) Airworthiness Directives 2004-07-22 R1 and 2006-01-07 are
related to this service bulletin.
Revision 1 is sent to add more airplanes to the service bulletin effectivity and add Appendix A to give
information on methods for disconnecting tension ties.
Boeing Service Related Problem (SRP) 747-SRP-53-0200 is related to this service bulletin.
D. Description
Get access to the Frame to Tension Tie joints at STA 720 through STA 940 or STA 840 through STA
940 depending on the group. At each station, disconnect and remove a section of the tension tie
between the frame and approximate Buttock Line (BL) 36. For each frame, remove a specified section
of the frame above and below the tension tie attach point. After the existing frame and tension tie
structure has been removed and discarded, install new frame and tension tie structure. Do the
modification on both sides of the airplane.
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After modification, do initial and repeat inspections of the unmodified areas of the tension ties at the
compliance time specified in paragraph 1.E., Compliance. Also, if the airplane will be operated past
the post-modification inspection compliance time specified in paragraph 1.E., then contact Boeing for
post-modification inspection instructions and do initial and repeat inspections of the modified tension
tie and frame structure.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1, 3:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-100, 747-200B
Group 2, 11-15:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-100
Group 4, 6:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-100, 747-100B, 747-200B,
747SR
Group 5, 7:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-200B, 747SR
Group 8:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-200F
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Group 9:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-200C
Group 10:
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244747-400F
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 2004-07-22 R1 and 2006-01-07 are
related to this service bulletin.
Table 1: Tension Tie and Frame - Modification and Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 30,000
total flight cy-
cles.
Do the tension tie and
frame structure modifica-
tion in accordance with
the Accomplishment In-
structions, paragraph
3.B., Part 1.
All airplanes.
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Table 1: Tension Tie and Frame - Modification and Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before 6,000 flight cycles after
modification in accordance with
the Accomplishment Instructions,
paragraph 3.B., Part 1.
Do a detailed inspection
of the unmodified areas
of the tension ties for
cracks, in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 2.
Modification has been done
in accordance with the Ac-
complishment Instructions,
paragraph 3.B., Part 1 of
this service bulletin. (a)
-Before 20,000 flight cycles after
modification in accordance with
the Accomplishment Instructions,
paragraph 3.B., Part 1.
Do an inspection of the
modified areas of the
tension tie and frame
structure in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 3. Contact
Boeing for post-modifica-
tion inspection instruc-
tions.
6,000 flight cycles.-Repeat the detailed in-
spection of the unmodi-
fied areas of the tension
ties for cracks, in accor-
dance with the Accom-
plishment Instructions,
paragraph 3.B., Part 2.
No crack found during in-
spection in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 2.
-Before further flight.Contact Boeing for repair
instructions, and do the
repair.
Any crack found during in-
spection in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 2. (a) 6,000 flight cycles.-Repeat the detailed in-spection of the unmodi-
fied areas of the tension
ties for cracks, in accor-
dance with the Accom-
plishment Instructions,
paragraph 3.B., Part 2.
Contact Boeing for
repeat interval.
-Repeat the inspection of
the modified areas of the
tension tie and frame
structure in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 3. Contact
Boeing for post-modifica-
tion inspection instruc-
tions.
No discrepancy found dur-
ing post-modification in-
spection in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 3.
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Table 1: Tension Tie and Frame - Modification and Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact Boeing for repair
instructions, and do the
repair.
Any discrepancy found
during post-modification in-
spection in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 3. (a)
Contact Boeing for
repeat interval.
-Repeat the inspection of
the modified areas of the
tension tie and frame
structure in accordance
with the Accomplishment
Instructions, paragraph
3.B., Part 3. Contact
Boeing for post-modifica-
tion inspection instruc-
tions.
(a) Do all of the actions specified for this condition.
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 Seattle Aircraft
Certification Office (ACO) approves the accomplishment of the modification, post modification inspection
and corrective action with the corresponding compliance times specified in Table 1, under paragraph
1.E.,"Compliance," of Service Bulletin 747-53A2605, Revision 1, as an alternative method of compliance
(AMOC) to the inspections and corrective action required by paragraphs (h), (i), and (j) of AD 2004-07-22
R1, for the inspection of Structural Significant Item (SSI) F-19A of the Supplemental Structural Inspection
Document (SSID) D6-35022, Revision G. This AMOC only applies to the areas inspected by this service
bulletin. When this service bulletin specifies contacting Boeing for repair instructions, the repair
instructions must be approved by the FAA in accordance with paragraph (l) of the AD. All provisions
of AD 2004-07-22 R1 that are not specifically referenced in this paragraph remain fully applicable and
must be complied with.
In addition, the Manager of the Seattle ACO approves the accomplishment of the modification,
inspections, corrective and related investigative actions with the corresponding compliance times
specified in Table 1, under paragraph 1.E., "Compliance," of Service Bulletin 747-53A2605 Revision
1 as an AMOC to the inspections, corrective and related investigative actions with the corresponding
compliance times specified under paragraph 1.E., "Compliance," of Service Bulletin 747-53-2502, dated
April 21, 2005, required by paragraph (f) of AD 2006-01-07. When this service bulletin specifies
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contacting Boeing for repair instructions, the repair instructions must be approved by the FAA in
accordance with paragraph (g) of the AD. All provisions of AD 2006-01-07 that are not specifically
referenced in this paragraph, including but not limited to repeat inspections in accordance with paragraph
(f) until the modification in accordance with Service Bulletin 747-53A2605 Revision 1 is installed, remain
fully applicable and must be complied with.
In addition, the Manager of the Seattle ACO approves the accomplishment of the modification,
inspections and repair with the corresponding compliance times specified in Table 1, under paragraph
1.E., "Compliance," of Service Bulletin 747-53A2605 Revision 1 as an AMOC to the inspections, repair
and modification with the corresponding compliance times required by paragraphs A. and B. of AD
84-19-01. When this service bulletin specifies contacting Boeing for repair instructions, the repair
instructions must be approved by the FAA in accordance with paragraph C. of the AD. All provisions
of AD 84-19-01 that are not specifically referenced in this paragraph, including but not limited to repeat
inspections in accordance with paragraphs A. and B. until the modification in accordance with Service
Bulletin 747-53A2605 Revision 1 is installed, remain fully applicable and must be complied with.
In addition, the Manager of the Seattle ACO approves the accomplishment of the modification,
inspections and repair with the corresponding compliance times specified in Table 1, under paragraph
1.E., "Compliance," of Service Bulletin 747-53A2605 Revision 1 as an AMOC to the inspections, repair
and modification with the corresponding compliance times required by paragraphs (a) and (b) of AD
94-13-06. When this service bulletin specifies contacting Boeing for repair instructions, the repair
instructions must he approved by the FAA in accordance with paragraph (c) of the AD. All provisions
of AD 94-13-06 that are not specifically referenced in this paragraph, including but not limited to repeat
inspections in accordance with paragraphs (a) and (b) until the modification in accordance with Service
Bulletin 747-53A2605 Revision 1 is installed, remain fully applicable and must be complied with.
G. Manpower
The table below shows an estimate of the task hours necessary to do the modification for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to inspect the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
6.0024.004Access
7.5030.004Restoration
13.5054.00TOTAL FOR EACH AIRPLANE
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Group 1-5, 8-9, 11-15:
Shear Panel Removal/Installation
Elapsed HoursTask HoursNumber of PersonsTask
5.0010.002Remove
5.0010.002Install
10.0020.00TOTAL FOR EACH AIRPLANE
Group 6-7:
Shear Panel Removal/Installation
Elapsed HoursTask HoursNumber of PersonsTask
5.0010.002Remove
5.0010.002Install
10.0020.00TOTAL FOR EACH AIRPLANE
Group 10:
Shear Panel Removal/Installation
Elapsed HoursTask HoursNumber of PersonsTask
5.0010.002Remove
5.0010.002Install
10.0020.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 720 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Remove
3.507.002Install
7.0014.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 740 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Remove
3.507.002Install
7.0014.00TOTAL FOR EACH AIRPLANE
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Group 1, 13:
STA 760 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.757.502Remove
3.757.502Install
7.5015.00TOTAL FOR EACH AIRPLANE
Group 2-3, 14:
STA 760 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.256.502Remove
3.256.502Install
6.5013.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 760 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.006.002Remove
3.006.002Install
6.0012.00TOTAL FOR EACH AIRPLANE
Group 1-2, 8, 11, 13-15:
STA 780 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Remove
3.507.002Install
7.0014.00TOTAL FOR EACH AIRPLANE
Group 3, 12:
STA 780 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.256.502Remove
3.256.502Install
6.5013.00TOTAL FOR EACH AIRPLANE
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Group 10:
STA 780 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
2.505.002Remove
2.505.002Install
5.0010.00TOTAL FOR EACH AIRPLANE
Group 1-5, 8-9, 11-15:
STA 800 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
3.256.502Remove
3.256.502Install
6.5013.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 800 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
2.505.002Remove
2.505.002Install
5.0010.00TOTAL FOR EACH AIRPLANE
Group 1-5, 9, 11-15:
STA 820 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.0026.002Remove
13.0026.002Install
26.0052.00TOTAL FOR EACH AIRPLANE
Group 8, 10:
STA 820 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.7527.502Remove
13.7527.502Install
27.5055.00TOTAL FOR EACH AIRPLANE
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Group 1-5, 9-15:
STA 840 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.0024.002Remove
12.0024.002Install
24.0048.00TOTAL FOR EACH AIRPLANE
Group 6-7:
STA 840 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
11.7523.502Remove
11.7523.502Install
23.5047.00TOTAL FOR EACH AIRPLANE
Group 8:
STA 840 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.0026.002Remove
13.0026.002Install
26.0052.00TOTAL FOR EACH AIRPLANE
Group 1-5, 8, 11-15:
STA 860 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.7527.502Remove
13.7527.502Install
27.5055.00TOTAL FOR EACH AIRPLANE
Group 6-7:
STA 860 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.0026.002Remove
13.0026.002Install
26.0052.00TOTAL FOR EACH AIRPLANE
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Group 9:
STA 860 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.5027.002Remove
13.5027.002Install
27.0054.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 860 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.7525.502Remove
12.7525.502Install
25.5051.00TOTAL FOR EACH AIRPLANE
Group 1-9, 11-15:
STA 880 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
14.0028.002Remove
14.0028.002Install
28.0056.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 880 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.5025.002Remove
12.5025.002Install
25.0050.00TOTAL FOR EACH AIRPLANE
Group 1-4, 6, 11-15:
STA 900 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.0026.002Remove
13.0026.002Install
26.0052.00TOTAL FOR EACH AIRPLANE
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Group 5, 7:
STA 900 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.2524.502Remove
12.2524.502Install
24.5049.00TOTAL FOR EACH AIRPLANE
Group 8:
STA 900 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.7525.502Remove
12.7525.502Install
25.5051.00TOTAL FOR EACH AIRPLANE
Group 9-10:
STA 900 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.0024.002Remove
12.0024.002Install
24.0048.00TOTAL FOR EACH AIRPLANE
STA 920 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
12.5025.002Remove
12.5025.002Install
25.0050.00TOTAL FOR EACH AIRPLANE
Group 1-2, 11:
STA 940 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
14.2528.502Remove
14.2528.502Install
28.5057.00TOTAL FOR EACH AIRPLANE
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Group 3-4, 6, 12:
STA 940 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
14.5029.002Remove
14.5029.002Install
29.0058.00TOTAL FOR EACH AIRPLANE
Group 5, 7, 9:
STA 940 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
16.0032.002Remove
16.0032.002Install
32.0064.00TOTAL FOR EACH AIRPLANE
Group 8:
STA 940 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
14.0028.002Remove
14.0028.002Install
28.0056.00TOTAL FOR EACH AIRPLANE
Group 10:
STA 940 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
16.2532.502Remove
16.2532.502Install
32.5065.00TOTAL FOR EACH AIRPLANE
Group 13-15:
STA 940 Left ,Right Side, and Center Modification
Elapsed HoursTask HoursNumber of PersonsTask
13.0026.002Remove
13.0026.002Install
26.0052.00TOTAL FOR EACH AIRPLANE
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H. Weight and Balance Changes
Weight and Balance Changes data will be included in a future revision of this service bulletin.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. 747-100/200/300 Aircraft Maintenance Manual (AMM) 24-22-00, 25-21-04, 25-22-01, and
25-25-01.
b. 747-400 Aircraft Maintenance Manual (AMM) 24-22-00, 25-21-04, 25-22-01, and 25-25-01.
c. 747-100/200/300 Structural Repair Manual (SRM) 51-10-01, 51-30-09, and 53-11-21.
d. 747-400F Structural Repair Manual (SRM) 51-10-02, 51-40-09, 53-20-07.
e. 747 Non-Destructive Testing (NDT) Manual, Part 6, Chapter 51-00-00, Figure 1, 11, or 16.
f. Federal Aviation Administration (FAA) Airworthiness Directives 2004-07-22 R1 and 2006-01-07.
g. Boeing Service Related Problem (SRP) 747-53-0200.
h. Boeing Service Letter 747-SL-53-088B.
i. Standard Overhaul Practices Manual (SOPM) 20-41-01 and 20-41-05.
j. Engineering Change Memo PRR-85901-68RS.
2. Data supplied with this Service Bulletin:
a. Drawings:
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ADCNDCN/REVSheetTitleDrawing No
--1TOP KIT - FRAME AND TENSION TIE
MODIFICATION, STA 720 - STA 940
142U0100
--10
--11
--12
--13
--14
--2
--3
--4
--5
--6
--7
--9
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ADCNDCN/REVSheetTitleDrawing No
--1KIT - FRAME MODIFICATION, STA 820 -
STA 940
142U0101
--10
--11
--12
--13
--14
--15
--16
--17
--18
--19
--2
--20
--21
--22
--23
--24
--3
--4
--5
--6
--7
--8
--9
-BPSDLKIT - FRAME MODIFICATION, STA 820 -
STA 940
142U0101#DL
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ADCNDCN/REVSheetTitleDrawing No
--1KIT - TENSION TIE MODIFICATION, STA
720 - STA 940
142U0102
-A10
-A11
-A12
-A13
-A14
-A15
-A16
-A17
-A18
-A19
-A2
-A20
-A21
-A22
-A23
-A24
-A25
-A26
-A27
-A28
-A29
-A3
-A30
-A31
-A32
--33
--34
--35
-A4
-A5
-A6
-A7
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ADCNDCN/REVSheetTitleDrawing No
8- A
-A9
--PSDLKIT - TENSION TIE MODIFICATION, STA
720 - STA 940
142U0102#DL
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications
Chapter-SectionPublication
53-11747-100/200/300 Structural Repair Manual
53-20747-400F Structural Repair Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane, as shown
below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.
More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the
date Boeing gets the purchase order.
Unit Price thru De-
cember 31, 2011
ROLT
(Weeks)
QTYDateNameKit Number
$635,004.005718/26/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1001
634,277.0057-(a)TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1002
655,323.005718/28/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1003
623,027.005718/31/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1004
623,719.005719/03/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1005
535,131.005719/04/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1006
535,823.005719/08/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1007
645,067.005719/10/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1008
623,537.0057-(a)TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1009
658,423.0057-(a)TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1010
618,575.005719/11/09TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1011
639,219.0057-(a)TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-1012
18,657.0057-(a)TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-2001
21,288.0057-(a)TOP KIT - TENSION TIE AND
FRAME MODIFICATION
142U0100-2002
(a) Contact Boeing Spares for price and availability.
NOTE: Due to the limited number of kits available and the long ROLT, Boeing recommends that
operators submit purchase orders 18 months in advance of performing the modification.
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The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that
follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle,
Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the inspection or modification procedures given in this
service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
NOTE: The top kits shown in the table that follows and the items shown in Paragraph 2.C.2.,
Parts and Materials Supplied by the Operator, are necessary for each airplane.
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Top KitGroup(s)
142U0100-1001 and 142U0100-20021
142U0100-1002 and 142U0100-20022
142U0100-10033
142U0100-10044
142U0100-10055
142U0100-10066
142U0100-10077
142U0100-10088
142U0100-10099
142U0100-101010
142U0100-1011 and 142U0100-200211
142U0100-101212
142U0100-1001 and 142U0100-200113
142U0100-1002 and 142U0100-200114
142U0100-1011 and 142U0100-200115
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Group 1, 13:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1001
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODI-
FICATION, STA 760
1142U0102-203
KIT - TENSION TIE MODI-
FICATION, STA 780
1142U0102-207
KIT - TENSION TIE MODI-
FICATION, STA 800
1142U0102-210
KIT - TENSION TIE MODI-
FICATION, STA 820
1142U0102-212
KIT - TENSION TIE MODI-
FICATION, STA 840
1142U0102-214
KIT - TENSION TIE MODI-
FICATION, STA 860
1142U0102-217
KIT - TENSION TIE MODI-
FICATION, STA 880
1142U0102-220
KIT - TENSION TIE MODI-
FICATION, STA 900
1142U0102-222
KIT - TENSION TIE MODI-
FICATION, STA 920
1142U0102-225
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
39 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 40

Group 2, 14:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1002
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODIFI-
CATION, STA 760
1142U0102-204
KIT - TENSION TIE MODIFI-
CATION, STA 780
1142U0102-207
KIT - TENSION TIE MODIFI-
CATION, STA 800
1142U0102-210
KIT - TENSION TIE MODIFI-
CATION, STA 820
1142U0102-212
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-214
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-217
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-222
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-225
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
40 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 41

Group 3:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1003
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODIFI-
CATION, STA 760
1142U0102-205
KIT - TENSION TIE MODIFI-
CATION, STA 780
1142U0102-208
KIT - TENSION TIE MODIFI-
CATION, STA 800
1142U0102-210
KIT - TENSION TIE MODIFI-
CATION, STA 820
1142U0102-212
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-214
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-217
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-222
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-225
KIT - TENSION TIE MODIFI-
CATION, STA 940
1142U0102-229
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
41 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 42

Group 4:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1004
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODIFI-
CATION, STA 800
1142U0102-210
KIT - TENSION TIE MODIFI-
CATION, STA 820
1142U0102-212
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-214
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-217
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-222
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-225
KIT - TENSION TIE MODIFI-
CATION, STA 940
1142U0102-229
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
42 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 43

Group 5:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1005
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-125
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-126
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-127
KIT - TENSION TIE MODIFI-
CATION, STA 800
1142U0102-210
KIT - TENSION TIE MODIFI-
CATION, STA 820
1142U0102-212
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-214
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-217
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-223
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-226
KIT - TENSION TIE MODIFI-
CATION, STA 940
1142U0102-230
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
43 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 44

Group 6:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1006
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-215
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-218
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-222
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-225
KIT - TENSION TIE MODIFI-
CATION, STA 940
1142U0102-229
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-302
Group 7:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1007
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
44 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 45

Group 7:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1007
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-125
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-126
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-127
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-215
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-218
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-223
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-226
KIT - TENSION TIE MODIFI-
CATION, STA 940
1142U0102-230
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-302
Group 8:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1008
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-102
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-105
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-108
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
45 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 46

Group 8:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1008
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-114
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODIFI-
CATION, STA 780
1142U0102-207
KIT - TENSION TIE MODIFI-
CATION, STA 800
1142U0102-210
KIT - TENSION TIE MODIFI-
CATION, STA 820
1142U0102-212
KIT - TENSION TIE MODIFI-
CATION, STA 840
1142U0102-214
KIT - TENSION TIE MODIFI-
CATION, STA 860
1142U0102-217
KIT - TENSION TIE MODIFI-
CATION, STA 880
1142U0102-220
KIT - TENSION TIE MODIFI-
CATION, STA 900
1142U0102-222
KIT - TENSION TIE MODIFI-
CATION, STA 920
1142U0102-225
KIT - TENSION TIE MODIFI-
CATION, STA 940
1142U0102-228
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
Group 9:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1009
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
46 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 47

Group 9:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1009
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-109
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-115
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-119
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-123
KIT - TENSION TIE MODI-
FICATION, STA 800
1142U0102-210
KIT - TENSION TIE MODI-
FICATION, STA 820
1142U0102-212
KIT - TENSION TIE MODI-
FICATION, STA 840
1142U0102-214
KIT - TENSION TIE MODI-
FICATION, STA 860
1142U0102-217
KIT - TENSION TIE MODI-
FICATION, STA 880
1142U0102-220
KIT - TENSION TIE MODI-
FICATION, STA 900
1142U0102-223
KIT - TENSION TIE MODI-
FICATION, STA 920
1142U0102-226
KIT - TENSION TIE MODI-
FICATION, STA 940
1142U0102-230
KIT - SHEAR PANEL INSTL
- TENSION TIE MODIFICA-
TION
1142U0102-301
Group 10:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1010
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-103
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
47 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 48

Group 10:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1010
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-106
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-110
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-112
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-116
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-120
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-124
KIT - TENSION TIE MODI-
FICATION, STA 720
1142U0102-201
KIT - TENSION TIE MODI-
FICATION, STA 740
1142U0102-202
KIT - TENSION TIE MODI-
FICATION, STA 760
1142U0102-206
KIT - TENSION TIE MODI-
FICATION, STA 780
1142U0102-209
KIT - TENSION TIE MODI-
FICATION, STA 800
1142U0102-211
KIT - TENSION TIE MODI-
FICATION, STA 820
1142U0102-213
KIT - TENSION TIE MODI-
FICATION, STA 840
1142U0102-216
KIT - TENSION TIE MODI-
FICATION, STA 860
1142U0102-219
KIT - TENSION TIE MODI-
FICATION, STA 880
1142U0102-221
KIT - TENSION TIE MODI-
FICATION, STA 900
1142U0102-224
KIT - TENSION TIE MODI-
FICATION, STA 920
1142U0102-227
KIT - TENSION TIE MODI-
FICATION, STA 940
1142U0102-231
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
48 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 49

Group 10:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1010
KIT - SHEAR PANEL IN-
STL - TENSION TIE MODI-
FICATION
1142U0102-303
Group 11, 15:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1011
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODI-
FICATION, STA 780
1142U0102-207
KIT - TENSION TIE MODI-
FICATION, STA 800
1142U0102-210
KIT - TENSION TIE MODI-
FICATION, STA 820
1142U0102-212
KIT - TENSION TIE MODI-
FICATION, STA 840
1142U0102-214
KIT - TENSION TIE MODI-
FICATION, STA 860
1142U0102-217
KIT - TENSION TIE MODI-
FICATION, STA 880
1142U0102-220
KIT - TENSION TIE MODI-
FICATION, STA 900
1142U0102-222
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
49 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 50

Group 11, 15:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1011
KIT - TENSION TIE MODI-
FICATION, STA 920
1142U0102-225
KIT - SHEAR PANEL IN-
STL - TENSION TIE MOD-
IFICATION
1142U0102-301
Group 12:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1012
KIT - FRAME MODIFICA-
TION, STA 820
1142U0101-101
KIT - FRAME MODIFICA-
TION, STA 840
1142U0101-104
KIT - FRAME MODIFICA-
TION, STA 860
1142U0101-107
KIT - FRAME MODIFICA-
TION, STA 880
1142U0101-111
KIT - FRAME MODIFICA-
TION, STA 900
1142U0101-113
KIT - FRAME MODIFICA-
TION, STA 920
1142U0101-117
KIT - FRAME MODIFICA-
TION, STA 940
1142U0101-121
KIT - TENSION TIE MODI-
FICATION, STA 780
1142U0102-208
KIT - TENSION TIE MODI-
FICATION, STA 800
1142U0102-210
KIT - TENSION TIE MODI-
FICATION, STA 820
1142U0102-212
KIT - TENSION TIE MODI-
FICATION, STA 840
1142U0102-214
KIT - TENSION TIE MODI-
FICATION, STA 860
1142U0102-217
KIT - TENSION TIE MODI-
FICATION, STA 880
1142U0102-220
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
50 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 51

Group 12:
Kit 142U0100
NotesExisting Part NumberNameQTYNew Part Number
-1012
KIT - TENSION TIE MODI-
FICATION, STA 900
1142U0102-222
KIT - TENSION TIE MODI-
FICATION, STA 920
1142U0102-225
KIT - TENSION TIE MODI-
FICATION, STA 940
1142U0102-229
KIT - SHEAR PANEL IN-
STL - TENSION TIE MODI-
FICATION
1142U0102-301
Group 13-15:
Kit 142U0100
NotesExisting Part
Number
NameQTYNew Part Number
-2001
KIT - TENSION TIE MODIFICATION,
STA 940
1142U0102-232
Group 1-2, 11:
Kit 142U0100
NotesExisting Part
Number
NameQTYNew Part Number
-2002
KIT - TENSION TIE MODIFICA-
TION, STA 940
1142U0102-233
Group 1-5, 9, 11-15:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-101
STRAP2142U0106-11
STRAP2142U0106-19
STRAP2142U0106-21
FRAME SEGMENT1142U0107-23
FRAME SEGMENT1142U0107-24
TRIPLER1142U0107-27
TRIPLER1142U0107-28
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
51 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 52

Group 1-5, 9, 11-15:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-101
DOUBLER1142U0107-29
DOUBLER1142U0107-30
STIFFENER2142U0107-55
STRINGER CLIP TEE2142U0108-11
STRINGER CLIP TEE2142U0108-12
SHEAR TIE TEE, S-11 TO S-121142U0108-47
SHEAR TIE TEE, S-11 TO S-121142U0108-48
SHEAR TIE TEE, S-10A TO S-112142U0108-49
SHEAR TIE TEE, S-10 TO S-10A2142U0108-50
SHEAR TIE TEE, S-9 TO S-102142U0108-51
SHEAR TIE, S-8 TO S-92142U0108-53
CHORD SPLICE - UPPER2142U0108-54
CHORD SEGMENT1142U0108-55
CHORD SEGMENT1142U0108-56
CHORD SPLICE - LOWER2142U0108-115
STIFFENER1142U0108-117
STIFFENER1142U0108-118
STIFFENER2142U0108-119
STRINGER CLIP TEE2144U0064-6
STRINGER CLIP TEE2144U0064-7
STRINGER CLIP TEE8144U0064-8
STRINGER CLIP TEE8144U0064-9
INSULATOR269B41412-3
BRACKET, ANGLE2BACB2D018B0F0
BOLT, 100 DEG HEX DR88BACB30NW6K5Y
BOLT, 100 DEG HEX DR26BACB30NW6K6X
BOLT, PROTRUDING HD139BACB30NX6K3
BOLT, PROTRUDING HD4BACB30NX6K3X
BOLT, PROTRUDING HD48BACB30NX6K3Y
BOLT, PROTRUDING HD238BACB30NX6K4
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
52 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 53

Group 1-5, 9, 11-15:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-101
BOLT, PROTRUDING HD31BACB30NX6K4X
BOLT, PROTRUDING HD27BACB30NX6K4Y
BOLT201BACB30NX6K5
BOLT, PROTRUDING HD2BACB30NX6K5X
BOLT, PROTRUDING HD12BACB30NX6K5Y
BOLT40BACB30NX6K6
HI-LOK46BACB30NX6K7
BOLT, PROTRUDING HD18BACB30NX6K7X
BOLT, PROTRUDING HD112BACB30NX6K8
BOLT, PROTRUDING HD13BACB30NX6K8X
BOLT, PROTRUDING HD2BACB30NX6K9X
COLLAR83BACC30AC6
COLLAR840BACC30BH6
COLLAR26BACC30M6
COLLAR88BACC30R6
RADIUS FILLER4BACF3H05JF008HN
FILLER, TAPERED8BACF3T01B10-40
NUT STANDOFF2BACN10TL3A12
RIVET, UNIVERSAL HD2BACR15BB12AD8C
RIVETS4BACR15BB4AD5C
RIVET4BACR15BB4AD6C
RIVET, UNIVERSAL HD26BACR15BB6AD4C
RIVET, UNIVERSAL HD2BACR15BB8AD6C
RIVET26BACR15GF6D5
SHIM,LAMINATED4BACS40R005C005F
SHIM, LAMINATED4BACS40R008B035F
SHIM, LAMINATED4BACS40R008B038F
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
53 of 158
BOEING SERVICE BULLETIN 747-53A2605
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### Page 54

Group 8:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-102
STRAP2142U0106-23
STRAP2142U0106-25
STRAP2142U0106-27
FRAME SEGMENT1142U0107-23
FRAME SEGMENT1142U0107-24
DOUBLER1142U0107-25
DOUBLER1142U0107-26
TRIPLER1142U0107-27
TRIPLER1142U0107-28
STIFFENER2142U0107-55
STRINGER CLIP TEE4142U0108-11
STRINGER CLIP TEE4142U0108-12
SHEAR TIE TEE, S-11 TO S-121142U0108-47
SHEAR TIE TEE, S-11 TO S-121142U0108-48
SHEAR TIE TEE, S-10A TO S-112142U0108-49
SHEAR TIE TEE, S-10 TO S-10A2142U0108-50
SHEAR TIE TEE, S-9 TO S-102142U0108-51
SHEAR TIE, S-8 TO S-92142U0108-53
CHORD SPLICE - UPPER2142U0108-54
CHORD SEGMENT1142U0108-55
CHORD SEGMENT1142U0108-56
CHORD SPLICE - LOWER2142U0108-115
STIFFENER1142U0108-117
STIFFENER1142U0108-118
STIFFENER2142U0108-119
STRINGER CLIP TEE2144U0064-6
STRINGER CLIP TEE2144U0064-7
STRINGER CLIP TEE8144U0064-8
STRINGER CLIP TEE8144U0064-9
BRACKET, ANGLE2BACB2D016B0F0
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
54 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 55

Group 8:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-102
BOLT, 100 DEG HEX DR88BACB30NW6K5Y
BOLT, PROTRUDING HD113BACB30NX6K3
BOLT, PROTRUDING HD29BACB30NX6K3X
BOLT, PROTRUDING HD136BACB30NX6K3Y
BOLT, PROTRUDING HD222BACB30NX6K4
BOLT, PROTRUDING HD20BACB30NX6K4X
BOLT, PROTRUDING HD86BACB30NX6K4Y
BOLT196BACB30NX6K5
BOLT, PROTRUDING HD6BACB30NX6K5X
BOLT, PROTRUDING HD22BACB30NX6K5Y
BOLT40BACB30NX6K6
BOLT, PROTRUDING HD6BACB30NX6K6Y
HI-LOK42BACB30NX6K7
BOLT, PROTRUDING HD24BACB30NX6K7X
BOLT, PROTRUDING HD4BACB30NX6K7Y
BOLT, PROTRUDING HD103BACB30NX6K8
BOLT, PROTRUDING HD6BACB30NX6K8X
BOLT, PROTRUDING HD6BACB30NX6K8Y
BOLT, PROTRUDING HD2BACB30NX6K9X
COLLAR262BACC30AC6
COLLAR775BACC30BH6
COLLAR26BACC30M6
COLLAR88BACC30R6
RADIUS FILLER2BACF3H05JF008HN
FILLER, TAPERED8BACF3T01B10-40
SPACER PLATE NUT2BACN10TL3A6
RIVET, UNIVERSAL HD2BACR15BB12AD8C
RIVETS4BACR15BB4AD5C
RIVET, UNIVERSAL HD26BACR15BB6AD4C
RIVET, UNIVERSAL HD2BACR15BB8AD6C
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
55 of 158
BOEING SERVICE BULLETIN 747-53A2605
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### Page 56

Group 8:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-102
RIVET26BACR15GF6D5
SHIM,LAMINATED4BACS40R005C005F
SHIM, LAMINATED4BACS40R008B035F
SHIM, LAMINATED4BACS40R008B038F
Group 10:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-103
STRAP2142U0106-3
STRAP2142U0106-27
STRAP2142U0106-41
FRAME SEGMENT1142U0107-23
FRAME SEGMENT1142U0107-24
DOUBLER1142U0107-25
DOUBLER1142U0107-26
TRIPLER1142U0107-27
TRIPLER1142U0107-28
STIFFENER4142U0107-55
STRINGER CLIP TEE4142U0108-11
STRINGER CLIP TEE4142U0108-12
SHEAR TIE TEE, S-11 TO S-121142U0108-47
SHEAR TIE TEE, S-11 TO S-121142U0108-48
SHEAR TIE TEE, S-10A TO S-112142U0108-49
SHEAR TIE TEE, S-10 TO S-10A2142U0108-50
SHEAR TIE TEE, S-9 TO S-102142U0108-51
SHEAR TIE TEE, S-8 TO S-92142U0108-52
CHORD SPLICE - UPPER2142U0108-54
CHORD SEGMENT1142U0108-77
CHORD SEGMENT1142U0108-78
CHORD SPLICE - LOWER2142U0108-115
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
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56 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 57

Group 10:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-103
STRINGER CLIP TEE10144U0064-6
STRINGER CLIP TEE10144U0064-7
BOLT, 100 DEG HEX DR26BACB30NW6K6X
BOLT, 100 DEG HEX DR106BACB30NW6K6Y
BOLT, PROTRUDING HD189BACB30NX6K3
BOLT, PROTRUDING HD29BACB30NX6K3X
BOLT, PROTRUDING HD29BACB30NX6K3Y
BOLT, PROTRUDING HD209BACB30NX6K4
BOLT, PROTRUDING HD53BACB30NX6K4X
BOLT, PROTRUDING HD62BACB30NX6K4Y
BOLT196BACB30NX6K5
BOLT, PROTRUDING HD20BACB30NX6K5X
BOLT, PROTRUDING HD2BACB30NX6K5Y
BOLT53BACB30NX6K6
BOLT, PROTRUDING HD6BACB30NX6K6Y
HI-LOK42BACB30NX6K7
BOLT, PROTRUDING HD26BACB30NX6K7X
BOLT, PROTRUDING HD110BACB30NX6K8
BOLT, PROTRUDING HD13BACB30NX6K8X
BOLT, PROTRUDING HD2BACB30NX6K9X
COLLAR100BACC30AC6
COLLAR941BACC30BH6
COLLAR26BACC30M6
COLLAR106BACC30R6
FILLER, TAPERED8BACF3T01B10-40
RIVET, UNIVERSAL HD2BACR15BB12AD8C
RIVET, UNIVERSAL HD31BACR15BB6AD4C
RIVET, UNIVERSAL HD2BACR15BB8AD6C
RIVET31BACR15GF6D5
SHIM,LAMINATED4BACS40R005C005F
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
57 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 58

Group 10:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-103
SHIM, LAMINATED4BACS40R008B035F
SHIM, LAMINATED4BACS40R008B038F
Group 1-7, 9, 11-15:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-104
STRAP2142U0106-15
STRAP2142U0106-29
STRAP2142U0106-31
STIFFENER4142U0107-39
FRAME SEGMENT1142U0107-41
FRAME SEGMENT1142U0107-42
DOUBLER1142U0107-43
DOUBLER1142U0107-44
TRIPLER1142U0107-45
TRIPLER1142U0107-46
STRINGER CLIP TEE2142U0108-11
STRINGER CLIP TEE2142U0108-12
SHEAR TIE, S-8 TO S-92142U0108-79
SHEAR TIE TEE, S-9 TO S-102142U0108-81
SHEAR TIE TEE, S-10 TO S-
10A / S-10A TO S-11
4142U0108-83
SHEAR TIE TEE, S-11 TO S-121142U0108-85
SHEAR TIE TEE, S-11 TO S-121142U0108-86
CHORD SPLICE - UPPER2142U0108-87
CHORD SPLICE - LOWER2142U0108-89
CHORD SEGMENT1142U0108-91
CHORD SEGMENT1142U0108-92
STRINGER CLIP TEE10144U0064-8
STRINGER CLIP TEE10144U0064-9
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
58 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 59

Group 1-7, 9, 11-15:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-104
INSULATOR269B41412-3
BRACKET, ANGLE2BACB2D018B0F0
BOLT, 100 DEG HEX DR88BACB30NW6K5Y
BOLT, 100 DEG HEX DR27BACB30NW6K6X
BOLT, 100 DEG HEX DR2BACB30NW6K7Y
BOLT, PROTRUDING HD110BACB30NX6K3
BOLT, PROTRUDING HD4BACB30NX6K3X
BOLT, PROTRUDING HD29BACB30NX6K3Y
BOLT, PROTRUDING HD216BACB30NX6K4
BOLT, PROTRUDING HD18BACB30NX6K4X
BOLT, PROTRUDING HD20BACB30NX6K4Y
BOLT190BACB30NX6K5
BOLT, PROTRUDING HD2BACB30NX6K5X
BOLT, PROTRUDING HD11BACB30NX6K5Y
BOLT40BACB30NX6K6
BOLT, PROTRUDING HD4BACB30NX6K6X
HI-LOK47BACB30NX6K7
BOLT, PROTRUDING HD14BACB30NX6K7X
BOLT, PROTRUDING HD104BACB30NX6K8
BOLT, PROTRUDING HD6BACB30NX6K8X
BOLT, PROTRUDING HD2BACB30NX6K9X
COLLAR60BACC30AC6
COLLAR748BACC30BH6
COLLAR27BACC30M6
COLLAR90BACC30R6
FILLER, TAPERED8BACF3T01B10-40
NUT STANDOFF2BACN10TL3A12
RIVETS4BACR15BB4AD5C
RIVET4BACR15BB4AD6C
RIVET, UNIVERSAL HD27BACR15BB6AD4C
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
59 of 158
BOEING SERVICE BULLETIN 747-53A2605
ALERTALERT

### Page 60

Group 1-7, 9, 11-15:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-104
RIVET27BACR15GF6D5
SHIM,LAMINATED4BACS40R005C005F
SHIM,LAMINATED4BACS40R007B034F
SHIM, LAMINATED4BACS40R008B038F
Group 8:
Kit 142U0101
NotesExisting Part
Number
NameQTYNew Part Number
-105
STRAP2142U0106-17
STRAP2142U0106-29
STRAP2142U0106-31
STIFFENER4142U0107-39
FRAME SEGMENT1142U0107-41
FRAME SEGMENT1142U0107-42
TRIPLER1142U0107-45
TRIPLER1142U0107-46
DOUBLER1142U0107-47
DOUBLER1142U0107-48
STRINGER CLIP TEE4142U0108-11
STRINGER CLIP TEE4142U0108-12
SHEAR TIE, S-8 TO S-92142U0108-79
SHEAR TIE TEE, S-9 TO S-102142U0108-81
SHEAR TIE TEE, S-10 TO S-10A
/ S-10A TO S-11
4142U0108-83
SHEAR TIE TEE, S-11 TO S-121142U0108-85
SHEAR TIE TEE, S-11 TO S-121142U0108-86
CHORD SPLICE - UPPER2142U0108-87
CHORD SPLICE - LOWER2142U0108-89
CHORD SEGMENT1142U0108-91
CHORD SEGMENT1142U0108-92
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 08, 2009
747-53A2605Revision 1: May 27, 2010
60 of 158
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