# Boeing Alert Service Bulletin 747-53A2562: Revision 3

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2014-0774; AD 2016-06-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 747-53A2562](https://openairdocs.org/service-documents/boeing/747-53a2562.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 747-53A2562-03
- Pages: 136
- PDF: https://openairdocs.org/files/sha256/77/d0/77d05bc77cf540334c87b1a694807ded98de91dcd53fe8220a3657168ed8c27a
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
Number: 747-53A2562
Original Issue: June 16, 2005
Revision 3: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener
Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2005 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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4.0

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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 ........................................ 2 2
B. Concurrent Requirements ...................................... 2 2
C. Reason ................................................ 2 2
D. Description .............................................. 2 4
E. Compliance .............................................. 2 5
F. Approval ............................................... 2 7
G. Manpower .............................................. 2 8
H. Weight and Balance Changes .................................... 2 9
I. Electrical Load Data ......................................... 2 9
J. References .............................................. 2 9
1. Existing Data: ......................................... 2 9
2. Data Supplied with this Service Bulletin: ........................... 3 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 1
K. Publications Affected ........................................ 3 1
L. Interchangeability and Intermixability of Parts ........................... 3 1
M. Software Accomplishment Summary ................................ 3 1
2. MATERIAL INFORMATION ........................................ 3 3
A. Material - Price and Availability ................................... 3 3
B. Industry Support Information .................................... 3 4
C. Parts Necessary for Each Airplane ................................. 3 4
1. Kits/Parts: ........................................... 3 4
2. Parts and Materials Supplied by the Operator: ........................ 6 2
3. Parts Modified and Reidentified: ............................... 6 4
4. Parts Removed and Not Replaced: .............................. 6 4
D. Parts Necessary to Change Spares ................................. 6 4
E. Special Tooling - Price and Availability ............................... 6 4
F. Special Tooling Necessary to do this Service Bulletin ....................... 6 4
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 5
A. GENERAL INFORMATION ..................................... 6 5
B. WORK INSTRUCTIONS ....................................... 6 7
FIGURE 1: THIS FIGURE IS DELETED .................................. 7 7
FIGURE 2: REMOVAL OF TOP PANEL [Group 1-3] ........................... 7 8
FIGURE 3: REMOVAL OF LEFT SIDE PANEL .............................. 8 1
FIGURE 4: INSTALLATION OF LEFT SIDE PANEL [Group 1-2, 4] ................... 8 4
FIGURE 5: REMOVAL OF RIGHT SIDE PANEL ............................. 8 7
FIGURE 6: INSTALLATION OF RIGHT SIDE PANEL [Group 1-2, 4] .................. 9 0
FIGURE 7: INSTALLATION OF LEFT SIDE PANEL [Group 3] ...................... 9 3
FIGURE 8: INSTALLATION OF RIGHT SIDE PANEL [Group 3] ..................... 9 7
FIGURE 9: INSTALLATION OF TOP PANEL [Group 1-2] ........................ 1 0 1
FIGURE 10: INSTALLATION OF TOP PANEL [Group 3] ......................... 1 0 4
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FIGURE 11: THIS FIGURE IS DELETED ................................. 1 0 7
FIGURE 12: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 260 BULKHEAD ....... 1 0 8
FIGURE 13: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 340 BULKHEAD ....... 1 1 1
FIGURE 14: REMOVAL OF TOP PANEL COMPONENTS [Group 4] .................. 1 1 3
FIGURE 15: INSTALLATION OF NEW TOP PANEL COMPONENTS [Group 4] ............ 1 1 6
FIGURE 16: RESTORATION AT NOSE WHEEL WELL STA 340 BULKHEAD ............. 1 1 9
FIGURE 17: RESTORATION AT NOSE WHEEL WELL STA 260 BULKHEAD ............. 1 2 1
FIGURE 18: POST MODIFICATION INSPECTION - SIDE PANEL WEB EXTERNAL DETAILED INSPECTION
................................................. 1 2 3
FIGURE 19: POST MODIFICATION INSPECTION - TOP PANEL WEB EXTERNAL DETAILED INSPECTION
................................................. 1 2 6
FIGURE 20: POST MODIFICATION INSPECTION - TOP AND SIDE PANEL STIFFENER INTERNAL
DETAILED AND HFEC INSPECTIONS ........................... 1 2 9
APPENDIX A: NOSE WHEEL WELL MODIFICATION - SUGGESTED SEQUENCE OF STEPS .... 1 3 2
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Commercial 
Airplanes
747
Service Bulletin
Revision Transmittal SheetNumber: 747-53A2562Original Issue: June 16, 2005
Revision 3: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener
Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
More work is necessary on airplanes changed as given in the original issue, Revision 1, or Revision 2 of this
service bulletin. Airplanes that were previously modified as given in this service bulletin will require the addition
of post modification inspections as identified in paragraph 1.E., Compliance, but no additional modification work
is required.
Airplanes RL403, RL655, RM887, RL752, and RL420 were added to Group 4 of this service bulletin effectivity.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service bulletin.
REASON FOR REVISION
This revision is sent to add five airplanes to the effectivity of this service bulletin, and to add post modification
inspection instructions.
These sections were changed:
1. In the Summary: Updated the Background information, added Planning Data table, and updated the
Action section with post modification inspection requirement.
2. In paragraph 1.A., Effectivity: Added airplanes RL403, RL655, RM887, RL752, and RL420 to Group 4
and updated the Group/Configuration Table. Also, airplanes that have been modified to Boeing Converted
Freighter configuration as of the time of development of Revision 3 of this service bulletin have been
moved to Group 2.
3. In paragraph 1.C., Reason: Updated the background information, added reference to related service
letter and Fleet Team Digest articles, and added the reason for Revision 3.
4. In paragraph 1.D., Description: Added post modification inspection action, added "more work" statement
for Revision 3, and added maintenance zone information.
5. In paragraph 1.E., Compliance: Added compliance Tables 1 and 2 for nose wheel well modification.
Added Tables 3 and 4 for post modification inspections.
6. In paragraph 1.F., Approval: Added Alternative Method of Compliance (AMOC) and Method of
Compliance (MOC) statements related to AD 2006-22-15.
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7. In paragraph 1.H., Weight and Balance Changes: Added weight and moment changes resulting from
modification.
8. In paragraph 1.J.2., Data Supplied with this Service Bulletin: Updated list of drawings and parts lists
to be supplied with the service bulletin.
9. In paragraph 1.K., Publications Affected: Added statement for damage tolerance based inspections.
10. In paragraph 2.A., Material - Price and Availability: Added new 141U1192-53 top kit for Group 1 - 3
airplanes. Updated price and re-order lead time information for 141U1192-2 top kit.
11. In paragraph 2.C.1., Parts Necessary for Each Airplane: Added bill of material for 141U1192-53 top
kit. Updated footnotes in all tables.
12. In paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added supplemental parts that are
needed if a 141U1192-1 top kit is used for Group 1-3 airplanes.
13. In paragraph 3.A., General Information: Updated general notes.
14. In paragraph 3.B., Work Instructions: Revised PART 2 instructions to include a detailed inspection of
existing structure before installation of new nose wheel well panels. Added PART 6 and PART 7 for
post modification inspections.
15. In Figure 4: Added reference to correct left side panel kit for Group 4 airplanes.
16. In Figure 6: Added reference to correct right side panel kit for Group 4 airplanes.
17. Figures 18, 19, and 20: These new figures were added for post modification inspections.
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
June 16, 2005Original Issue:
July 28, 2005Revision 1:
May 31, 2007Revision 2:
July 11, 2013Revision 3:
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Commercial 
Airplanes
747
Service Bulletin
SummaryNumber: 747-53A2562Original Issue: June 16, 2005
Revision 3: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener
Replacement
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This Service Bulletin gives instruction for a modification to the nose wheel well top and side panels. This
modification makes the nose wheel well top and side panels more resistant to fatigue cracks in the areas that
must be inspected to satisfy requirements given in the FAA Airworthiness Directive AD 2006-22-15. This
modification can be done to permanently satisfy requirements related to this Airworthiness Directive, and terminate
inspections of Service Bulletin 747-53A2465.
Three operators have reported finding cracks in the nose wheel well side panel webs on four airplanes. The
cracks ranged from 1.5 inches to 14.5 inches in length. The airplanes on which these cracks were found had
between 15,900 and 32,018 flight cycles. In addition, a 17.5 inch crack was found in the side panel web of the
Boeing 747-400 fatigue test airplane, which had accumulated 58,890 pressure cycles.
One operator has also reported a 13 inch long crack in the nose wheel well top panel web of an airplane with
15,726 flight cycles.
Two operators have also reported finding cracks in the nose wheel well side panel stiffeners on two airplanes.
The cracks were between 12 and 13 inches in length and were found on airplanes with between 19,577 and
31,863 flight cycles.
As of the time of development of Revision 3 of this service bulletin, Boeing has received a total of 16 reports of
cracking in the nose wheel well top panel and side panel webs and/or stiffeners. One airplane lost pressurization
due to cracking in a nose wheel well side panel.
Boeing has determined that all the cracks were caused by fatigue. Furthermore, the nose wheel well top and
side panels have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD).
Although loss of pressurization due to cracks in the nose wheel well structure is not necessarily an airplane
safety concern, WFD could result in a depressurization event with damage significant enough to adversely affect
the structural integrity of the fuselage.
Accomplishment of this service bulletin will install new nose wheel well side and top panel structure, and will
eliminate the concern of WFD in the nose wheel well. For more information about WFD, refer to 747-SL-53-088.
The modification given in this service bulletin terminates the repetitive inspections given in Service Bulletin
747-53A2465.
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Boeing Structural Item Interim Advisory SIIA 747-129 is related to this Service Bulletin.
Boeing Service Related Problem (SRP) 747-SRP-53-0133 and 747-SRP-53-0231 are related to this Service
Bulletin.
Boeing Fleet Team Digest articles 747 FTD 53-04002 and 747 FTD 53-12006 are related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 85901-63RS)
Open the nose landing gear doors, and jack the airplane. Remove the nose landing gear, nose landing gear
doors, nose landing gear door actuator, passenger seats, floor covering, floor panels, and insulation as necessary
to get access to the upper, left, and right hand webs in the nose wheel well.
Group 1-3:
Replace the top panel web and the left and right side panel webs. Also, replace the horizontal stiffeners spanning
between the vertical beams, and the stiffeners common to the top panel.
Group 4:
Replace the left and right side panel webs. Also, replace the horizontal stiffeners spanning between the vertical
beams, and the stiffeners common to the top panel.
Install all parts removed for access at completion of the modification, and return airplane to a serviceable
condition.
Do post modification inspections (detailed and eddy current) at the times specified in paragraph 1.E., Compliance.
If any crack is found, contact Boeing for repair instructions and do the repair.
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EFFECTIVITY
747-100/-100B/-100B SUD/-200B/-200C/-200F/-300/-400/-400D/-400F/-SP/-SR airplanes. Refer to Paragraph
1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service bulletin.
Refer to Paragraph 1.E for compliance information.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes 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 747-53A2562
0000000000000
GROUP 1-3:
INSTALL NEW TOP PANEL
WEB STRUCTURE
STA
280
STA
400
STA
340
STA
400
BLO
GROUP 1-4:
INSTALL NEW SIDEWALL
WEB STRUCTURE - LEFT
UP  AND RIGHT SIDE
> FWD
INSIDE NOSE WHEEL WELL
LEFT SIDE SHOWN  D72410
RIGHT SIDE OPPOSITE
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Commercial 
Airplanes
747
Service Bulletin
Number: 747-53A2562
Original Issue: June 16, 2005
Revision 3: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener
Replacement
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplanes shown below. Refer to PRR 85901-63RS for data about
this change.
DESCRIPTIONCONFIGURATIONGROUP
747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400,
747-400D, 747SP, and 747SR airplanes, line numbers 1 through
1303, except line number 952 and airplanes modified by Boeing to
Special Freighter or Boeing Converted Freighter. These airplanes
do not have a nose cargo door.
-1
747-100, 747-200B, 747-300, 747-400, and 747SR airplanes, line
numbers 5 through 1188, that have been modified by Boeing to
Special Freighter or Boeing Converted Freighter configuration (prior
to December 14, 2012) . These airplanes do not have a nose cargo
door.
-2
747-400D airplane, line number 952.-3
747-200C, 747-200F, and 747-400F airplanes, line numbers 168
through 1314. These airplanes have a nose cargo door.
-4
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SP, 747SR
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GroupVariable Number
1RA001 - RA025
2RA026
1RA027 - RA028
2RA029
1RA030 - RA032
2RA033
1RA034
2RA101 - RA103
1RA104 - RA110
2RA111 - RA112
1RA113 - RA115
2RA161 - RA163
1RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA523
2RA524
1RA525 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631
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GroupVariable Number
2RA632
1RA633
2RA634 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
2RA901 - RA902
1RA903 - RA909
2RA910 - RA916
1RB001 - RB016
2RB041
1RB042
2RB043
1RB044
1RB071 - RB075
1RB101 - RB102
1RB411 - RB413
1RB421
1RB601 - RB603
2RB604 - RB605
1RB606
2RB607
1RB681 - RB695
2RB696
1RB697
1RB711
1RB721 - RB723
1RB741 - RB748
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GroupVariable Number
1RD001 - RD004
1RD021 - RD022
2RD041
1RD042
2RD043 - RD044
1RD045 - RD054
2RD055
1RD056 - RD059
1RD071 - RD072
1RD081
2RD082 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD141
2RD142
1RD143
2RD144
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD224
2RD225
1RD226
2RD227
1RD231 - RD232
2RD233 - RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
2RD301 - RD302
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GroupVariable Number
1RD311
1RD351 - RD357
2RD358
2RD361 - RD366
1RD381 - RD383
2RD411 - RD412
1RD413 - RD414
1RD421 - RD426
1RD431 - RD435
2RD441 - RD442
1RD451 - RD456
2RD461
1RD471 - RD475
1RD513 - RD519
1RD531 - RD533
2RD551
1RD561
1RD571
2RD581 - RD583
1RD591 - RD593
2RD601 - RD602
1RD603 - RD607
1RD621
2RD622 - RD623
2RD641 - RD643
1RD644 - RD645
2RD646
1RD647 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
2RD691
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GroupVariable Number
1RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751
2RD752
1RD753 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
1RG001 - RG009
1RG091
1RG095
1RG101 - RG104
1RG121 - RG126
1RG141 - RG142
1RG161 - RG164
1RG171 - RG174
1RG191 - RG193
1RG211 - RG213
1RG221 - RG222
1RH101 - RH102
1RH111 - RH112
1RH121 - RH122
4RJ131 - RJ133
4RJ151 - RJ152
4RJ301 - RJ303
4RJ321 - RJ322
4RJ331 - RJ333
4RL401 - RL403
4RL411 - RL420
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GroupVariable Number
4RL651 - RL655
4RL751 - RL752
1RM001 - RM007
1RM010 - RM013
1RM021 - RM024
1RM026 - RM029
1RM036 - RM045
1RM051 - RM052
1RM071
1RM081 - RM084
1RM091
1RM096 - RM097
1RM116 - RM117
1RM126 - RM127
2RM128
1RM129 - RM132
1RM136 - RM147
1RM156 - RM158
1RM166 - RM177
1RM191 - RM192
1RM231 - RM233
1RM241 - RM246
1RM261 - RM264
1RM316 - RM318
1RM331 - RM333
1RM341
1RM351 - RM355
1RM366 - RM367
1RM801 - RM803
1RM811 - RM813
4RM851 - RM858
4RM861 - RM862
4RM871 - RM876
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GroupVariable Number
4RM881 - RM887
4RM891 - RM899
4RM901 - RM905
4RM911
4RR001 - RR005
4RR021 - RR025
4RR031
4RR201 - RR206
4RR221 - RR226
4RR261 - RR267
4RR301 - RR310
4RR331 - RR332
4RR336
4RR341 - RR345
4RR361 - RR362
4RR421 - RR422
4RR431 - RR432
4RR441 - RR442
4RR451
4RR501 - RR504
4RR521 - RR522
4RR526
4RR531
4RR551 - RR556
4RR561
4RR566
4RR701
4RR721 - RR724
4RR746 - RR748
4RR851 - RR856
4RR861 - RR862
4RR951 - RR952
1RS001 - RS002
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GroupVariable Number
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
1RS711 - RS713
2RS721 - RS722
1RS731 - RS732
2RS741
1RS742
2RS743
1RS751 - RS752
1RS761
2RS762
2RS771
1RS781 - RS782
2RS786
1RT001 - RT014
2RT021 - RT022
2RT031 - RT033
1RT034 - RT035
1RT041 - RT047
2RT061
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GroupVariable Number
2RT071 - RT072
1RT073 - RT074
2RT075
1RT101 - RT103
1RT121
1RT131 - RT137
1RT151 - RT152
2RT161
1RT162 - RT163
2RT164
1RT165 - RT168
1RT401 - RT412
1RT431 - RT447
1RT451 - RT455
2RT456
1RT457 - RT460
2RT461
1RT462 - RT469
1RT471 - RT499
2RT501
1RT502 - RT505
2RT506 - RT510
1RT511 - RT512
2RT513
1RT514 - RT515
2RT516
1RT517
2RT518 - RT520
1RT521 - RT523
2RT524
1RT525
2RT526
1RT527
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GroupVariable Number
2RT528
1RT529
2RT530
1RT531 - RT535
1RT551 - RT568
1RT571
2RT572 - RT579
1RT580 - RT591
1RT601 - RT641
2RT642
1RT643 - RT653
2RT654 - RT657
1RT671 - RT673
1RT681 - RT682
2RT691 - RT692
1RT693 - RT699
1RT701 - RT704
1RT711 - RT717
1RT741 - RT750
2RT751 - RT752
1RT753 - RT757
1RT776 - RT777
2RT781 - RT782
1RT783 - RT784
1RT801 - RT803
1RT811 - RT814
1RT831 - RT836
2RT837
1RT861 - RT864
1RT876 - RT880
1RT931 - RT932
1RT945 - RT949
1RT951 - RT955
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GroupVariable Number
1RT966
2RT967
1RU001 - RU006
1RU016 - RU017
1RU031 - RU032
1RU051 - RU052
1RU059 - RU062
1RU081 - RU083
1RU101 - RU102
1RU121 - RU132
1RU801 - RU809
1RU831 - RU834
3RU835
1RU836 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This Service Bulletin gives instruction for a modification to the nose wheel well top and side panels.
This modification makes the nose wheel well top and side panels more resistant to fatigue cracks in
the areas that must be inspected to satisfy requirements given in the FAA Airworthiness Directive AD
2006-22-15. This modification can be done to permanently satisfy requirements related to this
Airworthiness Directive, and terminate inspections of Service Bulletin 747-53A2465.
Three operators have reported finding cracks in the nose wheel well side panel webs on four airplanes.
The cracks ranged from 1.5 inches to 14.5 inches in length. The airplanes on which these cracks were
found had between 15,900 and 32,018 flight cycles. In addition, a 17.5 inch crack was found in the
side panel web of the Boeing 747-400 fatigue test airplane, which had accumulated 58,890 pressure
cycles.
One operator has also reported a 13 inch long crack in the nose wheel well top panel web of an airplane
with 15,726 flight cycles.
Two operators have also reported finding cracks in the nose wheel well side panel stiffeners on two
airplanes. The cracks were between 12 and 13 inches in length and were found on airplanes with
between 19,577 and 31,863 flight cycles.
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As of the time of development of Revision 3 of this service bulletin, Boeing has received a total of 16
reports of cracking in the nose wheel well top panel and side panel webs and/or stiffeners. One airplane
lost pressurization due to cracking in a nose wheel well side panel.
Boeing has determined that all the cracks were caused by fatigue. Furthermore, the nose wheel well
top and side panels have been determined to be structure that is susceptible to Widespread Fatigue
Damage (WFD). Although loss of pressurization due to cracks in the nose wheel well structure is not
necessarily an airplane safety concern, WFD could result in a depressurization event with damage
significant enough to adversely affect the structural integrity of the fuselage.
Accomplishment of this service bulletin will install new nose wheel well side and top panel structure,
and will eliminate the concern of WFD in the nose wheel well. For more information about WFD, refer
to 747-SL-53-088.
The modification given in this service bulletin terminates the repetitive inspections given in Service
Bulletin 747-53A2465.
Boeing Structural Item Interim Advisory SIIA 747-129 is related to this Service Bulletin.
Boeing Service Related Problem (SRP) 747-SRP-53-0133 and 747-SRP-53-0231 are related to this
Service Bulletin.
Boeing Fleet Team Digest articles 747 FTD 53-04002 and 747 FTD 53-12006 are related to this service
bulletin.
Revision 1 is sent to provide revised engineering drawings. Sheets 1 through 7 of Drawing 141U1192
have all been changed and are included with this revision. In addition, Top Kit 141U1192-1 has been
revised. Updated parts list drawings for Top Kit 141U1192-1 and Subkits 141U1192-5, 141U1192-7,
141U1192-8, 141U1192-31, and 141U1192-33 are also included with this revision. New Subkit parts
lists drawings are included with this revision for new Subkits 141U1192-49 and 141U1192-50. Also, a
step has been added to the Accomplishment Instructions to specify a cabin pressure leak test after the
nose wheel well structure has been replaced. Airplanes modified by Boeing to the Special Freighter
configuration have been moved to new Group 2 in this revision. Modification instructions for Group 2
airplanes will be included in a future revision to this service bulletin. Group 3 and Figures 9, 10, and
11 have been added for airplane RU835 (line number 952), which has a unique modification
configuration.
Revision 2 is sent to add modification instructions for airplanes modified by Boeing to Special Freighter
configuration (Group 2), add modification instructions for airplanes with a nose cargo door (Group 4),
and to clarify access and restoration instructions. A detailed list of changes can be found in the Revision
Transmittal Sheet section of Revision 2.
NOTE: Because of common access, Boeing highly recommends, if applicable, that the modifications
specified in Service Bulletin 747-53A2293 'FUSELAGE - Nose Wheel Well - Body Structure
Reinforcement' be done at the same time as the modification specified in this service bulletin.
Revision 3 is sent to add five airplanes to the effectivity of this service bulletin, and to add post
modification inspection instructions. Other changes have also been made. A detailed list of changes
can be found in the Revision Transmittal Sheet section of Revision 3.
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D. Description
Open the nose landing gear doors, and jack the airplane. Remove the nose landing gear, nose landing
gear doors, nose landing gear door actuator, passenger seats, floor covering, floor panels, and insulation
as necessary to get access to the upper, left, and right hand webs in the nose wheel well.
Group 1-3:
Replace the top panel web and the left and right side panel webs. Also, replace the horizontal stiffeners
spanning between the vertical beams, and the stiffeners common to the top panel.
Group 4:
Replace the left and right side panel webs. Also, replace the horizontal stiffeners spanning between
the vertical beams, and the stiffeners common to the top panel.
Install all parts removed for access at completion of the modification, and return airplane to a serviceable
condition.
Do post modification inspections (detailed and eddy current) at the times specified in paragraph 1.E.,
Compliance. If any crack is found, contact Boeing for repair instructions and do the repair.
Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this
service bulletin.
Revision 2 - No more work is necessary on airplanes changed as shown in the original issue or Revision
1 of this service bulletin.
Revision 3 - More work is necessary on airplanes changed as given in the original issue, Revision 1,
or Revision 2 of this service bulletin. Airplanes that were previously modified as given in this service
bulletin will require the addition of post modification inspections as identified in paragraph 1.E.,
Compliance, but no additional modification work is required.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
113, 114747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747-
400, 747-400D, 747SP, 747SR
Group 2:
Affected Maintenance Zones
ZoneModel
113, 114747-100, 747-200B, 747-300,
747-400, 747SR
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Group 3:
Affected Maintenance Zones
ZoneModel
113, 114747-400D
Group 4:
Affected Maintenance Zones
ZoneModel
113, 114747-200C, 747-200F, 747-400F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service
bulletin.
The post modification inspection recommendations given in this service bulletin supersede the damage
tolerance inspection recommendations given in paragraph 1.E., Compliance, Table 37, of Service
Bulletin 747-00-2157 and paragraph 1.E., Compliance, Table 18, of Service Bulletin 747-00-2158.
Group 1, 3:
Table 1: Nose Wheel Well Modification
Compliance Time (Whichever Occurs Later)ActionCondition
Within 48 months after
December 11, 2006.
Before 22,000 total flight
cycles. (a)
Do the nose wheel well
modification and inspection
of adjacent structural ele-
ments as given in Para-
graph 3.B., Work Instruc-
tions, PART 2.
All airplanes.
-Before further flight.Contact Boeing for repair
instructions, and do the re-
pair.
Any crack or damage
found in an adjacent struc-
tural element.
(a) Airplanes that have the modification accomplished before 15,000 total flight cycles will require post modi-
fication inspections as given in Table 3 in order to allow continued operation to the Limit of Validity (LOV)
of 35,000 total flight cycles.
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Group 2, 4:
Table 2: Nose Wheel Well Modification
Compliance Time (Whichever Occurs Later)ActionCondition
Within 57 months after
December 11, 2006.
Before 22,000 total flight
cycles. (a)
Do the nose wheel well
modification and inspection
of adjacent structural ele-
ments as given in Para-
graph 3.B., Work Instruc-
tions, PART 2.
All airplanes.
-Before further flight.Contact Boeing for repair
instructions, and do the re-
pair.
Any crack or damage
found in an adjacent struc-
tural element.
(a) Airplanes that have the modification accomplished before 15,000 total flight cycles will require post modi-
fication inspections as given in Table 3 or 4, as applicable, in order to allow continued operation to the
Limit of Validity (LOV) of 35,000 total flight cycles.
Group 1-3:
Table 3: Nose Wheel Well - Post Modification Inspections for Airplanes on Which the Modification has
been Done
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 20,000 flight
cycles after modifi-
cation as given in
Paragraph 3.B.,
Work Instructions,
PART 2, or within
1,000 flight cycles
after the Revision
3 date of this ser-
vice bulletin,
whichever occurs
later.
Do an external detailed inspection for
cracks in the side panel webs, and do
internal detailed and high frequency ed-
dy current (HFEC) inspections for cracks
in the top and side panel stiffeners as
given in Paragraph 3.B., Work Instruc-
tions, PART 6.
All airplanes on which the
nose wheel well modifica-
tion has been done as giv-
en in Paragraph 3.B., Work
Instructions, PART 2.
Do an external detailed inspection for
cracks in the top panel web as given in
Paragraph 3.B., Work Instructions,
PART 7.
-Before further
flight.
Contact Boeing for repair instructions
and do the repair.
Any crack found.
6,000 flight cycles.-Repeat the external detailed inspection
for cracks in the side panel webs, and
repeat the internal detailed and HFEC
inspections for cracks in the top and side
panel stiffeners as given in Paragraph
3.B., Work Instructions, PART 6.
No crack found, or crack
has been repaired.
6,000 flight cycles.-Repeat the external detailed inspection
for cracks in the top panel web as given
in Paragraph 3.B., Work Instructions,
PART 7.
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Group 4:
Table 4: Nose Wheel Well - Post Modification Inspections for Airplanes on Which the Modification has
been Done
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 20,000 flight
cycles after modifi-
cation as given in
Paragraph 3.B.,
Work Instructions,
PART 2, or within
1,000 flight cycles
after the Revision
3 date of this ser-
vice bulletin,
whichever occurs
later.
Do an external detailed inspection for
cracks in the side panel webs, and do
internal detailed and high frequency ed-
dy current (HFEC) inspections for cracks
in the top and side panel stiffeners as
given in Paragraph 3.B., Work Instruc-
tions, PART 6.
All airplanes on which the
nose wheel well modifica-
tion has been done as giv-
en in Paragraph 3.B., Work
Instructions, PART 2.
Do an external detailed inspection for
cracks in the top panel web as given in
Paragraph 3.B., Work Instructions,
PART 7.
-Before further
flight.
Contact Boeing for repair instructions
and do the repair.
Any crack found.
6,000 flight cycles.-Repeat the external detailed inspection
for cracks in the side panel webs, and
repeat the internal detailed and HFEC
inspections for cracks in the top and side
panel stiffeners as given in Paragraph
3.B., Work Instructions, PART 6.
No crack found, or crack
has been repaired.
3,000 flight cycles.-Repeat the external detailed inspection
for cracks in the top panel web as given
in Paragraph 3.B., Work Instructions,
PART 7.
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.
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Group 1, 3:
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office (ACO) approves the accomplishment of the modification action with the corresponding
compliance times specified in paragraph 1.E., "Compliance", of Service Bulletin 747-53A2562, Revision
3, as an Alternative Method of Compliance (AMOC) to the actions with corresponding compliance times
required by paragraph (n) of AD 2006-22-15. All provisions of AD 2006-22-15 that are not specifically
referenced in the above statement remain fully applicable and must be complied with accordingly.
Group 2, 4:
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office (ACO) approves the accomplishment of the modification action with the corresponding
compliance times specified in paragraph 1.E., "Compliance", of Service Bulletin 747-53A2562, Revision
3, as a Method of Compliance (MOC) to the actions with corresponding compliance times required by
paragraph (o) of AD 2006-22-15. All provisions of AD 2006-22-15 that are not specifically referenced
in the above statement remain fully applicable and must be complied with accordingly.
Modification as given in this service bulletin is consistent with AD 2006-22-15, except AD 2006-22-15
paragraph (o) requires top panel replacement for airplanes that were not identified in Service Bulletin
747-53A2562, Revision 1 (Group 4 airplanes). Boeing analysis, however, has shown that top panel
web replacement is not required for Group 4 airplanes.
G. Manpower
The table below shows an estimate of the task-hours necessary to do this 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 examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1-3:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
15604Open Access
30012004Change
20804Close Access
3.06.02Test
3381346TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
14.5584Open Access
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Group 4:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2008004Change
19.5784Close Access
3.06.02Test
237942TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+35,239+105.0Group 1-3
+33,481+99.0Group 4
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 85901-63RS
b. Boeing Service Bulletin 747-00-2157, 747-00-2158, 747-53A2465
c. Boeing Service Letter 747-SL-51-048, 747-SL-53-088
d. Boeing Service Related Problem (SRP) 747-SRP-53-0133, 747-SRP-53-0231
e. Boeing Structural Item Interim Advisory (SIIA) 747-129
f. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-22-15
g. Service Bulletin Index D6-30300
h. Standard Overhaul Practices Manual (SOPM) 20-50-01
i. 747 Fleet Team Digest (FTD) 53-04002, 53-12006
j. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00
k. 747-100/200/300 Aircraft Maintenance Manual (AMM) 05-51-08, 07-11-01, 09-11-00, 12-15-05,
20-11-05, 24-22-00, 25-25-01, 25-27-01, 25-28-02, 25-57-01, 25-57-04, 29-11-00, 32-00-30,
32-09-03, 32-21-01, 32-22-01, 32-22-03, 32-22-05, 32-34-00, 32-34-05, 32-34-06, 32-34-07,
32-34-10, 32-34-14, 32-34-15, 32-36-04, 32-45-05, 33-31-00, 53-21-02
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### Page 30

l. 747-400 Aircraft Maintenance Manual (AMM) 05-51-08, 07-11-01, 09-11-00, 12-15-05,
20-11-05, 24-22-00, 25-25-01, 25-27-01, 25-28-03, 25-57-01, 25-57-04, 29-11-00, 32-00-30,
32-09-03, 32-21-01, 32-22-01, 32-22-03, 32-22-05, 32-34-05, 32-34-06, 32-34-07, 32-34-08,
32-34-10, 32-34-14, 32-34-15, 32-35-04, 32-45-05, 33-31-00, 53-21-02
2. Data Supplied with this Service Bulletin:
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-C1Kit - Nose Wheel Well Modification, STA
260 - STA 340
141U1192
-B2
-C3
-B4
-B5
-B6
-D7
-C8
-C9
-APSDL
-CKPLNOSE WHEEL WELL MODIFICATION, STA
260 TO STA 340 - TOP KIT
141U1192-1
-BKPLLEFT SIDE PANEL MODIFICATION - KIT141U1192-11
-BKPLRIGHT SIDE PANEL MODIFICATION - KIT141U1192-12
-BKPLNOSE WHEEL WELL MODIFICATION, STA
260 TO STA 340 - TOP KIT
141U1192-2
-AKPLTOP PANEL MODIFICATION FASTENERS
- KIT
141U1192-31
-AKPLSIDE PANEL MODIFICATION FASTENERS
- KIT
141U1192-33
-BKPLTOP PANEL MODIFICATION FASTENERS
- KIT
141U1192-35
-AKPLSIDE PANEL MODIFICATION FASTENERS
- KIT
141U1192-37
-AKPLLEFT SIDE SUPPLEMENTAL PARTS - KIT141U1192-49
-DKPLTOP PANEL MODIFICATION - KIT141U1192-5
-AKPLRIGHT SIDE SUPPLEMENTAL PARTS -
KIT
141U1192-50
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ADCNDCN/REVSheetTitleDrawing No
-AKPLNOSE WHEEL WELL MODIFICATION, STA
260 TO STA 340 - REPLACEMENT TOP
KIT
141U1192-53
-AKPLTOP PANEL MODIFICATION - KIT141U1192-55
-AKPLLEFT SIDE PANEL MODIFICATION - KIT141U1192-57
-AKPLRIGHT SIDE PANEL MODIFICATION - KIT141U1192-58
-AKPLSIDE PANEL MODIFICATION FASTENERS
- KIT
141U1192-59
-AKPLTOP PANEL MODIFICATION FASTENERS
- KIT
141U1192-60
-CKPLLEFT SIDE PANEL MODIFICATION - KIT141U1192-7
-CKPLRIGHT SIDE PANEL MODIFICATION - KIT141U1192-8
-CKPLTOP PANEL MODIFICATION - KIT141U1192-9
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Nose Wheel Well Rework691U1046
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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BLANK PAGE

### Page 33

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Group 1-3:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price thru
January 30,
2014
ROLT
(Weeks)
QTYDateNameKit Number
(a)(a)(a)(a)TOP KIT - NOSE
WHEEL WELL MODIFI-
CATION, STA 260 TO
STA 340
141U1192-1
$121,439.0052(b)(b)TOP KIT - NOSE
WHEEL WELL MODIFI-
CATION, STA 260 TO
STA 340
141U1192-53
(a) 141U1192-1 top kit is no longer available. If 141U1192-1 top kit has been purchased, then the
supplemental parts identified in paragraph 2.C.2., "Parts and Materials Supplied by the Operator"
are necessary.
(b) Refer to the Boeing Part Page on MyBoeingFleet.com or contact Boeing Spares for availability.
Group 4:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price thru
January 30,
2014
ROLT
(Weeks)
QTYDateNameKit Number
$144,298.0078(a)(a)TOP KIT - NOSE
WHEEL WELL MODIFI-
CATION, STA 260 TO
STA 340
141U1192-2
(a) Refer to the Boeing Part Page on MyBoeingFleet.com or contact Boeing Spares for availability.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 34

B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes inspection, and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(c)NOSE WHEEL
WELL MODIFICA-
TION, STA 260 TO
STA 340 - TOP KIT
.....-141U1192-1
TOP PANEL MOD-
IFICATION - KIT
....-1141U1192-5
LEFT SIDE PANEL
MODIFICATION -
KIT
...-.1141U1192-7
RIGHT SIDE PAN-
EL MODIFICA-
TION - KIT
..-..1141U1192-8
TOP PANEL MOD-
IFICATION FAS-
TENERS - KIT
.-...1141U1192-31
SIDE PANEL
MODIFICATION
FASTENERS - KIT
-....2141U1192-33
TOP PANEL MOD-
IFICATION - KIT
....-1141U1192-5
LEFT SIDE PANEL
MODIFICATION -
KIT
...-.1141U1192-7
RIGHT SIDE PAN-
EL MODIFICA-
TION - KIT
..-..1141U1192-8
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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### Page 35

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
TOP PANEL MOD-
IFICATION FAS-
TENERS - KIT
.-...1141U1192-31
SIDE PANEL
MODIFICATION
FASTENERS - KIT
-....2141U1192-33
LEFT SIDE SUP-
PLEMENTAL
PARTS - KIT
.....1141U1192-49
RIGHT SIDE SUP-
PLEMENTAL
PARTS - KIT
.....1141U1192-50
WEB - ROUGH
MACHINED
..11..141U1193-1
WEB....1.141U1193-3
BEAM....1.141U1193-4
BEAM....6.141U1193-5
BEAM....1.141U1193-6
BEAM....1.141U1193-7
BEAM....1.141U1193-8
BEAM....2.141U1193-9
BEAM....2.141U1193-10
ANGLE....2.141U1193-11
ANGLE....2.141U1193-12
BEAM....1.141U1193-13
BEAM....1.141U1193-14
ANGLE....1.141U1193-16
BEAM....7.141U1193-17
BEAM....8.141U1193-18
BEAM....1.141U1193-19
CLIP....1.141U1193-20
CLIP....5.141U1193-21
BEAM..33..141U1193-23
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 36

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
ANGLE..13131.141U1193-25
BEAM..22..141U1193-27
BEAM..11..141U1193-29
BEAM...2..141U1193-31
BEAM..2...141U1193-32
BEAM...7..141U1193-33
BEAM..7...141U1193-34
ANGLE....14.141U1193-35
BEAM...1..141U1193-37
BEAM..1...141U1193-38
BEAM...1..141U1193-39
BEAM..1...141U1193-40
BEAM...1..141U1193-41
BEAM..1...141U1193-42
BEAM...3..141U1193-43
BEAM..3...141U1193-44
BEAM...1..141U1193-45
BEAM..1...141U1193-46
BEAM...7..141U1193-47
BEAM..8...141U1193-48
BEAM...1..141U1193-49
BEAM...1..141U1193-51
BEAM..1...141U1193-52
BEAM...1..141U1193-53
BEAM..1...141U1193-54
STIFFENER....3.141U5190-219
STIFFENER....2.141U5190-220
(d)ANGLE - SIDE....1.65B07941U109
(d)ANGLE - SIDE....1.65B07941U110
(d)ANGLE - SIDE....1.65B07941U111
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 37

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(d)ANGLE - SIDE....1.65B07941U112
(d)GUSSET-AFT....2.65B07941U21
(d)GUSSET-FWD....1.65B07941U76
(d)ANGLE-FWD....1.65B07941Y9
(d)BEAM..1...65B07942U100
(d)CLIP...1..65B07942U103
(d)CLIP..1...65B07942U104
(d)ANGLE...3..65B07942U127
(d)ANGLE..3...65B07942U128
(d)CHORD...1..65B07942U15
(d)BEAM...1..65B07942U151
(d)BEAM..1...65B07942U152
(d)CHORD..1...65B07942U16
(d)CLIP..66..65B07942U183
(d)CHORD...1..65B07942U67
(d)CHORD..1...65B07942U68
(d)CHORD...1..65B07942U71
(d)CHORD..1...65B07942U72
(d)CHORD...1..65B07942U75
(d)CHORD..1...65B07942U76
(d)BEAM...1..65B07942U85
(d)BEAM..1...65B07942U86
(d)BEAM...1..65B07942U87
(d)BEAM..1...65B07942U88
(d)CLIP...1..65B07942U89
(d)CLIP..1...65B07942U90
(d)CLIP...1..65B07942U93
(d)CLIP..1...65B07942U94
(d)BEAM...1..65B07942U95
(d)CLIP..1...65B07942U96
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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### Page 38

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(d)BEAM...1..65B07942U97
(d)CLIP..1...65B07942U98
(d)BEAM...1..65B07942U99
(d)ANGLE...1..65B07953U17
(d)ANGLE..1...65B07953U18
(d)ANGLE...1..65B07953U19
(d)ANGLE..1...65B07953U20
(d)FITTING...1..65B07953U3
(d)FITTING..1...65B07953U4
(d)FITTING...1..65B07953U5
(65B07953U229
optional)
(d)FITTING..1...65B07953U6
(65B07953U230
optional)
(d)FITTING...1..65B07953U7
(d)FITTING..1...65B07953U8
(d)CORNER FITTING...1..69B17168U1
(d)CORNER FITTING..1...69B17168U2
TAPERED SHIM....30.90-9195-147
TAPERED SHIM..55..90-9195-309
TAPERED SHIM..11..90-9195-320
TAPERED SHIM..1616..90-9195-9
(a) (b)HI-LOK9.....BACB30MY8K9
(a) (b)BOLT, HEX HEAD.9....BACB30NM4K18
(a) (b)BOLT, HEX HEAD56....BACB30NR4K10
(a) (b)BOLT54....BACB30NR4K11
(a) (b)BOLT, PROTRUD-
ING HD
426....BACB30NX6K10X
(a) (b)BOLT, PROTRUD-
ING HD
26....BACB30NX6K11X
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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### Page 39

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(a) (b)BOLT, PROTRUD-
ING HD
.7....BACB30NX6K12X
(a) (b)BOLT, PROTRUD-
ING HD
.2....BACB30NX6K13X
(a) (b)BOLT, PROTRUD-
ING HD
27.....BACB30NX6K3X
(a) (b)BOLT, PROTRUD-
ING HD
.20....BACB30NX6K4
(a) (b)BOLT, PROTRUD-
ING HD
3.....BACB30NX6K4X
(a) (b)BOLT16.....BACB30NX6K5
(a) (b)BOLT, PROTRUD-
ING HD
3177....BACB30NX6K5X
(a) (b)BOLT7.....BACB30NX6K6
(a) (b)BOLT, PROTRUD-
ING HD
17124....BACB30NX6K6X
(a) (b)BOLT, PROTRUD-
ING HD
.104....BACB30NX6K7X
(a) (b)BOLT, PROTRUD-
ING HD
286....BACB30NX6K8X
(a) (b)BOLT, PROTRUD-
ING HD
.38....BACB30NX6K9X
(a) (b)BOLT, PROTRUD-
ING HD
.9....BACB30NX8K13X
(a) (b)BOLT, PROTRUD-
ING HD
.3....BACB30NX8K16X
(a) (b)BOLT, HEX DRIVE.3....BACB30NX8K17X
(a) (b)BOLT, PROTRUD-
ING HD
.2....BACB30NX8K20X
(a) (b)BOLT, PROTRUD-
ING HD
.5....BACB30NX8K6X
(a) (b)BOLT, PROTRUD-
ING HD
4.....BACB30NX8K7X
(a) (b)BOLT, PROTRUD-
ING HD
.20....BACB30NX8K8X
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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### Page 40

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(a) (b)BOLT, 100 DEG
HEX DR
.4....BACB30YP5K4
(a)COLLAR.36....BACC30AG6
(a)COLLAR94450....BACC30BH6
(a)COLLAR439....BACC30BH8
(a)COLLAR, SHEAR.4....BACC30BL5
FILLER, RECTAN-
GULAR
....5.BACF3H10RK020BN
FILLER....5.BACF3T01E05-07
FILLER....5.BACF3T01G07-07
NUTPLATE.2....BACN10JR3CD
NUTPLATE, SELF-
LOCK
3.....BACN10JR3CKD
NUT PLATE14.....BACN10JR4CFD
NUTPLATE6.....BACN10JR5CFD
NUTPLATE6.....BACN10JR6CFD
NUTPLATE, SELF-
LOCK
.6....BACN10JZ4A2CD-
MU
NUTPLATE.2....BACN10JZ4B2CDM
NUT8.....BACN10YR4CD
(a) (b)RIVET, 100 DEG.9....BACR15BA3D11C
(a) (b)RIVET, 100 DEG.5....BACR15BA3D4C
(a) (b)RIVET, 100 DEG.9....BACR15BA3D9C
(a) (b)RIVET, 100 DEG.5....BACR15BA6D7C
(a) (b)RIVET43108....BACR15BB5D5C
(a) (b)RIVET, UNIVER-
SAL HD
2953....BACR15BB5D6C
(a) (b)RIVET, UNIVER-
SAL HD
238....BACR15BB5D7C
(a) (b)RIVET, UNIVER-
SAL HD
36....BACR15BB5D8C
(a) (b)RIVET, UNIVER-
SAL HD
36....BACR15BB6D10C
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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BOEING SERVICE BULLETIN 747-53A2562

### Page 41

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(a) (b)RIVET, UNIVER-
SAL HD
3.....BACR15BB6D11C
(a) (b)RIVET, UNIVER-
SAL HD
2305....BACR15BB6D5C
(a) (b)RIVET, UNIVER-
SAL HD
452303....BACR15BB6D6C
(a) (b)RIVET, UNIVER-
SAL HD
639682....BACR15BB6D7C
(a) (b)RIVET, UNIVER-
SAL HD
159107....BACR15BB6D8C
(a) (b)RIVET, UNIVER-
SAL HD
4431....BACR15BB6D9C
(a) (b)RIVET, UNIVER-
SAL HD
2.....BACR15BB8D10C
(a) (b)RIVET, UNIVER-
SAL HD
25.....BACR15BB8D11C
(a) (b)RIVET, UNIVER-
SAL HD
.3....BACR15BB8D19C
(a) (b)RIVET, UNIVER-
SAL HD
29.....BACR15BB8D6C
(a) (b)RIVET, UNIVER-
SAL HD
20.....BACR15BB8D7C
(a) (b)RIVET, UNIVER-
SAL HD
362....BACR15BB8D8C
(a) (b)RIVET, UNIVER-
SAL HD
23....BACR15BB8D9C
(a) (b)RIVET, 100 DEG3.....BACR15GF3D7
(a) (b)RIVET, 100 DEG14.....BACR15GF3D8
(a) (b)RIVET, 100 DEG9.....BACR15GF3D9
(a) (b)RIVET, 100 DEG7.....BACR15GF4D10
(a) (b)RIVET, 100 DEG7.....BACR15GF4D8
(a) (b)RIVET, 100 DEG23....BACR15GF6D6
(a) (b)RIVET, 100 DEG95....BACR15GF6D7
(a) (b)RIVET, 100 DEG.5....BACR15GF6D9
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 42

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-33-31-8-7-5-1
(a) (b)SHIM,LAMINATED....22.BACS40R008B008F
SHIM, LAMINAT-
ED
....2.BACS40R010C023F
WASHER.9....BACW10BN4AC
(a) There may be more parts than are necessary.
(b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
(c) 141U1192-1 top kit has been superseded by 141U1192-53 top kit. See Paragraph 2.C.2., Parts and Ma-
terials Supplied by the Operator for supplemental parts that could be necessary if the 141U1192-1 top kit
has already been purchased, but not installed.
(d) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify
these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts
are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this
service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service
Letter 747-SL-00-018 for more information.
Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-50-49
LEFT SIDE SUP-
PLEMENTAL
PARTS - KIT
.-141U1192-49
RIGHT SIDE SUP-
PLEMENTAL
PARTS - KIT
-.141U1192-50
(c)PLATE5565B07942U107
(c)PLATE4365B07942U108
(c)PLATE4465B07942U110
(c)STRAP2265B07942U25
FITTING ASSY.165B11111-501
(c)PLATE2269B10107U1
(c)PLATE2269B10107U2
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 43

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-50-49
TAPERED SHIM3390-9195-1749
(a) (b)BOLT.4BACB30NR4K11
(a) (b)BOLT, PROTRUD-
ING HD
1010BACB30NX6K3X
(a)COLLAR1111BACC30BH6
(a)COLLAR1010BACC30M8
(a) (b)RIVET3131BACR15BB5D5C
(a) (b)RIVET, UNIVER-
SAL HD
55BACR15BB6D10C
(a) (b)RIVET, UNIVER-
SAL HD
22BACR15BB6D11C
(a) (b)RIVET, UNIVER-
SAL HD
3232BACR15BB6D6C
(a) (b)RIVET, UNIVER-
SAL HD
4848BACR15BB6D7C
(a) (b)RIVET, UNIVER-
SAL HD
44BACR15BB6D9C
(a) (b)RIVET, UNIVER-
SAL HD
2929BACR15BB8D6C
(a) (b)RIVET, UNIVER-
SAL HD
1515BACR15BB8D9C
(a) (b)RIVET, 100 DEG22BACR15GF6D6
(a) (b)RIVET, 100 DEG22BACR15GF6D7
(a) (b)BOLT44BACS12HN3-14
WASHER,
SPRING
44BACW10EC3S
WASHER77NAS1149D0316H
(a) There may be more parts than are necessary.
(b) If grip length shown is not available at Boeing, fasteners supplied in kits may
be one grip length longer than indicated. Also, if any fasteners part numbers
listed are not available or have been superseded, substitute fasteners may be
supplied in kits.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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43 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 44

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-50-49
(c) To make installation easier, some Boeing parts are sent in an 'interim' configu-
ration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in
place of the '-' (dash) in the part number. Interim parts are changed to the 'dash'
configuration when installed as given in the Accomplishment Instructions of this
service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS -
SPARES" and Boeing Service Letter 747-SL-00-018 for more information.
Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
(a)NOSE WHEEL
WELL MODIFICA-
TION, STA 260 TO
STA 340 - RE-
PLACEMENT TOP
KIT
.....-141U1192-53
TOP PANEL MOD-
IFICATION - KIT
....-1141U1192-55
LEFT SIDE PANEL
MODIFICATION -
KIT
...-.1141U1192-57
RIGHT SIDE PAN-
EL MODIFICA-
TION - KIT
..-..1141U1192-58
SIDE PANEL
MODIFICATION
FASTENERS - KIT
.-...2141U1192-59
TOP PANEL MOD-
IFICATION FAS-
TENERS - KIT
-....1141U1192-60
TOP PANEL MOD-
IFICATION - KIT
....-1141U1192-55
LEFT SIDE PANEL
MODIFICATION -
KIT
...-.1141U1192-57
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 45

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
RIGHT SIDE PAN-
EL MODIFICA-
TION - KIT
..-..1141U1192-58
SIDE PANEL
MODIFICATION
FASTENERS - KIT
.-...2141U1192-59
TOP PANEL MOD-
IFICATION FAS-
TENERS - KIT
-....1141U1192-60
WEB - ROUGH
MACHINED
..11..141U1193-1
WEB....1.141U1193-3
BEAM....1.141U1193-4
BEAM....6.141U1193-5
BEAM....1.141U1193-6
BEAM....1.141U1193-7
BEAM....1.141U1193-8
BEAM....2.141U1193-9
BEAM....2.141U1193-10
ANGLE....2.141U1193-11
ANGLE....2.141U1193-12
BEAM....1.141U1193-13
BEAM....1.141U1193-14
ANGLE....1.141U1193-16
BEAM....7.141U1193-17
BEAM....8.141U1193-18
BEAM....1.141U1193-19
CLIP....1.141U1193-20
CLIP....5.141U1193-21
BEAM..33..141U1193-23
ANGLE..13131.141U1193-25
BEAM..22..141U1193-27
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 46

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
BEAM..11..141U1193-29
BEAM...2..141U1193-31
BEAM..2...141U1193-32
BEAM...7..141U1193-33
BEAM..7...141U1193-34
ANGLE....14.141U1193-35
BEAM...1..141U1193-37
BEAM..1...141U1193-38
BEAM...1..141U1193-39
BEAM..1...141U1193-40
BEAM...1..141U1193-41
BEAM..1...141U1193-42
BEAM...3..141U1193-43
BEAM..3...141U1193-44
BEAM...1..141U1193-45
BEAM..1...141U1193-46
BEAM...7..141U1193-47
BEAM..8...141U1193-48
BEAM...1..141U1193-49
BEAM...1..141U1193-51
BEAM..1...141U1193-52
BEAM...1..141U1193-53
BEAM..1...141U1193-54
STIFFENER....3.141U5190-219
STIFFENER....2.141U5190-220
(d)ANGLE - SIDE....1.65B07941U109
(d)ANGLE - SIDE....1.65B07941U110
(d)ANGLE - SIDE....1.65B07941U111
(d)ANGLE - SIDE....1.65B07941U112
(d)GUSSET-AFT....2.65B07941U21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
46 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 47

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
(d)CLIP....2.65B07941U60
(d)GUSSET-FWD....1.65B07941U76
(d)ANGLE-FWD....1.65B07941Y9
(d)BEAM..1...65B07942U100
(d)CLIP...1..65B07942U103
(d)CLIP..1...65B07942U104
(d)PLATE..55..65B07942U107
(d)PLATE..43..65B07942U108
(d)PLATE..44..65B07942U110
(d)CLIP..11..65B07942U113
(d)ANGLE...3..65B07942U127
(d)ANGLE..3...65B07942U128
(d)CHORD...1..65B07942U15
(d)BEAM...1..65B07942U151
(d)BEAM..1...65B07942U152
(d)CHORD..1...65B07942U16
(d)CLIP..66..65B07942U183
(d)STRAP..22..65B07942U25
(d)CLIP..11..65B07942U329
(d)CHORD...1..65B07942U67
(d)CHORD..1...65B07942U68
(d)CHORD...1..65B07942U71
(d)CHORD..1...65B07942U72
(d)CHORD...1..65B07942U75
(d)CHORD..1...65B07942U76
(d)BEAM...1..65B07942U85
(d)BEAM..1...65B07942U86
(d)BEAM...1..65B07942U87
(d)BEAM..1...65B07942U88
(d)CLIP...1..65B07942U89
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
47 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 48

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
(d)CLIP..1...65B07942U90
(d)CLIP...1..65B07942U93
(d)CLIP..1...65B07942U94
(d)BEAM...1..65B07942U95
(d)CLIP..1...65B07942U96
(d)BEAM...1..65B07942U97
(d)CLIP..1...65B07942U98
(d)BEAM...1..65B07942U99
(d)ANGLE...1..65B07953U17
(d)ANGLE..1...65B07953U18
(d)ANGLE...1..65B07953U19
(d)ANGLE..1...65B07953U20
(d)FITTING...1..65B07953U3
(d)FITTING..1...65B07953U4
(d)FITTING...1..65B07953U5
(65B07953U229
optional)
(d)FITTING..1...65B07953U6
(65B07953U230
optional)
(d)FITTING...1..65B07953U7
(d)FITTING..1...65B07953U8
FITTING ASSY...1..65B11111-501
(d)PLATE..22..69B10107U1
(d)PLATE..22..69B10107U2
(d)CORNER FITTING...1..69B17168U1
(d)CORNER FITTING..1...69B17168U2
TAPERED SHIM....30.90-9195-147
TAPERED SHIM..33..90-9195-1749
TAPERED SHIM..55..90-9195-309
TAPERED SHIM..11..90-9195-320
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
48 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 49

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
TAPERED SHIM..1616..90-9195-9
(b) (c)BOLT, PROTRUD-
ING HD
4.....BACB30MY8K7X
(b) (c)HI-LOK.9....BACB30MY8K9
(b) (c)BOLT, PROTRUD-
ING HD
4.....BACB30MY8K9X
(b) (c)BOLT, HEX HEAD9.....BACB30NM4K18
(b) (c)BOLT, HEX HEAD65....BACB30NR4K10
(b) (c)BOLT49....BACB30NR4K11
(b) (c)BOLT, HEX HEAD.5....BACB30NR4K12
(b) (c)BOLT.3....BACB30NR4K15
(b) (c)BOLT, PROTRUD-
ING HD
264....BACB30NX6K10X
(b) (c)BOLT, PROTRUD-
ING HD
62....BACB30NX6K11X
(b) (c)BOLT, PROTRUD-
ING HD
7.....BACB30NX6K12X
(b) (c)BOLT, PROTRUD-
ING HD
2.....BACB30NX6K13X
(b) (c)BOLT, PROTRUD-
ING HD
.37....BACB30NX6K3X
(b) (c)BOLT, PROTRUD-
ING HD
20.....BACB30NX6K4
(b) (c)BOLT, PROTRUD-
ING HD
.3....BACB30NX6K4X
(b) (c)BOLT.16....BACB30NX6K5
(b) (c)BOLT, PROTRUD-
ING HD
7745....BACB30NX6K5X
(b) (c)BOLT.7....BACB30NX6K6
(b) (c)BOLT, PROTRUD-
ING HD
12421....BACB30NX6K6X
(b) (c)BOLT, PROTRUD-
ING HD
104.....BACB30NX6K7X
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
49 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 50

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
(b) (c)BOLT, PROTRUD-
ING HD
863....BACB30NX6K8X
(b) (c)BOLT, PROTRUD-
ING HD
38.....BACB30NX6K9X
(b) (c)BOLT, PROTRUD-
ING HD
5.....BACB30NX8K11X
(b) (c)BOLT, PROTRUD-
ING HD
2.....BACB30NX8K12X
(b) (c)BOLT, PROTRUD-
ING HD
10.....BACB30NX8K13X
(b) (c)BOLT, PROTRUD-
ING HD
3.....BACB30NX8K16X
(b) (c)BOLT, HEX DRIVE3.....BACB30NX8K17X
(b) (c)BOLT, PROTRUD-
ING HD
2.....BACB30NX8K20X
(b) (c)BOLT, PROTRUD-
ING HD
5.....BACB30NX8K6X
(b) (c)BOLT, PROTRUD-
ING HD
.4....BACB30NX8K7X
(b) (c)BOLT, PROTRUD-
ING HD
20.....BACB30NX8K8X
(b) (c)BOLT, 100 DEG
HEX DR
4.....BACB30YP5K4
(b)COLLAR36.....BACC30AG6
(b)COLLAR450123....BACC30BH6
(b)COLLAR475....BACC30BH8
(b)COLLAR, SHEAR4.....BACC30BL5
(b)COLLAR810....BACC30M8
FILLER, RECTAN-
GULAR
....5.BACF3H10RK020BN
FILLER....5.BACF3T01E05-07
FILLER....5.BACF3T01G07-07
NUTPLATE2.....BACN10JR3CD
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
50 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 51

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
NUTPLATE, SELF-
LOCK
.3....BACN10JR3CKD
NUT PLATE.14....BACN10JR4CFD
NUTPLATE.6....BACN10JR5CFD
NUTPLATE.6....BACN10JR6CFD
NUTPLATE, SELF-
LOCK
6.....BACN10JZ4A2CD-
MU
NUTPLATE2.....BACN10JZ4B2CDM
(b) (c)RIVET, 100 DEG9.....BACR15BA3D11C
(b) (c)RIVET, 100 DEG5.....BACR15BA3D4C
(b) (c)RIVET, 100 DEG9.....BACR15BA3D9C
(b) (c)RIVET4.....BACR15BA4D9C
(b) (c)RIVET, 100 DEG5.....BACR15BA6D7C
(b) (c)RIVET10874....BACR15BB5D5C
(b) (c)RIVET, UNIVER-
SAL HD
5535....BACR15BB5D6C
(b) (c)RIVET, UNIVER-
SAL HD
382....BACR15BB5D7C
(b) (c)RIVET, UNIVER-
SAL HD
63....BACR15BB5D8C
(b) (c)RIVET, UNIVER-
SAL HD
68....BACR15BB6D10C
(b) (c)RIVET, UNIVER-
SAL HD
.5....BACR15BB6D11C
(b) (c)RIVET, UNIVER-
SAL HD
5232....BACR15BB6D5C
(b) (c)RIVET, UNIVER-
SAL HD
303486....BACR15BB6D6C
(b) (c)RIVET, UNIVER-
SAL HD
682687....BACR15BB6D7C
(b) (c)RIVET, UNIVER-
SAL HD
107159....BACR15BB6D8C
(b) (c)RIVET, UNIVER-
SAL HD
3148....BACR15BB6D9C
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
51 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 52

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
(b) (c)RIVET, UNIVER-
SAL HD
.2....BACR15BB8D10C
(b) (c)RIVET, UNIVER-
SAL HD
.25....BACR15BB8D11C
(b) (c)RIVET, UNIVER-
SAL HD
3.....BACR15BB8D19C
(b) (c)RIVET, UNIVER-
SAL HD
.58....BACR15BB8D6C
(b) (c)RIVET, UNIVER-
SAL HD
.20....BACR15BB8D7C
(b) (c)RIVET, UNIVER-
SAL HD
236....BACR15BB8D8C
(b) (c)RIVET, UNIVER-
SAL HD
317....BACR15BB8D9C
(b) (c)RIVET, 100 DEG.3....BACR15GF3D7
(b) (c)RIVET, 100 DEG.14....BACR15GF3D8
(b) (c)RIVET, 100 DEG.9....BACR15GF3D9
(b) (c)RIVET, 100 DEG.7....BACR15GF4D10
(b) (c)RIVET, 100 DEG.7....BACR15GF4D8
(b) (c)RIVET, 100 DEG34....BACR15GF6D6
(b) (c)RIVET, 100 DEG511....BACR15GF6D7
(b) (c)RIVET, 100 DEG5.....BACR15GF6D9
(b) (c)BOLT.4....BACS12HN3-14
SHIM,LAMINATED....22.BACS40R008B008F
SHIM, LAMINAT-
ED
....2.BACS40R010C023F
WASHER9.....BACW10BN4AC
WASHER,
SPRING
.4....BACW10EC3S
WASHER.7....NAS1149D0316H
(a) 141U1192-1 top kit has been superseded by 141U1192-53 top kit. See Paragraph 2.C.2., Parts and Ma-
terials Supplied by the Operator for supplemental parts that could be necessary if the 141U1192-1 top kit
has already been purchased, but not installed.
(b) There may be more parts than are necessary.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
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52 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 53

Group 1-3:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-60-59-58-57-55-53
(c) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
(d) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify
these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts
are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this
service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service
Letter 747-SL-00-018 for more information.
Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
NOSE WHEEL
WELL MODIFICA-
TION, STA 260 TO
STA 340 - TOP KIT
.....-141U1192-2
TOP PANEL MOD-
IFICATION - KIT
....-1141U1192-9
LEFT SIDE PANEL
MODIFICATION -
KIT
...-.1141U1192-11
RIGHT SIDE PAN-
EL MODIFICA-
TION - KIT
..-..1141U1192-12
TOP PANEL MOD-
IFICATION FAS-
TENERS - KIT
.-...1141U1192-35
SIDE PANEL
MODIFICATION
FASTENERS - KIT
-....2141U1192-37
TOP PANEL MOD-
IFICATION - KIT
....-1141U1192-9
LEFT SIDE PANEL
MODIFICATION -
KIT
...-.1141U1192-11
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
53 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 54

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
RIGHT SIDE PAN-
EL MODIFICA-
TION - KIT
..-..1141U1192-12
TOP PANEL MOD-
IFICATION FAS-
TENERS - KIT
.-...1141U1192-35
SIDE PANEL
MODIFICATION
FASTENERS - KIT
-....2141U1192-37
WEB - ROUGH
MACHINED
..11..141U1193-1
BEAM....1.141U1193-4
BEAM....4.141U1193-5
BEAM....1.141U1193-6
BEAM....1.141U1193-7
BEAM....1.141U1193-8
BEAM....2.141U1193-9
BEAM....2.141U1193-10
ANGLE....2.141U1193-11
ANGLE....2.141U1193-12
BEAM....1.141U1193-13
BEAM....1.141U1193-14
BEAM....1.141U1193-15
ANGLE....1.141U1193-16
BEAM....6.141U1193-17
BEAM....6.141U1193-18
CLIP....1.141U1193-20
CLIP....5.141U1193-21
BEAM..33..141U1193-23
ANGLE..13133.141U1193-25
BEAM..22..141U1193-27
BEAM..11..141U1193-29
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
54 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 55

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
BEAM...2..141U1193-31
BEAM..2...141U1193-32
BEAM...7..141U1193-33
BEAM..7...141U1193-34
ANGLE....14.141U1193-35
BEAM...1..141U1193-37
BEAM..1...141U1193-38
BEAM...1..141U1193-39
BEAM..1...141U1193-40
BEAM...1..141U1193-41
BEAM..1...141U1193-42
BEAM...3..141U1193-43
BEAM..3...141U1193-44
BEAM...1..141U1193-45
BEAM..1...141U1193-46
BEAM...6..141U1193-47
BEAM..6...141U1193-48
BEAM...1..141U1193-51
BEAM..1...141U1193-52
BEAM...1..141U1193-53
BEAM..1...141U1193-54
BEAM....1.141U1193-55
BEAM....2.141U1193-56
BEAM....1.141U1193-57
FILLER..21..141U1193-58
FILLER...1..141U1193-59
FILLER..11..141U1193-60
SPLICE ANGLE....5.141U1193-61
STIFFENER....1.141U5385-34
(c)STIFFENER....1.141U5385U353
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
55 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 56

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
(c)STIFFENER....1.141U5385U391
(c)STIFFENER....1.141U5385U392
(c)STIFFENER....1.141U5385U393
(c)STIFFENER....1.141U5385U394
(c)CLIP....2.65B07941U60
(c)BEAM..1...65B07942U100
(c)CLIP...1..65B07942U103
(c)CLIP..1...65B07942U104
(c)PLATE..55..65B07942U107
(c)PLATE..43..65B07942U108
(c)PLATE..44..65B07942U110
(c)CLIP..11..65B07942U113
(c)ANGLE...2..65B07942U127
(c)ANGLE..2...65B07942U128
(c)CHORD...1..65B07942U15
(c)BEAM...1..65B07942U151
(c)BEAM..1...65B07942U152
(c)CHORD..1...65B07942U16
(c)CLIP..66..65B07942U183
(c)STRAP..22..65B07942U25
(c)CLIP..11..65B07942U329
(c)CHORD...1..65B07942U519
(c)CHORD..1...65B07942U520
(c)CHORD...1..65B07942U71
(c)CHORD..1...65B07942U72
(c)CHORD...1..65B07942U75
(c)CHORD..1...65B07942U76
(c)BEAM...1..65B07942U85
(c)BEAM..1...65B07942U86
(c)BEAM...1..65B07942U87
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
56 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 57

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
(c)BEAM..1...65B07942U88
(c)CLIP...1..65B07942U89
(c)CLIP..1...65B07942U90
(c)CLIP...1..65B07942U93
(c)CLIP..1...65B07942U94
(c)BEAM...1..65B07942U95
(c)CLIP..1...65B07942U96
(c)BEAM...1..65B07942U97
(c)CLIP..1...65B07942U98
(c)BEAM...1..65B07942U99
(c)ANGLE...1..65B07953U17
(c)ANGLE..1...65B07953U18
(c)ANGLE...1..65B07953U19
(c)ANGLE..1...65B07953U20
(c)FITTING...1..65B07953U3
(c)FITTING..1...65B07953U4
(c)FITTING...1..65B07953U5
(65B07953U229
optional)
(c)FITTING...1..65B07953U541
(c)FITTING..1...65B07953U542
(c)FILLER..11..65B07953U543
(c)FILLER..11..65B07953U544
(c)FILLER..11..65B07953U549
(c)FITTING..1...65B07953U6
(65B07953U230
optional)
FITTING ASSY...1..65B11111-503
(c)ANGLE...1..65B11784U507
(c)ANGLE..1...65B11784U508
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
57 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 58

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
(c)FITTING-STRUT...1..65B14749U1
(65B14749U5 op-
tional)
(c)FITTING-STRUT..1...65B14749U2
(65B14749U6 op-
tional)
(c)PLATE..22..69B10107U1
(c)PLATE..22..69B10107U2
(c)CLIP...2..69B13450Y5
(c)CLIP..2...69B13450Y6
TAPERED SHIM....20.90-9195-147
TAPERED SHIM..55..90-9195-309
TAPERED SHIM..11..90-9195-320
TAPERED SHIM..1616..90-9195-9
(a) (b)BOLT3.....BACB30FP8A3
(a) (b)BOLT6.....BACB30MC6A3
(a) (b)BOLT5.....BACB30MC6A9
(a) (b)BOLT5.....BACB30MC8A4
(a) (b)BOLT, PROTRUD-
ING HD
4.....BACB30MY8K10X
(a) (b)BOLT, PROTRUD-
ING HD
5.....BACB30MY8K11X
(a) (b)HI-LOK9.....BACB30MY8K9
(a) (b)BOLT, HEX HEAD.4....BACB30NR4K10
(a) (b)BOLT, HEX HEAD7.....BACB30NR4K12
(a) (b)BOLT3.....BACB30NR4K15
(a) (b)BOLT, HEX HEAD.6....BACB30NR4K9
(a) (b)BOLT, 100 DEG
HEX DR
7.....BACB30NW8K14X
(a) (b)BOLT, PROTRUD-
ING HD
47....BACB30NX6K10X
(a) (b)BOLT, PROTRUD-
ING HD
210....BACB30NX6K11X
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
58 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 59

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
(a) (b)BOLT, PROTRUD-
ING HD
.5....BACB30NX6K12X
(a) (b)BOLT, PROTRUD-
ING HD
.2....BACB30NX6K13X
(a) (b)BOLT, PROTRUD-
ING HD
36.....BACB30NX6K3X
(a) (b)BOLT, PROTRUD-
ING HD
.11....BACB30NX6K3Y
(a) (b)BOLT, PROTRUD-
ING HD
.128....BACB30NX6K4
(a) (b)BOLT, PROTRUD-
ING HD
287....BACB30NX6K4X
(a) (b)BOLT, PROTRUD-
ING HD
.11....BACB30NX6K4Y
(a) (b)BOLT164....BACB30NX6K5
(a) (b)BOLT, PROTRUD-
ING HD
3154....BACB30NX6K5X
(a) (b)BOLT7.....BACB30NX6K6
(a) (b)BOLT, PROTRUD-
ING HD
1775....BACB30NX6K6X
(a) (b)BOLT, PROTRUD-
ING HD
.45....BACB30NX6K7X
(a) (b)BOLT, PROTRUD-
ING HD
241....BACB30NX6K8X
(a) (b)BOLT, PROTRUD-
ING HD
.22....BACB30NX6K9X
(a) (b)BOLT, PROTRUD-
ING HD
8.....BACB30NX8K6X
(a) (b)BOLT, PROTRUD-
ING HD
4.....BACB30NX8K7X
(a) (b)BOLT, 100 DEG
HEX DR
.4....BACB30YP6K3
COLLAR.22....BACC30AC6
COLLAR.22....BACC30AG6
COLLAR140362....BACC30BH6
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
59 of 136
BOEING SERVICE BULLETIN 747-53A2562

### Page 60

Group 4:
Kit 141U1192
NotesExisting Part
Number
NameQTYNew Part Number
-37-35-12-11-9-2
COLLAR15.....BACC30BH8
COLLAR.4....BACC30BL6
COLLAR27.....BACC30M8
FILLER....2.BACF3F005L008NN
FILLER, FLAT..21..BACF3F008B104NN
FILLER, FLAT,
ALUMINUM AL-
LOY
..22..BACF3F010B010NN
FILLER, FLAT...1..BACF3F010B104NN
FILLER, RECTAN-
GULAR
....5.BACF3H09RF085AN
FILLER, RECTAN-
GULAR
....5.BACF3H10RK020BN
FILLER....1.BACF3T01E05-07
FILLER - TA-
PERED
....4.BACF3T01E05-08
FILLER, TAPERED....1.BACF3T01H08-08
TAPERED FILLER....1.BACF3T01H08-15
FILLER....3.BACF3T01L11-08
NUT, SPACER
PLATE
....1.BACN10GH3A10
NUTPLATE, SELF-
LOCK
3.....BACN10JR3CKD
NUT PLATE14.....BACN10JR4CFD
NUTPLATE6.....BACN10JR5CFD
NUTPLATE6.....BACN10JR6CFD
NUT10.....BACN10YR4CD
(a) (b)RIVET, UNIVER-
SAL HEAD
.3....BACR15BB4D5C
(a) (b)RIVET7486....BACR15BB5D5C
(a) (b)RIVET, UNIVER-
SAL HD
2949....BACR15BB5D6C
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 16, 2005
747-53A2562Revision 3: July 11, 2013
60 of 136
BOEING SERVICE BULLETIN 747-53A2562

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