# Boeing Alert Service Bulletin 747-53A2887: No revision named

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- Document: [Boeing Alert Service Bulletin 747-53A2887](https://openairdocs.org/service-documents/boeing/747-53a2887.md)
- Title as filed: SB BOEING-747-53A2887-00
- Pages: 85
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## Text

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### Page 1

Commercial
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2887
Original Issue: December 02, 2015
ATA System: 5315
SUBJECT: FUSELAGE - Nose Wheel Well - Body Structure Reinforcement Modification and
Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2015 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Unpublished Work.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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Table of Contents
S u m m a r y  ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A . E f f e c t i v i t y  ................................................ 9
1. Airplanes ............................................. 9
2 . S p a r e s  A f f e c t e d  ........................................ 1 9
B. Concurrent Requirements ...................................... 1 9
C. Reason ................................................ 1 9
D . D e s c r i p t i o n  .............................................. 2 0
E. Compliance .............................................. 2 1
F . A p p r o v a l  ............................................... 2 5
G. Manpower .............................................. 2 6
H. Weight and Balance Changes .................................... 2 6
I. Electrical Load Data ......................................... 2 6
J . R e f e r e n c e s  .............................................. 2 7
1. Existing Data: ......................................... 2 7
2. Data Supplied with this Service Bulletin: ........................... 2 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 7
K. Publications Affected ........................................ 2 7
L. Interchangeability and Intermixability of Parts ........................... 2 8
M. Software Accomplishment Summary ................................ 2 8
2. MATERIAL INFORMATION ........................................ 2 9
A. Material - Price and Availability ................................... 2 9
B. Industry Support Information .................................... 2 9
C . P a r t s  N e c e s s a r y  f o r  E a c h  A i r p l a n e  ................................. 2 9
1 . K i t s / P a r t s  ............................................ 2 9
2. Parts and Materials Supplied by the Operator ........................ 2 9
3. Parts Modified and Reidentified ................................ 2 9
4. Parts Removed and Not Replaced .............................. 2 9
D. Parts Necessary to Change Spares ................................. 3 0
E. Special Tooling - Price and Availability ............................... 3 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1
A. GENERAL INFORMATION ..................................... 3 1
B. WORK INSTRUCTIONS ....................................... 3 3
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION [Group 1-2,
Configuration 1; Group 3, 5] .................................. 3 6
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION [Group
1-2, Configuration 1; Group 3, 5] ............................... 4 3
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION [Group 1-2,
Configuration 2; Group 4, 6] .................................. 5 0
FIGURE 4: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION [Group
1-2, Configuration 2; Group 4, 6] ............................... 5 6
FIGURE 5: LEFT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – SURFACE HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, 4] ............ 6 2
FIGURE 6: RIGHT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – SURFACE HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, 4] ............ 6 5
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FIGURE 7: LEFT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – OPEN HOLE HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, 4] ............ 6 8
FIGURE 8: RIGHT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – OPEN HOLE HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, 4] ............ 7 0
FIGURE 9: LEFT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – RIVET INSTALLATION
[Group 1] ............................................ 7 2
FIGURE 10: RIGHT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – RIVET
INSTALLATION [Group 1] ................................... 7 4
FIGURE 11: LEFT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – BOLT INSTALLATION
[Group 4] ............................................ 7 6
FIGURE 12: RIGHT SIDE STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB – BOLT
INSTALLATION [Group 4] ................................... 7 8
APPENDIX A: LOGIC DIAGRAM FOR TABLE 1 - MODIFICATION AND INSPECTION [Group 1, 4] . . . 80
APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 - DETAILED INSPECTION [Group 2-3, 5-6] ....... 8 4
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Commercial
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2887Original Issue: December 02, 2015
ATA System: 5315
SUBJECT: FUSELAGE - Nose Wheel Well - Body Structure Reinforcement 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 to do the modification required in accordance with service bulletin
747-53A2293 Areas 1, 3 and 4. If the modification work has been previously accomplished in accordance with
service bulletin 747-53A2293, then there is no further modification work required. The modification provided in
service bulletin 747-53A2293 for Areas 1, 3, and 4 must be completed to meet the intent of Widespread Fatigue
Damage (WFD) methods. This service bulletin also gives instructions to inspect for fatigue cracking in the Nose
Wheel Well Body Structure. If the inspections given in this service bulletin are not done, fatigue cracking could
remain undetected. Such fatigue cracking could adversely affect the structural integrity of the airplane.
Boeing Service Related Problem (SRP) 747-SRP-53-0479 is 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 ChangesNoWeight 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)
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ReferenceAffectedPlanning Data
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Group 1, 4:
Do the modification in accordance with service bulletin 747-53A2293 at the times given in Paragraph 1.E.,
Compliance of this service bulletin. If the modification work has been done in accordance with service bulletin
747-53A2293, no further modification work is required. Do a detailed inspection of the vertical beams, vertical
beam clips, main deck floor beams and the fore aft stiffeners for cracks and do a surface or open hole High
Frequency Eddy Current (HFEC) inspection of the vertical beams outer chord and web for cracks. If any crack
is found, do a detailed inspection of adjacent structure to determine the full extent of the damage, contact Boeing
for repair instructions and do the repair, then repeat detailed inspection and surface or open hole HFEC inspections
at the times given in Paragraph 1.E., Compliance. If no crack is found, repeat detailed inspection and surface
or open hole HFEC inspections at the times given in Paragraph 1.E., Compliance.
Group 2-3, 5-6:
Do a detailed inspection of the vertical beams, vertical beam clips, main deck floor beams and the stiffeners for
cracks. If any crack is found, do a detailed inspection of adjacent structure to determine the full extent of the
damage, contact The Boeing Company for repair instructions and do the repair, then repeat detailed inspections
for cracks at the times given in Paragraph 1.E., Compliance. If no crack is found, repeat detailed inspections
for cracks at the times given in Paragraph 1.E., Compliance.
EFFECTIVITY
747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F, 747SP, 747SR Airplanes in eight
groups. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an additional 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 Directive AD 90-06-14 R1 is related to this service bulletin.
The effective date of AD 90-06-14 R1 is April 24, 1990.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2001-14-18 is related to this service bulletin.
The effective date of AD 2001-14-18 is August 30, 2001.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspections given in this service bulletin.
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MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
250
STA
280
STA
STA  300  STA  STA
CANTED STA  260  340  RBL 10~  RBL 22  320  340
LBL 10~
LBL 22~
GROUP 2, 3, 5, 6
DO A DETAILED INSPECTION
OF THE VERTICAL BEAMS
VERTICAL BEAM CLIPS, MAIN
DECK FLOOR BEAMS AND THE
STIFFENERS FOR CRACKS.
IF ANY CRACK IS FOUND, DO A
DETAILED INSPECTION OF
ADJACENT STRUCTURE TO
DETERMINE THE FULL EXTENT
OF THE DAMAGE, CONTACT
BOEING FOR REPAIR INSTRUCTIONS AND
DO THE REPAIR, THEN REPEAT DETAILED
INSPECTIONS FOR CRACKS AT THE
TIMES GIVEN IN PARAGRAPH 1.E.,
COMPLIANCE. IF NO CRACK IS FOUND,
REPEAT DETAILED INSPECTIONS FOR
CRACKS AT THE TIMES GIVEN IN
PARAGRAPH 1.E., COMPLIANCE
GROUP 1, 4
DO THE MODIFICATION IN ACCORDANCE WITH SERVICE BULLETIN  LEFT SIDE SHOWN
(SB) 747-53A2293 AT THE TIMES GIVEN IN PARAGRAPH 1.E.,  RIGHT SIDE OPPOSITE
COMPLIANCE OF THIS SERVICE BULLETIN. IF THE MODIFICATION
WORK HAS BEEN DONE IN ACCORDANCE WITH SERVICE BULLETIN
747-53A2293, NO FURTHER MODIFICATION WORK IS REQUIRED. DO A
DETAILED INSPECTION OF THE VERTICAL BEAMS, VERTICAL BEAM
CLIPS, MAIN DECK FLOOR BEAMS AND THE FORE AFT STIFFENERS
FOR CRACKS  A SURFACE OR OPEN HOLE HIGH FREQUENCY
EDDY CURREI  SPECTION OF THE VERTICAL BEAMS OUTER
CHORD,  RACKS. IF ANY CRACK IS FOUND, DO A
DETAILED INSPE  I OF ADJACENT STRUCTURE TO DETERMINE
THE FU  IF THE DAMAGE, CONTACT BOEING FOR REPAIR
INSTRUC  DO THE REPAIR, THEN REPEAT DETAILED
INSPEC  OR OPEN HOLE HFEC INSPECTIONS AT
THE TIMES GIVEN IN PARAGRAPH 1.E., COMPLIANCE. IF NO CRACK IS
FOUND, REPEAT DETAILED INSPECTION AND SURFACE OR OPEN  HOLE HFEC INSPECTIONS AT THE TIMES GIVEN IN PARAGRAPH 1.E.,  2429723
COMPLIANCE.
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### Page 9

Commercial
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2887
Original Issue: December 02, 2015
ATA System: 5315
SUBJECT: FUSELAGE - Nose Wheel Well - Body Structure Reinforcement 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
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400,
-400D, -400F, 747SP, and 747SR airplanes, line numbers 1-1419, in six Groups. The Variable
Numbers and Group Information for the applicable airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
747-100, -100B, -100B SUD, -200B, -300, 747SP and 747SR
airplanes, line numbers 1-685.
-1
747-100, -100B, -100B SUD, -200B, -300, 747SP and 747SR
airplanes, line numbers 1-685, which have reinforcing straps installed
in accordance with 747-53-2272.
1
747-100, -100B, -100B SUD, -200B, -300, 747SP and 747SR
airplanes, line numbers 1-685, which don't have reinforcing straps
installed in accordance with 747-53-2272.
2
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DESCRIPTIONCONFIGURATIONGROUP
747-300 airplanes, line numbers 686-695.-2
747-300 airplanes, line numbers 686-695 with reinforcing straps
installed in accordance with 747-53-2272.
1
747-300 airplanes, line numbers 686-695 without reinforcing straps
installed in accordance with 747-53-2272.
2
747-200B, -300, -400, and -400D airplanes, line numbers 696-1419.-3
747-200C and -200F airplanes, line numbers 1-685.-4
747-200C, -200F, and -400F airplanes, line numbers 696-1419.-5
747-200F airplanes, line numbers 686-695.-6
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SP, 747SR
GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
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GroupVariable Number
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
1RB411 - RB412
3RB413
3RB421
1RB601 - RB607
1RB681 - RB697
1RB711
1RB721 - RB723
1RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD144
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GroupVariable Number
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD227
1RD231 - RD234
3RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
1RD301 - RD302
1RD311
1RD351 - RD358
1RD361 - RD366
1RD381 - RD383
1RD411 - RD414
1RD421 - RD426
1RD431 - RD435
1RD441 - RD442
1RD451 - RD456
1RD461
1RD471 - RD475
1RD513 - RD519
1RD531 - RD533
1RD551
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD601 - RD607
1RD621 - RD623
1RD641 - RD649
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GroupVariable Number
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791
3RD792
1RE001
3RF001 - RF006
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
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GroupVariable Number
4RJ321
5RJ322
4RJ331 - RJ333
5RL401 - RL403
5RL411 - RL436
5RL451 - RL456
5RL461 - RL462
5RL471 - RL481
5RL491 - RL492
5RL501 - RL502
5RL511 - RL516
5RL521 - RL522
5RL531 - RL534
5RL551
5RL561 - RL568
5RL571 - RL572
5RL576 - RL577
5RL579
5RL581 - RL586
5RL651 - RL655
5RL671 - RL675
5RL681 - RL684
5RL751 - RL752
3RM001 - RM007
3RM010 - RM013
3RM021 - RM024
3RM026 - RM030
3RM036 - RM045
3RM051 - RM053
3RM071
3RM081 - RM084
3RM091
3RM096 - RM097
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GroupVariable Number
3RM116 - RM117
3RM126 - RM132
3RM136 - RM147
3RM156 - RM158
3RM166 - RM177
3RM191 - RM192
3RM231 - RM233
3RM241 - RM246
3RM261 - RM264
3RM316 - RM318
3RM331 - RM333
3RM341
3RM351 - RM355
3RM366 - RM367
3RM401 - RM403
3RM426
3RM431
3RM441 - RM443
3RM445
3RM801 - RM803
3RM811 - RM813
5RM851 - RM859
5RM861 - RM863
5RM871 - RM899
5RM901 - RM906
5RM911
4RR001 - RR005
4RR021 - RR023
5RR024 - RR025
4RR031
4RR201 - RR205
5RR206
4RR221 - RR226
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GroupVariable Number
4RR261 - RR267
4RR301 - RR306
5RR307 - RR310
4RR331 - RR332
4RR336
4RR341 - RR345
4RR361 - RR362
4RR421 - RR422
4RR431 - RR432
6RR441
5RR442
5RR451
4RR501 - RR504
4RR521
5RR522
5RR526
4RR531
4RR551 - RR553
6RR554
5RR555 - RR556
4RR561
5RR566
5RR701
5RR721 - RR724
5RR746 - RR748
5RR851 - RR856
5RR861 - RR862
5RR951 - RR952
1RS001 - RS002
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
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GroupVariable Number
1RS251 - RS258
2RS259
3RS263
2RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS304
2RS305
3RS306
1RS311 - RS320
3RS331 - RS333
1RS341
2RS342
1RS699
1RS701 - RS702
2RS703
1RS711 - RS713
1RS721 - RS722
3RS731 - RS732
1RS741 - RS743
1RS751 - RS752
1RS761
3RS762
1RS771
3RS781 - RS782
3RS786
3RT001 - RT014
3RT021 - RT022
3RT031 - RT035
3RT041 - RT047
3RT061
3RT071 - RT075
3RT101 - RT103
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GroupVariable Number
3RT121
3RT131 - RT137
3RT151 - RT152
3RT161 - RT168
3RT401 - RT412
3RT431 - RT447
3RT451 - RT469
3RT471 - RT499
3RT501 - RT535
3RT551 - RT568
3RT571 - RT591
3RT601 - RT657
3RT671 - RT673
3RT681 - RT682
3RT691 - RT699
3RT701 - RT704
3RT711 - RT717
3RT741 - RT757
3RT776 - RT777
3RT781 - RT784
3RT801 - RT803
3RT811 - RT814
3RT831 - RT837
3RT861 - RT864
3RT876 - RT880
3RT931 - RT932
3RT945 - RT949
3RT951 - RT955
3RT966 - RT967
3RU001 - RU006
3RU016 - RU017
3RU031 - RU032
3RU051 - RU052
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GroupVariable Number
3RU059 - RU062
3RU081 - RU083
3RU101 - RU102
3RU121 - RU132
3RU801 - RU809
3RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to do the modification required in accordance with service bulletin
747-53A2293 Areas 1, 3 and 4. If the modification work has been previously accomplished in accordance
with service bulletin 747-53A2293, then there is no further modification work required. The modification
provided in service bulletin 747-53A2293 for Areas 1, 3, and 4 must be completed to meet the intent
of Widespread Fatigue Damage (WFD) methods. This service bulletin also gives instructions to inspect
for fatigue cracking in the Nose Wheel Well Body Structure. If the inspections given in this service
bulletin are not done, fatigue cracking could remain undetected. Such fatigue cracking could adversely
affect the structural integrity of the airplane.
Boeing Service Related Problem (SRP) 747-SRP-53-0479 is related to this service bulletin.
This service bulletin is related to the following service bulletins:
TitleBoeing Service Bulletin
FUSELAGE - Nose Section 41 - Body Frame Structure Inspections and Crack
Repairs
747-53A2265
FUSELAGE-NOSE SECTION 41 BODY FRAME STRUCTURE REPLACE-
MENT AND REINFORCEMENT
747-53A2272
FUSELAGE - NOSE WHEEL WELL - BODY STRUCTURE REINFORCEMENT747-53A2293
FUSELAGE - MAIN FRAME - WHEEL WELLS NOSE WHEEL WELL SIDE-
WALL AND VERTICAL BEAM INSPECTION AND REPAIR
747-53A2338
FUSELAGE - Inspections Based On Fatigue Test Results747-53A2349
FUSELAGE - Main Frame - Inspections Based on Fatigue Test Results747-53A2500
FUSELAGE - Main Frame - Nose Wheel Well Side Panel and Top Panel -
Web and Stiffener Inspection
747-53A2465
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TitleBoeing Service Bulletin
FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and
Stiffener Replacement
747-53A2562
FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and
Stiffener Replacement
747-53A2808
FUSELAGE - Nose Section 41 - Body Frame Structure Inspections and Crack
Repairs
747-53A2732
FUSELAGE - Nose Section 41 - Body Frame Structure Inspections and Crack
Repairs
747-53A2753
D. Description
Group 1, 4:
Do the modification in accordance with service bulletin 747-53A2293 at the times given in Paragraph
1.E., Compliance of this service bulletin. If the modification work has been done in accordance with
service bulletin 747-53A2293, no further modification work is required. Do a detailed inspection of the
vertical beams, vertical beam clips, main deck floor beams and the fore aft stiffeners for cracks and do
a surface or open hole High Frequency Eddy Current (HFEC) inspection of the vertical beams outer
chord and web for cracks. If any crack is found, do a detailed inspection of adjacent structure to
determine the full extent of the damage, contact The Boeing Company for repair instructions and do
the repair, then repeat detailed inspection and surface or open hole HFEC inspections at the times
given in Paragraph 1.E., Compliance. If no crack is found, repeat detailed inspection and surface or
open hole HFEC inspections at the times given in Paragraph 1.E., Compliance.
Group 2-3, 5-6:
Do a detailed inspection of the vertical beams, vertical beam clips, main deck floor beams and the
stiffeners for cracks. If any crack is found, do a detailed inspection of adjacent structure to determine
the full extent of the damage, contact The Boeing Company for repair instructions and do the repair,
then repeat detailed inspections for cracks at the times given in Paragraph 1.E., Compliance. If no
crack is found, repeat detailed inspections for cracks at the times given in Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
113, 114747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300,
747SP, 747SR
Group 2:
Affected Maintenance Zones
ZoneModel
113, 114747-300
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Group 3:
Affected Maintenance Zones
ZoneModel
113, 114747-200B, 747-300, 747-400,
747-400D
Group 4:
Affected Maintenance Zones
ZoneModel
113, 114747-200C, 747-200F
Group 5:
Affected Maintenance Zones
ZoneModel
113, 114747-200C, 747-200F, 747-400F
Group 6:
Affected Maintenance Zones
ZoneModel
113, 114747-200F
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an additional 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 Directive AD 90-06-14 R1 is related to this service
bulletin. The effective date of AD 90-06-14 R1 is April 24, 1990.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2001-14-18 is related to this service
bulletin. The effective date of AD 2001-14-18 is August 30, 2001.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
A and APPENDIX B.
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Group 1, 4:
Table 1 - Modification and Inspection
Repeat Inter-
val (Not to Ex-
ceed)
Compliance time (Whichever is later)ActionCondition
-Within 4 years after the original
issue date of this service bulletin.
Before 20,000 to-
tal flight cycles.
Do PART 1: MODIFI-
CATION.
All airplanes
-Within 12
months after
the original is-
sue date of this
service bul-
letin.
Within 3,000
flight cycles after
PART 1: MODIFI-
CATION.
Before 25,000 to-
tal flight cycles.
Do PART 2: NOSE
WHEEL WELL BODY
STRUCTURE DE-
TAILED INSPEC-
TION for any crack.
All airplanes that
have done PART
1: MODIFICA-
TION
-Within 2,200 flight cycles after the
original issue date of this service
bulletin.
Before 30,000 to-
tal flight cycles.
Do PART 3: STA
280-320 VERTICAL
BEAM OUTER
CHORD AND WEB
SURFACE OR OPEN
HOLE HIGH FRE-
QUENCY EDDY
CURRENT (HFEC)
INSPECTION for any
crack.
-Before further flight.CONDITION 1 (AC-
TION 1): Do PART 4:
SECONDARY IN-
SPECTION AND RE-
PAIR.
CONDITION 1:
ANY CRACK
FOUND during
PART 2.
3,000 flight cy-
cles.
-CONDITION 1 (AC-
TION 2): Repeat
PART 2: NOSE
WHEEL WELL BODY
STRUCTURE DE-
TAILED INSPEC-
TION for any crack at
unrepaired areas on-
ly.
3,000 flight cy-
cles.
-Repeat PART 2:
NOSE WHEEL WELL
BODY STRUCTURE
DETAILED INSPEC-
TION for any crack at
unrepaired areas on-
ly.
CONDITION 2:
NO CRACK
FOUND during
PART 2.
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Group 1, 4:
Table 1 - Modification and Inspection
Repeat Inter-
val (Not to Ex-
ceed)
Compliance time (Whichever is later)ActionCondition
-Before further flight.CONDITION 3 (AC-
TION 1): Do PART 4:
SECONDARY IN-
SPECTION AND RE-
PAIR.
CONDITION 3:
SURFACE HIGH
FREQUENCY
EDDY CUR-
RENT (HFEC)
INSPECTION
DONE. ANY
CRACK FOUND
during PART 3.
3,000 flight cy-
cles.
-CONDITION 3 (AC-
TION 2): Repeat
PART 3: STA 280-
320 VERTICAL
BEAM OUTER
CHORD AND WEB
SURFACE OR OPEN
HOLE HIGH FRE-
QUENCY EDDY
CURRENT (HFEC)
INSPECTION for any
crack at unrepaired
areas only.
3,000 flight cy-
cles.
-Repeat PART 3: STA
280-320 VERTICAL
BEAM OUTER
CHORD AND WEB
SURFACE OR OPEN
HOLE HIGH FRE-
QUENCY EDDY
CURRENT (HFEC)
INSPECTION for any
crack at unrepaired
areas only.
CONDITION 4:
SURFACE HIGH
FREQUENCY
EDDY CUR-
RENT (HFEC)
INSPECTION
DONE. NO
CRACK FOUND
during PART 3.
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Group 1, 4:
Table 1 - Modification and Inspection
Repeat Inter-
val (Not to Ex-
ceed)
Compliance time (Whichever is later)ActionCondition
-Before further flight.CONDITION 5 (AC-
TION 1): Do PART 4:
SECONDARY IN-
SPECTION AND RE-
PAIR.
CONDITION 5:
OPEN HOLE
HIGH FREQUEN-
CY EDDY CUR-
RENT (HFEC)
INSPECTION
DONE. ANY
CRACK FOUND
during PART 3.
6,000 flight cy-
cles.
-CONDITION 5 (AC-
TION 2): Repeat
PART 3: STA 280-
320 VERTICAL
BEAM OUTER
CHORD AND WEB
SURFACE OR OPEN
HOLE HIGH FRE-
QUENCY EDDY
CURRENT (HFEC)
INSPECTION for any
crack at unrepaired
areas only.
-Before further flight.CONDITION 6 (AC-
TION 1): Install new
fasteners.
CONDITION 6:
OPEN HOLE
HIGH FREQUEN-
CY EDDY CUR-
RENT (HFEC)
INSPECTION
DONE. NO
CRACK FOUND
during PART 3.
6,000 flight cy-
cles.
-CONDITION 6 (AC-
TION 2): Repeat
PART 3: STA 280-
320 VERTICAL
BEAM OUTER
CHORD AND WEB
SURFACE OR OPEN
HOLE HIGH FRE-
QUENCY EDDY
CURRENT (HFEC)
INSPECTION for any
crack at unrepaired
areas only.
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Group 2-3, 5-6:
Table 2 - Detailed Inspection
Repeat Interval
(Not to Exceed)
Compliance time (Whichever is later)ActionCondition
-Within 3,000 flight
cycles after the
original issue date
of this service bul-
letin.
Before 25,000 total
flight cycles.
Do PART 2: NOSE
WHEEL WELL
BODY STRUC-
TURE DETAILED
INSPECTION for
any crack.
All airplanes
-Before further flight.CONDITION 1
(ACTION 1): Do
PART 4: SEC-
ONDARY INSPEC-
TION AND RE-
PAIR.
CONDITION 1:
ANY CRACK
FOUND during
PART 2.
3,000 flight cycles.-CONDITION 1
(ACTION 2): Re-
peat PART 2:
NOSE WHEEL
WELL BODY
STRUCTURE DE-
TAILED INSPEC-
TION for any crack
at unrepaired areas
only.
3,000 flight cycles.-Repeat PART 2:
NOSE WHEEL
WELL BODY
STRUCTURE DE-
TAILED INSPEC-
TION for any crack
at unrepaired areas
only.
CONDITION 2: NO
CRACK FOUND
during PART 2.
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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G. Manpower
The following breakdown of manpower requirements is suggested as a guide to assist operators in
planning and accomplishing this modification. This estimate is for direct labor performed by an
experienced crew. It does not include setup, planning, familiarization, cure time, part fabrication, tool
acquisition, or lost time. Factor this estimate as necessary based on your own experience.
The manpower estimates are given for the following options:
• Inspection for each area
• Modification for each area
• Inspection for each inspection interval
• Modification for each airplane group
Group 1, 4:
Elapsed HoursTask HoursNumber of PersonsTask
4.008.002Open Access
70.00140.002Detailed Inspection
1.553.102Surface HFEC In-
spection
1.553.102Open Hole HFEC In-
spection
4.008.002Close Access
81.10162.20TOTAL FOR EACH AIRPLANE
Group 2-3, 5-6:
Elapsed HoursTask HoursNumber of PersonsTask
4.008.002Open Access
70.00140.002Detailed Inspection
4.008.002Close Access
78.00156.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not affected.
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J. References
1. Existing Data:
a. Boeing Service Bulletin 747-53A2265, 747-53A2272, 747-53A2293, 747-53A2338,
747-53A2349, 747-53A2465, 747-53A2500, 747-53A2562, 747-53A2732, 747-53A2753,
747-53A2808
b. Boeing Service Letter 747-SL-51-048
c. Boeing Service Related Problem (SRP) 747-SRP-53-0479
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2001-14-18, 90-06-14 R1
e. Service Bulletin Index D6-30300
f. Standard Overhaul Practices Manual (SOPM) 20-50-01, 20-50-19
g. 747 Non-Destructive Testing (NDT) Manual Part 6, Section 51-00-00, Part 6, Section 53-30-19
h. 747-100/200/300 Aircraft Maintenance Manual (AMM) 25-00-00
i. 747-100/200/300 Structural Repair Manual (SRM) 51-30-02
j. 747-400 Aircraft Maintenance Manual (AMM) 25-00-00
k. 747-SP Structural Repair Manual (SRM) 51-30-02
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Frame Installation - Body Station 30065B01708
Frame Installation - Body Station 32065B01709
Side Panel Installation65B07942
The table above lists applicable drawings used to prepare this service bulletin. These drawings
are not necessary to make the specified changes, and are not supplied with this service bulletin.
The drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
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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
None.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 1:
NotesNameQTYPart Number /
Specification
Or BACR15BB10AD.Rivet12BACR15ET9D
Or BACR15ET9D.Rivet12BACR15BB10AD
Group 4:
NotesNameQTYPart Number /
Specification
Or BACB30MY6K6Y.Bolt12BACB30MY6K6X
Or BACB30MY6K6X.Bolt12BACB30MY6K6Y
To be installed with bolt
BACB30MY6K6X.
Collar12BACC30M6
To be installed with bolt
BACB30MY6K6Y.
Collar12BACC30AC6
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
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D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 747
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
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7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
8. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
9. Refer to Appendix A and B for logic diagrams. Logic diagrams are provided as an
aid only. Information contained in Paragraph 1.E., Compliance is the primary source
for compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
10. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
11. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
12. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
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B. WORK INSTRUCTIONS
1. Get access to nose wheel well top and side wall panels. Remove and keep insulation blankets.
Refer to 747-100/200/300 AMM 25-00-00, or 747-400 AMM 25-00-00 as accepted procedures.
2. Group 1, 4:
RC- Do PART 1: MODIFICATION.
3. RC- Do PART 2: NOSE WHEEL WELL BODY STRUCTURE DETAILED INSPECTION for any
crack.
a. CONDITION 1: ANY CRACK FOUND during PART 2.
(1) CONDITION 1 (ACTION 1): Do PART 4: SECONDARY INSPECTION AND REPAIR.
(2) CONDITION 1 (ACTION 2): Repeat PART 2: NOSE WHEEL WELL BODY STRUCTURE
DETAILED INSPECTION for any crack at unrepaired areas only.
b. CONDITION 2: NO CRACK FOUND during PART 2.
(1) Repeat PART 2: NOSE WHEEL WELL BODY STRUCTURE DETAILED INSPECTION
for any crack at unrepaired locations only.
4. Group 1, 4:
RC- Do PART 3: STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB SURFACE OR
OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION for any crack.
a. CONDITION 3: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
DONE. ANY CRACK FOUND during PART 3.
(1) CONDITION 3 (ACTION 1): Do PART 4: SECONDARY INSPECTION AND REPAIR.
(2) CONDITION 3 (ACTION 2): Repeat PART 3: STA 280-320 VERTICAL BEAM OUTER
CHORD AND WEB SURFACE OR OPEN HOLE HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any crack at unrepaired areas only.
b. CONDITION 4: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
DONE. NO CRACK FOUND during PART 3.
(1) Repeat PART 3: STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB SURFACE
OR OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION for any
crack at unrepaired areas only.
c. CONDITION 5: OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
DONE. ANY CRACK FOUND during PART 3.
(1) CONDITION 5 (ACTION 1): Do PART 4: SECONDARY INSPECTION AND REPAIR.
(2) CONDITION 5 (ACTION 2): Repeat PART 3: STA 280-320 VERTICAL BEAM OUTER
CHORD AND WEB SURFACE OR OPEN HOLE HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any crack at unrepaired areas only.
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ALERTALERT

### Page 34

d. CONDITION 6: OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
DONE. NO CRACK FOUND during PART 3.
(1) Group 1:
CONDITION 6 (ACTION 1): Install new fasteners in accordance with FIGURE 9 and
FIGURE 10.
(2) Group 4:
CONDITION 6 (ACTION 1): Install new fasteners in accordance with FIGURE 11 and
FIGURE 12.
(3) CONDITION 6 (ACTION 2): Repeat PART 3: STA 280-320 VERTICAL BEAM OUTER
CHORD AND WEB SURFACE OR OPEN HOLE HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any crack at unrepaired areas only.
5. Install kept insulation blankets. Refer to 747-100/200/300 AMM 25-00-00, or 747-400 AMM 25-00-00
as accepted procedures.
6. Put the airplane back to serviceable condition.
Group 1, 4:
PART 1: MODIFICATION
1. Do the modification in accordance with service bulletin (SB) 747-53A2293 for areas 1, 3 and 4 in
accordance with the time given in Paragraph 1.E., Compliance of this Service Bulletin. If the
modification work was previously done in accordance with SB 747-53A2293, then there is no
further modification work required.
NOTE: In SB 747-53A2293, the Area 4 modification requires the same access as the Area 3
modification.
PART 2: NOSE WHEEL WELL BODY STRUCTURE DETAILED INSPECTION
1. Group 1-2, Configuration 1; Group 3, 5:
Do a detailed inspection of the left side nose wheel well body structure for any crack in accordance
with FIGURE 1.
2. Group 1-2, Configuration 1; Group 3, 5:
Do a detailed inspection of the right side nose wheel well body structure for any crack in accordance
with FIGURE 2.
3. Group 1-2, Configuration 2; Group 4, 6:
Do a detailed inspection of the left side nose wheel well body structure for any crack in accordance
with FIGURE 3.
4. Group 1-2, Configuration 2; Group 4, 6:
Do a detailed inspection of the right side nose wheel well body structure for any crack in accordance
with FIGURE 4.
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PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 747-53A2887
ALERTALERT

### Page 35

Group 1, 4:
PART 3: STA 280-320 VERTICAL BEAM OUTER CHORD AND WEB SURFACE OR OPEN HOLE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
1. Do one of the following options:
a. OPTION 1:
(1) ACTION 1: Do a Surface HFEC Inspection of the left side STA 280-320 vertical beam
outer chord and web for any crack in accordance with FIGURE 5.
(2) ACTION 2: Do a Surface HFEC Inspection of the right side STA 280-320 vertical beam
outer chord and web for any crack in accordance with FIGURE 6.
b. OPTION 2:
(1) ACTION 1: Do an Open Hole HFEC Inspection of the left side STA 280-320 vertical beam
outer chord and web for any crack in accordance with FIGURE 7.
(2) ACTION 2: Do an Open Hole HFEC Inspection of the right side STA 280-320 vertical
beam outer chord and web for any crack in accordance with FIGURE 8.
PART 4: SECONDARY INSPECTION AND REPAIR
1. Do a detailed inspection for any crack within 20 inches of the original crack, to determine the full
extent of the damage.
2. Contact The Boeing Company for repair instructions and do the repair.
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ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
This Figure applies only to: Group 1-2, Configuration 1; Group 3, 5.
STA
260
STA
260  / STA
CANTED STA  1280
340  /STA
300
STA
RBL 22  340
RBL 10
LBL 10 -
LBL 22 ~
2454876
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 1 OF 7)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
280.
300
FLOORBEAM
TOP PANEL WEB
FORE AFT
STIFFENER
FORE AFT
STIFFENER
- BL
22
FORE AFT  STIFFENER (1  INTERCOSTAL
TYPICAL
CRACK
LOCATION  1 CLIP
POTENTIAL CRACK  TYPICAL STA 280-STA 300.  LBL 10 AND 22
LOCATION IN FORE AFT
STIFFENER
• INTERCOSTAL
BL
10
22
TYPICAL
U TOP PANEL  2454879
WEB
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 2 OF 7)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
® CHORD
1 SIDE WALL
VERTICAL  PANEL WEB
BEAM
VERTICAL
BEAM CLIP
TYPICAL CRACKS
IN VERTICAL
BEAM WEB
TYPICAL
INSULATION
BLANKET
STANDOFF/TOOL
HOLE LOCATION
2) HORIZONTAL
STIFFENER
VERTICAL (
BEAM CLIP
CHORD 1  STATIONS 260 THROUGH 320  (TYPICAL)
D
2454881
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 3 OF 7)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
MAIN DECK FLOOR BEAM
(AT STA 280, 300 AND 320 ONLY
VERTICAL BEAM 2
S-40L
S-41L
INBD
TYPICAL STATIONS 260 TO 320
A-A
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 4 OF 7)
Original Issue: December 02, 2015
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Work - See page 1 for details.  39 of 85

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
280
300
320
12.0
12.0
3) LOWER CHORI  FLOOR BEAN
® STRAP
STA
280
300
320
2) BEAM OUTER  VERTICAL
CHORD
TYPICAL
VERTICAL
BEAM
TYPICAL
CRACK
VERTICAL  BEAM WEB  ₴
VERTICAL BEAM (2
INNER CHORD
LOOF (3  FAM
LOWER CHORD 3  FLOOR BEAM  2454887
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 5 OF 7)
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PROPRIETARY - Copyright © Unpublished
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### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fore Aft StiffenersInspect1
(b)--ClipsInspect
(c)--IntercostalInspect
(d)--Floor BeamInspect
(e)--Top Panel WebInspect
(f)--Vertical BeamInspect2
(f)--Vertical Beam WebInspect
(f)--Vertical Beam ChordInspect
(g)--Vertical Beam ClipsInspect
(h)--Horizontal StiffenersInspect
(i)--Main Deck Floor
Beams
Inspect3
(j)--Floor Beam Lower
Chords
Inspect
(k)--StrapsInspect
(a) Do a detailed inspection of the fore aft stiffeners, between Body Station (STA) 280 and STA 300, Left
Buttock Line (LBL) 10 and LBL 22, common to the top panel. Inspect from the top side, around all fastener
heads and in the stiffeners fillet radius, common to the horizontal flange attached to the nose wheel well
top panel web.
(b) Do a detailed inspection of all attachments of the clips to the fore aft stiffeners.
(c) Do a detailed inspection of the intercostals in the area surrounding the connection to the clip and the fore
aft stiffeners.
(d) Do a detailed inspection of the main deck floor beams in the area surrounding the connection to the fore
aft stiffeners.
(e) Do a detailed inspection of the top panel web in the area surrounding the connection to the fore aft stiff-
eners.
(f) Do a detailed inspection of the full length of the vertical beams, vertical beam webs and vertical beam
chords. Inspect both the forward and aft side of the beams. Inspect the joints between the vertical beams
and the frames and between the vertical beams and the main deck floor beams.
(g) Do a detailed inspection of all attachments of the vertical beam clips to the vertical beams, from inside
the fuselage.
(h) Do a detailed inspection of the horizontal stiffeners in the area surrounding the connection to the vertical
beams.
(i) Do a detailed inspection of the main deck floor beams, 12 inches outboard of the vertical beam to 12
inches inboard of the vertical beam. Inspect both the forward and aft side of the beams.
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 6 OF 7)
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BOEING SERVICE BULLETIN 747-53A2887
ALERTALERT

### Page 42

More DataQtyIdentificationNameTaskStep
(j) Do a detailed inspection of the floor beam lower chords, 12 inches outboard of the vertical beam to 12
inches inboard of the vertical beam. Inspect both the forward and aft side of the chord.
(k) Do a detailed inspection of the floor beam lower chords in the area around the ends of the reinforcing
straps.
FIGURE 1: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
This Figure applies only to: Group 1-2, Configuration 1; Group 3, 5.
STA
260
STA
260
STA  _ CANTED
340
280
STA
300
STA
340  32  - LBL 22
- LBL 10
-RBL 10
RBL 22
2455847
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 1 OF 7)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
280,
300
FLOORBEAM
TOP PANEL WEB
FORE AFT
STIFFENER
FORE AFT
STIFFENER
BL
22
FORE AFT
INTERCOSTAL  STIFFENER
TYPICAL
CRACK
BI  LOCATION
10
TYPICAL STA 280-STA 300,  POTENTIAL CRACK
RBL 10 AND 22  LOCATION IN
FORE AFT STIFFENER
INTERCOSTAL
1 TOP PANEL  2455863
WEB
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 2 OF 7)
Original Issue: December 02, 2015
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### Page 45 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
CHORD
SIDE WALL
PANEL WEB
VERTICAL
BEAM
2) VERTICAL
BEAM CLIP
TYPICAL CRACKS
IN VERTICAL
BEAM WEB
TYPICAL
INSULATION
BLANKET
STANDOFF/TOOL
HOLE LOCATION
HORIZONTAL
STIFFENER
2) VERTICAL
BEAM CLIF
STATIONS 260 THROUGH 320  CHORD
(TYPICAL
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 3 OF 7)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
MAIN DECK FLOOR BEAM
(AT STA 230, 300 AND 320 ONLY)
2) VERTICAL BEAM
S-39R
S-40R
S-41R
INBD
TYPICAL STATIONS 260 TO 320  2455880
A-A
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 4 OF 7)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
280
300
320
12.0
FLOOR BEAM
LOWER CHORD
STRAP
VERTICAL
BEAM OUTER 2
CHORD
TYPICAL  BEAM  VERTICAL
TYPICAL
CRACK
VERTICAL
BEAM WEB
2) VERTICAL BEA  INNER CHORI
3 BEAM  FLOOR
FLOOR BEAI  2455892
/LOWER CHOR
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 5 OF 7)
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### Page 48

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fore Aft StiffenersInspect1
(b)--ClipsInspect
(c)--IntercostalInspect
(d)--Floor BeamInspect
(e)--Top Panel WebInspect
(f)--Vertical BeamInspect2
(f)--Vertical Beam WebInspect
(f)--Vertical Beam ChordInspect
(g)--Vertical Beam ClipsInspect
(h)--Horizontal StiffenersInspect
(i)--Main Deck Floor
Beams
Inspect3
(j)--Floor Beam Lower
Chords
Inspect
(k)--StrapsInspect
(a) Do a detailed inspection of the fore aft stiffeners, between Body Station (STA) 280 and STA 300, Right
Buttock Line (RBL) 10 and RBL 22, common to the top panel. Inspect from the top side, around all fastener
heads and in the stiffeners fillet radius, common to the horizontal flange attached to the nose wheel well
top panel web.
(b) Do a detailed inspection of all attachments of the clips to the fore aft stiffeners.
(c) Do a detailed inspection of the intercostals in the area surrounding the connection to the clip and the fore
aft stiffeners.
(d) Do a detailed inspection of the main deck floor beams in the area surrounding the connection to the fore
aft stiffeners.
(e) Do a detailed inspection of the top panel web in the area surrounding the connection to the fore aft stiff-
eners.
(f) Do a detailed inspection of the full length of the vertical beams, vertical beam webs and vertical beam
chords. Inspect both the forward and aft side of the beams. Inspect the joints between the vertical beams
and the frames and between the vertical beams and the main deck floor beams.
(g) Do a detailed inspection of all attachments of the vertical beam clips to the vertical beams, from inside
the fuselage.
(h) Do a detailed inspection of the horizontal stiffeners in the area surrounding the connection to the vertical
beams.
(i) Do a detailed inspection of the main deck floor beams, 12 inches outboard of the vertical beam to 12
inches inboard of the vertical beam. Inspect both the forward and aft side of the beams.
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 6 OF 7)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 747-53A2887
ALERTALERT

### Page 49

More DataQtyIdentificationNameTaskStep
(j) Do a detailed inspection of the floor beam lower chords, 12 inches outboard of the vertical beam to 12
inches inboard of the vertical beam. Inspect both the forward and aft side of the chord.
(k) Do a detailed inspection of the floor beam lower chords in the area around the ends of the reinforcing
straps.
FIGURE 2: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
This Figure applies only to: Group 1-2, Configuration 2; Group 4, 6.
STA
260
STA
260  A STA
CANTED STA  1280
340  /STA
300
STA
RBL 22  340
RBL 10
LBL 10 -
LBL 22 ~
2454877
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 1 OF 6)
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### Page 51 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
280
300
FLOORBEAM
Q
TOP PANEL WEB
FORE AFT
STIFFENER
FORE AFT
STIFFENER
- BL
22
FORE AFT  STIFFENER 1  INTERCOSTAL
TYPICAL
CRACK
LOCATION  1 CLIP
POTENTIAL CRAC  TYPICAL STA 280-STA 300.  LBL 10 AND 22
OCATION IN FOR
AFT STIFFENER
1 INTERCOSTAL
BL
10
22
TYPICAL
1 TOP PANEL  2454880
WEB
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 2 OF 6)
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### Page 52 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
® CHORD
1 SIDE WALL
VERTICAL  PANEL WEB
BEAM
VERTICAL
BEAM CLIP
TYPICAL CRACKS
IN VERTICAL
BEAM WEB
TYPICAL
INSULATION
BLANKET
STANDOFF/TOOL
HOLE LOCATION
2) HORIZONTAL
STIFFENER
VERTICAL 3
BEAM CLIP
CHORDE  STATIONS 260 THROUGH 320  (TYPICAL)
D
2454883
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 3 OF 6)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
MAIN DECK FLOOR BEAM
(AT STA 280, 300 AND 320 ONLY)
VERTICAL BEAM 2
S-40L
S-41L
INED
TYPICAL STATIONS 260 TO 320
A-A
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 4 OF 6)
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### Page 54 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
STA
280
300
320
12.0
12.0
3) LOWER CHORI  FLOOR BEAI
STA
280
300
320
VERTICAL
(2) BEAM OUTER
CHORD
TYPICAL
VERTICAL
BEAM
TYPICAL
CRACK
VERTICAL
BEAM WEB
VERTICAL BEAM (2
INNER CHORD
LOOF (3  FAM
LOWER CHORD 3  FLOOR BEAM  2454894
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 5 OF 6)
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### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fore Aft StiffenersInspect1
(b)--ClipsInspect
(c)--IntercostalInspect
(d)--Floor BeamInspect
(e)--Top Panel WebInspect
(f)--Vertical BeamInspect2
(f)--Vertical Beam WebInspect
(f)--Vertical Beam ChordInspect
(g)--Vertical Beam ClipsInspect
(h)--Horizontal StiffenersInspect
(i)--Main Deck Floor
Beams
Inspect3
(j)--Floor Beam Lower
Chords
Inspect
(a) Do a detailed inspection of the fore aft stiffeners, between Body Station (STA) 280 and STA 300, Left
Buttock Line (LBL) 10 and LBL 22, common to the top panel. Inspect from the top side, around all fastener
heads and in the stiffeners fillet radius, common to the horizontal flange attached to the nose wheel well
top panel web.
(b) Do a detailed inspection of all attachments of the clips to the fore aft stiffeners.
(c) Do a detailed inspection of the intercostals in the area surrounding the connection to the clip and the fore
aft stiffeners.
(d) Do a detailed inspection of the floor beams in the area surrounding the connection to the fore aft stiffeners.
(e) Do a detailed inspection of the top panel web in the area surrounding the connection to the fore aft stiff-
eners.
(f) Do a detailed inspection of the full length of the vertical beams, vertical beam webs and vertical beam
chords. Inspect both the forward and aft side of the beams. Inspect the joints between the vertical beams
and the frames and between the vertical beams and the floor beams.
(g) Do a detailed inspection of all attachments of the vertical beam clips to the vertical beams, from inside
the fuselage.
(h) Do a detailed inspection of the horizontal stiffeners in the area surrounding the connection to the vertical
beams.
(i) Do a detailed inspection of the main deck floor beams, 12 inches outboard of the vertical beam to 12
inches inboard of the vertical beam. Inspect both the forward and aft side of the beams.
(j) Do a detailed inspection of the floor beam lower chords, 12 inches outboard of the vertical beam to 12
inches inboard of the vertical beam. Inspect both the forward and aft side of the chord.
FIGURE 3: LEFT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 747-53A2887
ALERTALERT

### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
This Figure applies only to: Group 1-2, Configuration 2; Group 4, 6.
STA
260
STA
260
CANTED
STA
340
STA
280
STA
300
STA  STA
340  320  - LBL 20
- LBL 10
- RBL 10
RBL 22
2456026
FIGURE 4: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 1 OF 6)
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### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
FLOORBEAM
TOP PANEL WEB
FORE AFT
STIFFENER
FORE AFT
STIFFENER
BL
22
FORE AFT
INTERCOSTAL  STIFFENER
TYPICAL
CRACK
CLIP  LOCATION
BL
10
TYPICAL STA 280-STA 300,
RBL 10 AND 22  POTENTIAL CRACK
LOCATION IN FORE AFT
STIFFENER
INTERCOSTAL
*BL
TOP PANEL  10
WEB  22
TYPICAL
FIGURE 4: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 2 OF 6)
Original Issue: December 02, 2015
Export Controlled ECCN: 9E991 - BOEING  747-53A2887
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  57 of 85

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
SIDE WALL  PANEL WEB  CHORD
VERTICAL
BEAM
2) VERTICAL
BEAM CLIP
TYPICAL CRACKS
•IN VERTICAL
BEAM WEB
TYPICAL
INSULATION
- BLANKET
STANDOFF/TOOL
HOLE LOCATION
HORIZONTAL
STIFFENER
2) VERTICAL
BEAM CLIP
STATIONS 260 THROUGH 320
(TYPICAL)  CHORD
2456061
FIGURE 4: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 3 OF 6)
Original Issue: December 02, 2015
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-53A2887
Work - See page 1 for details.  58 of 85

### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
MAIN DECK FLOOR BEAM
(AT STA 280, 300 AND 320 ONLY)
3 VERTICAL BEAM
S-39R
S-40R
S-41R
INBD
TYPICAL STATIONS 260 TO 320  2456067
A-A
FIGURE 4: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 4 OF 6)
Original Issue: December 02, 2015
Export Controlled ECCN: 9E991 - BOEING  747-53A2887
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  59 of 85

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-53A2887
ALERT  ALERT
12.0
FLOOR BEAM
LOWER CHORD
VERTICAL
BEAM OUTER (2)
CHORD
*YPICA  • VERTICAL  BEAM
TYPICAL
CRACK
VERTICAL
BEAM WEB
-E WERE CAPE
3) BEA  FLOO
FLOOR BEAI  2456071
A LOWER CHOR
FIGURE 4: RIGHT SIDE NOSE WHEEL WELL BODY STRUCTURE - DETAILED INSPECTION
(SHEET 5 OF 6)
Original Issue: December 02, 2015
Export Controlled ECCN: 9E991 - BOEING  747-53A2887
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  60 of 85

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