# Boeing Alert Service Bulletin 747-53A2465: Revision 5

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- Document: [Boeing Alert Service Bulletin 747-53A2465](https://openairdocs.org/service-documents/boeing/747-53a2465.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 747-53A2465-05
- Pages: 51
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## Text

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Commercial 
Airplanes
747
Service Bulletin
Number: 747-53A2465
Original Issue: April 05, 2001
Revision 5: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side Panel and Top Panel - Web and
Stiffener 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 © 2001 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Unpublished Work.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 0
B. Concurrent Requirements ...................................... 2 0
C. Reason ................................................ 2 0
D. Description .............................................. 2 2
E. Compliance .............................................. 2 3
F. Approval ............................................... 2 5
G. Manpower .............................................. 2 5
H. Weight and Balance Changes .................................... 2 6
I. Electrical Load Data ......................................... 2 6
J. References .............................................. 2 6
1. Existing Data: ......................................... 2 6
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. Parts Necessary for Each Airplane ................................. 2 9
1. Kits/Parts: ........................................... 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 ................................. 2 9
E. Special Tooling - Price and Availability ............................... 2 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1
A. GENERAL INFORMATION ..................................... 3 1
B. WORK INSTRUCTIONS ....................................... 3 2
FIGURE 1: INSPECTION OF AREA 1 - ALL AIRPLANES ........................ 3 5
FIGURE 2: INSPECTION OF AREA 2 [Group 1] ............................. 3 8
FIGURE 3: INSPECTION OF AREA 2 [Group 2] ............................. 4 2
FIGURE 4: INSPECTION OF AREA 3 - ALL AIRPLANES ........................ 4 5
FIGURE 5: SECONDARY INSPECTION OF SIDE PANEL VERTICAL BEAMS AND HORIZONTAL
STIFFENERS - ALL AIRPLANES ............................... 4 8
FIGURE 6: SECONDARY INSPECTION OF LONGITUDINAL STIFFENERS, FLOOR BEAM LOWER
CHORDS, FLOOR BEAM WEBS, AND VERTICAL BEAM UPPER ENDS [Group 1] . . . 50
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Commercial 
Airplanes
747
Service Bulletin
Revision Transmittal SheetNumber: 747-53A2465Original Issue: April 05, 2001
Revision 5: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side Panel and Top Panel - Web and
Stiffener Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
More work is necessary on the airplanes inspected in accordance with the original issue or Revision 1 of this
service bulletin. Revision 2 changed inspection requirements and compliance times.
More work may be necessary on the airplanes inspected in accordance with the Revision 2 of this service bulletin.
Revision 3 changed the initial compliance threshold for airplanes with 19,000 or more total flight cycles.
More work may be necessary on the airplanes inspected in accordance with the Revision 3 of this service bulletin.
Revision 4 changed the inspection methods and repeat inspection intervals for airplanes with 20,000 flight cycles
or more.
No more work is necessary on airplanes inspected in accordance with the Revision 4 of this service bulletin.
However, this revision reduces the initial threshold for inspection of the nose wheel well sidewall panel webs
and top panel web.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the revised compliance tasks and times given in this
service bulletin mandatory.
REASON FOR REVISION
This revision is sent to reduce the initial threshold for inspection of the nose wheel well sidewall panel webs and
top panel web, and to clarify inspection requirements in Figures 1, 2, and 3.
These sections were changed:
1. In Summary: Added service history information since Revision 4. Added reference to Service Related
Problem 747-SRP-53-0408 and related Fleet Team Digest articles. Also, added Planning Data table
and reference to AD 2006-22-15.
2. In paragraph 1.C., Reason: Added service history information since Revision 4. Added reference to
Service Related Problem 747-SRP-53-0408 and related Fleet Team Digest articles.
3. In paragraph 1.D., Description: Added "no more work" statement for Revision 5.
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4. In paragraph 1.E., Compliance: Tables identified as "Table 1" and "Table 2" in previous revisions of
this service bulletin have been re-identified as "Table 2" and "Table 3", respectively. A new Table
identified as "Table 1" has been added for inspection of the nose wheel well sidewall panel webs and
top panel web at a reduced initial inspection threshold. Also, added reference to related AD 2006-22-15,
and revised compliance Table 2 and Table 3 to reflect the compliance times specified in AD 2006-22-15.
5. In paragraph 1.F., Approval: Updated approval statement and added Alternative Method of Compliance
statement for AD 2006-22-15.
6. In paragraph 1.K., Publications Affected: Added damage tolerance inspection statement.
7. In paragraph 3.A., General Information: Updated general notes.
8. In paragraph 3.B., Work Instructions: Updated SRM references.
9. In Figure 1: Added sentence to footnote (b) related to UT inspection information, that was previously
in footnote (a). Figure 1 inspection requirements have not changed.
10. In Figure 2: Added cross sections B-B and C-C. Clarified side panel web detailed inspection.
11. In Figure 3: Added cross section B-B, and clarified side panel web detailed inspection.
12. In Figure 4: Added footnotes (a), (b), (c), and (d) to clarify inspection requirements.
13. Throughout the service bulletin, the words "as shown in" or "shown in" have been changed to "as given
in" or "given in" when referring to procedures or bulletin sections that must be used. The words "as
shown in" have been changed to "refer to" when referring to maintenance manual procedures. Vertical
lines have not been put on the left edge of the pages where these changes were made.
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
April 05, 2001Original Issue:
October 16, 2003Revision 1:
November 11, 2004Revision 2:
December 23, 2004Revision 3:
February 24, 2005Revision 4:
July 11, 2013Revision 5:
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Commercial 
Airplanes
747
Service Bulletin
SummaryNumber: 747-53A2465Original Issue: April 05, 2001
Revision 5: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side Panel and Top Panel - Web and
Stiffener Inspection
CONCURRENT REQUIREMENTS
None
BACKGROUND
Accomplishment of the inspections shown in this service bulletin will ensure the structural integrity of the nose
wheel well top panel and side panels. Cracks in the top panel or side panel webs and stiffeners that are not
found and repaired could become large and cause in flight depressurization and loss of structural integrity.
Three operators have told Boeing about nose wheel well side panel web cracks that were found on four airplanes
with 15,900 - 32,018 flight cycles. The cracks that were found were 1.5 inch to 14.5 inch long. In addition, a 17.5
inch long crack was found in the side panel web on Boeing's 747-400 Fatigue Test airplane at 58,890 pressure
cycles.
One operator has also reported a 13 inch long nose wheel well top panel web crack on one airplane. This airplane
had flown 15,726 total flight cycles.
Two operators have also reported nose wheel well side panel horizontal stiffener cracks on two airplanes. On
one airplane with 19,577 flight cycles, a 12 inch long stiffener crack was found. On the other airplane with 31,863
flight cycles, 9 inch and 13 inch long stiffener cracks were found.
Revision 2: After the initial release of this service bulletin, two operators have told Boeing that large sidewall
panel web cracks (up to 12 inches long) were found during visual inspection on two airplanes. On one airplane,
a 12 inch long side panel crack was found 1,178 flight cycles after the ultrasonic inspections shown in the initial
release and Revision 1 of this service bulletin was accomplished. On the other airplane, multiple side panel
cracks (up to 8.8 inches long) were found approximately 3,500 flight cycles after the ultrasonic inspection was
accomplished.
Revision 3: After Revision 2 of this service bulletin, an operator reported an in flight decompression of an airplane
with 27,241 flight cycles. Upon inspection, the nose wheel well right hand side panel web was torn open between
STA 260 and STA 280, and from WL 160 to WL 170. The airplane landed safely, however, the decompression
resulted in deployment of the oxygen masks and a decision by the crew to conduct an air turn back. In addition,
the decompression caused damage to the Nose Landing Gear doors and adjacent structure.
Since Revision 4 of this service bulletin, Boeing has received six additional reports of cracks in the nose wheel
well side panels and/or side panel stiffeners. Two of the reports were on airplanes with 17,320 and 21,623 flight
cycles. The other four reports were on airplanes with between 13,541 and 13,828 flight cycles.
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Boeing has determined that all the reported nose wheel well cracks were caused by fatigue. Furthermore, the
nose wheel well top and side panels have been determined to be structure that could develop Widespread
Fatigue Damage (WFD). For more information about WFD, refer to 747-SL-53-088.
Service history and Boeing analysis show that fatigue cracking in the NWW top and side panels before 16,000
total flight cycles will be confined to a single bay between web stiffeners. Boeing has determined that cracking
in a single stiffener bay is not an airplane safety concern. However, beyond 16,000 total flight cycles, WFD could
result in cracking across multiple stiffener bays and a depressurization event significant enough to affect the
structural integrity of the fuselage.
In order to detect and repair possible cracking, and prevent a possible depressurization event, Boeing recommends
that operators accomplish the inspections given in this service bulletin. Due to the possibility that the Federal
Aviation Administration (FAA) will issue a new Airworthiness Directive to address cracking before 16,000 total
flight cycles, the initial threshold for inspection of the nose wheel well sidewall panel webs and top panel web
is being reduced to 13,000 total flight cycles.
Boeing Structural Item Interim Advisory SIIA 747-129 is related to this service bulletin.
Boeing Service Related Problems (SRP) 747-SRP-53-0133, 747-SRP-53-0231, and 747-SRP-53-0408  are
related to this service bulletin.
Boeing Fleet Team Digest (FTD) articles 747 FTD 53-12006 and 747 FTD 53-04002 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 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)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
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ACTION
AREA 1 - Sidewall Panel Web at WL 150, WL 160, and WL 170: Open the Nose Landing Gear doors. Do a
detailed inspection (and a UT inspection, if over 20,000 total flight cycles) of the Nose Wheel Well side panel
for cracks. If no cracks are found, put the airplane back in serviceable condition. If cracks are found, repair
before any more flights. Repair web cracks as given in the Structural Repair Manual or ask Boeing for repair
data.
AREA 2 - Sidewall Panel Web at WL 140 and WL 180 and Top Panel Web: Open the Nose Landing Gear doors.
Do a detailed inspection (and a UT inspection, if over 20,000 total flight cycles) of the Nose Wheel Well side
panel and top panel webs for cracks. If no cracks are found, put the airplane back in serviceable condition. If
cracks are found, repair before any more flights. Repair web cracks as given in the Structural Repair Manual or
ask Boeing for repair data.
AREA 3 - Sidewall Panel and Top Panel Stiffeners: Get internal access to the Nose Wheel Well side panels and
top panel. Do detailed and surface High Frequency Eddy Current (HFEC) inspections of the longitudinal stiffeners
for cracks. If no cracks are found, put the airplane back in serviceable condition. If cracks are found, repair
before any more flights. Replace cracked stiffeners, or ask Boeing for repair data.
Do the AREA 1, AREA 2, and AREA 3 inspections again at the times given in this service bulletin.
EFFECTIVITY
All 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.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the revised compliance tasks and times given in this
service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.
MANPOWER
Elapsed Time (Hours)Total Man-HoursAirplanes
13.527All Airplanes - Area 1
1020Group 1 - Area 2
510Group 2 - Area 2
3672All Airplanes - Area 3
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BOEING SERVICE BULLETIN 747-53A2465
MATERIAL INFORMATION
None
STA
265
STA
280
STA
300  STA
400
WL 180  STA
320
WL 170  STA
340
WL 160
WL 150
FWD
AREA 1: FROM INSIDE THE NOSE WHEEL  WELL, DO
EXTERNAL DETAILED AND/OR UT INSPECTIONS
OF THE SIDEWALL PANEL WEB AT WL 150, 160
AND 170 FOR CRACKS.
AREA 2: FROM INSIDE THE NOSE WHEEL WELL, DO  EXTERNAL DETAILED AND/OR UT INSPECTIONS OF  WL 140
THE TOP PANEL WEB (GROUP 1 ONLY) AND SIDEWALL
PANEL WEB AT WL 140 AND 180 FOR CRACKS.  WL 130
AREA 3: DO INTERNAL DETAILED AND SURFACE HFEC INSPECTIONS
OF  THE NOSE WHEEL WELL TOP PANEL AND SIDE PANEL
STIFFENERS FOR CRACKS.
IF CRACKS ARE FOUND, REPAIR BEFORE ANY MORE FLIGHTS.  V43411
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Commercial 
Airplanes
747
Service Bulletin
Number: 747-53A2465
Original Issue: April 05, 2001
Revision 5: July 11, 2013
ATA System: 5311
SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side Panel and Top Panel - Web and
Stiffener Inspection
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 airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP
747 airplanes, line numbers 1 - 1419, except 747-200C, 747-200F,
and 747-400F airplanes.
-1
All 747-200C, 747-200F, and 747-400F airplanes.-2
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
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GroupVariable Number
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
1RB411 - RB413
1RB421
1RB601 - RB607
1RB681 - RB697
1RB711
1RB721 - RB723
1RB741 - RB748
1RD001 - RD004
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GroupVariable Number
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD144
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD227
1RD231 - RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
1RD301 - RD302
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
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GroupVariable Number
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD601 - RD607
1RD621 - RD623
1RD641 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
1RF001 - RF006
1RG001 - RG009
1RG091
1RG095
1RG101 - RG104
1RG121 - RG126
1RG141 - RG142
1RG161 - RG164
1RG171 - RG174
1RG191 - RG193
1RG211 - RG213
1RG221 - RG222
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GroupVariable Number
1RH101 - RH102
1RH111 - RH112
1RH121 - RH122
2RJ131 - RJ133
2RJ151 - RJ152
2RJ301 - RJ303
2RJ321 - RJ322
2RJ331 - RJ333
2RL401 - RL403
2RL411 - RL436
2RL451 - RL456
2RL461 - RL462
2RL471 - RL481
2RL491 - RL492
2RL501 - RL502
2RL511 - RL516
2RL521 - RL522
2RL531 - RL534
2RL551
2RL561 - RL568
2RL571 - RL572
2RL576 - RL577
2RL579
2RL581 - RL586
2RL651 - RL655
2RL671 - RL675
2RL681 - RL684
2RL751 - RL752
1RM001 - RM007
1RM010 - RM013
1RM021 - RM024
1RM026 - RM030
1RM036 - RM045
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GroupVariable Number
1RM051 - RM053
1RM071
1RM081 - RM084
1RM091
1RM096 - RM097
1RM116 - RM117
1RM126 - RM132
1RM136 - RM147
1RM156 - RM158
1RM166 - RM177
1RM191 - RM192
1RM231 - RM233
1RM241 - RM246
1RM261 - RM264
1RM316 - RM318
1RM331 - RM333
1RM341
1RM351 - RM355
1RM366 - RM367
1RM401 - RM403
1RM426
1RM431
1RM441 - RM443
1RM445
1RM801 - RM803
1RM811 - RM813
2RM851 - RM859
2RM861 - RM863
2RM871 - RM899
2RM901 - RM906
2RM911
2RR001 - RR005
2RR021 - RR025
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GroupVariable Number
2RR031
2RR201 - RR206
2RR221 - RR226
2RR261 - RR267
2RR301 - RR310
2RR331 - RR332
2RR336
2RR341 - RR345
2RR361 - RR362
2RR421 - RR422
2RR431 - RR432
2RR441 - RR442
2RR451
2RR501 - RR504
2RR521 - RR522
2RR526
2RR531
2RR551 - RR556
2RR561
2RR566
2RR701
2RR721 - RR724
2RR746 - RR748
2RR851 - RR856
2RR861 - RR862
2RR951 - RR952
1RS001 - RS002
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
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GroupVariable Number
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
1RS711 - RS713
1RS721 - RS722
1RS731 - RS732
1RS741 - RS743
1RS751 - RS752
1RS761 - RS762
1RS771
1RS781 - RS782
1RS786
1RT001 - RT014
1RT021 - RT022
1RT031 - RT035
1RT041 - RT047
1RT061
1RT071 - RT075
1RT101 - RT103
1RT121
1RT131 - RT137
1RT151 - RT152
1RT161 - RT168
1RT401 - RT412
1RT431 - RT447
1RT451 - RT469
1RT471 - RT499
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GroupVariable Number
1RT501 - RT535
1RT551 - RT568
1RT571 - RT591
1RT601 - RT657
1RT671 - RT673
1RT681 - RT682
1RT691 - RT699
1RT701 - RT704
1RT711 - RT717
1RT741 - RT757
1RT776 - RT777
1RT781 - RT784
1RT801 - RT803
1RT811 - RT814
1RT831 - RT837
1RT861 - RT864
1RT876 - RT880
1RT931 - RT932
1RT945 - RT949
1RT951 - RT955
1RT966 - RT967
1RU001 - RU006
1RU016 - RU017
1RU031 - RU032
1RU051 - RU052
1RU059 - RU062
1RU081 - RU083
1RU101 - RU102
1RU121 - RU132
1RU801 - RU809
1RU831 - RU841
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2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of the inspections shown in this service bulletin will ensure the structural integrity of
the nose wheel well top panel and side panels. Cracks in the top panel or side panel webs and stiffeners
that are not found and repaired could become large and cause in flight depressurization and loss of
structural integrity.
Three operators have told Boeing about nose wheel well side panel web cracks that were found on
four airplanes with 15,900 - 32,018 flight cycles. The cracks that were found were 1.5 inch to 14.5 inch
long. In addition, a 17.5 inch long crack was found in the side panel web on Boeing's 747-400 Fatigue
Test airplane at 58,890 pressure cycles.
One operator has also reported a 13 inch long nose wheel well top panel web crack on one airplane.
This airplane had flown 15,726 total flight cycles.
Two operators have also reported nose wheel well side panel horizontal stiffener cracks on two airplanes.
On one airplane with 19,577 flight cycles, a 12 inch long stiffener crack was found. On the other airplane
with 31,863 flight cycles, 9 inch and 13 inch long stiffener cracks were found.
Revision 1 was sent to add instructions for visual and surface High Frequency Eddy Current (HFEC)
inspection of more nose wheel well sidewall stiffeners. Instructions for the inspection of all of the
stiffeners between STA 320 and STA 340 and the lower stiffener between STA 300 and 320 have been
added.
Revision 2: After the initial release of this service bulletin, two operators have told Boeing that large
sidewall panel web cracks (up to 12 inches long) were found during visual inspection on two airplanes.
On one airplane, a 12 inch long side panel crack was found 1,178 flight cycles after the ultrasonic
inspections shown in the initial release and Revision 1 of this service bulletin was accomplished. On
the other airplane, multiple side panel cracks (up to 8.8 inches long) were found approximately 3,500
flight cycles after the ultrasonic inspection was accomplished.
Revision 2 was sent to change the inspection method for the sidewall and top panel webs. Two operators
have reported that large sidewall panel cracks (up to 12 inches long) were found during visual inspections
on two airplanes. On one airplane, a 12 inch long side panel crack was found approximately 1,178
flight cycles after the ultrasonic inspections shown in the initial release and Revision 1 of this service
bulletin was accomplished. On the other airplane, multiple side panel cracks (up to 8.8 inches long)
were found approximately 3,500 flight cycles after the ultrasonic inspection was accomplished. The
ultrasonic inspection of the web has been removed from this service bulletin. Instead, operators should
do an external detailed inspection of the sidewall panel webs and the top panel (on Group 1 airplanes
only) from inside the nose wheel well. This inspection should be repeated every 1,000 flight cycles.
The inspection of the stiffeners common to the sidewall panel and top panel has not been changed.
Also, the effectivity is divided into two groups due to differences in the top panel web. Airplanes with
a nose cargo door (Group 2 airplanes) have a thicker top panel web than Group 1 airplanes. An
inspection is not necessary on the thicker top panel web. References to FAA NPRM 2001-NM-179-AD
have been added.
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Revision 3: After Revision 2 of this service bulletin, an operator reported an in flight decompression of
an airplane with 27,241 flight cycles. Upon inspection, the nose wheel well right hand side panel web
was torn open between STA 260 and STA 280, and from WL 160 to WL 170. The airplane landed
safely, however, the decompression resulted in deployment of the oxygen masks and a decision by
the crew to conduct an air turn back. In addition, the decompression caused damage to the Nose
Landing Gear doors and adjacent structure.
Revision 3 was sent to recommend that operators inspect Area 1 and Area 2 within 100 flight cycles
or 90 days after the release date of Revision 3, whichever is sooner, on airplanes with 20,000 or more
flight cycles. This recommendation is to address an immediate concern that airplanes with 20,000 or
more flight cycles could have large cracks that can cause in flight depressurization. Table 3 has been
added to Paragraph 1.E., Compliance, to incorporate the urgent inspection requirement for Area 1 and
Area 2. Revision 3 does not affect Area 3 inspections.
Revision 4 was sent to change the Area 1 and Area 2 repeat inspection interval and method for airplanes
with 20,000 total flight cycles or more. When affected airplanes reach 20,000 total flight cycles, start
to do repeated detailed and UT inspections of Area 1 and Area 2 every 500 flight cycles. Also, the
repeat inspection interval for Area 3 has been changed from every 6,000 flight cycles to every 1,500
flight cycles. Figures 1 and 2 have been changed to include inspection of the web from STA 260 to
STA 270 along WL 140.
Since Revision 4 of this service bulletin, Boeing has received six additional reports of cracks in the
nose wheel well side panels and/or side panel stiffeners. Two of the reports were on airplanes with
17,320 and 21,623 flight cycles. The other four reports were on airplanes with between 13,541 and
13,828 flight cycles.
Boeing has determined that all the reported nose wheel well cracks were caused by fatigue. Furthermore,
the nose wheel well top and side panels have been determined to be structure that could develop
Widespread Fatigue Damage (WFD). For more information about WFD, refer to 747-SL-53-088.
Service history and Boeing analysis show that fatigue cracking in the NWW top and side panels before
16,000 total flight cycles will be confined to a single bay between web stiffeners. Boeing has determined
that cracking in a single stiffener bay is not an airplane safety concern. However, beyond 16,000 total
flight cycles, WFD could result in cracking across multiple stiffener bays and a depressurization event
significant enough to affect the structural integrity of the fuselage.
In order to detect and repair possible cracking, and prevent a possible depressurization event, Boeing
recommends that operators accomplish the inspections given in this service bulletin. Due to the possibility
that the Federal Aviation Administration (FAA) will issue a new Airworthiness Directive to address
cracking before 16,000 total flight cycles, the initial threshold for inspection of the nose wheel well
sidewall panel webs and top panel web is being reduced to 13,000 total flight cycles.
Revision 5 is sent to reduce the initial threshold for inspection of the nose wheel well sidewall panel
webs and top panel web, and to clarify inspection requirements in Figures 1, 2, and 3. Other minor
changes have also been made. A detailed list of changes is given in the Revision Transmittal Sheet
section of Revision 5.
Boeing Structural Item Interim Advisory SIIA 747-129 is related to this service bulletin.
Boeing Service Related Problems (SRP) 747-SRP-53-0133, 747-SRP-53-0231, and 747-SRP-53-0408
are related to this service bulletin.
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Boeing Fleet Team Digest (FTD) articles 747 FTD 53-12006 and 747 FTD 53-04002 are related to this
service bulletin.
D. Description
AREA 1 - Sidewall Panel Web at WL 150, WL 160, and WL 170: Open the Nose Landing Gear doors.
Do a detailed inspection (and a UT inspection, if over 20,000 total flight cycles) of the Nose Wheel Well
side panel for cracks. If no cracks are found, put the airplane back in serviceable condition. If cracks
are found, repair before any more flights. Repair web cracks as given in the Structural Repair Manual
or ask Boeing for repair data.
AREA 2 - Sidewall Panel Web at WL 140 and WL 180 and Top Panel Web: Open the Nose Landing
Gear doors. Do a detailed inspection (and a UT inspection, if over 20,000 total flight cycles) of the Nose
Wheel Well side panel and top panel webs for cracks. If no cracks are found, put the airplane back in
serviceable condition. If cracks are found, repair before any more flights. Repair web cracks as given
in the Structural Repair Manual or ask Boeing for repair data.
AREA 3 - Sidewall Panel and Top Panel Stiffeners: Get internal access to the Nose Wheel Well side
panels and top panel. Do detailed inspections and surface High Frequency Eddy Current (HFEC)
inspections of the longitudinal stiffeners for cracks. If no cracks are found, put the airplane back in
serviceable condition. If cracks are found, repair before any more flights. Replace cracked stiffeners,
or ask Boeing for repair data.
Do the AREA 1, AREA 2, and AREA 3 inspections again at the times given in this service bulletin.
Revision 1 - No more work is necessary on airplanes inspected as shown in the initial release of this
service bulletin. However, for airplanes that had accomplished a prior inspection per the initial release
of this service bulletin, at the time of the next scheduled inspection, do the inspections as shown in this
revision. All inspections accomplished after receipt of Revision 1 of this service bulletin shall be done
as shown in Revision 1.
Revision 2 - More work is necessary on airplanes inspected as shown in the initial release or Revision
1 of this service bulletin. Begin to do inspections in Area 1 and Area 2 as defined in this revision within
1,000 flight cycles of the last inspection done as shown in the initial release or Revision 1 of this service
bulletin. Continue to do inspections in Area 3 as defined in this revision within 6,000 flight cycles of the
last inspection done as shown the initial release or Revision 1 of this service bulletin.
Revision 3 - For airplanes with 19,000 or more total flight cycles that have not been previously inspected
as shown in a previous release of this service bulletin, the initial Compliance threshold has been
changed. Refer to Table 3 in Paragraph 1.E., Compliance. For airplanes with less than 19,000 flight
cycles, no more work is required per Revision 3, but inspections should be completed as specified in
paragraph 1.E., Table 1 and Table 2.
Refer to paragraph 1.E. for detailed compliance information.
Revision 4 - More work may be necessary on airplanes previously inspected as shown in earlier releases
of this service bulletin. In Area 1 and Area 2, when affected airplanes reach 20,000 total flight cycles,
start to do repeated detailed and UT inspections of Area 1 and Area 2 every 500 flight cycles. In Area
3, do repeated detailed and HFEC inspections every 1,500 flight cycles. Refer to Paragraph 1.E.,
Compliance.
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Revision 5 - No more work is necessary on airplanes inspected in accordance with the Revision 4 of
this service bulletin. However, this revision reduces the initial threshold for inspection of the nose wheel
well sidewall panel webs and top panel web.
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, 114747-200C, 747-200F, 747-400F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service
bulletin.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive
related to this service bulletin. The Airworthiness Directive will make the revised compliance tasks and
times given in this service bulletin mandatory.
TABLE 1: Inspections for Airplanes With Less Than 15,000 Total Flight-Cycles as of the Revision
5 date of this service bulletin.
Repeat Inter-
val Not to Ex-
ceed (Flight-
Cycles)
ActionInitial Threshold (Use
whichever occurs later)
Flight-CyclesTotal Flight-
Cycles
1,000 (a)AREA 1: External Detailed Inspection of
the Sidewall Panel Web at WL 150, WL
160, and WL 170 for Cracks.
Within 1,000
flight cycles after
the Revision 5
date of this ser-
vice bulletin.
13,000
AREA 2: External Detailed Inspection of
the Sidewall Panel Web at WL 140 and
WL 180 and Top Panel Web for Cracks.
(a) When the airplane has 16,000 total flight cycles, continue to inspect as given in TABLE
2.
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TABLE 2: Inspections for Airplanes With Less Than 19,000 Total Flight-Cycles as of December 11, 2006
(the effective date of AD 2006-22-15)
Repeat Interval Not to Exceed
(Flight-Cycles)
ActionInitial Threshold (Use
whichever occurs later)
Detailed and
Surface HFEC
Detailed In-
spection
Flight-CyclesTotal Flight-
Cycles
-1,000 (a)AREA 1: External Detailed Inspection of
the Sidewall Panel Web at WL 150, WL
160, and WL 170 for Cracks.
1,000 (after May
10, 2005)
16,000
AREA 2: External Detailed Inspection of
the Sidewall Panel Web at WL 140 and
WL 180 and Top Panel Web for Cracks.
1,500 (b)-AREA 3: Internal Detailed and HFEC In-
spection of the Sidewall Panel and Top
Panel Stiffeners for Cracks.
1,000 (after Jan-
uary 27, 2005)
(a) When the airplane has 20,000 total flight cycles, continue to inspect as given in TABLE 3.
(b) If previously inspected as given in an earlier release of this service bulletin, repeat the inspection
within 6,000 flight cycles of the last inspection, or within 1,500 flight cycles after December 11, 2006,
whichever occurs first.
TABLE 3: Inspections for Airplanes With 19,000 Total Flight-Cycles or more as of December 11, 2006
(the effective date of AD 2006-22-15)
Repeat Interval Not to Ex-
ceed (Flight-Cycles)
ActionInitial Threshold (Use whichever oc-
curs later)
Detailed and
Surface
HFEC
Detailed
and UT In-
spection
DaysFlight-CyclesTotal
Flight-
Cycles (Use whichever occurs first)
-500AREA 1: External Detailed and UT In-
spections of the Sidewall Panel Web
at WL 150, WL 160, and WL 170 for
Cracks.
90 (after May
10, 2005)
100 (after May
10, 2005)
20,000
AREA 2: External Detailed and UT In-
spections of the Sidewall Panel Web
at WL 140 and WL 180 and Top Panel
Web for Cracks.
1,500 (a)-AREA 3: Internal Detailed and HFEC
Inspection of the Sidewall Panel and
Top Panel Stiffeners for Cracks.
-1000 (after Jan-
uary 27, 2005)
-
(a) If previously inspected as given in an earlier release of this service bulletin, repeat the inspection within
6,000 flight cycles of the last inspection, or within 1,500 flight cycles after December 11, 2006, whichever
occurs first.
NOTE: On airplanes previously inspected as given in earlier releases of this service bulletin, continue
to do repeat inspections using the repeat intervals in this service bulletin.
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NOTE: Modification in accordance with Service Bulletin 747-53A2562 or Service Bulletin 747-53A2808,
as applicable, terminates the inspection requirements of this service bulletin.
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.
In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the accomplishment
of the inspections and corrective actions defined in this service bulletin as an alternate method of
compliance to the requirements of paragraphs (f), (g), (h), (i), and (j) of AD 2006-22-15. This AMOC
only applies to the areas inspected, repaired, or modified in accordance with this service bulletin. When
this service bulletin specifies contacting Boeing for repair instructions, the repair instructions must be
approved by the FAA in accordance with paragraph (p) of the AD. 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.
G. Manpower
The table below shows an estimate of the man-hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
man-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 1-2:
Area 1 Inspection as given in Figure 1
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
0.512Open Access
12.5252Examine
0.512Close Access
13.527TOTAL FOR EACH AIRPLANE
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Group 1:
Area 2 Inspection as given in Figure 2
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
0.512Open Access
9182Examine
0.512Close Access
1020TOTAL FOR EACH AIRPLANE
Group 2:
Area 2 Inspection as given in Figure 3
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
0.512Open Access
482Examine
0.512Close Access
510TOTAL FOR EACH AIRPLANE
Group 1-2:
Area 3 Inspection as given in Figure 4
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
4.592Open Access
27542Examine
4.592Close Access
3672TOTAL FOR EACH AIRPLANE
NOTE: More time will be necessary for repairs if cracks are found.
H. Weight and Balance Changes
None
I. Electrical Load Data
747-400: Not changed
All other 747 models: Not applicable
J. References
1. Existing Data:
a. Boeing Service Bulletin 747-53A2562, 747-53A2808
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b. Boeing Service Letter 747-SL-51-048, 747-SL-53-088
c. Boeing Service Related Problem (SRP) 747-SRP-53-0133, 747-SRP-53-0231,
747-SRP-53-0408
d. Boeing Structural Item Interim Advisory (SIIA) 747-129
e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-22-15
f. Service Bulletin Index D6-30300
g. 747 Fleet Team Digest (FTD) 53-04002, 53-12006
h. 747 Non-Destructive Testing (NDT) Manual Part 4, 53-10-12, Part 6, 51-00-00
i. 747-100/200/300 Aircraft Maintenance Manual (AMM) 09-11-00, 25-25-01, 25-27-01, 32-00-30,
53-21-02
j. 747-100/200/300 Structural Repair Manual (SRM) 53-10-04
k. 747-400 Aircraft Maintenance Manual (AMM) 09-11-00, 25-25-01, 25-27-01, 32-00-30, 53-21-02
l. 747-400 Structural Repair Manual (SRM) 53-10-14
m. 747-400F Structural Repair Manual (SRM) 53-10-14
n. 747-400SF Structural Repair Manual (SRM) 53-10-14
o. 747-SP Structural Repair Manual (SRM) 53-19-02
p. 747-E4B Structural Repair Manual (SRM) 53-10-04
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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 but no new DTIs are necessary.
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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 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:
None.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 31

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
4. Use the approved fastener and process 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.
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.
7. 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.
8. 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.
9. 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.
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10. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "as
given in" are included in the instruction, the procedure in the Boeing document must
be used.
B. WORK INSTRUCTIONS
INSPECTION OF AREA 1 - NOSE WHEEL WELL SIDEWALL PANEL WEB AT WL 150, WL 160,
AND WL 170
1. PART 1 - ACCESS AND INSPECTION
a. Install the ground locks on the landing gear. Refer to 747-100/200/300 AMM 09-11-00 or
747-400 AMM 09-11-00.
WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE DOOR
OPERATION AREA. FAST MOVEMENT OF THE DOORS CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.
b. Open the nose landing gear doors and install door locks. Refer to 747-100/200/300 AMM
32-00-30 or 747-400 AMM 32-00-30.
c. Do inspections of the side panel webs for cracks as given in FIGURE 1.
d. If no cracks are found, continue to PART 2. Do the inspections in PART 1 again at the times
given in Paragraph 1.E., Compliance.
e. If cracks are found, repair before any more flights. For repair of web cracks, refer to
747-100/200/300 SRM 53-10-04; or 747-400 SRM 53-10-14; or 747-400F SRM 53-10-14; or
747-400SF SRM 53-10-14 ; or 747-SP SRM 53-19-02; or 747-E4B SRM 53-10-04.
f. If cracks are found common to the side panel, do a detailed inspection of the vertical beams
and the horizontal stiffeners in the areas where cracks were found, as given in FIGURE 5.
Inspect within a 20 inch radius of where web cracks were found. If cracks are found during
this secondary inspection, contact Boeing for repair data.
g. Continue to PART 2. Do the inspections in PART 1 again at the times given in Paragraph
1.E., Compliance.
2. PART 2 - RESTORATION
WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE DOOR
OPERATION AREA. FAST MOVEMENT OF THE DOORS CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.
a. Remove the door locks and close the nose landing gear doors. Refer to 747-100/200/300
AMM 32-00-30 or 747-400 AMM 32-00-30.
b. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
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### Page 33

INSPECTION OF AREA 2 - NOSE WHEEL WELL SIDEWALL PANEL WEB AT WL 140 AND WL
180, AND TOP PANEL WEB:
1. PART 1 - ACCESS AND INSPECTION
a. Install the ground locks on the landing gear. Refer to 747-100/200/300 AMM 09-11-00 or
747-400 AMM 09-11-00.
WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE DOOR
OPERATION AREA. FAST MOVEMENT OF THE DOORS CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.
b. Open the nose landing gear doors and install door locks. Refer to 747-100/200/300 AMM
32-00-30 or 747-400 AMM 32-00-30.
c. Group 1:
Do inspections of the top panel and side panel webs for cracks as given in FIGURE 2.
d. Group 2:
Do inspections of the side panel webs for cracks as given in FIGURE 3.
e. If no cracks are found, continue to PART 2. Do the inspections in PART 1 again at the times
given in Paragraph 1.E., Compliance.
f. If cracks are found, repair before any more flights. For repair of web cracks, refer to
747-100/200/300 SRM 53-10-04; or 747-400 SRM 53-10-14; or 747-400F SRM 53-10-14; or
747-400SF SRM 53-10-14 ; or 747-SP SRM 53-19-02; or 747-E4B SRM 53-10-04.
g. If cracks are found common to the side panel, do a detailed inspection of the vertical beams
and the horizontal stiffeners in the areas where cracks were found, as given in FIGURE 5.
Inspect within a 20 inch radius of where cracks were found. If cracks are found during this
secondary inspection, contact Boeing for repair data.
h. Group 1:
If cracks are found common to the top panel, do a detailed inspection of the longitudinal
stiffeners, the floor beam lower chords, the floor beam webs, and the vertical beam upper
ends in the areas where cracks were found, as given in FIGURE 6. Inspect within a 20 inch
radius of where cracks were found. If cracks are found during this secondary inspection,
contact Boeing for repair data.
i. Continue to PART 2. Do the inspections in PART 1 again at the times given in Paragraph
1.E., Compliance.
2. PART 2 - RESTORATION
WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE DOOR
OPERATION AREA. FAST MOVEMENT OF THE DOORS CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.
a. Remove the door locks and close the nose landing gear doors. Refer to 747-100/200/300
AMM 32-00-30 or 747-400 AMM 32-00-30.
b. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-53A2465

### Page 34

INSPECTION OF AREA 3 - NOSE WHEEL WELL SIDEWALL PANEL AND TOP PANEL STIFFENERS
1. PART 1 - ACCESS AND INSPECTION
a. Remove the equipment that follows from the main deck as necessary for access to the nose
wheel well top panel from STA 260 to STA 340, between LBL 20 and RBL 20. Refer to the
following procedures:
AMM SubjectEquipment
747-100/200/300 AMM 25-25-01
or 747-400 AMM 25-25-01
Passenger Seats
747-100/200/300 AMM 25-27-01
or 747-400 AMM 25-27-01
Floor Covering
747-100/200/300 AMM 53-21-02
or 747-400 AMM 53-21-02
Floor Panels
b. Remove and keep the insulation blankets from the nose wheel well top panel and side panels.
c. Do detailed inspections and surface HFEC inspections of the top panel and side panel stiffeners
for cracks as given in FIGURE 4.
d. If no cracks are found, continue to PART 2. Do the inspections in PART 1 again at the time
given in Paragraph 1.E., Compliance.
e. If any cracked stiffener is found, replace the cracked stiffener before further flight, or contact
Boeing for repair instructions. Cracked stiffeners can be replaced using AND10139-2202
7075-T6511 extrusion. Make sure to attach the 0.75 inch flange (of the new stiffener) to the
web using a filler that has a thickness equal to the depth of the joggle in the production stiffener.
After cracked stiffeners are repaired or replaced, continue to PART 2. Do the inspections in
PART 1 again at the time given in Paragraph 1.E., Compliance.
2. PART 2 - RESTORATION
a. Install the insulation blankets that were removed from the nose wheel well top panel and side
panels.
b. Install any equipment that was removed from the main deck for access.
c. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-53A2465

### Page 35 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
STA
STA  280  RBL
STA  300  30  CANTED
320~  - BL  BULKHEAD
STA  LBL
340  30
STA
STA  360
380
STA
400
SEE A
SIDEWALL
PANEL
STA 340
BULKHEAD
STA 400
BULKHEAD  LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE  430687
INSIDE NOSE WHEEL WELL
FIGURE 1: INSPECTION OF AREA 1 - ALL AIRPLANES
(SHEET 1 OF 3)
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### Page 36

FIGURE 1: INSPECTION OF AREA 1 - ALL AIRPLANES
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2001
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36 of 51
BOEING SERVICE BULLETIN 747-53A2465

### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESREFERENCESPROCEDURENAMETASKSTEP
For cracks. (a)-Detailed InspectionSide Panel WebsInspect1
On airplanes with 20,000 to-
tal flight cycles or more, do a
UT inspection for cracks. (b)
747 NDT Part 4,
53-10-12
UT Inspection
(a) Typically, the webs crack at the lower edge of the bonded strap on the sidewall web. Pay particular at-
tention to this location.
(b) The UT inspection is only necessary along the lower edge of the bonded strap. If paint was removed to
do the UT inspection, it is not necessary to reapply paint. Make sure that primer is present in areas
where paint was removed. Apply primer if necessary. If necessary, reapply organic corrosion inhibitor
to the affected area.
FIGURE 1: INSPECTION OF AREA 1 - ALL AIRPLANES
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 05, 2001
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BOEING SERVICE BULLETIN 747-53A2465

### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
This Figure applies only to: Group 1.
STA  SEE ®
280  TOP PANEL
STA  • RBL
STA  300  30  CANTED
320  - BL  • BULKHEAD
STA  _ LBL
340  30
STA
STA  360
380
STA
400
SEE
SIDEWALL
PANEL
STA 340
BULKHEAD
STA 400
BULKHEAD  LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
INSIDE NOSE WHEEL WELL
FIGURE 2: INSPECTION OF AREA 2
(SHEET 1 OF 4)
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Work - See page 1 for details.  38 of 51

### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
STA  STA  STA  STA  CANTED
340  320  300  280  BULKHEAD
-WL180
→ A
￾ B
WL140-
UP
→ FWD
(LEFT SIDE PANEL SHOWN
FAIRING  RIGHT SIDE PANEL OPPOSITE)
COVER
DOUBLER•  WEB  1 TIPICAL  WEB CRACK
BONDED  BONDED
• STRAP  STRAP
WEB -
) TYPICAL  DOUBLER~
WEB CRACK
A-A  B-B  433894
(TYPICAL)  (TYPICAL)
FIGURE 2: INSPECTION OF AREA 2
(SHEET 2 OF 4)
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Work - See page 1 for details.  39 of 51

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
RBL  RBL  BL  LBL  LBL
20  10  10  20
0000
CANTED
0000  BULKHEAD
— STA 280
• TYPICA
WEB ~  - WEB CRAC
BONDED
STRAP
TOP PANEL  1 TYPICAL  WEB CRAC
c-C
ROTATED 90° CCW  (TYPICAL)  431500
FIGURE 2: INSPECTION OF AREA 2
(SHEET 3 OF 4)
Original Issue: April 05, 2001
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Work - See page 1 for details.  40 of 51

### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESREFERENCESPROCEDURENAMETASKSTEP
For cracks (a)-Detailed InspectionSide Panel WebsInspect1
On airplanes with 20,000 total
flight cycles or more (b) (c)
747 NDT Part 4,
53-10-12
UT Inspection
For cracks-Detailed InspectionTop Panel WebsInspect2
On airplanes with 20,000 total
flight cycles or more (c) (d)
747 NDT Part 4,
53-10-12
UT Inspection
(a) At WL 180, the sidewall webs typically crack at the lower edge of the bonded strap. At WL 140, the
sidewall webs typically crack at the upper edge of the bonded strap. Pay particular attention to these lo-
cations.
(b) At WL 180, do the UT inspection along the lower edge of the bonded strap. At WL 140 from STA 260 to
approximately STA 270, do the UT inspection along the edge of the fairing cover. At WL 140 from approx-
imately STA 270 to STA 320, do the UT inspection along the upper edge of the bonded strap.
(c) If paint was removed to do the UT inspection, it is not necessary to reapply paint. Make sure that primer
is present in areas where paint was removed. Apply primer if necessary. If necessary, reapply organic
corrosion inhibitor to the affected area.
(d) At RBL 10, BL 0, and LBL 10, do the UT inspection along the inboard and outboard edges of the bonded
strap. At RBL 20 and LBL 20, do the UT inspection along only the inboard edge of the bonded strap.
FIGURE 2: INSPECTION OF AREA 2
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 747-53A2465

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
This Figure applies only to: Group 2.
STA
STA  280  • RBL
STA  300  30  CANTED
320  • BL  • BULKHEAD
STA  → LBL
340  30
STA
STA  360
380
STA
400
SEE
SIDEWALL
PANEL
STA 340
BULKHEAD
STA 400
BULKHEAD  LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
INSIDE NOSE WHEEL WELL
FIGURE 3: INSPECTION OF AREA 2
(SHEET 1 OF 3)
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Work - See page 1 for details.  42 of 51

### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
STA  STA  STA  STA  CANTED
BULKHEAD
340  320  300  280
-WL180
→ A
• B
WL140-
UP
→ FWD
(LEFT SIDE PANEL SHOWN
FAIRING  RIGHT SIDE PANEL OPPOSITE)
COVER
TYPICAL
DOUBLER  WEB  WEB CRACK
BONDED  BONDED
• STRAP  "STRAP
WEB
1) TYPICAL  DOUBLER-
WEB CRACK
A—A  B-B
(TYPICAL)  (TYPICAL)
FIGURE 3: INSPECTION OF AREA 2
(SHEET 2 OF 3)
Original Issue: April 05, 2001
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### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESREFERENCESPROCEDURENAMETASKSTEP
For cracks (a)-Detailed InspectionSide Panel WebsInspect1
On airplanes with 20,000 to-
tal flight cycles or more (b)
(c)
747 NDT Part 4,
53-10-12
UT Inspection
(a) At WL 180, the sidewall webs typically crack at the lower edge of the bonded strap. At WL 140, the
sidewall webs typically crack at the upper edge of the bonded strap. Pay particular attention to these
locations.
(b) At WL 180, do the UT inspection along the lower edge of the bonded strap. At WL 140 from STA 260 to
approximately STA 270, do the UT inspection along the edge of the fairing cover. At WL 140 from ap-
proximately STA 270 to STA 320, do the UT inspection along the upper edge of the bonded strap.
(c) If paint was removed to do the UT inspection, it is not necessary to reapply paint. Make sure that primer
is present in areas where paint was removed. Apply primer if necessary. If necessary, reapply organic
corrosion inhibitor to the affected area.
FIGURE 3: INSPECTION OF AREA 2
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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44 of 51
BOEING SERVICE BULLETIN 747-53A2465

### Page 45 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
BL 00  STA  STA
- 265  400
LBL
LBL 10\  STA
20  - 280  1X2
STA
300
WL 180
STA
320
WL 170\  STA
340
WL 160 -
WL 150 -
112)
SEE A  12
(TYPICAL)
WL 140
UP
WL 130
FWD
LEFT SIDE SHOWN  V43415
RIGHT SIDE OPPOSITE
FIGURE 4: INSPECTION OF AREA 3 - ALL AIRPLANES
(SHEET 1 OF 3)
Original Issue: April 05, 2001
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Work - See page 1 for details.  45 of 51

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
SIDE WALL PANEL
VERTICAL
BEAM
SIDEWALL
PANEL WEB
BONDED STRAP
• STIFFENERS
SIDEWALL
PANEL WEB
BONDED STRAP
FWD
TYPICAL SIDEWALL PANEL STIFFENER
(TOP PANEL SIMILAR, EXCEPT ROTATED 90°)
WEB _
BONDED STRAP
TYPICAL STIFFENER
CRACK  1X2
UP
A-A  →INBD  V43418
(TYPICAL)
FIGURE 4: INSPECTION OF AREA 3 - ALL AIRPLANES
(SHEET 2 OF 3)
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### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESREFERENCESPROCEDURENAMETASKSTEP
(a) (c)-Detailed InspectionTop Panel and Side
Panel Stiffeners
Inspect1
(b) (c) (d)747 NDT Part 6, 51-
00-00, Procedure 4 or
23
Surface HFECTop Panel and Side
Panel Stiffeners
Inspect2
(a) Do an internal detailed inspection of the side panel stiffeners and top panel stiffeners for cracks.
(b) Do a surface HFEC inspection for cracks parallel to (along the length of) the radius using a "transverse
scan" method as shown in 747 NDT Part 6, 51-00-00, Procedure 4, Figure 11, or 747 NDT Part 6, 51-
00-00, Procedure 23, Figure 13. If a strap, or filler, or angle is installed in the radius of the stiffener, do
the surface HFEC inspection of the stiffener surface that is opposite the radius, as shown.
(c) Only the left side stiffeners are shown in the illustration, but inspection of the right side stiffeners is also
required.
(d) At STA 260 - 270, there is a reinforcing angle that prevents the surface HFEC inspection of the radius
of the stiffener. Inspect the radius of the reinforcing angle as specified in note (b).
FIGURE 4: INSPECTION OF AREA 3 - ALL AIRPLANES
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 747-53A2465

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
BL 00  STA  STA
BL 10 _  265  400
STA
BL 20  - 280
STA
— 300
WL 180 -  STA
320
WL 170\  STA
WL 160 \  — 340
WL 150-
UP
• WL 140
FWD .
WL 130
LEFT SIDE SHOWN  D41668
RIGHT SIDE OPPOSITE
FIGURE 5: SECONDARY INSPECTION OF SIDE PANEL VERTICAL BEAMS AND HORIZONTAL STIFFENERS
- ALL AIRPLANES
(SHEET 1 OF 2)
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### Page 49

The step numbers shown in the table below agree with the numbers shown in the circle symbols in the figure.
NOTESREFERENCESPROCEDURENAMETASKSTEP
as necessary, from the nose
wheel well side panel.
--Insulation BlanketsRemove
/ Keep
1 (not
shown)
Inspect the horizontal stiffen-
ers and the vertical beams for
cracks. Inspection of the entire
area is not required. Only in-
spect within a 20 inch radius
of cracks that were found in
the side panel.
-Detailed Inspec-
tion
Side Panel Horizontal
Stiffeners
Inspect2
Side Panel Vertical
Beams
as necessary, from the nose
wheel well side panel.
--Insulation Blankets
(kept)
Install3 (not
shown)
FIGURE 5: SECONDARY INSPECTION OF SIDE PANEL VERTICAL BEAMS AND HORIZONTAL STIFFENERS
- ALL AIRPLANES
(SHEET 2 OF 2)
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Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-53A2465

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-53A2465
This Figure applies only to: Group 1.
STA
STA  400
280
FLOOR BEAMS
STA
300  STA  STA
320  340
_LONGITUDINAL
STIFFENERS
VERTICAL BEAMS
FWD <
LEFT SIDE SHOWN  D41663
RIGHT SIDE OPPOSITE
FIGURE 6: SECONDARY INSPECTION OF LONGITUDINAL STIFFENERS, FLOOR BEAM LOWER CHORDS,
FLOOR BEAM WEBS, AND VERTICAL BEAM UPPER ENDS
(SHEET 1 OF 2)
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### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESREFERENCESPROCEDURENAMETASKSTEP
as necessary.-747-100/200/300
AMM 25-25-01 or
747-400 AMM 25-
25-01
Passenger SeatsRemove
/ Keep
1 (not
shown)
-747-100/200/300
AMM 25-27-01 or
747-400 AMM 25-
27-01
Floor Coverings
-747-100/200/300
AMM 53-21-02 or
747-400 AMM 53-
21-02
Floor Panels
as necessary, from the nose
wheel well side panel.
--Insulation Blankets
Inspect the longitudinal stiffen-
ers that are on the top of the
panel for cracks. Inspection of
all stiffeners is not required,
only inspect stiffeners within
a 20 inch radius of cracks that
were found in the top panel.
-Detailed InspectionLongitudinal Stiffen-
ers
Inspect2
For cracks. It is only neces-
sary to inspect floor beams
and vertical beams within a 20
inch radius of the cracks that
were found in the top panel.
-Detailed InspectionFloor Beam Lower
Chords
Inspect3
Floor Beam Webs
Vertical Beam Up-
per Ends
as necessary, from the nose
wheel well side panel.
--Insulation Blankets
(kept)
Install4 (not
shown)
as necessary.-747-100/200/300
AMM 53-21-02 or
747-400 AMM 53-
21-02
Floor Panels (kept)
-747-100/200/300
AMM 25-27-01 or
747-400 AMM 25-
27-01
Floor Coverings
(kept)
-747-100/200/300
AMM 25-25-01 or
747-400 AMM 25-
25-01
Passenger Seats
(kept)
FIGURE 6: SECONDARY INSPECTION OF LONGITUDINAL STIFFENERS, FLOOR BEAM LOWER CHORDS,
FLOOR BEAM WEBS, AND VERTICAL BEAM UPPER ENDS
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 747-53A2465

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