# Boeing Alert Service Bulletin 747-53A2839: No revision named

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- Document: [Boeing Alert Service Bulletin 747-53A2839](https://openairdocs.org/service-documents/boeing/747-53a2839.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 747-53A2839-00
- Pages: 76
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2839
Original Issue: November 06, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Skin and Bear Strap Crack at the Aft Upper Corner of the Main
Entry Door 5 Cutout - Inspection, Repair and Modification
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2012 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 8
B. Concurrent Requirements ...................................... 1 9
C. Reason ................................................ 1 9
D. Description .............................................. 1 9
E. Compliance .............................................. 2 0
F. Approval ............................................... 2 5
G. Manpower .............................................. 2 6
H. Weight and Balance Changes .................................... 2 8
I. Electrical Load Data ......................................... 2 9
J. References .............................................. 2 9
1. Existing Data .......................................... 2 9
2. Data supplied with this Service Bulletin ............................ 2 9
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 3 0
K. Publications Affected ........................................ 3 0
L. Interchangeability and Intermixability of Parts ........................... 3 0
2. MATERIAL INFORMATION ........................................ 3 1
A. Material - Price and Availability ................................... 3 1
B. Industry Support Information .................................... 3 2
C. Parts Necessary For Each Airplane ................................. 3 2
1. Kits/Parts ............................................ 3 2
2. Parts and Materials Supplied by the Operator ........................ 4 5
3. Parts Modified and Reidentified ................................ 4 6
4. Parts Removed and Not Replaced .............................. 4 6
D. Parts Necessary to Change Spares ................................. 4 6
E. Special Tooling - Price and Availability ............................... 4 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 7
A. GENERAL INFORMATION ..................................... 4 7
B. WORK INSTRUCTIONS ....................................... 4 8
FIGURE 1: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE LEFT MAIN
ENTRY DOOR 5 CUTOUT .................................. 5 3
FIGURE 2: EDGE MARGIN MEASUREMENT AT THE AFT UPPER CORNER OF THE LEFT MAIN ENTRY
DOOR 5 CUTOUT ....................................... 5 6
FIGURE 3: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE RIGHT MAIN
ENTRY DOOR 5 CUTOUT [Group 1-2, 4] .......................... 5 9
FIGURE 4: EDGE MARGIN MEASUREMENT AT THE AFT UPPER CORNER OF THE RIGHT MAIN ENTRY
DOOR 5 CUTOUT [Group 1-2, 4] ............................... 6 2
FIGURE 5: INSPECTION FOR SKIN CRACKS AT THE AFT UPPER CORNER OF THE LEFT MAIN ENTRY
DOOR 5 CUTOUT ....................................... 6 5
FIGURE 6: INSPECTION FOR SKIN CRACKS AT THE AFT UPPER CORNER OF THE RIGHT MAIN
ENTRY DOOR 5 CUTOUT [Group 1-2, 4] .......................... 6 8
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FIGURE 7: POST-REPAIR/POST-MODIFICATION INSPECTIONS AT THE AFT UPPER CORNER OF
THE MAIN ENTRY DOOR 5 CUTOUT ............................ 7 1
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2839Original Issue: November 06, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Skin and Bear Strap Crack at the Aft Upper Corner of the Main
Entry Door 5 Cutout - Inspection, Repair and Modification
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 inspections of the fuselage skin and internal bear strap at the aft
upper corner of the cutout for Main Entry Door (MED) 5. Skin and bear strap cracks that are not found and
repaired can become large and result in in-flight depressurization of the airplane.
An operator has told Boeing that a 3.65 inch long crack was found at the aft upper corner of the right MED 5
cutout on an airplane with 11,047 flight-cycles. The skin (including the bonded doubler and tripler) and bear
strap were found to be cracked. This is the first reported crack to extend up to the door edge frame.
Boeing has received several reports of cracks that did not extend up to the door edge frame on more than thirty
airplanes. The affected airplanes had flown between 10,042 and 31,410 total flight-cycles at the time the cracks
were found.
Accomplishment of the inspections in this service bulletin and installation of a repair or modification will help
prevent in-flight depressurization of the airplane and ensure the structural integrity of the aft upper corner of the
MED 5 cutout.
Boeing Service Related Problem (SRP) 747-SRP-53-0361 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., ComplianceYesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
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ReferenceAffectedPlanning Data
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 85901-110RS)
Do a detailed inspection for existing repairs at the aft upper corner of the main entry door 5 cutout. If any repair
is found, contact Boeing for instructions.
Measure the edge margin at certain fastener locations around the corner of the door cutout. The threshold of
the subsequent inspection is dependent on the measured edge margin. At the applicable times given in Paragraph
1.E., Compliance, do detailed and High Frequency Eddy Current (HFEC) inspections of the skin and bear strap
for cracks at the aft upper corner of the door cutout. If any crack is found, repair in accordance with this service
bulletin. If no cracks are found, put the airplane back to a serviceable condition and do the inspections again
and install the preventive modification at the applicable times given in Paragraph 1.E., Compliance. As an
alternative to repeat inspections, install a preventive modification in accordance with this service bulletin.
Do post-repair or post-modification detailed and Low Frequency Eddy Current (LFEC) inspections at the times
given in Paragraph 1.E., Compliance, Table 3.
EFFECTIVITY
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F,
and 747SR Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directives AD 2009-18-07 and AD 2010-01-01 are related
to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of September 2, 1997. Please refer to
Paragraph 2.B., Industry Support Information.
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MANPOWER
Group 1-2, 4:
Elapsed HoursTotal Task HoursAirplanes
1.001.00Inspection for previous repairs and edge
margin measurement
23.1035.70Inspection and preventive modification
installed on both sides
16.7033.20Post repair/post modification inspection
Group 3, 5:
Elapsed HoursTotal Task HoursAirplanes
0.500.50Inspection for previous repairs and edge
margin measurement
13.0520.85Inspection and preventive modification
installed on the left side
8.4516.70Post repair/post modification inspection
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-53A2839
ALERT  ALERT
~ DO AN INSPECTION FOR EXISTING REPAIRS AT
THE UPPER CORNER OF THE LEFT AND RIGHT (IF
INSTALLED) MAIN ENTRY DOOR 5 CUTOUT. ALSO
MEASURE THE EDGE MARGIN AT CERTAIN
FASTENER LOCATIONS AT THE AFT UPPER
CORNER OF THE DOOR CUTOUT
DO DETAILED AND HFEC INSPECTIONS OF THE
SKIN AT THE AFT UPPER CORNER OF THE CUTOUT
FOR THE LEFT AND RIGHT (IF INSTALLED) MAIN
ENTRY DOOR 5 FOR CRACKS. IF CRACKS ARE
FOUND, INSTALL A REPAIR IN ACCORDANCE WITH
THIS SERVICE BULLETIN.  2118198
Original Issue: November 06, 2012
747-53A2839
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2839
Original Issue: November 06, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Skin and Bear Strap Crack at the Aft Upper Corner of the Main
Entry Door 5 Cutout - Inspection, Repair and Modification
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 for the airplanes shown below. Refer to PRR85901-110RS for data about
this change.
DESCRIPTIONCONFIGURATIONGROUP
All 747 airplanes line number 1 through 85.-1
All 747SR, 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C,
747-300, 747-400 and 747-400D airplanes line number 86 through
1235, except 747 Large Cargo Freighter (LCF) airplanes. Door 5
does not exist on LCF airplanes.
-2
All 747-200F and 747-400F airplanes line number 86 through 1235.
These airplanes do not have a Door 5 on the right side.
-3
All 747-400 airplanes line number 1236 through 1419.-4
All 747-400F airplanes line number 1236 through 1419. These
airplanes do not have a Door 5 on the right side.
-5
Airplane Models:
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747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR
GroupVariable Number
1RA001 - RA026
2RA027 - RA034
1RA101 - RA112
2RA113 - RA115
1RA161 - RA162
2RA163 - RA164
1RA201 - RA203
2RA216 - RA217
2RA245 - RA246
1RA251 - RA254
2RA255 - RA266
1RA301 - RA303
2RA304 - RA318
1RA351 - RA359
2RA360
2RA369 - RA373
1RA401 - RA405
2RA406 - RA418
1RA501
2RA502
1RA521 - RA523
2RA524 - RA528
2RA532 - RA548
1RA551 - RA552
2RA559 - RA561
1RA581
2RA582
2RA585
1RA601 - RA602
1RA631 - RA632
2RA633 - RA635
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GroupVariable Number
2RA651 - RA652
2RA671 - RA677
2RA701 - RA702
2RA721 - RA731
2RA741 - RA745
2RA749 - RA750
2RA761 - RA762
2RA781 - RA784
1RA901 - RA907
2RA908 - RA916
2RB001 - RB016
1RB041 - RB043
2RB044
2RB071 - RB075
2RB101 - RB102
2RB411 - RB413
2RB421
2RB601 - RB607
2RB681 - RB697
2RB711
2RB721 - RB723
2RB741 - RB748
2RD001 - RD004
2RD021 - RD022
2RD041 - RD059
2RD071 - RD072
2RD081 - RD083
2RD091 - RD092
2RD101 - RD104
2RD121 - RD127
2RD131 - RD144
2RD166 - RD167
2RD171 - RD172
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GroupVariable Number
2RD181 - RD183
2RD201 - RD204
2RD221 - RD227
2RD231 - RD235
2RD241 - RD243
2RD251 - RD262
2RD271 - RD272
2RD291 - RD292
2RD301 - RD302
2RD311
2RD351 - RD358
2RD361 - RD366
2RD381 - RD383
2RD411 - RD414
2RD421 - RD426
2RD431 - RD435
2RD441 - RD442
2RD451 - RD456
2RD461
2RD471 - RD475
2RD513 - RD519
2RD531 - RD533
2RD551
2RD561
2RD571
2RD581 - RD583
2RD591 - RD593
2RD601 - RD607
2RD621 - RD623
2RD641 - RD649
2RD651 - RD659
2RD661
2RD671
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GroupVariable Number
2RD681 - RD682
2RD691 - RD692
2RD701 - RD702
2RD721 - RD722
2RD741 - RD742
2RD751 - RD755
2RD761
2RD771 - RD775
2RD781 - RD783
2RD791 - RD792
2RE001
4RF001 - RF006
2RJ131 - RJ133
2RJ151 - RJ152
2RJ301 - RJ303
2RJ321 - RJ322
2RJ331 - 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
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GroupVariable Number
5RL651 - RL655
5RL671 - RL675
5RL681 - RL684
5RL751 - RL752
2RM001 - RM002
4RM003 - RM007
4RM010
2RM011 - RM012
4RM013
2RM021 - RM024
2RM026 - RM027
4RM028 - RM030
2RM036 - RM038
4RM039 - RM045
2RM051
4RM052 - RM053
2RM071
2RM081 - RM084
2RM091
2RM096 - RM097
2RM116 - RM117
2RM126 - RM130
4RM131 - RM132
2RM136 - RM147
2RM156 - RM157
4RM158
2RM166 - RM176
4RM177
2RM191 - RM192
2RM231 - RM232
4RM233
2RM241 - RM244
4RM245 - RM246
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GroupVariable Number
2RM261 - RM264
2RM316
4RM317 - RM318
2RM331 - RM332
4RM333
4RM341
4RM351 - RM355
4RM366 - RM367
4RM401 - RM403
4RM426
4RM431
4RM441 - RM443
4RM445
2RM801
4RM802 - RM803
2RM811 - RM813
3RM851 - RM852
5RM853 - RM859
3RM861
5RM862 - RM863
3RM871
5RM872 - RM880
3RM881 - RM885
5RM886 - RM890
3RM891 - RM899
5RM901 - RM906
5RM911
3RR001 - RR005
3RR021 - RR025
3RR031
3RR201 - RR206
3RR221 - RR226
3RR261 - RR267
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GroupVariable Number
3RR301 - RR310
3RR331 - RR332
3RR336
3RR341 - RR345
3RR361 - RR362
3RR421 - RR422
3RR431 - RR432
3RR441 - RR442
3RR451
3RR501 - RR504
3RR521 - RR522
3RR526
3RR531
3RR551 - RR556
3RR561
3RR566
3RR701
3RR721 - RR724
3RR746 - RR748
3RR851 - RR856
3RR861 - RR862
3RR951 - RR952
2RS001 - RS002
2RS201
2RS211 - RS212
2RS221 - RS222
2RS231 - RS241
2RS251 - RS259
2RS263
2RS265 - RS268
2RS271 - RS276
2RS291 - RS292
2RS301 - RS306
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GroupVariable Number
2RS311 - RS320
2RS331 - RS333
2RS341 - RS342
2RS699
2RS701 - RS703
2RS711 - RS713
2RS721 - RS722
2RS731 - RS732
2RS741 - RS743
2RS751 - RS752
2RS761 - RS762
2RS771
2RS781 - RS782
2RS786
2RT001 - RT014
2RT021 - RT022
2RT031 - RT035
2RT041 - RT047
2RT061
2RT071 - RT075
2RT101 - RT103
2RT121
2RT131 - RT137
2RT151 - RT152
2RT161 - RT168
2RT401 - RT412
2RT431 - RT447
2RT451 - RT469
2RT471 - RT499
2RT501 - RT535
2RT551 - RT568
2RT571 - RT591
2RT601 - RT630
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GroupVariable Number
2RT633 - RT657
2RT671 - RT673
2RT681 - RT682
2RT691 - RT699
2RT701 - RT704
2RT711 - RT717
2RT741 - RT742
2RT744 - RT757
2RT776 - RT777
2RT781 - RT784
2RT801 - RT803
2RT811 - RT814
2RT831 - RT837
2RT861 - RT864
2RT877 - RT880
2RT931 - RT932
2RT945 - RT949
2RT951 - RT955
2RT966 - RT967
2RU001 - RU006
2RU016 - RU017
2RU031 - RU032
2RU051 - RU052
2RU059 - RU062
2RU081 - RU083
2RU101 - RU102
2RU121 - RU132
2RU801 - RU809
2RU831 - RU841
2. Spares Affected
None.
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B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to do inspections of the fuselage skin and internal bear strap at
the aft upper corner of the cutout for Main Entry Door (MED) 5. Skin and bear strap cracks that are not
found and repaired can become large and result in in-flight depressurization of the airplane.
An operator has told Boeing that a 3.65 inch long crack was found at the aft upper corner of the right
MED 5 cutout on an airplane with 11,047 flight-cycles. The skin (including the bonded doubler and
tripler) and bear strap were found to be cracked. This is the first reported crack to extend up to the door
edge frame.
Boeing has received several reports of cracks that did not extend up to the door edge frame on more
than thirty airplanes. The affected airplanes had flown between 10,042 and 31,410 total flight-cycles
at the time the cracks were found.
Accomplishment of the inspections in this service bulletin and installation of a repair or modification
will help prevent in-flight depressurization of the airplane and ensure the structural integrity of the aft
upper corner of the MED 5 cutout.
Boeing Service Related Problem (SRP) 747-SRP-53-0361 is related to this service bulletin.
D. Description
Do a detailed inspection for existing repairs at the aft upper corner of the main entry door 5 cutout. If
any repair is found, contact Boeing for instructions.
Measure the edge margin at certain fastener locations around the corner of the door cutout. The
threshold of the subsequent inspection is dependent on the measured edge margin. At the applicable
times given in Paragraph 1.E., Compliance, do detailed and High Frequency Eddy Current (HFEC)
inspections of the skin and bear strap for cracks at the aft upper corner of the door cutout. If any crack
is found, repair in accordance with this service bulletin. If no cracks are found, put the airplane back
to a serviceable condition and do the inspections again and install the preventive modification at the
applicable times given in Paragraph 1.E., Compliance. As an alternative to repeat inspections, install
a preventive modification in accordance with this service bulletin.
Do post-repair or post-modification detailed and Low Frequency Eddy Current (LFEC) inspections at
the times given in Paragraph 1.E., Compliance, Table 3.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
271, 272747-100
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Group 2:
Affected Maintenance Zones
ZoneModel
271, 272747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C,
747-300, 747-400, 747-400D,
747SR
Group 3:
Affected Maintenance Zones
ZoneModel
271747-200F, 747-400F
Group 4:
Affected Maintenance Zones
ZoneModel
271, 272747-400
Group 5:
Affected Maintenance Zones
ZoneModel
271747-400F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directives AD 2009-18-07 and AD 2010-01-01
are related to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
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### Page 21

Table 1: Inspection at the aft upper corner of the cutout for left Main Entry Door 5
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,500
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 10,000
total flight-cy-
cles.
Do a detailed inspection
to determine if a repair
exists at the aft upper
corner of the cutout for
left Main Entry Door 5 in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 1.
All airplanes.
AND
Measure the edge margin
at certain fastener loca-
tions at the aft upper cor-
ner of the cutout for left
Main Entry Door 5 in ac-
cordance with Paragraph
3.B., Work Instructions,
PART 1.
-Before further flight.Contact Boeing with de-
tails of the installed re-
pair. Do inspections or
change the repair in ac-
cordance with the Boeing
instructions.
Any door cutout where a
repair is found.
-Before further flight.Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 3.
If no repair is found, and if
the measured edge margin
at any affected fastener lo-
cation is less than 0.70
inch.
-Within 1,500
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 18,000
total flight-cy-
cles.
Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 3.
If no repair is found, and if
the measured edge margin
at all affected fastener loca-
tions is 0.70 inch or
greater.
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### Page 22

Table 1: Inspection at the aft upper corner of the cutout for left Main Entry Door 5
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
No crack found, and the
measured edge margin at
any affected fastener loca-
tion is less than 0.70 inch.
OR
3,000 flight-cyclesWithin 3,000 flight-cycles of the
previous inspection done in accor-
dance with Paragraph 3.B., Work
Instructions, PART 3.
Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 3.
AND
-Within 6,000
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 20,000
total flight-cy-
cles.
Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
-Before further flight.Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
No crack found, and the
measured edge margin at
all affected fastener loca-
tions is 0.70 inch or
greater.
OR
3,000 flight-cyclesWithin 3,000 flight-cycles of the
previous inspection done in accor-
dance with Paragraph 3.B., Work
Instructions, PART 3.
Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 3.
AND
-Within 1,500
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 35,000
total flight-cy-
cles.
Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
-Before further flight.Install a repair in accor-
dance with Paragraph
3.B., Work Instructions,
PART 5.
All cracks found are less
than 3.0 inch long.
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### Page 23

Table 1: Inspection at the aft upper corner of the cutout for left Main Entry Door 5
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Install a repair in accor-
dance with Paragraph
3.B., Work Instructions,
PART 6.
Any crack found to be
equal to or greater than 3.0
inch long.
Group 1-2, 4:
Table 2: Inspection at the aft upper corner of the cutout for right Main Entry Door 5
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,500
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 10,000
total flight-cy-
cles.
Do a detailed inspection
to determine if a repair
exists at the aft upper
corner of the cutout for
right Main Entry Door 5 in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 2.
All airplanes.
AND
Measure the edge margin
at certain fastener loca-
tions at the aft upper cor-
ner of the cutout for right
Main Entry Door 5 in ac-
cordance with Paragraph
3.B., Work Instructions,
PART 2.
-Before further flight.Contact Boeing with de-
tails of the installed re-
pair. Do inspections or
change the repair in ac-
cordance with the Boeing
instructions.
Any door cutout where a
repair is found.
-Before further flight.Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 4.
If no repair is found, and if
the measured edge margin
at any affected fastener lo-
cation is less than 0.70
inch.
-Within 1,500
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 18,000
total flight-cy-
cles.
Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 4.
If no repair is found, and if
the measured edge margin
at all affected fastener loca-
tions is 0.70 inch or
greater.
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### Page 24

Group 1-2, 4:
Table 2: Inspection at the aft upper corner of the cutout for right Main Entry Door 5
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
No crack found, and the
measured edge margin at
any affected fastener loca-
tion is less than 0.70 inch.
OR
3,000 flight-cyclesWithin 3,000 flight-cycles of the
previous inspection done in accor-
dance with Paragraph 3.B., Work
Instructions, PART 4.
Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 4.
AND
-Within 6,000
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 20,000
total flight-cy-
cles.
Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
-Before further flight.Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
No crack found, and the
measured edge margin at
all affected fastener loca-
tions is 0.70 inch or
greater.
OR
3,000 flight-cyclesWithin 3,000 flight-cycles of the
previous inspection done in accor-
dance with Paragraph 3.B., Work
Instructions, PART 4.
Do detailed, open-hole
HFEC and surface HFEC
inspections for cracks in
accordance with Para-
graph 3.B., Work Instruc-
tions, PART 4.
AND
-Within 1,500
flight-cycles af-
ter the original
issue date on
this service bul-
letin.
Before 35,000
total flight-cy-
cles.
Install a preventive modi-
fication in accordance
with Paragraph 3.B.,
Work Instructions, PART
5.
-Before further flight.Install a repair in accor-
dance with Paragraph
3.B., Work Instructions,
PART 5.
All cracks found are less
than 3.0 inch long.
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Group 1-2, 4:
Table 2: Inspection at the aft upper corner of the cutout for right Main Entry Door 5
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Install a repair in accor-
dance with Paragraph
3.B., Work Instructions,
PART 6.
Any crack found to be
equal to or greater than 3.0
inch long.
Table 3: Post-Repair/Post-Modification Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 15,000 flight-cycles after
the repair or the modification was
installed.
Do post-repair/post-modi-
fication detailed and
LFEC inspections for
cracks in accordance with
Paragraph 3.B., Work In-
structions, PART 7.
Any Main Entry Door 5 aft
upper corner modified or
repaired in accordance with
Paragraph 3.B., Work In-
structions, PART 5 or
PART 6.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Cracks found during post-
repair/post-modification in-
spections in accordance
with Paragraph 3.B., Work
Instructions, PART 7.
3,000 flight-cyclesWithin 3,000 flight-cycles of the
previous inspection done in accor-
dance with Paragraph 3.B., Work
Instructions, PART 7.
Do post-repair/post-modi-
fication detailed and
LFEC inspections for
cracks in accordance with
Paragraph 3.B., Work In-
structions, PART 7.
No crack found during
post-repair/post-modifica-
tion inspections in accor-
dance with Paragraph 3.B.,
Work Instructions, PART 7.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
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The manager of the FAA Seattle Aircraft Certification Office (ACO) approves the inspections, repairs
and modifications with the corresponding compliance times specified in Paragraph 1.E., Compliance,
of Service Bulletin 747-53A3839, as an AMOC to the inspections and repairs at the main entry door 5
aft upper corner required by paragraphs (g)(4) and (j)(4) of AD 2009-18-07. This AMOC is valid only
for areas where inspections, repairs or modifications are done in accordance with this Service Bulletin.
All other areas of MED 5 and MED 1 through 4 remain fully applicable and must be complied with
accordingly. 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 AD 2009-18-07. All
provisions of AD 2009-18-07 that are not specifically referenced in this paragraph remain fully applicable
and must be complied with accordingly.
In addition, the manager of the FAA Seattle Aircraft Certificate Office (ACO) approves the inspections,
repairs and modifications with the corresponding compliance times specified in Paragraph 1.E.,
Compliance, of Service Bulletin 747-53A2839, as an AMOC to the inspections and repairs at the main
entry door 5 aft upper corner required by paragraphs (g)(1) and (j) of AD 2010-01-01. This AMOC is
valid only for areas where inspections, repairs or modifications are done in accordance with this SB.
Other areas of MED 5 and all other areas per SB 747-53A2500 Revision 1 remain fully applicable and
must be complied with accordingly. When this SB specifies contacting Boeing for repair instructions,
the repair instructions must be approved by the FAA in accordance with paragraph (m) of AD 2010-01-01.
All provisions of AD 2010-01-01 that are not specifically referenced in this paragraph remain fully
applicable and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection and repair for
each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate
with operator task hour data if necessary. The estimate does not include lost time. These are some
examples of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1-2, 4:
Table 1 - Left and Right Main Entry Door 5 Cutout Upper Aft Corner Inspection for Existing
Repairs and Edge Margin Measurement
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Inspect left side for
existing repair - FIG-
URE 1
0.250.251Inspect right side for
existing repair - FIG-
URE 3
0.250.251Measure left side
edge margin - FIG-
URE 2
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Group 1-2, 4:
Table 1 - Left and Right Main Entry Door 5 Cutout Upper Aft Corner Inspection for Existing
Repairs and Edge Margin Measurement
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Measure right side
edge margin - FIG-
URE 4
1.001.00TOTAL FOR EACH AIRPLANE
Group 3, 5:
Table 2 - Left Main Entry Door 5 Cutout Upper Aft Corner Inspection for Existing Repairs
and Edge Margin Measurement
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Inspect left side for
existing repair - FIG-
URE 1
0.250.251Measure left side
edge margin - FIG-
URE 2
0.500.50TOTAL FOR EACH AIRPLANE
Group 1-2, 4:
Table 3 - Inspection and Repair or Preventive Modification
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
5.255.251Inspect left side -
FIGURE 5
5.255.251Inspect right side -
FIGURE 6
4.809.602Left side repair or
preventive modifica-
tion (Paragraph 3.B.,
Work Instructions,
PART 5)
4.809.602Right side repair or
preventive modifica-
tion (Paragraph 3.B.,
Work Instructions,
PART 5)
1.503.002Close Access
23.1035.70TOTAL FOR EACH AIRPLANE
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Group 3, 5:
Table 4 - Inspection and Repair or Preventive modification
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
5.255.251Inspect left side -
FIGURE 5
4.809.602Left side repair or
preventive modifica-
tion (Paragraph 3.B.,
Work Instructions,
PART 5)
1.503.002Close Access
13.0520.85TOTAL FOR EACH AIRPLANE
Group 1-2, 4:
Table 5 - Post-Repair/Post-Modification Inspection
Elapsed HoursTask HoursNumber of PersonsTask
0.100.101Open Access
16.5033.002Inspect left and right
side - FIGURE 7
0.100.101Close Access
16.7033.20TOTAL FOR EACH AIRPLANE
Group 3, 5:
Table 6 - Post-Repair/Post-Modification Inspection
Elapsed HoursTask HoursNumber of PersonsTask
0.100.101Open Access
8.2516.502Inspect left side only
- FIGURE 7
0.100.101Close Access
8.4516.70TOTAL FOR EACH AIRPLANE
NOTE: Additional time may be required for repairs if cracks are found.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+132935.5+58.2Group 1
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Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+132935.5+58.2Group 2
+66467.7+29.1Group 3
+132935.5+58.2Group 4
+65709.7+28.8Group 5
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR 85901-110RS
b. Boeing Service Related Problem (SRP) 747-SRP-53-0361
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2009-18-07, 2010-01-01
d. Service Bulletin Index D6-30300
e. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 53-30-00
f. 747-100/200/300 Aircraft Maintenance Manual (AMM) 25-21-03, 25-21-04
g. 747-400 Aircraft Maintenance Manual (AMM) 25-21-01, 52-11-00
2. Data supplied with this Service Bulletin
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
--1Kit - Aft Upper Corner Repair, Main Entry
Door #5
675U0001
--2
--3
--4
--5
--6
--7
--8
--DL
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3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Skin Panel Instl - STA 2181.1 to STA 2360 S-12 thru S-1965B04157
Strap Installation - No. 5 Entry Door65B04850
Reveal Instl - Upper & Lower No. 5 Main Entry Door65B04856
The table above lists applicable drawings used to prepare this service bulletin. The 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:
Chapter-SectionPublication
747 Aircraft Maintenance Manual
747 Corrosion Prevention Manual
747 Fault Reporting Manual
747 Fault Isolation Manual
747 Structural Repair Manual
53-12747 Illustrated Parts Catalog
747 Weight and Balance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the origi-
nal issue date of this Ser-
vice Bulletin (US Dollars)
ROLT as of the original
issue date of this Service
Bulletin (Calendar Days)
NameKit Number
$16,336(a)Top Kit - Door 5 Cutout Aft
Upper Corner Small Repair
- Group 1
015U1914-1
$17,426(a)Top Kit - Door 5 Cutout Aft
Upper Corner Small Repair
- Group 2
015U1914-2
$8,713(a)Top Kit - Door 5 Cutout Aft
Upper Corner Small Repair
- Group 3
015U1914-3
$16,362(a)Top Kit - Door 5 Cutout Aft
Upper Corner Small Repair
- Group 4
015U1914-4
$7,731(a)Top Kit - Door 5 Cutout Aft
Upper Corner Small Repair
- Group 5
015U1914-5
$16,016(a)Top Kit - Door 5 Cutout Aft
Upper Corner Large Repair
- Group 1
015U1914-11
$17,130(a)Top Kit - Door 5 Cutout Aft
Upper Corner Large Repair
- Group 2
015U1914-12
$8,565(a)Top Kit - Door 5 Cutout Aft
Upper Corner Large Repair
- Group 3
015U1914-13
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REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the origi-
nal issue date of this Ser-
vice Bulletin (US Dollars)
ROLT as of the original
issue date of this Service
Bulletin (Calendar Days)
NameKit Number
$15,890(a)Top Kit - Door 5 Cutout Aft
Upper Corner Large Repair
- Group 4
015U1914-14
$7,654(a)Top Kit - Door 5 Cutout Aft
Upper Corner Large Repair
- Group 5
015U1914-15
(a) Refer to the Boeing PART page on myboeingfleet.com or contact first responder at fr@boeing.com for
Reorder Lead Time (ROLT) information.
B. Industry Support Information
Boeing warranty remedies are available for 747 airplanes in warranty as of September 2, 1997. For
task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be
supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order.
Boeing warranty remedies are not available for the inspection or repair procedures given in this service
bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials
Supplied by the Operator, are necessary for each airplane.
1.
2. If grip length shown is not available at Boeing, fasteners supplied in kits may be
one grip length longer than indicated. Also, if any fasteners part numbers listed
are not available or have been superseded, substitute fasteners may be supplied
in kits. Boeing Document D-590 and Boeing Drawing 65B88700 are used to
determine the part numbers used as substitutes.
Kit 015U1914
NotesExisting Part
Number
NameQTYNew Part Number
-5-4-3-2-1
Top Kit - Door 5
Cutout Aft Upper
Corner Small Re-
pair - Group 1
....-015U1914-1
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Kit 015U1914
NotesExisting Part
Number
NameQTYNew Part Number
-5-4-3-2-1
Top Kit - Door 5
Cutout Aft Upper
Corner Small Re-
pair - Group 2
...-.015U1914-2
Top Kit - Door 5
Cutout Aft Upper
Corner Small Re-
pair - Group 3
..-..015U1914-3
Top Kit - Door 5
Cutout Aft Upper
Corner Small Re-
pair - Group 4
.-...015U1914-4
Top Kit - Door 5
Cutout Aft Upper
Corner Small Re-
pair - Group 5
-....015U1914-5
KIT....1675U0001-1
KIT....1675U0001-2
KIT..11.675U0001-3
KIT...1.675U0001-4
KIT.1...675U0001-5
KIT.1...675U0001-6
KIT1....675U0001-7
Kit 015U1914
NotesExisting Part
Number
NameQTYNew Part Number
-15-14-13-12-11
Top Kit - Door 5
Cutout Aft Upper
Corner Large Re-
pair - Group 1
....-015U1914-11
Top Kit - Door 5
Cutout Aft Upper
Corner Large Re-
pair - Group 2
...-.015U1914-12
Top Kit - Door 5
Cutout Aft Upper
Corner Large Re-
pair - Group 3
..-..015U1914-13
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Kit 015U1914
NotesExisting Part
Number
NameQTYNew Part Number
-15-14-13-12-11
Top Kit - Door 5
Cutout Aft Upper
Corner Large Re-
pair - Group 4
.-...015U1914-14
Top Kit - Door 5
Cutout Aft Upper
Corner Large Re-
pair - Group 5
-....015U1914-15
KIT....1675U0001-10
KIT..11.675U0001-11
KIT...1.675U0001-12
KIT.1...675U0001-13
KIT.1...675U0001-14
KIT1....675U0001-15
KIT....1675U0001-9
Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
KIT...-675U0001-1
KIT..-.675U0001-2
KIT.-..675U0001-3
KIT-...675U0001-4
UPR AFT DEPRES-
SOR
.1.165B04856-25
UPR AFT DEPRES-
SOR
1.1.65B04856-26
UPR AFT DEPRES-
SOR
.1.165B04856-27
UPR AFT DEPRES-
SOR
1.1.65B04856-28
SHIM111165B04856-31
DOUBLER.1.1675U0002-1
FILLER.1.1675U0002-13
FILLER1.1.675U0002-14
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### Page 35

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
DOUBLER1.1.675U0002-2
TRIPLER.1.1675U0002-3
TRIPLER1.1.675U0002-4
QUADRUPLER.1.1675U0002-5
QUADRUPLER1.1.675U0002-6
BOLT1111BACB30MY5K3
BOLT1111BACB30MY5K8
BOLT2222BACB30MY8K7
BOLT17171111BACB30NW6K10X
BOLT88..BACB30NW6K10Y
BOLT15151313BACB30NW6K11X
BOLT41414141BACB30NW6K12X
BOLT1111BACB30NW6K13X
BOLT1111BACB30NW6K14X
BOLT2233BACB30NW6K5X
BOLT2211BACB30NW6K5Y
BOLT4422BACB30NW6K6X
BOLT30301111BACB30NW6K7X
BOLT5555BACB30NW6K8
BOLT112020BACB30NW6K8X
BOLT1818..BACB30NW6K8Y
BOLT14141212BACB30NW6K9X
BOLT22..BACB30NW8K10Y
BOLT3333BACB30NW8K11X
BOLT20201818BACB30NW8K12X
BOLT6644BACB30NW8K13X
BOLT2222BACB30NW8K14X
BOLT7766BACB30NW8K15X
BOLT8888BACB30NW8K16X
BOLT7777BACB30NW8K17X
BOLT22222222BACB30NW8K3
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### Page 36

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
BOLT74747474BACB30NW8K4
BOLT9999BACB30NW8K5
BOLT36364242BACB30NW8K6
BOLT66..BACB30NW8K6Y
BOLT772424BACB30NW8K7
BOLT..22BACB30NW8K8
BOLT4444BACB30NW8K8X
BOLT22..BACB30NW8K8Y
BOLT337575BACB30NW8K9
BOLT8844BACB30NW8K9X
BOLT6666..BACB30NW8K9Y
COLLAR2222BACC30M5
COLLAR120120130130BACC30M6
COLLAR247247317317BACC30M8
COLLAR333311BACC30R6
COLLAR7777..BACC30R8
FILLER1111BACF3F011M030NF
FILLER1111BACF3F011M042NF
FILLER1111BACF3F023M024NF
FILLER1111BACF3F023M036NF
FILLER1111BACF3F065X069NN
RIVET2222BACR15BB5D5C
RIVET1111BACR15BB5D7C
RIVET1111BACR15BB5D9C
RIVET2222BACR15BB8D12C
RIVET1111BACR15GF6D9
SHIM1111BACS40R010E010F
SHIM1111BACS40R065E069F
WASHER, SELF-
ALIGN
30302121BACW10CA104CC
WASHER, SELF-
ALIGN
30302121BACW10CA31PV
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### Page 37

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
WASHER, SELF-
ALIGNING
15151212BACW10CA41PV
WASHER15151212BACW10CA5CC
RIVET7777MS20615-6MP13
RIVET4444MS20615-6MP18
RIVET1111MS20615-8MP14
RIVET1111MS20615-8MP15
Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-7-6-5
KIT..-675U0001-5
KIT.-.675U0001-6
KIT-..675U0001-7
UPR AFT DEPRES-
SOR
1.165B04856-25
UPR AFT DEPRES-
SOR
.1.65B04856-26
UPR AFT DEPRES-
SOR
1.165B04856-27
UPR AFT DEPRES-
SOR
.1.65B04856-28
SHIM11165B04856-31
DOUBLER1.1675U0002-1
FILLER..1675U0002-13
FILLER.1.675U0002-14
DOUBLER.1.675U0002-2
TRIPLER1.1675U0002-3
TRIPLER.1.675U0002-4
QUADRUPLER1.1675U0002-5
QUADRUPLER.1.675U0002-6
BOLT.11BACB30MY5K3
BOLT.11BACB30MY5K8
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### Page 38

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-7-6-5
BOLT.22BACB30MY8K7
BOLT1499BACB30NW6K10X
BOLT.88BACB30NW6K10Y
BOLT121212BACB30NW6K11X
BOLT382727BACB30NW6K12X
BOLT.44BACB30NW6K15X
BOLT444BACB30NW6K5X
BOLT211BACB30NW6K5Y
BOLT466BACB30NW6K6X
BOLT122BACB30NW6K6Y
BOLT999BACB30NW6K7X
BOLT555BACB30NW6K8
BOLT171818BACB30NW6K8Y
BOLT111111BACB30NW6K9X
BOLT.22BACB30NW8K10Y
BOLT333BACB30NW8K11X
BOLT202020BACB30NW8K12X
BOLT444BACB30NW8K13X
BOLT222BACB30NW8K14X
BOLT777BACB30NW8K15X
BOLT888BACB30NW8K16X
BOLT777BACB30NW8K17X
BOLT222222BACB30NW8K3
BOLT797474BACB30NW8K4
BOLT999BACB30NW8K5
BOLT373636BACB30NW8K6
BOLT866BACB30NW8K6Y
BOLT212424BACB30NW8K7
BOLT444BACB30NW8K8X
BOLT322BACB30NW8K8Y
BOLT333BACB30NW8K9
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### Page 39

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-7-6-5
BOLT444BACB30NW8K9X
BOLT686868BACB30NW8K9Y
COLLAR.22BACC30M5
COLLAR103106106BACC30M6
COLLAR240240240BACC30M8
COLLAR203232BACC30R6
COLLAR807979BACC30R8
FILLER.11BACF3F011M030NF
FILLER.11BACF3F011M042NF
FILLER.11BACF3F023M024NF
FILLER.11BACF3F023M036NF
FILLER111BACF3F065X069NN
RIVET.22BACR15BB5D5C
RIVET.11BACR15BB5D7C
RIVET.11BACR15BB5D9C
RIVET222BACR15BB8D12C
RIVET111BACR15GF6D9
SHIM111BACS40R010E010F
SHIM111BACS40R065E069F
WASHER, SELF-
ALIGN
131313BACW10CA104CC
WASHER, SELF-
ALIGN
131313BACW10CA31PV
WASHER, SELF-
ALIGNING
151515BACW10CA41PV
WASHER151515BACW10CA5CC
RIVET777MS20615-6MP13
RIVET444MS20615-6MP18
RIVET111MS20615-8MP14
RIVET111MS20615-8MP15
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### Page 40

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-12-11-10-9
KIT..-.675U0001-10
KIT.-..675U0001-11
KIT-...675U0001-12
KIT...-675U0001-9
UPR AFT DEPRES-
SOR
.1.165B04856-25
UPR AFT DEPRES-
SOR
1.1.65B04856-26
UPR AFT DEPRES-
SOR
.1.165B04856-27
UPR AFT DEPRES-
SOR
1.1.65B04856-28
SHIM111165B04856-31
TRIPLER1.1.675U0002-10
QUADRUPLER.1.1675U0002-11
QUADRUPLER1.1.675U0002-12
FILLER.1.1675U0002-13
FILLER1.1.675U0002-14
DOUBLER.1.1675U0002-7
DOUBLER1.1.675U0002-8
TRIPLER.1.1675U0002-9
BOLT1111BACB30MY5K3
BOLT1111BACB30MY5K8
BOLT2222BACB30MY8K7
BOLT19191313BACB30NW6K10X
BOLT88..BACB30NW6K10Y
BOLT16161414BACB30NW6K11X
BOLT48484848BACB30NW6K12X
BOLT1111BACB30NW6K13X
BOLT1111BACB30NW6K14X
BOLT44..BACB30NW6K4Y
BOLT3333BACB30NW6K5X
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### Page 41

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-12-11-10-9
BOLT8877BACB30NW6K5Y
BOLT8822BACB30NW6K6X
BOLT44..BACB30NW6K6Y
BOLT13131313BACB30NW6K7X
BOLT11..BACB30NW6K7Y
BOLT4444BACB30NW6K8
BOLT..1919BACB30NW6K8X
BOLT1818..BACB30NW6K8Y
BOLT16161414BACB30NW6K9X
BOLT22..BACB30NW8K10Y
BOLT3333BACB30NW8K11X
BOLT20201818BACB30NW8K12X
BOLT6644BACB30NW8K13X
BOLT2222BACB30NW8K14X
BOLT7766BACB30NW8K15X
BOLT8888BACB30NW8K16X
BOLT7777BACB30NW8K17X
BOLT22222222BACB30NW8K3
BOLT84848383BACB30NW8K4
BOLT21212121BACB30NW8K5
BOLT90909494BACB30NW8K6
BOLT..22BACB30NW8K6X
BOLT66..BACB30NW8K6Y
BOLT24242424BACB30NW8K7
BOLT..22BACB30NW8K8
BOLT4444BACB30NW8K8X
BOLT22..BACB30NW8K8Y
BOLT337474BACB30NW8K9
BOLT4444BACB30NW8K9X
BOLT7070..BACB30NW8K9Y
COLLAR2222BACC30M5
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### Page 42

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-12-11-10-9
COLLAR139139142142BACC30M6
COLLAR319319392392BACC30M8
COLLAR484877BACC30R6
COLLAR8181..BACC30R8
FILLER1111BACF3F023M024NF
FILLER1111BACF3F023M036NF
FILLER1111BACF3F069X078NN
RIVET2222BACR15BB5D5C
RIVET1111BACR15BB5D7C
RIVET1111BACR15BB5D9C
RIVET2222BACR15BB8D12C
RIVET1111BACR15GF6D9
SHIM1111BACS40R010E010F
SHIM1111BACS40R069E078F
WASHER, SELF-
ALIGN
33332424BACW10CA104CC
WASHER, SELF-
ALIGN
33332424BACW10CA31PV
WASHER, SELF-
ALIGNING
15151212BACW10CA41PV
WASHER15151212BACW10CA5CC
RIVET7777MS20615-6MP13
RIVET4444MS20615-6MP18
RIVET1111MS20615-8MP14
RIVET1111MS20615-8MP15
Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-15-14-13
KIT..-675U0001-13
KIT.-.675U0001-14
KIT-..675U0001-15
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### Page 43

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-15-14-13
UPR AFT DEPRES-
SOR
1.165B04856-25
UPR AFT DEPRES-
SOR
.1.65B04856-26
UPR AFT DEPRES-
SOR
1.165B04856-27
UPR AFT DEPRES-
SOR
.1.65B04856-28
SHIM11165B04856-31
TRIPLER.1.675U0002-10
QUADRUPLER1.1675U0002-11
QUADRUPLER.1.675U0002-12
FILLER..1675U0002-13
FILLER.1.675U0002-14
DOUBLER1.1675U0002-7
DOUBLER.1.675U0002-8
TRIPLER1.1675U0002-9
BOLT.11BACB30MY5K3
BOLT.11BACB30MY5K8
BOLT.22BACB30MY8K7
BOLT1399BACB30NW6K10X
BOLT.88BACB30NW6K10Y
BOLT131212BACB30NW6K11X
BOLT444444BACB30NW6K12X
BOLT.44BACB30NW6K15X
BOLT.44BACB30NW6K4Y
BOLT444BACB30NW6K5X
BOLT777BACB30NW6K5Y
BOLT355BACB30NW6K6X
BOLT.66BACB30NW6K6Y
BOLT141414BACB30NW6K7X
BOLT.11BACB30NW6K7Y
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### Page 44

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-15-14-13
BOLT444BACB30NW6K8
BOLT333BACB30NW6K8X
BOLT181818BACB30NW6K8Y
BOLT111111BACB30NW6K9X
BOLT.22BACB30NW8K10Y
BOLT333BACB30NW8K11X
BOLT202020BACB30NW8K12X
BOLT444BACB30NW8K13X
BOLT222BACB30NW8K14X
BOLT777BACB30NW8K15X
BOLT888BACB30NW8K16X
BOLT777BACB30NW8K17X
BOLT222222BACB30NW8K3
BOLT858181BACB30NW8K4
BOLT212121BACB30NW8K5
BOLT939090BACB30NW8K6
BOLT866BACB30NW8K6Y
BOLT212424BACB30NW8K7
BOLT444BACB30NW8K8X
BOLT322BACB30NW8K8Y
BOLT333BACB30NW8K9
BOLT444BACB30NW8K9X
BOLT666868BACB30NW8K9Y
COLLAR.22BACC30M5
COLLAR116119119BACC30M6
COLLAR316318318BACC30M8
COLLAR284444BACC30R6
COLLAR797979BACC30R8
FILLER.11BACF3F023M024NF
FILLER.11BACF3F023M036NF
FILLER111BACF3F069X078NN
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### Page 45

Kit 675U0001
NotesExisting Part
Number
NameQTYNew Part Number
-15-14-13
RIVET.22BACR15BB5D5C
RIVET.11BACR15BB5D7C
RIVET.11BACR15BB5D9C
RIVET222BACR15BB8D12C
RIVET111BACR15GF6D9
SHIM111BACS40R010E010F
SHIM111BACS40R069E078F
WASHER, SELF-
ALIGN
131313BACW10CA104CC
WASHER, SELF-
ALIGN
131313BACW10CA31PV
WASHER, SELF-
ALIGNING
151515BACW10CA41PV
WASHER151515BACW10CA5CC
RIVET, SOLID777MS20615-6MP13
RIVET, SOLID444MS20615-6MP18
RIVET, SOLID111MS20615-8MP14
RIVET, SOLID111MS20615-8MP15
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
4 to 10 necessary, depend-
ing on airplane group and
seal depressor configura-
tion, for each open-hole
HFEC inspection done in
accordance with FIGURE 5
and/or FIGURE 6. (b)
Rivet4 - 10BACR15CE6D8
(a)Sealant1 pintBMS 5-95
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(b) Optional: BACR15GF6D8, BACR15GF61D8 or BACR15GF7D8.
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### Page 46

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 47

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
– 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 limits to tighten nuts and bolts are in SRM Chapter 51
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. 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.
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### Page 48

9. 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.
10. 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.
11. 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.
12. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
13. Edge Margin is defined as the distance from the centerline of a fastener hole (or
fastener) to the nearest part edge.
B. WORK INSTRUCTIONS
PART 1 - Left Main Entry Door 5 Inspection for Existing Repair and Edge Margin Measurement
1. Get external access to the aft upper corner of the cutout for left Main Entry Door 5.
2. Do a detailed inspection of the aft upper corner of the cutout for left Main Entry Door 5 for the
existence of a repair in accordance with FIGURE 1.
3. Measure the edge margin at certain fastener locations in accordance with FIGURE 2.
4. If a repair is found at the aft upper corner of the cutout for left Main Entry Door 5, contact Boeing
with details of the repair, including the fastener edge margins measured in accordance with FIGURE
2. Do inspections or change the repair, as described by Boeing.
5. If no repair is found, do an inspection in accordance with PART 3 at the applicable time given in
Paragraph 1.E., Compliance, Table 1.
Group 1-2, 4:
PART 2 - Right Main Entry Door 5 Inspection for Existing Repair and Edge Margin Measurement
1. Get external access to the aft upper corner of the cutout for right Main Entry Door 5.
2. Do a detailed inspection of the aft upper corner of the cutout for right Main Entry Door 5 for the
existence of a repair in accordance with FIGURE 3.
3. Measure the edge margin at certain fastener locations in accordance with FIGURE 4.
4. If a repair is found at the aft upper corner of the cutout for right Main Entry Door 5, contact Boeing
with details of the repair, including the fastener edge margins measured in accordance with FIGURE
4. Do inspections or change the repair, as described by Boeing.
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### Page 49

5. If no repair is found, do an inspection in accordance with PART 4 at the applicable time given in
Paragraph 1.E., Compliance, Table 2.
PART 3 - Left Main Entry Door 5 Detailed and HFEC Inspections
1. Open left Main Entry Door 5. Refer to 747-400 AMM 52-11-00 as an accepted procedure.
2. Remove and keep the doorway lining and sidewall insulation above MED 5. Refer to 747-400 AMM
25-21-01 or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04 as accepted
procedures.
3. Do inspections of the aft upper corner of the cutout for left Main Entry Door 5 in accordance with
FIGURE 5.
4. If no crack is found, install equipment removed for access and put the airplane back to a serviceable
condition. Do the inspections in PART 3 again and install the preventive modification in accordance
with PART 5 at the applicable times given in Paragraph 1.E., Compliance, Table 1.
NOTE: As an alternative, install a preventive modification in accordance with PART 5
5. If all cracks found are less than 3.0 inches long, install a repair in accordance with PART 5.
6. If any crack found that is 3.0 inches long or longer, install a repair in accordance with PART 6.
Group 1-2, 4:
PART 4 - Right Main Entry Door 5 Detailed and HFEC Inspections
1. Open right Main Entry Door 5. Refer to 747-400 AMM 52-11-00 as an accepted procedure.
2. Remove and keep the doorway lining and sidewall insulation above MED 5. Refer to 747-400 AMM
25-21-01 or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04 as accepted
procedures.
3. Do inspections of the aft upper corner of the cutout for right Main Entry Door 5 in accordance with
FIGURE 6.
4. If no crack is found, install equipment removed for access and put the airplane back to a serviceable
condition. Do the inspections in PART 4 again and install the preventive modification in accordance
with PART 5 at the applicable times given in Paragraph 1.E., Compliance, Table 2.
NOTE: As an alternative, install a preventive modification in accordance with PART 5.
5. If all cracks found are less than 3.0 inches long, install a repair in accordance with PART 5.
6. If any crack found that is 3.0 inches long or longer, install a repair in accordance with PART 6.
PART 5 - Preventive Modification/Small Repair (Repair for Cracks Less Than 3.0 Inches Long,
or if No Cracks are Found)
1. Open the affected Main Entry Door 5. Refer to 747-400 AMM 52-11-00 as an accepted procedure.
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### Page 50

2. Remove and keep the doorway lining and sidewall insulation above MED 5. Refer to 747-400 AMM
25-21-01 or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04 as accepted
procedures.
3. Do the steps that follow. For each affected airplane group, do the work in accordance with the
Boeing drawings shown in the table that follows:
Right SideLeft SideGroup
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 1
(675U0001-2 Installation)
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 1
(675U0001-1 Installation)
1
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 2
(675U0001-4 Installation)
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 2
(675U0001-3 Installation)
2
-Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 2
(675U0001-3 Installation)
3
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 3
(675U0001-6 Installation)
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 3
(675U0001-5 Installation)
4
-Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 4
(675U0001-7 Installation)
5
a. Remove and keep the gutter from above the door cutout.
b. Remove and discard seal depressors at the aft upper corner of the door cutout.
c. Trim the skin and bear strap at the aft upper corner of the door cutout. The table that follows
gives the location of the detailed trim dimensions on each affected drawing sheet. If a different
trim profile than shown in the drawing is necessary, contact Boeing.
NOTE: It is not necessary to trim the skin and bear strap if no cracks were found during the
inspections done in accordance with PART 3 or PART 4, and if the edge margin
measured in PART 1 or PART 2 at all affected fastener holes is 3.50D or greater
(where D is the fastener hole diameter).
Trim Detail LocationDrawingGroup
View 1D13 in Zone B28Drawing 675U0001, Sheet 11
View 1D13 in Zone E27Drawing 675U0001, Sheet 22, 3
View 2D13 in Zone B27Drawing 675U0001, Sheet 34
View 1D13 in Zone B28Drawing 675U0001, Sheet 45
d. Install seal depressors and a doubler, tripler and a quadrupler, and reinstall the gutter in
accordance with the applicable Boeing drawings.
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### Page 51

4. Install the sidewall insulation and doorway lining above MED 5. Refer to 747-400 AMM 25-21-01
or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04 as accepted procedures.
5. Put the airplane back in a serviceable condition. Do the post-repair/post-modification inspection
in PART 7 at the time given in Paragraph 1.E., Compliance, Table 3.
PART 6 - Large Repair (Repair for Cracks 3.0 Inches Long or Longer)
1. Open the affected Main Entry Door 5. Refer to 747-400 AMM 52-11-00 as an accepted procedure.
2. Remove and keep the doorway lining and sidewall insulation above MED 5. Refer to 747-400 AMM
25-21-01 or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04 as accepted
procedures.
3. Do the steps that follow. For each affected airplane group, do the work in accordance with the
Boeing drawings shown in the table that follows:
Right SideLeft SideGroup
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 5
(675U0001-10 Installation)
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 5
(675U0001-9 Installation)
1
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 6
(675U0001-12 Installation)
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 6
(675U0001-11 Installation)
2
-Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 6
(675U0001-11 Installation)
3
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 7
(675U0001-14 Installation)
Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 7
(675U0001-13 Installation)
4
-Boeing Drawing 675U0001, Sheet DL and
Boeing Drawing 675U0001, Sheet 8
(675U0001-15 Installation)
5
a. Remove and keep the gutter from above the door cutout.
b. Remove and discard seal depressors at the aft upper corner of the door cutout.
c. Trim the skin and bear strap at the aft upper corner of the door cutout. The table that follows
gives the location of the detailed trim dimensions on each affected drawing sheet. If a different
trim profile than shown in the drawing is necessary, contact Boeing.
Trim Detail LocationDrawingGroup
View 1D14 in Zone B28Drawing 675U0001, Sheet 51
View 1D13 in Zone E27Drawing 675U0001, Sheet 62, 3
View 3D13 in Zone B27Drawing 675U0001, Sheet 74
View 1D14 in Zone B28Drawing 675U0001, Sheet 85
BOEING PROPRIETARY -
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Original Issue: November 06, 2012
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### Page 52

d. Install seal depressors and a doubler, tripler and a quadrupler, and reinstall the gutter in
accordance with the applicable Boeing drawings.
4. Install the sidewall insulation and doorway lining above MED 5. Refer to 747-400 AMM 25-21-01
or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04 as accepted procedures.
5. Put the airplane back in a serviceable condition. Do the post-repair/post-modification inspection
in PART 7 at the time given in Paragraph 1.E., Compliance, Table 3.
PART 7 - Post-Repair/Post-Modification Inspection
1. Open left Main Entry Door 5. Refer to 747-400 AMM 52-11-00 as an accepted procedure.
2. Group 1-2, 4:
Open right Main Entry Door 5. Refer to 747-400 AMM 52-11-00 as an accepted procedure.
3. Remove and keep the doorway lining and sidewall insulation above the affected MED 5. Refer to
747-400 AMM 25-21-01 or 747-100/200/300 AMM 25-21-03 and 747-100/200/300 AMM 25-21-04
as accepted procedures.
4. Do inspections in accordance with FIGURE 7.
5. If any crack is found, contact Boeing for repair instructions and do the repair.
6. If no crack is found, install equipment removed for access and put the airplane back in a serviceable
condition. Do the inspection in PART 7 again at the time given in Paragraph 1.E., Compliance,
Table 3.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 06, 2012
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-53A2839
ALERT  ALERT
AND  STA
2285  SKIN
'UPPER
MAIN
SILL
+
•EDGE
OF
BEAR
STRAP
+  +-5-17
EDGE OF SKIN
AND BEAR
STRAP
FWD  8L8L12
FIGURE 1: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE LEFT MAIN
ENTRY DOOR 5 CUTOUT
(SHEET 1 OF 3)
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BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  53 of 76

### Page 54

FIGURE 1: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE LEFT MAIN
ENTRY DOOR 5 CUTOUT
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 06, 2012
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### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do a detailed Inspec-
tion at the aft upper
corner of the door 5
cutout, for any repair
installed in the area
shown. (a)
--Fuselage SkinInspect1
(a) A repair may consist of external doublers, freeze plugs, blendouts, or oversize fasteners. Any rivet with
a manufactured head diameter greater than 0.298 inch should be considered an oversize fastener for the
purposes of this inspection.
FIGURE 1: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE LEFT MAIN
ENTRY DOOR 5 CUTOUT
(SHEET 3 OF 3)
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### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-53A2839
ALERT  ALERT
A AND B  STA  2285  SKIN
UPPER
MAIN
SILL
+
•EDGE
EDGE  OF
MARGIN  BEAR
(TYPICAL)  STRAP
+-8-17
EDGE OF SKIN
AND BEAR
STRAP
FWD
FIGURE 2: EDGE MARGIN MEASUREMENT AT THE AFT UPPER CORNER OF THE LEFT MAIN ENTRY
DOOR 5 CUTOUT
(SHEET 1 OF 3)
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Copyright © Unpublished Work - See page 1 for details.  56 of 76

### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-53A2839
ALERT  ALERT
STA
2285  SKIN
- UPPER
MAIN
SILL
• EDGE OF
EDGE  BEAR
MARGIN  STRAP
(TYPICAL)
- S-17
EDGE OF
SKIN AND
BEAR STRAP
+17
FWD
ALTERNATE CONFIGURATION  2117515
FIGURE 2: EDGE MARGIN MEASUREMENT AT THE AFT UPPER CORNER OF THE LEFT MAIN ENTRY
DOOR 5 CUTOUT
(SHEET 2 OF 3)
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Copyright © Unpublished Work - See page 1 for details.  57 of 76

### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)--Fastener Edge MarginMeasure1
(a)--Fastener Edge MarginRecord
(a) At each of the four fastener locations (as shown in Detail A) or five fastener locations (as shown in Detail
B), depending on the existing configuration, common to the seal depressor in the area shown.
FIGURE 2: EDGE MARGIN MEASUREMENT AT THE AFT UPPER CORNER OF THE LEFT MAIN ENTRY
DOOR 5 CUTOUT
(SHEET 3 OF 3)
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### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-53A2839
ALERT  ALERT
This Figure applies only to: Group 1-2, 4.
SKIN  2285  STA  AND B
UPPER -
MAIN
SILL
EDGE
OF
BEAR
STRAP
S-17-\
EDGE OF SKIN
AND BEAR
STRAP
FWD  2117550
FIGURE 3: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE RIGHT MAIN
ENTRY DOOR 5 CUTOUT
(SHEET 1 OF 3)
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### Page 60

FIGURE 3: INSPECTION FOR EXISTING REPAIRS AT THE AFT UPPER CORNER OF THE RIGHT MAIN
ENTRY DOOR 5 CUTOUT
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 06, 2012
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