# Boeing Alert Service Bulletin 747-53A2451: Revision 2

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- Document: [Boeing Alert Service Bulletin 747-53A2451](https://openairdocs.org/service-documents/boeing/747-53a2451.md)
- Title as filed: U.S. DOT/FAA - SB-747-53A2451-02
- Pages: 163
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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2451
Original Issue: October 05, 2000
Revision 2: June 13, 2014
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Door Number 2 Forward Edge Frame at Body Station 800
- Inspection and Repair
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 © 2000 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Unpublished Work.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.
Original Issue: October 05, 2000
747-53A2451Revision 2: June 13, 2014
1 of 163
6.0

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Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 8
B. Concurrent Requirements ...................................... 1 8
C. Reason ................................................ 1 8
D. Description .............................................. 2 0
E. Compliance .............................................. 2 1
F. Approval ............................................... 2 5
G. Manpower .............................................. 2 5
H. Weight and Balance Changes .................................... 2 9
I. Electrical Load Data ......................................... 2 9
J. References .............................................. 2 9
1. Existing Data: ......................................... 2 9
2. Data Supplied with this Service Bulletin: ........................... 3 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 0
4. Process Data: ......................................... 3 0
K. Publications Affected ........................................ 3 0
L. Interchangeability and Intermixability of Parts ........................... 3 1
M. Software Accomplishment Summary ................................ 3 1
2. MATERIAL INFORMATION ........................................ 3 3
A. Material - Price and Availability ................................... 3 3
B. Industry Support Information .................................... 3 3
C. Parts Necessary for Each Airplane ................................. 3 3
1. Kits/Parts: ........................................... 3 3
2. Parts and Materials Supplied by the Operator: ........................ 3 3
3. Parts Modified and Reidentified: ............................... 4 7
4. Parts Removed and Not Replaced: .............................. 4 8
D. Parts Necessary to Change Spares ................................. 4 8
E. Special Tooling - Price and Availability ............................... 4 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 9
A. GENERAL INFORMATION ..................................... 4 9
B. WORK INSTRUCTIONS ....................................... 5 0
FIGURE 1: THIS FIGURE IS DELETED .................................. 5 7
FIGURE 2: ACCESS ............................................ 5 8
FIGURE 3: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL [Group 1] ................. 6 4
FIGURE 4: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL [Group 2] ................. 6 7
FIGURE 5: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL [Group 3] ................. 7 0
FIGURE 6: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - INSPECTION [Group 1] ........ 7 3
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FIGURE 7: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - INSPECTION [Group 2] ........ 7 7
FIGURE 8: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - INSPECTION [Group 3] ........ 8 2
FIGURE 9: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - FASTENER REMOVAL [Group 4] . . 87
FIGURE 10: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - INSPECTION [Group 4] ........ 9 0
FIGURE 11: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - INSPECTION [Group 5] ........ 9 5
FIGURE 12: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL [Group 6] ................ 1 0 1
FIGURE 13: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL - INSPECTION [Group 6] ....... 1 0 4
FIGURE 14: DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN STRINGER
14 AND STRINGER 18 - FASTENER REMOVAL [Group 5] ................ 1 0 9
FIGURE 15: LEFT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
STRINGER 18 AND DOOR STOP NO. 5 - FASTENER REMOVAL ............ 1 1 2
FIGURE 16: LEFT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
STRINGER 18 AND DOOR STOP NO. 5 - INSPECTION ................. 1 1 5
FIGURE 17: LEFT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 5 AND DOOR STOP NO. 1 - FASTENER REMOVAL ......... 1 2 0
FIGURE 18: LEFT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 5 AND DOOR STOP NO. 1 - INSPECTION .............. 1 2 3
FIGURE 19: LEFT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 1 AND STRINGER 30 - FASTENER REMOVAL ............ 1 2 8
FIGURE 20: LEFT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 1 AND STRINGER 30 - INSPECTION ................. 1 3 1
FIGURE 21: RIGHT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
STRINGER 18 AND DOOR STOP NO. 5 - FASTENER REMOVAL ............ 1 3 6
FIGURE 22: RIGHT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
STRINGER 18 AND DOOR STOP NO. 5 - INSPECTION ................. 1 3 9
FIGURE 23: RIGHT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 5 AND DOOR STOP NO. 1 - FASTENER REMOVAL ......... 1 4 4
FIGURE 24: RIGHT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 5 AND DOOR STOP NO. 1 - INSPECTION .............. 1 4 7
FIGURE 25: RIGHT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 1 AND STRINGER 30 - FASTENER REMOVAL ............ 1 5 2
FIGURE 26: RIGHT SIDE DOOR NUMBER 2 FORWARD EDGE FRAME AT BODY STATION 800 BETWEEN
DOOR STOP NO. 1 AND STRINGER 30 - INSPECTION ................. 1 5 5
APPENDIX A: ADDENDUM - FLIGHT SAFETY SECTION ......................... 1 6 0
APPENDIX B: LOGIC DIAGRAM - INSPECTION OF DOOR NUMBER 2 FORWARD EDGE FRAME AT STA
800 BETWEEN STRINGER 14 AND STRINGER 18 .................... 1 6 2
APPENDIX C: LOGIC DIAGRAM - INSPECTION OF DOOR NUMBER 2 FORWARD EDGE FRAME AT STA
800 BETWEEN STRINGER 18 AND STRINGER 30 .................... 1 6 3
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BOEING SERVICE BULLETIN 747-53A2451
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-53A2451Original Issue: October 05, 2000
Revision 2: June 13, 2014
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Door Number 2 Forward Edge Frame at Body Station 800
- Inspection and Repair
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2007-16-08, is related to this service bulletin.
More work is necessary on the airplane(s) inspected in accordance with the original issue or Revision 1 of this
service bulletin. Inspection of the STA 800 frame inner chord between stringer 18 and stringer 30 is necessary.
Large Cargo Freighter (LCF) Airplanes RT743, RT876, RT631 and RT632 were removed from this service
bulletin effectivity.
REASON FOR REVISION
This revision is sent to expand the inspection area to include the STA 800 frame inner chord between stringer
18 and stringer 30. Additionally a new inspection threshold for STA 800 frame inner chord between stringer 18
and stringer 30 has been added.
Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph
3.A., General Information - Notes.
These sections were changed:
1. Summary, Background - added Planning Data table and additional service history.
2. Summary, revised Summary illustration.
3. Summary, revised Compliance to reference a new Airworthiness Directive (AD) .
4. Paragraph 1.A.1., Airplanes - RT743, RT876, RT631 and RT632 were removed.
5. Paragraph 1.E., Compliance, revised Compliance paragraph to reference a new Airworthiness Directive
(AD) and compliance tables to give new inspection areas and new inspection thresholds.
6. Paragraph 1.F., Approval - deleted a paragraph and added a paragraph.
7. Paragraph 1.G., Manpower - Revised manpower tables.
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8. Paragraph 1.J., Existing Data - added references.
9. Paragraph 2.C.2., Parts and Materials Supplied by the Operator - added fasteners.
10. Paragraph 3.A., General Information - Revised and added general notes.
11. Paragraph 3.B., Work Instructions - Revised work instructions to include new inspection areas.
12. Figure 1 - Deleted, information is now included in compliance tables and Appendix B and Appendix C.
13. Figure 2 - Title revised and steps added.
14. Figure 3 to Figure 14 - Figure title revised.
15. New Figures 15 to 26 - Showing fastener removal and new inspection areas between stringer 18 and
stringer 30.
16. Figures 6-26 - Alternative hole sizing added
17. Appendix B and Appendix C - New logic diagrams are added.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
October 05, 2000Original Issue:
November 10, 2005Revision 1:
June 13, 2014Revision 2:
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 747-53A2451
ALERTALERT

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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2451Original Issue: October 05, 2000
Revision 2: June 13, 2014
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Door Number 2 Forward Edge Frame at Body Station 800
- Inspection and Repair
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
Accomplishment of this service bulletin will make sure that the body frame at station 800, between stringers 14
through 30, does not have cracks which could cause damage to adjacent body structure which could result in
rapid depressurization of the airplane. This frame is the forward edge frame for the number 2 main entry door
opening. Frame cracks that are not found and repaired could extend with continued operation and fully sever
the frame. If the frame becomes severed, skin cracks could occur which could cause a rapid depressurization
of the airplane.
Two operators have reported cracks in the strap and inner chord angle at station 800 frame. The 747-100SR
fatigue test airplane had a severed inner chord angle and strap. Refer to Paragraph 1.C., Reason, for additional
service history.
Since the initial release of this service bulletin, Boeing has received several additional reports of STA 800 frame
strap and inner chord angle cracks. Inner chord angle cracks between 0.4 and 0.8 inch long were found on three
airplanes with 15,735 - 16,428 flight-cycles. An inner chord angle crack 0.05 inch long was found on one airplane
with 9,675 flight-cycles.
In addition, the STA 800 frame aft inner chord angle was found to be cracked near S-17 on a Stretched Upper
Deck (SUD) 747-300 airplane with 23,475 total flight-cycles. As a result of this report, Boeing examined the
747-400 Fatigue Test airplane and found significant damage in this area, including severed inner chord angles
on both the left and right sides, at 54,000 test cycles.
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Since the release of revision 1 of this service bulletin, Boeing has received several additional reports of cracks
found at the STA 800 frame on the left and right side Main Entry Door (MED) forward and aft inner chord angles
and frame straps. One operator reported cracks on the left and right side STA 800 frame, S-17 common to the
aft inner chord angle fastener holes. The crack lengths were between 0.0625 and 1.00 inches long. The airplane
had approximately 11,950 flight cycles. Another operator reported 8 cracks found on the right side STA 800
frame common to the aft inner chord angle fastener holes. Four of the cracks were found between S-18R and
S-20R, which is outside the inspection areas of revision 1 of this service bulletin.
A structural reassessment of the 747 airplane was conducted under the requirements of Federal Aviation
Administration (FAA) Advisory Circular 91-56, in accordance with Federal Aviation Regulation (FAR) 25.571 as
amended in 1978, to ensure safe operation of 747 airplanes throughout their operational life. From this
requirement, the main entry door forward edge frame at body station 800 was determined to be significant, in
that it is critical to airplane structural integrity. Therefore, a flight safety inspection program which will continue
throughout the operational life of the airplane is specified in this service bulletin.
The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires incorporation
of this service bulletin.
Boeing Service Related Problem (SRP) 747-SRP-53-0419 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Do a detailed inspection of the Station 800 Frame Assembly between stringers 14 through 30. The inner chord
strap, angles, and frame web are to be inspected for cracks. Also do surface and open-hole High Frequency
Eddy Current (HFEC) Inspections of the Station 800 Frame Assembly. If any crack is found contact the Boeing
Company for repair instructions and do the repair.
Export Controlled ECCN: 9E991 - BOEING
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EFFECTIVITY
All 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D and 747SR airplanes.
Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
NOTE: 747-100 and 747-200 airplanes converted to special freighter by Boeing are included in the effectivity
of this service bulletin.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2007-16-08, is related to this service bulletin.
The effective date of AD 2007-16-08 is September 13, 2007.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspections given in this service bulletin.
MANPOWER
See service bulletin Paragraph 1.G.
MATERIAL INFORMATION
Operator supplied Parts
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BOEING SERVICE BULLETIN 747-53A2451
ALERT  ALERT
GROUP 1 AND 3  GROUP 2, 4, 5,
AND 6
CRACK IN
CRACK IN
STRAP AND
ACCESS  AFT ANGLE  AFT ANGLE  STRAP AND
STR  STR
17  17
UP
UP
→ FWD  →→FWD
UPPER DECK FLOOR BEAM
INSPECTION
(IF INSTALLED)
AREA
S-14
- S-15
DOOR 2 LEFT  • S-16
DOOR 2 RIGHT OPPOSITE  - S-17
S-18
LIFE RAFT  5-19
LOCATION
-S-20
/ STOP #9
UPPER SILL
• S-22
• S-23
STOP #8  / S-24
S-27
S-28
- S-29
DO A DETAILED INSPECTION FOR CRACKS ON THE  - S-30
INNER CHORD STRAP, ANGLES AND EXPOSED WEB
ADJACENT TO THE INNER CHORD BETWEEN
STRINGER 14 AND 30. ALSO DO HFEC INSPECTIONS  FOR CRACKS ON STATION 800 FRAME ASSEMBLY.  780  STA  > FWD
STA
800
STA
STA 840  STA  820  LEFT SIDE  SHOWN  V33568
854  RIGHT SIDE OPPOSITE
Original Issue: October 05, 2000
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### Page 11

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2451
Original Issue: October 05, 2000
Revision 2: June 13, 2014
ATA System: 5312
SUBJECT: FUSELAGE - Section 42 - Door Number 2 Forward Edge Frame at Body Station 800
- Inspection and Repair
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
747SR, 747-100, 747-100B, 747-200B, and 747-200C without a
Stretched Upper Deck (SUD), that have a tension tie installed at STA
800.
-1
747SR, 747-100, 747-100B, 747-200B, and 747-200C without a
Stretched Upper Deck (SUD), that were delivered with an upper deck
floor beam installed at STA 800.
-2
747SR, 747-100, 747-100B, 747-200B, and 747-200C airplanes
without a Stretched Upper Deck (SUD), that were modified after
delivery to remove the tension tie and install an upper deck floor
beam at STA 800.
-3
747-100B SUD and 747-300 airplanes which were delivered with a
Stretched Upper Deck (SUD).
-4
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DESCRIPTIONCONFIGURATIONGROUP
747-400 and 747-400D airplanes, which were delivered with a
Stretched Upper Deck (SUD).
-5
747-200B airplanes that were modified by Boeing to the Stretched
Upper Deck (SUD) configuration.
-6
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D,
747SR
GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
3RA245 - RA246
1RA251 - RA266
3RA301 - RA317
2RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA544
3RA545 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
3RA671 - RA675
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GroupVariable Number
1RA676
3RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
2RB411 - RB413
1RB421
1RB601 - RB607
2RB681 - RB697
2RB711
1RB721 - RB723
1RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081
2RD082 - RD083
2RD091 - RD092
1RD101 - RD104
1RD121
2RD122 - RD127
2RD131 - RD144
2RD166 - RD167
1RD171 - RD172
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GroupVariable Number
2RD181 - RD183
2RD201 - RD204
2RD221 - RD227
2RD231 - RD235
2RD241 - RD243
1RD251 - RD262
2RD271 - RD272
2RD291 - RD292
2RD301 - RD302
2RD311
2RD351 - RD358
2RD361 - RD366
6RD381 - RD383
2RD411 - RD414
2RD421 - RD426
1RD431 - RD435
2RD441 - RD442
2RD451 - RD456
2RD461
2RD471 - RD475
2RD513 - RD519
2RD531 - RD533
1RD551
2RD561
1RD571
2RD581 - RD583
2RD591 - RD593
6RD601 - RD607
1RD621 - RD623
2RD641 - RD649
2RD651 - RD659
2RD661
1RD671
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GroupVariable Number
2RD681 - RD682
2RD691 - RD692
2RD701 - RD702
6RD721 - RD722
2RD741 - RD742
2RD751 - RD755
2RD761
2RD771 - RD775
2RD781 - RD783
2RD791 - RD792
2RE001
5RF001 - RF006
1RJ131 - RJ133
1RJ151 - RJ152
1RJ301 - RJ303
1RJ321 - RJ322
1RJ331 - RJ333
5RM001 - RM007
5RM010 - RM013
5RM021 - RM024
5RM026 - RM030
5RM036 - RM045
5RM051 - RM053
5RM071
5RM081 - RM084
5RM091
5RM096 - RM097
5RM116 - RM117
5RM126 - RM132
5RM136 - RM147
5RM156 - RM158
5RM166 - RM177
5RM191 - RM192
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GroupVariable Number
5RM231 - RM233
5RM241 - RM246
5RM261 - RM264
5RM316 - RM318
5RM331 - RM333
5RM341
5RM351 - RM355
5RM366 - RM367
5RM401 - RM403
5RM426
5RM431
5RM441 - RM443
5RM445
5RM801 - RM803
5RM811 - RM813
4RS001 - RS002
4RS201
4RS211 - RS212
4RS221 - RS222
4RS231 - RS241
4RS251 - RS259
4RS263
4RS265 - RS268
4RS271 - RS276
4RS291 - RS292
4RS301 - RS306
4RS311 - RS320
4RS331 - RS333
4RS341 - RS342
4RS699
4RS701 - RS703
4RS711 - RS713
4RS721 - RS722
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GroupVariable Number
4RS731 - RS732
4RS741 - RS743
4RS751 - RS752
4RS761 - RS762
4RS771
4RS781 - RS782
4RS786
5RT001 - RT014
5RT021 - RT022
5RT031 - RT035
5RT041 - RT047
5RT061
5RT071 - RT075
5RT101 - RT103
5RT121
5RT131 - RT137
5RT151 - RT152
5RT161 - RT168
5RT401 - RT412
5RT431 - RT447
5RT451 - RT469
5RT471 - RT499
5RT501 - RT535
5RT551 - RT568
5RT571 - RT591
5RT601 - RT630
5RT633 - RT657
5RT671 - RT673
5RT681 - RT682
5RT691 - RT699
5RT701 - RT704
5RT711 - RT717
5RT741 - RT742
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GroupVariable Number
5RT744 - RT757
5RT776 - RT777
5RT781 - RT784
5RT801 - RT803
5RT811 - RT814
5RT831 - RT837
5RT861 - RT864
5RT877 - RT880
5RT931 - RT932
5RT945 - RT949
5RT951 - RT955
5RT966 - RT967
5RU001 - RU006
5RU016 - RU017
5RU031 - RU032
5RU051 - RU052
5RU059 - RU062
5RU081 - RU083
5RU101 - RU102
5RU121 - RU132
5RU801 - RU809
5RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None
C. Reason
Accomplishment of this service bulletin will make sure that the body frame at station 800, between
stringers 14 through 30, does not have cracks which could cause damage to adjacent body structure
which could result in rapid depressurization of the airplane. This frame is the forward edge frame for
the number 2 main entry door opening. Frame cracks that are not found and repaired could extend
with continued operation and fully sever the frame. If the frame becomes severed, skin cracks could
occur which could cause a rapid depressurization of the airplane.
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Two operators have reported cracks in the strap and inner chord angle at station 800 frame. The
747-100SR fatigue test airplane had a severed inner chord angle and strap. Service history is
summarized in the table below.
Service History
Crack LengthCrack LocationCycles/HoursReport
1.10inner chord aft angle25,927 / 30,7131
0.04inner chord aft angle21,989 / 87,6752
0.32inner chord strap
severedinner chord fwd angle and strap26,000 cycles-100SR Fatigue test
Since the initial release of this service bulletin, Boeing has received several additional reports of STA
800 frame strap and inner chord angle cracks. Inner chord angle cracks between 0.4 and 0.8 inch long
were found on three airplanes with 15,735 - 16,428 flight-cycles. An inner chord angle crack 0.05 inch
long was found on one airplane with 9,675 flight-cycles.
In addition, the STA 800 frame aft inner chord angle was found to be cracked near S-17 on a Stretched
Upper Deck (SUD) 747-300 airplane with 23,475 total flight-cycles. As a result of this report, Boeing
examined the 747-400 Fatigue Test airplane and found significant damage in this area, including
severed inner chord angles on both the left and right sides, at 54,000 test cycles.
Since the release of revision 1 of this service bulletin, Boeing has received several additional reports
of cracks found at the STA 800 frame on the left and right side Main Entry Door (MED) forward and aft
inner chord angles and frame straps. One operator reported cracks on the left and right side STA 800
frame, S-17 common to the aft inner chord angle fastener holes. The crack were between 0.0625 and
1.00 inches long. The airplane had approximately 11,950 flight cycles. Another operator reported 8
cracks found on the right side STA 800 frame common to the aft inner chord angle fastener holes. Four
of the cracks were found between S-18R and S-20R, which is outside the inspection areas of revision
1 of this service bulletin.
A structural reassessment of the 747 airplane was conducted under the requirements of Federal Aviation
Administration (FAA) Advisory Circular 91-56, in accordance with Federal Aviation Regulation (FAR)
25.571 as amended in 1978, to ensure safe operation of 747 airplanes throughout their operational
life. From this requirement, the main entry door forward edge frame at body station 800 was determined
to be significant, in that it is critical to airplane structural integrity. Therefore, a flight safety inspection
program which will continue throughout the operational life of the airplane is specified in this service
bulletin.
The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires
incorporation of this service bulletin.
Boeing Service Related Problem (SRP) 747-SRP-53-0419 is related to this service bulletin.
Revision 1 was sent to add all 747 airplanes with a Stretched Upper Deck (SUD) to the effectivity of
this service bulletin. These airplanes have been included as new Groups 4, 5, and 6. New Figures 9
through 14 have been added to give inspection instructions for these airplanes. Airplanes RA545-RA548
have been moved from Group 1 to Group 3. These airplanes were previously modified to install an
upper deck floor beam at STA 800. As a result of additional in-service crack reports, the inspection
threshold has been changed from 19,000 total flight-cycles to 16,000 total flight-cycles. Figure 1 has
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been changed to reflect this threshold reduction. The repeat inspection interval has not been changed.
Figures 6, 7, and 8 have been changed to make the inspection area larger for Group 1, 2, and 3
airplanes. The detailed and surface eddy current inspection area has been extended to just above
Stringer 14. The inspection steps in Figures 6, 7, and 8 have been reformatted to make them more
clear. References to FAA Airworthiness Directive 2001-14-22, Amendment 39-12333 have been added.
Revision 2 is sent to expand the inspection area to include the STA 800 frame inner chord between
stringer 18 and stringer 30. Additionally a new inspection threshold for STA 800 frame inner chord
between stringer 18 and stringer 30 has been added.
D. Description
Do a detailed inspection of the Station 800 Frame Assembly between stringers 14 through 30. The
inner chord strap, angles, and frame web are to be inspected for cracks. Also do surface and open-hole
High Frequency Eddy Current (HFEC) inspections of the Station 800 Frame Assembly. If cracks are
found, repair before next flight.
This service bulletin is applicable to all 747s, except 747SP, 747-200F, and 747-400F airplanes, in six
groups.
NOTE: 747 airplanes converted to special freighter by Boeing are included in the effectivity of this
service bulletin.
An evaluation form is attached to this service bulletin. Please use this form to tell us what you think of
the quality of this service bulletin.
Revision 1 - No additional work is necessary on airplanes inspected as shown in the original issue of
this service bulletin. However, the initial threshold has been changed to an earlier time and the affected
inspection areas have been made larger. At the time of the next scheduled repeat inspection, do the
inspection of the area as defined in this revision.
Revision 2 - More work is necessary on the airplane(s) inspected in accordance with the original issue
or Revision 1 of this service bulletin. Inspection of the STA 800 frame inner chord between stringer 18
and stringer 30 is necessary.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
231747-100, 747-100B, 747-200B,
747-200C, 747SR
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Group 2:
Affected Maintenance Zones
ZoneModel
231747-100, 747-100B, 747-200B,
747SR
Group 3:
Affected Maintenance Zones
ZoneModel
231747-100, 747-200B
Group 4:
Affected Maintenance Zones
ZoneModel
231747-100B SUD, 747-300
Group 5:
Affected Maintenance Zones
ZoneModel
231747-400, 747-400D
Group 6:
Affected Maintenance Zones
ZoneModel
231747-200B
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2007-16-08 is related to this service
bulletin. The effective date of AD 2007-16-08 is September 13, 2007. Airworthiness Directive AD
2007-16-08 superseded AD 2006-12-12, and the effective date of AD 2006-12-12 was July 17, 2006.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
B and APPENDIX C.
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Table 1: Inspection of Door Number 2 Forward Edge Frame at Body Station 800 between stringer 14
and stringer 18.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,500
flight cycles af-
ter July 17,
2006.
Before 16,000
total flight-cy-
cles.
Do a detailed inspection
for any crack at the inner
chord strap, angles and
exposed web adjacent to
the inner chords, and do
surface and open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 2.
All Airplanes with less than
16,000 total flight cycles as
of July 17, 2006.
-Within 1,000
flight cycles af-
ter the effective
date of AD
2007-16-08.
Within 1,500
flight cycles af-
ter July 17,
2006.
Do a detailed inspection
for any crack at the inner
chord strap, angles and
exposed web adjacent to
the inner chords, and do
surface and open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 2.
All Airplanes with 16,000
total flight cycles or more,
but 21,250 total flight cy-
cles or less, as of July 17,
2006.
-Within 500 flight
cycles after the
effective date of
AD 2007-16-08.
Within 750 flight
cycles after July
17, 2006.
Do a detailed inspection
for any crack at the inner
chord strap, angles and
exposed web adjacent to
the inner chords, and do
surface and open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 2.
All Airplanes with 21,250
total flight cycles or more
as of July 17, 2006.
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Table 1: Inspection of Door Number 2 Forward Edge Frame at Body Station 800 between stringer 14
and stringer 18.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact the Boeing Com-
pany for repair instruc-
tions and do the repair.
CONDITION 1: ANY
CRACK FOUND.
AND
3,000 flight cycles-Repeat the detailed in-
spection for any crack at
the inner chord strap, an-
gles and exposed web
adjacent to the inner
chords, and the surface
and open-hole HFEC in-
spections for any crack
on the inner chord strap
and angles in accordance
with PART 2.
3,000 flight cycles-Repeat the detailed in-
spection for any crack at
the inner chord strap, an-
gles and exposed web
adjacent to the inner
chords, and the surface
and open-hole HFEC in-
spections for any crack
on the inner chord strap
and angles in accordance
with PART 2.
CONDITION 2: NO
CRACK FOUND.
Table 2: Inspection of Door Number 2 Forward Edge Frame at Body Station 800 between stringer 18
and stringer 30.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Revision
2 date of this
service bulletin.
Before 16,000
total flight cy-
cles.
Do a detailed inspection
for any crack at the inner
chord strap, angles and
exposed web adjacent to
the inner chords, and do
surface and open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
All Airplanes with less than
16,000 total flight cycles as
of the Revision 2 date of
this service bulletin.
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Table 2: Inspection of Door Number 2 Forward Edge Frame at Body Station 800 between stringer 18
and stringer 30.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,500 flight cycles after the
Revision 2 date of this service
bulletin.
Do a detailed inspection
for any crack at the inner
chord strap, angles and
exposed web adjacent to
the inner chords, and do
surface and open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
All Airplanes with 16,000
total flight cycles or more,
but 21,250 total flight cy-
cles or less, as of the Revi-
sion 2 date of this service
bulletin.
-Within 750 flight cycles after the
Revision 2 date of this service
bulletin.
Do a detailed inspection
for any crack at the inner
chord strap, angles and
exposed web adjacent to
the inner chords, and do
surface and open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
All Airplanes with 21,250
total flight cycles or more
as of the Revision 2 date
of this service bulletin.
-Before further flight.Contact the Boeing Com-
pany for repair instruc-
tions and do the repair.
CONDITION 1: ANY
CRACK FOUND.
AND
3,000 flight-cycles-Repeat the detailed in-
spection for any crack at
the inner chord strap, an-
gles and exposed web
adjacent to the inner
chords, and the surface
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
AND
6,000 flight-cycles-Repeat the open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
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Table 2: Inspection of Door Number 2 Forward Edge Frame at Body Station 800 between stringer 18
and stringer 30.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight-cycles-Repeat the detailed in-
spection for any crack at
the inner chord strap, an-
gles and exposed web
adjacent to the inner
chords, and the surface
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
CONDITION 2: NO
CRACK FOUND.
AND
6,000 flight-cycles-Repeat the open-hole
HFEC inspections for any
crack on the inner chord
strap and angles in accor-
dance with PART 3.
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 alternative method of
compliance (AMOC) to the accomplishment of the inspection and corrective actions required by SB
747-53A2451, Revision 1, dated November 10,2005 per paragraph (f) and (h) of AD 2007-16-08. All
provisions of AD 2007-16-08 that are not specifically referenced in the above statement remain fully
applicable and must be complied with accordingly. Where this service bulletin states to contact Boeing
for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph
(I) of the AD.
G. Manpower
The table below shows an estimate of the man-hours necessary to do this service bulletin 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:
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— 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:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Figure 2
1.001.001Figure 3
6.0012.002Figure 6
0.450.451Figure 15
4.254.251Figure 16
0.450.451Figure 17
4.604.601Figure 18
0.100.101Figure 19
4.054.051Figure 20
0.450.451Figure 21
4.254.251Figure 22
0.450.451Figure 23
4.604.601Figure 24
0.100.101Figure 25
4.054.051Figure 26
39.3049.80TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Figure 2
1.501.501Figure 4
7.0014.002Figure 7
0.450.451Figure 15
4.254.251Figure 16
0.450.451Figure 17
4.604.601Figure 18
0.100.101Figure 19
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Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
4.054.051Figure 20
0.450.451Figure 21
4.254.251Figure 22
0.450.451Figure 23
4.604.601Figure 24
0.100.101Figure 25
4.054.051Figure 26
40.8052.30TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Figure 2
1.251.251Figure 5
7.0014.002Figure 8
0.450.451Figure 15
4.254.251Figure 16
0.450.451Figure 17
4.604.601Figure 18
0.100.101Figure 19
4.054.051Figure 20
0.450.451Figure 21
4.254.251Figure 22
0.450.451Figure 23
4.604.601Figure 24
0.100.101Figure 25
4.054.051Figure 26
40.5552.05TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Figure 2
1.501.501Figure 9
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Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
7.0014.002Figure 10
0.450.451Figure 15
4.254.251Figure 16
0.450.451Figure 17
4.604.601Figure 18
0.100.101Figure 19
4.054.051Figure 20
0.450.451Figure 21
4.254.251Figure 22
0.450.451Figure 23
4.604.601Figure 24
0.100.101Figure 25
4.054.051Figure 26
40.8052.30TOTAL FOR EACH AIRPLANE
Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.02Figure 2
1.501.501Figure 14
7.0014.002Figure 11
0.450.451Figure 15
4.254.251Figure 16
0.450.451Figure 17
4.604.601Figure 18
0.100.101Figure 19
4.054.051Figure 20
0.450.451Figure 21
4.254.251Figure 22
0.450.451Figure 23
4.604.601Figure 24
0.100.101Figure 25
4.054.051Figure 26
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Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
40.8052.30TOTAL FOR EACH AIRPLANE
Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Figure 2
1.501.501Figure 12
7.0014.002Figure 13
0.450.451Figure 15
4.254.251Figure 16
0.450.451Figure 17
4.604.601Figure 18
0.100.101Figure 19
4.054.051Figure 20
0.450.451Figure 21
4.254.251Figure 22
0.450.451Figure 23
4.604.601Figure 24
0.100.101Figure 25
4.054.051Figure 26
40.8052.30TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None
I. Electrical Load Data
Not applicable
J. References
1. Existing Data:
a. 747-100/200/300 Aircraft Maintenance Manual (AMM) 12-09-02, 25-21-03, 25-21-04, 25-22-01,
25-27-01, 53-21-02
b. 747-400 Aircraft Maintenance Manual (AMM) 06-09-02, 25-21-03, 25-21-04, 25-22-01,
25-27-01, 52-11-01, 53-21-02
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c. 747 Nondestructive Test (NDT) Manual D6-7170, Part 6, Subject 51-00-00
d. 747 Supplemental Structural Inspection Document D6-35022 Item F-41
e. Boeing Service Bulletin 747-53-2349, "FUSELAGE - Inspection Based on Fatigue Test Results"
f. Boeing Service Letter 747-SL-51-048
g. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-12-12, 2007-16-08
h. Service Bulletin Index D6-30300
i. Standard Overhaul Practices Manual (SOPM) 20-50-01
j. Boeing Service Related Problem (SRP) 747-SRP-53-0419
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Sill Instl - Upper Main Entry Door No. 265B05028
Stop Instl - FWD Frame, Main Entry Door No. 2, STA 80065B05002
Frame Instl - FWD, Main Entry Door No. 2, STA 80065B01840
Frame Installation - STA 80065B01733
Support Instl - Liferaft, STA 800 - 86065B54006
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
4. Process Data:
Boeing Process specifications referred to on the drawings are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
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
None.
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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BLANK PAGE

### Page 33

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None
B. Industry Support Information
Boeing warranty remedies are not available for the inspections given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
Group 1
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY6K98
BoltBACB30MY6K114
BoltBACB30MY8K66
BoltBACB30MY8K74
BoltBACB30MY8K912
BoltBACB30MY8K104
BoltBACB30MY8K122
BoltBACB30NW8K720
BoltBACB30NW8K94
BoltBACB30NW8K104
CollarBACC30M612
CollarBACC30M856
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 34

Group 1
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9X or8
BoltBACB30MY6K9X
BoltBACB30NX6K11X or4
BoltBACB30MY6K11X
BoltBACB30MY8K6X6
BoltBACB30MY8K7X4
BoltBACB30MY8K9X12
BoltBACB30MY8K10X4
BoltBACB30MY8K12X2
BoltBACB30NW8K7X20
BoltBACB30NW8K9X4
BoltBACB30NW8K10X4
CollarBACC30M612
CollarBACC30M856
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 1
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9Y or8
BoltBACB30MY6K9Y
BoltBACB30NX6K11Y or4
BoltBACB30MY6K11Y
BoltBACB30MY8K6Y6
BoltBACB30MY8K7Y4
BoltBACB30MY8K9Y12
Export Controlled ECCN: 9E991 - BOEING
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### Page 35

Group 1
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY8K10Y4
BoltBACB30MY8K12Y2
BoltBACB30NW8K7Y20
BoltBACB30NW8K9Y4
BoltBACB30NW8K10Y4
CollarBACC30R612
CollarBACC30R856
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 2
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY6K98
BoltBACB30MY6K114
BoltBACB30MY8K62
BoltBACB30MY8K74
BoltBACB30MY8K914
BoltBACB30MY8K1010
BoltBACB30MY8K122
BoltBACB30MY10K114
BoltBACB30NW8K720
BoltBACB30NW8K94
BoltBACB30NW8K104
CollarBACC30M612
CollarBACC30M860
CollarBACC30M104
Export Controlled ECCN: 9E991 - BOEING
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### Page 36

Group 2
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 2
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9X or8
BoltBACB30MY6K9X
BoltBACB30NX6K11X or4
BoltBACB30MY6K11X
BoltBACB30MY8K6X2
BoltBACB30MY8K7X4
BoltBACB30MY8K9X14
BoltBACB30MY8K10X10
BoltBACB30MY8K12X2
BoltBACB30MY10K11X4
BoltBACB30NW8K7X20
BoltBACB30NW8K9X4
BoltBACB30NW8K10X4
CollarBACC30M612
CollarBACC30M860
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 37

Group 2
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 2
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9Y or8
BoltBACB30MY6K9Y
BoltBACB30NX6K11Y or4
BoltBACB30MY6K11Y
BoltBACB30MY8K6Y2
BoltBACB30MY8K7Y4
BoltBACB30MY8K9Y14
BoltBACB30MY8K10Y10
BoltBACB30MY8K12Y2
BoltBACB30MY10K11Y4
BoltBACB30NW8K7Y20
BoltBACB30NW8K9Y4
BoltBACB30NW8K10Y4
CollarBACC30R612
CollarBACC30R860
CollarBACC30R104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 38

Group 3
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K118
BoltBACB30NX6K134
BoltBACB30NX8K84
BoltBACB30NX8K92
BoltBACB30NX8K104
BoltBACB30NX8K114
BoltBACB30MY8K62
BoltBACB30MY8K910
BoltBACB30MY8K104
BoltBACB30MY8K122
BoltBACB30NW8K720
BoltBACB30NW8K94
BoltBACB30NW8K104
CollarBACC30M612
CollarBACC30M860
BoltBACB30NN3K8X or4
BoltBACB30LU3-8X
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 3
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K11X8
BoltBACB30NX6K13X4
BoltBACB30NX8K8X4
BoltBACB30NX8K9X2
BoltBACB30NX8K10X4
BoltBACB30NX8K11X4
Export Controlled ECCN: 9E991 - BOEING
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### Page 39

Group 3
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY8K6X2
BoltBACB30MY8K9X10
BoltBACB30MY8K10X4
BoltBACB30MY8K12X2
BoltBACB30NW8K7X20
BoltBACB30NW8K9X4
BoltBACB30NW8K10X4
CollarBACC30X612
CollarBACC30M846
CollarBACC30X814
BoltBACB30NN3K8X or4
BoltBACB30LU3-8X
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 3
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K11Y8
BoltBACB30NX6K9K13Y4
BoltBACB30NX8K8Y4
BoltBACB30NX8K9Y2
BoltBACB30NX8K10Y4
BoltBACB30NX8K11Y4
BoltBACB30MY8K6Y2
BoltBACB30MY8K9Y10
BoltBACB30MY8K10Y4
BoltBACB30MY8K12Y2
BoltBACB30NW8K7Y20
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 40

Group 3
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NW8K9Y4
BoltBACB30NW8K10Y4
CollarBACC30AC612
CollarBACC30R846
CollarBACC30AC814
BoltBACB30NN3K8X or4
BoltBACB30LU3-8X
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 4
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY6K98
BoltBACB30MY6K114
BoltBACB30MY8K62
BoltBACB30MY8K74
BoltBACB30MY8K910
BoltBACB30MY8K1014
BoltBACB30MY8K122
BoltBACB30MY10K114
BoltBACB30NW8K720
BoltBACB30NW8K94
BoltBACB30NW8K104
CollarBACC30M612
CollarBACC30M860
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 41

Group 4
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 4
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9X or8
BoltBACB30MY6K9X
BoltBACB30NX6K11X or4
BoltBACB30MY6K11X
BoltBACB30MY8K6X2
BoltBACB30MY8K7X4
BoltBACB30MY8K9X10
BoltBACB30MY8K10X14
BoltBACB30MY8K12X2
BoltBACB30MY10K11X4
BoltBACB30NW8K7X20
BoltBACB30NW8K9X4
BoltBACB30NW8K10X4
CollarBACC30M612
CollarBACC30M860
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 42

Group 4
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9Y or8
BoltBACB30MY6K9Y
BoltBACB30NX6K11Y or4
BoltBACB30MY6K11Y
BoltBACB30MY8K6Y2
BoltBACB30MY8K7Y4
BoltBACB30MY8K9Y10
BoltBACB30MY8K10Y14
BoltBACB30MY8K12Y2
BoltBACB30MY10K11Y4
BoltBACB30NW8K7Y20
BoltBACB30NW8K9Y4
BoltBACB30NW8K10Y4
CollarBACC30R612
CollarBACC30R860
CollarBACC30R104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 5
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY6K98
BoltBACB30MY6K114
BoltBACB30MY8K62
BoltBACB30MY8K74
BoltBACB30MY8K914
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 43

Group 5
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY8K1020
BoltBACB30MY8K122
BoltBACB30MY10K114
BoltBACB30NW8K720
BoltBACB30NW8K94
BoltBACB30NW8K104
CollarBACC30M612
CollarBACC30M860
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 5
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9X or8
BoltBACB30MY6K9X
BoltBACB30NX6K11X or4
BoltBACB30MY6K11X
BoltBACB30MY8K6X2
BoltBACB30MY8K7X4
BoltBACB30MY8K9X14
BoltBACB30MY8K10X20
BoltBACB30MY8K12X2
BoltBACB30MY10K11X4
BoltBACB30NW8K7X20
BoltBACB30NW8K9X4
Export Controlled ECCN: 9E991 - BOEING
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### Page 44

Group 5
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NW8K10X4
CollarBACC30M612
CollarBACC30M860
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 5
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9Y or8
BoltBACB30MY6K9Y
BoltBACB30NX6K11Y or4
BoltBACB30MY6K11Y
BoltBACB30MY8K6Y2
BoltBACB30MY8K7Y4
BoltBACB30MY8K9Y14
BoltBACB30MY8K10Y20
BoltBACB30MY8K12Y2
BoltBACB30MY10K11Y4
BoltBACB30NW8K7Y20
BoltBACB30NW8K9Y4
BoltBACB30NW8K10Y4
CollarBACC30R612
CollarBACC30R860
CollarBACC30R104
Export Controlled ECCN: 9E991 - BOEING
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### Page 45

Group 5
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 6
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30MY6K98
BoltBACB30MY6K114
BoltBACB30MY8K62
BoltBACB30MY8K74
BoltBACB30MY8K910
BoltBACB30MY8K106
BoltBACB30MY8K116
BoltBACB30MY8K122
BoltBACB30MY8K136
BoltBACB30MY10K112
BoltBACB30MY10K122
BoltBACB30NW8K720
BoltBACB30NW8K94
BoltBACB30NW8K104
CollarBACC30M612
CollarBACC30M862
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 46

Group 6
FOR STANDARD SIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
NutBACN10YR3CD or4
NutBACN10JC3CD
Group 6
FOR 1/64 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9X or8
BoltBACB30MY6K9X
BoltBACB30NX6K11X or4
BoltBACB30MY6K11X
BoltBACB30MY8K6X2
BoltBACB30MY8K7X4
BoltBACB30MY8K9X10
BoltBACB30MY8K10X6
BoltBACB30MY8K11X6
BoltBACB30MY8K12X2
BoltBACB30MY8K13X6
BoltBACB30MY10K11X2
BoltBACB30MY10K12X2
BoltBACB30NW8K7X20
BoltBACB30NW8K9X4
BoltBACB30NW8K10X4
CollarBACC30M612
CollarBACC30M862
CollarBACC30M104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 47

Group 6
FOR 1/32 OVERSIZE BOLT REPLACEMENT
NamePart Number (b)QTY (a)
BoltBACB30NX6K9Y or8
BoltBACB30MY6K9Y
BoltBACB30NX6K11Y or4
BoltBACB30MY6K11Y
BoltBACB30MY8K6Y2
BoltBACB30MY8K7Y4
BoltBACB30MY8K9Y10
BoltBACB30MY8K10Y6
BoltBACB30MY8K11Y6
BoltBACB30MY8K12Y2
BoltBACB30MY8K13Y6
BoltBACB30MY10K11Y2
BoltBACB30MY10K12Y2
BoltBACB30NW8K7Y20
BoltBACB30NW8K9Y4
BoltBACB30NW8K10Y4
CollarBACC30R612
CollarBACC30R862
CollarBACC30R104
BoltBACB30NN3K4 or4
BoltBACB30LU3LN4
WasherNAS1149D0363J or4
WasherAN960PD10
NutBACN10YR3CD or4
NutBACN10JC3CD
Quantities are per airplane with Main Entry Door #2 (active or inactive) on both
sides of the airplane.
(a)
Refer to 747 Structural Repair Manual Chapter 51 for alternative fasteners.(b)
3. Parts Modified and Reidentified:
None.
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### Page 48

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 49

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Airplane Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 747
Airplane Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
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### Page 50

7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
8. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
9. 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.
10. 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.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
12. Refer to APPENDIX A for addendum flight safety section.
13. Refer to APPENDIX B for the inspection of door number 2 forward edge frame at
STA 800 between stringer 14 and stringer 18 logic diagram.
14. Refer to APPENDIX C for the inspection of door number 2 forward edge frame at
STA 800 between stringer 18 and stringer 30 logic diagram.
B. WORK INSTRUCTIONS
PART 1 - ACCESS
1. Get access to door number 2, forward edge frame at body station 800 between stringer 14 and
stringer 30 in accordance with FIGURE 2.
PART 2: STA 800 FRAME INSPECTION, S-14 TO S-18
1. Group 1:
Remove fasteners in accordance with FIGURE 3.
2. Group 2:
Remove fasteners in accordance with FIGURE 4.
3. Group 3:
Remove fasteners in accordance with FIGURE 5.
4. Group 4:
Remove fasteners in accordance with FIGURE 9.
5. Group 5:
Remove fasteners in accordance with FIGURE 14.
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### Page 51

6. Group 6:
Remove fasteners in accordance with FIGURE 12.
7. Group 1:
Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface High Frequency Eddy Current (HFEC) and open hole HFEC inspections
for any crack in the strap and inner chord angles, and install fasteners in accordance with FIGURE
6.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
8. Group 2:
Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 7.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 52

9. Group 3:
Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 8.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
10. Group 4:
Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 10.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
11. Group 5:
Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 11.
a. CONDITION 1: ANY CRACK FOUND.
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### Page 53

(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
12. Group 6:
Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 13.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface and open-hole HFEC inspections for any crack on the inner chord
strap and angles.
PART 3: STA 800 FRAME INSPECTION, S-18 TO S-30
1. Remove fasteners in accordance with FIGURE 15.
2. Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface High Frequency Eddy Current (HFEC) and open hole HFEC inspections
for any crack in the strap and inner chord angles, and install fasteners in accordance with FIGURE
16.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
Export Controlled ECCN: 9E991 - BOEING
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### Page 54

(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(4) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(3) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
3. Remove fasteners in accordance with FIGURE 17.
4. Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 18.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(4) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(3) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
5. Remove fasteners in accordance with FIGURE 19.
6. Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 20.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 55

(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(4) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(3) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
7. Remove fasteners in accordance with FIGURE 21.
8. Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 22.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(4) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(3) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
9. Remove fasteners in accordance with FIGURE 23.
10. Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 24.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
Export Controlled ECCN: 9E991 - BOEING
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### Page 56

(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(4) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(3) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
11. Remove fasteners in accordance with FIGURE 25.
12. Do a detailed inspection for any crack in the inner chord strap, angles and exposed web adjacent
to the inner chords, surface HFEC and open hole HFEC inspections for any crack in the strap and
inner chord angles, and install fasteners in accordance with FIGURE 26.
a. CONDITION 1: ANY CRACK FOUND.
(1) Contact the Boeing Company for repair instructions and do the repair.
(2) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(3) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(4) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat the detailed inspection for any crack at the inner chord strap, angles and exposed
web adjacent to the inner chords.
(2) Repeat the surface HFEC inspections for any crack on the inner chord strap and angles.
(3) Repeat the open-hole HFEC inspections for any crack on the inner chord strap and angles.
PART 4: : CLOSE ACCESS
1. Close access in accordance with FIGURE 2.
2. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-53A2451
ALERT  ALERT
THIS FIGURE IS DELETED.
FIGURE THE LOES DELETED
Original Issue: October 05, 2000  Revision 2 June 13, 2014  Export Controlled ECCN: 9E991 - BOEING  747-53A2451
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  57 of 163

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-53A2451
ALERT  ALERT
SEE O
SEE  13)
114
→FWD
DOOR 2 RIGHT SIDE OPPOSITE  DOOR 2 LEFT SIDE  V33574
FIGURE 2: ACCESS
(SHEET 1 OF 6)
Original Issue: October 05, 2000
Revision 2 June 13, 2014  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2451
Work - See page 1 for details.  58 of 163

### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-53A2451
ALERT  ALERT
FLOOR BEAMS  STA
GROUPS 2 AND 3 ONLY  STA  780  - 5-14
800
LIFE RAFT
LOCATION  - 8-15
=— S-16
SEE
: — S-17
=- S-18
UPPER SILL
- S-19
DOORWAY CUTOUT
- S-20
4 X11
- S-22
- S-23  FWD
S-24
S-25
S-26
S-27
S-28
DOOR 2 RIGHT SIDE OPPOSITE  DOOR 2 LEFT SIDE  S-30  S-29  V33588
FIGURE 2: ACCESS
(SHEET 2 OF 6)
Original Issue: October 05, 2000
Revision 2 June 13, 2014  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2451
Work - See page 1 for details.  59 of 163

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-53A2451
ALERT  ALERT
STA
800
DOORWAY  - FRAME
CUTOUT
STOP 9  - S-17
STOP 8
REVEAL
STOP 7
STOP 6
STOP 5 -
STOP 4
STOP 3
STOP 2
STOP 1  S-25
→FWD
DOOR 2 LEFT SIDE  2325386
DOOR 2 RIGHT SIDE OPPOSITE
FIGURE 2: ACCESS
(SHEET 3 OF 6)
Original Issue: October 05, 2000
Revision 2 June 13, 2014  Export Controlled ECCN: 9E991 - BOEING  747-53A2451
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  60 of 163

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