# Airbus Service Bulletin A300-53-0369

Copy: Revision 03 ("SB A300-53-0369_Rev3"), 62 pages: PDF https://openairdocs.org/files/sha256/c2/3e/c23e12d02183882dad8b0f1a455fa9a49145a47ae77b55e4be434c7e3a632863; text https://openairdocs.org/service-documents/airbus/a300-53-0369/file/c23e12d02183.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9298; AD 2017-05-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A300-53-0369
- Latest revision known: A300-53-0369, Revision 03, dated September 1, 2010 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-53-0369

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2017-05-01](https://openairdocs.org/ad/2017-05-01.md), effective Apr 7, 2017: Revision 03

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-53-0369/proposed.md).

## Text (62 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9298; AD 2017-05-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORA TE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Tel : (33) 5 61 93 33 33
Telex : AIRBU 530526F
Fax : (33) 5 61 93 42 51
MANDATORY MANDATORY MANDATORY MANDATORY
A T A SYSTEM : 53
TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE THE BUTT JOINT A T FRAME 72
MODIFICA TION No. : 12737D21977
This page transmits Revision No. 03 of Service Bulletin No. A300-53-0369.
ADDITIONAL WORK
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
This Revision is issued to :
- add the Config. 01 thru Config. 03,
- update the effectivity,
- introduce minor changes.
CHANGES
SUMMARY :
- REASON/DESCRIPTION/OPERA TIONAL CONSEQUENCES
. NOTE amended, AIRBUS department deleted.
- EFFECTIVITY
. Effectivity updated.
- MANPOWER
. Config. 01, Config. 02 and Config. 03 added.
- MA TERIAL INFORMA TION
. Config. 01, Config. 02 and Config. 03 added.
PLANNING INFORMA TION :
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REVISION No. : 03 - Sep 01/10 Page : 1 of 4
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### Page 2

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
- REASON
- Operational/Maintenance Consequences
. 1.C.(4) NOTE amended, AIRBUS department deleted.
- DESCRIPTION
. 1.D.(1) Config. 01 added.
. 1.D.(2) Config. 02 added.
. 1.D.(3) Config. 03 added.
- COMPLIANCE
- Accomplishment Timescale
. 1.E.(2) Airworthiness Directive (AD) 2006-0071 deleted and superseded by the new AD 2009-0155.
- MANPOWER
. 1.G. Config. 01, Config. 02 and Config. 03 added.
- WEIGHT AND BALANCE
. 1.H. Config. 01, Config. 02 and Config. 03 added.
MA TERIAL INFORMA TION :
- MA TERIAL - PRICE AND AVAILABILITY
- Material
. 2.A.(1) Address updated.
ACCOMPLISHMENT INSTRUCTIONS :
- GENERAL
- Preparation
. 3.A.(1) Config. 01 thru Config. 03 added.
- MODIFICA TION
. 3.B.(1) Config. 01 added.
. 3.B.(2) Config. 02 added.
. 3.B.(3) Config. 03 added.
- CLOSE-UP
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### Page 3

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
. 3.D.(1) Config. 01 thru Config. 03 added.
- Figure 1
. Title : Config. 01 added.
- Figure 2
. Title : Config. 02 added.
- Figure 3
. Title : Config. 03 added.
APPENDIX 1 :
- Figure 1
. Sheet 3 updated.
- 1. Config. 01 thru Config. 02 added.
. 1.A. Part numbers updated.
. 1.C.(2) Sentence updated.
. 1.C.(3) Sentence and NOTEs updated.
NOTE : Layout changes due to computerization of this revision are not identified.
FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision T ransmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
Revision 01 was issued to :
- incorporate an appendix for the jacking of the aircraft and to change the compliance from
recommended to mandatory.
Revision 02 was issued to :
- update the effectivity , remove aircraft MSN 0106, 0140, 0146, 0163, 0177, 0222 and 0269 from the
effectivity,
- amend the appendix figure for the jacking of the aircraft.
- revise the sentence in the para INDUSTRIAL SUPPORT .
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### Page 4

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
REVISION SEQUENCE
ORIGINAL : Apr 07/05
REVISION No. : 01 - Dec 04/06
REVISION No. : 02 - Nov 19/07
REVISION No. : 03 - Sep 01/10
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### Page 5

A300A300
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORA TE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Tel : (33) 5 61 93 33 33
Telex : AIRBU 530526F
Fax : (33) 5 61 93 42 51
This summary is for information only and is
not approved for modification of the aircraft
MANDATORY MANDATORY MANDATORY MANDATORY
A T A SYSTEM : 53
TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE THE BUTT JOINT A T FRAME 72
MODIFICA TION No. : 12737D21977
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
Airworthiness regulations such as 14 Code of Federal Regulations (CFR) for ageing aircraft and proposed
revisions to FAR/JAR 25.571 to incorporate Widespread Fatigue Damage (WFD) require evidence that
the possibility of WFD is precluded prior to the aircraft reaching the design service goal. T o satisfy the
requirements, a Structural Modification Point (SMP) has been determined from the overall fatigue endurance
in the presence of WFD. T o extend the design service goal of the A300 B2/B4/C4/F4 it is necessary to
introduce modifications before the SMP is reached.
This Service Bulletin details the procedure to reinforce the butt joint at FR72 by installation of an additional
external doubler without cutout at the butt joint of FR72 at STGR13, LH/RH and to extend the butt joint
doubler by 3 rivet rows beyond the lap joint at STGR13 LH/RH, before the SMP of 40750 FC is reached.
The accomplishment of this Service Bulletin will allow A300 B2/B4/C4/F4 aircraft to reach the Limit of Validity
(LOV).
NOTE : Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin
No. A300-53-0262 (FUSELAGE - INSPECT THE INNER RIVET ROWS ON EACH SIDE OF THE
CENTER REGION OF THE CIRCUMFERENTIAL JOINT CROSS BUTT STRAP A T FRAME 72,
BETWEEN STGR12 AND STGR4, LH AND RH).
NOTE : This Service Bulletin is only applicable, if there are no previous repairs and/or modifications
performed in the whole affected area. In case of existing repairs and/or modifications in this area
the operators are kindly requested to contact AIRBUS far in advance of this Service Bulletin
giving all the repair or modification details to get specific solutions.
EVALUATION T ABLE
COMPLIANCE Mandatory CANCELS INSPECTION SB Ye s
POTENTIAL AD Ye s A/C OPERA TION AFFECTED No
RELIABILITY AFFECTED No P AX COMFORT AFFECTED No
COST SAVING No ETOPS AFFECTED No
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### Page 6

A300A300
SERVICE BULLETIN
SUMMARY
EVALUATION T ABLE
STRUCTURAL LIFE EXTN Ye s VENDOR SB INVOL VED No
ZERO STRESS JACKING Ye s
KIT PRICE (USD) D01 5706 KIT PRICE (USD) D02 7185
KIT PRICE (USD) D03 7080
MODIFICA TION CLASSIFICA TION
MAJOR 12737D21977
MINOR None
As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural
strength, reliability , operational characteristics affecting the airworthiness of the product. All other changes
are major changes.
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
50W 69X 72U ABR AFG C2A DHL F2I FLM IAW IRA IRM KZU MIX MNB MSR NTR P2A RUN SOP TDX
TNO TSY
CONCURRENT REQUIREMENTS
None
REFERENCES/REPERCUSSIONS
TFU : None
OEB : None
AOT : None
SIL : None
LIFE LIMIT : None
LINE MAINTENANCE AFFECTED : No
OTHERS : None
NATURE OF THE WORK
AIRCRAFT : YES
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### Page 7

A300A300
SERVICE BULLETIN
SUMMARY
EQUIPMENT : NO
HARD : NO
SOFT : NO
OBRM : NO
MANPOWER
Config. 01
TOT AL MANHOURS 476.00
ELAPSED TIME (HOURS) 150.00
Config. 02
TOT AL MANHOURS 469.75
ELAPSED TIME (HOURS) 148.00
Config. 03
TOT AL MANHOURS 370.25
ELAPSED TIME (HOURS) 119.00
MATERIAL INFORMATION
AIRCRAFT DA T A
Config. 01
Straps, wedges, shims, pins, collars and rivets.
Config. 02
Straps, wedges, shims, pins, collars and rivets.
Config. 03
Straps, wedges, shims, pins, collars and rivets.
APPENDICES
Appendix 1 - Jacking Instructions
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### Page 8 (OCR)

© A300
SERVICE BULLETIN
SUMMARY
Z250
STGR10 STGR7 STGR4
AIRCRAFT
CENTERLINE
STGR4
STGR7
STGR14
ADDITIONAL EXTERNAL  STGR14
DOUBLER
AB6 53 0369 AAMA-A  FR73
FR72
FR71
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 4
Printed in France © AIRBUS 2008 All rights reserved

### Page 9

A300A300
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORA TE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Tel : (33) 5 61 93 33 33
Telex : AIRBU 530526F
Fax : (33) 5 61 93 42 51
MANDATORY MANDATORY MANDATORY MANDATORY
A T A SYSTEM : 53
TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE THE BUTT JOINT A T FRAME 72
MODIFICA TION No. : 12737D21977
This document contains AIRBUS PROPRIET ARY INFORMA TION and shall at all times remain the property
of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information
contained in it. It is delivered on the express condition that the said document and the information contained
in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby
delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any
manner (except for the purposes of performing the tasks described hereunder and provided that any recipient
of such document shall comply with the conditions herein), without AIRBUS prior written consent.
1. P LANNING INFORMATION
A. E FFECTIVITY
(1) Models
B2-1C B2-203 B2K-3C B4-103 B4-120 B4-203 B4-2C C4-203 F4-203
(2) Aircraft
(a) Effectivity by MSN
This Service Bulletin is applicable to aircraft MSN :
0003 0019 0041 0044 0045 0047 0053 0055 0075 0079 0080 0082-0085 0090 0094
0095 0100 0101 0105 0107 0116 0117 0123-0126 0128 0129 0133-0137 0139 0141
0147-0152 0154-0157 0160 0170 0173 0175 0176 0180 0183-0185 0187 0189
0190 0196 0199 0200 0203 0204 0208 0210-0212 0216 0218-0220 0226 0227
0234-0236 0239 0243 0244 0247 0249 0250 0255 0256 0259 0261 0265 0274 0277
0289 0292 0299 0302 0304
(b) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the
time of issue in accordance with the information available to AIRBUS. Any future
changes resulting from transfer of an aircraft from one operator to another will not be
reflected in this list unless the Service Bulletin is revised for another reason.
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### Page 10

A300A300
SERVICE BULLETIN
OPERA TOR MSN
50W 0003
69X 0095
72U 0079
ABR 0148 0152 0184 0189 0199 0208 0219 0220 0234 0236 0250
0259 0274 0289
AFG 0180 0190
C2A 0211
DHL 0084 0085 0141 0149 0249 0265
F2I 0083 0094 0128 0133 0135 0136 0137 0156 0170 0235 0243
FLM 0082 0151 0176 0256
IAW 0239
IRA 0080 0139 0173 0185 0187 0226 0299 0302
IRM 0055 0090 0160 0175 0204 0244
KZU 0041 0044 0101 0117
MIX 0125 0134 0157 0196 0203 0218
MNB 0019 0047 0123 0212 0277 0292 0304
MSR 0200 0255
NTR 0124 0155 0261
P2A 0116 0150
RUN 0075 0105 0107 0147 0154 0183
SOP 0126
TDX 0053 0100 0216
TNO 0045 0210 0227 0247
TSY 0129
(c) Effectivity by MSN and Kit/Configuration
The Kits and configurations applicable to these MSNs are given at the end of this list
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### Page 11

A300A300
SERVICE BULLETIN
0003 0019 0041 0044-0045 0047
KIT No. QTY PER A/C CONFIGURA TION
530369D01R03 1 01
The Kits and configurations applicable to these MSNs are given at the end of this list
0053 0055 0075 0079-0080 0082-0085 0090 0094-0095 0100-0101 0105 0107
0116-0117 0123-0126 0128-0129 0133-0137 0139 0141 0147-0152 0154-0156
KIT No. QTY PER A/C CONFIGURA TION
530369D02R03 1 02
The Kits and configurations applicable to these MSNs are given at the end of this list
0157 0160 0170 0173 0175-0176 0180 0183-0185 0187 0189-0190 0196 0199-0200
0203-0204 0208 0210-0212 0216 0218-0220 0226-0227 0234-0236 0239 0243-0244
0247 0249-0250 0255-0256 0259 0261 0265 0274 0277 0289 0292 0299 0302 0304
KIT No. QTY PER A/C CONFIGURA TION
530369D03R03 1 03
NOTE : Config. 01 is valid for aircraft on which the Mod. No. 001610D00916
(Title : TO IMPROVE FR72 JOINTS) has not been embodied in the
production line.
NOTE : Config. 02 is valid for aircraft, which have the Mod. No. 001610D00916
(Title : TO IMPROVE FR72 JOINTS) embodied but the Mod. No.
2611D02031 (Title : FUSELAGE STRUCTURE - IMPROVE THE
FA TIGUE LIFE OF LONGITUDINAL LAP JOINTS OF OUTER SKIN) not
embodied in the production line.
NOTE : Config. 03 is valid for aircraft on which the Mod. No. 001610D00916
(Title : TO IMPROVE FR72 JOINTS) and the Mod. No. 2611D02031
(Title : FUSELAGE STRUCTURE - IMPROVE THE FA TIGUE LIFE OF
LONGITUDINAL LAP JOINTS OF OUTER SKIN) have been embodied
in the production line.
(3) Spares
None
B. C ONCURRENT REQUIREMENTS
None
C. R EASON
(1) History
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### Page 12

A300A300
SERVICE BULLETIN
Airworthiness regulations such as 14 Code of Federal Regulations (CFR) for ageing aircraft
and proposed revisions to FAR/JAR 25.571 to incorporate Widespread Fatigue Damage
(WFD) require evidence that the possibility of WFD is precluded prior to the aircraft reaching
the design service goal. T o satisfy the requirements, a Structural Modification Point (SMP)
has been determined from the overall fatigue endurance in the presence of WFD. T o
extend the design service goal of the A300 B2/B4/C4/F4 it is necessary to introduce
modifications before the SMP is reached.
(2) Objective/Action
This Service Bulletin details the procedure to reinforce the butt joint at FR72 by installation
of an additional external doubler without cutout at the butt joint of FR72 at STGR13, LH/RH
and to extend the butt joint doubler by 3 rivet rows beyond the lap joint at STGR13 LH/RH,
before the SMP of 40750 FC is reached.
(3) Advantages
The accomplishment of this Service Bulletin will allow A300 B2/B4/C4/F4 aircraft to reach
the Limit of Validity (LOV).
NOTE : Accomplishment of this Service Bulletin cancels the inspection requirements
of Service Bulletin No. A300-53-0262 (FUSELAGE - INSPECT THE INNER
RIVET ROWS ON EACH SIDE OF THE CENTER REGION OF THE
CIRCUMFERENTIAL JOINT CROSS BUTT STRAP A T FRAME 72, BETWEEN
STGR12 AND STGR4, LH AND RH).
(4) Operational/Maintenance Consequences
NOTE : This Service Bulletin is only applicable, if there are no previous repairs and/or
modifications performed in the whole affected area. In case of existing
repairs and/or modifications in this area the operators are kindly requested to
contact AIRBUS far in advance of this Service Bulletin giving all the repair or
modification details to get specific solutions.
D. D ESCRIPTION
T o accomplish this Service Bulletin it is necessary to :
(1) Config. 01
(a) Reinforce butt joint at FR72 between STGR14 LH and STGR14 RH
(2) Config. 02
(a) Reinforce butt joint at FR72 between STGR14 LH and STGR14 RH
(3) Config. 03
(a) Reinforce butt strap at FR72 between STGR14 LH and STGR14 RH
E. C OMPLIANCE
(1) Classification
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### Page 13

A300A300
SERVICE BULLETIN
Mandatory
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin is rendered mandatory at a threshold of 40750 FC.
The aircraft that have accumulated more than 40750 FC must be modified within 2000
FC after receipt of this Service Bulletin.
This Service Bulletin is associated to an Airworthiness Limitation Item (ALI) task mandated
by Airworthiness Directive (AD) 2009-0155, published by the European Aviation Safety
Agency (EASA).
Refer to the associated ALI task and the A300 ALI AD, 2009-0155.
F. A PPROVAL
Approved under EASA Design Organisation Approval No. EASA 21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS
origin, and which affects the content of this Service Bulletin, the operator is responsible for
obtaining approval by its airworthiness authority for any adaptation necessary before incorporation
of the Service Bulletin.
G. M ANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the
work. These estimates assume that the work will be done by experienced personnel, and may
need to be revised upwards to suit operators’ circumstances. The estimates do not include the
time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying
time for paints, sealants, etc. and general administration work are also not included.
Config. 01
Get Access 2.75
Modification 468.25
Close-up 5.00
TOT AL MANHOURS 476.00
ELAPSED TIME (HOURS) 150.00
Config. 02
Get Access 2.75
Modification 462.00
Close-up 5.00
TOT AL MANHOURS 469.75
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### Page 14

A300A300
SERVICE BULLETIN
ELAPSED TIME (HOURS) 148.00
Config. 03
Get Access 2.75
Modification 362.50
Close-up 5.00
TOT AL MANHOURS 370.25
ELAPSED TIME (HOURS) 119.00
H. W EIGHT AND BALANCE
Config. 01
Manufacturers Empty Weight : +16.17 kg (+35.65 lb)
Effect on Balance : +739.42 kgm (+5348.15 lb.ft)
Config. 02
Manufacturers Empty Weight : +16.26 kg (+35.85 lb)
Effect on Balance : +743.54 kgm (+5377.95 lb.ft)
Config. 03
Manufacturers Empty Weight : +15.87 kg (+34.99 lb)
Effect on Balance : +725.70 kgm (+5248.92 lb.ft)
I. E LECTRICAL LOAD DATA
Not changed
J. R EFERENCES
Aircraft Maintenance Manual (AMM) : 07-11-00 24-00-00 25-22-11 25-23-11
25-23-21 25-23-31 25-24-11
Elec. Std. Practices Manual (ESPM) : 20-55-00
Structural Repair Manual (SRM) : 51-30-34 51-30-40 51-30-43 51-30-45
51-30-50 51-41-50 51-51-00
Consumable Material List (CML)
Standards Manual (SM)
Appendix 1
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### Page 15

A300A300
SERVICE BULLETIN
K. P UBLICATIONS AFFECTED
Structural Repair Manual (SRM) : 53-18-12
L. I NTERCHANGEABILITY/MIXABILITY
None
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A300A300
SERVICE BULLETIN
This Page Intentionally Left Blank
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### Page 17

A300A300
SERVICE BULLETIN
2. M ATERIAL INFORMATION
A. M ATERIAL - PRICE AND AVAILABILITY
(1) Material
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :
AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 Hamburg
Germany
For ordering by internet:http://spares.airbus.com
For SB Kits by fax : +49 40 50 76 25 90
For Spares by fax : +49 40 50 76 40 12
(2) Price and Availability
Kit 530369D01R03
Cost : 5706 US dollars
Availability : 99 calendar days from receipt of order
The Kit availability given above is the standard lead time from the date of your purchase
order. If you require the Kit(s) before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to the economic conditions
at the issue date of the Service Bulletin.
Kit 530369D02R03
Cost : 7185 US dollars
Availability : 99 calendar days from receipt of order
The Kit availability given above is the standard lead time from the date of your purchase
order. If you require the Kit(s) before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to the economic conditions
at the issue date of the Service Bulletin.
Kit 530369D03R03
Cost : 7080 US dollars
Availability : 99 calendar days from receipt of order
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A300A300
SERVICE BULLETIN
The Kit availability given above is the standard lead time from the date of your purchase
order. If you require the Kit(s) before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to the economic conditions
at the issue date of the Service Bulletin.
B. I NDUSTRY SUPPORT INFORMATION
Airbus will participate to the costs of accomplishment of this Service Bulletin by providing a
35% reduction to the applicable sales prices given in paragraph 2.A.(2) for orders placed before
31 December 2018.
C. L IST OF COMPONENTS
Kit 530369D01R03
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
1 A5397985220000 1 EA STRAP
2 A5397985220200 2 EA STRAP
3 A5397985320400 1 EA WEDGE
4 A5397985320500 1 EA WEDGE
5 A5397985320000 4 EA WEDGE
6 A5397985420400 2 EA SHIM
7 A5397985420600 2 EA SHIM
8 A5397985420000 2 EA SHIM
9 A5397985420200 2 EA SHIM
15 MBBN4477-4011 40 EA RIVET
16 DAN6-6-6 20 EA PIN
17 NSA5075-6 712 EA COLLAR
18 DAN6-6-9X 28 EA PIN
19 DAN11-6X 974 EA COLLAR
20 DAN6-6-8X 96 EA PIN
21 DAN6-6-7X 212 EA PIN
22 DAN6-6-5 144 EA PIN
23 DAN6-6-6X 288 EA PIN
25 DAN6-6-5X 350 EA PIN
26 DAN6-6-4 208 EA PIN
27 DAN6-6-3 340 EA PIN
NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you can not identify in the LIST OF
COMPONENTS of this Service Bulletin. The SM will give you the correct part number
to part number relationship.
Kit 530369D02R03
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
1 A5397985220000 1 EA STRAP
2 A5397985220200 2 EA STRAP
3 A5397985320400 1 EA WEDGE
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 10
Printed in France © AIRBUS 2008 All rights reserved

### Page 19

A300A300
SERVICE BULLETIN
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
4 A5397985320500 1 EA WEDGE
5 A5397985320000 4 EA WEDGE
6 A5397985420400 2 EA SHIM
7 A5397985420600 2 EA SHIM
8 A5397985420000 2 EA SHIM
9 A5397985420200 2 EA SHIM
15 MBBN4477-4011 36 EA RIVET
16 DAN6-6-6 16 EA PIN
17 NSA5075-6 726 EA COLLAR
18 DAN6-6-9X 56 EA PIN
19 DAN11-6X 1008 EA COLLAR
20 DAN6-6-8X 92 EA PIN
21 DAN6-6-7X 178 EA PIN
22 DAN6-6-5 130 EA PIN
23 DAN6-6-6X 316 EA PIN
25 DAN6-6-5X 366 EA PIN
26 DAN6-6-4 240 EA PIN
27 DAN6-6-3 340 EA PIN
NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you can not identify in the LIST OF
COMPONENTS of this Service Bulletin. The SM will give you the correct part number
to part number relationship.
Kit 530369D03R03
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
1 A5397985220000 1 EA STRAP
2 A5397985220200 2 EA STRAP
5 A5397985320000 4 EA WEDGE
6 A5397985420400 2 EA SHIM
7 A5397985420600 2 EA SHIM
8 A5397985420000 2 EA SHIM
9 A5397985420200 2 EA SHIM
10 A5397985320200 1 EA WEDGE
11 A5397985320300 1 EA WEDGE
15 MBBN4477-4011 35 EA RIVET
16 DAN6-6-6 16 EA PIN
17 NSA5075-6 702 EA COLLAR
18 DAN6-6-9X 58 EA PIN
19 DAN11-6X 992 EA COLLAR
20 DAN6-6-8X 116 EA PIN
21 DAN6-6-7X 152 EA PIN
22 DAN6-6-5 124 EA PIN
23 DAN6-6-6X 290 EA PIN
24 DAN6-6-10X 2 EA PIN
25 DAN6-6-5X 374 EA PIN
26 DAN6-6-4 208 EA PIN
27 DAN6-6-3 354 EA PIN
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 11
Printed in France © AIRBUS 2008 All rights reserved

### Page 20

A300A300
SERVICE BULLETIN
NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you can not identify in the LIST OF
COMPONENTS of this Service Bulletin. The SM will give you the correct part number
to part number relationship.
D. L IST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP
MA T No.
Sealant Mat. No. 09-013 As required
Cleaning agent Mat. No. 11-026 As required
Polyurethane primer Mat. No. 16-001 As required
Polyurethane top coat Mat. No. 16-002 As required
External top coat Mat. No. 16-018 As required
Wash primer Mat. No. 16-020 As required
(2) Components
None
E. P ARTS TO BE RE-IDENTIFIED BY THE OPERATOR
None
F. T OOLING - PRICE AND AVAILABILITY
T o accomplish this Service Bulletin, it is necessary to use the jacking equipment listed in Appendix
1
G. S PECIAL TOOLS
None
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 12
Printed in France © AIRBUS 2008 All rights reserved

### Page 21

A300A300
SERVICE BULLETIN
3. A CCOMPLISHMENT INSTRUCTIONS
A. G ENERAL
WARNING : MAKE SURE THA T YOU OBEY ALL THE WARNINGS AND CAUTIONS INCLUDED
IN THE REFERENCED PROCEDURES.
CAUTION : ALWA YS OBEY THE PRECAUTIONS THA T FOLLOW TO KEEP ELECTRICAL
WIRING IN A SA TISFACTORY CONDITION (ELECTRICALL Y AND MECHANICALL Y
SERVICEABLE).
WHEN YOU DO MAINTENANCE WORK, REP AIRS OR MODIFICA TIONS, ALWAYS
KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN
AS POSSIBLE. TO DO THIS :
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON ELECTRICAL WIRING AND COMPONENTS
- REGULARL Y REMOVE ALL SHAVINGS, UNWANTED MA TERIAL AND OTHER
CONT AMINA TION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONT AMINA TION AND
DAMAGE TO THE ELECTRICAL WIRING INST ALLA TION.
IF THERE IS CONT AMINA TION REFER TO ESPM 20-55-00.
(1) Preparation
(a) Config. 01 thru Config. 03
1 Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00,
Page block 301.
2 Put access platform(s) in position.
3 Remove and retain the overhead stowage compartments LH and RH as
necessary , refer to AMM 25-24-11, Page block 401.
4 Remove and retain the ceiling panels as necessary , refer to AMM 25-23-11,
Page block 401.
5 Remove and retain the lower sidewall panels as necessary , refer to AMM
25-23-31, Page block 401.
6 Remove and retain the upper sidewall panels as necessary , refer to AMM
25-23-21, Page block 401.
7 Remove the heat and sound insulation as necessary , refer to AMM 25-22-11,
Page block 401.
8 Do the jacking procedure, refer to Appendix 1.
(2) Standard Practices
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 13
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### Page 22

A300A300
SERVICE BULLETIN
(a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you can not identify in the LIST
OF COMPONENTS of this Service Bulletin. The SM will give you the correct part
number to part number relationship.
(b) For material specifications (Mat. No.) given in this Service Bulletin, refer to the
Consumable Material List (CML) .
(c) For stripping/paint removal in the reinforcement area, refer to SRM 51-41-50, Page
block 701.
(d) For fastener hole and drill data, refer to SRM 51-30-40, Page block 001.
(e) For alternative and substitute fasteners, refer to SRM 51-30-34, Page block 001.
(f) For fastener spacing and margin data, refer to SRM 51-30-50, Page block 001.
(g) T ransfer drill the existing holes with a pilot drill and drill bush.
(h) For countersinking information, refer to SRM 51-30-43, Page block 001.
(i) After drilling, remove all the burrs from the holes.
(j) Cut solid rivets to the correct length, as necessary .
(k) After drilling/riveting apply wash primer (Mat. No. 16-020), polyurethane primer (Mat.
No. 16-001) and polyurethane top coat (Mat. No. 16-002) (internal).
(l) Clean the surfaces to be sealed with cleaning agent (Mat. No. 11-026).
(m) Before installation of structural items apply sealant (Mat. No. 09-013) on all
mating surfaces.
(n) Wet install all fasteners and countersink washers with sealant (Mat. No. 09-013).
(o) Apply the external structure paint (Mat. No. 16-018) (color in accordance with the
operators livery) on the affected areas.
B. M ODIFICATION
(1) Config. 01
Refer to Kit 530369D01R03
Refer to Figure 1
NOTE : This Service Bulletin is only applicable, if there are no previous repairs and/or
modifications performed in the whole affected area. In case of existing repairs
and/or modifications in this area the operators are kindly requested to contact
AIRBUS giving all the repair or modification details to get specific solutions.
(a) Reinforce butt joint at FR72 between STGR14 LH and STGR14 RH
1 Put these items in position and mark their contour on the aircraft outer skin :
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 14
Printed in France © AIRBUS 2008 All rights reserved

### Page 23

A300A300
SERVICE BULLETIN
1 strap A5397985220000 Item 1
2 strap A5397985220200 Item 2
1 wedge LH A5397985320400 Item 3
1 wedge RH A5397985320500 Item 4
4 wedge A5397985320000 Item 5
2 shim A5397985420400 Item 6
2 shim A5397985420600 Item 7
2 shim A5397985420000 Item 8
2 shim A5397985420200 Item 9
NOTE : Make sure that the required rivet edge distance is 12.0 mm (0.472
in.) nominal and 10.0 mm (0.394 in.) minimum.
2 Rework the straps, Item 2, as necessary as shown in Detail C.
3 Identify the fasteners you must remove in the modification area at FR72 between
STGR14 LH and STGR14 RH with a wax pencil.
4 Remove and retain the straps, Item 1 and 2, the wedges, Item 3, 4 and 5
and the shims, Item 6, 7, 8 and 9.
5 Remove and discard the identified fasteners.
6 Put these items in position, transfer drill the fastener holes and drill new
fastener holes :
1 strap A5397985220000 Item 1
2 strap A5397985220200 Item 2
1 wedge LH A5397985320400 Item 3
1 wedge RH A5397985320500 Item 4
4 wedge A5397985320000 Item 5
2 shim A5397985420400 Item 6
2 shim A5397985420600 Item 7
2 shim A5397985420000 Item 8
2 shim A5397985420200 Item 9
7 Remove all temporarily attached items and deburr.
8 Countersink the straps, Items 1 and 2 and shims, Items 6, 7, 8 and 9.
9 Apply wash primer (Mat. No. 16-020), polyurethane primer (Mat. No. 16-001)
and polyurethane top coat (Mat. No. 16-002) to the remaining countersinks.
10 Fill the existing countersinks with countersunk repair washers, refer to SRM
51-30-45, Page block 001.
11 Apply a thin layer of sealant (Mat. No. 09-013) to the mating surfaces of the
straps, Item 1 and 2, wedges, Item 3, 4 and 5 and shims, Item 6, 7, 8 and 9.
12 Put the straps, Items 1 and 2, wedges, Items 3, 4 and 5 and shims, Items 6, 7, 8
and 9 in the correct installation position and install with :
40 rivet MBBN4477-4011 Item 15
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 15
Printed in France © AIRBUS 2008 All rights reserved

### Page 24

A300A300
SERVICE BULLETIN
20 pin DAN6-6-6 Item 16
712 collar NSA5075-6 Item 17
28 pin DAN6-6-9X Item 18
974 collar DAN11-6X Item 19
96 pin DAN6-6-8X Item 20
212 pin DAN6-6-7X Item 21
144 pin DAN6-6-5 Item 22
288 pin DAN6-6-6X Item 23
350 pin DAN6-6-5X Item 25
208 pin DAN6-6-4 Item 26
340 pin DAN6-6-3 Item 27
(2) Config. 02
Refer to Kit 530369D02R03
Refer to Figure 2
(a) Reinforce butt joint at FR72 between STGR14 LH and STGR14 RH
1 Put these items in position and mark their contour on the aircraft outer skin :
1 strap A5397985220000 Item 1
2 strap A5397985220200 Item 2
1 wedge LH A5397985320400 Item 3
1 wedge RH A5397985320500 Item 4
4 wedge A5397985320000 Item 5
2 shim A5397985420400 Item 6
2 shim A5397985420600 Item 7
2 shim A5397985420000 Item 8
2 shim A5397985420200 Item 9
NOTE : Make sure that the required rivet edge distance is 12.0 mm (0.472
in.) nominal and 10.0 mm (0.394 in.) minimum.
2 Rework the straps, Item 2, as necessary as shown in Detail C.
3 Identify the fasteners you must remove in the modification area at FR72 between
STGR14 LH and STGR14 RH with a wax pencil.
4 Remove and retain the straps, Item 1 and 2, the wedges, Item 3, 4 and 5
and the shims, Item 6, 7, 8 and 9.
5 Remove and discard the identified fasteners.
6 Put these items in position, transfer drill the fastener holes and drill new
fastener holes :
1 strap A5397985220000 Item 1
2 strap A5397985220200 Item 2
1 wedge LH A5397985320400 Item 3
1 wedge RH A5397985320500 Item 4
4 wedge A5397985320000 Item 5
2 shim A5397985420400 Item 6
2 shim A5397985420600 Item 7
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 16
Printed in France © AIRBUS 2008 All rights reserved

### Page 25

A300A300
SERVICE BULLETIN
2 shim A5397985420000 Item 8
2 shim A5397985420200 Item 9
7 Remove all temporarily attached items and deburr.
8 Countersink the straps, Items 1 and 2 and shims, Items 6, 7, 8 and 9.
9 Apply wash primer (Mat. No. 16-020), polyurethane primer (Mat. No. 16-001)
and polyurethane top coat (Mat. No. 16-002) to the remaining countersinks.
10 Fill the existing countersinks with countersunk repair washers, refer to SRM
51-30-45, Page block 701.
11 Apply a thin layer of sealant (Mat. No. 09-013) to the mating surfaces of the
straps, Item 1 and 2, wedges, Item 3, 4 and 5 and shims, Item 6, 7, 8 and 9.
12 Put the straps, Items 1 and 2, wedges, Items 3, 4 and 5 and shims, Items 6, 7, 8
and 9 in the correct installation position and install with :
36 rivet MBBN4477-4011 Item 15
16 pin DAN6-6-6 Item 16
726 collar NSA5075-6 Item 17
56 pin DAN6-6-9X Item 18
1008 collar DAN11-6X Item 19
92 pin DAN6-6-8X Item 20
178 pin DAN6-6-7X Item 21
130 pin DAN6-6-5 Item 22
316 pin DAN6-6-6X Item 23
366 pin DAN6-6-5X Item 25
240 pin DAN6-6-4 Item 26
340 pin DAN6-6-3 Item 27
(3) Config. 03
Refer to Kit 530369D03R03
Refer to Figure 3
(a) Reinforce butt strap at FR72 between STGR14 LH and STGR14 RH
1 Put these items in position and mark their contour on the aircraft outer skin :
1 strap A5397985220000 Item 1
2 strap A5397985220200 Item 2
4 wedge A5397985320000 Item 5
2 shim A5397985420400 Item 6
2 shim A5397985420600 Item 7
2 shim A5397985420000 Item 8
2 shim A5397985420200 Item 9
1 wedge LH A5397985320200 Item 10
1 wedge RH A5397985320300 Item 11
NOTE : Make sure that the required rivet edge distance is 12.0 mm (0.472
in.) nominal and 10.0 mm (0.394 in.) minimum.
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 17
Printed in France © AIRBUS 2008 All rights reserved

### Page 26

A300A300
SERVICE BULLETIN
2 Rework the straps, Item 2, as necessary as shown in Detail C.
3 Identify the fasteners you must remove in the modification area at FR72 between
STGR14 LH and STGR14 RH with a wax pencil.
4 Remove and retain the straps, Item 1 and 2, the wedges, Item 5, 10 and 11
and the shims, Item 6, 7, 8 and 9.
5 Remove and discard the identified fasteners.
6 Put these items in position, transfer drill the fastener holes and drill new
fastener holes :
1 strap A5397985220000 Item 1
2 strap A5397985220200 Item 2
4 wedge A5397985320000 Item 5
2 shim A5397985420400 Item 6
2 shim A5397985420600 Item 7
2 shim A5397985420000 Item 8
2 shim A5397985420200 Item 9
1 wedge LH A5397985320200 Item 10
1 wedge RH A5397985320300 Item 11
7 Remove all temporarily attached items and deburr.
8 Countersink the straps, Items 1 and 2 and shims, Items 6, 7, 8 and 9.
9 Apply wash primer (Mat. No. 16-020), polyurethane primer (Mat. No. 16-001)
and polyurethane top coat (Mat. No. 16-002) to the remaining countersinks.
10 Fill the existing countersinks with countersunk repair washers, refer to SRM
51-30-45, Page block 701.
11 Apply a thin layer of sealant (Mat. No. 09-013) to the mating surfaces of the
straps, Item 1 and 2, wedges, Item 5, 10 and 11 and shims, Item 6, 7, 8 and 9.
12 Put the straps, Items 1 and 2, wedges, Items 5, 10 and 11 and shims, Items 6, 7,
8 and 9 in the correct installation position and install with :
35 rivet MBBN4477-4011 Item 15
16 pin DAN6-6-6 Item 16
702 collar NSA5075-6 Item 17
58 pin DAN6-6-9X Item 18
992 collar DAN11-6X Item 19
116 pin DAN6-6-8X Item 20
152 pin DAN6-6-7X Item 21
124 pin DAN6-6-5 Item 22
290 pin DAN6-6-6X Item 23
2 pin DAN6-6-10X Item 24
374 pin DAN6-6-5X Item 25
208 pin DAN6-6-4 Item 26
354 pin DAN6-6-3 Item 27
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 18
Printed in France © AIRBUS 2008 All rights reserved

### Page 27

A300A300
SERVICE BULLETIN
C. T EST
None
D. C LOSE UP
(1) Config. 01 thru Config. 03
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the retained ceiling panels, refer to AMM 25-23-11, Page block 401.
(c) Install the retained upper sidewall panels, refer to AMM 25-23-21, Page block 401.
(d) Install the retained lower sidewall panels, refer to AMM 25-23-31, Page block 401.
(e) Install the retained heat and sound insulation, refer to AMM 25-22-11, Page block
401.
(f) Install the retained overhead stowage compartments LH and RH, refer to AMM
25-24-11, Page block 401.
(g) Remove the access platform(s).
(h) Lower the aircraft to the ground, refer to Appendix 1.
E. D OCUMENTATION
Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 19
Printed in France © AIRBUS 2008 All rights reserved

### Page 28 (OCR)

© A300
SERVICE BULLETIN
Z250
D
STGR10  STGR7 STGR4
AIRCRAFT
CENTERLINE
STGR4
STGR7
STGR14
STGR10
STGR14
AB6 53 0369 ACMA-A  FR73
FR72
FR71
Figure 1, Sheet 1
Config. 01 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D01)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 20
Printed in France © AIRBUS 2008 All rights reserved

### Page 29 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  - WD
AIRCRAFT CENTERLINE
STGR1
STGR2
STGR3
AB6 53 0269 ACMB-A  5
STGR4
Figure 1, Sheet 2
Contig. 01 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D01)
DATE: Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 21
Printed in France © AIRBUS 2008 All rights reserved

### Page 30 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD
STGR4
5
STGR5
STGRO
10.0mm
(0.39 in.)
2
10.0mm  10_0mm
AB6 53 0269 ACMC-A  (0.39in.)  (0.39in.)
===== = =
STGR7
-BIC
Figure 1, Sheet 3
Contig. 01 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D01)
DATE: Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 22
Printed in France © AIRBUS 2008 All rights reserved

### Page 31 (OCR)

• A300
SERVICE BULLETIN
SECTION
A - A  FWD
SECTION
B- B
SECTION
C- C
AB6 53 0369 ACMD-A
Figure 1, Sheet 4
Config. 01 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D01)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 23

### Page 32 (OCR)

© A300
SERVICE BULLETIN
LH SHOWN
RH SYMMETRICAL  FWD
FR72
STRG7
STRG8
STRG9
AB6 53 0369АСМЕ-A  STRG10
Figure 1, Sheet 5
Config. 01 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D01)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 24
Printed in France © AIRBUS 2008 All rights reserved

### Page 33 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD  EIF
STRG10
2
STRG11
STRG12
36.0mm  1.42 in.)  D  2 × 18.0mm = 36_0mm  = 1.42in.)
STRG13  D  + 0  (2 × 0.71 in.
10.0mm  (0.39in.)  9  10.0mm  (0.39 in.)
10.0mm  10.0mm
(0.39 in.)  KERF  (0-39 in.)
Figure 1, Sheet 6
Contig. 01 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D01)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 25
Printed in France © AIRBUS 2008 All rights reserved

### Page 34 (OCR)

• A300
SERVICE BULLETIN
SECTION
D- D  -WDI  SECTION
E-E
STGR12
STGR5
STGR13
8
STGR14
AB6 53 0369 ACMG-A
Figure 1, Sheet 7
Config. 01 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D01)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 26

### Page 35 (OCR)

© A300
SERVICE BULLETIN
HOLE  ITEM  P/N  DESCRIPTION  KIT  HOLE DIAMETER  REMARKS
SYMBOL  MIN  MAX
15  MBBN4477-4011  RIVET  D01  (0.160in.)  4.06mm  (0.164in.)  1.17mm  NOMINAL SIZE
•  16  17  NSA5075-6  DAN6-6-6  PIN  COLLAR  D01  (0.188in.)  4.78mm  (0.190in.)  4.82mm  NOMINAL SIZE  TRANSITION FIT
•  18  19  DAN11-6X  DAN6-6-9X  PIN  COLLAR  D01  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
•  20  19  DAN6-6-8X  DAN11-6X  PIN  COLLAR  D01  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  TRANSITION FIT  FIRST OVERSIZE
19  21  DAN6-6-7X  DAN11-6X  COLLAR  PIN  D01  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  TRANSITION FIT  FIRST OVERSIZE
•  22  17  DAN6-6-5  NSA5075-6  PIN  COLLAR  D01  (0.188in.)  4.78mm  (0.190in.)  4.82mm  NOMINAL SIZE  TRANSITION FIT
23  19  DAN6-6-6X  DAN11-6X  PIN  COLLAR  D01  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
25  DAN6-6-5X  PIN  5.113mm  5.152mm  FIRST OVERSIZE
19  DAN11-6X  COLLAR  D01  (0.2013in.)  (0.2028in.)  TRANSITION FIT
26  17  NSA5075-6  DAN6-6-4  PIN  COLLAR  D01  (0.188in.)  4.78mm  (0.190in.)  4.82mm  NOMINAL SIZE  TRANSITION FIT
27  17  NSA5075-6  DAN6-6-3  PIN  COLLAR  D01  (0.188in.)  4.78mm  4.82mm  (0.190in.)  NOMINAL SIZE  TRANSITION FIT
AB6 53 0369 ACMH-B
Figure 1, Sheet 8
Config. 01 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D01)
DATE : Apr 07/05  SERVICE BULLETIN No. : А300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 27
Printed in France © AIRBUS 2008 All rights reserved

### Page 36 (OCR)

© A300
SERVICE BULLETIN
Z250
DA
STGR10  STGR7 STGR4
AIRCRAFT
CENTERLINE
STGR4
STGR7
STGR14
STGR10
STGR14
AB6 53 0369 AEMA-A  FR73
FR72
FR71
Figure 2, Sheet 1
Config. 02 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 28
Printed in France © AIRBUS 2008 All rights reserved

### Page 37 (OCR)

© A300
SERVICE BULLETIN
LH SHOWN  FR72
RH SYMMETRICAL  - WD
APC MSN 0133-0156
AIRCRAFT CENTERLINE
STGR1
STGR2
STGR3
5
STGR4
Figure 2, Sheet 2
Contig. 02 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 29
Printed in France © AIRBUS 2008 All rights reserved

### Page 38 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD
4/C MSN 0052-  APPLICABLE  -0131  AIRCRAFT
CENTERLINE
STGRI
= =
STGR2
STGR3
AB6 53 0269 AEMC-A  5
STGR4
Figure 2, Sheet 3
Contig. 02 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D02)
DATE: Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 30
Printed in France © AIRBUS 2008 All rights reserved

### Page 39 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD
STGR4
5
STGR5
STGR6
10.0mm
(0.39 in.)
2
10.0mm  10_0mm
AB6 53 0269 AEMD-A  (0.39in.)  e  (0.39in.)
STGR7  ==
-BIC
Figure 2, Sheet 4
Contig. 02 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D02)
DATE: Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 31
Printed in France © AIRBUS 2008 All rights reserved

### Page 40 (OCR)

• A300
SERVICE BULLETIN
SECTION
A- A  FWD
SECTION
B- B
C- C
AB6 53 0369 AEME-A
Figure 2, Sheet 5
Config. 02 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 32

### Page 41 (OCR)

© A300
SERVICE BULLETIN
LH SHOWN
RH SYMMETRICAL  FWD
FR72
======
STRG7
STRG8
STRG9
AB6 53 0369 AEMF-A  STRG10
Figure 2, Sheet 6
Config. 02 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 33
Printed in France © AIRBUS 2008 All rights reserved

### Page 42 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD  - EIF
STRG10
- 2
STRG11
STRG12  D
36.0mm  1.42 in.)  2 × 18.0mm = 36_0mm  1.42 in.)
STRG13  D  + 0  (2 × 0.71 in.
10.0mm  (0.39in.)  •) (•  10.0mm  (0.39 in.)
10.0mm  10.0mm
(0.39in.)  MERF  (0.39 in.)
Figure 2, Sheet 7
Contig. 02 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 34
Printed in France © AIRBUS 2008 All rights reserved

### Page 43 (OCR)

• A300
SERVICE BULLETIN
SECTION
D- D  -WDI  SECTION
E-E
STGR12
STGR5
STGR13
8
STGR14
AB6 53 0369 AEMH-A
Figure 2, Sheet 8
Config. 02 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 35

### Page 44 (OCR)

© A300
SERVICE BULLETIN
HOLE  ITEM  P/N  DESCRIPTION  KIT  HOLE DIAMETER  REMARKS
SYMBOL  MIN  MAX
15  MBBN4477-4011  RIVET  D02  (0.160in.)  4.06mm  (0.164in.)  1.17mm  NOMINAL SIZE
•  16  17  NSA5075-6  DAN6-6-6  PIN  COLLAR  D02  (0.188in.)  4.78mm  (0.190in.)  4.82mm  NOMINAL SIZE  TRANSITION FIT
•  18  19  DAN11-6X  DAN6-6-9X  PIN  COLLAR  D02  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
20  DAN6-6-8X  PIN
•  19  DAN11-6X  COLLAR  D02  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  TRANSITION FIT  FIRST OVERSIZE
19  21  DAN6-6-7X  DAN11-6X  COLLAR  PIN  D02  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  TRANSITION FIT  FIRST OVERSIZE
•  22  17  DAN6-6-5  NSA5075-6  PIN  COLLAR  D02  (0.188in.)  4.78mm  4.82mm  (0.190in.)  TRANSITION FIT  NOMINAL SIZE
23  19  DAN6-6-6X  DAN11-6X  PIN  COLLAR  D02  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
25  DAN6-6-5X  PIN
19  DAN11-6X  COLLAR  D02  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
26  DAN6-6-4  PIN  D02  4.78mm  4.82mm  NOMINAL SIZE
17  NSA5075-6  COLLAR  (0.188in.)  (0.190in.)  TRANSITION FIT
27  17  NSA5075-6  DAN6-6-3  PIN  COLLAR  D02  4.78mm  (0.188in.)  4.82mm  (0.190in.)  NOMINAL SIZE  TRANSITION FIT
AB6 53 0369 AEMJ-B
Figure 2, Sheet 9
Config. 02 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D02)
DATE : Apr 07/05  SERVICE BULLETIN No. : А300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 36
Printed in France © AIRBUS 2008 All rights reserved

### Page 45 (OCR)

© A300
SERVICE BULLETIN
2250
Л А
STGR 10  STGRZ STGR4
AIRCRAFT
B  CENTERLINE
STGR4
C  STGR7
STGR 14
STGR14
AB6 53 0369 AGMA-A  FR73
FR7Z
FRZ1
Figure 3, Sheet 1
Config. 03 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 37
Printed in France © AIRBUS 2008 All rights reserved

### Page 46 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  - WD
AIRCRAFT CENTERLINE
STGR1
STGR2
STGR3
AB6 53 0269 AGMB-A  5
STGR4
Figure 3, Sheet 2
Contig. 03 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D03)
DATE: Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 38
Printed in France © AIRBUS 2008 All rights reserved

### Page 47 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD
+ BC
STGR4
5
5
STGR5
STGR6
10.0mm
(0.39in.)
2
10.0mm  10-0mm
(0.39 in.)  (0.39in.)
AB6 53 0269 AGMC-A  STGR7
-BIC
Figure 3, Sheet 3
Contig. 03 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 39
Printed in France © AIRBUS 2008 All rights reserved

### Page 48 (OCR)

• A300
SERVICE BULLETIN
SECTION
A- A  FWD
SECTION
B- B
C- C
AB6 53 0369 AGMD-A
Figure 3, Sheet 4
Config. 03 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 40

### Page 49 (OCR)

© A300
SERVICE BULLETIN
LH SHOWN
RH SYMMETRICAL  FWD
FR72
STRG7
STRG8
STRG9
AB6 53 0369 AGME-A  STRG10
Figure 3, Sheet 5
Config. 03 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 41
Printed in France © AIRBUS 2008 All rights reserved

### Page 50 (OCR)

© A300
SERVICE BULLETIN
FR72
LH SHOWN
RH SYMMETRICAL  FWD  - EIF
STRG10
- 2
STRG11
STRG12
36.0mm  1.42 in.)  2 × 18.0mm = 36.0mm  1.42 in.)
0.71 in.  D  (2 × 0.71in.
×
STRG13
AB6 53 0369 AGMF-A  10.0mm  39 in.)  8
10.0mm  10_0mm
(0.39 in.)  KERF  (0.39in.)
Figure 3, Sheet 6
Contig. 03 : Reinforce Butt Joint at FR72 between STGR14 LA and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 42
Printed in France © AIRBUS 2008 All rights reserved

### Page 51 (OCR)

• A300
SERVICE BULLETIN
SECTION
D- D  -WDI  SECTION
E- E
STGR 12
STGR5
10 LH  10 L
11 RH
STGR13
STGR14
AB6 53 0369 AGMG-A
Figure 3, Sheet 7
Config. 03 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 43
Printed in France © AIRBUS 2008 All riahts reserved

### Page 52 (OCR)

© A300
SERVICE BULLETIN
SYMBOL  HOLE  ITEM  P/N  DESCRIPTION  KIT  MIN  HOLE DIAMETER  MAX  REMARKS
15  MBBN4477-4011  RIVET  D03  (0.160In.)  4.06mm  (0.164in.)  4.17mm  NOMINAL SIZE
16  DAN6-6-6  PIN
D03  4.78mm  4.82mm  NOMINAL SIZE
17  NSA5075-6  COLLAR  (0.188in.)  (0.190in.)  TRANSITION FIT
18  DAN6-6-9X  PIN
19  DAN11-6X  COLLAR  D03  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  TRANSITION FIT  FIRST OVERSIZE
20  19  DAN6-6-8X  DAN11-6X  PIN  COLLAR  D03  (0.2013in.)  5.113mm  0.2028in.  5.152mm  TRANSITION FIT  FIRST OVERSIZE
•  19  21  DAN6-6-7X  DAN11-6X  PIN  COLLAR  D03  (0.2013in.)  5.113mm  5.152mm  (0.2028in.)  FIRST OVERSIZE  TRANSITION FIT
•  22  17  NSA5075-6  DAN6-6-5  PIN  COLLAR  D03  (0.188in.)  4.78mm  (0.190in.)  4.82mm  TRANSITION FI  NOMINAL SIZE
23  19  DAN6-6-6X  DAN11-6X  PIN  COLLAR  D03  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
24  19  DAN6-6-10X  DAN11-6X  PIN  COLLAR  D03  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
25  19  DAN6-6-5X  DAN11-6X  PIN  COLLAR  D03  (0.2013in.)  5.113mm  (0.2028in.)  5.152mm  FIRST OVERSIZE  TRANSITION FIT
26  17  DAN6-6-4  NSA5075-6  COLLAR  PIN  D03  (0.188in.)  4.78mm  4.82mm  (0.190in.)  NOMINAL SIZE  TRANSITION FIT
27  17  NSA5075-6  DAN6-6-3  PIN  COLLAR  D03  (0.188in.  4.78mm  4.82mm  (0.190in.)  NOMINAL SIZE  TRANSITION FIT
AB6 53 0369 AGMH-B
Figure 3, Sheet 8
Config. 03 : Reinforce Butt Joint at FR72 between STGR14 LH and STGR14 RH (Kit D03)
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 44
Printed in France © AIRBUS 2008 All rights reserved

### Page 53

A300A300
SERVICE BULLETIN
APPENDIX 1
AIRBUS
CUSTOMER SERVICES DIRECTORA TE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Tel : (33) 5 61 93 33 33
Telex : AIRBU 530526F
Fax : (33) 5 61 93 42 51
A T A SYSTEM : 53
TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE THE BUTT JOINT A T FRAME 72
MODIFICA TION No. : 12737D21977
1. Config. 01 thru Config. 03
Jacking procedure for the installation of the external doubler on the fuselage skin at FR72.
A. FIXTURES, TOOLS TEST AND SUPPORT EQUIPMENT
ITEM P ART NUMBER QTY DESCRIPTION
343A160KN2 1 LOAD CELL
343A100KN2 4 LOAD CELL
343A63KN2 1 LOAD CELL
343A400KN2 2 LOAD CELL
98A07003910200 1 ADAPTOR
98A07003906200 6 ADAPTOR
98A07003909200 2 ADAPTOR
98A07003911200 2 ADAPTOR
98A07003907200 5 ADAPTOR
D30-11 1 JACK
D8004 2 JACK
D05-04 1 JACK
MS02-2 4 JACK
98A07003903001 2 FITTING for FR17
RT A 075009 LH 1 FITTING for FR76
RT A 075010 RH 1 FITTING for FR76
Refer to Figure 1, Sheet 3.
B. AIRCRAFT CONFIGURA TION
- This jacking procedure is only applicable to the configuration below :
The aircraft without :
. Fuel (except undrainable fuel)
. Payload
. Water (potable)
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 1
Printed in France © AIRBUS 2008 All rights reserved

### Page 54

A300A300
SERVICE BULLETIN
APPENDIX 1
. Baggage containers
. Pallets
. Emergency equipment
. Catering
. Documents and aircraft tool package
- For the complete aircraft configuration:
. Refer to Figure 1, Sheet 1.
NOTE : If the aircraft configuration is not the same as the configuration ab ove, contact
AIRBUS.
NOTE : If you do other tasks on the aircraft at the same time, contact AIRBUS.
C. JACKING PROCEDURE
(1) Obey the general jacking instructions, refer to SRM 51-51-00, Page block 001.
(2) Lift the aircraft on jacks at points A, B1, B2 and C as shown in Figure 1, Sheet 2, refer to
AMM 07-11-00, Page block 001.
Install :
- Jacking point A load cell PN 343A160KN2
- Jacking point B1 and B2 load cell PN 343A400KN2
- Jacking point C load cell PN 343A63KN2
(3) Install the additional jacking equipment at FR17 and FR76.
Refer to Figure 1, Sheet 2 and 3.
Install :
- FR17 LH/RH Jacking Fitting PN 98A07003903001 with load cell PN 343A100KN2
- FR76 LH jacking fitting PN RT A075009 LH with load cell PN 343A100KN2
NOTE : For the load cell PN 343A100KN2 an alternative load cell PN 343A63KN2
can be used.
- FR76 RH jacking fitting PN RT A075010 RH with load cell PN 343A100KN2
NOTE : For the load cell PN 343A100KN2 an alternative load cell PN 343A63KN2
can be used.
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 2
Printed in France © AIRBUS 2008 All rights reserved

### Page 55

A300A300
SERVICE BULLETIN
APPENDIX 1
CAUTION : MAKE SURE THA T THE LOADS NEVER EXCEED THE MAXIMUM PERMITTED
LOADS SPECIFIED IN FIGURE 1, SHEET 4.
(4) Apply the loads shown in step 1, to the jacks at FR17, FR76 and FR85.
Refer to Figure 1, Sheet 4.
(5) Wait until the loads on the jacks become stable and make sure that they are within a
tolerance of +/- 10 percent.
(6) Do the same procedure to apply the loads shown in step 2, step 3 and step 4.
NOTE : When the loads given in step 4 are stable and within a tolerance of +/-
10 percent, you can do the procedure given in the ACCOMPLISHMENT
INSTRUCTIONS, paragraph B.
D. CLOSE-UP
(1) Obey the general de-jacking instructions, refer to SRM 51-51-00, Page block 001.
(2) Gradually decrease the loads one step after the other, from step 4 to zero on the jacks at
FR17, FR76 and FR85.
Refer to Figure 1, Sheet 4.
(3) Remove the jacking equipment at FR17 and FR76.
(4) Lower the aircraft and remove jacking equipment at points A, B1, B2 and C as shown in
Figure 1, Sheet 2, refer to AMM 07-11-00, Page block 001.
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 3
Printed in France © AIRBUS 2008 All rights reserved

### Page 56 (OCR)

© A300
SERVICE BULLETIN
APPENDIX 1
A/C CONFIGURATION FOR JACKING
FUSELAGE  EQUIPMENT/  INSTALLED  REMOVED  LH WING  INSTALLED  REMOVED  RH WING  INSTALLED  REMOVED
FURNISHINGS
FUSELAGE SECTION 11  BELLY FAIRING  BELLY FAIRING
FUSELAGE SECTION 12  LH SLAT  RH SLAT
FUSELAGE SECTION 13  LH FLAP  RH FLAP
FUSELAGE SECTION 14  LH FLAP TRACKS  RH FLAP TRACKS
FUSELAGE SECTION 15  SPOILER  SPOILER
FUSELAGE SECTION 16
FUSELAGE SECTION 17 X
FUSELAGE SECTION 18
FUSELAGE SECTION 19 X
MOVABLE ELEMENTS  OTHERS
INSTALLED REMOVED  LANDING GEARS  INSTALLED REMOVED
HORIZONTAL STABILIZER  NOSE LANDING GEAR
VERTICAL STABILIZER  LH MAIN LANDING GEAR
FWD LH PAX DOOR  RH MAIN LANDING GEAR
FWD RH PAX DOOR
MID LH PAX DOOR  PYLONS
MID RH PAX DOOR  LH PYLON
LH EMERGENCY EXIT  RH PYLON
RH EMERGENCY EXIT
AFT LH PAX DOOR  ENGINES
AFT RH PAX DOOR  LH ENGINE
FWD CARGO DOOR  RH ENGINE
AFT CARGO DOOR
APU  THRUST REVERSERS
LH ENGINE
RH ENGINE
FUEL
LH WING TANKS
RH WING TANKS
TRIM TANK (WHERE INSTALLED)
EXCEPT UNDRAINABLE FUEL
A_SB_530369_6_APXX_01_00
Figure 1, Sheet 1
Jacking of the Aircraft for the Installation of the External Doubler at FR72
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 4
Printed in France © AIRBUS 2008 All rights reserved

### Page 57 (OCR)

© A300
SERVICE BULLETIN
APPENDIX 1
FR17  FR76
FR17  B2
A_SB_530369_6_APХX_02_00
Figure 1, Sheet 2
Jacking of the Aircraft for the Installation of the External Doubler at FR72
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 5
Printed in France © AIRBUS 2008 All rights reserved

### Page 58 (OCR)

© A300
SERVICE BULLETIN
APPENDIX 1
QTY
LOAD CELL PART  NUMBER  343A160KN2  343A400KN2  343A400KN2  343A63KN2  343A100KN2  343A100KN2  343A100KN2  OR  343A63KN2  343A100KN2  OR  343A63KN2
QTY
LOAD CELL ADAPTOR  98A07003910200  98A07003906200  98A07003909200  98A07003911200  98A07003909200  98A07003911200  98A07003907200  98A07003906200  98A07003907200  98A07003906200  98A07003907200  98A07003906200  98A07003907200  98A07003906200  98A07003907200  98A07003906200
QTY
MS02-2  MS02-2  MS02-2  MS02-2
98A07003903001  98A07003903001  RTA 075009 LH  RTA 075010 RH
POINT  B1  19
JACKING OR SUPPORT  POINTS  FRONT JACK  LH MAIN JACK  RH MAIN JACK  SAFETY (FR85)  JACK FR17 LH  JACK FR17 RH  JACK FR76 LH  JACK FR76 RH  N/A: NOT APPLICABLE
A_SB_530369_6_APXX_03_02
Figure 1, Sheet 3
Jacking of the Aircraft for the Installation of the External Doubler at FR72
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 6
Printed in France © AIRBUS 2008 All rights reserved

### Page 59 (OCR)

© A300
SERVICE BULLETIN
APPENDIX 1
JACKING POINTS  MAX. LOAD  (daN)  APPLIED LOADS (daN) +/- 10%  % OF TOTAL  LOADS  ACTUAL LOADS
STEP 1  STEP 2  STEP 3  STEP 4
FR17 LH  8250  1000  2000  3000  4000  4
FR17 RH  8250  1000  2000  3000  4000  4
FR76 LH  5200  750  1500  2250  3000
FR76 RH  5200  750  1500  2250  3000
FR85
(SAFETY JACK)  4500  1000  2000  3000  4000
NOTE 1: TO INSTALL THE MODIFICATION KIT (REFER TO ACCOMPLISHMENT INSTRUCTION PARAGRAPH B.),
MAKE SURE THAT THE ACTUAL LOADS ARE WITHIN A TOLERANCE OF +/- 10% OF THE
VALUES GIVEN IN STEP 4.
NOTE 2: APPLIED LOADS ARE THE TOTAL LOADS PER STATION (FOR A STATION WITH 2 JACKS, THE LOAD
FOR EACH JACK IS THE APPLIED LOAD DIVIDED BY TWO).
SUPPORT POINTS  MAX. LOAD  (daN)  REMAINING LOADS (daN)
FRONT JACK  12000  FOR INFORMATION  6500  7
LH MAIN JACK  59600  FOR INFORMATION  32200  36
RH MAIN JACK  59600  FOR INFORMATION  32200  36
CORRESPONDING WEIGHT OF THE AIRCRAFT  80200 Kg (INCLUDING ANY BALLAST)
A_SB_530369_6_APXX_04_00
Figure 1, Sheet 4
Jacking of the Aircraft for the Installation of the External Doubler at FR72
DATE : Apr 07/05  SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10  Page : 7
Printed in France © AIRBUS 2008 All rights reserved

### Page 60

A300A300
SERVICE BULLETIN
APPENDIX 1
This Page Intentionally Left Blank
DA TE : Apr 07/05 SERVICE BULLETIN No. : A300-53-0369
REVISION No. : 03 - Sep 01/10 Page : 8
Printed in France © AIRBUS 2008 All rights reserved

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