# Airbus Service Bulletin A300-53-0373

Copy: Revision 03 ("SB A300-53-0373_Rev3"), 68 pages: PDF https://openairdocs.org/files/sha256/9a/e0/9ae0a94a372c340b40dc8aa3d44909cb3afb8bcf79097434a36071a4f194962f; text https://openairdocs.org/service-documents/airbus/a300-53-0373/file/9ae0a94a372c.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: A300-53-0373
- Latest revision known: A300-53-0373, Revision 03, dated September 1, 2010 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-53-0373

## 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/a300-53-0373/proposed.md).

## Text (68 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 FR65
MODIFICA TION No. : 12796D21988
This page transmits Revision No. 03 of Service Bulletin No. A300-53-0373
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. 04,
- update the effectivity,
- introduce minor changes.
CHANGES
SUMMARY :
- REASON/DESCRIPTION/OPERA TIONAL CONSEQUENCES
. NOTE amended, AIRBUS department deleted.
- MANPOWER
. Config. 01 thru Config. 03 added.
- MA TERIAL INFORMA TION
. Config. 01 thru Config. 03 added.
PLANNING INFORMA TION :
- EFFECTIVITY
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 1 of 4
Printed in France © AIRBUS 2008 All rights reserved

### Page 2

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
. 1.A. Effectivity updated and Config. 01 thru Config. 04 added. Effectivity by MSN : NOTES
amended, AIRBUS department deleted. Effectivity by MSN and Kit/Configuration : NOTE for
config. 04 amended, AIRBUS department deleted.
- DESCRIPTION
. 1.D. Config. 01 thru 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 thru Config. 03 added.
- WEIGHT AND BALANCE
. 1.H. Config. 01 thru Config. 03 added.
MA TERIAL INFORMA TION :
- 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. NOTE amended, AIRBUS department deleted.
. 3.B.(2) Config. 02 added. NOTE amended, AIRBUS department deleted.
. 3.B.(3) Config. 03 added. NOTE amended, AIRBUS department deleted.
- CLOSE-UP
. 3.D.(1) Config. 01 thru Config. 03 added.
- Figure 1
. Config. 01 added.
- Figure 2
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 2
Printed in France © AIRBUS 2008 All rights reserved

### Page 3

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
. Config. 02 added.
- Figure 3
. Config. 03 added.
- Figure 4
. Config. 01 thru 03 added.
APPENDIX 1 :
- Figure 1
. Figure updated.
- 1. Config. 01 thru Config. 03 added.
. 1.A. Part numbers updated.
. 1.C.(2) Sentence updated.
. 1.C.(3) Sentence updated and NOTE added.
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.
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 .
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 3
Printed in France © AIRBUS 2008 All rights reserved

### Page 4

A300A300
SERVICE BULLETIN
REVISION TRANSMITT AL SHEET
REVISION SEQUENCE
ORIGINAL : May 30/05
REVISION No. : 01 - Dec 04/06
REVISION No. : 02 - Nov 19/07
REVISION No. : 03 - Sep 01/10
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 4
Printed in France © AIRBUS 2008 All rights reserved

### 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 FR65
MODIFICA TION No. : 12796D21988
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
As a result of an additional Wide Spread Fatigue Damage (WFD) calculation on aircraft A300B2/B4/C4, it
was found that certain areas of the upper fuselage circumferential joint may not reach the design service
goal without reinforcement of the joint.
This Service Bulletin details the procedure to reinforce the butt joint at FR65 by installation of an additional
external doubler without cutout at the butt joint of FR65 between STGR 13LH and STGR 13RH. The butt joint
doubler is to be extended by 3 rivet rows beyond the lap joint at STGR 13 LH/RH.
This Service Bulletin has been issued to describe the modification requirements associated to Airworthiness
Limitation Item (ALI) task reference 536703.
NOTE : This Service Bulletin cancels the inspection given by the Service Bulletin No. A300-53-0261
(FUSELAGE - INSPECT THE INNER RIVET ROWS ON EACH SIDE OF CENTER REGION OF
THE CIRCUMFERENTIAL JOINT CROSS BUTT STRAP A T FRAME 65 BETWEEN STGR12,
LH AND RH, AND CROWN CENTERLINE).
The accomplishment of this Service Bulletin will reinforce this circumferential joint and consequently extend
the service life up to the Limit Of Validity (LOV). It will avoid unscheduled repairs later in the life of aircraft,
provided it is accomplished within the recommended time scale.
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
embodiment giving all the repair or modification details to get specific solutions.
EVALUATION T ABLE
COMPLIANCE Mandatory CANCELS INSPECTION SB Ye s
AD Ye s A/C OPERA TION AFFECTED No
RELIABILITY AFFECTED No P AX COMFORT AFFECTED No
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 1 of 4
Printed in France © AIRBUS 2008 All rights reserved

### Page 6

A300A300
SERVICE BULLETIN
SUMMARY
EVALUATION T ABLE
COST SAVING No ETOPS AFFECTED No
STRUCTURAL LIFE EXTN Ye s VENDOR SB INVOL VED No
ZERO STRESS JACKING Ye s
KIT PRICE (USD) D01 8430 KIT PRICE (USD) D02 8140
KIT PRICE (USD) D03 8380
MODIFICA TION CLASSIFICA TION
MAJOR 12796D21988
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
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 2
Printed in France © AIRBUS 2008 All rights reserved

### Page 7

A300A300
SERVICE BULLETIN
SUMMARY
NATURE OF THE WORK
AIRCRAFT : YES
EQUIPMENT : NO
HARD : NO
SOFT : NO
OBRM : NO
MANPOWER
Config. 01
TOT AL MANHOURS 328.00
ELAPSED TIME (HOURS) 162.00
Config. 02
TOT AL MANHOURS 326.00
ELAPSED TIME (HOURS) 161.00
Config. 03
TOT AL MANHOURS 328.00
ELAPSED TIME (HOURS) 162.00
MATERIAL INFORMATION
AIRCRAFT DA T A
Config. 01
Straps, angles, shims, pins, collars and rivets.
Config. 02
Straps, angles, shims, pins, collars and rivets.
Config. 03
Straps, angles, shims, pins, collars and rivets.
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 3
Printed in France © AIRBUS 2008 All rights reserved

### Page 8 (OCR)

© A300
SERVICE BULLETIN
SUMMARY
APPENDICES
Appendix 1 - Jacking Instructions
2250
B
REINFORCEMENT
STRAP
FR65
AIRCRAFT
CENTERLINE
REINFORCEMENT
STRAP
REINFORCEMENT
AB6 53 0373 AAMA-A  STRAP
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
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 FR65
MODIFICA TION No. : 12796D21988
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
NOTE : For MSN 0003 a specific solution is required, please contact AIRBUS
for further instructions.
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
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 1 of 50
Printed in France © AIRBUS 2008 All rights reserved

### Page 10

A300A300
SERVICE BULLETIN
Bulletin embodiment giving all the repair or modification details to get
specific solutions.
(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.
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
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 2
Printed in France © AIRBUS 2008 All rights reserved

### Page 11

A300A300
SERVICE BULLETIN
OPERA TOR MSN
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
0003
KIT No. QTY PER A/C CONFIGURA TION
None 04
The Kits and configurations applicable to these MSNs are given at the end of this list
0019 0041 0044-0045 0047
KIT No. QTY PER A/C CONFIGURA TION
530373D01R00 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
530373D02R00 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
530373D03R00 1 03
NOTE : Config. 01 is valid for aircraft on which the Mod. No. 001610D00916
(TO IMPROVE FR72 JOINTS) and Mod. No. 2611D02031 (FUSELAGE
STRUCTURE - IMPROVE THE FA TIGUE LIFE OF LONGITUDINAL
LAP JOINTS OF OUTER SKIN) has not been embodied in the
production line.
NOTE : Config. 02 is valid for aircraft, which have the Mod. No. 001610D00916
(TO IMPROVE FR72 JOINTS) embodied but the Mod. No. 2611D02031
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 3
Printed in France © AIRBUS 2008 All rights reserved

### Page 12

A300A300
SERVICE BULLETIN
(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
(TO IMPROVE FR72 JOINTS) and Mod. No. 2611D02031 (FUSELAGE
STRUCTURE - IMPROVE THE FA TIGUE LIFE OF LONGITUDINAL LAP
JOINTS OF OUTER SKIN) have been embodied in the production line.
NOTE : Config. 04 is valid for aircraft MSN 0003 only . A specific solution is
required, please contact AIRBUS for further instructions.
(3) Spares
None
B. C ONCURRENT REQUIREMENTS
None
C. R EASON
(1) History
As a result of an additional Wide Spread Fatigue Damage (WFD) calculation on aircraft
A300B2/B4/C4, it was found that certain areas of the upper fuselage circumferential joint
may not reach the design service goal without reinforcement of the joint.
(2) Objective/Action
This Service Bulletin details the procedure to reinforce the butt joint at FR65 by installation
of an additional external doubler without cutout at the butt joint of FR65 between STGR
13LH and STGR 13RH. The butt joint doubler is to be extended by 3 rivet rows beyond
the lap joint at STGR 13 LH/RH.
This Service Bulletin has been issued to describe the modification requirements associated
to Airworthiness Limitation Item (ALI) task reference 536703.
NOTE : This Service Bulletin cancels the inspection given by the Service Bulletin
No. A300-53-0261 (FUSELAGE - INSPECT THE INNER RIVET ROWS ON
EACH SIDE OF CENTER REGION OF THE CIRCUMFERENTIAL JOINT
CROSS BUTT STRAP A T FRAME 65 BETWEEN STGR12, LH AND RH, AND
CROWN CENTERLINE).
(3) Advantages
The accomplishment of this Service Bulletin will reinforce this circumferential joint and
consequently extend the service life up to the Limit Of Validity (LOV). It will avoid
unscheduled repairs later in the life of aircraft, provided it is accomplished within the
recommended time scale.
(4) Operational/Maintenance Consequences
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 4
Printed in France © AIRBUS 2008 All rights reserved

### Page 13

A300A300
SERVICE BULLETIN
None
D. D ESCRIPTION
T o accomplish this Service Bulletin it is necessary to :
(1) Config. 01
(a) Remove the AFT fairing of the ADF-Sense-Antenna.
(b) Remove the angles for the fairing of the ADF-Sense-Antenna.
(c) Reinforce the butt joint at FR65 between STGR13 LH and STGR13 RH.
(d) Install the angles for the fairing of the ADF-Sense-Antenna.
(e) Install the AFT fairing of the ADF-Sense-Antenna.
(2) Config. 02
(a) Remove the AFT fairing of the ADF-Sense-Antenna.
(b) Remove the angles for the fairing of the ADF-Sense-Antenna.
(c) Reinforce the butt joint at FR65 between STGR13 LH and STGR13 RH.
(d) Install the angles for the fairing of the ADF-Sense-Antenna.
(e) Install the AFT fairing of the ADF-Sense-Antenna.
(3) Config. 03
(a) Remove the AFT fairing of the ADF-Sense-Antenna.
(b) Remove the angles for the fairing of the ADF-Sense-Antenna.
(c) Reinforce the butt joint at FR65 between STGR13 LH and STGR13 RH.
(d) Install the angles for the fairing of the ADF-Sense-Antenna.
(e) Install the AFT fairing of the ADF-Sense-Antenna.
E. C OMPLIANCE
(1) Classification
Mandatory
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin is rendered mandatory at a threshold of :
- 42500 FC (for Aircraft Model A300B2)
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 5
Printed in France © AIRBUS 2008 All rights reserved

### Page 14

A300A300
SERVICE BULLETIN
- 41700 FC (for Aircraft Model A300B4-100)
- 48000 FC (for Aircraft Models A300B4-200, A300C4 and A300F4)
The aircraft that have accumulated more than :
- 42500 FC (for Aircraft Model A300B2)
- 41700 FC (for Aircraft Model A300B4-100)
- 48000 FC (for Aircraft Models A300B4-200, A300C4 and A300F4)
must be modified within 2000 FC after receipt of this Service Bulletin.
This Service Bulletin is associated to Airworthiness Limitation Item (ALI) tasks mandated
by Airworthiness Directive (AD) 2009-0155, published by the European Aviation Safety
Agency (EASA).
Refer to the associated ALI tasks 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 5.00
Modification 314.00
Close-up 9.00
TOT AL MANHOURS 328.00
ELAPSED TIME (HOURS) 162.00
Config. 02
Get Access 5.00
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 6
Printed in France © AIRBUS 2008 All rights reserved

### Page 15

A300A300
SERVICE BULLETIN
Modification 312.00
Close-up 9.00
TOT AL MANHOURS 326.00
ELAPSED TIME (HOURS) 161.00
Config. 03
Get Access 5.00
Modification 314.00
Close-up 9.00
TOT AL MANHOURS 328.00
ELAPSED TIME (HOURS) 162.00
H. W EIGHT AND BALANCE
Config. 01
Manufacturers Empty Weight : +8.088 kg (+17.834 lb)
Effect on Balance : +344.209 kgm (+2488.873 lb.ft)
Config. 02
Manufacturers Empty Weight : +8.097 kg (+17.854 lb)
Effect on Balance : +344.592 kgm (+2491.642 lb.ft)
Config. 03
Manufacturers Empty Weight : +8.040 kg (+17.728 lb)
Effect on Balance : +342.166 kgm (+2474.102 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
25-24-11 25-24-12 53-57-11
Elec. Std. Practices Manual (ESPM) : 20-55-00
Structural Repair Manual (SRM) : 51-30-31 51-30-40 51-30-43 51-30-45
51-30-50 51-41-50 51-51-00 53-10-20
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REVISION No. : 03 - Sep 01/10 Page : 7
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### Page 16

A300A300
SERVICE BULLETIN
Consumable Material List (CML)
Standards Manual (SM)
Process and Material Specification (PMS) 01-07-17
Appendix 1
K. P UBLICATIONS AFFECTED
Structure Repair Manual (SRM) : 53-17-00
L. I NTERCHANGEABILITY/MIXABILITY
Not applicable
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REVISION No. : 03 - Sep 01/10 Page : 8
Printed in France © AIRBUS 2008 All rights reserved

### 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 530373D01R00
Cost : 8430 US dollars
Availability : 90 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 530373D02R00
Cost : 8140 US dollars
Availability : 90 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 530373D03R00
Cost : 8380 US dollars
Availability : 90 calendar days from receipt of order
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 9
Printed in France © AIRBUS 2008 All rights reserved

### Page 18

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
As a special policy applied to this Service Bulletin, Airbus will provide a 35% reduction to the
applicable sales prices given in the paragraph ’Price and Availability’ for orders placed before
31 December 2018.
C. L IST OF COMPONENTS
Kit 530373D01R00
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
1 A5397986320000 2 EA SHIM
2 A5397985820200 2 EA STRAP
3 A5397985820000 1 EA STRAP
4 A5397986420000 1 EA ANGLE (4) A5397363020000
5 A5397986420100 1 EA ANGLE (5) A5397363020100
7 DAN6-6-3 684 EA PIN
8 DAN6-6-4 48 EA PIN
9 DAN6-6-5 12 EA PIN
10 NSA5075-6 744 EA COLLAR
11 DAN6-6-5X 529 EA PIN
12 DAN6-6-6X 285 EA PIN
13 DAN6-6-7X 162 EA PIN
14 DAN6-6-8X 32 EA PIN
16 DAN11-6X 1008 EA COLLAR
17 MBBN4477-4008 32 EA RIVET
18 DIN65399-4807CF 4 EA RIVET
NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you cannot identify in the LIST OF
COMPONENTS of this Service Bulletin. The SM will give you the correct part number
to part number relationship.
Kit 530373D02R00
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
1 A5397986320000 2 EA SHIM
2 A5397985820200 2 EA STRAP
3 A5397985820000 1 EA STRAP
4 A5397986420000 1 EA ANGLE (4) A5397363020000
5 A5397986420100 1 EA ANGLE (5) A5397363020100
7 DAN6-6-3 684 EA PIN
8 DAN6-6-4 48 EA PIN
9 DAN6-6-5 8 EA PIN
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ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
10 NSA5075-6 740 EA COLLAR
11 DAN6-6-5X 563 EA PIN
12 DAN6-6-6X 329 EA PIN
13 DAN6-6-7X 92 EA PIN
14 DAN6-6-8X 16 EA PIN
15 DAN6-6-9X 12 EA PIN
16 DAN11-6X 1012 EA COLLAR
17 MBBN4477-4008 32 EA RIVET
18 DIN65399-4807CF 4 EA RIVET
NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you cannot identify in the LIST OF
COMPONENTS of this Service Bulletin. The SM will give you the correct part number
to part number relationship.
Kit 530373D03R00
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART No. INT INST DISP
1 A5397986320600 2 EA SHIM
2 A5397985820200 2 EA STRAP
3 A5397985820000 1 EA STRAP
4 A5397986420000 1 EA ANGLE (4) A5397363020000
5 A5397986420100 1 EA ANGLE (5) A5397363020100
6 A5397986320200 2 EA SHIM
7 DAN6-6-3 684 EA PIN
8 DAN6-6-4 16 EA PIN
9 DAN6-6-5 72 EA PIN
10 NSA5075-6 772 EA COLLAR
11 DAN6-6-5X 461 EA PIN
12 DAN6-6-6X 295 EA PIN
13 DAN6-6-7X 148 EA PIN
14 DAN6-6-8X 16 EA PIN
15 DAN6-6-9X 56 EA PIN
16 DAN11-6X 992 EA COLLAR
17 MBBN4477-4008 36 EA RIVET
18 DIN65399-4807CF 4 EA RIVET
19 A5397986320400 2 EA SHIM
NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you cannot 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.
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Sealant Mat. No. 09-013 As required
Cleaning agent Mat. No. 11-026 As required
Alodine Mat. No. 13-002 As required
Polyurethane primer Mat. No. 16-001 As required
Polyurethane topcoat intern Mat. No. 16-002 As required
Polyurethane topcoat extern 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
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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 the center overhead stowage-compartment for access as necessary ,
refer to AMM 25-24-12, Page block 401.
6 Remove and retain the lower sidewall panels as necessary , refer to AMM
25-23-31, Page block 401.
7 Remove and retain the upper sidewall panels as necessary , refer to AMM
25-23-21, Page block 401.
8 Remove the heat and sound insulation as necessary , refer to AMM 25-22-11,
Page block 401.
9 Open, safety and tag this the circuit breaker(s) :
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- For circuit breakers, refer to AMM 53-57-11, Page block 401.
10 Do the jacking procedure, refer to Appendix 1.
(2) Standard Practices
(a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the
hardware components in the related kit(s) which you cannot identify in the LIST OF
COMPONENTS of this Service Bulletin. The SM will give you the correct part
number to part number relationship.
(b) Refer to the Consumable Material List (CML) for specification of materials you must
use in this Service Bulletin.
(c) Do electrical bonding in accordance with the Process and Material Specification
(PMS) 01-07-17.
(d) For stripping/paint removal in the reinforced area (Refer to SRM 51-41-50, Page
block 701).
(e) For fasteners hole and drill data (Refer to SRM 51-30-40).
NOTE : T ransition fit is to be used for Hi-Lok installation.
(f) For alternative and substitute fasteners (Refer to SRM 51-30-31).
(g) For fastener spacing and margin data (Refer to SRM 51-30-50).
NOTE : Use existing pitch where necessary .
(h) T ransfer drill the existing holes with a pilot drill and drill bush.
(i) For countersinking information (Refer to SRM 51-30-43).
(j) Fill the existing countersinks with countersunk repair washers (Refer to SRM
51-30-45, Page block 701).
(k) After drilling, remove all the burrs from the holes.
(l) Cut the solid rivets to the correct length, as necessary .
(m) Clean the surfaces to be sealed with cleaning agent (Mat. No. 11-026).
(n) Wet install all fasteners and countersink-washers with sealant (Mat. No. 09-013).
(o) On new parts, if necessary , apply :
- Chromic Acid Anodizing (CAA) or alodine (Mat. No. 13-002),
- primer (Mat. No. 16-001),
- topcoat (Mat. No. 16-018) for external application (in accordance with the
operators livery),
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- topcoat, grey (Mat. No. 16-002) for internal application.
(p) On reworked areas, apply :
- wash primer (Mat. No. 16-020),
- primer (Mat. No. 16-001),
- topcoat, grey (Mat. No. 16-002) for internal application.
- topcoat (Mat. No. 16-018) for external application (in accordance with the
operators livery),
(q) Before installation of structural items, apply sealant (Mat. No. 09-013) on all
mating surfaces.
(r) Chamfer all unstated corners on straps, shims and angles to 5.0mm x 5.0mm
(0.20in. x 0.20in.).
(s) For all not mentioned general requirements (Refer to SRM butt-joint repairs, in
accordance with SRM 53-10-20).
B. M ODIFICATION
(1) Config. 01
Refer to Kit 530373D01R00
Refer to Figure 1
Refer to Figure 4
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.
NOTE : If you find existing doubler(s) (e.g. skin repairs) with a distance less than 4
rivet-pitches between the outer rivet-rows of the doublers, contact AIRBUS.
(a) Remove the AFT fairing of the ADF-Sense-Antenna.
Refer to AMM 53-57-11, Page block 401
Refer to Figure 4
1 Remove the AFT fairing from the fuselage between FR64 and FR66 on top
centerline, refer to Sheet 2, Detail B :
1 fairing A5397012000200 Item (30) Retain
4 screw Item (31) Retain
6 washer Item (32) Retain
2 clip nut Item (33) Retain
2 screw Item (34) Retain
(b) Remove the angles for the fairing of the ADF-Sense-Antenna.
Refer to Figure 1
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1 Identify the fasteners to be removed in the modification area at FR65 between
STGR1 LH/RH and STGR2 LH/RH with a pencil.
2 Remove and discard the identified fasteners.
3 Remove, refer to Sheet 6, Detail G :
1 angle A5397363020000 Item (4) Discard
1 angle A5397363020100 Item (5) Discard
(c) Reinforce the butt joint at FR65 between STGR13 LH and STGR13 RH.
Refer to Figure 1
1 Put these items in position and mark their contour on the aircraft outer skin :
2 shim A5397986320000 Item 1
2 strap A5397985820200 Item 2
1 strap A5397985820000 Item 3
NOTE : Make sure that the edge-distance of the fasteners is in accordance
with the SRM 51-30-50.
NOTE : Make sure that the fastener spacing is in accordance with the
existing pitch or refer to SRM 51-30-50.
2 Remove and retain the shims, Item 1, the straps, Item 2 and the strap, Item 3.
3 Rework the strap, Item 3 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary, refer to Sheet 2, Detail C and Sheet
3, Detail D.
4 Rework the straps, Item 2 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary , refer to Sheet 3, Detail D, Sheet 4,
Detail E and Sheet 5, Detail F .
5 Rework the shims, Item 1 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary , refer to Sheet 5, Detail F .
6 Identify the fasteners that need to be removed in the modification area at FR65
between STGR13 LH and STGR13 RH with a pencil.
7 Remove and discard the identified fasteners.
8 Put in position :
2 shim A5397986320000 Item 1
2 strap A5397985820200 Item 2
1 strap A5397985820000 Item 3
transfer drill the fastener holes and drill the new fastener holes.
9 Put in position :
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1 angle A5397986420000 Item 4
1 angle A5397986420100 Item 5
transfer drill the fastener holes and drill the new fastener holes, refer to Sheet
2, Detail C and Sheet 6, Detail G.
10 Remove all temporarily attached items and deburr them.
11 Countersink the shims, Item 1, the straps, Item 2, the strap, Item 3 and the
angles, Item 4 and 5.
12 Apply wash primer (Mat. No. 16-020), primer (Mat. No. 16-001) and topcoat,
grey (Mat. No. 16-002)to the remaining countersinks.
13 Fill the existing countersinks with countersunk repair washers, refer to SRM
51-30-45, Page block 701.
14 Apply a thin layer of sealant (Mat. No. 09-013) to the mating surface of the shims,
Item 1, the straps, Item 2, the strap, Item 3 and the angles, Item 4 and Item 5.
15 Put the shims, Item 1, the straps, Item 2 and the strap, Item 3 in the correct
installation position and install with :
684 pin DAN6-6-3 Item 7
48 pin DAN6-6-4 Item 8
12 pin DAN6-6-5 Item 9
744 collar NSA5075-6 Item 10
529 pin DAN6-6-5X Item 11
281 pin DAN6-6-6X Item 12
158 pin DAN6-6-7X Item 13
32 pin DAN6-6-8X Item 14
1000 collar DAN11-6X Item 16
32 rivet MBBN4477-4008 Item 17
4 rivet DIN65399-4807CF Item 18
NOTE : For fastener identification, refer to Figure 1, Sheet 7.
(d) Install the angles for the fairing of the ADF-Sense-Antenna.
Refer to Figure 1
Refer to Figure 4
1 Put the angles, Item 4 and Item 5 in the correct installation position at FR65
between STGR1 LH/RH and STGR2 LH/RH, refer to Figure 1, Sheet 2, Detail C
and Sheet 6, Detail G and install with :
4 pin DAN6-6-6X Item 12
4 pin DAN6-6-7X Item 13
8 collar DAN11-6X Item 16
NOTE : For fastener identification, refer to Figure 1, Sheet 7.
2 Drill the holes in the angles, Item 4 and Item 5 for attachment of the fairing, Item
(30) at FR65, refer to Figure 4, Sheet 2, Detail B :
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a T emporarily install the AFT fairing of the ADF-Sense-Antenna, refer to
Figure 4, Sheet 2, Detail B :
1 fairing A5397012000200 Item (30) Retained
with (FWD attachments only) :
2 screw Item (31) Retained
2 washer Item (32) Retained
b Carefully push down the AFT end of the fairing for the ADF-Sense-Antenna.
c T ransfer drill the holes of the fairing at FR65 to the angles, Item 4 and Item 5.
d Open the holes in the angles, Item 4 and Item 5 to a diameter of 7.30mm
(0.287in.).
e Remove the fairing with the screws and the washers.
f Deburr the drilled holes.
g Apply wash primer (Mat. No. 16-020), primer (Mat. No. 16-001)and topcoat,
grey (Mat. No. 16-002)to the new holes of the angles.
(e) Install the AFT fairing of the ADF-Sense-Antenna.
Refer to AMM 53-57-11, Page block 401
1 Install the AFT fairing of the ADF-Sense-Antenna, refer to Figure 4, Sheet 2,
Detail B :
1 fairing A5397012000200 Item (30) Retained
with :
4 screw Item (31) Retained
6 washer Item (32) Retained
2 clip nut Item (33) Retained
2 screw Item (34) Retained
(2) Config. 02
Refer to Kit 530373D02R00
Refer to Figure 2
Refer to Figure 4
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.
NOTE : If you find existing doubler(s) (e.g. skin repairs) with a distance less than 4
rivet-pitches between the outer rivet-rows of the doublers, contact AIRBUS.
(a) Remove the AFT fairing of the ADF-Sense-Antenna.
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Refer to AMM 53-57-11, Page block 401
Refer to Figure 4
1 Remove the AFT fairing from the fuselage between FR64 and FR66 on top
centerline, refer to Sheet 2, Detail B :
1 fairing A5397012000200 Item (30) Retain
4 screw Item (31) Retain
6 washer Item (32) Retain
2 clip nut Item (33) Retain
2 screw Item (34) Retain
(b) Remove the angles for the fairing of the ADF-Sense-Antenna.
Refer to Figure 2
1 Identify the fasteners to be removed in the modification area at FR65 between
STGR1 LH/RH and STGR2 LH/RH with a pencil.
2 Remove and discard the identified fasteners.
3 Remove, refer to Sheet 6, Detail G :
1 angle A5397363020000 Item (4) Discard
1 angle A5397363020100 Item (5) Discard
(c) Reinforce the butt joint at FR65 between STGR13 LH and STGR13 RH.
Refer to Figure 2
1 Put these items in position and mark their contour on the aircraft outer skin :
2 shim A5397986320000 Item 1
2 strap A5397985820200 Item 2
1 strap A5397985820000 Item 3
NOTE : Make sure that the edge-distance of the fasteners is in accordance
with the SRM 51-30-50.
NOTE : Make sure that the fastener spacing is in accordance with the
existing pitch or refer to SRM 51-30-50.
2 Remove and retain the shims, Item 1, the straps, Item 2 and the strap, Item 3.
3 Rework the strap, Item 3 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary, refer to Sheet 2, Detail C and Sheet
3, Detail D.
4 Rework the straps, Item 2 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary , refer to Sheet 3, Detail D, Sheet 4,
Detail E and Sheet 5, Detail F .
5 Rework the shims, Item 1 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary , refer to Sheet 5, Detail F .
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6 Identify the fasteners that need to be removed in the modification area at FR65
between STGR13 LH and STGR13 RH with a pencil.
7 Remove and discard the identified fasteners.
8 Put in position :
2 shim A5397986320000 Item 1
2 strap A5397985820200 Item 2
1 strap A5397985820000 Item 3
transfer drill the fastener holes and drill the new fastener holes.
9 Put in position :
1 angle A5397986420000 Item 4
1 angle A5397986420100 Item 5
transfer drill the fastener holes and drill the new fastener holes, refer to Sheet
2, Detail C and Sheet 6, Detail G.
10 Remove all temporarily attached items and deburr them.
11 Countersink the shims, Item 1, the straps, Item 2, the strap, Item 3 and the
angles, Item 4 and 5.
12 Apply wash primer (Mat. No. 16-020), primer (Mat. No. 16-001) and topcoat,
grey (Mat. No. 16-002)to the remaining countersinks.
13 Fill the existing countersinks with countersunk repair washers, refer to SRM
51-30-45, Page block 701.
14 Apply a thin layer of sealant (Mat. No. 09-013) to the mating surface of the shims,
Item 1, the straps, Item 2, the strap, Item 3 and the angles, Item 4 and Item 5.
15 Put the shims, Item 1, the straps, Item 2 and the strap, Item 3 in the correct
installation position and install with :
684 pin DAN6-6-3 Item 7
48 pin DAN6-6-4 Item 8
8 pin DAN6-6-5 Item 9
740 collar NSA5075-6 Item 10
559 pin DAN6-6-5X Item 11
329 pin DAN6-6-6X Item 12
88 pin DAN6-6-7X Item 13
16 pin DAN6-6-8X Item 14
12 pin DAN6-6-9X Item 15
1004 collar DAN11-6X Item 16
32 rivet MBBN4477-4008 Item 17
4 rivet DIN65399-4807CF Item 18
NOTE : For fastener identification, refer to Figure 2, Sheet 7.
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(d) Install the angles for the fairing of the ADF-Sense-Antenna.
Refer to Figure 2
Refer to Figure 4
1 Put the angles, Item 4 and Item 5 in the correct installation position at FR65
between STGR1 LH/RH and STGR2 LH/RH, refer to Figure 2, Sheet 2, Detail C
and Sheet 6, Detail G and install with :
4 pin DAN6-6-5X Item 11
4 pin DAN6-6-7X Item 13
8 collar DAN11-6X Item 16
NOTE : For fastener identification, refer to Figure 2, Sheet 7.
2 Drill the holes in the angles, Item 4 and Item 5 for attachment of the fairing, Item
(30) at FR65, refer to Figure 4, Sheet 2, Detail B :
a T emporarily install the AFT fairing of the ADF-Sense-Antenna, refer to
Figure 4, Sheet 2, Detail B :
1 fairing A5397012000200 Item (30) Retained
with (FWD attachments only) :
2 screw NSA5022-3-3 Item (31) Retained
2 washer NAS1169DD10L Item (32) Retained
b Carefully push down the AFT end of the fairing for the ADF-Sense-Antenna.
c T ransfer drill the holes of the fairing at FR65 to the angles, Item 4 and Item 5.
d Open the holes in the angles, Item 4 and Item 5 to a diameter of 7.30mm
(0.287in.).
e Remove the fairing with the screws and the washers.
f Deburr the drilled holes.
g Apply wash primer (Mat. No. 16-020), primer (Mat. No. 16-001) and
topcoat, grey (Mat. No. 16-002)to the new holes of the angles.
(e) Install the AFT fairing of the ADF-Sense-Antenna.
Refer to AMM 53-57-11, Page block 401
1 Install the AFT fairing of the ADF-Sense-Antenna, refer to Figure 4, Sheet 2,
Detail B :
1 fairing A5397012000200 Item (30) Retained
with :
4 screw Item (31) Retained
6 washer Item (32) Retained
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2 clip nut Item (33) Retained
2 screw Item (34) Retained
(3) Config. 03
Refer to Kit 530373D03R00
Refer to Figure 3
Refer to Figure 4
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.
NOTE : If you find existing doubler(s) (e.g. skin repairs) with a distance less than 4
rivet-pitches between the outer rivet-rows of the doublers, contact AIRBUS.
(a) Remove the AFT fairing of the ADF-Sense-Antenna.
Refer to AMM 53-57-11, Page block 401
Refer to Figure 4
1 Remove the AFT fairing from the fuselage between FR64 and FR66 on top
centerline, refer to Sheet 2, Detail B :
1 fairing A5397012000200 Item (30) Retain
4 screw Item (31) Retain
6 washer Item (32) Retain
2 clip nut Item (33) Retain
2 screw Item (34) Retain
(b) Remove the angles for the fairing of the ADF-Sense-Antenna.
Refer to Figure 3
1 Identify the fasteners to be removed in the modification area at FR65 between
STGR1 LH/RH and STGR2 LH/RH with a pencil.
2 Remove and discard the identified fasteners.
3 Remove, refer to Sheet 6, Detail G :
1 angle A5397363020000 Item (4) Discard
1 angle A5397363020100 Item (5) Discard
(c) Reinforce the butt joint at FR65 between STGR13 LH and STGR13 RH.
Refer to Figure 3
1 Put these items in position and mark their contour on the aircraft outer skin :
2 shim A5397986320600 Item 1
2 strap A5397985820200 Item 2
1 strap A5397985820000 Item 3
2 shim A5397986320200 Item 6
2 shim A5397986320400 Item 19
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SERVICE BULLETIN
NOTE : Make sure that the edge-distance of the fasteners is in accordance
with the SRM 51-30-50.
NOTE : Make sure that the fastener spacing is in accordance with the
existing pitch or refer to SRM 51-30-50.
2 Remove and retain the shims, Item 1, the straps, Item 2, the strap, Item 3, the
shims, Item 6 and the shims, Item 19.
3 Rework the strap, Item 3 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary, refer to Sheet 2, Detail C and Sheet
3, Detail D.
4 Rework the straps, Item 2 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary , refer to Sheet 3, Detail D, Sheet 4,
Detail E and Sheet 5, Detail F .
5 Rework the shims, Item 1 and Item 19 (outer dimension in relation to fasteners
edge-distance and fastener spacing, radii), as necessary , refer to Sheet 5,
Detail F .
6 Rework the shims, Item 6 (outer dimension in relation to fasteners edge-distance
and fastener spacing, radii), as necessary , refer to Sheet 3, Detail D.
7 Identify the fasteners that need to be removed in the modification area at FR65
between STGR13 LH and STGR13 RH with a pencil.
8 Remove and discard the identified fasteners.
9 Put in position :
2 shim A5397986320600 Item 1
2 strap A5397985820200 Item 2
1 strap A5397985820000 Item 3
2 shim A5397986320200 Item 6
2 shim A5397986320400 Item 19
transfer drill the fastener holes and drill the new fastener holes.
10 Put in position :
1 angle A5397986420000 Item 4
1 angle A5397986420100 Item 5
transfer drill the fastener holes and drill the new fastener holes, refer to Sheet
2, Detail C and Sheet 6, Detail G.
11 Remove all temporarily attached items and deburr them.
12 Countersink the strap, Item 3, the straps, Item 2, the shims, Item 1, the shims,
Item 6, the shims, Item 19 and the angles, Item 4 and 5.
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 23
Printed in France © AIRBUS 2008 All rights reserved

### Page 32

A300A300
SERVICE BULLETIN
13 Apply wash primer (Mat. No. 16-020), primer (Mat. No. 16-001) and topcoat,
grey (Mat. No. 16-002)to the remaining countersinks.
14 Fill the existing countersinks with countersunk repair washers, refer to SRM
51-30-45, Page block 701.
15 Apply a thin layer of sealant (Mat. No. 09-013) to the mating surface of the
shims, Item 1, the straps, Item 2, the strap, Item 3, the angles, Item 4 and 5, the
shims, Item 6 and the shims, Item 19.
16 Put the shims, Item 1, the straps, Item 2, the strap, Item 3, the shims, Item 6 and
the shims, Item 19 in the correct installation position and install with :
684 pin DAN6-6-3 Item 7
16 pin DAN6-6-4 Item 8
72 pin DAN6-6-5 Item 9
772 collar NSA5075-6 Item 10
461 pin DAN6-6-5X Item 11
291 pin DAN6-6-6X Item 12
144 pin DAN6-6-7X Item 13
16 pin DAN6-6-8X Item 14
56 pin DAN6-6-9X Item 15
984 collar DAN11-6X Item 16
36 rivet MBBN4477-4008 Item 17
4 rivet DIN65399-4807CF Item 18
NOTE : For fastener identification, refer to Figure 3, Sheet 7.
(d) Install the angles for the fairing of the ADF-Sense-Antenna.
Refer to Figure 3
Refer to Figure 4
1 Put the angles, Item 4 and 5 in the correct installation position at FR65 between
STGR1 LH/RH and STGR2 LH/RH, refer to Figure 3, Sheet 2, Detail C and
Sheet 6, Detail G and install with :
4 pin DAN6-6-6X Item 12
4 pin DAN6-6-7X Item 13
8 collar DAN11-6X Item 16
NOTE : For fastener identification, refer to Figure 3, Sheet 7.
2 Drill the holes in the angles, Item 4 and 5 for fixing the fairing, Item (30) at FR65,
refer to Figure 4, Sheet 2, Detail B :
a T emporarily install the AFT fairing of the ADF-Sense-Antenna, refer to
Figure 4, Sheet 2, Detail B :
1 fairing A5397012000200 Item (30) Retained
with (FWD attachments only) :
2 screw NSA5022-3-3 Item (31) Retained
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 24
Printed in France © AIRBUS 2008 All rights reserved

### Page 33

A300A300
SERVICE BULLETIN
2 washer NAS1169DD10L Item (32) Retained
b Carefully push down the AFT end of the fairing for the ADF-Sense-Antenna.
c T ransfer drill the holes of the fairing at FR65 to the angles, Item 4 and Item 5.
d Open the holes in the angles, Item 4 and Item 5 to a diameter of 7.30mm
(0.287in.).
e Remove the fairing with the screws and the washers.
f Deburr the drilled holes.
g Apply wash primer (Mat. No. 16-020), primer (Mat. No. 16-001) and
topcoat, grey (Mat. No. 16-002)to the new holes of the angles.
(e) Install the AFT fairing of the ADF-Sense-Antenna.
Refer to AMM 53-57-11, Page block 401
1 Install the AFT fairing of the ADF-Sense-Antenna, refer to Figure 4, Sheet 2,
Detail B :
1 fairing A5397012000200 Item (30) Retained
with these items
4 screw Item (31) Retained
6 washer Item (32) Retained
2 clip nut Item (33) Retained
2 screw Item (34) Retained
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 sidewall overhead stowage-compartments LH and RH, refer to AMM
25-24-11, Page block 401.
(d) Install the retained upper sidewall panels, refer to AMM 25-23-21, Page block 401.
(e) Install the center overhead stowage-compartment refer to AMM 25-24-12, Page
block 401
(f) Install the retained lower sidewall panels, refer to AMM 25-23-31, Page block 401.
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 25
Printed in France © AIRBUS 2008 All rights reserved

### Page 34

A300A300
SERVICE BULLETIN
(g) Install the retained heat and sound insulation, refer to AMM 25-22-11, Page block
401.
(h) Install the retained overhead stowage compartments LH and RH, refer to AMM
25-24-11, Page block 401.
(i) Remove the access platform(s).
(j) Remove the safety clip(s) and tag(s) and close the circuit breaker(s) :
- For circuit breakers, refer to AMM 53-57-11, Page block 401.
(k) 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 : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 26
Printed in France © AIRBUS 2008 All rights reserved

### Page 35 (OCR)

© A300
SERVICE BULLETIN
2250
B
• FR66
FR65
FR54
STGR7 STGR4
F
FR65
STGR4
AIRCRAFT  CENTERLINE  \ D  STGR7
E  STGR 10
STGR13
AB6 53 0373 ACMA-A
Figure 1, Sheet 1
Config. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 27
Printed in France © AIRBUS 2008 All rights reserved

### Page 36 (OCR)

© A300
SERVICE BULLETIN
RH SYMMETRICAL  LH SHOWN  - WD  AIRCRAFT CENTERLINE
APPLICABLE TO
A/C MSN 0005-0052
STGR1
(4)4 (LH)
(5)5 (RH)
3
AB6 53 0373 ACMB-A  STGR4
Figure 1, Sheet 2
Contig. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 28
Printed in France © AIRBUS 2008 All rights reserved

### Page 37 (OCR)

© A300
SERVICE BULLETIN
RH SYMMETRICAL  LH SHOWN  FWD
APPLICABLE TO
A/C MSN 0005-0052
STGR4
2
AB6 53 0373 ACMC-A  STGRY
Figure 1, Sheet 3
Config. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 29
Printed in France © AIRBUS 2008 All rights reserved

### Page 38 (OCR)

© A300
SERVICE BULLETIN
E  RH SYMMETRICAL  LH SHOWN  - WD
APPLICABLE TO
A/C MSN 0005-0052
STGRZ
2
AB6 53 0373 ACMD-A  STGR10
Figure 1, Sheet 4
Config. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 30
Printed in France © AIRBUS 2008 All rights reserved

### Page 39 (OCR)

© A300
SERVICE BULLETIN
STGR 10
LH SHOWN
RH SYMMETRICAL  FWD
APPLICABLE TO
A/C MSN 0005-0052
STGR13
AB6 53 0373 ACME-A
Figure 1, Sheet 5
Config. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 31
Printed in France © AIRBUS 2008 All rights reserved

### Page 40 (OCR)

© A300
SERVICE BULLETIN
GI  LH SHOWI
CH SYMMETRICA
APPLICABLE TO
A/C MSN 0005-0052
Oe  (5) RH SYMMETRICAL
5
(4) LH SHOWN  4
STGR1
STGR2
AB6 53 0373 ACMF-A  NOTE:
BONDING APPLICABLE TO A/C MSN 0029-0052.
FOR FASTENER AND COLLAR IDENTIFICATION,
REFER TO SHEET 2 AND SHEET 7.
Figure 1, Sheet 6
Config. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 32
Printed in France © AIRBUS 2008 All rights reserved

### Page 41 (OCR)

A300
SERVICE BULLETIN
REMARKS  NOMINAL SIZE  TRANSITION FIT  NOMINAL SIZE  TRANSITION FIT  TRANSITISN FIT  TRANSITION  1st OVERSIZE  TRANSITION FIT  1st OVERSIZE  TRANSITION FIT  1st OVERSIZE  TRANSITION FIT  NOMINAL SIZE  NOMINAL SIZE
FINAL HOLE DIAMETER  MAX  (0. 190 im.)  (o. 180 in.)  (0. 180 )  (0.205 in.)  (0.205 n.›  co.205 9.)  5.15mm  (0.203 in.)  co. 167Tn)  (0. 195 9n.)
MIN  78mm  (0.188in.)  78mm  (0.188in.)  4.78mm  (0.188 in.)  5.11mm  (0.201 in.)  (0.201fn.>  11mm  5.11mm  (0.201in.)  4.06mm  (0.160 in.)  4.85mm  (0.191 in.)
KIT  DO1  DO1  DO1  DO1  DO1  DO1  DO1  DO1  DO1
DESCRIPTION  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  RIVET  RIVET
P/N  DAN6-6-3  NSA5075-6  DAN6-6-4  NSA5075-6  DAN6-6-5  NSA5075-6  DAN6-6-6X  DAN11-6X  DAN6-6-7X  DAN11-6X  MBBN4477-4008
~  00
HOLE  SYMBOL  •
Figure 1, Sheet 7
Config. 01: Install the External Doubler at FR65 (Kit D01)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 33
Printed in France © AIRBUS 2008 All rights reserved

### Page 42 (OCR)

© A300
SERVICE BULLETIN
2250
B
• FR66
FR65
FR54
STGR7 STGR4
F
FR65
STGR4
AIRCRAFT  CENTERLINE  \ D  STGR7
E  STGR 10
STGR13
AB6 53 0373 AEMA-A
Figure 2, Sheet 1
Config. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 34
Printed in France © AIRBUS 2008 All rights reserved

### Page 43 (OCR)

© A300
SERVICE BULLETIN
RH SYMMETRICAL  LH SHOWN  - WD  AIRCRAFT CENTERLINE
APPLICABLE TO
A/C MSN 0053-0156
STGR1
(4)4 (LH)
(5)5 (RH)
3
AB6 53 0373 AEMB-A  STGR4
Figure 2, Sheet 2
Contig. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 35
Printed in France © AIRBUS 2008 All rights reserved

### Page 44 (OCR)

© A300
SERVICE BULLETIN
RH SYMMETRICAL  LH SHOWN  FWD
APPLICABLE TO
A/C MSN 0053-0156
STGR4
2
AB6 53 0373 AEMC-A  STGRY
Figure 2, Sheet 3
Contig. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 36
Printed in France © AIRBUS 2008 All rights reserved

### Page 45 (OCR)

© A300
SERVICE BULLETIN
E  RH SYMMETRICAL  LH SHOWN  - WD
APPLICABLE TO
A/C MSN 0053-0156
STGR7
2
AB6 53 0373 AEMD-A  STGR10
Figure 2, Sheet 4
Config. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 37
Printed in France © AIRBUS 2008 All rights reserved

### Page 46 (OCR)

© A300
SERVICE BULLETIN
STGR 10
LH SHOWN
RH SYMMETRICAL  FWD
APPLICABLE TO
A/C MSN 0053-0156
STGR13
AB6 53 0373 AEME-A
Figure 2, Sheet 5
Config. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 38
Printed in France © AIRBUS 2008 All rights reserved

### Page 47 (OCR)

© A300
SERVICE BULLETIN
G  LA SHOWI  RH SYMMETRICA
APPLICABLE TO
A/C MSN 0053-0156
e  (5) RH SYMMETRICAL
(4) LH SHOWN
STGR1
STGR2
AB6 53 0373 AEMF-A  NOTE:
FOR FASTENER AND COLLAR IDENTIFICATION,
REFER TO SHEET 2 AND SHEET 7.
Figure 2, Sheet 6
Config. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 39
Printed in France © AIRBUS 2008 All rights reserved

### Page 48 (OCR)

A300
SERVICE BULLETIN
TRANSITION FIT  TRANSITION FIT  TRANSITISN FIT  A SERENEIT  TRANSITION FIT  TRANSITION FIT  FIT  TRANSITION FIT
REMARKS  NOMINAL SIZE  NOMINAL SIZE  TRANSITION  OVERSIZE  1st  1st OVERSIZE  1s+ OVFRSI7F  TRANSITION  OVERSIZE  1st  NOMINAL SIZE  NOMINAL SIZE
FINAL HOLE DIAMETER  MAX  (0. 190 im.)  (o. 180 in.)  (0. 180 )  (0.205 in.)  (0.205%n.)  5.15mm  (0.203 in.)  5.15mm  (0.203 in.)  (0.205 n>  4.17mm  (0.164 in.)  4.95mm  (0.195 in.)
MIN  ramm  (0.188in.)  78mm  (0.188in.)  4.78mm  (0.188 in.)  5.11mm  (0.201 in.)  (0.201fn.>  11mm  5.11mm  (0.201in.)  11mm  (0.201in.)  - 11mm  (0.201 in.)  4.06mm  (0.160 in.)  . 85mm  (0.191 in.)
KIT  DOZ  D02  D02  DOZ  DOZ  D02  DO2  DOZ  D02  DOZ
DESCRIPTION  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  RIVET  RIVET
P/N  DAN6-6-3  NSA5075-6  DAN6-6-4  NSA5075-6  DAN6-6-5  NSA5075-6  DAN6-6-5X  DAN11-6X  DAN6-6-6X  DAN11-6X  DAN6-6-7X  DAN11-6X  DAN6-6-9X  DAN11-6X  MBBN4477-4008  DIN 65399-4807CF
00
HOLE  SYMBOL  •
Figure 2, Sheet 7
Config. 02: Install the External Doubler at FR65 (Kit D02)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 40
Printed in France © AIRBUS 2008 All rights reserved

### Page 49 (OCR)

© A300
SERVICE BULLETIN
2250
B
FR66
FR65
FR54
2  6  STGR7 STGR4
19 F
FR65
C
AIRCRAFT  CENTERLINE  \ D
19
AB6 53 0373 AGMA-A
Figure 3, Sheet 1
Config. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 41
Printed in France © AIRBUS 2008 All rights reserved

### Page 50 (OCR)

© А300
SERVICE BULLETIN
RH SYMMETRICAL  LH SHOWN  - WD  AIRCRAFT CENTERLINE
APPLICABLE TO
A/C MSN 0157-0305
STGR1
(4)4(Lн)
(5)5 (RH)
3
AB6 53 0373 AGMB-A  STGR4
Figure 3, Sheet 2
Contig. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 42
Printed in France © AIRBUS 2008 All rights reserved

### Page 51 (OCR)

© A300
SERVICE BULLETIN
LH SHOWN
RH SYMMETRICAL
APPLICABLE TO
A/C MSN 0157-0305
STGR4
SECTION
A- A
AB6 53 0373 AGMC-A  STGRY  -_#
Figure 3, Sheet 3
Contig. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 43
Printed in France © AIRBUS 2008 All rights reserved

### Page 52 (OCR)

© A300
SERVICE BULLETIN
LH SHOWN  RH SYMMETRICAL  FWD
APPLICABLE TO
A/C MSN 0157-0305
STGRZ
2
AB6 53 0373 AGMD-A  STGR10
Figure 3, Sheet 4
Config. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 44
Printed in France © AIRBUS 2008 All rights reserved

### Page 53 (OCR)

© A300
SERVICE BULLETIN
STGR 10
LH SHOWN
RH SYMMETRICAL  FWD
APPLICABLE TO
A/C MSN 0157-0305
STGR11
SECTION
B- B
STGR 13
STGR12
19
19
STGR13
AB6 53 0373 AGME-A
Figure 3, Sheet 5
Contig. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 45
Printed in France © AIRBUS 2008 All rights reserved

### Page 54 (OCR)

© A300
SERVICE BULLETIN
G  LA SHOWI  CH SYMMETRICA
APPLICABLE TO
A/C MSN 0157-0305
(5) RH SYMMETRICAL
(4) LH SHOWN
STGR1
STGR2
AB6 53 0373 AGMF-A  NOTE:
FOR FASTENER AND COLLAR IDENTIFICATION,
REFER TO SHEET 2 AND SHEET 7.
Figure 3, Sheet 6
Config. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 46
Printed in France © AIRBUS 2008 All rights reserved

### Page 55 (OCR)

© A300
SERVICE BULLETIN
REMARKS  NOMINAL SIZE  TRANSITION  NOMINAL SIZE  TRANSITION  NOMINAL SIZE  TRANSITION  1st OVERSIZE  TRANSITION  1st OVERSIZE  TRANSITION  1st OVERSIZE  TRANSITION  1st OVERSIZE  TRANSITION  1st OVERSIZE  TRANSITION  NOMINAL SIZE  NOMINAL SIZE
FINAL HOLE DIAMETER  MAX  (0. 190 im.)  (o. 180 in.)  (0. 192 .)  (0.205 in.)  (0.205%n.)  5.15mm  (0.203 in.)  5.15mm  (0.203in.)  (0.205 n>  4.17mm  (0.164 in.)  (0. 195 in.)
MIN  ramm  (0.188in.)  78mm  (0.188in.)  4.78mm  (0.188 in.)  5.11mm  (0.201 in.)  (0.201fn.>  11mm  5.11mm  (0.201in.)  11mm  (0.201in.)  - 11mm  (0.201 in.)  4.06mm  (0.160 in.)  . 85mm  (0.191 in.)
KIT  DO3  D03  D03  DO3  DO3  D03  D03  D03  DO3  D03
DESCRIPTION  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  PIN  COLLAR  RIVET  RIVET
P/N  DAN6-6-3  NSA5075-6  DAN6-6-4  NSA5075-6  DAN6-6-5  NSA5075-6  DAN6-6-5X  DAN11-6X  DAN6-6-6X  DAN11-6X  DAN6-6-7X  DAN11-6X  DAN6-6-9X  DAN11-6X  MBBN4477-4008  DIN 65399-4800CF
AB6 53 0373 AGMG-A  ~  00
HOLE  SYMBOL  •
Figure 3, Sheet 7
Config. 03: Install the External Doubler at FR65 (Kit D03)
DATE: May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 47
Printed in France © AIRBUS 2008 All rights reserved

### Page 56 (OCR)

O A300
SERVICE BULLETIN
2250
B
FR65
AB6 53 0373 AJMA-A  FR56
Figure 4, Sheet 1
Config. 01 thru 03: Install the Angles for the Antenna Cover at FR65 (all Kits)
DATE : May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 48
Printed in France © AIRBUS 2008 All rights reserved

### Page 57 (OCR)

© A300
SERVICE BULLETIN
(34) (2 POS)
(30)  (32) (2 POS)
(32) (2 POS)
(31)
(2 POS)
(33)  (2 POS) (31)  (32)  (2 POS)
FR65
AB6 53 0373 AJMA-A  NOTE:
1) DRILL THE HOLE AFTER ASSEMBLY.
Figure 4, Sheet 2
Config. 01 thru 03: Install the Angles for the Antenna Cover at FR65 (all Kits)
DATE : May 30/05  SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10  Page : 49
Printed in France © AIRBUS 2008 All rights reserved

### Page 58

A300A300
SERVICE BULLETIN
This Page Intentionally Left Blank
DA TE : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 50
Printed in France © AIRBUS 2008 All rights reserved

### Page 59

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 FR65
MODIFICA TION No. : 12796D21988
1. Config. 01 thru Config. 03
Jacking procedure for the installation of the external doubler on the fuselage skin at FR65.
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 : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 1
Printed in France © AIRBUS 2008 All rights reserved

### Page 60

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 : May 30/05 SERVICE BULLETIN No. : A300-53-0373
REVISION No. : 03 - Sep 01/10 Page : 2
Printed in France © AIRBUS 2008 All rights reserved

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