A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

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

ATA SYSTEM : 53

TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58

MODIFICATION No. : 12795D21987

This page transmits Revision No. 01 of Service Bulletin No. A300-53-6146

ADDITIONAL WORK

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

This Revision is issue to :

- update the effectivity and the operators,

- amend the reason paragraph,

- Accomplishment Timescale : sentence and threshold table added.

- introduce minor changes.

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Reason amended.

- EFFECTIVITY

. Operators updated.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity and operators updated.

- REASON

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 1 of 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- Advantages

. 1.C.(3) Second sentence amended.

- COMPLIANCE

- Accomplishment Timescale

. 1.E.(2) Sentence and threshold table added.

- REFERENCES

. 1.J. AMM reference 28-25-00 added.

MATERIAL INFORMATION :

- Material

. 2.A.(1) Address updated.

- Price and Availability

. 2.A.(2) Cost updated.

- GENERAL

- Preparation

. 3.A.(1)(a)2 AMM reference 28-25-00 added.

- CLOSE-UP

. 3.D.(1)(h) AMM reference 28-25-00 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 Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revisions.

REVISION SEQUENCE

ORIGINAL : Dec 03/08

REVISION No. : 01 - Jun 26/09

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

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

ATA SYSTEM : 53

TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58

MODIFICATION No. : 12795D21987

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

As a result of a Wide Spread Fatigue Damage (WFD) calculation on A300-600 aircraft, it was found that a

modification of the upper fuselage circumferential joint at FR58 is required to enable the aircraft to reach the

Extended Service Goal (ESG).

This Service Bulletin details the work necessary to reinforce the circumferential joint, by installation of an

additional external doubler at the butt joint at FR58, between STGR13 LH and STGR13 RH. The butt joint

doubler is extended by 4 rivet rows beyond the lap joint at FR58, STGR13, LH/RH.

Accomplishment of this Service Bulletin reinforces the circumferential joint at FR58 and extends the Design

Service goal.

Accomplishment of this Service Bulletin also cancels the Airworthiness Limitations Items (ALI) document

tasks 53.16.04-01-1 and 53.16.22-01-1.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No

AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No

KIT PRICE (USD) See SB ZERO STRESS JACKING Yes

MODIFICATION CLASSIFICATION

MAJOR 12795D21987

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) :

AAL AAW ABD AHK AMU BKV CES CSN DLH F2I FDX G8E GXY IRA JAL KAC KAL LAA MNB MON

MSR MXU OHY QTR SUD TAR THA UPS UZB

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

Config. 01 thru Config. 02

TOTAL MANHOURS 347.00

ELAPSED TIME (HOURS) 127.50

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01 thru Config. 02

Straps, shims, rivets, pins and collars.

APPENDICES

Appendix 1 - Jacking Instructions

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

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

ATA SYSTEM : 53

TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58

MODIFICATION No. : 12795D21987

This document contains AIRBUS PROPRIETARY INFORMATION 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 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. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/F C4-620 F4-605R F4-622R

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358

0361 0365 0368 0380 0384 0388 0395 0398 0401 0405 0408 0411 0414 0417 0423

0459-0466 0469-0471 0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0533

0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582

0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659

0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694

0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750

0752-0764 0766-0775 0777-0794 0797 0799-0841 0845-0878

(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

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 1 of 40

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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.

OPERATOR MSN

AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 0508

0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612

0615 0619 0626 0639 0643 0645 0675

AAW 0354

ABD 0529 0557 0755

AHK 0855 0856 0857 0858 0859 0860 0870 0871

AMU 0677 0743

BKV 0411 0414 0546 0553 0608

CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763

CSN 0733 0734 0739 0750 0756 0762

DLH 0380 0405 0408 0618 0623 0701 0773

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0341 0348 0351

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559

0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664

0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745

0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774

0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799

0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878

G8E 0462 0465

GXY 0872

IRA 0632 0696 0723 0727

JAL 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 0729

0730 0737 0740 0753 0770 0783 0797 0836 0837 0838

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692 0731

LAA 0601 0616

MNB 0758

MON 0540 0556 0604 0605

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

OPERATOR MSN

MSR 0561 0607

MXU 0767 0788

OHY 0584 0603 0744 0747 0749 0764

QTR 0554 0560 0614

SUD 0252 0666 0775

TAR 0505 0558 0563

THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 0705

0782 0784 0785 0786 0787

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816

0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0839 0840 0841 0845 0846

0847 0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864

0865 0866 0867 0868 0869

UZB 0717 0722

(c) Effectivity by MSN and Kit/Configuration

The Kits and configurations applicable to these MSNs are given at the end of this list

0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358

0361 0365 0368 0380 0384 0388 0395 0398 0401 0405 0408 0411 0414 0417

KIT No. QTY PER A/C CONFIGURATION

536146D01R00 1 01

The Kits and configurations applicable to these MSNs are given at the end of this list

0423 0459-0466 0469-0471 0474 0477 0479 0505-0518 0521 0525 0529-0530

0532-0533 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579

0581-0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645

0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688

0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719

0721-0750 0752-0764 0766-0775 0777-0794 0797 0799-0841 0845-0878

KIT No. QTY PER A/C CONFIGURATION

536146D02R00 1 02

NOTE : Config. 01 is valid for aircraft without Mod. No. 006133D05214

(FUSELAGE - STRUCTURE - REINFORCE STRUCTURE TO MAKE

PROVISIONS FOR INCREASE DESIGN WEIGHTS) embodied in

production.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

NOTE : Config. 02 is valid for aircraft with Mod. No. 006133D05214 (FUSELAGE

- STRUCTURE - REINFORCE STRUCTURE TO MAKE PROVISIONS

FOR INCREASE DESIGN WEIGHTS) embodied in production.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

As a result of a Wide Spread Fatigue Damage (WFD) calculation on A300-600 aircraft, it

was found that a modification of the upper fuselage circumferential joint at FR58 is required

to enable the aircraft to reach the Extended Service Goal (ESG).

(2) Objective/Action

This Service Bulletin details the work necessary to reinforce the circumferential joint, by

installation of an additional external doubler at the butt joint at FR58, between STGR13

LH and STGR13 RH. The butt joint doubler is extended by 4 rivet rows beyond the lap

joint at FR58, STGR13, LH/RH.

(3) Advantages

Accomplishment of this Service Bulletin reinforces the circumferential joint at FR58 and

extends the Design Service goal.

Accomplishment of this Service Bulletin also cancels the Airworthiness Limitations Items

(ALI) document tasks 53.16.04-01-1 and 53.16.22-01-1.

(4) Operational/Maintenance Consequences

This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first

aircraft delivery configuration and modified by the reported incorporation of AIRBUS

SBs). Prior to Service Bulletin embodiment, the operator is reminded to pay specific

attention to structural damage which may exist and to repairs which were performed on

the aircraft because they may be affected by the Service Bulletin. Operators must verify

that all allowable damage limits and repairs performed (both in accordance with the SRM

and outside of the SRM) are still applicable and effective to the new Service Bulletin

configuration. There may be additional or modified maintenance requirements, such as

temporary limits or additional inspections, that apply with respect to the Service Bulletin

configuration. AIRBUS disclaims any liability for the effect which the Service Bulletin may

have on repairs performed on the aircraft before embodiment of the Service Bulletin.

If the post Service Bulletin repair status is no more covered by the SRM and for repairs

outside of the SRM covered by a RAS issued by AIRBUS, the operator should contact

AIRBUS Customer Services Repair Engineering Support (SER1). Repair review will be

done by AIRBUS at conditions of the Customer Services Catalogue.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Install the external doubler at FR58, between STGR13 LH and STGR13 RH.

(2) Config. 02

(a) Install the external doubler at FR58, between STGR13 LH and STGR13 RH.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

It is mandatory to accomplish this Service Bulletin before a threshold of 42500 FC.

For aircraft that are at or above the threshold, this Service Bulletin should be accomplished

within 2000 FC.

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue

of an Airworthiness Directive (AD) published by the European Aviation Safety Agency

(EASA). It is anticipated that the AD will confirm the thresholds given above but reference

should be made to the AD for confirmation of the mandated accomplishment timescale.

In order to avoid the further inspections before reaching the Limit of Validity (LOV) after

the accomplishment of this Service Bulletin, we recommend to accomplish this Service

Bulletin after the following thresholds (see Threshold Table) :

Threshold Table

Model : Recommended threshold :

A300B4-601

A300B4-603

A300B4-605R

A300B4-620

A300B4-622R

A300B4-622

36800 FC

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 5

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

A300C4-605R Variant F

A300C4-620

A300F4-605R Pre Mod12699

28300 FC

A300F4-605R Post Mod12699

A300F4-622R

15800 FC

This table is valid for the actual LOV at the issue date of revision 01 of this Service Bulletin

In case of earlier accomplishment of this Service Bulletin before the above recommended

thresholds are reached, operator has to contact AIRBUS to define an additional appropriate

inspection program.

F. APPROVAL

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. MANPOWER

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 operator’s circumstances. The estimates do not include the

time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying

times for paints, sealants, etc, and general administration work are also not included.

Config. 01 thru Config. 02

Get access 5.50

Lift the aircraft 7.00

Remove the fasteners 45.0

Transfer drill fastener holes 18.0

Clean and treat surfaces 3.5

Install the doubler 250.00

Lower the aircraft 10.50

Test 0.5

Close up 7.00

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 6

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

TOTAL MANHOURS 347.00

ELAPSED TIME (HOURS) 127.50

H. WEIGHT AND BALANCE

Config. 01 thru Config. 02

Manufacturers Empty Weight : +21.80 kg (+48.069 lb)

Effect on Balance : +812.05 kgm (+5871.690 lb.ft)

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-41-53 07-11-00 24-00-00 24-41-00

25-22-11 25-23-11 25-24-11 25-24-21

28-25-00

Elec. Std. Practices Manual (ESPM) : 20-55-00

Structural Repair Manual (SRM) : 51-40-30 51-40-44 51-40-47 51-40-50

51-51-00 51-71-70

Consumable Material List (CML)

Standards Manual (SM)

Appendix 1

K. PUBLICATIONS AFFECTED

Structural Repair Manual (SRM) : 53-17-12

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 8

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A300-600 A300-600

SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - 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 536146D01R00

Cost : 5670 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 economic conditions

at the issue date of the Service Bulletin.

Kit 536146D02R00

Cost : 5670 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 economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will participate to the cost of accomplishment of this Service Bulletin by providing a

20% reduction to the applicable sales prices given in paragraph 2.A.(2) for orders placed before

31 December 2019.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 9

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A300-600 A300-600

SERVICE BULLETIN

C. LIST OF COMPONENTS

Kit 536146D01R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

1 A5397986322000 2 SHIM

2 A5397986322600 2 SHIM

3 A5397986020600 2 STRAP

4 A5397986322200 2 SHIM

5 A5397986020400 1 STRAP

6 DAN6-6-3 739 PIN

7 NSA5075-6 814 COLLAR

8 DAN6-6-5X 518 PIN

9 DAN11-6X 1060 COLLAR

10 DAN6-6-7X 224 PIN

11 DAN6-6-6X 200 PIN

12 DAN6-6-8X 90 PIN

13 DAN6-6-4 18 PIN

14 DAN6-6-6 10 PIN

15 DAN6-6-10X 26 PIN

16 DAN6-6-9X 16 PIN

17 DAN6-6-5 44 PIN

18 MBBN4477-4010 17 RIVET

19 MBBN4477-4011 7 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 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 536146D02R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

1 A5397986322000 2 SHIM

2 A5397986322600 2 SHIM

3 A5397986020600 2 STRAP

4 A5397986322200 2 SHIM

5 A5397986020400 1 STRAP

6 DAN6-6-3 739 PIN

7 NSA5075-6 814 COLLAR

8 DAN6-6-5X 508 PIN

9 DAN11-6X 1060 COLLAR

10 DAN6-6-7X 224 PIN

11 DAN6-6-6X 196 PIN

12 DAN6-6-8X 105 PIN

13 DAN6-6-4 18 PIN

14 DAN6-6-6 10 PIN

15 DAN6-6-10X 29 PIN

16 DAN6-6-9X 14 PIN

17 DAN6-6-5 44 PIN

18 MBBN4477-4010 17 RIVET

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 10

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

19 MBBN4477-4011 7 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 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. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP

MAT No.

Sealant Mat. No. 09-013 As required

Solvent General Purpose Mat. No. 11-026 As required

Alodine Mat. No. 13-002 As required

Anti-Corrosion Primer

(Polyurethane)

Mat. No. 16-001 As required

Polyurethane Top Coat Grey (For

Internal Applic.)

Mat. No. 16-002 As required

External Top Coat (Polyurethane) Mat. No. 16-018 As required

Wash Primer Mat. No. 16-020 As required

Lint-Free Cotton Cloth Mat. No. 19-003 As required

(2) Components

To accomplish this Service Bulletin it is necessary to use the repair washers listed in

SRM 51-71-70.

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

To accomplish this Service Bulletin it is necessary to use the jacking tools listed in the SRM

51-51-00. For details refer to Appendix 1.

G. SPECIAL TOOLS

None

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

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A300-600 A300-600

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 12

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A300-600 A300-600

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY

SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, 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

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

(1) Preparation

(a) Config. 01 thru Config. 02

1 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00,

Page block 301).

2 Defuel the system (Refer to AMM 28-25-00, Page block 301).

3 Remove the sidewall Overhead Stowage Compartments (OHSC) as necessary

to get access to the work area (Refer to AMM 25-24-11, Page block 401).

4 Remove the centre OHSC as necessary to get access to the work area (Refer

to AMM 25-24-21, Page block 401).

5 Remove the ceiling panels as necessary to get access to the work area (Refer

to AMM 25-23-11, Page block 401).

6 Remove the air conditioning duct(s) as necessary to get access to the work area.

7 Remove the heat and sound insulation as necessary to get access to the work

area (Refer to AMM 25-22-11, Page block 401).

8 Obey the general jacking instructions (Refer to SRM 51-51-00).

9 Obey the maintenance jacking procedure (Refer to AMM 07-11-00, Page block

001).

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 13

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SERVICE BULLETIN

(2) Standard Practices

(a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers of 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) For material specifications (Mat. No.) given in this Service Bulletin, refer to the

Consumable Material List (CML) .

(c) For location of the access panel (Refer to AMM 06-41-53, Page block 001).

(d) For Frame (FR) identification (Refer to AMM 06-41-53, Page block 001).

(e) For hole and drill data (Refer to SRM 51-40-44). Use transition fit for HiLok

installation.

(f) For information on fastener spacing and edge margin data (Refer to SRM 51-40-50).

(g) For countersinking (Refer to SRM 51-40-47).

(h) Transfer drill the existing holes with a pilot drill and drill bush.

(i) After drilling, remove all the burrs from the holes.

(j) For alternative and substitute fasteners (Refer to SRM 51-40-30).

(k) Clean the surfaces to be sealed with Solvent General Purpose (Mat. No. 11-026)

and a Lint-Free Cotton Cloth (Mat. No. 19-003).

(l) Assemble all structural parts and fasteners with Sealant (Mat. No. 09-013).

(m) Radius all unstated corners of straps and shims to a radius of 10 mm (0.39 in.).

(n) On new parts, if necessary, apply :

- Chromic Acid Anodizing (CAA) or Alodine (Mat. No. 13-002),

- Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001),

- Polyurethane Top Coat Grey (For Internal Applic.) (Mat. No. 16-002),

- External Top Coat (Polyurethane) (Mat. No. 16-018) (in accordance with the

operators livery).

(o) On reworked areas apply :

- Wash Primer (Mat. No. 16-020),

- Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001),

- Polyurethane Top Coat Grey (For Internal Applic.) (Mat. No. 16-002),

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 14

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SERVICE BULLETIN

- External Top Coat (Polyurethane) (Mat. No. 16-018).

(p) To accomplish this Service Bulletin it is necessary to use the repair washers listed in

SRM 51-71-70.

B. MODIFICATION

NOTE : If you find existing doublers (e.g. skin repair) with a distance less than 4 rivet pitches

between the outer rivet rows of the doublers, contact AIRBUS.

(1) Config. 01

Refer to Figure 1

Refer to Kit 536146D01R00

(a) Install the external doubler at FR58, between STGR13 LH and STGR13 RH.

Refer to Figure 1

1 Temporarily put these items in position and mark their outer shape on the

fuselage skin :

2 Shim A5397986322000 Item 1

2 Shim A5397986322600 Item 2

2 Strap A5397986020600 Item 3

2 Shim A5397986322200 Item 4

1 Strap A5397986020400 Item 5

NOTE : Make sure that the edge distance of the fasteners is in accordance

with the SRM 51-40-50.

NOTE : Make sure that the fastener spacing is the same as the existing pitch or

in accordance with the SRM 51-40-50.

2 Identify the fasteners that you must remove in the modification area with a

wax pencil.

3 Remove and discard the identified fasteners.

4 Temporarily put in position on the outer fuselage skin :

2 Shim A5397986322000 Item 1

2 Shim A5397986322600 Item 2

2 Strap A5397986020600 Item 3

2 Shim A5397986322200 Item 4

1 Strap A5397986020400 Item 5

and transfer drill the existing and new fastener holes.

5 Remove the shims, Item 1, the shims, Item 2, the shims, Item 4, the straps, Item

3, and the strap, Item 5, and deburr them.

6 Countersink the straps, Item 3, and the strap, Item 5.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 15

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SERVICE BULLETIN

7 Fill the existing countersinks in the outer fuselage skin with countersink repair

washers (Refer to SRM 51-71-70).

8 Apply a thin layer of Sealant (Mat. No. 09-013) to all the mating surfaces.

9 Put in position on the outer fuselage skin :

2 Shim A5397986322000 Item 1

2 Shim A5397986322600 Item 2

2 Strap A5397986020600 Item 3

2 Shim A5397986322200 Item 4

1 Strap A5397986020400 Item 5

and wet install with Sealant (Mat. No. 09-013) :

739 Pin DAN6-6-3 Item 6

814 Collar NSA5075-6 Item 7

518 Pin DAN6-6-5X Item 8

1060 Collar DAN11-6X Item 9

224 Pin DAN6-6-7X Item 10

200 Pin DAN6-6-6X Item 11

90 Pin DAN6-6-8X Item 12

18 Pin DAN6-6-4 Item 13

10 Pin DAN6-6-6 Item 14

26 Pin DAN6-6-10X Item 15

16 Pin DAN6-6-9X Item 16

44 Collar DAN6-6-5 Item 17

17 Rivet MBBN4477-4010 Item 18

7 Rivet MBBN4477-4011 Item 19

10 Remove any excess sealant with Lint-Free Cotton Cloth (Mat. No. 19-003) and

Solvent General Purpose (Mat. No. 11-026).

(2) Config. 02

Refer to Figure 2

Refer to Kit 536146D02R00

(a) Install the external doubler at FR58, between STGR13 LH and STGR13 RH.

Refer to Figure 2

1 Temporarily put these items in position and mark their outer shape on the

fuselage skin :

2 Shim A5397986322000 Item 1

2 Shim A5397986322600 Item 2

2 Strap A5397986020600 Item 3

2 Shim A5397986322200 Item 4

1 Strap A5397986020400 Item 5

NOTE : Make sure that the edge distance of the fasteners is in accordance

with the SRM 51-40-50.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 16

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SERVICE BULLETIN

NOTE : Make sure that the fastener spacing is the same as the existing pitch or

in accordance with the SRM 51-40-50.

2 Identify the fasteners that you must remove in the modification area with a

wax pencil.

3 Remove and discard the identified fasteners.

4 Temporarily put in position on the outer fuselage skin :

2 Shim A5397986322000 Item 1

2 Shim A5397986322600 Item 2

2 Strap A5397986020600 Item 3

2 Shim A5397986322200 Item 4

1 Strap A5397986020400 Item 5

and transfer drill the existing and new fastener holes.

5 Remove the shims, Item 1, the shims, Item 2, the shims, Item 4, the straps, Item

3, and the strap, Item 5, and deburr them.

6 Countersink the straps, Item 3, and the strap, Item 5.

7 Fill the existing countersinks in the outer fuselage skin with countersink repair

washers (Refer to SRM 51-71-70).

8 Apply a thin layer of Sealant (Mat. No. 09-013) to all the mating surfaces.

9 Put in position on the outer fuselage skin :

2 Shim A5397986322000 Item 1

2 Shim A5397986322600 Item 2

2 Strap A5397986020600 Item 3

2 Shim A5397986322200 Item 4

1 Strap A5397986020400 Item 5

and wet install with Sealant (Mat. No. 09-013) :

739 Pin DAN6-6-3 Item 6

814 Collar NSA5075-6 Item 7

508 Pin DAN6-6-5X Item 8

1060 Collar DAN11-6X Item 9

224 Pin DAN6-6-7X Item 10

196 Pin DAN6-6-6X Item 11

105 Pin DAN6-6-8X Item 12

18 Pin DAN6-6-4 Item 13

10 Pin DAN6-6-6 Item 14

29 Pin DAN6-6-10X Item 15

14 Pin DAN6-6-9X Item 16

44 Collar DAN6-6-5 Item 17

17 Rivet MBBN4477-4010 Item 18

7 Rivet MBBN4477-4011 Item 19

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 17

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A300-600 A300-600

SERVICE BULLETIN

10 Remove any excess sealant with Lint-Free Cotton Cloth (Mat. No. 19-003) and

Solvent General Purpose (Mat. No. 11-026).

C. TEST

(1) Config. 01 thru Config. 02

(a) Do a leak check of the removed air conditioning duct(s).

NOTE : Do this test after installation of the air conditioning duct(s), refer

to paragraph D.

1 Make sure that the aircraft electrical circuits are energized (Refer to AMM

24-41-00, Page block 301).

2 Make sure that the ventilation for electronics rack is correct.

3 On the panel 438VU, push in the CABIN FANS pushbutton switch.

4 Make sure that there are no leaks at the connections of the removed air

conditioning duct(s).

5 On the panel 438VU, release out the CABIN FANS pushbutton switch.

D. CLOSE UP

(1) Config. 01 thru Config. 02

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the removed heat and sound insulation (Refer to AMM 25-22-11, Page

block 401).

(c) Install the removed air conditioning duct(s).

(d) Install the removed ceiling panels (Refer to AMM 25-23-11, Page block 401).

(e) Install the removed sidewall OHSC (Refer to AMM 25-24-11, Page block 401).

(f) Install the removed centre OHSC (Refer to AMM 25-24-21, Page block 401).

(g) Obey the general de-jacking instructions (Refer to SRM 51-51-00).

(h) Refuel the system (Refer to AMM 28-25-00, Page block 301).

E. DOCUMENTATION

Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 18

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SERVICE BULLETIN

Figure 1, Sheet 1

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 19

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SERVICE BULLETIN

Figure 1, Sheet 2

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 20

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

Figure 1, Sheet 3

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 21

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A300-600 A300-600

SERVICE BULLETIN

Figure 1, Sheet 4

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 22

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 1, Sheet 5

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 23

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 1, Sheet 6

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 24

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

Figure 1, Sheet 7

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 25

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SERVICE BULLETIN

Figure 1, Sheet 8

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 26

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SERVICE BULLETIN

Figure 1, Sheet 9

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 27

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

Figure 1, Sheet 10

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 28

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 1, Sheet 11

Config. 01: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 29

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SERVICE BULLETIN

Figure 2, Sheet 1

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 30

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SERVICE BULLETIN

Figure 2, Sheet 2

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 31

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SERVICE BULLETIN

Figure 2, Sheet 3

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 32

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SERVICE BULLETIN

Figure 2, Sheet 4

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 33

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SERVICE BULLETIN

Figure 2, Sheet 5

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 34

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SERVICE BULLETIN

Figure 2, Sheet 6

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 35

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SERVICE BULLETIN

Figure 2, Sheet 7

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 36

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SERVICE BULLETIN

Figure 2, Sheet 8

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 37

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SERVICE BULLETIN

Figure 2, Sheet 9

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 38

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A300-600 A300-600

SERVICE BULLETIN

Figure 2, Sheet 10

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 39

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 2, Sheet 11

Config. 02: Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 40

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SERVICE BULLETIN

APPENDIX 1

AIRBUS

CUSTOMER SERVICES DIRECTORATE

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

ATA SYSTEM : 53

TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58

MODIFICATION No. : 12795D21987

1. Jacking procedure for the installation of the external doubler on the fuselage skin at FR58, between

STGR13 LH and STGR13 RH.

A. AIRCRAFT CONFIGURATION

- This jacking procedure is only applicable to the configuration below:

The aircraft without :

. Fuel (except undrainable fuel)

. Payload

. Water (potable)

. 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 above, contact

AIRBUS.

NOTE : If you do other tasks on the aircraft at the same time, contact AIRBUS.

B. JACKING PROCEDURE

(1) Obey the general jacking instructions (Refer to SRM 51-51-00)

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 1

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SERVICE BULLETIN

APPENDIX 1

(2) In addition to above mentioned SRM procedure, obey all safety precautions mentioned in

AMM 07-11-00, Page block 001 prior to any action on the aircraft.

(3) Lift the aircraft on jacks at points A, B1 and B2 as shown in Figure 1, Sheet 2 (Refer to

AMM 07-11-00, Page block 001).

(4) Install the additional jacking equipment at FR17, FR59, FR76 and FR85.

Refer to Figure 1, Sheet 2

CAUTION : MAKE SURE THAT THE LOADS NEVER EXCEED THE MAXIMUM PERMITTED

LOADS SPECIFIED IN FIGURE 1, SHEET 3.

(5) Gradually apply the loads shown in step 1, to the jacks at FR17, FR59, FR76 and FR85.

Refer to Figure 1, Sheet 3.

(6) Wait until the loads on the jacks become stable and make sure that they are within a

tolerance of +/- 10 percent.

(7) 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.

C. CLOSE-UP

(1) Gradually decrease the loads one step after the other (Refer to Figure 1, Sheet 3 for steps

definition) from step 4 to zero on the jacks at FR17, FR59, FR76 and FR85.

(2) Remove safety stay at point C as shown in Figure 1, Sheet 2, (Refer to AMM 07-11-00,

Page block 001).

NOTE : Keep the removed safety stay far away from the aircraft.

(3) Remove the jacking equipments at FR17, FR59 and FR76 (Refer to AMM 07-11-00,

Page block 001).

NOTE : Keep the removed jacking equipment far away from the aircraft.

(4) For lowering the aircraft from maintenance jacks at points A, B1 and B2 as shown in Figure

1, Sheet 2, refer to AMM 07-11-00, Page block 001.

(5) For close up refer to AMM 07-11-00, Page block 001.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 2

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SERVICE BULLETIN

APPENDIX 1

Figure 1, Sheet 1

Jacking of the Aircraft for the Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 3

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SERVICE BULLETIN

APPENDIX 1

Figure 1, Sheet 2

Jacking of the Aircraft for the Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 4

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SERVICE BULLETIN

APPENDIX 1

Figure 1, Sheet 3

Jacking of the Aircraft for the Installation of the External Doubler at FR58

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

REVISION No. : 01 - Jun 26/09 Page : 5

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SERVICE BULLETIN

APPENDIX 1

This Page Intentionally Left Blank

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

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REPORTING SHEET

TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58

MODIFICATION No. : 12795D21987

Please complete the appropriate item (A or B):

A - SB WILL BE embodied .................................................................. YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

.............................................................................................................................................................................

.............................................................................................................................................................................

B - SB HAS BEEN embodied on aircraft: ............................................................................................................

.............................................................................................................................................................................

.............................................................................................................................................................................

Operator comments:............................................................................................................................................

.............................................................................................................................................................................

.............................................................................................................................................................................

From Airline: ........................................................................................................................................................

Name/Title: ..........................................................................................................................................................

Signature:..................... Date: .....................................................

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next

normal revision or prior to SB embodiment, please indicate required service(s):

Either : Advance data................................................................................... YES/NO

Or : Intermediate/Temporary revision ..................................................... YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational documentation

if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible

revision, this will result in

- updating of maintenance documentation to show pre and post SB data.

- updating of maintenance and operational documentation to show post SB data

after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include

them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SEDCC1 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

Or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

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SERVICE BULLETIN

REPORTING QUALITY

TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58

MODIFICATION No. : 12795D21987

Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that you

provide us will be used to analyse areas of difficulties and to take corrective action to futher improve the quality

of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

-Quality rating of this SB 4 3 2 1

-Quality rating of the Accomplishment Instructions 4 3 2 1

-Quality rating of the Illustrations 4 3 2 1

-Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short

description of the issue.

Planning Material Instructions

X Effectivity X Kit Content X Preparation

X Reason X List of Materials X Mod/Inspection

X Manpower Operator Supplied X Test

X References X Re-identification X Close-up

X Publication X Tooling X Illustrations

Comments :

Operator : Date:

Name/Title :

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Dec 03/08 SERVICE BULLETIN No. : A300-53-6146

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