# 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** M A N DA T

O RY M A N DA T

O RY M A N DA TO RY M A N D A

TO RY **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 A D D I T I O N A L WO R K No additional work is required by this revision for aircraft modified by any previous issue. R E A S O N 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. C H A N G E S 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. F I L I N G I N S T R U C T I O N S 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. H I S T O R Y O F P R E V I O U S R E V I S I O N S No previous revisions. R E V I S I O N S E Q U E N C E 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 M A N DA T

O RY M A N DA T

O RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 53 TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58**  **MODIFICATION No. :** 12795D21987 R E A S O N /D E S C R I PT I O N /O P E RA T I O N A L C O N S E Q U E N C E S 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. **E F**  **F E**  **C T**  **I V**  **I T** **Y** 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 C O N C U R R E N T R E Q U I R E M E N T S None R E F E R E N C E S/ R E P E R C U S S I O N S 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

N A T U R E O F T H E WO R K AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No M A N P OW E R Config. 01 thru Config. 02
**TOTAL MANHOURS 347.00 ELAPSED TIME (HOURS) 127.50**  M A T E R I A L I N F O R M A T I O N AIRCRAFT DATA Config. 01 thru Config. 02 Straps, shims, rivets, pins and collars. A P P E N D I C E S 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** M A N DA T

O RY M A N DA T

O RY M A N DA TO RY M A N DA TO RY **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. P L**  **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. E**  **F F**  **E C** **T I**  **V I**  **T Y**  (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. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  None **C. R E** **A S**  **O N**  (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. D E**  **S C**  **R I**  **P T**  **I O**  **N** 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. C O**  **M P**  **L I**  **A N**  **C E**  (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. A P**  **P R**  **O V**  **A L**  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 A**  **N P**  **O W**  **E R**  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. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  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. E L**  **E C** **T R**  **I C**  **A L**  **L O** **A D**  **D A** 

**T**

**A** Not changed **J. R E**  **F E**  **R E**  **N C**  **E S**  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. P U**  **B L**  **I C**  **A T**  **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  Structural Repair Manual (SRM) : 53-17-12 **L. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** Not applicable

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

REVISION No. : 01 - Jun 26/09 Page : 7 Printed in France © AIRBUS 2008 All rights reserved

# 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 : 8 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**2. M A**  **T E**  **R I**  **A L**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. M**  **A T**  **E R**  **I A**  **L -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  (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. I N**  **D U**  **S T**  **R Y**  **S U**  **P P**  **O R** **T I**  **N F**  **O R**  **M A**  **T I**  **O N**  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 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**C. L I**  **S T**  **O F**  **C O**  **M P**  **O N**  **E N**  **T S**  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. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L**  **S -**  **O P**  **E R**  **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (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. P A**  **R T** **S T** **O B**  **E R**  **E -**  **I D**  **E N**  **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** None **F. T O**  **O L**  **I N**  **G -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  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. S P**  **E C**  **I A**  **L T** **O O**  **L S**  None

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

REVISION No. : 01 - Jun 26/09 Page : 11 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**3. A C**  **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** 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 Printed in France © AIRBUS 2008 All rights reserved

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

# A300-600 **A300-600** 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. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  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 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** 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 1 0 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 Printed in France © AIRBUS 2008 All rights reserved

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

# A300-600 **A300-600** SERVICE BULLETIN

1 0 Remove any excess sealant with Lint-Free Cotton Cloth (Mat. No. 19-003) and Solvent General Purpose (Mat. No. 11-026). **C. T E**  **S T**  (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. C L**  **O S**  **E U**  **P** (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. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  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 Printed in France © AIRBUS 2008 All rights reserved

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

# A300-600 **A300-600** 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

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

# 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

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

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

# A300-600 **A300-600** 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

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

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

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

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

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

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

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

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

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

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

# 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 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** 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 ab ove, 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 Printed in France © AIRBUS 2008 All rights reserved

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

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

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

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

# A300-600 **A300-600** SERVICE BULLETIN APPENDIX 1

This Page Intentionally Left Blank

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 REPORTING SHEET

**TITLE : FUSELAGE - REAR FUSELAGE - REINFORCE BUTT JOINT AT FR58 MODIFICATION No. :**  12795D21987 P l e a s e c o m p l ete t h e a p p ro p r i ate i te m (A o r B ) : A - SB W I L L B E 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 H AS B E E N embodied on aircraft: ............................................................................................................

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

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

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

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

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

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

...................................... Signature:..................... Date: ..................................................... I f o p e rat i o n a l d o c u m e n t at i o n i s affe cte d ( s e e Pa ra g ra p h 1

. K of t h i s S B ) : 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 I m p o rt a n t I n fo r m at i o n : 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. P l e a s e re t u r n t h i s c o m p l ete d s h e et 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.

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

REVISION No. : 01 - Jun 26/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** 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 C o m m e n ts :

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

REVISION No. : 01 - Jun 26/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved