# @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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECT REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE. MODIFICATION No.: None This page transmits Revision No.05 of Service Bulletin No.A300-57-6086 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 05 issued to: - add a note concerning the threshold of the inspection - modify the Figure A-FFBAA sheet 01 CHANGES SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL AVAILABILITY UPDATED MATERIAL PRICE UPDATED R
LIST OF COMPONENTS Kit 576086A01R05 PART MATERIAL SET UPDATED QUANTITY UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 576086- 833-802-001-Repair Subtask 576086-833-017-001 SUBTASK SOLUTION UPDATED R Subtask 576086-833-018-001 SUBTASK SOLUTION UPDATED R Subtask 576086-833-019-001 SUBTASK SOLUTION UPDATED R Subtask 576086-833-020-001 SUBTASK SOLUTION UPDATED R Fig. A-FFBAA Fig. A-FFBAA Sheet 01 SHEET UPDATED R FILLING 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 Revision No. 01 issued to update the PNs of the fasteners and add Kit A02. Also, this revision is issued to inform the operators that this Service Bulletin is rendered mandatory by Airworthiness Directive No. 2000-533-328(B). Revision No. 02 issued to delete the Airworthiness Directive (AD) No. the synoptic chart and the effectivity and add a NOTE which specifies that this inspection is no longer necessary if Service Bulletin No. A300-57-6069 is accomplished. Revision No. 03 issued to modify figure 2 sheet 3 : the values in the table must be in accordance with SRM 51-40-00. Revision No. 04 issued to . modify the threshold and interval of the inspection add an Ultra Sonic inspection of the CWB lower panel add an instruction for the installation of removed fasteners in transition fit instead of interference. REVISION SEQUENCE ORIGINAL: Jun 06/00 REVISION No.: 01 - Apr 02/02 DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION No.: 02 - Dec 22/06 REVISION No.: 03 - Sep 24/07 REVISION No. : 04 - Oct 17/11 REVISION No. : 05 - Jan 30/12

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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# @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. 

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECT REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE. **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During accomplishment of Structure Significant Item (SSI) Inspection 571011 and Modification as per the Service Bulletin No. A300-57-6050, cracks have been found on the horizontal flange of the Frame 47 internal corner angle fitting, on three aircraft. At the time of the findings, the aircraft were below the SSI inspection threshold of 18,000 FC. This Service Bulletin calls for a rotating probe inspection of ten holes in the horizontal flange of the Frame 47 internal corner angle fitting and for an Ultra Sonic inspection of the CWB lower panel. In the event of cracks findings, this Service Bulletin defines the repair solution which consists in reaming the affected holes and installing oversize fasteners. If undetected, cracks can increase in magnitude, leading to a reduction of the residual strength of the structure. Thus, accomplishment of this Service Bulletin will avoid extensive structural repairs. Accomplishment of Service Bulletin No. A300-57-6069 cancels the requirement of inspection of holes H and I of the corner angle fitting defined in Service Bulletin No. A300-57-6049 and cancels the requirement of inspection of the rear spar and bottom panel at junction with fuselage defined in this Service Bulletin. This Service Bulletin supersedes Maintenance Planning Document (MPD) task 571011-01-1, SSI task 571011. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN SUMMARY EVALUATION TABLE RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 576086A01R05 1 18,720.00 Bolt, Nut, Washer **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 576086A02R02 1 11,750.00 Bolt, Nut, Washer. EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

34Z 83V AAL ABD AIB AMU BCS CES F2I FDX G8E GBG IRA IRM JAL KAC KAL MNB MON MSR MXU OHY QTR RUN SUD TAR THA URS UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.10.00.003 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN SUMMARY SOFT NO OBRM NO MANPOWER **CONF 001 Task 576086-832-801-001: Inspection TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 28.50 Task 576086-833-802-001: Repair TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Task 576086-832-801-001: Inspection TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 28.50 Task 576086-833-802-001: Repair TOTAL MANHOURS 0.00 APPENDICES **CONF ALL Appendix 01 Appendix 02 Appendix 03

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF ALL

FUEL CENTER TANK

D_SB_576086_5_SAAA_01_00 FR47

RIB1 DATUM REAR SPAR

DATUM RIB1 DATUM REAR SPAR DATUM FR47 FR47



## B **C A**  **A C**  **B**

Figure A-FSAAA - Sheet 01

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 4 5

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# @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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECT REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE. MODIFICATION No.: None 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 **CONF ALL A. EFFECTIVITY (1) Models B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/FC4-620 F4-605R (2) Effectivity by MSN 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0423 0459-0461 0463-0466 0469-0470 0474 0477 0479 0505-0518 0521 0525 0529-0530 0532 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0602-0615 0617-0618 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 0799-0804 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN 34Z 0685 83V 0423 0459 0460 0463 0466 0470 0474 0510 0511 0512 0615 0639 0675 AAL 0517 0612 ABD 0529 0557 AIB 0507 0508 0515 AMU 0677 BCS 0621 0637 0641 0670 0679 0711 0724 0729 0740 CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763 F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0461 0518 0606 0610 0645 0753 0770 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 G8E 0465 0469 0506 0509 0513 0514 0516 GBG 0626 0643 IRA 0632 0696 0723 0727 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 0750 0762 0773 JAL 0602 0617 0683 0703 0730 0737 0783 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0609 0627 0631 0662 0692 0731 MNB 0734 0739 0755 0756 0758 MON 0540 0556 0604 0605 MSR 0561 0607 MXU 0767 0788 0797 OHY 0584 0603 0744 0747 0749 0764 QTR 0554 0560 0614 RUN 0743 SUD 0666 0775 TAR 0505 0558 0563 THA 0464 0566 0569 0577 0628 0629 0635 0681 0705 0782 0784 0785 0786 0787 URS 0733 UZB 0717 0722 (4) Configuration by MSN MSN CONFIGURATION 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0423 0459 0460 0461 0463 0465 0466 0469 0470 0474 0477 0479 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0521 0525 0532 0543 0555 0558 0563 0606 0610 0611 0612 0615 0625 0626 0633 0639 0643 0645 0666 0675 0677 0707 0713 0715 001 002

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# @A300-600 SERVICE BULLETIN
MSN CONFIGURATION 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0505 0518 0529 0530 0536 0540 0546 0553 0554 0556 0557 0559 0560 0561 0566 0569 0572 0575 0577 0579 0581 0582 0584 0602 0603 0604 0605 0607 0608 0609 0613 0614 0617 0618 0621 0623 0627 0628 0629 0630 0631 0632 0635 0637 0641 0657 0659 0662 0664 0668 0670 0673 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0709 0711 0717 0719 0721 002

0722 0723 0724 0725 0726 0727 0728 0729 0730 0731 0732 0733 0734 0735 0736 0737 0738 0739 0740 0741 0742 0743 0744 0745 0746 0747 0748 0749 0750 0752 0753 0754 0755 0756 0757 0758 0759 0760 0761 0762 0763 0764 0766 0767 0768 0769 0770 0771 0772 0773 0774 0775 0777 0778 0779 0780 0781 0782 0783 0784 0785 0786 0787 0788 0789 0790 0791 0792 0793 0794 0797 0799 0800 0801 0802 0803 0804 001

(5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which Service Bulletin No. A300-57-6050 (Mod. No. 10454S20572 : FUSELAGE - CENTER SECTION - IMPROVE ATTACHMENT OF ANGLE FITTINGS AT FRAME 47 (RETROFIT SOLUTION)) is not embodied or on which Mod. No. 10155S20321 : SECTION 21 - IMPROVEMENT OF ATTACHMENTS OF CORNER ANGLE FITTING AT FRAME 47 (SERIAL SOLUTION) is embodied. **CONF 002 Config. 002 is valid for aircraft on which Service Bulletin No. A300-57-6050 (Mod. No. 10454S20572 : FUSELAGE - CENTER SECTION - IMPROVE ATTACHMENT OF ANGLE FITTINGS AT FRAME 47 (RETROFIT SOLUTION)) is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 576086A01R05 1 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 576086A02R02 1 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None

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# @A300-600 SERVICE BULLETIN
C. REASON (1) History During accomplishment of Structure Significant Item (SSI) Inspection 571011 and Modification as per the Service Bulletin No. A300-57-6050, cracks have been found on the horizontal flange of the Frame 47 internal corner angle fitting, on three aircraft. At the time of the findings, the aircraft were below the SSI inspection threshold of 18,000 FC. (2) Objective/Action This Service Bulletin calls for a rotating probe inspection of ten holes in the horizontal flange of the Frame 47 internal corner angle fitting and for an Ultra Sonic inspection of the CWB lower panel. In the event of cracks findings, this Service Bulletin defines the repair solution which consists in reaming the affected holes and installing oversize fasteners. (3) Advantages If undetected, cracks can increase in magnitude, leading to a reduction of the residual strength of the structure. Thus, accomplishment of this Service Bulletin will avoid extensive structural repairs. Accomplishment of Service Bulletin No. A300-57-6069 cancels the requirement of inspection of holes H and I of the corner angle fitting defined in Service Bulletin No. A300-57-6049 and cancels the requirement of inspection of the rear spar and bottom panel at junction with fuselage defined in this Service Bulletin. (4) Operational/Maintenance Consequences This Service Bulletin supersedes Maintenance Planning Document (MPD) task 571011-01-1, SSI task 571011. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 576086-832-801-001: Inspection (1) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box (2) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box (3) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box (4) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box
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# @A300-600 SERVICE BULLETIN (5) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box (6) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box Task 576086-833-802-001: Repair (1) Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box (2) Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box (3) Repair the crack(s) found in the hole T (adjacent to the hole G), at the LH internal angle of the center wing box (4) Repair the crack(s) found in the hole T (adjacent to the hole G), at the RH internal angle of the center wing box **CONF 002 Task 576086-832-801-001: Inspection (1) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box (2) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box (3) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box (4) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box (5) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box (6) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin is to be accomplished at the following thresholds :
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# @A300-600 SERVICE BULLETIN Interval (whichever occurs first) Threshold (whichever occurs first) AFT>1.5 Flight Hour (FH)/Flight Cycle (FC) AFT<1.5 FH/FC FC FH FC FH FC FH 13,400 (1) 34,600 (1) 1,260 2,720 1,360 2,200 Table 1 : Ultrasonic Inspection Threshold and Interval Threshold (whichever occurs first) Interval (whichever occurs first) FC FH FC FH 13,400 (1) 34,600 (1) 6,900 17,700 Table 2 : HFEC Rotating Probe Inspection Threshold and Interval NOTE (1): If Service Bulletin A300-57-6050 is embodied, threshold must be counted from the accomplishment of Service Bulletin A300-57-6050. If Service Bulletin A300-57-6050 is not embodied, threshold must be counted from the Entry Into Service (EIS). AFT : Average Flight Time A grace period of 650 FC or 8 months whichever occurs first from Service Bulletin data dispatch is granted to aircraft which have exceeded the revised thresholds/intervals after receipt of the Service Bulletin. The grace period is valid only for Ultrasonic inspection. For Rototest inspection, current interval and threshold are still applicable. Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. 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.

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# @A300-600 SERVICE BULLETIN
**CONF 001 Task 576086-832-801-001: Inspection Get Access 12.00 On Aircraft Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box 4.00 Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box 4.00 Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box 0.50 Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box 0.50 Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box 2.00 Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box 2.00
Tests 0.50 Close-Up 9.50 TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 28.50 NOTE: For the elapsed time assumption, refer to Appendix 03 . Task 576086-833-802-001: Repair Get Access 12.00 On Aircraft Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box 2.00 Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box 2.00 Repair the crack(s) found in the hole T (adjacent to the hole G), at the LH internal angle of the center wing box 2.00 Repair the crack(s) found in the hole T (adjacent to the hole G), at the RH internal angle of the center wing box 2.00
Tests 0.50 Close-Up 9.50 TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 26.00 NOTE: For the elapsed time assumption, refer to Appendix 02 .

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# @A300-600 SERVICE BULLETIN
**CONF 002 Task 576086-832-801-001: Inspection Get Access 12.00 On Aircraft Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box 4.00 Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box 4.00 Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box 0.50 Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box 0.50 Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box 2.00 Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box 2.00
Tests 0.50 Close-Up 9.50 TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 28.50 NOTE: For the elapsed time assumption, refer to Appendix 03 . Task 576086-833-802-001: Repair On Aircraft TOTAL MANHOURS 0.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-10-00 28-10-00 28-11-00 28-11-29 28-25-00

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# @A300-600 SERVICE BULLETIN Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-10-11 57-10-45 Service Bulletin (SB) A300-57-6050 A300-57-6069 Standards Manual (SM) Structural Repair Manual (SRM) 51-21-00 51-24-00 51-40-21 51-40-30 51-40-44 51-40-47 SRM Chapter 51 **CONF 002 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-10-00 28-10-00 28-11-00 28-11-29 28-25-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-10-11 57-10-45 Service Bulletin (SB) A300-57-6050 A300-57-6069 Standards Manual (SM) Structural Repair Manual (SRM) 51-21-00 51-24-00 51-40-21 51-40-30 51-40-44 51-40-47 SRM Chapter 51 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 57-1011-01-1 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A300-600 SERVICE BULLETIN

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 576086A01R05 Kit 576086A02R02 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 ordering by fax : +49 40 50 76 25 90 For ordering by E-mail : airbus.kit@airbus.com (2) Price and Availability

Kit 576086A01R05 Cost 18,720.00 USD Availability 180 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 Kits 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 576086A02R02 Cost 11,750.00 USD Availability 180 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 Kits 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 11 5

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# @A300-600 SERVICE BULLETIN
C. LIST OF COMPONENTS Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 ASNA2532-9 8 Nut 1 NAS1727-9E 24 Nut 2 ASNA2026T9-40 2 Bolt 2 NSA5356-9-40 4 Bolt 2 NSA5358-9-40 4 Bolt 3 NSA5368PD916B 12 Washer 3 NSA5369PD916B 4 Washer 4 ASNA2026T9-32 2 Bolt 4 NSA5356-9-32 4 Bolt 4 NSA5358-9-32 4 Bolt 5 ASNA2532-8 8 Nut 5 NAS1727-8E 24 Nut 6 NSA5368PD816D 22 Washer 6 NSA5369PD816D 10 Washer 7 ASNA2026T8-32 2 Bolt 7 NSA5356-8-32 4 Bolt 7 NSA5358-8-32 4 Bolt 8 ASNA2026T9-30 2 Bolt 8 NSA5356-9-30 4 Bolt 8 NSA5358-9-30 4 Bolt 9 ASNA2026T8-27 2 Bolt 9 NSA5356-8-27 4 Bolt 9 NSA5358-8-27 4 Bolt 10 NSA5368PD816B 12 Washer 10 NSA5369PD816B 4 Washer 11 ASNA2026T8-36 2 Bolt 11 NSA5356-8-36 4 Bolt 11 NSA5358-8-36 4 Bolt 12 ASNA2026T8-38 2 Bolt 12 NSA5356-8-38 4 Bolt 12 NSA5358-8-38 4 Bolt 13 ASNA2531-8 2 Nut 13 NAS1726-8E 6 Nut 15 ASNA2026T9-42 2 Bolt 15 NSA5356-9-42 4 Bolt 15 NSA5358-9-42 4 Bolt 16 ASNA2532-10 4 Nut 16 NAS1727-10E 12 Nut 17 ASNA2026T10-44 2 Bolt 17 NSA5356-10-44 4 Bolt 17 NSA5358-10-44 4 Bolt 18 ASNA2026T10-47 2 Bolt DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 12 5

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 18 NSA5356-10-47 4 Bolt 18 NSA5358-10-47 4 Bolt 19 ASNA2027T8-26 2 Bolt 19 NSA5357-8-24 4 Bolt 19 NSA5359-8-24 4 Bolt NOTE: 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, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 576086A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 ASNA2532-9 8 Nut 1 NAS1727-9E 8 Nut 2 NSA5358-9-40 2 Bolt 3 NSA5368PD916B 4 Washer 4 NSA5358-9-32 2 Bolt 5 ASNA2532-8 8 Nut 5 NAS1727-8E 8 Nut 6 NSA5368PD816D 8 Washer 7 NSA5358-8-32 2 Bolt 8 NSA5358-9-30 2 Bolt 9 NSA5358-8-27 2 Bolt 10 NSA5368PD816B 4 Washer 11 NSA5358-8-36 2 Bolt 12 NSA5358-8-38 2 Bolt 13 ASNA2531-8 2 Nut 13 NAS1726-8E 2 Nut 15 NSA5358-9-42 2 Bolt 16 ASNA2532-10 4 Nut 16 NAS1727-10E 4 Nut 17 NSA5358-10-44 2 Bolt 18 NSA5358-10-47 2 Bolt 19 NSA5359-8-24 2 Bolt NOTE: 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, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 13 5

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# @A300-600 SERVICE BULLETIN
D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Primer Coating Epoxy Polyamide Chemical 16-006 As required Polyurethane Finish Paint (For External Applic.) 16-018 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability Tools listed in NTM 57-10-11 Part 6 and NTM 57-10-45 Part 4. (2) Tools (1) To accomplish this Service Bulletin it is necessary to use the following tools and equipment : Equipment and materials for check of holes as per NTM 57-10-11 Part 6 and NTM 57-10-45 Part 4. None (3) Special Tools None

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 14 5

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 576086-832-801-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT YOU OBEY ALL THE SAFETY PRECAUTIONS APPLICABLE TO THE ACCESS TO AND THE WORK IN THE FUEL CENTER TANK. 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 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. Task Associated Data **CONF 001 Manpower TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 28.50 **CONF 002 Manpower TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 28.50 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 576086-910-001-001 Manpower Resources Skills NON SPECIFIC DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 15 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Primer Coating Epoxy Polyamide Chemical 16-006 As required Polyurethane Finish Paint (For External Applic.) 16-018 As required
References Consumable Material List (CML) Structural Repair Manual (SRM) 51-21-00 51-24-00 51-40-21 51-40-30 51-40-44 51-40-47 (a) For the specification of the material numbers (Mat. No.), refer to the CML. (b) Clean the surfaces to do an inspection of with Solvent 11-026 As required (c) Renew the protective finish, (Refer to SRM 51-21-00) with Chemical Conversion Coating Yellow Aluminum 13-002 As required
Primer Coating Epoxy Polyamide Chemical 16-006 As required

and Polyurethane Finish Paint (For External Applic.) 16-018 As required
(d) Apply Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 16 5

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# @A300-600 SERVICE BULLETIN to the fasteners, (Refer to SRM 51-24-00). (e) For alternative and substitute fasteners, (Refer to SRM 51-40-30). (f) For the removal and installation of fasteners, (Refer to SRM 51-40-21). (g) For fastener hole diameters and drill and deburr data, (Refer to SRM 51-40-44). (h) Countersink the holes, (Refer to SRM 51-40-47). (i) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent 11-026 As required (2) Subtask 576086-839-001-001 - Administrative (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 576086-910-001-001 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Primer Coating Epoxy Polyamide Chemical 16-006 As required Polyurethane Finish Paint (For External Applic.) 16-018 As required
References Consumable Material List (CML) Structural Repair Manual (SRM) 51-21-00 51-24-00 51-40-21 51-40-30 51-40-44 51-40-47 (a) For the specification of the material numbers (Mat. No.), refer to the CML. DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 17 5

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# @A300-600 SERVICE BULLETIN (b) Clean the surfaces to do an inspection of with Solvent 11-026 As required (c) Renew the protective finish, (Refer to SRM 51-21-00) with Chemical Conversion Coating Yellow Aluminum 13-002 As required
Primer Coating Epoxy Polyamide Chemical 16-006 As required

and Polyurethane Finish Paint (For External Applic.) 16-018 As required
(d) Apply Fuel Tank Sealant Polysulfide 09-001 As required

to the fasteners, (Refer to SRM 51-24-00). (e) For alternative and substitute fasteners, (Refer to SRM 51-40-30). (f) For the removal and installation of fasteners, (Refer to SRM 51-40-21). (g) For fastener hole diameters and drill and deburr data, (Refer to SRM 51-40-44). (h) Countersink the holes, (Refer to SRM 51-40-47). (i) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent 11-026 As required (2) Subtask 576086-839-001-001 - Administrative (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 576086-941-001-001 Manpower Resources Skills NON SPECIFIC DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 18 5

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# @A300-600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00, Page Block 301 24-10-00, Page Block 301 28-10-00, Page Block 301 28-11-29, Page Block 401 28-25-00, Page Block 301 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00 Page Block 301). (b) Put the access platform(s) in position. (c) Defuel the fuel center tank (Refer to AMM 28-25-00 Page Block 301). NOTE: Defuel the fuel center tank only for the HFEC inspection. (d) Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29 Page Block 401 and AMM 06-41-53). (e) Respect the procedure required to work in the fuel center tank (Refer to AMM 28-10-00 Page Block 301). **CONF 002 (1) Subtask 576086-941-001-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00, Page Block 301 24-10-00, Page Block 301 28-10-00, Page Block 301 28-11-29, Page Block 401 28-25-00, Page Block 301 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00 Page Block 301). (b) Put the access platform(s) in position. (c) Defuel the fuel center tank (Refer to AMM 28-25-00 Page Block 301). NOTE: Defuel the fuel center tank only for the HFEC inspection. (d) Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29 Page Block 401 and AMM 06-41-53). (e) Respect the procedure required to work in the fuel center tank (Refer to AMM 28-10-00 Page Block 301).
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 19 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL C. PROCEDURE NOTE: If the length of any fastener specified in this Service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. **CONF 001 (1) Subtask 576086-832-004-001 - Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ASNA2532-9 4 Nut 1 NAS1727-9E 4 Nut 2 ASNA2026T9-40 1 Bolt 2 NSA5356-9-40 1 Bolt 2 NSA5358-9-40 1 Bolt 3 NSA5368PD916B 2 Washer 3 NSA5369PD916B 2 Washer 4 ASNA2026T9-32 1 Bolt 4 NSA5356-9-32 1 Bolt 4 NSA5358-9-32 1 Bolt 5 ASNA2532-8 3 Nut 5 NAS1727-8E 3 Nut 6 NSA5368PD816D 3 Washer 6 NSA5369PD816D 3 Washer 7 ASNA2026T8-32 1 Bolt 7 NSA5356-8-32 1 Bolt 7 NSA5358-8-32 1 Bolt 8 ASNA2026T9-30 1 Bolt 8 NSA5356-9-30 1 Bolt 8 NSA5358-9-30 1 Bolt 9 ASNA2026T8-27 1 Bolt 9 NSA5356-8-27 1 Bolt DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 20 5

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 NSA5358-8-27 1 Bolt 10 NSA5368PD816B 2 Washer 10 NSA5369PD816B 2 Washer 11 ASNA2026T8-36 1 Bolt 11 NSA5356-8-36 1 Bolt 11 NSA5358-8-36 1 Bolt 12 ASNA2026T8-38 1 Bolt 12 NSA5356-8-38 1 Bolt 12 NSA5358-8-38 1 Bolt 13 ASNA2531-8 1 Nut 13 NAS1726-8E 1 Nut 15 ASNA2026T9-42 1 Bolt 15 NSA5356-9-42 1 Bolt 15 NSA5358-9-42 1 Bolt 16 ASNA2532-10 2 Nut 16 NAS1727-10E 2 Nut 17 ASNA2026T10-44 1 Bolt 17 NSA5356-10-44 1 Bolt 17 NSA5358-10-44 1 Bolt 18 ASNA2026T10-47 1 Bolt 18 NSA5356-10-47 1 Bolt 18 NSA5358-10-47 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Structural Repair Manual (SRM) Chapter 51 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 NOTE: Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. NOTE: The installed fasteners shall be checked in accordance with the DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 21 5

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# @A300-600 SERVICE BULLETIN requirements of SRM Chapter 51 to ensure that adequate thread protrusion is maintained after installation. (a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box Refer to Fig. A-FBAAAand Fig. A-FFBAA (b) Remove the sealant around the fasteners. (c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1) thru (18)). (d) Clean the holes with Solvent 11-026 As required (e) Measure the diameter of the holes (nominal diameter, R1 oversize or R2 oversize). (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) 1 No crack found Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the removed fasteners a Install : Hole A : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt ASNA2026T9-40 Item 2 or 1 Bolt NSA5356-9-40 Item 2 or 1 Bolt NSA5358-9-40 Item 2 Hole B : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 22 5

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# @A300-600 SERVICE BULLETIN
1 Washer NSA5369PD916B Item 3 or 1 Washer NSA5368PD916B Item 3 1 Bolt ASNA2026T9-32 Item 4 or 1 Bolt NSA5356-9-32 Item 4 or 1 Bolt NSA5358-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2026T8-32 Item 7 or 1 Bolt NSA5356-8-32 Item 7 or 1 Bolt NSA5358-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Washer NSA5369PD916B Item 3 or DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 23 5

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# @A300-600 SERVICE BULLETIN
1 Washer NSA5368PD916B Item 3 1 Bolt ASNA2026T9-30 Item 8 or 1 Bolt NSA5356-9-30 Item 8 or 1 Bolt NSA5358-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2026T8-27 Item 9 or 1 Bolt NSA5356-8-27 Item 9 or 1 Bolt NSA5358-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816B Item 10 or 1 Washer NSA5368PD816B Item 10 or DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 24 5

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# @A300-600 SERVICE BULLETIN
1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2026T8-36 Item 11 or 1 Bolt NSA5356-8-36 Item 11 or 1 Bolt NSA5358-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : 1 Nut NAS1726-8E Item 13 or 1 Nut ASNA2531-8 Item 13 1 Washer NSA5369PD816B Item 10 or 1 Washer NSA5368PD816B Item 10 1 Bolt ASNA2026T8-38 Item 12 or 1 Bolt NSA5356-8-38 Item 12 or 1 Bolt NSA5358-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt ASNA2026T9-42 Item 15 or DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 25 5

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# @A300-600 SERVICE BULLETIN
1 Bolt NSA5356-9-42 Item 15 or 1 Bolt NSA5358-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt ASNA2026T10-44 Item 17 or 1 Bolt NSA5356-10-44 Item 17 or 1 Bolt NSA5358-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt ASNA2026T10-47 Item 18 or 1 Bolt NSA5356-10-47 Item 18 or 1 Bolt NSA5358-10-47 Item 18 b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Repair as written in SUBTASK 576086-833-017 001 Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box . DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 26 5

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# @A300-600 SERVICE BULLETIN (2) Subtask 576086-832-005-001 - Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ASNA2532-9 4 Nut 1 NAS1727-9E 4 Nut 2 ASNA2026T9-40 1 Bolt 2 NSA5356-9-40 1 Bolt 2 NSA5358-9-40 1 Bolt 3 NSA5368PD916B 2 Washer 3 NSA5369PD916B 2 Washer 4 ASNA2026T9-32 1 Bolt 4 NSA5356-9-32 1 Bolt 4 NSA5358-9-32 1 Bolt 5 ASNA2532-8 3 Nut 5 NAS1727-8E 3 Nut 6 NSA5368PD816D 3 Washer 6 NSA5369PD816D 3 Washer 7 ASNA2026T8-32 1 Bolt 7 NSA5356-8-32 1 Bolt 7 NSA5358-8-32 1 Bolt 8 ASNA2026T9-30 1 Bolt 8 NSA5356-9-30 1 Bolt 8 NSA5358-9-30 1 Bolt 9 ASNA2026T8-27 1 Bolt 9 NSA5356-8-27 1 Bolt 9 NSA5358-8-27 1 Bolt 10 NSA5368PD816B 2 Washer 10 NSA5369PD816B 2 Washer 11 ASNA2026T8-36 1 Bolt 11 NSA5356-8-36 1 Bolt 11 NSA5358-8-36 1 Bolt 12 ASNA2026T8-38 1 Bolt 12 NSA5356-8-38 1 Bolt 12 NSA5358-8-38 1 Bolt 13 ASNA2531-8 1 Nut 13 NAS1726-8E 1 Nut 15 ASNA2026T9-42 1 Bolt DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 27 5

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 NSA5356-9-42 1 Bolt 15 NSA5358-9-42 1 Bolt 16 ASNA2532-10 2 Nut 16 NAS1727-10E 2 Nut 17 ASNA2026T10-44 1 Bolt 17 NSA5356-10-44 1 Bolt 17 NSA5358-10-44 1 Bolt 18 ASNA2026T10-47 1 Bolt 18 NSA5356-10-47 1 Bolt 18 NSA5358-10-47 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 (a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box refer to Fig. A-FBAAAand Fig. A-FFBAA (b) Remove the sealant around the fasteners. (c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1) thru (18)). (d) Clean the holes with Solvent 11-026 As required (e) Measure the diameter of the holes (nominal diameter, R1 oversize or R2 oversize). (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 28 5

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# @A300-600 SERVICE BULLETIN
1 No crack found Install the new nominal R1 oversize or R2 oversize fasteners in relation to the removed fasteners a Install : Hole A : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt ASNA2026T9-40 Item 2 or 1 Bolt NSA5356-9-40 Item 2 or 1 Bolt NSA5358-9-40 Item 2 Hole B : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Washer NSA5369PD916B Item 3 or 1 Washer NSA5368PD916B Item 3 1 Bolt ASNA2026T9-32 Item 4 or 1 Bolt NSA5356-9-32 Item 4 or 1 Bolt NSA5358-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 or DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 29 5

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# @A300-600 SERVICE BULLETIN
1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2026T8-32 Item 7 or 1 Bolt NSA5356-8-32 Item 7 or 1 Bolt NSA5358-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Washer NSA5369PD916B Item 3 or 1 Washer NSA5368PD916B Item 3 1 Bolt ASNA2026T9-30 Item 8 or 1 Bolt NSA5356-9-30 Item 8 or 1 Bolt NSA5358-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816D Item 6 DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 30 5

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# @A300-600 SERVICE BULLETIN

or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2026T8-27 Item 9 or 1 Bolt NSA5356-8-27 Item 9 or 1 Bolt NSA5358-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816B Item 10 or 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2026T8-36 Item 11 or 1 Bolt NSA5356-8-36 Item 11 or 1 Bolt NSA5358-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : 1 Nut NAS1726-8E Item 13 or
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 31 5

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# @A300-600 SERVICE BULLETIN
1 Nut ASNA2531-8 Item 13 1 Washer NSA5369PD816B Item 10 or 1 Washer NSA5368PD816B Item 10 1 Bolt ASNA2026T8-38 Item 12 or 1 Bolt NSA5356-8-38 Item 12 or 1 Bolt NSA5358-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt ASNA2026T9-42 Item 15 or 1 Bolt NSA5356-9-42 Item 15 or 1 Bolt NSA5358-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt ASNA2026T10-44 Item 17 or 1 Bolt NSA5356-10-44 Item 17 or 1 Bolt NSA5358-10-44 Item 17 Hole S : DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 32 5

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# @A300-600 SERVICE BULLETIN
1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt ASNA2026T10-47 Item 18 or 1 Bolt NSA5356-10-47 Item 18 or 1 Bolt NSA5358-10-47 Item 18 b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Repair as written in SUBTASK 576086-833-018 001 Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box . (3) Subtask 576086-832-006-001 - Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 ASNA2532-8 1 Nut 5 NAS1727-8E 1 Nut 6 NSA5368PD816D 1 Washer 6 NSA5369PD816D 1 Washer 19 ASNA2027T8-26 1 Bolt 19 NSA5357-8-24 1 Bolt DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 33 5

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 NSA5359-8-24 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 NOTE: Remove partially the vapor seal in order to access to the area to be inspected. (a) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box refer to Fig. A-FBAAAand Fig. A-FFBAA NOTE: Only do this inspection if you found a crack in the hole G. (b) Remove the sealant around the fasteners. (c) Remove the fastener from the hole T (adjacent to the hole G) (Item (19)). (d) Clean the hole with Solvent 11-026 As required (e) Measure the diameter of the hole (nominal diameter, R1 oversize or R2 oversize). (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) 1 No crack found Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the removed fasteners

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 34 5

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# @A300-600 SERVICE BULLETIN

a Install in the hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2027T8-26 Item 19 or 1 Bolt NSA5357-8-24 Item 19 or 1 Bolt NSA5359-8-24 Item 19 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fastener adjacent to the fastener of the hole G. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Repair as written in SUBTASK 576086-833-019 001 Repair the crack(s) found in the hole T (adjacent to the hole G), at the LH internal angle of the center wing box . (4) Subtask 576086-832-007-001 - Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 35 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 ASNA2532-8 1 Nut 5 NAS1727-8E 1 Nut 6 NSA5368PD816D 1 Washer 6 NSA5369PD816D 1 Washer 19 ASNA2027T8-26 1 Bolt 19 NSA5357-8-24 1 Bolt 19 NSA5359-8-24 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 NOTE: Remove partially the vapor seal in order to access to the area to be inspected. (a) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box refer to Fig. A-FBAAAand Fig. A-FFBAA NOTE: Only do this inspection if you found a crack in the hole G. (b) Remove the sealant around the fasteners. (c) Remove the fastener from the hole T (adjacent to the hole G) (Item (19)). (d) Clean the hole with Solvent 11-026 As required (e) Measure the diameter of the hole (nominal diameter, R1 oversize or R2 oversize). DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 36 5

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# @A300-600 SERVICE BULLETIN (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) 1 No crack found Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the removed fasteners a Install in the hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5369PD816D Item 6 or 1 Washer NSA5368PD816D Item 6 1 Bolt ASNA2027T8-26 Item 19 or 1 Bolt NSA5357-8-24 Item 19 or 1 Bolt NSA5359-8-24 Item 19 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fastener adjacent to the fastener of the hole G. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Repair as written in SUBTASK 576086-833-020 001 Repair the crack(s) found in the hole T (adjacent to the hole G), at the RH internal angle of the center wing box .

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 37 5

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# @A300-600 SERVICE BULLETIN (5) Subtask 576086-832-008-001 - Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-10-45 Fig. A-FCAAA Ultrasonic Inspection of the Holes type 1, type 2 and type 3. Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 (a) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box (Refer to NTM 57-10-45). refer to Fig. A-FFBAA Sheet 01, Fig. A-FFBAA Sheet 02 and Fig. A-FCAAA Sheet 01
. 1 No crack found a Do the subsequent inspections at the interval given in the PARA Accomplishment Timescale Table 1. 2 Crack found a Contact AIRBUS before the next flight. (6) Subtask 576086-832-009-001 - Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-10-45 Fig. A-FCAAA Ultrasonic Inspection of the Holes type 1, type 2 and type 3. Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 38 5

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# @A300-600 SERVICE BULLETIN (a) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box (Refer to NTM 57-10-45). refer to Fig. A-FFBAA Sheet 01, Fig. A-FFBAA Sheet 02 and Fig. A-FCAAA Sheet 01
. 1 No crack found a Do the subsequent inspections at the interval given in the PARA Accomplishment Timescale Table 1. 2 Crack found a Contact AIRBUS before the next flight. **CONF 002 (1) Subtask 576086-832-004-002 - Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 576086A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ASNA2532-9 4 Nut 1 NAS1727-9E 4 Nut 2 NSA5358-9-40 1 Bolt 3 NSA5368PD916B 2 Washer 4 NSA5358-9-32 1 Bolt 5 ASNA2532-8 3 Nut 5 NAS1727-8E 3 Nut 6 NSA5368PD816D 3 Washer 7 NSA5358-8-32 1 Bolt 8 NSA5358-9-30 1 Bolt 9 NSA5358-8-27 1 Bolt 10 NSA5368PD816B 2 Washer 11 NSA5358-8-36 1 Bolt 12 NSA5358-8-38 1 Bolt 13 ASNA2531-8 1 Nut 13 NAS1726-8E 1 Nut 15 NSA5358-9-42 1 Bolt 16 ASNA2532-10 2 Nut 16 NAS1727-10E 2 Nut DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 39 5

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 17 NSA5358-10-44 1 Bolt 18 NSA5358-10-47 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 (a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box Refer to Fig. A-FBAAAand Fig. A-FFBAA (b) Remove the sealant around the fasteners. (c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1) thru (18)). (d) Clean the holes with Solvent 11-026 As required (e) Measure the diameter of the R2 oversize holes. (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) 1 No crack found Install the new R2 oversize fasteners in relation to the removed fasteners a Install : Hole A : 1 Nut NAS1727-9E Item 1 DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 40 5

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# @A300-600 SERVICE BULLETIN

or 1 Nut ASNA2532-9 Item 1 1 Bolt NSA5358-9-40 Item 2 Hole B : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 or DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 41 5

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# @A300-600 SERVICE BULLETIN
1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : 1 Nut NAS1726-8E Item 13 or 1 Nut ASNA2531-8 Item 13 1 Washer NSA5368PD816B Item 10 1 Bolt NSA5358-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt NSA5358-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 42 5

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# @A300-600 SERVICE BULLETIN

or 1 Nut ASNA2532-10 Item 16 1 Bolt NSA5358-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt NSA5358-10-47 Item 18 b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Contact AIRBUS before the next flight. (2) Subtask 576086-832-005-002 - Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 576086A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ASNA2532-9 4 Nut 1 NAS1727-9E 4 Nut 2 NSA5358-9-40 1 Bolt 3 NSA5368PD916B 2 Washer 4 NSA5358-9-32 1 Bolt 5 ASNA2532-8 3 Nut 5 NAS1727-8E 3 Nut 6 NSA5368PD816D 3 Washer DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 43 5

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5358-8-32 1 Bolt 8 NSA5358-9-30 1 Bolt 9 NSA5358-8-27 1 Bolt 10 NSA5368PD816B 2 Washer 11 NSA5358-8-36 1 Bolt 12 NSA5358-8-38 1 Bolt 13 ASNA2531-8 1 Nut 13 NAS1726-8E 1 Nut 15 NSA5358-9-42 1 Bolt 16 ASNA2532-10 2 Nut 16 NAS1727-10E 2 Nut 17 NSA5358-10-44 1 Bolt 18 NSA5358-10-47 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 (a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box Refer to Fig. A-FBAAAand Fig. A-FFBAA (b) Remove the sealant around the fasteners. (c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1) thru (18)). (d) Clean the holes with Solvent 11-026 As required (e) Measure the diameter of the R2 oversize holes.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 44 5

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# @A300-600 SERVICE BULLETIN (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) 1 No crack found Install the new R2 oversize fasteners in relation to the removed fasteners a Install : Hole A : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt NSA5358-9-40 Item 2 Hole B : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 or
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 45 5

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# @A300-600 SERVICE BULLETIN
1 Nut ASNA2532-9 Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : 1 Nut NAS1726-8E Item 13 or 1 Nut ASNA2531-8 Item 13 1 Washer NSA5368PD816B Item 10 1 Bolt NSA5358-8-38 Item 12
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 46 5

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# @A300-600 SERVICE BULLETIN
NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 or 1 Nut ASNA2532-9 Item 1 1 Bolt NSA5358-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt NSA5358-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 or 1 Nut ASNA2532-10 Item 16 1 Bolt NSA5358-10-47 Item 18 b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Contact AIRBUS before the next flight.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 47 5

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# @A300-600 SERVICE BULLETIN (3) Subtask 576086-832-006-002 - Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 576086A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 ASNA2532-8 1 Nut 5 NAS1727-8E 1 Nut 6 NSA5368PD816D 1 Washer 19 NSA5359-8-24 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 NOTE: Remove partially the vapor seal in order to access to the area to be inspected. (a) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of the center wing box refer to Fig. A-FBAAAand Fig. A-FFBAA NOTE: Only do this inspection if you found a crack in the hole G. (b) Remove the sealant around the fasteners. (c) Remove the fastener from the hole T (adjacent to the hole G) (Item (19)). DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 48 5

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# @A300-600 SERVICE BULLETIN (d) Clean the hole with Solvent 11-026 As required (e) Measure the diameter of the R2 oversize hole. (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) 1 No crack found Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the removed fasteners a Install in the hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5359-8-24 Item 19 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fastener adjacent to the fastener of the hole G. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Contact AIRBUS before the next flight. (4) Subtask 576086-832-007-002 - Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 49 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 576086A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 ASNA2532-8 1 Nut 5 NAS1727-8E 1 Nut 6 NSA5368PD816D 1 Washer 19 NSA5359-8-24 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Non Destructive Test Manual (NTM) 57-10-11 Service Bulletin (SB) A300-57-6069 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 NOTE: Remove partially the vapor seal in order to access to the area to be inspected. (a) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of the center wing box refer to Fig. A-FBAAAand Fig. A-FFBAA NOTE: Only do this inspection if you found a crack in the hole G. (b) Remove the sealant around the fasteners. (c) Remove the fastener from the hole T (adjacent to the hole G) (Item (19)). (d) Clean the hole with Solvent 11-026 As required (e) Measure the diameter of the R2 oversize hole. (f) Do a rotating probe inspection (Refer to NTM 57-10-11, Part 6) DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 50 5

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# @A300-600 SERVICE BULLETIN
1 No crack found Install the R2 oversize fasteners in relation to the removed fasteners a Install in the hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 or 1 Nut ASNA2532-8 Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5359-8-24 Item 19 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. b Apply Fuel Tank Sealant Polysulfide 09-001 As required to the fastener adjacent to the fastener of the hole G. c Do the subsequent inspections at the intervals given in Accomplishment Timescale Table 2. 2 Crack found a Contact AIRBUS before the next flight. (5) Subtask 576086-832-008-001 - Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-10-45 Fig. A-FCAAA Ultrasonic Inspection of the Holes type 1, type 2 and type 3. Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 51 5

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# @A300-600 SERVICE BULLETIN (a) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft bottom panel of the center wing box (Refer to NTM 57-10-45). refer to Fig. A-FFBAA Sheet 01, Fig. A-FFBAA Sheet 02 and Fig. A-FCAAA Sheet 01
. 1 No crack found a Do the subsequent inspections at the interval given in the PARA Accomplishment Timescale Table 1. 2 Crack found a Contact AIRBUS before the next flight. (6) Subtask 576086-832-009-001 - Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-10-45 Fig. A-FCAAA Ultrasonic Inspection of the Holes type 1, type 2 and type 3. Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 Sheet 02 (a) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft bottom panel of the center wing box (Refer to NTM 57-10-45). refer to Fig. A-FFBAA Sheet 01, Fig. A-FFBAA Sheet 02 and Fig. A-FCAAA Sheet 01
. 1 No crack found a Do the subsequent inspections at the interval given in the PARA Accomplishment Timescale Table 1. 2 Crack found a Contact AIRBUS before the next flight.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 52 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 (1) Subtask 576086-700-001-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 (a) Do the leak test of the center fuel tank, (Refer to AMM 28-11-00 Page Block 501). **CONF 002 (1) Subtask 576086-700-001-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 (a) Do the leak test of the center fuel tank, (Refer to AMM 28-11-00 Page Block 501). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 576086-942-001-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 28-10-00 28-11-29, Page Block 401 28-25-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Respect the procedure to leave the fuel center tank, (Refer to AMM 28-10-00). (c) Close the access doors 147AZ and 148AZ, (Refer to AMM 28-11-29 Page Block 401 and AMM 06-41-53). DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 53 5

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# @A300-600 SERVICE BULLETIN (d) Refuel the fuel center tank, (Refer to AMM 28-25-00 Page Block 301). (e) Remove the access platform(s). (f) Restore the systems and the aircraft to normal operating condition. **CONF 002 (1) Subtask 576086-942-001-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 28-10-00 28-11-29, Page Block 401 28-25-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Respect the procedure to leave the fuel center tank, (Refer to AMM 28-10-00). (c) Close the access doors 147AZ and 148AZ, (Refer to AMM 28-11-29 Page Block 401 and AMM 06-41-53). (d) Refuel the fuel center tank, (Refer to AMM 28-25-00 Page Block 301). (e) Remove the access platform(s). (f) Restore the systems and the aircraft to normal operating condition.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 54 5

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# @A300-600 SERVICE BULLETIN Task 576086-833-802-001 - Repair **CONF ALL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT YOU OBEY ALL THE SAFETY PRECAUTIONS APPLICABLE TO THE ACCESS TO AND THE WORK IN THE FUEL CENTER TANK. 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 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. Task Associated Data **CONF 001 Manpower TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Manpower TOTAL MANHOURS 0.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 576086-910-002-001 Manpower Resources Skills NON SPECIFIC

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 55 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Primer Coating Epoxy Polyamide Chemical 16-006 As required Polyurethane Finish Paint (For External Applic.) 16-018 As required
References Consumable Material List (CML) Structural Repair Manual (SRM) 51-21-00 51-24-00 51-40-47 (a) For the specification of the material numbers (Mat. No.), refer to the CML. (b) Clean the surfaces to do an inspection of with Solvent 11-026 As required (c) Renew the protective finish, (Refer to SRM 51-21-00) with Chemical Conversion Coating Yellow Aluminum 13-002 As required
Primer Coating Epoxy Polyamide Chemical 16-006 As required

and Polyurethane Finish Paint (For External Applic.) 16-018 As required
(d) Apply Fuel Tank Sealant Polysulfide 09-001 As required

to the fasteners, (Refer to SRM 51-24-00). (e) Countersink the holes, (Refer to SRM 51-40-47). DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 56 5

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# @A300-600 SERVICE BULLETIN (f) Use a nonmetallic spatula to remove the sealant and clean the areas with Solvent 11-026 As required (2) Subtask 576086-839-002-001 - Administrative (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 None **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 576086-941-002-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00, Page Block 301 28-10-00, Page Block 301 28-11-29, Page Block 401 28-25-00, Page Block 301 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00 Page Block 301). (b) Put the access platform(s) in position. (c) Defuel the fuel center tank (Refer to AMM 28-25-00 Page Block 301). (d) Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29 Page Block 401 and AMM 06-41-53). (e) Respect the procedure required to work in the fuel center tank (Refer to AMM 28-10-00 Page Block 301). **CONF 002 None

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 57 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 576086-833-017-001 - Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 NAS1727-9E 8 Nut 2 NSA5356-9-40 1 Bolt 2 NSA5358-9-40 1 Bolt 3 NSA5368PD916B 4 Washer 4 NSA5356-9-32 1 Bolt 4 NSA5358-9-32 1 Bolt 5 NAS1727-8E 6 Nut 6 NSA5368PD816D 6 Washer 7 NSA5356-8-32 1 Bolt 7 NSA5358-8-32 1 Bolt 8 NSA5356-9-30 1 Bolt 8 NSA5358-9-30 1 Bolt 9 NSA5356-8-27 1 Bolt 9 NSA5358-8-27 1 Bolt 10 NSA5368PD816B 4 Washer 11 NSA5356-8-36 1 Bolt 11 NSA5358-8-36 1 Bolt 12 NSA5356-8-38 1 Bolt 12 NSA5358-8-38 1 Bolt 13 NAS1726-8E 2 Nut 15 NSA5356-9-42 1 Bolt 15 NSA5358-9-42 1 Bolt 16 NAS1727-10E 4 Nut 17 NSA5356-10-44 1 Bolt 17 NSA5358-10-44 1 Bolt 18 NSA5356-10-47 1 Bolt 18 NSA5358-10-47 1 Bolt

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 58 5

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# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Structural Repair Manual (SRM) 51-40-44 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal angle of the center wing box refer to Fig. A-FBAAA (b) If the diameter of the hole is equal to the nominal diameter : 1 ream up to the R1 oversize 2 do a rotating probe inspection : a if crack is removed, refer to Repair PARA.3.C.(1).(e). b if crack is not removed, ream up to the R2 oversize <1> do a rotating probe inspection : <a> if crack is removed, refer to Repair PARA.3.C.(1).(f). <b> if crack is not removed, contact AIRBUS before the next flight. (c) If the diameter of the hole is equal to the R1 oversize : 1 ream up to the R2 oversize a do a rotating probe inspection : <1> if crack is removed, refer to Repair PARA.3.C.(1).(f). <2> if crack is not removed, contact AIRBUS before the next flight. (d) If you found a crack in a hole with R2 oversize, contact AIRBUS before the next flight. (e) Install the R1 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 59 5

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# @A300-600 SERVICE BULLETIN
1 Hole A : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5356-9-40 Item 2 or Hole B : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5356-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5356-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5356-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5356-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F :
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 60 5

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# @A300-600 SERVICE BULLETIN
1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5356-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : 1 Nut NAS1726-8E Item 13 1 Washer NSA5368PD816B Item 10 1 Bolt NSA5356-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5356-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5356-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5356-10-47 Item 18 (f) Install the R2 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). 1 Hole A : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5358-9-40 Item 2 Hole B : 1 Nut NAS1727-9E Item 1 DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 61 5

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# @A300-600 SERVICE BULLETIN
1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 62 5

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# @A300-600 SERVICE BULLETIN
Hole G : 1 Nut NAS1726-8E Item 13 1 Washer NSA5368PD816B Item 10 1 Bolt NSA5358-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5358-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5358-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5358-10-47 Item 18 (g) Clean the areas with Solvent 11-026 As required (h) Apply Fuel Tank Sealant Polysulfide 09-001 As required

to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S. (i) Contact AIRBUS, use the inspection report to get a new inspection interval. (2) Subtask 576086-833-018-001 - Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 63 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 NAS1727-9E 8 Nut 2 NSA5356-9-40 1 Bolt 2 NSA5358-9-40 1 Bolt 3 NSA5368PD916B 4 Washer 4 NSA5356-9-32 1 Bolt 4 NSA5358-9-32 1 Bolt 5 NAS1727-8E 6 Nut 6 NSA5368PD816D 6 Washer 7 NSA5356-8-32 1 Bolt 7 NSA5358-8-32 1 Bolt 8 NSA5356-9-30 1 Bolt 8 NSA5358-9-30 1 Bolt 9 NSA5356-8-27 1 Bolt 9 NSA5358-8-27 1 Bolt 10 NSA5368PD816B 4 Washer 11 NSA5356-8-36 1 Bolt 11 NSA5358-8-36 1 Bolt 12 NSA5356-8-38 1 Bolt 12 NSA5358-8-38 1 Bolt 13 NAS1726-8E 2 Nut 15 NSA5356-9-42 1 Bolt 15 NSA5358-9-42 1 Bolt 16 NAS1727-10E 4 Nut 17 NSA5356-10-44 1 Bolt 17 NSA5358-10-44 1 Bolt 18 NSA5356-10-47 1 Bolt 18 NSA5358-10-47 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Structural Repair Manual (SRM) 51-40-44 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 64 5

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# @A300-600 SERVICE BULLETIN (a) Repair the crack(s) found in the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal angle of the center wing box refer to Fig. A-FBAAA (b) If the diameter of the hole is equal to the nominal diameter : 1 ream up to the R1 oversize 2 do a rotating probe inspection : a if crack is removed, refer to Repair PARA.3.C.(2).(e). b if crack is not removed, ream up to the R2 oversize <1> do a rotating probe inspection : <a> if crack is removed, refer to Repair PARA.3.C.(2).(f). <b> if crack is not removed, contact AIRBUS before the next flight. (c) If the diameter of the hole is equal to the R1 oversize : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). 1 ream up to the R2 oversize a do a rotating probe inspection : <1> if crack is removed, refer to Repair PARA.3.C.(2).(f). <2> if crack is not removed, contact AIRBUS before the next flight. (d) If you found a crack in a hole with R2 oversize, contact AIRBUS before the next flight. (e) Install the R1 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). 1 Hole A : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5356-9-40 Item 2 or Hole B : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 65 5

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# @A300-600 SERVICE BULLETIN
1 Bolt NSA5356-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5356-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5356-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5356-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5356-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 66 5

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# @A300-600 SERVICE BULLETIN
1 Nut NAS1726-8E Item 13 1 Washer NSA5368PD816B Item 10 1 Bolt NSA5356-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5356-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5356-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5356-10-47 Item 18 (f) Install the R2 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). 1 Hole A : 1 Nut NAS1727-9E Item 1 1 Bolt NSA5358-9-40 Item 2 Hole B : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-32 Item 4 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole C : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 67 5

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# @A300-600 SERVICE BULLETIN
1 Bolt NSA5358-8-32 Item 7 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole D : 1 Nut NAS1727-9E Item 1 1 Washer NSA5368PD916B Item 3 1 Bolt NSA5358-9-30 Item 8 NOTE: Only install the washer Item 3 if you found a washer during the removal procedure. Hole E : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-27 Item 9 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. Hole F : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816B Item 10 or 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5358-8-36 Item 11 NOTE: Only install the washer Item 6 or Item 10 if you found a washer during the removal procedure. Hole G : 1 Nut NAS1726-8E Item 13 1 Washer NSA5368PD816B Item 10 1 Bolt NSA5358-8-38 Item 12 NOTE: Only install the washer Item 10 if you found a washer during the removal procedure. Hole P : DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 68 5

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# @A300-600 SERVICE BULLETIN
1 Nut NAS1727-9E Item 1 1 Bolt NSA5358-9-42 Item 15 Hole Q : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5358-10-44 Item 17 Hole S : 1 Nut NAS1727-10E Item 16 1 Bolt NSA5358-10-47 Item 18 (g) Clean the areas with Solvent 11-026 As required (h) Apply Fuel Tank Sealant Polysulfide 09-001 As required

to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S. (i) Contact AIRBUS, use the inspection report to get a new inspection interval. (3) Subtask 576086-833-019-001 - Repair the crack(s) found in the hole T (adjacent to the hole G), at the LH internal angle of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 NAS1727-8E 2 Nut 6 NSA5368PD816D 1 Washer 6 NSA5369PD816D 1 Washer 19 NSA5357-8-24 1 Bolt 19 NSA5359-8-24 1 Bolt

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 69 5

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# @A300-600 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Structural Repair Manual (SRM) 51-40-44 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Repair the crack(s) found in the hole T (adjacent to the hole G), at the LH internal angle of the center wing box refer to Fig. A-FBAAA (a) Measure the diameter of the hole (nominal diameter, R1 oversize or R2 oversize). (b) If the diameter of the hole is equal to the nominal diameter : 1 ream up to the R1 oversize 2 do a rotating probe inspection : a if crack is removed, refer to Repair PARA.C.(3).(e). b if crack is not removed, ream up to the R2 oversize <1> do a rotating probe inspection : <a> if crack is removed, refer to Repair PARA.C.(3).(f). <b> if crack is not removed, contact AIRBUS before the next flight. (c) If the diameter of the hole is equal to the R1 oversize : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). 1 ream up to the R2 oversize a do a rotating probe inspection : <1> if crack is removed, refer to Repair PARA.C.(3).(f). <2> if crack is not removed, contact AIRBUS before the next flight. (d) If you found a crack in a hole with R2 oversize, contact AIRBUS before the next flight. DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 70 5

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# @A300-600 SERVICE BULLETIN (e) Install the R1 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). Hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5357-8-24 Item 19 (f) Install the R2 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). Hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 1 Washer NSA5369PD816D Item 6 1 Bolt NSA5359-8-24 Item 19 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. (g) Clean the areas with Solvent 11-026 As required (h) Apply Fuel Tank Sealant Polysulfide 09-001 As required

to the fastener of the hole T. (i) Contact AIRBUS before the next flight. (4) Subtask 576086-833-020-001 - Repair the crack(s) found in the hole T (adjacent to the hole G), at the RH internal angle of the center wing box Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 71 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Kit 576086A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 NAS1727-8E 2 Nut 6 NSA5368PD816D 1 Washer 6 NSA5369PD816D 1 Washer 19 NSA5357-8-24 1 Bolt 19 NSA5359-8-24 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Solvent 11-026 As required References Structural Repair Manual (SRM) 51-40-44 Fig. A-FBAAA Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Measure the diameter of the hole (nominal diameter, R1 oversize or R2 oversize). (b) If the diameter of the hole is equal to the nominal diameter : 1 ream up to the R1 oversize 2 do a rotating probe inspection : a if crack is removed, refer to Repair PARA.C.(3).(e). b if crack is not removed, ream up to the R2 oversize <1> do a rotating probe inspection : <a> if crack is removed, refer to Repair PARA.C.(3).(f). <b> if crack is not removed, contact AIRBUS before the next flight. (c) If the diameter of the hole is equal to the R1 oversize : 1 ream up to the R2 oversize a do a rotating probe inspection : <1> if crack is removed, refer to Repair PARA.C.(3).(f). DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 72 5

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# @A300-600 SERVICE BULLETIN <2> if crack is not removed, contact AIRBUS before the next flight. (d) If you found a crack in a hole with R2 oversize, contact AIRBUS before the next flight. (e) Install the R1 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). Hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 1 Washer NSA5368PD816D Item 6 1 Bolt NSA5357-8-24 Item 19 (f) Install the R2 oversize fasteners : NOTE: installation of fasteners with transition fit (Refer to SRM 51-40-44). Hole T (adjacent to the hole G) : 1 Nut NAS1727-8E Item 5 1 Washer NSA5369PD816D Item 6 1 Bolt NSA5359-8-24 Item 19 NOTE: Only install the washer Item 6 if you found a washer during the removal procedure. (g) Clean the areas with Solvent 11-026 As required (h) Apply Fuel Tank Sealant Polysulfide 09-001 As required

to the fastener of the hole T. (i) Contact AIRBUS before the next flight. **CONF 002 None

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 73 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 (1) Subtask 576086-700-002-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 (a) Do the leak test of the center fuel tank, (Refer to AMM 28-11-00 Page Block 501). **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 576086-942-002-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 28-10-00 28-11-29, Page Block 401 28-25-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Respect the procedure to leave the fuel center tank, (Refer to AMM 28-10-00). (c) Close the access doors 147AZ and 148AZ, (Refer to AMM 28-11-29 Page Block 401 and AMM 06-41-53). (d) Refuel the fuel center tank, (Refer to AMM 28-25-00 Page Block 301). (e) Remove the access platform(s). (f) Restore the systems and the aircraft to normal operating condition.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 74 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 None

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 75 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING AT THE THRESHOLD GIVEN IN PARA. E.(2).

No. 0300−57−6069

YES NO DO A SPECIAL INSPECTION REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE (REFER TO FIG. A−FBAAA SHEET 01 AND 02)

CONTACT AIRBUS BEFORE THE NEXT FLIGHT CRACKS FINDING NO YES
INSTALL NEW NOMINAL, R1 OVERSIZE

OR R2 OVERSIZE FASTENERS (*) IN SERVICE BULLETIN ACCOMPLISHMENT
AND

(REFER TO NTM 57−10−11, PARAGRAPH 7) REMOVE THE FASTENERS A, B, C, D, E, F, G, P, Q AND S. DO THE ROTATING PROBE INSPECTION OF THE HOLES

AT THE THRESHOLD GIVEN IN PARA. E.(2). TABLE 2.

RELATION TO THE REMOVED FASTENERS

DO THE SEALING OF THE FASTENERS A, B, C, D, E, F, G, P, Q AND S.
DO THE SUBSEQUENT INSPECTIONS CRACKS FINDING YES NO DO A SPECIAL ULTRASONIC INSPECTION OF THE HOLES (REFER TO NTM 57−10−45, PART 4 AND FIG. A−FCAAA SHEET 01) PARA. E.(2). TABLE 1.

AT THE INTERVAL GIVEN IN PARA. E.(2). TABLE 2. DO THE SUBSEQUENT INSPECTIONS AT THE INTREVAL GIVEN IN PARA. E.(2). TABLE 1. No. 57−6050 NO SERVICE BULLETIN ACCOMPLISHMENT AND YES

INSPECTION AS PER SB No.57−6102

MEASURE THE DIAMETER OF THE HOLE. CRACKS FINDING NO YES INSTALL NEW NOMINAL, R1 OVERSIZE OR R2 OVERSIZE FASTENERS (*) IN RELATION TO THE REMOVED FASTENERS

DO THE SEALING OF THE FASTENER T (ADJACENT TO THE HOLE G) AND INSPECT THE HOLE IF A CRACK IS FOUND ON THE HOLE G, REMOVE THE FASTENERS FROM THE HOLE T AT THE THRESHOLD AND THE INTERVAL GIVEN IN

(REFER TO NTM 57−10−11, PARAGRAPH 7)

(*) INSTALLATION FASTENERS WITH TRANSITION FIT, (REFER TO SRM 51−40−44). **NOTE:** SEE FIGURE A−FFBAA SHEET 02 CONTACT AIRBUS BEFORE THE NEXT FLIGHT

D_SB_576086_5_FBAA_01_04 Figure A-FFBAA - Sheet 01 Flow Chart
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 76 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING OR
DIAMETER OF THE HOLE = R1 OVERSIZE DIAMETER OF THE HOLE

= NOMINAL DIAMETER. DIAMETER OF THE HOLE = R2 OVERSIZE
REAM UP TO THE R1 OVERSIZE TO REMOVE THE CRACKS.

DO A ROTATING PROBE INSPECTION.
CRACK NO YES REMOVED INSTALL WITH THE R1 (*) OVERSIZE FASTENERS REAM UP TO THE R2 OVERSIZE TO REMOVE THE CRACKS.

CRACK NO YES REMOVED INSTALL WITH THE R2 (*) OVERSIZE FASTENERS CONTACT AIRBUS BEFORE THE NEXT FLIGHT DO A ROTATING PROBE INSPECTION.

SEAL THE FASTENERS
REPEAT INSPECTON AT THE INTERVAL GIVEN IN PARA E.(2). TABLE 2. **NOTE:** FROM FIGURE A−FFBAA SHEET 01

(*) INSTALLATION FASTENERS WITH TRANSITION FIT, (REFER TO SRM 51−40−44). D_SB_576086_5_FBAA_02_02 Figure A-FFBAA - Sheet 02 Flow Chart
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 77 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

FUEL CENTER TANK FR47

RIB1 DATUM REAR SPAR

DATUM RIB1 DATUM REAR SPAR DATUM FR47 FR47



## B **C A**  **A C**  **B**

D_SB_576086_5_BAAA_01_00 

### D **D**

Figure A-FBAAA - Sheet 01 Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 78 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

REAR SPAR DATUM HOLE S HOLE Q HOLE A HOLE C HOLE E HOLE G

HOLE P

HOLE B HOLE D HOLE F

ADJACENT HOLE LH SIDE SHOWN, SAME LOCATION FOR THE RH SIDE ONLY INSTALL THE WASHERS ITEM 3, 6 OR 10 IF YOU FOUND WASHERS DURING THE REMOVAL PROCEDURE HOLE T

D_SB_576086_5_BAAA_02_00 **NOTE:** (16) (17)16 17

(16) (18)16 18

(1) (15) 1 15

(1) (3) 1 3 (4) 4 (1) (3) 1 3 (8) 8 (5) (6) 5 6 (19)19 (5) (6) 5 6 (11)11 (10)10 (12)12 OR (10) (12)10 12 (13)13 (14)14 OR (1) (2) 1 2 (5) (6) 5 6 (5) (6) 5 6 (7) 7 (9) 9



## D

Figure A-FBAAA - Sheet 02 Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 79 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

HOLE ITEM PART NUMBER 2 ASNA2026T9−40 1 A ITEM PART NUMBER ITEM PART NUMBER

1 B C D E F G P Q S T ASNA2532−9

ASNA2532−9 4 ASNA2532−9 3 NSA5369PD916B 1 7 6 NSA5369PD816D ASNA2532−8 5

ASNA2532−9 8 9 3 NSA5369PD916B 6 NSA5369PD816D ASNA2532−8

15 17 18 ASNA2026T9−42 ASNA2026T10−44 ASNA2532−10 ASNA2532−10 **−**

**−**

**−**

**− − −**  **− −** 

16 16 BOLT WASHER NUT TORQUE

5

1 

### DIAMETER NOMINAL HOLES

ASNA2026T9−32 ASNA2026T8−32 ASNA2026T9−30 ASNA2026T8−27 11 6 NSA5369PD816D 5 ASNA2532−8 ASNA2026T8−38 12 10 NSA5369PD816B 13 ASNA2531−8

ASNA2026T10−47 ASNA2027T8−24 19 6 NSA5369PD816D 5 ASNA2532−8 m.daN min/max Lbf.in. min/max 6.7/8.0 593/708

9.6/11.5 4.65/5.55 412/491

850/1018 593/708

593/708

593/708

850/1018 412/491 412/491 412/491

412/491 ASNA2026T8−36 6.7/8.0

6.7/8.0

6.7/8.0 4.65/5.55 4.65/5.55 4.65/5.55

4.65/5.55 9.6/11.5

D_SB_576086_5_BAAA_03_00 Figure A-FBAAA - Sheet 03 Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 80 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

HOLE ITEM PART NUMBER 2 1 A ITEM PART NUMBER ITEM PART NUMBER

1 B C D E F G P Q S T 4 3 1 7 6 5 8 9 3 6

15 17 18 **−**

**−**

**−**

**− − −**  **− −** 

16 16 BOLT WASHER NUT TORQUE

5

1 

### DIAMETER OVERSIZE R1 HOLES

11 6 5 12 10 13

19 6 5 m.daN min/max Lbf.in. min/max 6.7/8.0 593/708

9.6/11.5 4.65/5.55 412/491

850/1018 593/708

593/708

593/708

850/1018 412/491 412/491 412/491

412/491 6.7/8.0

6.7/8.0

6.7/8.0 4.65/5.55 4.65/5.55 4.65/5.55

4.65/5.55 9.6/11.5 NAS1727−9E NAS1727−9E

NAS1727−9E

NAS1727−9E NAS1727−8E

NAS1727−8E

NAS1727−10E NAS1727−10E NAS1727−8E NSA5356−9−40 NSA5356−9−32 NSA5356−8−32 NSA5356−9−30 NSA5356−8−27 NAS1727−8E NSA5356−8−38 NAS1726−8E NSA5356−9−42 NSA5356−10−44 NSA5356−10−47 NSA5357−8−24 NSA5368PD916B NSA5368PD816D NSA5368PD916B NSA5368PD816D

NSA5368PD816D NSA5368PD816B NSA5368PD816B NSA5356−8−36

D_SB_576086_5_BAAA_04_00 Figure A-FBAAA - Sheet 04 Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 81 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

HOLE ITEM PART NUMBER 2 1 A ITEM PART NUMBER ITEM PART NUMBER

1 B C D E F G P Q S T 4 3 1 7 6 5 8 9 3 6

15 17 18 **−**

**−**

**−**

**− − −**  **− −** 

16 16 BOLT WASHER NUT TORQUE

5

1 

### DIAMETER OVERSIZE R2 HOLES

11 6 5 12 10 13

19 6 5 m.daN min/max Lbf.in. min/max 6.7/8.0 593/708

9.6/11.5 4.65/5.55 412/491

850/1018 593/708

593/708

593/708

850/1018 412/491 412/491 412/491

412/491 6.7/8.0

6.7/8.0

6.7/8.0 4.65/5.55 4.65/5.55 4.65/5.55

4.65/5.55 9.6/11.5 NAS1727−9E NAS1727−9E

NAS1727−9E

NAS1727−9E NAS1727−8E

NAS1727−8E

NAS1727−10E NAS1727−10E NAS1727−8E NSA5358−9−40 NSA5358−9−32 NSA5358−8−32 NSA5358−9−30 NSA5358−8−27 NAS1727−8E NSA5358−8−38 NAS1726−8E NSA5358−9−42 NSA5358−10−44 NSA5358−10−47 NSA5359−8−24 NSA5368PD916B NSA5368PD816D NSA5368PD916B NSA5368PD816D

NSA5368PD816D NSA5368PD816B NSA5368PD816B NSA5358−8−36

D_SB_576086_5_BAAA_05_00 Figure A-FBAAA - Sheet 05 Inspection of the Holes A, B, C, D, E, F, G, P, Q, S and T (adjacent to the Hole G), at LH and RH Internal Angle of the Center Wing Box DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 82 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

FR47



## A **A**

FR40 

### B **B**

HOLES TO BE INSPECTED : HOLES TYPE 1: FATIGUE CRACKS 3 mm (0.118 in.) **NOTE:** HOLES TYPE 2: FATIGUE CRACKS 4 mm (0.157 in.) HOLES TYPE 3: FATIGUE CRACKS 5 mm (0.197 in.) LH SIDE SHOWN RH SIDE SYMMETRICAL **FWD**

D_SB_576086_5_CAAA_01_00 

## B FR47

RIB1

Figure A-FCAAA - Sheet 01 Ultrasonic Inspection of the Holes type 1, type 2 and type 3.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 83 5

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# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 84 5

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# @A300-600 SERVICE BULLETIN Appendix 01 **CONF ALL The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to airbus dept. SEES1, on the attached inspection.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN Appendix 01
**CONF ALL

NOTE: LH SIDE SHOWN, SAME LOCATION FOR THE RH SIDE

SERVICE BULLETIN AREA REPAIRED IN ACCORDANCE WITH : LEFT SIDE HOLES

ON INTERNAL ANGLE HOLE A RIGHT SIDE NO CRACK DEPTH CRACK CRACKED COMPONENT REAR SPAR DATUM HOLE G HOLE E HOLE C HOLE A HOLE S

HOLE P HOLE B HOLE D HOLE F

REAR SPAR FITTING ANGLE

BOTTOM PANEL HOLE Q

FITTING ANGLE LENGTH

DEPTH OF THE CRACK TYPICAL SECTION

HOLE T (ADJACENT TO THE HOLE G) HOLE T (ADJACENT TO THE HOLE G)

PLEASE RECORD OTHER FINDINGS HERE:
D_SB_576086_5_RAAA_01_00 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6086

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : ROTATING PROBE 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

LENGTH OF THE CRACK

STRUCTURAL REPAIR MANUAL HOLE B HOLE C HOLE D HOLE E HOLE F HOLE G HOLE P HOLE Q HOLE S

Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN Appendix 02 **CONF ALL This chart is only a proposal, operators may determine that an another way to do the work is more suitable for them.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN Appendix 02
**CONF ALL
**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A300−600 57−6086**

SB ELAPSED TIME (HOURS) MH PER ET/S

TOTAL MANHOURS (MH) ELAPSED TIME (ET) 30.00 26.00 2.00 1 2.00

0 GET ACCESS 12.00 1 12.00

5 10 0.50 1 0.50

9.50 1 9.50 CLOSE−UP TEST

15 20 25 30 35 01 02

STEPS

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. MANHOURS GIVEN IN VENDOR SERVICE BULLETINS ARE NOT REFLECTED IN THIS GANTT CHART. 01
02 **NOTES:**

: : REPAIR THE CRACKS OF THE HOLES AT THE LH INTERNAL ANGLE OF THE CENTER WING BOX

2.00 1 2.00 REPAIR THE CRACKS OF THE HOLES AT THE RH INTERNAL ANGLE OF THE CENTER WING BOX
2.00 1 2.00 REPAIR THE CRACK OF THE HOLE T AT THE LH INTERNAL ANGLE OF THE CENTER WING BOX

2.00 1 2.00 REPAIR THE CRACK OF THE HOLE T AT THE LH INTERNAL ANGLE OF THE CENTER WING BOX

D_SB_576086_5_APAA_01_00 Figure A-FAPAA - Sheet 01 Gantt Chart for the Repair
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN Appendix 03 **CONF ALL This chart is only a proposal, operators may determine that an another way to do the work is more suitable for them.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN Appendix 03
**CONF 001
**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A300−600 57−6086**

SB ELAPSED TIME (HOURS) MH PER ET/S

TOTAL MANHOURS (MH) ELAPSED TIME (ET) 35.00 28.50 4.00 1 4.00

0 GET ACCESS 12.00 1 12.00

5 10 0.50 1 0.50
9.50 1 9.50 CLOSE−UP TEST

15 20 25 30 35 STEPS

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. MANHOURS GIVEN IN VENDOR SERVICE BULLETINS ARE NOT REFLECTED IN THIS GANTT CHART. **NOTES:**

: : INSPECTION OF THE HOLES AT THE LH INTERNAL ANGLE OF THE CENTER WING BOX 4.00 1 4.00 INSPECTION OF THE HOLES AT THE RH INTERNAL ANGLE OF THE CENTER WING BOX 0.50 1 0.5 INSPECTION OF THE HOLE T AT THE LH INTERNAL ANGLE OF THE CENTER WING BOX 0.50 1 0.5 INSPECTION OF THE HOLE T AT THE RH INTERNAL ANGLE OF THE CENTER WING BOX 2.00 1 2.00 UTRASONIC INSPECTION OF THE HOLES AT THE LH INTERNAL ANGLE OF THE CENTER WING BOX 2.00 1 2.00 UTRASONIC INSPECTION OF THE HOLES AT THE RH INTERNAL ANGLE OF THE CENTER WING BOX

D_SB_576086_5_ARAA_01_00 01 02

01
02 Figure A-FARAA - Sheet 01 Gantt Chart for the Inspection
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECT REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE. MODIFICATION No.: None 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 embodiment:

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: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate 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: SDC32 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: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN QUALITY PERCEPTION FORM 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 further 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 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - 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 Operator Supplied X Mod/Inspection X Manpower X Industry support 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 : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086 REVISION No.: 05 - Jan 30/12 Page: 1 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.