@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

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

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

REVISION No.: 05 - Jan 30/12 Page: 1

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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

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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

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

REVISION No.: 05 - Jan 30/12 Page: 3

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

REVISION No.: 05 - Jan 30/12 Page: 4

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

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

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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

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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

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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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

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

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

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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

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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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

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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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

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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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 :

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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SERVICE BULLETIN

Threshold (whichever occurs Interval (whichever occurs first)

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.

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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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 .

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

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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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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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This Page Intentionally Left Blank

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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.

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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

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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.

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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

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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

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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

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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.

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(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

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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).

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**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

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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

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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-FBAAA and 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

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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

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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

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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

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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

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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

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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-FBAAA and 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

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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

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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

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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

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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

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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

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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-FBAAA and 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

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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

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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-FBAAA and 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

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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

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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

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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

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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-FBAAA and 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

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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

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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

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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

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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-FBAAA and 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

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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

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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

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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

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(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-FBAAA and 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

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(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

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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-FBAAA and 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

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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

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(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

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**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

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(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

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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

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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

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(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

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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

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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

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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

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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

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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

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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

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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

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(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

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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

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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

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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

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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

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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

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(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

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

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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

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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

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SERVICE BULLETIN

**CONF 002

None

DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086

REVISION No.: 05 - Jan 30/12 Page: 75

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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

NO CRACKS FINDING 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

NO CRACKS FINDING YES

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

No. 57−6050 NO PARA. E.(2). TABLE 1.

SERVICE BULLETIN

ACCOMPLISHMENT

AND

YES

INSPECTION

AS PER SB No.57−6102

MEASURE THE DIAMETER

OF THE HOLE.

YES CRACKS FINDING NO

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

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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 YES NO REMOVED

INSTALL WITH THE R1 (*)

OVERSIZE FASTENERS

REAM UP TO THE R2 OVERSIZE

TO REMOVE THE CRACKS.

CRACK YES NO 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

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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

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@A300-600

SERVICE BULLETIN

**CONF ALL

REAR SPAR DATUM

HOLE S

HOLE G HOLE E HOLE C HOLE A HOLE Q

HOLE P

HOLE F HOLE D HOLE B

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

OR (14)14

(1)

(2)

1

2

(5)

(6)

5

6

(5)

(6)

5

6

(9) 9 (7) 7

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

HOLE

ITEM PART NUMBER

A 2 ASNA2026T9−40 1

ITEM PART NUMBER ITEM PART NUMBER

1

B

C

D

E

F

G

P

Q

S

T

ASNA2532−9

ASNA2532−9

4 3 NSA5369PD916B 1 ASNA2532−9

7 6 NSA5369PD816D 5 ASNA2532−8

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

12 ASNA2026T8−38 10 NSA5369PD816B 13 ASNA2531−8

ASNA2026T10−47

19 ASNA2027T8−24 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

A 2 1

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

A 2 1

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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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 F HOLE D HOLE B HOLE P

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

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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

CLOSE−UP 9.50 1 9.50

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

CLOSE−UP 9.50 1 9.50

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

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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

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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

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