@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 - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION

AT RIB 1

MODIFICATION No.: None

This page transmits Revision No.06 of Service Bulletin No.A300-57-6047

ADDITIONAL WORK

**CONF ALL

REASON

Revision No. 06 issued to delete reference to MPD 571066 and to modify the threshold and Interval.

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-FSAAA Minor editorial or document structure change N

Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLA01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 2

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REVISION TRANSMITTAL SHEET

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 576047- 832-801-001-Inspection Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 576047-839-001-001 Minor editorial or document structure change N

Subtask 576047-910-001-001 Minor editorial or document structure change N

Subtask 576047-941-001-001 Minor editorial or document structure change N

Subtask 576047-832-001-001 Minor editorial or document structure change N

Subtask 576047-832-006-001 Minor editorial or document structure change N

Subtask 576047-832-002-001 Minor editorial or document structure change N

Subtask 576047-832-003-001 Minor editorial or document structure change N

Subtask 576047-833-003-001 Minor editorial or document structure change N

Subtask 576047-833-004-001 Minor editorial or document structure change N

Subtask 576047-833-006-001 Minor editorial or document structure change N

Subtask 576047-833-005-001 Minor editorial or document structure change N

Subtask 576047-833-001-001 Minor editorial or document structure change N

Subtask 576047-833-002-001 Minor editorial or document structure change N

Subtask 576047-700-001-001 Minor editorial or document structure change N

Subtask 576047-942-002-001 Minor editorial or document structure change N

Fig. A-FBAAA Minor editorial or document structure change N

Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FFAAA Minor editorial or document structure change N

Fig. A-FFAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FFAAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBBAA Minor editorial or document structure change N

Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBCAA Minor editorial or document structure change N

Fig. A-FBCAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBGAA Minor editorial or document structure change N

Fig. A-FBGAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBDAA Minor editorial or document structure change N

Fig. A-FBDAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBEAA Minor editorial or document structure change N

Fig. A-FBEAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBFAA Minor editorial or document structure change N

Fig. A-FBFAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBFAA Sheet 02 Minor editorial or document structure change N

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Appendix 1- Inspection Report -

APPENDIX CONTENT Minor editorial or document structure change N

Fig. A-FRAAA Minor editorial or document structure change N

Fig. A-FRAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 02 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 03 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 04 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 05 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 06 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 07 Minor editorial or document structure change N

Fig. A-FRAAA Sheet 08 Minor editorial or document structure change N

Appendix 2- Repair Report -

APPENDIX CONTENT Minor editorial or document structure change N

Fig. A-FRBAA Minor editorial or document structure change N

Fig. A-FRBAA Sheet 01 Minor editorial or document structure change N

Fig. A-FRBAA Sheet 02 Minor editorial or document structure change N

Fig. A-FRBAA Sheet 03 Minor editorial or document structure change N

Fig. A-FRBAA Sheet 04 Minor editorial or document structure change N

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 clarify the permissable limits of rework and to update the effectivity.

Revision No. 02 issued to inform the operators that the compliance has changed into mandatory and

update the effectivity.

Revision No. 03 issued to add aircraft model C4-605R/F, aircraft MSN 775 and 788 for customer CAL

and aircraft 797 for customer JAS.

Revision No. 04 issued to add customers AHK and UPS, to delete MSN 420 and 374, to add MSN 836,

837, 838 and to modify the Figure 4, Table B.

Revision No. 05 issued to modify the Para. Pub. affected, to update the effectivity and to limit the

effectivity as aircraft post production modification 10599S20695 (FUSELAGE - FUSELAGE CENTER

SECTION - WING FUSELAGE JUNCTION - PROVIDE WET INSTALLATION OF FASTENERS) are

now inspected as per MRBR task 571066, to update the Para. Approval and to modify the Figure 4.

REVISION SEQUENCE

ORIGINAL: Jan 04/96

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 4

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REVISION No.: 01 - Oct 16/96

REVISION No.: 02 - Apr 02/99

REVISION No.: 03 - Sep 28/99

REVISION No.: 04 - Mar 01/05

REVISION No.: 05 - May 27/08

REVISION No. : 06 - Oct 17/11

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 5

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 6

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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 - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION

AT RIB 1

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Eight operators of A300 aircraft have reported 20 cases of corrosion on the lower wing root joint during

scheduled maintenance. The aircraft have been in-service between 4 and 10 years. The corrosion was

located in the wing bottom skin inboard and outboard of the external lower surface splice.

One operator of an A310 aircraft has also reported severe corrosion in the same area. Most of the

corrosion was found in the area aft of FR 43 and initiated at the edge of the countersinks of the

fasteners.

For A300 aircraft, no similar incidents have been reported by the operators.

Most of the corrosion was found in the area aft of FR 43, althought corrosion has also been found

forward of this area. The corrosion initiated at the edge of the contersinks of the fasteners.

This Service Bulletin recommends a detailed visual inspection of the rib 1 external lower surface splice,

between FR 40 and FR 47. Repair of the corrosion damage is by local blend-out and spotfacing.

Once the corrosion has been removed, if the corrosion damage exceeds a certain limit, there would be

a reduction in strenght margins, which could lead to cracking from the fastener holes. Non Destructive

Testing or detailed visual inspections are then necessary to detect the presence of cracks around the

fastener holes. A fatigue program inspection has been developed in this Service Bulletin to cover this

possibility.

Accomplishement of this Service Bulletin permits detection of corrosion in the wing bottom skin at an

early stage. This will avoid extensive corrosion damage, resulting in extensive rework and/or repairs

and possible fatigue cracks in the future.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

5

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@A300-600

SERVICE BULLETIN

SUMMARY

This inspection is recommended at a threshold of 5 years, with a repetitive inspection of 5 years. For

aircraft exceeding 5 years, the first inspection is to be performed within 6 months after receipt of this

Service Bulletin.

After corrosion removal, a repetitive inspection for possible fatigue damaged is recommended. The

thresholds and intervals given for the fatigue inspection depend on the results of the corrosion

inspection.

Previous issue of this Service Bulletin was rendered mandatory by Airworthiness Directive No.

2008-0208R1.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

30T 83V AAL ABD AIB AMU BCS CES F2I FDX G8E IRA IRM

JAL KAC KAL MON MSR OHY QTR RNV SUD TAR THA UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 53.15.00.021

OEB None

AOT None

SIL 38-013

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 2

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SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

Task 576047-832-801-001: Inspection

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 3.75

APPENDICES

Appendix 1- Inspection Report -

Appendix 2- Repair Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 3

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

A

B

FR40

FR47

RIB1

AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA

OUTBOARD AREA

EXTERNAL LOWER

SURFACE SPLICE

B

D_SB_576047_5_SAAA_01_00

A

A

Figure A-FSAAA - Sheet 01

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 4

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

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION

AT RIB 1

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 C4-620

(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 0459-0466 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

(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: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

30T 0626 0643

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

CES 0521 0525 0532 0707

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0461 0518

0606 0610 0645

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

G8E 0462 0465 0469 0506 0509 0513 0514 0516

IRA 0632 0696

IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701

JAL 0602 0617 0683 0703

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692

MON 0540 0556 0604 0605

MSR 0561 0607

OHY 0584 0603

QTR 0554 0560 0614

RNV 0464

SUD 0666

TAR 0505 0558 0563

THA 0566 0569 0577 0628 0629 0635 0681 0705

UZB 0717

(4) Configuration by MSN

MSN CONFIGURATION

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351

0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417

0423 0459 0460 0461 0462 0463 0464 0465 0466 0469 0470

0474 0477 0479 0505 0506 0507 0508 0509 0510 0511 0512

0513 0514 0515 0516 0517 0518 0521 0525 0529 0530 0532

0536 0540 0543 0546 0553 0554 0555 0556 0557 0558 0559

0560 0561 0563 0566 0569 0572 0575 0577 0579 0581 0582

0584 0602 0603 0604 0605 0606 0607 0608 0609 0610 0611

0612 0613 0614 0615 0617 0618 0621 0623 0625 0626 0627

0628 0629 0630 0631 0632 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

001

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 2

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@A300-600

SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA02 1

Consumable CMLA03 1

Consumable CMLA04 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Eight operators of A300 aircraft have reported 20 cases of corrosion on the lower wing

root joint during scheduled maintenance. The aircraft have been in-service between 4

and 10 years. The corrosion was located in the wing bottom skin inboard and outboard

of the external lower surface splice.

One operator of an A310 aircraft has also reported severe corrosion in the same area.

Most of the corrosion was found in the area aft of FR 43 and initiated at the edge of the

countersinks of the fasteners.

For A300 aircraft, no similar incidents have been reported by the operators.

Most of the corrosion was found in the area aft of FR 43, althought corrosion has also

been found forward of this area. The corrosion initiated at the edge of the contersinks of

the fasteners.

(2) Objective/Action

This Service Bulletin recommends a detailed visual inspection of the rib 1 external lower

surface splice, between FR 40 and FR 47. Repair of the corrosion damage is by local

blend-out and spotfacing.

Once the corrosion has been removed, if the corrosion damage exceeds a certain limit,

there would be a reduction in strenght margins, which could lead to cracking from the

fastener holes. Non Destructive Testing or detailed visual inspections are then necessary

to detect the presence of cracks around the fastener holes. A fatigue program inspection

has been developed in this Service Bulletin to cover this possibility.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 3

5

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SERVICE BULLETIN

(3) Advantages

Accomplishement of this Service Bulletin permits detection of corrosion in the wing

bottom skin at an early stage. This will avoid extensive corrosion damage, resulting in

extensive rework and/or repairs and possible fatigue cracks in the future.

(4) Operational/Maintenance Consequences

This inspection is recommended at a threshold of 5 years, with a repetitive inspection of

5 years. For aircraft exceeding 5 years, the first inspection is to be performed within 6

months after receipt of this Service Bulletin.

After corrosion removal, a repetitive inspection for possible fatigue damaged is

recommended. The thresholds and intervals given for the fatigue inspection depend on

the results of the corrosion inspection.

Previous issue of this Service Bulletin was rendered mandatory by Airworthiness

Directive No. 2008-0208R1.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 576047-832-801-001: Inspection

(1) Do a Detailed Inspection of rib 1 between FR40 and FR47

(2) Do a Detailed Inspection of the Protection

(3) Do a Detailed Inspection of the rework depth of rib 1 between FR40 and FR47

(4) Do a Non Destructive Test of rib 1 between FR40 and FR47

(5) Do a Surface Treatment for a New Protection Coating

(6) Remove the corrosion of rib 1 between FR40 and FR47

(7) Do a Surface Treatment for a New Protection Coating ( D =< 5% )

(8) Do a Surface Treatment for a New Protection Coating ( 5% < D =< d )

(9) Replace the Fasteners

(10) Do the Sealing

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 4

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(2) Accomplishment Timescale

Condition Action Compliance Time Repetitive

Interval

Config.001 Do a Detailed Inspection of rib

1 between FR40 and FR47,

refer to subtask

576047-832-001-001

See Note (1) In 5 years

Corrosion is not detected

and the protection is not

missing or damaged

Do a repeat Inspection for

corrosion

In 5 years None

Corrosion is not detected

and the protection is missing

or damaged

Do a Surface Treatment for a

New Coating, Refer to Subtask

576047-833-003-001

and

Do the Sealing, Refer to

Subtask 576047-833-002-001

Before next flight None

Corrosion is detected Remove the corrosion of rib 1

between FR40 and FR 47,

Refer to Subtask

576047-833-004-001

See Note (2)

Before next flight None

The rework is not the

permissible limits

Contact AIRBUS Before next flight None

The reworked depth (D) is

higher than permissible limit

of the reworked depth per

area (d)

Contact AIRBUS Before next flight None

The reworked depth (D) is

less or equal to 5 % of the

initial thickness of the panel

(E)

Do a Surface Treatment for a

New Protection Coating (5%

=< D), Refer to Subtask

576047-833-006-001

and

Do the Sealing, Refer to

Subtask 576047-833-002-001

Before next flight None

The reworked depth (D) is

higher than 5 % of the initial

thickness of the panel (E)

and less or equal to the

permissible limit of the

reworked depth per area (d)

and cracks are not detected

Do a Surface Treatment for a

New Protection Coating (5% <

D =< d), Refer to Subtask

576047-833-005-001

and

Inspect for fatigue damage:

Refer to Fig.A-BGAA Sheet 01

and

Do the Sealing, Refer to

Subtask 576047-833-002-001,

See Note(3)

Before next flight None

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 5

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SERVICE BULLETIN

Condition Action Compliance Time Repetitive

Interval

The reworked depth (D) is

higher than 5 % of the initial

thickness of the panel (E)

and less or equal to the

permissible limit of the

reworked depth per area (d)

and cracks are detected

Contact AIRBUS Before next flight None

Table 1, Detailed Inspection of rib 1 between FR40 and FR47

NOTE (1): The corrosion inspection is to be done on aircraft which have been in

service for 5 years or more from the date of delivery. The inspection

must be repeated every 5 years. Aircraft that have been in service more

than 5 years should be inspected within the timescales given below :

- Aircraft with more than 5 years but less than 15 years service should

be inspected not later than 18 months from receipt of this Service

Bulletin, or at the next C-check, whichever occurs last.

- Aircraft with more than 15 years but less than 20 years service should

be inspected not later than 12 months from receipt of this Service

Bulletin.

- Aircraft with more than 20 years service since delivery should be

inspected within 6 months from receipt of this Service Bulletin.

NOTE (2): If you find corrosion around the fasteners remove and replace the

fasteners, Refer to SUBTASK 576047-833-001-001

NOTE (3): A grace period of 500FC / 1050FH is granted to aircraft which have

exceeded the revised threshold / intervals after receipt of the SB without

exceeding previous SB revision value.

F. APPROVAL

The technical content of this document is approved under the authority of 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.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 6

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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.

Task 576047-832-801-001: Inspection

Get Access 0.50

On Aircraft

Do a Detailed Inspection of rib 1 between FR40 and

FR47

0.25

Do a Detailed Inspection of the Protection 0.25

Do a Detailed Inspection of the rework depth of rib 1

between FR40 and FR47

0.50

Do a Non Destructive Test of rib 1 between FR40 and

FR47

0.50

Do a Surface Treatment for a New Protection Coating 0.50

Remove the corrosion of rib 1 between FR40 and

FR47

0.50

Do a Surface Treatment for a New Protection Coating (

D =< 5% )

0.50

Do a Surface Treatment for a New Protection Coating (

5% < D =< d )

0.50

Replace the Fasteners 1.50

Do the Sealing 1.00

Close-Up 1.00

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 3.75

H. WEIGHT AND BALANCE

None

I. ELECTRICAL LOAD DATA

None

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J. REFERENCES

Airworthiness Directive (AD) Airworthiness Directive No.

2008-0208R1

Aircraft Maintenance Manual (AMM) 12-11-28 24-00-00 24-41-00

28-00-00 28-10-00 28-11-22

28-25-00

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

Non Destructive Test Manual (NTM) 51-10-04 51-10-05 51-10-08

Structural Repair Manual (SRM) 51-22-00 51-23-00 51-23-10

51-23-20 51-40-20 51-40-21

51-40-40 51-40-44 51-40-46

51-40-47 51-43-00 51-49-00

51-74-10 51-75-20 51-76-10

51-76-20 53-23-20

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

No Material Set

C. LIST OF COMPONENTS

No Kit

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 Polysulfid(no

Longeravailable

09-002 As required

Corrosion Inhibitingsealant

Sprayable

09-025 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Wash Primer 16-020 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

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F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the tools listed in NTM and

SRM tasks mentioned in paragraphs:

- Equipment and materials for inspection, refer to NTM 51-10-04, NTM 51-10-05 and

NTM 51-10-08.

- Equipment and tools for repair, refer to SRM 51-40-21, SRM 51-40-44, SRM 51-40-47,

SRM 51-43-00and SRM 51-74-10.

(3) Special Tools

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 576047-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON 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.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

Zone

541 641

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 3.75

A. GENERAL

(1) Subtask 576047-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 576047-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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References

Structural Repair Manual (SRM) 51-23-00

51-23-10

51-23-20

51-40-20

51-40-21

51-40-40

51-40-44

51-40-46

51-40-47

51-49-00

51-75-20

(a) If paint stripping is required (Refer to SRM 51-75-20).

(b) To drill and deburr the holes (Refer to SRM 51-40-40 and SRM 51-40-44).

(c) Countersinking (Refer to SRM 51-40-46 and SRM 51-40-47).

(d) Data for installation and removal fasteners (Refer to SRM 51-40-20 and SRM

51-40-21).

(e) To torque standard threaded fasteners (Refer to SRM 51-49-00).

(f) If paint coating is required (Refer to SRM 51-23-00, SRM 51-23-10 and SRM

51-23-20).

B. PREPARATION

(1) Subtask 576047-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-41-00

28-00-00, Page Block 301

28-10-00, Page Block 301

28-11-22, Page Block 401

28-25-00, Page Block 301

(a) De-energize the aircraft electrical network and connect the aircraft to ground (Refer

to AMM 24-41-00 and AMM 24-00-00, Page Block 301).

(b) Put the access platforms in position.

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WARNING: TO REPLACE THE FASTENERS, DRAIN THE CENTER AND INNER

FUEL TANKS.

BEFORE UNDERTAKING MAINTENANCE WORK ON THE FUEL

SYSTEM, PERSONNEL MUST RIGOROUSLY OBSERVE THE

FOLLOWING SAFETY PRECAUTIONS. THE DESCRIPTIONS SHOULD

BE READ AT THE SAME TIME AS THE SPECIAL INSTRUCTIONS

AND SAFETY MEASURES CONCERNING SPECIFIC MAINTENANCE

PROCEDURES AND, IN PARTICULAR, THE FOLLOWING

OPERATIONS :

NOTE: The operations below are necessary only if the fasteners are removed,

refer to SUBTASK 576047-833-001 001 Replace the Fasteners .

1 General servicing precaution (Refer to AMM 28-00-00, Page Block 301).

2 Tank defueling (Refer to AMM 28-25-00, Page Block 301).

3 Access to fuel tanks (Refer to AMM 28-10-00, Page Block 301).

4 Manhole cover removal the 541AB, 542 CB, 641AB and 642CB (Refer to AMM

28-11-22, Page Block 401).

5 Fuel tank working area (Refer to AMM 28-10-00, Page Block 301).

6 Use of flammable gas detection devices (Refer to AMM 28-10-00, Page Block 301).

7 Fuel tank ventilation (Refer to AMM 28-10-00, Page Block 301).

C. PROCEDURE

(1) Subtask 576047-832-001-001 - Do a Detailed Inspection of rib 1 between FR40 and

FR47

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

(a) At the threshold given in the Planning Information Paragraph E.(2) :

On the center wing bottom skin, inboard and outboard areas of rib 1 between

frames 40 and 47, do a Detailed Inspection for corrosion around the fasteners and

on the surface of panels without stripping off paint.

1 If no corrosion is detected :

- Check condition of paint finish, touch up if necessary, refer to SUBTASK

576047-832-006 001 Do a Detailed Inspection of the Protection .

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2 If corrosion is detected :

- Refer to SUBTASK 576047-833-004 001 Remove the corrosion of rib 1

between FR40 and FR47 .

(2) Subtask 576047-832-006-001 - Do a Detailed Inspection of the Protection

Work Zones and Access Panels

Zone Access/Work location

541 Work location from Frame 40 to Frame 47

641 Work location from Frame 40 to Frame 47

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

(a) If protection is missing or damaged :

- Refer to SUBTASK 576047-833-003 001 Do a Surface Treatment for a New

Protection Coating .

(b) If protection is not missing or not damaged :

- Next Visual inspection for corrosion in 5 years.

(3) Subtask 576047-832-002-001 - Do a Detailed Inspection of the rework depth of rib 1

between FR40 and FR47

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-08 part 6

Structural Repair Manual (SRM) 51-23-00

51-23-10

53-23-20

Fig. A-FBCAA

Permissible Limits of the Reworked

Depth

Sheet 01

Fig. A-FBGAA

Inspection Program

Sheet 01

NOTE: At the threshold given in the Planning Information Paragraph E.(2) :

In this part of the inspection, the reference value is reworked depth (D)

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(result of corrosion inspection, SUBTASK 576047-832-001 001 Do a

Detailed Inspection of rib 1 between FR40 and FR47 . The permissible

limits (5%, d) are reference values with respect to the initial thickness of

the panel (E). Permissible limit of reworked depth (D), 5% of the initial

thickness of the panels (E), permissible limit of reworked depth per area

(d) :

Refer to Fig. A-FBCAA Sheet 01

Check the reworked depth (D) with respect to the initial thickness of the

panel (E), and the permissible limit of the reworked depth per area (d)

previously defined.

NOTE: According to damaged areas, permissible limits of the reworked depth

are specified :

Refer to Fig. A-FBCAA Sheet 01

(a) If the reworked depth (D) is higher than 5% of the initial thickness of the panel (E)

and less or equal to the permissible limit of the reworked depth per area (d), refer

to SUBTASK 576047-832-003 001 Do a Non Destructive Test of rib 1 between

FR40 and FR47 .

(b) If the reworked depth (D) is less or equal to 5 percent of the initial thickness of the

panel (E), refer to SUBTASK 576047-833-006 001 Do a Surface Treatment for a

New Protection Coating ( D =< 5% ) .

(c) If the reworked depth (D) is higher than permissible limit of the reworked depth per

area (d) :

- Contact AIB before next flight.

(4) Subtask 576047-832-003-001 - Do a Non Destructive Test of rib 1 between FR40

and FR47

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-08 Part 6

Structural Repair Manual (SRM) 51-23-00

51-23-10

51-23-20

Fig. A-FBCAA

Permissible Limits of the Reworked

Depth

Sheet 01

Fig. A-FBGAA

Inspection Program

Sheet 01

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(a) The reworked depth (D) is higher than 5% of the initial thickness of the panel (E)

and less or equal to the permissible limit of the reworked depth per area (d) :

Refer to Fig. A-FBCAA Sheet 01

Detect presence of crack around the fasteners and on the surface of forward and

aft lower surface panels. Do a Non Destructive Test (NDT) for fatigue damage,

refer to NTM 51-10-08 Part 6.

1 If crack is detected :

- Contact AIB before the next flight.

2 If no crack is detected :

- Refer to SUBTASK 576047-833-005 001 Do a Surface Treatment for a

New Protection Coating ( 5% < D =< d ) .

(5) Subtask 576047-833-003-001 - Do a Surface Treatment for a New Protection

Coating

Work Zones and Access Panels

Zone Access/Work location

541 Work location from Frame 40 to Frame 47

641 Work location from Frame 40 to Frame 47

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Wash Primer 16-020 As required

References

Structural Repair Manual (SRM) 51-23-00

51-23-10

51-23-20

(a) Apply :

Wash Primer 16-020 As required

and

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Anti-Corrosion

Primer

(polyurethane)

16-001 As required

(b) Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM

51-23-20.

- Next visual inspection for corrosion in 5 years.

(6) Subtask 576047-833-004-001 - Remove the corrosion of rib 1 between FR40 and

FR47

Work Zones and Access Panels

Zone Access/Work location

541 Work location from Frame 40 to Frame 47

641 Work location from Frame 40 to Frame 47

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-04 Part 4

51-10-05 Part 1

Structural Repair Manual (SRM) 51-22-00

51-40-20

51-40-21

51-74-10

Fig. A-FBBAA

Evaluation Principle of Corrosion

Sheet 01

For the correspondence of the different reference values used in this part of the

inspection (W, L, delta 1, delta 2, D) :

Refer to Fig. A-FBBAA Sheet 01

These values enable to determine the rework conditions and also to check the

permissible limits.

W : Rework length in flight direction

L : Rework length in outboard direction

Delta 1 : Distance between two adjacent rework areas in flight direction

Delta 2 : Distance between two adjacent rework areas in outboard direction

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(a) Remove the corrosion, refer to SRM 51-22-00 and SRM 51-74-10. Obey the rework

conditions specified below.

REWORK CONDITIONS

Refer to Fig. A-FBBAA Sheet 01

L/2 > 4 (D)

And

w/2 > 4 (D)

NOTE: If you find corrosion around the fasteners, remove the fasteners,

refer to SRM 51-40-20 and SRM 51-40-21.

(b) Measure the reworked depth (D), do a Non Destructive Test (NTD), refer to NTM

51-10-04 Part 4 or NTM 51-10-05 Part 1.

(c) Make sure that the rework is in the permissible limits specified below.

REWORK PERMISSIBLE LIMITS

Refer to Fig. A-FBBAA Sheet 01

W < 50 mm (1.968 in.)

L < 100 mm (3.937 in.)

Delta 1 > 50 mm (1.968 in.)

Delta 2 > not limited

1 If the rework is not in the permissible limits :

- Contact AIB before the next flight.

2 If the rework is in the permissible limits :

- Continue the inspection, refer to SUBTASK 576047-832-002 001 Do a

Detailed Inspection of the rework depth of rib 1 between FR40 and FR47 .

(7) Subtask 576047-833-006-001 - Do a Surface Treatment for a New Protection

Coating ( D =< 5% )

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(polyurethane)

16-001

Wash Primer 16-020 As required

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References

Structural Repair Manual (SRM) 51-23-00

51-23-10

51-23-20

Fig. A-FBGAA

Inspection Program

Sheet 01

Fig. A-FBCAA

Permissible Limits of the Reworked

Depth

Sheet 01

(a) The reworked depth (D) is less or equal to 5 percent of the initial thickness of the

panel :

Refer to Fig. A-FBCAA Sheet 01

1 Apply :

Wash Primer 16-020 As required

and

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

2 Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM

51-23-20.

NOTE: Replace the fastener if they have been removed for the

corrosion inspection, refer to SUBTASK 576047-833-001 001

Replace the Fasteners .

- Next visual inspection for corrosion in 5 years.

(8) Subtask 576047-833-005-001 - Do a Surface Treatment for a New Protection

Coating ( 5% < D =< d )

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Wash Primer 16-020 As required

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References

Non Destructive Test Manual (NTM) 51-10-08 Part 6

Structural Repair Manual (SRM) 51-23-00

51-23-10

51-23-20

Fig. A-FBGAA

Inspection Program

Sheet 01

(a) Apply on countersunk heads and reworked areas :

Wash Primer 16-020 As required

and

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

(b) Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM

51-23-20.

NOTE: Replace the fastener if they have been removed for the corrosion

inspection, refer to SUBTASK 576047-833-001 001 Replace the

Fasteners .

(c) Inspection program :

- Next visual inspection for corrosion in 5 years.

- Next inspection for fatigue damage :

Refer to Fig. A-FBGAA Sheet 01

NOTE: According to damaged areas, the fatigue inspection program gives

the thresholds and intervals (FC or FH whichever comes first)

applicable to the visual check or the Non Destructive Test (NDT) :

Refer to Fig. A-FBGAA Sheet 01

(9) Subtask 576047-833-001-001 - Replace the Fasteners

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 0.75

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

Polysulfid(no

Longeravailable

09-002 As required

Corrosion Inhibitingsealant

Sprayable

09-025 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Wash Primer 16-020 As required

References

Non Destructive Test Manual (NTM) 51-10-04 part 4

51-10-05 part 1

Structural Repair Manual (SRM) 51-23-00

51-23-10

51-23-20

51-40-40

51-40-44

51-40-46

51-40-47

51-43-00

51-76-10

51-76-20

Fig. A-FBDAA

Replacement Principle of Fasteners and

Sealing principle

Sheet 01

Fig. A-FBEAA

Location of Existing Fasteners on

Forward and Aft Lower Surface Panels

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBFAA

Location of Existing Fasteners on

Forward and Aft Lower Surface Panels

Sheet 01

Sheet 02

NOTE: Replace fasteners of damaged holes when sitting is not correct or/and

the fasteners have been removed for rework.

The reference value is the remaining thickness of the panel (X).

The permissible remaining thickness varies depending on the fastener

replacement area.

Permissible remaining thickness minimum thickness (X) for the forward

lower surface panel : 3.5 mm (0.138 in.) mini.

Permissible remaining thickness minimum thickness (X) for the aft lower

surface panel : 4.5 mm (0.177 in.) mini.

The remaining minimun thickness (X) is the panel thickness below the

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head of the fastener.

Refer to Fig. A-FBDAA Sheet 01, View A and B

(a)

CAUTION: BEFORE YOU DO THE NEW COUNTERSINK OR THE

SPOTFACING FOR THE NEW FASTENER, REFER TO Fig.

A-FBDAA Sheet 01, DO A CHECK OF THE REMAINING

THICKNESS (X) REFER TO NON DESTRUCTIVE TEST (NDT),

REFER TO NTM 51-10-04 part 4 and NTM 51-10-05 part 1.

If the remaining minimum panel thickness is in the permissible limits :

- Install an oversize countersunk head fastener :

Refer to Fig. A-FBDAA Sheet 01, View A

FWD LOWER SURFACE PANEL

X => 3.5 mm (138 in.)

and

AFT LOWER SURFACE PANEL

X => 4.5 mm (0.177 in.)

Do the subsequent steps to install an oversize countersunk head fastener.

1 Drill and deburr the holes, refer to SRM 51-40-40 and SRM 51-40-44.

2 Perform the new contersink for an oversize countersunk head fastener, refer

to SRM 51-40-46 and SRM 51-40-47.

3 Do wet assembly of all parts and fasteners to be installed with :

Corrosion

Inhibitingsealant

Sprayable

09-025 As required

Refer to SRM 51-76-10 and SRM 51-76-20

4 Torque standard threaded fasteners, refer to SRM 51-43-00.

5 Apply on countersunk heads and reworked areas :

Wash Primer 16-020 As required

and

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

NOTE: According to damaged areas, for each type of existing fastener

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to be replaced and associated tables which give the alternative

fastener identification (First oversize or second oversize).

Refer to Fig. A-FBEAA Sheet 01, Fig. A-FBEAA Sheet 02,

Fig. A-FBEAA Sheet 03, Fig. A-FBFAA Sheet 02 and Fig. AFBFAA Sheet 01

6 Apply on the head of the fasteners :

Fuel Tank Sealant

Polysulfid(no

Longeravailable

09-002 As required

Make sure that the sealant does not come out of the skin :

Refer to Fig. A-FBDAA Sheet 01, View B

7 Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM

51-23-20.

(b) If the remaining minimum panel thickness is not in the limits to install an oversize

contersunk head fastener :

- Install an oversize protruding head fastener :

Refer to Fig. A-FBDAA Sheet 01, View B

FWD LOWER SURFACE PANEL

X = > 3.5 mm (138 in.)

and

AFT LOWER SURFACE PANEL

X => 4.5 mm (0.177 in.)

Do the subsequent steps to install an oversize protruding head fastener.

1 Drill and deburr the holes, refer to SRM 51-40-40 and SRM 51-40-44.

2 Do a spotfacing to insure a good seating for an oversize protruding head

fastener

3 Do wet assembly of all parts and fasteners to be installed with (Refer to SRM

51-76-10 and SRM 51-76-20) :

Corrosion

Inhibitingsealant

Sprayable

09-025 As required

4 Torque standard threaded fasteners, refer to SRM 51-43-00.

5 Apply on countersunk heads and reworked areas :

Wash Primer 16-020 As required

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 23

5

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@A300-600

SERVICE BULLETIN

and

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

NOTE: According to damaged areas, for each type of existing fastener

to be replaced and associated tables which give the alternative

fastener identification (First oversize or second oversize).

Refer to Fig. A-FBEAA Sheet 01, Fig. A-FBEAA Sheet 02,

Fig. A-FBEAA Sheet 03, Fig. A-FBFAA Sheet 02 and Fig. AFBFAA Sheet 01

6 Apply on the head of the fasteners :

Fuel Tank Sealant

Polysulfid(no

Longeravailable

09-002 As required

Make sure that the sealant does not come out of the skin :

Refer to Fig. A-FBDAA Sheet 01, View B

7 Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM

51-23-20.

(10) Subtask 576047-833-002-001 - Do the Sealing

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 0.50

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

Polysulfid(no

Longeravailable

09-002 As required

(a) Along the external lower surface splice and fuselage pick-up angle, apply :

Fuel Tank Sealant

Polysulfid(no

Longeravailable

09-002 As required

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 24

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@A300-600

SERVICE BULLETIN

D. TEST

(1) Subtask 576047-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

None

E. CLOSE-UP

(1) Subtask 576047-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301

24-00-00, Page Block 301

24-41-00

28-11-22, Page Block 401

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

equipment.

(b) Install the manhole covers, refer to AMM 28-11-22, Page Block 401.

(c) Fill the fuel tank, refer to AMM 12-11-28, Page Block 301.

(d) Make an inspection for leaks of the manhole cover.

(e) Remove the access platforms.

(f) De-energize the aircraft electrical circuits and disconnect the electrical groundconnection (Refer to AMM 24-41-00 and AMM 24-00-00, Page Block 301).

(g) Write in the applicable aircraft records that you have done all the work given in this

service bulletin.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 25

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@A300-600

SERVICE BULLETIN

**CONF ALL

D_SB_576047_5_BAAA_01_00

A

B

FR40

FR47

RIB1

AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA

OUTBOARD AREA

INSPECT A

WIDE OF 50 mm

(1.968 in.) ONLY

EXTERNAL LOWER

SURFACE SPLICE

MANHOLE

COVER

541 AB/541 AB

MANHOLE

COVER

542 CB/542 CB

B

FWD LOWER

SURFACE PANEL

AFT LOWER

SURFACE PANEL

A

A

Figure A-FBAAA - Sheet 01

Areas to Be Inspected

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 26

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

DO A DETAILLED VISUAL INSPECTION FOR CORROSION

AROUND THE FASTENERS AND ON THE SURFACE OF PANELS

NO YES

REMOVE THE CORROSION

(REFER TO SRM 51−22−00

ON THE CENTER WING BOTTOM SKIN, AT INBOARD AND

OUTBOARD AREAS OK RIB1 BETWEEN FR40 AND FR47.

MAKE SURE THAT THE REWORK IS

IN THE PERMISIBLE LIMITS (**)

NO IS MISSING OR YES

SURFACE TREATMENT,

APPLY NEW

REPEAT VISUAL INSPECTION

FOR CORROSION AT 5 YEARS

CORROSION

PROTECTION

DAMAGED

PROTECTION COATING.

REFER TO SRM 51−23−00,

51−23−10 and 51−23−20

AND 51−74−10)

SEE NOTE (1).

OBEY THE REWORK

CONDITIONS (*),

MEASURE THE REWORKED

DEPTH (D)

REFER TO NTM 51−10−04

PART 4 OR 51−10−05 PART 1

NO RESULTS YES

SEE FIG. A−FFAAA

SHEET 2 CONTACT AIRBUS

BEFORE SUBSEQUENT FLIGHT

AT THRESHOLD: SEE TABLE LH AND RH CENTER WING BOTTOM

SKIN INBOARD AND OUTBOARD AREAS, REFER TO FIG. A−FBGAA SHEET 01

NOTE:

(1) IF YOU FIND CORROSION AROUND THE FASTENERS REMOVE THE FASTENERS.

(REFER TO SRM 51−40−20 AND 51−40−21)

(**) REWORK PERMISSIBLE LIMITS

W 50mm (1.958 in)

L 100mm (3.937 in)

1 50mm (1.958 in)

2 NOT LIMITED

(*) REWORK CONDITIONS

L/2 4D AND W/2 4D

REFER TO FIG. A−FBAAA

SHEET 01

REFER TO FIG. A−FBCAA

SHEET 01

REFER TO FIG. A−FBCAA

SHEET 01

D_SB_576047_5_FAAA_01_02

Figure A-FFAAA - Sheet 01

- Flow Chart -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 27

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

SURFACE TREATMENT, APPLY

REPEAT VISUAL INSPECTION

FOR CORROSION AT 5 YEARS

5% D d **

NEW PROTECTION COATING.

REFER TO SRM 51−23−00,

51−23−10 and 51−23−20

NO CRACKS YES

CONTACT AIRBUS

BEFORE NEXT FLIGHT

NOTE:

(2) REPLACE THE FASTENERS IF THEY HAVE BEEN REMOVED

FROM FIG. A−FFAAA

SHEET 1

D 5% * D d **

NON DESTRUCTIVE TEST

(NDT)

FOR FATIGUE DAMAGE

REFER TO NTM 51−10−08

SEE NOTE (2) PART 8

SURFACE TREATMENT, APPLY

NEW PROTECTION COATING.

REFER TO SRM 51−23−00,

51−23−10 and 51−23−20

SEE NOTE (2)

INSPECTION PROGRAM

INSPECTION FOR CORROSION IN 5 YEARS

INSPECTION FOR FATIGUE DAMAGE:

SEE TABLE LH AND RH CENTER WING BOTTOM

SKIN INBOARD AND OUTBOARD AREAS,

FOR THE CORROSION INSPECTION.

* 5% : REFERENCE VALUE WITH RESPECT TO THE INITIAL

THICKNESS OF THE PANEL (E).

PERMISSIBLE LIMIT OF THE REWORKED DEPTH (D).

(REFER TO FIG. A−FBCAA SHEET 01)

** d : REFERENCE VALUE WITH RESPECT TO THE INITIAL

THICKNESS OF THE PANEL (E).

ACCORDING TO DAMAGED AREAS, PERMISSIBLE

LEGEND:

LIMITS OF THE REWORKED DEPTH PER AREA (d).

REFER TO FIG. A−FBCAA

SHEET 01

REFER TO FIG. A−FBGAA SHEET 01

(REFER TO FIG. A−FBCAA SHEET 01)

D_SB_576047_5_FAAA_02_02

Figure A-FFAAA - Sheet 02

- Flow Chart -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 28

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

PICK−UP ANGLE

INBOARD AREA

EXTERNAL LOWER

SURFACE SPLICE

AFT LOWER

SURFACE

D_SB_576047_5_BBAA_01_00

REWORKED

DEPTH

REWORK CONDITION

L/2 > 4D AND W/2 > 4D

REWORK PERMISSIBLE LIMITS

W < 50mm (1.968in.)

L < 100mm (3.937in.)

1 > 50mm (1.968in.)

2 NOT LIMITED

D

W/2

E

PANEL

RIB1

STIFFENER 44.2

LATTICE FLANGE 45

STIFFENER 45.1

STIFFENER 45.2

LATTICE FLANGE 46

STIFFENER 46.1

STIFFENER 46.2

REF. FR47

A−A

SECTION LEGEND:

W: REWORK LENGTH IN FLIGHT DIRECTION

L: REWORK LENGTH IN OUTBOARD DIRECTION

1: DISTANCE BETWEEN TWO ADJACENT

REWORK AREAS IN FLIGHT DIRECTION

2: DISTANCE BETWEEN TWO ADJACENT

REWORK AREAS IN OUTBOARD DIRECTION

D: REWORKED DEPTH

E: INITIAL THICKNESS OF THE PANEL

W

2 L

A

A

1

Figure A-FBBAA - Sheet 01

Evaluation Principle of Corrosion

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 29

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@A300-600

SERVICE BULLETIN

**CONF ALL

A

B

FR40

FR47

RIB1

AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA

OUTBOARD AREA

EXTERNAL LOWER

SURFACE SPLICE

B

FWD LOWER

SURFACE PANEL

AFT LOWER

SURFACE PANEL

RIB2

RIB1

SPAR

EXTERNAL LOWER

SURFACE SPLICE

A

B

FWD LOWER

SURFACE PANEL

AFT LOWER

SURFACE PANEL

EXTERNAL LOWER

SURFACE SPLICE

OUTBOARD AREA INBOARD AREA

STGR 2

1

STGR 3

STGR 4

STGR 5

STGR 6

STGR 7

STGR 8

STGR 9

STGR 10

STGR 11

STGR 12

STGR 19

STGR 18

STGR 17

STGR 16

STGR 15

STGR 14

STGR 13

CENTER

SPAR

FRONT

STIFFENER 40.1

STIFFENER 40.2

LATTICE FLANGE 41

STIFFENER 41.1

STIFFENER 41.2

LATTICE FLANGE 42

STIFFENER 42.1

STIFFENER 42.2

LATTICE FLANGE 43

STIFFENER 43.1

STIFFENER 43.2

STIFFENER 44.1

STIFFENER 44.2

LATTICE FLANGE 45

STIFFENER 45.1

STIFFENER 45.2

LATTICE FLANGE 46

STIFFENER 46.1

LATTICE FLANGE 44

STIFFENER 46.2

REF. FR40

REF. FR47 SPAR

AREAS TO INSPECT EXTERNAL LOWER

SURFACE SPLICE

REAR

FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL

AREA

DAMAGE

2

3

4

5

6

7

8

LH AND RH CENTER WING BOTTOM SKIN

INBOARD AND OUTBOARD AREAS

CONTACT AIRBUS

PICK−UP ANGLE

NOTE: ACCORDING TO DAMAGED AREAS PERMISSIBLE

LIMITS OF THE REWORKED DEPTH ARE SPECIFIED BELOW

D_SB_576047_5_BCAA_01_00

PERMISSIBLE LIMITS OF THE REWORKED DEPTH

5% TO THE INITIAL TICKNESS

OF THE PANEL

(INBOARD AREA) mm (in.)

5% TO THE INITIAL TICKNESS

OF THE PANEL

(OUTBOARD AREA) mm (in.)

PER AREA (d)

mm (in.)

CONTACT AIRBUS CONTACT AIRBUS

CONTACT AIRBUS CONTACT AIRBUS CONTACT AIRBUS

2.9mm

(0.114in.)

2.1mm

(0.082in.)

0.9mm

(0.035in.)

2.6mm

(0.102in.)

1.3mm

(0.051in.)

1.6mm

(0.062in.)

0.5mm

(0.019in.)

0.57mm

(0.022in.)

0.47mm

(0.018in.)

0.4mm

(0.015in.)

0.36mm

(0.014in.)

0.57mm

(0.022in.)

Figure A-FBCAA - Sheet 01

Permissible Limits of the Reworked Depth

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 30

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@A300-600

SERVICE BULLETIN

**CONF ALL

A

B

FR40

FR47

RIB1

AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA

OUTBOARD AREA

EXTERNAL LOWER

SURFACE SPLICE

B

FWD LOWER

SURFACE PANEL

AFT LOWER

SURFACE PANEL

RIB2

RIB1

SPAR

EXTERNAL LOWER

SURFACE SPLICE

A

B

FWD LOWER

SURFACE PANEL

AFT LOWER

SURFACE PANEL

EXTERNAL LOWER

SURFACE SPLICE

OUTBOARD AREA INBOARD AREA

STGR 2

1

STGR 3

STGR 4

STGR 5

STGR 6

STGR 7

STGR 8

STGR 9

STGR 10

STGR 11

STGR 12

STGR 19

STGR 18

STGR 17

STGR 16

STGR 15

STGR 14

STGR 13

CENTER

SPAR

FRONT

STIFFENER 40.1

STIFFENER 40.2

LATTICE FLANGE 41

STIFFENER 41.1

STIFFENER 41.2

LATTICE FLANGE 42

STIFFENER 42.1

STIFFENER 42.2

LATTICE FLANGE 43

STIFFENER 43.1

STIFFENER 43.2

STIFFENER 44.1

STIFFENER 44.2

LATTICE FLANGE 45

STIFFENER 45.1

STIFFENER 45.2

LATTICE FLANGE 46

STIFFENER 46.1

LATTICE FLANGE 44

STIFFENER 46.2

REF. FR40

REF. FR47 SPAR

AREAS TO INSPECT EXTERNAL LOWER

SURFACE SPLICE

REAR

FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL

AREA

DAMAGE

2

3

4

5

6

7

8

FATIGUE INSPECTION PROGRAME

AIRCRAFT WITH AFT < 1.5 FH/FC

THRESHOLD INTERVAL

VISUAL NDT

15700 FC

23600 FH

13400 FC

20200 FH

15700 FC

23600 FH

15700 FC

23600 FH

13400 FC

20200 FH

15700 FC

23600 FH

7400 FC

11200 FH

6700 FC

10100 FH

5500 FC

8200 FH

5100 FC

7700 FH

5500 FC

8200 FH

2300 FC

3500 FH

1000 FC

1600 FH

2300 FC

3500 FH

5500 FC

8200 FH

5100 FC

7700 FH

5500 FC

8200 FH

6200 FC

9300 FH

5900 FC

8800 FH

6200 FC

9300 FH

2700 FC

4100 FH

2400 FC

3500 FH

2700 FC

4000 FH

FATIGUE INSPECTION PROGRAME

AIRCRAFT WITH AFT > 1.5 FH/FC

THRESHOLD INTERVAL

VISUAL NDT

14500 FC

31500 FH

12400 FC

26900 FH

6900 FC

14900 FH

6200 FC

13500 FH

5100 FC

11000 FH

4800 FC

10300 FH

2200 FC

4700 FH

1000 FC

2100 FH

5800 FC

12500 FH

5400 FC

11800 FH

2500 FC

5500 FH

2200 FC

4800 FH

14500 FC

31500 FH

14500 FC

31500 FH

12400 FC

26900 FH

14500 FC

31500 FH

7400 FC

11200 FH

6900 FC

14900 FH

5100 FC

11000 FH

2200 FC

4700 FH

5100 FC

11000 FH

4800 FC

10300 FH

5100 FC

11000 FH

5800 FC

12500 FH

2500 FC

5400 FH

LH AND RH CENTER WING BOTTOM SKIN

INBOARD AND OUTBOARD AREAS

CONTACT AIRBUS

CONTACT AIRBUS

CONTACT AIRBUS

CONTACT AIRBUS

PICK−UP ANGLE NOTE: ACCORDING TO DAMAGED AREAS

THE FATIGUE INSPECTION PROGRAM BELOW GIVES

THE THRESHOLDS AND INTERVALS (FC OR FH WICHEVER COMES FIRST) APPLICABLE

TO THE VISUAL CHECK OR THE NON DESTRUCTRUCTIVE TEST (NDT)

D_SB_576047_5_BGAA_01_01

Figure A-FBGAA - Sheet 01

Inspection Program

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 31

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SERVICE BULLETIN

**CONF ALL

EXTERNAL LOWER

SURFACE SPLICE

RIB1 DATUM

PICK−UP ANGLE

SEALANT USE

MAT. NO. 09−002

C

B

REMAINING

MINIMUM

THICKNESS

X

(SEE NOTE 1)

OVERSIZE FOR NEW

PROTRUDING HEAD FASTENER

INITIAL THICKNESS OF THE

LOWER SURFACE PANEL E

SEALANT USE

MAT. NO. 09−002

NEW FASTENER

(SEE NOTE 2)

BASIC CONTOUR AND

BASIC FASTENER

REWORKED DEPTH (D)

A

INITIAL THICKNESS OF THE

LOWER SURFACE PANEL E REMAINING

MINIMUM

THICKNESS

X

(SEE NOTE 1)

OVERSIZE FOR NEW

COUNTERSUNK HEAD FASTENER

BASIC CONTOUR AND

BASIC FASTENER

SEALANT USE

MAT. NO. 09−002

NEW FASTENER

(SEE NOTE 2)

REWORKED DEPTH (D)

NOTE 1: PERMISSIBLE REMAINING MINIMUM THICKNESS (X) FOR THE

FWD LOWER SURFACE PANEL : 3.6mm (0.138in.)

PERMISSIBLE REMAINING MINIMUM THICKNESS (X) FOR THE

AFT LOWER SURFACE PANEL : 4.5mm (0.177in.)

NOTE 2: IN RELATION WITH THE DAMAGED AREAS, FOR EACH TYPE OF FASTENER THAT YOU MUST REPLACE,

REFER TO FIG. A−FBEAA SHEET 01, 02 AND 03, FIG. A−FBFAA SHEET 01 AND 02

AND THEIR TABLES, WHICH GIVE THE ALTERNATIVE IDENTIFICATION OF THE FASTENER (1st OVERSIZE OR 2st OVERSIZE).

D_SB_576047_5_BDAA_01_01

Figure A-FBDAA - Sheet 01

Replacement Principle of Fasteners and Sealing principle

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 32

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SERVICE BULLETIN

**CONF ALL

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

A A

B

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

BOTTOM STRUCTURE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR47

FR40

RIB1

C

LH AND RH CENTER WING BOTTOM SKIN

(INTBOARD AREA)

DETAIL VALID FOR ADAPTATION SOLUTION A

STIFFENER 40.2

STIFFENER 40.1

P

BRACKET FOR

WATER DRAIN

SYSTEM

A

D

C B D E F E F G H F

8

N

7

M

6

K L

4 5 2 3

J

1

REF.FR40

STIFFENER 40.1

STIFFENER 40.2

LATTICE FLANGE41STIFFENER 41.1

STIFFENER 41.2

LATTICE FLANGE42

STIFFENER 42.1

STIFFENER 42.2

LATTICE FLANGE43

STIFFENER 43.1

STIFFENER 43.2

STIFFENER 44.1

STIFFENER 44.2

STIFFENER 45.1

STIFFENER 45.2

STIFFENER 46.1

STIFFENER 46.2

REF.FR44

LATTICE FLANGE45

LATTICE FLANGE46

REF.FR47

AREA AREA AREA AREA AREA AREA AREA

AREA

RIB1

PICK−UP ANGLE

EXTERNAL LOWER 

SURFACE SPLICE

FRONT SPAR

CENTER SPAR

FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL

REAR SPAR

C

SEE DETAIL A

B

PICK−UP ANGLE

INBOARD AREA

D_SB_576047_5_BEAA_01_01

Figure A-FBEAA - Sheet 01

Location of Existing Fasteners on Forward and Aft Lower Surface Panels

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 33

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SERVICE BULLETIN

**CONF ALL

STANDARD MUMBER

A

B

C

D

E

F

G

H

NOTE: THE VALUES − XX ARE TO BE DETERMINED WITH RESPECT TO THE REMAINING THICKNESS (X)

REFER TO FIG. A−FBDAA SHEET 01

OR

OR

OR

OR

OR

OR

OR

OR

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

(SCREW) ITEM TYPE ASSOCIATEDHARDWAIR (NUT)

OR

OR

STANDARD MUMBER TYPE

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

PIN (THREADED)

(HI−LITE)

PIN (THREADED)

(HI−TIGUE)

ASSOCIATED

HARDWAIR (NUT)

STANDARD MUMBER TYPE

ASSOCIATED

HARDWAIR (NUT)

EXISTING FASTENER IDENTIFICATION ALTERNATIVE FASTENER IDENTIFICATION

REFER TO FIG. A−FBEAA SHEET 01 VIEW C

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE)

PIN (THREADED)

(BULLNOSE) NAS1726−6E

ASNA2031−6

NAS1726−5E

ASNA2031−5

NAS1726−6E

ASNA2031−6

NAS1726−5E

ASNA2031−5

NAS1726−4E

ASNA2031−4

NAS1726−5E

ASNA2031−5

NAS1726−5E

ASNA2031−5

NAS1726−4E

ASNA2031−4

NSA5479BV4−XX

NSA5479BV6−XX

NSA5479BV5−XX

NSA5479BV4−XX

NSA5479BV5−XX

NSA5479BV3−XX

NSA5479BV3−XX

NSA5479BV6−XX

NAS1726−6E

ASNA2031−4

NAS1726−5E

ASNA2031−5

NAS1726−6E

ASNA2031−6

NAS1726−5E

ASNA2031−5

NAS1726−4E

ASNA2031−4

NAS1726−5E

ASNA2031−5

NAS1726−5E

ASNA2031−5

NAS1726−4E

ASNA2031−4

HLT901BJ12−XX

NSA5477BV6−XX

HLT901BJ14−XX

NSA5477BV5−XX

HLT901BJ10−XX

NSA5477BV5−XX

HLT901BJ14−XX

NSA5477BV5−XX

HLT901BJ4−XX

NSA5477BV4−XX

HLT901BJ10−XX

NSA5477BV5−XX

HLT901BJ10−XX

NSA5477BV5−XX

HLT901BJ4−XX

NSA5477BV4−XX

NAS1726−4E

ASNA2031−6

NAS1726−5E

ASNA2031−5

NAS1726−6E

ASNA2031−6

NAS1726−5E

ASNA2031−5

NAS1726−4E

ASNA2031−4

NAS1726−5E

ASNA2031−5

NAS1726−5E

ASNA2031−5

NAS1726−4E

ASNA2031−4

ASNA2004V6−14

ASNA2026V6−14

ASNA2004V4−10

ASNA2026V4−10

ASNA2004V5−12

ASNA2026V5−12

ASNA2004V6−10

ASNA2026V6−10

ASNA2004V4−12

ASNA2026V4−12

ASNA2004V5−13

ASNA2026V5−13

ASNA2004V5−14

ASNA2026V5−14

ASNA2004V5−10

ASNA2026V5−10

D_SB_576047_5_BEAA_02_01

FIG. A−FBDAA SHEET 01 VIEW A)

1st OVERSIZE FOR COUNTERSUNK

HEAD FASTENER (REFER TO

1st OVERSIZE FOR PROTRUDING

FIG. A−FBDAA SHEET 01 VIEW A)

HEAD FASTENER (REFER TO

Figure A-FBEAA - Sheet 02

Location of Existing Fasteners on Forward and Aft Lower Surface Panels

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 34

5

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

SERVICE BULLETIN

**CONF ALL

STANDARD MUMBER

J

K

L

M

N

P

OR

OR

OR

OR

OR

OR

(SCREW) ITEM TYPE ASSOCIATEDHARDWAIR (NUT)

STANDARD MUMBER TYPE

ASSOCIATED

HARDWAIR (NUT)

STANDARD MUMBER TYPE

ASSOCIATED

HARDWAIR (NUT)

EXISTING FASTENER IDENTIFICATION ALTERNATIVE FASTENER IDENTIFICATION

NSA5154BVA6−XX

NSA5154BVA6−XX

NSA5154BVA9−XX

NSA5154BVA9−XX

NSA5154BVA9−XX

NSA5154BVA9−XX

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−4E

NAS1726−4E

NAS1726−4E

NAS1726−4E

ASNA2012K9−17

NSA5022V9−17

ASNA2012K9−18

NSA5022V9−18

ASNA2012K9−19

NSA5022V9−19

ASNA2012K9−20

NSA5022V9−20

ASNA2012K9−21

NSA5022V9−21

NSA5022V9−22

NSA5022V9−23

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

NSA5153VA6−XX

NSA5153VA6−XX

NSA5153VA9−XX

NSA5153VA9−XX

NSA5153VA9−XX

NSA5153VA9−XX

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

NAS1726−4E

NAS1726−4E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

NAS1726−4E

NAS1726−4E

NAS1726−9E

NAS1726−9E

NAS1726−9E

NAS1726−9E

D_SB_576047_5_BEAA_03_01

NOTE: THE VALUES − XX ARE TO BE DETERMINED WITH RESPECT TO THE REMAINING THICKNESS (X)

REFER TO FIG. A−FBDAA SHEET 01

REFER TO FIG. A−FBEAA SHEET 01 VIEW C

FIG. A−FBDAA SHEET 01 VIEW A)

1st OVERSIZE FOR COUNTERSUNK

HEAD FASTENER (REFER TO

1st OVERSIZE FOR PROTRUDING

FIG. A−FBDAA SHEET 01 VIEW A)

HEAD FASTENER (REFER TO

Figure A-FBEAA - Sheet 03

Location of Existing Fasteners on Forward and Aft Lower Surface Panels

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 35

5

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

SERVICE BULLETIN

**CONF ALL

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

A A

B

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

C

C

8 7 6 5 4 3 2 1

AREA AREA AREA AREA AREA AREA AREA

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL

REAR SPAR

LATTICE FLANGE 47

FRONT SPAR

REF.

FR40

RIB1

EXTERNAL LOWER 

SURFACE SPLICE

CENTER SPAR

G F E D C D C B A CENTER SPAR STGR19 STGR18 STGR17 STGR16 STGR15 STGR14 STGR13 STGR11 STGR10 STGR9 STGR8 STGR7

STGR6STGR5STGR4STGR3STGR2

LH AND RH CENTER WING BOTTOM SKIN

(OUTBOARD AREA)

AREA

D_SB_576047_5_BFAA_01_01

LATTICE FLANGE 46LATTICE FLANGE 45LATTICE FLANGE 44LATTICE FLANGE 43LATTICE FLANGE 42LATTICE FLANGE 41

Figure A-FBFAA - Sheet 01

Location of Existing Fasteners on Forward and Aft Lower Surface Panels

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 36

5

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

SERVICE BULLETIN

**CONF ALL

EXISTING FASTENER IDENTIFICATION ALTERNATIVE FASTENER IDENTIFICATION

ITEM TYPE

(SCREW)

HARDWARE 

(NUT)

ASSOCIATED STANDARD NUMBER

STANDARD NUMBER TYPE

FIG. A−FBDAA SHEET 01 VIEW A) HARDWARE 

(NUT)

ASSOCIATED

STANDARD NUMBER TYPE

HARDWARE 

(NUT)

ASSOCIATED

NSA5092V6−15

NSA5092V7−17

NSA5092V7−19

NSA5092V7−20

NSA5092V7−21

NSA5092V7−22

NSA5092V7−23

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

NSA5050−6

NSA5050−7

NSA5050−7

NSA5050−7

NSA5050−7

NSA5050−7

NSA5050−7

NSA5153VA6−XX

NSA5153VA7−XX

NSA5153VA7−XX

NSA5153VA7−XX

NSA5153VA7−XX

NSA5153VA7−XX

NSA5153VA7−XX

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

NAS1726−6E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NSA5154VA6−XX

NSA5154VA7−XX

NSA5154VA7−XX

NSA5154VA7−XX

NSA5154VA7−XX

NSA5154VA7−XX

NSA5154VA7−XX

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

TAPER−LOK

NAS1726−6E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NAS1726−7E

NAS1726−7E

REFER TO FIG. A−FBFAA SHEET 01 VIEW C

LH AND RH CENTER WING BOTTOM SKIN

(OUTSGARD AREA)

NOTE: THE VALUES − XX ARE TO BE DETERMINED WITH RESPECT TO THE REMAINING THICKNESS (X) REFER TO FIG. A−FBDAA SHEET 01.

A

B

C

D

E

F

G

1st OVERSIZE FOR COUNTERSUNK

HEAD FASTENER (REFER TO

1st OVERSIZE FOR PROTRUDING

FIG. A−FBDAA SHEET 01 VIEW A)

HEAD FASTENER (REFER TO

D_SB_576047_5_BFAA_02_01

Figure A-FBFAA - Sheet 02

Location of Existing Fasteners on Forward and Aft Lower Surface Panels

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 37

5

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

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 38

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

The results of the inspection, including no findings, replacement or action to be done, must be

forwarded to AIRBUS Departement SEES1, on the attached inspection report sheet.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

SERVICE BULLETIN

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

A

B

B

BOTTOM STRUCTURE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR47

FR40

RIB1

C

DETAIL VALID FOR ADAPTATION SOLUTION A

STIFFENER 46.2

STIFFENER 46.1

P

BRACKET FOR

WATER DRAIN

SYSTEM

PICK−UP ANGLE

INBOARD AREA

A

D

C B D E F E F G H F

8

N

7

M

6

K L

4 5 2 3

J

1

REF.FR40

STIFFENER 40.1

STIFFENER 40.2

LATTICE FLANGE41STIFFENER 41.1

STIFFENER 41.2

LATTICE FLANGE42

STIFFENER 42.1

STIFFENER 42.2

LATTICE FLANGE43

STIFFENER 43.1

STIFFENER 43.2

STIFFENER 44.1

STIFFENER 44.2

STIFFENER 45.1

STIFFENER 45.2

STIFFENER 46.1

STIFFENER 46.2

REF.FR44

LATTICE FLANGE45

LATTICE FLANGE46

REF.FR47

AREA AREA AREA AREA AREA AREA AREA

AREA

RIB1

PICK−UP ANGLE

EXTERNAL LOWER 

SURFACE SPLICE

FRONT SPAR

CENTER SPAR

FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL

REAR SPAR

C

SEE DETAIL A

NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS.

LH CENTER WING BOTTOM SKIN

(INBOARD AREA)

D_SB_576047_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 2

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

REPORT FOR CORROSION RESULT

AERA

DAMAGED

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

WIDTH

(W)

LENGTH

(L)

DEPTH

(D)

DISTANCE

A1

DISTANCE

A2

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

A

B B

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR47

FR40

RIB1

INBOARD AREA

D_SB_576047_5_RAAA_02_01

LH CENTER WING BOTTOM SKIN

(INBOARD AREA)

PICK−UP ANGLE

REFER TO FIG. A−FBEAA

Figure A-FRAAA - Sheet 02

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 3

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

SERVICE BULLETIN

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

DETAIL VALID FOR ADAPTATION SOLUTION A

A

D

C B D E F E F G H F

8

N

7

M

6

K L

4 5 2 3

J

1

REF.FR40

STIFFENER 40.1

STIFFENER 40.2

LATTICE FLANGE41STIFFENER 41.1

STIFFENER 41.2

LATTICE FLANGE42

STIFFENER 42.1

STIFFENER 42.2

LATTICE FLANGE43

STIFFENER 43.1

STIFFENER 43.2

STIFFENER 44.1

STIFFENER 44.2

STIFFENER 45.1

STIFFENER 45.2

STIFFENER 46.1

STIFFENER 46.2

REF.FR44

LATTICE FLANGE45

LATTICE FLANGE46

REF.FR47

AREA AREA AREA AREA AREA AREA AREA

AREA

RIB1

PICK−UP ANGLE

EXTERNAL LOWER 

SURFACE SPLICE

FRONT SPAR

CENTER SPAR

FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL

REAR SPAR

C

SEE DETAIL A

B

BOTTOM STRUCTURE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR40 PICK−UP ANGLE

INBOARD AREA

RIB1

FR47

C

NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS.

RH CENTER WING BOTTOM SKIN

(INBOARD AREA)

STIFFENER 46.1

STIFFENER 46.2

P

BRACKET FOR

WATER DRAIN

SYSTEM

D_SB_576047_5_RAAA_03_01

Figure A-FRAAA - Sheet 03

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 4

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

REPORT FOR CORROSION RESULT

AERA

DAMAGED

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

WIDTH

(W)

LENGTH

(L)

DEPTH

(D)

DISTANCE

A1

DISTANCE

A2

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

B

BOTTOM STRUCTURE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR40 PICK−UP ANGLE

INBOARD AREA

RIB1

FR47

C

D_SB_576047_5_RAAA_04_01

RH CENTER WING BOTTOM SKIN

(INBOARD AREA)

REFER TO FIG. A−FBEAA

Figure A-FRAAA - Sheet 04

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 5

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

SERVICE BULLETIN

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

C

1 2 3 4 5 6 7 8

AREA AREA AREA AREA AREA AREA AREA

FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL

FRONT SPAR

REAR SPAR

RIB1

EXTERNAL LOWER 

SURFACE SPLICE

CENTER SPAR

A B C D C D E F G CENTER SPAR

STGR2STGR3STGR4STGR5STGR6STGR7STGR8STGR9STGR10STGR11STGR13STGR14STGR15STGR16STGR17STGR18STGR19

AREA

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

C

REF.

FR40

LATTICE FLANGE 41

D_SB_576047_5_RAAA_05_01

NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS.

RH CENTER WING BOTTOM SKIN

(OUTBOARD AREA) LATTICE FLANGE 42

LATTICE FLANGE 43LATTICE FLANGE 44LATTICE FLANGE 45LATTICE FLANGE 46LATTICE FLANGE 47

Figure A-FRAAA - Sheet 05

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 6

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

REPORT FOR CORROSION RESULT

AERA

DAMAGED

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

WIDTH

(W)

LENGTH

(L)

DEPTH

(D)

DISTANCE

A1

DISTANCE

A2

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

D_SB_576047_5_RAAA_06_01

RH CENTER WING BOTTOM SKIN

(OUTBOARD AREA)

REFER TO FIG. A−FBFAA

Figure A-FRAAA - Sheet 06

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 7

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

SERVICE BULLETIN

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

C

C

8 7 6 5 4 3 2 1

AREA AREA AREA AREA AREA AREA AREA

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL

REAR SPAR

LATTICE FLANGE 47

FRONT SPAR REF. FR40

RIB1

EXTERNAL LOWER 

SURFACE SPLICE

CENTER SPAR

G F E D C D C B A CENTER SPAR STGR19 STGR18 STGR17 STGR16 STGR15 STGR14 STGR13 STGR11 STGR10 STGR9 STGR8 STGR7

STGR6STGR5STGR4STGR3STGR2

AREA

D_SB_576047_5_RAAA_07_01

LATTICE FLANGE 46LATTICE FLANGE 45LATTICE FLANGE 44LATTICE FLANGE 43LATTICE FLANGE 42LATTICE FLANGE 41

NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS.

LH CENTER WING BOTTOM SKIN

(OUTBOARD AREA)

Figure A-FRAAA - Sheet 07

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 8

5

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

SERVICE BULLETIN

Appendix 1- Inspection Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

REPORT FOR CORROSION RESULT

AERA

DAMAGED

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

WIDTH

(W)

LENGTH

(L)

DEPTH

(D)

DISTANCE

A1

DISTANCE

A2

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

AERA

mm

in

mm

in

mm

in

mm

in

mm

in

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

C

D_SB_576047_5_RAAA_08_01

LH CENTER WING BOTTOM SKIN

(OUTBOARD AREA)

REFER TO FIG. A−FBFAA

Figure A-FRAAA - Sheet 08

- Inspection Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 9

5

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

SERVICE BULLETIN

Appendix 2- Repair Report -

**CONF ALL

The results of the inspection, including no findings, replacement or action to be done, must be

forwarded to AIRBUS Departement SEES1, on the attached inspection report sheet.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

5

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

SERVICE BULLETIN

Appendix 2- Repair Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

REPAIR REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

REPORT FOR REPAIR RESULT

1st

OVERSIZE

OVERSIZE FOR COUNTERSUNK

HEAD FASTENER

SERVICE BULLETIN

AERA

DAMAGED

EXISTING

FASTENER

DAMAGED

AREA ITEM

2nd

OVERSIZE

STANDARD

NUMBER TYPE

OVERSIZE FOR PROTRUDING

HEAD FASTENER

STANDARD

NUMBER AFT LOWER TYPE

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

A

B B

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR47

FR40

RIB1

INBOARD AREA

LH CENTER WING BOTTOM SKIN

(INBOARD AREA)

REFER TO FIG. A−FBEAA

PICK−UP ANGLE

D_SB_576047_5_RBAA_01_00

Figure A-FRBAA - Sheet 01

- Repair Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 2

5

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

SERVICE BULLETIN

Appendix 2- Repair Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

SERVICE BULLETIN

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

B

BOTTOM STRUCTURE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

FR40 PICK−UP ANGLE

INBOARD AREA

RIB1

FR47

C

REPAIR REPORT

REPORT FOR REPAIR RESULT

1st

OVERSIZE

OVERSIZE FOR COUNTERSUNK

HEAD FASTENER

AERA

DAMAGED

EXISTING

FASTENER

DAMAGED

AREA ITEM

2nd

OVERSIZE

STANDARD

NUMBER TYPE

OVERSIZE FOR PROTRUDING

HEAD FASTENER

STANDARD

NUMBER TYPE

RH CENTER WING BOTTOM SKIN

(INBOARD AREA)

REFER TO FIG. A−FBEAA

D_SB_576047_5_RBAA_02_00

Figure A-FRBAA - Sheet 02

- Repair Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 3

5

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

SERVICE BULLETIN

Appendix 2- Repair Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

SERVICE BULLETIN

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

REPAIR REPORT

REPORT FOR REPAIR RESULT

1st

OVERSIZE

OVERSIZE FOR COUNTERSUNK

HEAD FASTENER

AERA

DAMAGED

EXISTING

FASTENER

DAMAGED

AREA ITEM

2nd

OVERSIZE

STANDARD

NUMBER TYPE

OVERSIZE FOR PROTRUDING

HEAD FASTENER

STANDARD

NUMBER TYPE

RH CENTER WING BOTTOM SKIN

(OUTBOARD AREA)

REFER TO FIG. A−FBFAA

D_SB_576047_5_RBAA_03_00

Figure A-FRBAA - Sheet 03

- Repair Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 4

5

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

SERVICE BULLETIN

Appendix 2- Repair Report -

**CONF ALL

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA REPAIRED IN ACCORDANCE WITH :

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−57−6047

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS

EDDY CURRENT

SERVICE BULLETIN

A

AFT LOWER 

SURFACE PANEL

FWD LOWER 

SURFACE PANEL

EXTERNAL LOWER 

SURFACE SPLICE

B

PICK−UP ANGLE

AREA TO INSPECT

EXTERNAL LOWER 

SURFACE SPLICE

OUTBOARD AREA

FR47

FR40

RIB1

C

D_SB_576047_5_RBAA_04_00

REPAIR REPORT

REPORT FOR REPAIR RESULT

1st

OVERSIZE

OVERSIZE FOR COUNTERSUNK

HEAD FASTENER

AERA

DAMAGED

EXISTING

FASTENER

DAMAGED

AREA ITEM

2nd

OVERSIZE

STANDARD

NUMBER TYPE

OVERSIZE FOR PROTRUDING

HEAD FASTENER

STANDARD

NUMBER TYPE

LH CENTER WING BOTTOM SKIN

(OUTBOARD AREA)

REFER TO FIG. A−FBFAA

Figure A-FRBAA - Sheet 04

- Repair Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 5

5

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION

AT RIB 1

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: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

5

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

SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047

REVISION No.: 06 - Oct 17/11 Page: 1

5

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