@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 - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14

MODIFICATION No.: 10326H5339

This page transmits Revision No.02 of Service Bulletin No.A300-57-6046

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 02 issued:

- to include a High Frequency Eddy Current (HFEC) inspection after accomplishment of this

modification Service Bulletin.

The opportunity is taken to produce this Service Bulletin in the latest format.

CHANGES

Summary of changes:

- part number of washer NAS5353-06A corrected to NSA5353-06A.

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

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

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

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

Fig. A-USAAA 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

CONF 002 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

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

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

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

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

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 2

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REVISION TRANSMITTAL SHEET

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

Kit 576046B01R00 Minor editorial or document structure change N

Kit 576046B02R00 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 CMLB01 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

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Standard tool TOOLB01 Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 576046- 831-895-001-

MODIFICATION

Minor editorial or document structure change N

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

Task associated data - 002 Minor editorial or document structure change N

Subtask 576046-910-401-001 Minor editorial or document structure change N

Subtask 576046-839-401-001 Minor editorial or document structure change N

Subtask 576046-910-401-001 Minor editorial or document structure change N

Subtask 576046-839-401-001 Minor editorial or document structure change N

Subtask 576046-941-401-001 Minor editorial or document structure change N

Subtask 576046-941-401-001 Minor editorial or document structure change N

Subtask 576046-831-401-001 Minor editorial or document structure change N

Subtask 576046-831-402-001 Minor editorial or document structure change N

Subtask 576046-831-403-001 Minor editorial or document structure change N

Subtask 576046-750-401-001 New detailed visual and HFEC inspection added N

Subtask 576046-831-401-001 Minor editorial or document structure change N

Subtask 576046-831-402-001 Minor editorial or document structure change N

Subtask 576046-831-403-002 Minor editorial or document structure change N

Subtask 576046-750-401-001 New detailed visual and HFEC inspection added N

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 3

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REVISION TRANSMITTAL SHEET

Subtask 576046-914-401-001 Minor editorial or document structure change N

Subtask 576046-942-401-001 Minor editorial or document structure change N

Subtask 576046-914-401-001 Minor editorial or document structure change N

Subtask 576046-942-401-001 Minor editorial or document structure change N

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

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

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

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

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

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

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

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

APPENDIX 01: INSPECTION REPORT FORM

APPENDIX CONTENT Minor editorial or document structure change N

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

Fig. A-URAAA Sheet 01 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

NOTE: This is only applicable for Revision No. 02 and subsequent. If information is required for

Revisions issued previous to this, please check your copies of Revision Transmittal

Sheets or contact AIRBUS.

REVISION SEQUENCE

ORIGINAL: Jan 18/94

REVISION No. : 02 - Jun 21/13

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 4

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 10326H5339

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Cracks were found during full-scale fatigue testing in the bottom skin stringers at Rib 14. Following the

introduction of Maintenance Review Board (MRB) document inspection SSI 57-21-64 and SSI 57-21-78,

cracks were found on in-service aircraft in the same area.

The accomplishment of this Service-Bulletin improves the design of the stringer run-outs by re-profiling.

This will reduce the risk of cracks initiating at the stringer run-outs.

This Service-Bulletin also details the removal of the stringer end run-out plate at Stringer 19 on the

bottom skin. This will relieve stresses from the rear spar at Rib 14.

This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out.

This modification limits the occurrence of cracks by reducing the stress concentrations in the affected

areas.

The embodiment of this Service Bulletin cancels the MRB document inspection SSI 57-21-64 and SSI

57-21-78 and changes the inspection requirements of SSI 57-21-66.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 1

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SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

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

DEFUEL/VENTING YES

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 576046B01R00 1 2,250.00 BOLTS, NUTS, WASHERS

Standard tool TOOLB01 1 See SB FTI KIT

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 576046B02R00 1 2,250.00 BOLTS, NUTS, WASHERS

EFFECTIVITY

**CONF ALL

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

14S 34Z ABD ABR BCS CES F2I FDX I2L IRA IRM KAC KAL

MON MSR OHY QTR RLB SUD TAR THA U1T UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 2

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@A300-600

SERVICE BULLETIN

SUMMARY

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 576046-831-895-001: MODIFICATION

TOTAL MANHOURS 63.00

ELAPSED TIME (HOURS) 28.50

**CONF 002

Task 576046-831-895-001: MODIFICATION

TOTAL MANHOURS 53.00

ELAPSED TIME (HOURS) 25.50

APPENDICES

**CONF ALL

APPENDIX 01: INSPECTION REPORT FORM

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 3

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

A

VIEW ON PANEL No. 3 BOTTOM SKIN:

STRINGERS 10, 11, 12 AND 17 EITHER SIDE OF RIB 14

(STRINGER 19 SIMILAR)

PROFILE BEFORE PROFILE AFTER

STRINGER

DATUM

RIB14

REAR

FRONT

MODIFICATION AREA

NOTE:

STRINGERS

SPAR

SPAR

RIB14

A

LH WING SHOWN

RH WING SIMILAR

D_SB_576046_7_SAAA_01_00

Figure A-USAAA - Sheet 01

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 4

7

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 - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14

MODIFICATION No.: 10326H5339

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

This modification is embodied prior to delivery on A/C MSN 0723 and subsequent.

(1) Models

B4-603 B4-605R B4-620 B4-622 B4-622R C4-620

(2) Effectivity by MSN

0284 0294 0301 0307 0312 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388

0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 0518 0521 0525 0529-0530

0532 0536 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582

0584 0602-0605 0607-0609 0611 0613-0614 0617-0618 0621 0623 0625-0633 0635

0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683

0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717

0719 0721-0722

(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 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 1

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

14S 0609

34Z 0685 0692

ABD 0529 0557

ABR 0683

BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711

CES 0521 0525 0532 0707

F2I 0284 0294 0301 0307 0312 0321 0336 0348 0351 0518

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

I2L 0677

IRA 0632 0696

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

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0627 0631 0662

MON 0556 0604 0605

MSR 0561 0607

OHY 0584 0603

QTR 0554 0560 0614

RLB 0626 0643

SUD 0666

TAR 0505 0558 0563

THA 0464 0566 0569 0577 0629 0635 0681 0705

U1T 0628

UZB 0717 0722

(4) Configuration by MSN

MSN CONFIGURATION

0284 0294 0301 0307 0312 0321 0336 0344 0348 0351 0358

0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464

0477 0479 0505

001

0518 0521 0525 0529 0530 0532 0536 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 0607

0608 0609 0611 0613 0614 0617 0618 0621 0623 0625 0626

0627 0628 0629 0630 0631 0632 0633 0635 0637 0641 0643

0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681

0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707

0709 0711 0713 0715 0717 0719 0721 0722

002

(5) Configuration definition

**CONF 001

Config. 001 is applicable to aircraft Pre Mod. No. 07207H1066.

**CONF 002

Config. 002 is applicable to aircraft Post Mod. No. 07207H1066.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 2

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SERVICE BULLETIN

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 576046B01R00 1 (1)

Standard tool TOOLB01 1

Consumable CMLB01 As required

NOTE (1): KITB01 contains the component parts to modify the LH and RH wings.

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 576046B02R00 1 (1)

Consumable CMLB01 As required

NOTE (1): KITB02 contains the component parts to modify the LH and RH wings.

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Cracks were found during full-scale fatigue testing in the bottom skin stringers at Rib 14.

Following the introduction of Maintenance Review Board (MRB) document inspection

SSI 57-21-64 and SSI 57-21-78, cracks were found on in-service aircraft in the same

area.

(2) Objective/Action

The accomplishment of this Service-Bulletin improves the design of the stringer run-outs

by re-profiling. This will reduce the risk of cracks initiating at the stringer run-outs.

This Service-Bulletin also details the removal of the stringer end run-out plate at Stringer

19 on the bottom skin. This will relieve stresses from the rear spar at Rib 14.

This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out.

(3) Advantages

This modification limits the occurrence of cracks by reducing the stress concentrations in

the affected areas.

The embodiment of this Service Bulletin cancels the MRB document inspection SSI

57-21-64 and SSI 57-21-78 and changes the inspection requirements of SSI 57-21-66.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 3

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@A300-600

SERVICE BULLETIN

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 576046-831-895-001: MODIFICATION

(1) RE-PROFILE THE STRINGER RUN-OUTS

(2) RE-PROFILE THE STRINGER 19 RUN-OUT

(3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19

(4) DETAILED VISUAL AND HFEC INSPECTION

**CONF 002

Task 576046-831-895-001: MODIFICATION

(1) RE-PROFILE THE STRINGER RUN-OUTS

(2) RE-PROFILE THE STRINGER 19 RUN-OUT

(3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19

(4) DETAILED VISUAL AND HFEC INSPECTION

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA).

For B4-600 (R) aircraft operating beyond ESG embodiment of this Service Bulletin,

accomplishment is mandatory at or before 42,500 Flight Cycles (FC), or within 2,000 FC

from the issue date of the AD.

For B4-600 (R) and C4-600 aircraft the recommended accomplishment timescales FC

and Flight Hours (FH) are given in Table 1:

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 4

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SERVICE BULLETIN

Aircraft Normal Range Short Range

FC FH FC FH

A300 B4-600 (R)

A300 C4-600

16,700 36,000 18,000 27,100

Table 1: Recommended Embodiment Time of Modification 10326H5339

F. APPROVAL

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

Organization Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

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

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

included.

**CONF 001

Task 576046-831-895-001: MODIFICATION

Get Access 13.00

On Aircraft

RE-PROFILE THE STRINGER RUN-OUTS 15.00

RE-PROFILE THE STRINGER 19 RUN-OUT 2.00

REMOVE THE STRINGER END RUN-OUT PLATE ON

STRINGER 19

15.00

DETAILED VISUAL AND HFEC INSPECTION 3.00

Close-Up 15.00

TOTAL MANHOURS 63.00

ELAPSED TIME (HOURS) 28.50

**CONF 002

Task 576046-831-895-001: MODIFICATION

Get Access 13.00

On Aircraft

RE-PROFILE THE STRINGER RUN-OUTS 15.00

RE-PROFILE THE STRINGER 19 RUN-OUT 2.00

REMOVE THE STRINGER END RUN-OUT PLATE ON

STRINGER 19

5.00

DETAILED VISUAL AND HFEC INSPECTION 3.00

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 5

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SERVICE BULLETIN

Task 576046-831-895-001: MODIFICATION

Close-Up 15.00

TOTAL MANHOURS 53.00

ELAPSED TIME (HOURS) 25.50

**CONF ALL

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition

of (MEW) and operator’s items refer to the Weight and Balance Manual (WBM) Chapter

1-00-07.

Manufacturers Empty Weight -3.210 KG (-7.077 LB)

Effect on Balance -101.115 KGM (-731.364 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 20-21-12 20-31-00 28-00-00

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

28-25-00

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01 57-21-64

Process and Material Specification (PMS)

Service Information Letter (SIL) 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-20 51-24-00 51-35-00

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

51-40-41 51-40-46 51-43-00

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

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF 002

Aircraft Maintenance Manual (AMM) 20-21-12 20-31-00 28-00-00

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

28-25-00

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01 57-21-64

Process and Material Specification (PMS)

Service Information Letter (SIL) 51-012

Standards Manual (SM)

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 6

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@A300-600

SERVICE BULLETIN

Structural Repair Manual (SRM) 51-23-20 51-24-00 51-35-00

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

51-40-41 51-40-44 51-40-46

51-43-00 51-75-10 51-76-10

51-76-20

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) SSI 57-21-64

SSI 57-21-66

SSI 57-21-78

Structural Repair Manual (SRM) 57-20-14

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 7

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This Page Intentionally Left Blank

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 8

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Kit 576046B01R00

Kit 576046B02R00

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 576046B01R00

Cost 2,250.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

Kit 576046B02R00

Cost 2,250.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 9

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@A300-600

SERVICE BULLETIN

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 576046B01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 NSA5475-6K7 20 NUT

2 NSA5476VHK6-11 10 BOLT

3 NSA5476VHK6-14 10 BOLT

4 NSA5353-06A 40 WASHER

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 576046B02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 NSA5475-5K7 20 NUT

2 NSA5478VHK5-11 10 BOLT

3 NSA5478VHK5-14 10 BOLT

4 SL4087-05A 40 WASHER

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Anti Corrosion Primer Epoxy 04DAB2 As required

Brushable Fuel Resistant Coating 06HAA1 As required

Non Aqueous Cleaner 08BAA9 As required

Chemical Conversion Coating

Yellow Aluminum

10ABC1 As required

(2) Components

None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 10

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@A300-600

SERVICE BULLETIN

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

(a) Procurement Addresses

Operators in Config. 001 interested in obtaining the FTI tool kits should contact:

Standard tool TOOLB01 Fatigue Technology Inc

401 Andover Park

East SEATTLE

WA 98188-7605

USA

Internet: www.fatiguetech.com

Phone: (206) 2462010 Fax: (206) 2449886

(b) Price and Availability

Operators in Config. 001 who require kit number FTI-A300-57-6046-1, refer to

Fatigue Technology Inc.

For operators in Config. 001, supply terms for the Start Drill Block part number

CHS371J-10-3-N are to be negotiated with:

AIRBUS

Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

internet: http://spares.airbus.com

fax: +49 40 50 76 2590

E-mail: airbus.kit@airbus.com

(2) Tools

For operators in Config. 001, AIRBUS Spares Support and Services with FTI have

allocated the following tool kit numbers for cold expansion: For the definition of capital,

durable and expendable tools refer to SIL 51-012.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 11

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@A300-600

SERVICE BULLETIN

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

DKA300576046-1 Durable Tooling 1 (1)

EKA300576046-1 Expendable Tooling 1 (2)

FTIA300576046-1 Capital Tooling 1 (3)

NOTE (1): Durable tooling: Ref. DK-A300-57-6046-1

The durable tool kit contains the minimum quantity of durable tools

necessary to accomplish the Service Bulletin on one aircraft. If the

Service Bulletin is to be accomplished on more than one aircraft, the

number of durable kits required can be established by reference to SIL

51-012.

NOTE (2): Expendable tooling: Ref. EK-A300-57-6046-1

The expendable tool kit contains the quantity of expendable tools

required to accomplish the Service Bulletin on one aircraft. Order one

expendable tool kit for every aircraft on which this Service Bulletin is to

be accomplished.

NOTE (3): Capital tooling: Ref. FTI-A300-57-6046-1

The capital tools provided in this kit are not specific to this Service

Bulletin and are normally already available in operator’s stock as a long

term investment or can be loaned from FTI.

(3) Special Tools

None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 12

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@A300-600

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 576046-831-895-001 - MODIFICATION

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY

KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION

(CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A

POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN

THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A

CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.

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

**CONF 001

Zone

543 550 643 650

Access

Panel 543DB 550BB 643DB 650BB

Manpower

TOTAL MANHOURS 63.00

ELAPSED TIME (HOURS) 28.50

**CONF 002

Zone

543 550 643 650

Access

Panel 543DB 550BB 643DB 650BB

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 13

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@A300-600

SERVICE BULLETIN

Manpower

TOTAL MANHOURS 53.00

ELAPSED TIME (HOURS) 25.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 576046-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Consumable Material List (CML)

Process and Material Specification

(PMS)

Structural Repair Manual (SRM) 51-24-00

51-40-20

51-40-40

51-75-10

(a) If you find process and material specifications that you do not know in the design

drawings, refer to the cross-reference list in the Process and Material Specification

(PMS).

(b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to

Consumable Materials List (CML).

(c) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(d) Remove and install fasteners in accordance with SRM 51-40-20.

(e) Apply sealant in accordance with SRM 51-24-00.

(f) Renew the protective finish in accordance with SRM 51-75-10.

(g) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM

51-40-40.

(2) Subtask 576046-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills UTILITY

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

Service Bulletin.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 14

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@A300-600

SERVICE BULLETIN

**CONF 002

(1) Subtask 576046-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Consumable Material List (CML)

Process and Material Specification

(PMS)

Structural Repair Manual (SRM) 51-24-00

51-40-20

51-40-40

51-75-10

(a) If you find process and material specifications that you do not know in the design

drawings, refer to the cross-reference list in the Process and Material Specification

(PMS).

(b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to

Consumable Materials List (CML).

(c) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(d) Remove and install fasteners in accordance with SRM 51-40-20.

(e) Apply sealant in accordance with SRM 51-24-00.

(f) Renew the protective finish in accordance with SRM 51-75-10.

(g) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM

51-40-40.

(2) Subtask 576046-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills UTILITY

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

Service Bulletin.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 15

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@A300-600

SERVICE BULLETIN

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 576046-941-401-001 - JOB SET-UP

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 28-00-00, Page Block 301

28-10-00, Page Block 301

28-11-00, Page Block 101

28-11-22, Page Block 401

28-25-00, Page Block 301

WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A

FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE (REFER TO

AMM 28-00-00, PAGE BLOCK 301).

(a) Defuel the aircraft (Refer to AMM 28-25-00, Page Block 301).

(b) Put the access platform(s) in position.

(c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between

RIBS Rib 13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM

28-11-00, Page Block 101).

(d) Vent the fuel tanks (Refer to AMM 28-10-00, Page Block 301).

**CONF 002

(1) Subtask 576046-941-401-001 - JOB SET-UP

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 28-00-00, Page Block 301

28-10-00, Page Block 301

28-11-00, Page Block 101

28-11-22, Page Block 401

28-25-00, Page Block 301

WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A

FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE (REFER TO

AMM 28-00-00, PAGE BLOCK 301).

(a) Defuel the aircraft (Refer to AMM 28-25-00, Page Block 301).

(b) Put the access platform(s) in position.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

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@A300-600

SERVICE BULLETIN

(c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between

RIBS Rib 13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM

28-11-00, Page Block 101).

(d) Vent the fuel tanks (Refer to AMM 28-10-00, Page Block 301).

**CONF ALL

C. PROCEDURE

NOTE: The procedures that follow must be accomplished on the LH and RH wings.

**CONF 001

(1) Subtask 576046-831-401-001 - RE-PROFILE THE STRINGER RUN-OUTS

Work Zones and Access Panels

Zone Access/Work location

543 Work location from Rib 13 to Rib 14

643 Work location from Rib 13 to Rib 14

550 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

650 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Manpower Resources

Manhours 15.00

Minimum number of person 2

Subtask elapsed time 7.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti Corrosion Primer

Epoxy

04DAB2 As required

Non Aqueous Cleaner 08BAA9 As required

Chemical Conversion

Coating Yellow Aluminum

10ABC1 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-20

51-35-00

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

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@A300-600

SERVICE BULLETIN

References

Fig. A-UBAAA

LOCATION AND AREA OF

MODIFICATION

Sheet 01

NOTE: The procedures that follow must be accomplished on the LH and RH

wings.

Refer to Fig. A-UBAAA Sheet 01

(a) Cut the stringers 10, 11, 12 and 17 on bottom skin panel No. 3, adjacent to Rib 14

to the new contour as follows:

1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the

new profile to the contour shown on Fig. A-UBAAA Sheet 01.

2 Cut the stringers to the new contour, take care to remove only unwanted

material.

3 Deburr, blend and polish all cut edges.

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.

4 Clean the cut surfaces with

Non Aqueous

Cleaner

08BAA9 As required

(Refer to SRM 51-35-00 and AMM 20-31-00).

5 Apply

Chemical

Conversion Coating

Yellow Aluminum

10ABC1 As required

and

Anti Corrosion

Primer Epoxy

04DAB2 As required

to the cut surfaces (Refer to SRM 51-23-20 and Consumable Material List

(CML)).

(2) Subtask 576046-831-402-001 - RE-PROFILE THE STRINGER 19 RUN-OUT

Work Zones and Access Panels

Zone Access/Work location

543 Work location from Rib 13 to Rib 14

Stringer 19

643 Work location from Rib 13 to Rib 14

Stringer 19

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

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@A300-600

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti Corrosion Primer

Epoxy

04DAB2 As required

Non Aqueous Cleaner 08BAA9 As required

Chemical Conversion

Coating Yellow Aluminum

10ABC1 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Structural Repair Manual (SRM) 51-23-20

51-35-00

Fig. A-UBCAA

MODIFICATION TO END OF

STRINGER 19

Sheet 01

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

(a) Cut the end of stringer 19 on bottom skin panel No. 3, adjacent to Rib 14, to the

new contour as follows:

1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the

new profile to the contour shown on Fig. A-UBCAA Sheet 01.

2 Cut the end of stringer 19 to the new contour, take care to remove only

unwanted material.

3 Deburr, blend and polish all cut edges.

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.

4 Clean the cut surfaces with:

Non Aqueous

Cleaner

08BAA9 As required

(Refer to SRM 51-35-00 and AMM 20-31-00).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

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@A300-600

SERVICE BULLETIN

5 Apply

Chemical

Conversion Coating

Yellow Aluminum

10ABC1 As required

and

Anti Corrosion

Primer Epoxy

04DAB2 As required

to the cut surfaces (Refer to SRM 51-23-20 and AMM 20-31-00).

(3) Subtask 576046-831-403-001 - REMOVE THE STRINGER END RUN-OUT PLATE ON

STRINGER 19

Work Zones and Access Panels

Zone Access/Work location

543 Work location from Rib 13 to Rib 14

Stringer 19

643 Work location from Rib 13 to Rib 14

Stringer 19

Manpower Resources

Manhours 15.00

Minimum number of person 2

Subtask elapsed time 7.50

Skills AIRFRAME

Material necessary to do the job

Kit 576046B01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA5475-6K7 20 NUT

2 NSA5476VHK6-11 10 BOLT

3 NSA5476VHK6-14 10 BOLT

4 NSA5353-06A 40 WASHER

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Brushable Fuel Resistant

Coating

06HAA1 As required

Non Aqueous Cleaner 08BAA9 As required

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

DKA300576046-1 Durable Tooling 1 (1)

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

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@A300-600

SERVICE BULLETIN

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

EKA300576046-1 Expendable Tooling 1 (2)

FTIA300576046-1 Capital Tooling 1 (3)

NOTE (1): Durable tooling: Ref. DK-A300-57-6046-1

The durable tool kit contains the minimum quantity of durable tools

necessary to accomplish the Service Bulletin on one aircraft. If the

Service Bulletin is to be accomplished on more than one aircraft, the

number of durable kits required can be established by reference to SIL

51-012.

NOTE (2): Expendable tooling: Ref. EK-A300-57-6046-1

The expendable tool kit contains the quantity of expendable tools

required to accomplish the Service Bulletin on one aircraft. Order one

expendable tool kit for every aircraft on which this Service Bulletin is to

be accomplished.

NOTE (3): Capital tooling: Ref. FTI-A300-57-6046-1

The capital tools provided in this kit are not specific to this Service

Bulletin and are normally already available in operator’s stock as a long

term investment or can be loaned from FTI.

References

Aircraft Maintenance Manual (AMM) 20-31-00

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Structural Repair Manual (SRM) 51-35-00

51-40-20

51-40-21

51-40-41

51-40-46

51-43-00

51-76-10

51-76-20

Fig. A-UBBAA

STRINGER END RUN-OUT PLATE

REMOVAL

Sheet 01

Fig. A-UBDAA

SPLIT SLEEVE POSITION ON REAR

SPAR

Sheet 01

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

Refer to Fig. A-UBBAA Sheet 01

(a) Get these items from KITB01 to modify the LH and RH wings:

20 Nut NSA5475-6K7 Item 1

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@A300-600

SERVICE BULLETIN

10 Bolt-Hi Lok NSA5476VHK6-11 Item 2

10 Bolt-Hi Lok NSA5476VHK6-14 Item 3

40 Washer-Special NSA5353-06A Item 4

(b) Remove the stringer end run-out plate on stringer 19 on bottom skin panel No. 3,

adjacent to Rib 14 as follows:

1 Go into the fuel tank. Remove the sealant from the ten Nuts, Item (1) (Refer to

SRM 51-76-20).

2 Remove and discard these items (Refer to SRM 51-40-20):

10 Nut Item (1)

5 Taperlock Bolt Item (2)

5 Taperlock Bolt Item (3)

1 Stringer End Run-Out

Plate

Item (5)

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.

3 Remove all traces of sealant. Use

Non Aqueous

Cleaner

08BAA9 As required

to clean the surfaces of the rear spar and the stringer flange which were

connected to the Stringer End Run-Out Plate, Item (5) (Refer to SRM

51-76-20, SRM 51-35-00 and AMM 20-31-00).

4 Use procedure C of the Eddy Current Technique NTM 51-10-01 Part 6 to

do an inspection of the ten fastener holes. Report any defects to AIRBUS

for repair instructions. Do not continue until repair instructions have been

received.

5 Install slave bolts in each second hole of the ten fastener holes to hold the

bottom skin to the stringer and the rear spar.

6 Use the FTI Tools:

FTIA300576046-1 Capital Tooling 1

DKA300576046-1 Durable Tooling 1

EKA300576046-1 Expendable Tooling 1

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@A300-600

SERVICE BULLETIN

Drill and ream the holes through the spar to the cold expansion start drill

diameter of 8.789 to 8.864 mm (0.346 to 0.349 in.). Use the tools given as

follows:

Tool Name Tool Part No.

Start Drill Block CHS371J-10-3-N

Start Reamer CXSR-.3460/.3260-1

Start Drill CBSD-10-3-N-1

7 Examine the reamed start holes through the rear spar. Use the combination

plug gage, Part No. CXG-.3460/.3490/.3500.

NOTE: If a hole is found oversize or oval, report the defect to

AIRBUS.

8 Drill and ream the holes through the stringer 19 to the cold expansion start

size diameter of 8.738 to 8.813 mm (0.344 to 0.347 in.).

Use the tools given as follows:

Tool Name Tool Part No.

Start Drill Block CHS371J-10-3-N

Start Reamer CBSR-10-3-N-1

Start Drill CBSD-10-3-N-1

9 Examine the reamed start holes through stringer 19. Use the combination plug

gage, Part No. CBG-10-3-N-1.

NOTE: If a hole is found oversize or oval, report the defect to

AIRBUS.

10 Cold expand and final ream the holes. Use the tools given as follows (Refer to

Fig. A-UBDAA Sheet 01 and SRM 51-40-41):

Tool Name Tool Part No.

Split Sleeve CBS-10-3-N-23F

Mandrel CBM-10-3-N-1-40-V1

Nose Cap CBCE-14B-1023F

Mandrel Checking Fixture CBMG-10-3-N

Finish Reamer CBR-10-3-N-1-.3695

11 Countersink the holes to 100 degrees for the new Bolts, Items 2 and 3 (Refer

to SRM 51-40-46).

12 Deburr the edges of the holes.

13 Apply

Brushable Fuel

Resistant Coating

06HAA1 As required

under the head of the new Bolts, Items 2 and 3 (Refer to AMM 20-31-00).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

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@A300-600

SERVICE BULLETIN

14 On each wing, assemble in each of the non-slave bolted holes the interference

fit

2 Bolt-Hi Lok NSA5476VHK6-11 Item 2

and

3 Bolt-Hi Lok NSA5476VHK6-14 Item 3

and the

5 Nut NSA5475-6K7 Item 1

with a maximum quantity of

2 Washer-Special NSA5353-06A Item 4

for each of the Bolts, Items 2 and 3.

a Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210

and 230 lbf.in.) (Refer to SRM 51-40-21 and SRM 51-43-00).

15 Remove the five slave bolts.

16 Do worksteps 6_ thru 13_ for the holes that remain.

17 On each wing, for the five holes that remain, assemble the interference fit

3 Bolt-Hi Lok NSA5476VHK6-11 Item 2

and

2 Bolt-Hi Lok NSA5476VHK6-14 Item 3

and the

5 Nut NSA5475-6K7 Item 1

with a maximum quantity of

2 Washer-Special NSA5353-06A Item 4

for each of the Bolts, Items 2 and 3.

a Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210

and 230 lbf.in.) (Refer to SRM 51-40-21 and SRM 51-43-00).

(4) Subtask 576046-750-401-001 - DETAILED VISUAL AND HFEC INSPECTION

Work Zones and Access Panels

Zone Access/Work location

550 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 24

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650 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 57-21-64

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

(a) Make sure that the inspection area is sufficiently clean to do an eddy current

inspection.

(b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10,

11, 12 and 17 (Refer to NTM 57-21-64).

(c) If there are signs of cracks or damage at stringers 10, 11, 12 or 17, contact

AIRBUS.

(d) Use the results from the eddy current inspection to complete the Inspection Report

Form to identify areas of stringer damage (cracks) (Refer to APPENDIX 01:

INSPECTION REPORT FORM ).

**CONF 002

(1) Subtask 576046-831-401-001 - RE-PROFILE THE STRINGER RUN-OUTS

Work Zones and Access Panels

Zone Access/Work location

543 Work location from Rib 13 to Rib 14

643 Work location from Rib 13 to Rib 14

550 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

650 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Manpower Resources

Manhours 15.00

Minimum number of person 2

Subtask elapsed time 7.50

Skills AIRFRAME

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 25

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Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti Corrosion Primer

Epoxy

04DAB2 As required

Non Aqueous Cleaner 08BAA9 As required

Chemical Conversion

Coating Yellow Aluminum

10ABC1 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-20

51-35-00

Fig. A-UBAAA

LOCATION AND AREA OF

MODIFICATION

Sheet 01

NOTE: The procedures that follow must be accomplished on the LH and RH

wings.

Refer to Fig. A-UBAAA Sheet 01

(a) Cut the stringers 10, 11, 12 and 17 on bottom skin panel No. 3, adjacent to Rib 14

to the new contour as follows:

1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the

new profile to the contour shown on Fig. A-UBAAA Sheet 01.

2 Cut the stringers to the new contour, take care to remove only unwanted

material.

3 Deburr, blend and polish all cut edges.

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.

4 Clean the cut surfaces with

Non Aqueous

Cleaner

08BAA9 As required

(Refer to SRM 51-35-00 and AMM 20-31-00).

5 Apply

Chemical

Conversion Coating

Yellow Aluminum

10ABC1 As required

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 26

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SERVICE BULLETIN

and

Anti Corrosion

Primer Epoxy

04DAB2 As required

to the cut surfaces (Refer to SRM 51-23-20 and Consumable Material List

(CML)).

(2) Subtask 576046-831-402-001 - RE-PROFILE THE STRINGER 19 RUN-OUT

Work Zones and Access Panels

Zone Access/Work location

543 Work location from Rib 13 to Rib 14

Stringer 19

643 Work location from Rib 13 to Rib 14

Stringer 19

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti Corrosion Primer

Epoxy

04DAB2 As required

Non Aqueous Cleaner 08BAA9 As required

Chemical Conversion

Coating Yellow Aluminum

10ABC1 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Structural Repair Manual (SRM) 51-23-20

51-35-00

Fig. A-UBCAA

MODIFICATION TO END OF

STRINGER 19

Sheet 01

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

(a) Cut the end of stringer 19 on bottom skin panel No. 3, adjacent to Rib 14, to the

new contour as follows:

1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the

new profile to the contour shown on Fig. A-UBCAA Sheet 01.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 27

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2 Cut the end of stringer 19 to the new contour, take care to remove only

unwanted material.

3 Deburr, blend and polish all cut edges.

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.

4 Clean the cut surfaces with:

Non Aqueous

Cleaner

08BAA9 As required

(Refer to SRM 51-35-00 and AMM 20-31-00).

5 Apply

Chemical

Conversion Coating

Yellow Aluminum

10ABC1 As required

and

Anti Corrosion

Primer Epoxy

04DAB2 As required

to the cut surfaces (Refer to SRM 51-23-20 and AMM 20-31-00).

(3) Subtask 576046-831-403-002 - REMOVE THE STRINGER END RUN-OUT PLATE ON

STRINGER 19

Work Zones and Access Panels

Zone Access/Work location

543 Work location from Rib 13 to Rib 14

Stringer 19

643 Work location from Rib 13 to Rib 14

Stringer 19

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 576046B02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA5475-5K7 20 NUT

2 NSA5478VHK5-11 10 BOLT

3 NSA5478VHK5-14 10 BOLT

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 28

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 SL4087-05A 40 WASHER

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Brushable Fuel Resistant

Coating

06HAA1 As required

Non Aqueous Cleaner 08BAA9 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Structural Repair Manual (SRM) 51-35-00

51-40-20

51-40-21

51-40-41

51-40-44

51-40-46

51-43-00

51-76-10

51-76-20

Fig. A-UBBAA

STRINGER END RUN-OUT PLATE

REMOVAL

Sheet 01

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

Refer to Fig. A-UBBAA Sheet 01

(a) Get these items from KITB02 to modify the LH and RH wings:

20 Nut NSA5475-5K7 Item 1

10 Bolt-Hi Lok NSA5478VHK5-11 Item 2

10 Bolt-Hi Lok NSA5478VHK5-14 Item 3

40 Washer SL4087-05A Item 4

(b) Remove the stringer end run-out plate on stringer 19 on bottom skin panel No. 3,

adjacent to Rib 14 as follows:

1 Go into the fuel tank. Remove the sealant from the ten Nuts, Item (1) (Refer to

SRM 51-76-20).

2 Remove and discard these items (Refer to SRM 51-40-20):

10 Nut Item (1)

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 29

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5 Interference Fit Bolt Item (2)

5 Interference Fit Bolt Item (3)

1 Stringer End Run-Out

Plate

Item (5)

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.

3 Remove all traces of sealant. Use

Non Aqueous

Cleaner

08BAA9 As required

to clean the surfaces of the rear spar and the stringer flange which were

connected to the Stringer End Run-Out Plate, Item (5) (Refer to SRM

51-76-20, SRM 51-35-00 and AMM 20-31-00).

4 Use procedure B of the Eddy Current Technique NTM 51-10-01 Part 6 to

do an inspection of the ten fastener holes. Report any defects to AIRBUS

for repair instructions. Do not continue until repair instructions have been

received.

5 Drill and ream the holes through the stringer 19 to between 8.738 to 8.813

mm (0.344 to 0.347 in.) for second oversize interference fit bolts (Refer to

SRM 51-40-44).

6 Deburr the edges of the holes.

7 Apply

Brushable Fuel

Resistant Coating

06HAA1 As required

under the head of the new Bolts, Items 2 and 3 (Refer to AMM 20-31-00).

8 On each wing, install second oversize interference fit

5 Bolt-Hi Lok NSA5478VHK5-11 Item 2

and

5 Bolt-Hi Lok NSA5478VHK5-14 Item 3

and the

10 Nut NSA5475-5K7 Item 1

with a maximum quantity of

2 Washer SL4087-05A Item 4

for each of the Bolts, Items 2 and 3.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 30

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a Torque tighten the Nuts, Item 1 to between 1.413 and 1.525 m.daN (125

and 135 lbf.in.) (Refer to SRM 51-40-20 and SRM 51-43-00).

(4) Subtask 576046-750-401-001 - DETAILED VISUAL AND HFEC INSPECTION

Work Zones and Access Panels

Zone Access/Work location

550 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

650 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 57-21-64

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

(a) Make sure that the inspection area is sufficiently clean to do an eddy current

inspection.

(b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10,

11, 12 and 17 (Refer to NTM 57-21-64).

(c) If there are signs of cracks or damage at stringers 10, 11, 12 or 17, contact

AIRBUS.

(d) Use the results from the eddy current inspection to complete the Inspection Report

Form to identify areas of stringer damage (cracks) (Refer to APPENDIX 01:

INSPECTION REPORT FORM ).

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 31

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SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 576046-914-401-001 - APPLY SEALANTS

Work Zones and Access Panels

Zone Access/Work location

550 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Stringer 19

650 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Stringer 19

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Brushable Fuel Resistant

Coating

06HAA1 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Structural Repair Manual (SRM) 51-76-10

51-76-20

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

(a) Apply

Brushable Fuel

Resistant Coating

06HAA1 As required

(Refer to AMM 20-31-00) as a bead along the stringer flange edges and also to

fully cover all the Nuts, Item 1 and the Special Washers, Item 4 (Refer to SRM

51-76-20).

(b) Allow the sealant to cure (Refer to SRM 51-76-10).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 32

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(2) Subtask 576046-942-401-001 - CLOSE-UP

Work Zones and Access Panels

Zone Access/Work location

543 Access Panel 543DB

643 Access Panel 643DB

550 Access Panel 550BB

650 Access Panel 650BB

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 101

28-11-00, Page Block 501

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 access panels 543DB (643DB) and 550BB (650BB) between RIBS Rib

13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page

Block 101).

(c) Remove the access platform(s).

(d) Refuel the aircraft and inspect for leaks (Refer to AMM 28-11-00, Page Block 501).

**CONF 002

(1) Subtask 576046-914-401-001 - APPLY SEALANTS

Work Zones and Access Panels

Zone Access/Work location

550 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Stringer 19

650 Work location from Rib 14 to Rib 15

from Stringer 10 to Stringer 12

Stringer 17

Stringer 19

Manpower Resources

Skills AIRFRAME

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 33

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Brushable Fuel Resistant

Coating

06HAA1 As required

References

Aircraft Maintenance Manual (AMM) 20-31-00

Structural Repair Manual (SRM) 51-76-10

51-76-20

NOTE: The worksteps that follow are to be accomplished on both the LH and

RH wings.

(a) Apply

Brushable Fuel

Resistant Coating

06HAA1 As required

(Refer to AMM 20-31-00) as a bead along the stringer flange edges and also to

fully cover all the Nuts, Item 1 and the Special Washers, Item 4 (Refer to SRM

51-76-20).

(b) Allow the sealant to cure (Refer to SRM 51-76-10).

(2) Subtask 576046-942-401-001 - CLOSE-UP

Work Zones and Access Panels

Zone Access/Work location

543 Access Panel 543DB

643 Access Panel 643DB

550 Access Panel 550BB

650 Access Panel 650BB

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 101

28-11-00, Page Block 501

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 access panels 543DB (643DB) and 550BB (650BB) between RIBS Rib

13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page

Block 101).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 34

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@A300-600

SERVICE BULLETIN

(c) Remove the access platform(s).

(d) Refuel the aircraft and inspect for leaks (Refer to AMM 28-11-00, Page Block 501).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 35

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SERVICE BULLETIN

**CONF ALL

F

W

D

INBD

REAR SPAR

DATUM

FRONT SPAR

DATUM

LH WING SHOWN

RH WING SIMILAR

PLAN VIEW LH WING

BOTTOM SKIN PANEL No. 3

STGR8

STGR10

STGR11

STGR12

STGR13

STGR16

STGR17

STGR19

RIB12

RIB9

RIB10

RIB11

RIB13

RIB14

RIB15

CONTOUR BEFORE

MODIFICATION

31.50 mm

(1.24 in)

CONTOUR BEFORE

MODIFICATION

RIB14 DATUM

A

EXAMPLE FOR ALL

AFFECTED STRINGERS

31.50 mm

(1.24 in)

CONTOUR AFTER

MODIFICATION

CONTOUR AFTER

MODIFICATION

25° 25°

R 50.80 mm

(2.00 in)

R 50.80 mm

(2.00 in)

STRINGER 13 AND 16

NOT AFFECTED STRINGER

RUN−OUTS

A

D_SB_576046_7_BAAA_01_00

Figure A-UBAAA - Sheet 01

LOCATION AND AREA OF MODIFICATION

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 36

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SERVICE BULLETIN

**CONF ALL

INBD

A STRINGER END

RUN−OUT PLATE

A

PLAN VIEW LH WING

BOTTOM SKIN PANEL No. 3

F

W

D

INBD

REAR SPAR

DATUM

FRONT SPAR

DATUM

LH WING SHOWN

RH WING SIMILAR

STGR8

STGR10

STGR11

STGR12

STGR13

STGR16

STGR17

STGR19

RIB12

RIB9

RIB10

RIB11

RIB13

RIB14

RIB15

REAR SPAR

DATUM

RIB14

STGR19 DATUM

DATUM

(1) 1

(2) 2

4

(1) 1

(3) 3

4

(5)

D_SB_576046_7_BBAA_01_00

Figure A-UBBAA - Sheet 01

STRINGER END RUN-OUT PLATE REMOVAL

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 37

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**CONF ALL

PLAN VIEW LH WING

BOTTOM SKIN PANEL No. 3

RIB13

RIB14

RIB15

A

CONTOUR BEFORE

MODIFICATION

CONTOUR AFTER

MODIFICATION

30°

R 76.20 mm

(3.00 in)

R 15.20 mm

(0.60 in)

30.50 mm

(1.20 in)

STGR19

FRONT SPAR

DATUM

REAR SPAR

DATUM

A

STGR10

STGR11

STGR12

STGR13

STGR16

STGR17

STGR19

F

W

D

INBD

LH WING SHOWN

RH WING SIMILAR

D_SB_576046_7_BCAA_01_00

Figure A-UBCAA - Sheet 01

MODIFICATION TO END OF STRINGER 19

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 38

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**CONF 001

OR OUTBOARD PERMITTED.

SPAR DATUM

PLAN VIEW

SPLIT SLEEVE POSITION ± 10°

SPLIT SLEEVE ON INBOARD

IN RELATION TO SPAR DATUM.

D_SB_576046_7_BDAA_01_00

Figure A-UBDAA - Sheet 01

SPLIT SLEEVE POSITION ON REAR SPAR

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 39

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 40

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@A300-600

SERVICE BULLETIN

APPENDIX 01: INSPECTION REPORT FORM

**CONF ALL

Record the location of cracks on the Inspection Report Form shown below:

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 1

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SERVICE BULLETIN

APPENDIX 01: INSPECTION REPORT FORM

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN NO:

FINDINGS:

RETURN TO:

AIRBUS

FAX +33 (0)5 61 93 36 14

A300−57−6046

LOCATION OF FINDINGS

STRINGER 10

AIRCRAFT MSN:

FLIGHT CYCLES:

FLIGHT HOURS:

CUSTOMER SERVICE ENGINEERING − SEES2

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

YES NO

Structure.sbinspectionresult@airbus.com

DATE OF INSPECTION:

INSPECTION METHOD:

HIGH FREQUENCY

EDDY CURRENT

STRINGER 11

STRINGER 12

STRINGER 17

CRACKS FOUND

YES: PROVIDE DETAILS BELOW NO

D_SB_576046_7_RAAA_01_00

Figure A-URAAA - Sheet 01

INSPECTION REPORT FORM

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 2

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REPORTING SHEET

TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14

MODIFICATION No.: 10326H5339

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 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 1

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@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 18/94 SERVICE BULLETIN No.: A300-57-6046

REVISION No.: 02 - Jun 21/13 Page: 1

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