@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 TOP SKIN AT FRONT SPAR BETWEEN RIBS

1 AND 7

MODIFICATION No.: None

This page transmits Revision No.10 of Service Bulletin No.A300-57-6045

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 10 issued to update the tables in the compliance paragraph.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

COMPLIANCE

Accomplishment Timescale Amended inspection time scales R

ACCOMPLISHMENT INSTRUCTIONS

TASK 576045- 832-895-001-INSPECTION TASK SOLUTION UPDATED

NOTE UPDATED

CAUTION UPDATED

R

Subtask 576045-250-401-001 Amended inspection area R

Subtask 576045-833-401-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

PART NUMBER UPDATED

PART NUMBER DESCRIPTION UPDATED

R

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

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 02 was issued to inform operators that this Inspection Service Bulletin has been made

mandatory, the effectivity was also updated.

Revision 03 was issued to update the effectivity, to add aircraft model C4-605R/F and aircraft MSN

0755 and 0758. The standard sentences for the approval and manpower were also updated.

Revision 04 was issued to add the aircraft model F4-622R, update the aircraft effectivity and to add the

operator UPS.

Revision 05 was issued to update the aircraft effectivity for operator JAS. The effectivity was updated

generally.

Revision 06 was issued to update the aircraft effectivity for operators UPS and AHK. The effectivity has

also been updated generally.

Revision 07 was issued to include the latest delivered aircraft for UPS.

Revision 08 was issued to include revised thresholds/intervals quoted in Flight Cycles (FC) and Flight

Hours (FH), to enable aircraft operation to the relevant Extended Service Goal (ESG).

Revision No. 09 issued to update the accomplishment instructions. The inspection area is extended to

included the top wing skin overhang forward of the front spar. The required frequency of this mandatory

inspection has been updated in line with a new fatigue and damage tolerance analysis.

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

REVISION SEQUENCE

ORIGINAL: Mar 18/93

REVISION No. : 01 - Aug 03/94

REVISION No. : 02 - Apr 21/98

REVISION No. : 03 - Oct 25/99

REVISION No. : 04 - Jan 11/02

REVISION No. : 05 - Jun 13/03

REVISION No. : 06 - Jan 13/05

REVISION No. : 07 - Aug 14/08

REVISION No. : 08 - Jun 06/11

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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REVISION TRANSMITTAL SHEET

REVISION No. : 09 - May 21/13

REVISION No. : 10 - Nov 13/13

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 3

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REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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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 TOP SKIN AT FRONT SPAR BETWEEN RIBS

1 AND 7

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full-scale fatigue testing, cracks were found at the wing top skin front spar joints between Rib 1

and Rib 7 at approximately 33,000 to 49,000 simulated flights. The cracks started in clearance fit

fastener holes in the skin to spar joint.

More recently, seven instances of cracking have been reported to AIRBUS that started at the skin edge

or fastener holes close to the skin edge forward of the front spar around Rib 7. The cracks have

occurred at between 25,000 and 42,000 Flight Cycles (FC) with crack lengths up to 43.0 mm (1.69 in.).

As a result of these in-service findings, a mandatory Detailed Inspection (DI) is required to detect

cracks on the wing top skin at the front spar joint and between the front spar joint and the leading edge

overhang, between Ribs 1 and 7.

The required frequency of this mandatory inspection is altered in line with new fatigue and damage

tolerance analysis.

Early detection of cracks can prevent the necessity of extensive and costly repairs at a later stage.

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 NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

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SUMMARY

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPB01 See SB BOLT (PLUG-REPAIR)

EFFECTIVITY

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

ABD ABR AHK BCS CES F2I FDX GBG I2L IRA IRM KAC KAL

MGC MNB MON MSR MXU OHY QTR SUD TAR THA TMA UPS URS

UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 576045-832-895-001: INSPECTION

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 1.00

APPENDICES

APPENDIX 01: INSPECTION REPORT

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SUMMARY

**CONF ALL

LH SHOWN

RH SIMILAR

TYPICAL SKIN CRACK

AT LEADING EDGE OVERHANG

FRONT SPAR

TYPICAL SKIN CRACKS AT

FRONT SPAR ATTACHMENT

STRINGER

WING TOP SKIN

VIEW ON TYPICAL AREA

A

INSPECTION AREA

NOTE:

Z512 (Z612)

RIB7

RIB1 A

D_SB_576045_7_SAAA_01_00

Figure A-USAAA - Sheet 01

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SUMMARY

This Page Intentionally Left Blank

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7

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF TOP SKIN AT FRONT SPAR BETWEEN RIBS

1 AND 7

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/FC4-620 F4-605R

F4-622R

(2) Effectivity by MSN

0294 0344 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 0572

0575 0577 0579 0581 0584 0602-0605 0607-0608 0611 0613-0614 0617-0618 0621

0623 0625-0626 0629-0633 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670

0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711

0713 0715 0717 0719 0721-0730 0732-0746 0748-0750 0752-0764 0766-0775

0777-0794 0797 0799-0840 0845-0878

(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: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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OPERATOR MSN

ABD 0529 0557

ABR 0683 0770

AHK 0855 0856 0857 0858 0859 0860 0870 0871

BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730

0737 0740 0753 0783

CES 0525 0532 0707 0725 0732 0741 0746 0754 0763

F2I 0294 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 0726 0728 0735 0736 0738 0742 0745

0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774

0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799

0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878

GBG 0626 0643

I2L 0677

IRA 0632 0696 0723 0727

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

0750 0762 0773 0838

KAC 0344 0673 0694 0699 0719 0721

KAL 0631 0662

MGC 0743

MNB 0521 0734 0739 0755 0756 0758

MON 0556 0604 0605

MSR 0561 0607

MXU 0767 0788 0797 0836 0837

OHY 0584 0603 0744 0749 0764

QTR 0554 0560 0614

SUD 0666 0775

TAR 0505 0558 0563

THA 0464 0577 0629 0681 0705 0782 0784 0785 0786 0787

TMA 0872

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816

0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0839 0840 0845 0846 0847

0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865

0866 0867 0868 0869

URS 0733

UZB 0717 0722

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(4) Configuration by MSN

MSN CONFIGURATION

0294 0344 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 0554 0555 0556 0557 0558 0559

0560 0561 0563 0572 0575 0577 0579 0581 0584 0602 0603

0604 0605 0607 0608 0611 0613 0614 0617 0618 0621 0623

0625 0626 0629 0630 0631 0632 0633 0637 0641 0643 0657

0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683

0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713

0715 0717 0719 0721 0722 0723 0724 0725 0726 0727 0728

0729 0730 0732 0733 0734 0735 0736 0737 0738 0739 0740

0741 0742 0743 0744 0745 0746 0748 0749 0750 0752 0753

0754 0755 0756 0757 0758 0759 0760 0761 0762 0763 0764

0766 0767 0768 0769 0770 0771 0772 0773 0774 0775 0777

0778 0779 0780 0781 0782 0783 0784 0785 0786 0787 0788

0789 0790 0791 0792 0793 0794 0797 0799 0800 0801 0802

0803 0804 0805 0806 0807 0808 0809 0810 0811 0812 0813

0814 0815 0816 0817 0818 0819 0820 0821 0822 0823 0824

0825 0826 0827 0828 0829 0830 0831 0832 0833 0834 0835

0836 0837 0838 0839 0840 0845 0846 0847 0848 0849 0850

0851 0852 0853 0854 0855 0856 0857 0858 0859 0860 0861

0862 0863 0864 0865 0866 0867 0868 0869 0870 0871 0872

0873 0874 0875 0876 0877 0878

001

(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

Component COMPB01 As required

Consumable CMLB01 As required

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During full-scale fatigue testing, cracks were found at the wing top skin front spar joints

between Rib 1 and Rib 7 at approximately 33,000 to 49,000 simulated flights. The

cracks started in clearance fit fastener holes in the skin to spar joint.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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More recently, seven instances of cracking have been reported to AIRBUS that started

at the skin edge or fastener holes close to the skin edge forward of the front spar around

Rib 7. The cracks have occurred at between 25,000 and 42,000 Flight Cycles (FC) with

crack lengths up to 43.0 mm (1.69 in.).

(2) Objective/Action

As a result of these in-service findings, a mandatory Detailed Inspection (DI) is required

to detect cracks on the wing top skin at the front spar joint and between the front spar

joint and the leading edge overhang, between Ribs 1 and 7.

The required frequency of this mandatory inspection is altered in line with new fatigue

and damage tolerance analysis.

(3) Advantages

Early detection of cracks can prevent the necessity of extensive and costly repairs at a

later stage.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

NOTE: Inspection results must be reported to AIRBUS on the Inspection Report

attached to this Service Bulletin (Appendix 01). If there are findings, a report

is to be completed as follows:

- if there is damage which is not within the limits given in this Service

Bulletin, contact AIRBUS immediately (within 48 hours) and before the

next flight for repair instructions

- after the corrective action is completed; damage within limits and

repaired by the accomplishment of the repair instructions given in this

Service Bulletin OR damage is not within limits but repaired by the

accomplishment of the repair instructions given by AIRBUS.

If there are no findings, the Inspection Report has to be sent as soon as the

maintenance check or visit report has been completed by accomplishment of

this Service Bulletin.

To accomplish this Service Bulletin it is necessary to :

Task 576045-832-895-001: INSPECTION

(1) DO A DETAILED INSPECTION OF THE WING TOP SKIN AT THE FRONT

SPAR JOINT AND BETWEEN THE FRONT SPAR JOINT AND THE LEADING EDGE

OVERHANG BETWEEN RIBS 1 AND 7

(2) DO AN EDDY CURRENT INSPECTION OF THE CRACK(S) OR AT THE SIGN OF

CRACK(S)

(3) REPAIR THE CRACK(S) AS NECESSARY

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E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Normal Range Operation

Inspection Threshold Inspection Interval Grace Period

FC FH FC FH FC FH

22,000 49,500 6,500 14,100 1,300 2,800

Table 1: Detailed Inspection Programme for Freighters (F4-600(R))

Normal Range Operation

Inspection Threshold Inspection Interval Grace Period

FC FH FC FH FC FH

17,100 38,400 5,100 11,000 1,000 2,200

Table 2: Detailed Inspection Programme for Passenger Aircraft (B4-600, B4-600(R), C4-600 and

C4-600(R))

Short Range Operation

Inspection Threshold Inspection Interval Grace Period

FC FH FC FH FC FH

22,000 49,500 7,000 10,600 1,300 2,800

Table 3: Detailed Inspection Programme for Freighters (F4-600(R))

Short Range Operation

Inspection Threshold Inspection Interval Grace Period

FC FH FC FH FC FH

17,100 38,400 5,500 8,300 1,000 2,200

Table 4: Detailed Inspection Programme for Passenger Aircraft (B4-600, B4-600(R), C4-600 and

C4-600(R))

Freighters (F4-600(R)) Passenger Aircraft (B4-600, B4-600(R) and

C4-600)

FC FH FC FH

50 110 50 110

Table 5: Repeat Detailed Inspection Programme for Temporary Repairs

NOTE: For aircraft already within the inspection programme, the repeat detailed

inspection can be done at the next inspection interval. For all other

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aircraft the applicable grace periods identified in Tables 1, 2, 3 and 4

must be used for the first detailed inspection.

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

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

be used as the reference document for the mandated accomplishment timescale.

The initial detailed inspections and repeat intervals are specified in Tables 1, 2, 3 and 4.

The repeat detailed inspection intervals for aircraft with temporary repairs are specified

in Table 5.

NOTE: Tables 1 and 2 give figures for normal range, Tables 3 and 4 give figures

for short range (average flight time of less than 1.50 hours) operations.

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.

Task 576045-832-895-001: INSPECTION

Get Access 0.50

On Aircraft

DO A DETAILED INSPECTION OF THE WING TOP

SKIN AT THE FRONT SPAR JOINT AND BETWEEN

THE FRONT SPAR JOINT AND THE LEADING EDGE

OVERHANG BETWEEN RIBS 1 AND 7

0.50

DO AN EDDY CURRENT INSPECTION OF THE

CRACK(S) OR AT THE SIGN OF CRACK(S)

0.25

REPAIR THE CRACK(S) AS NECESSARY 0.25

Close-Up 0.50

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 1.00

H. WEIGHT AND BALANCE

Not Changed

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I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-07 51-10-08

Process and Material Specification (PMS)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-40 51-75-10

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

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

C. LIST OF COMPONENTS

No AIRBUS kit will be provided.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Lubricant 03RBB1 As required

Anti Corrosion Primer Epoxy 04DAB2 As required

Polyurethane Finish Paint 04JAA3 As required

General Purpose Solvent 08BAA9 As required

Chemical Conversion Coating

(Yellow Aluminum)

10ABC1 As required

Lint-Free Cotton Cloth 14SBA1 As required

(2) Components

Component COMPB01

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

NOTES

EN6114-3-8 1 BOLT (1)

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

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

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NOTE (1): For each crack found (that is between 6.0 and 75.0 mm (0.24 and 2.95

in. in length), you will require one EN6114-3-8 Bolt to fill the crack-stop

drill hole.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 576045-832-895-001 - 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.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

Task Associated Data

Zone

512 612

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 11

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SERVICE BULLETIN

Manpower

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 1.00

A. GENERAL

(1) Subtask 576045-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-10-07

51-10-08

Process and Material Specification

(PMS)

Structural Repair Manual (SRM) 51-24-00

51-40-40

51-75-10

(a) For the Process and Material Specification (PMS) (Refer to 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) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(d) For High Frequency Eddy Current (HFEC) inspection for surface cracks in

aluminum refer to NTM 51-10-08.

(e) For ultrasonic evaluation of crack lengths refer to NTM 51-10-07.

(f) For the apply of sealant refer to SRM 51-24-00.

(g) For the renewal of the protective finish refer to SRM 51-75-10.

B. PREPARATION

(1) Subtask 576045-941-401-001 - JOB SET-UP

Work Zones and Access Panels

Zone Access/Work location

512 Work location from Rib 1 to Rib 7

612 Work location from Rib 1 to Rib 7

Manpower Resources

Skills NON SPECIFIC

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 12

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SERVICE BULLETIN

(a) Put a WARNING NOTICE in position in the cockpit to tell persons not to operate

the flight controls.

(b) Put the SAFETY GUARD PN 98A27503003000 in position on the flap/slat control

lever quadrant.

(c) Put an Access Platform 3.0 m (10.0 ft.) in position below the applicable inspection

area in Zone 512 (612) between Rib 1 and Rib 7.

(d) Put the safety barriers in position.

(2) Subtask 576045-110-401-001 - PREPARE THE AREA FOR INSPECTION

Work Zones and Access Panels

Zone Access/Work location

512 Work location from Rib 1 to Rib 7

612 Work location from Rib 1 to Rib 7

Manpower Resources

Skills AIRFRAME

CLEANING

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

General Purpose Solvent 08BAA9 As required

Lint-Free Cotton Cloth 14SBA1 As required

References

Fig. A-UBAAA

TYPICAL SKIN CRACKS AT THE

FRONT SPAR ATTACHMENT/SKIN

OVERHANG

Sheet 01

(a) Use

Lint-Free Cotton

Cloth

14SBA1 As required

made moist with

General Purpose

Solvent

08BAA9 As required

to clean the wing top skin between the front spar joint and the leading edge

overhang, between Rib 1 and Rib 7 (Refer to Fig. A-UBAAA Sheet 01).

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 13

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C. PROCEDURE

(1) Subtask 576045-832-401-001 - DO A DETAILED INSPECTION OF THE WING TOP

SKIN AT THE FRONT SPAR JOINT AND BETWEEN THE FRONT SPAR JOINT AND

THE LEADING EDGE OVERHANG BETWEEN RIBS 1 AND 7

Work Zones and Access Panels

Zone Access/Work location

512 Work location from Rib 1 to Rib 7

612 Work location from Rib 1 to Rib 7

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-UBAAA

TYPICAL SKIN CRACKS AT THE

FRONT SPAR ATTACHMENT/SKIN

OVERHANG

Sheet 01

NOTE: The worksteps that follows are to be accomplished on the LH and RH

wings.

(a) Do a detailed inspection of the wing top skin in the area adjacent to its attachment

at the front spar, and between the front spar joint and the leading edge overhang

between Rib 1 and Rib 7 (Refer to Fig. A-UBAAA Sheet 01):

1 If there are no cracks, repeat the detailed inspection at the applicable intervals

specified in Para. 1.E.(2). Fill in the reporting sheet and return to AIRBUS. Go

to SUBTASK 576045-942-401 001 CLOSE-UP .

2 If you find cracks or signs of cracks, go to SUBTASK 576045-250-401 001 DO

AN EDDY CURRENT INSPECTION OF THE CRACK(S) OR AT THE SIGN

OF CRACK(S) .

(2) Subtask 576045-250-401-001 - DO AN EDDY CURRENT INSPECTION OF THE

CRACK(S) OR AT THE SIGN OF CRACK(S)

Work Zones and Access Panels

Zone Access/Work location

512 Work location from Rib 1 to Rib 7

612 Work location from Rib 1 to Rib 7

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 14

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Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

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

Fig. A-UCAAA

SPECIFICATION FOR THE MAXIMUM

PERMITTED CRACK LENGTH

Sheet 01

Sheet 02

(a) Do an Eddy Current inspection of the cracks or of the signs of cracks refer to NTM

51-10-08

(b) If there are cracks in the top skin in the area forward of the front spar attachment,

report to AIRBUS for repair instructions before the subsequent flight.

(c) If there are no cracks, do a repeat detailed inspection at the applicable intervals

specified in Para. 1.E.(2).

(d) If there are crack(s) at the spar attachment (or aft of the spar attachment), measure

the length of the crack(s) (Refer to Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA

Sheet 02):

1 If the crack(s) is/are less than 6.0 mm (0.236 in.) in length, do a repeat

detailed inspection of the crack(s) at the intervals specified in Table 5 of Para.

1.E.(2) Do not stop drill the crack(s).

2 If the crack(s) is/are more than 6.0 mm (0.236 in.) in length but less than the

maximum permitted length of 75.0 mm (2.953 in.):

a Do a temporary repair (stop drill and plug the crack(s)), go to SUBTASK

576045-833-401 001 REPAIR THE CRACK(S) AS NECESSARY .

b Do a repeat detailed inspection of the temporary repair(s) at the intervals

specified in Table 5 of Para. 1.E.(2) but not more than 250 FC / 550 FH

after the initial repair. No later than 250 FC / 550 FH after the initial

repair, a permanent repair must be embodied.

3 If the crack(s) is/are more than the maximum permitted length of 75.0 mm

(2.953 in.), contact AIRBUS before next flight for an approved repair(s).

(e) Complete the Inspection Report (Refer to APPENDIX 01: INSPECTION REPORT )

with inspection results or NIL findings.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 15

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SERVICE BULLETIN

(3) Subtask 576045-833-401-001 - REPAIR THE CRACK(S) AS NECESSARY

Work Zones and Access Panels

Zone Access/Work location

512 Work location from Rib 1 to Rib 7

612 Work location from Rib 1 to Rib 7

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Component COMPB01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

EN6114-3-8 1 BOLT (1)

NOTE (1): For each crack found (that is between 6.0 and 75.0 mm (0.24 and 2.95

in. in length), you will require one EN6114-3-8 Bolt to fill the crack-stop

drill hole.

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lubricant 03RBB1 As required

Anti Corrosion Primer

Epoxy

04DAB2 As required

Renew the protective finish 04JAA3 As required

Chemical Conversion

Coating (Yellow Aluminum)

10ABC1 As required

References

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

Structural Repair Manual (SRM) 51-24-00

51-40-40

51-75-10

Fig. A-UDAAA

TEMPORARY REPAIR OF A CRACK IN

THE SPECIFIED INSPECTION AREAS

Sheet 01

Sheet 02

Sheet 03

NOTE: This repair is not applicable to crack(s) found on the wing top skin

leading edge overhang. Any crack(s) found on wing top skin leading

edge overhang, contact AIRBUS.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 16

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SERVICE BULLETIN

(a) General

1 A crack from a fastener hole must be at least 6.0 mm (0.236 in.) in length

before it can be stop drilled. The minimum distance from the edge of the

crack-stop drill hole to the edge of any adjacent fastener countersink must not

be less than 6.0 mm (0.236 in.).

2 If a crack is too near to an adjacent fastener to be crack-stop drilled, contact

AIRBUS before the next flight for an approved repair.

3 A crack that ends in unsupported wing skin must be crack-stop drilled and the

hole plugged with a blind plug.

4 A crack that ends near the edge of the spar boom may have a crack-stop hole

that overlaps the spar boom edge, only if a blind plug is installed.

5 When a crack-stop hole has been plugged, the total length that must be

recorded on the inspection report is the length of the crack plus the diameter

of the plug.

NOTE: The direction of the cracks is usually chord wise.

(b) Temporary Repair (Stop Drill and Plug) of a Crack in the Specified Inspection Areas

Refer to Fig. A-UDAAA Sheet 01, Fig. A-UDAAA Sheet 02 and Fig. A-UDAAA

Sheet 03.

1 Obtain fastener hole diameters, drill and de-burr the crack-stop hole, refer to

SRM 51-40-40.

NOTE: Make sure that the crack-stop hole is in line with the direction

of the crack.

NOTE: Make sure that you position the crack-stop hole at a distance

that equals the thickness ’T’ in front of the end of the crack.

2 Do an Eddy Current inspection to make sure that the crack does not continue

through the crack-stop hole refer to NTM 51-10-08.

3 End-mill the crack-stop hole to the correct dimensions.

4 Ream the crack-stop hole to the correct diameter.

NOTE: Make sure that the crack-stop hole is reamed over the full

depth and that it has a surface finish of 1.6 micrometers (63

micro-inches).

5 De-burr the crack-stop hole.

6 Make a plug to the correct dimensions, as shown on Fig. A-UDAAA Sheet 03.

Use:

1 Bolt EN6114-3-8

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 17

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SERVICE BULLETIN

NOTE: Make sure that the plug has a surface finish of 1.6

micrometers (63 micro-inches).

7 Apply a layer of

Lubricant 03RBB1 As required

to the plug.

8 Install the plug in the crack-stop hole.

NOTE: Make sure that the plug is engaged over the full depth of the

crack-stop hole.

9 If necessary, mill the plug so that it is flush with the surface of the wing top

skin.

10 Apply

Chemical

Conversion Coating

(Yellow Aluminum)

10ABC1 As required

Anti Corrosion

Primer Epoxy

04DAB2 As required

and

Renew the

protective finish

04JAA3 As required

to the milled surface of the plug and the area around the plug as necessary, in

accordance with SRM 51-75-10 and SRM 51-24-00

D. TEST

None

E. CLOSE-UP

(1) Subtask 576045-942-401-001 - CLOSE-UP

Work Zones and Access Panels

Zone Access/Work location

512 Work location from Rib 1 to Rib 7

612 Work location from Rib 1 to Rib 7

Manpower Resources

Skills NON SPECIFIC

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

equipment.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 18

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SERVICE BULLETIN

(b) Remove the safety barriers.

(c) Remove the access platforms.

(d) Remove the SAFETY GUARD PN 98A27503003000 from the flap/slat control lever

quadrant.

(e) Remove the WARNING NOTICE from the cockpit.

(2) Subtask 576045-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills UTILITY

(a) Send the completed Inspection Report (Refer to APPENDIX 01: INSPECTION

REPORT ) with inspection results or NIL findings to AIRBUS.

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

Service Bulletin.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 19

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SERVICE BULLETIN

**CONF ALL

LH SHOWN

RH SIMILAR

TYPICAL SKIN CRACK

AT LEADING EDGE OVERHANG

FRONT SPAR

TYPICAL SKIN CRACKS AT

FRONT SPAR ATTACHMENT

STRINGER

WING TOP SKIN

VIEW ON TYPICAL AREA

A

INSPECTION AREA

NOTE:

Z512 (Z612)

RIB7

RIB1 A

D_SB_576045_7_BAAA_01_00

Figure A-UBAAA - Sheet 01

TYPICAL SKIN CRACKS AT THE FRONT SPAR ATTACHMENT/SKIN OVERHANG

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 20

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SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_CAAA_01_03

FRONT SPAR

(A)

(B)

DIAGRAM (B) SHOWS THE MAXIMUM

PERMITTED LENGTH OF A MULTIPLE CRACK.

DIAGRAM (A) SHOWS THE MAXIMUM

PERMITTED LENGTH OF A SINGLE CRACK.

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

NOTE:

TEMPORARY REPAIRS OF CRACKS IN THIS AREA ARE NOT PERMITTED.

F

W

D

TOP SKIN LEADING EDGE

TYPICAL

CRACK

01 TYPICAL CRACK FROM A FASTENER HOLE ADJACENT TO THE TOP SKIN LEADING EDGE.

FRONT SPAR

TOP SKIN LEADING EDGE

F

W

D

01

TYPICAL

CRACK 01

Figure A-UCAAA - Sheet 01

SPECIFICATION FOR THE MAXIMUM PERMITTED CRACK LENGTH

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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**CONF ALL

D_SB_576045_7_CAAA_02_00

(C2)

(C1)

DIAGRAMS (C1) AND (C2) SHOW THE MAXIMUM PERMITTED CRACK

LENGTHS WHEN ADJACENT HOLES ARE CRACKED.

75.0 mm

(2.95 in)

A + B < 40.0 mm (1.57 in)

A B

FRONT SPAR

75.0 mm

(2.95 in)

40.0 mm

(1.57 in)

TOP SKIN LEADING EDGE

TYPICAL

CRACK 01

TOP SKIN LEADING EDGE

TYPICAL

CRACK 01

FRONT SPAR

F

W

D

F

W

D

NOTE:

TEMPORARY REPAIRS OF CRACKS IN THIS AREA ARE NOT PERMITTED.

01 TYPICAL CRACK FROM A FASTENER HOLE ADJACENT TO THE TOP SKIN LEADING EDGE.

Figure A-UCAAA - Sheet 02

SPECIFICATION FOR THE MAXIMUM PERMITTED CRACK LENGTH

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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**CONF ALL

D_SB_576045_7_DAAA_01_00

6.21 mm TO 6.26 mm

C/L OF PLUG HOLE

LOCAL THICKNESS ’T’

EXTREMITY OF VISIBLE CRACK

SKIN

T

(0.2445 in TO 0.2465 in)

(0.035 in TO 0.040 in)

TOP BOOM OF

FRONT SPAR

CRACK IN UNSUPPORTED SKIN

CSK 100° x 0.89 mm TO 1.02 mm

SEE SHEET 3 FOR DETAILS OF PLUG.

NOTE:

Figure A-UDAAA - Sheet 01

TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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**CONF ALL

D_SB_576045_7_DAAA_02_00

OPERATION 1

OPERATION 2

OPERATION 3

RADIUS 0.76 mm TO 1.02 mm

1.14 mm TO 1.27 mm

DRILL Ø 4.76 mm (0.1875 in)

0.64 mm TO 0.89 mm

1.02 mm TO 1.14 mm

END MILL Ø 5.95 mm (0.2343 in)

REAM Ø 6.21 mm TO 6.26 mm

RADIUS 0.76 mm TO 1.02 mm

(0.025 in TO 0.035 in)

(0.040 in TO 0.045 in)

(0.2445 in TO 0.2465 in)

(0.045 in TO 0.050 in)

(0.030 in TO 0.040 in)

(0.030 in TO 0.040 in)

DETAILS OF CRACK−STOP HOLE ABOVE SPAR BOOM

CSK 100° x 0.89 mm TO 1.02 mm

(0.035 in TO 0.040 in)

Figure A-UDAAA - Sheet 02

TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

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SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_DAAA_03_00

SPAR B00M

LUBRICANT HOLE

(IF PLUG IS TO BE FITTED

INTO UNSUPPORTED SKIN,

DO NOT DRILL THIS HOLE.)

1.27 mm

0.76 mm

0.89 mm

LENGTH AS SKIN THICKNESS

Ø 0.79 mm (0.031 in)

DETAIL OF CRACK−STOP PLUG

A

A

PLUG TO BE MADE FROM BOLT EN6114−3−8

PLAIN LENGTH OF PLUG MUST BE IN CONTACT WITH FULL LENGTH

OF THE HOLE IN THE SKIN PANEL.

01

NOTE:

01

(0.030 in)

(0.050 in)

(0.035 in)

SKIN SKIN

Figure A-UDAAA - Sheet 03

TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 25

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 26

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SERVICE BULLETIN

APPENDIX 01: INSPECTION REPORT

**CONF ALL

AIRBUS

AIRBUS CUSTOMER SERVICES

Structural Engineering

E-mail: structure.sbinspectionresult@airbus.com

FAX: +33 (0)5 61 93 36 14

Write the results of the inspection on the INSPECTION REPORT below and send them to AIRBUS

SEES2.

INSPECTION REPORT

A/C MSN:

FLIGHT CYCLES:

FLIGHT HOURS:

FINDINGS: YES/NO*

SKETCH OF DAMAGE FOUND

(INCLUDE CRACK LENGTH,

CRACK DEPTH, EDGE

DISTANCE, ETC):

RECORD OF DAMAGE (INCLUDE HOLE LOCATION AND

NUMBER, REPAIR METHOD, ETC)

SERVICE BULLETIN No.: DATE OF INSPECTION:

SERVICE BULLETIN No.: DATE OF INSPECTION:

SERVICE BULLETIN No.: DATE OF INSPECTION:

PLEASE GIVE DETAILS OF

ANY OTHER FINDINGS:

AREA REPAIRED IN

ACCORDANCE WITH:

WINGS - INSPECTION OF THE WING TOP SKIN BETWEEN THE FRONT SPAR JOINT AND THE

LEADING EDGE OVERHANG BETWEEN RIBS 1 AND 7

* Delete as applicable

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 1

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SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - INSPECTION OF TOP SKIN AT FRONT SPAR BETWEEN RIBS

1 AND 7

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: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045

REVISION No.: 10 - Nov 13/13 Page: 1

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