@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- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE

MEMBERS.

MODIFICATION No.: None

This page transmits Revision No.06 of Service Bulletin No.A300-57-6005

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 06 issued to:

- update the effectivity

- clarify aircraft not affected by this Service Bulletin

- add accomplishment instruction notes in the inspection tasks.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

Fig. A-USAAA FIGURE SOLUTION UPDATED R

PLANNING INFORMATION

EFFECTIVITY Effectivity has been updated R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

REASON REASON UPDATED R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

ACCOMPLISHMENT INSTRUCTIONS

TASK 576005- 832-895-001-INSPECTION Accomplishment instructions Notes added R

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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REVISION TRANSMITTAL SHEET

Subtask 576005-910-401-001 SUBTASK SOLUTION UPDATED R

Fig. A-UBAAA FIGURE SOLUTION UPDATED R

Fig. A-UCAAA FIGURE SOLUTION UPDATED R

Fig. A-UDAAA FIGURE SOLUTION UPDATED R

Fig. A-UEAAA FIGURE SOLUTION UPDATED R

Fig. A-UFAAA FIGURE SOLUTION UPDATED R

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

Revision 01 was issued to incorporate rewrites of Paras. 1 and 3 and amendments to references to

various manuals.

Revision 02 was issued to incorporate changes to the effectivity and changes to Paras. 1.B., 1.C. and

inclusion of the Summary pages.

Revision 03 was issued to incorporate Change Notices 2A through 2C, and include editorial changes

and updates to the effectivity.

Revision 04 issued to update the effectivity, to add new aircraft model C4-605R/F and the aircraft MSN

0755 and 0758. Also the statements for the approval and manpower are amended.

Revision No. 05 issued to re-introduce an inspection for aircraft Post Modification No. 05815H00968

and aircraft Post Modification No. 11133H05409. Service Bulletin No. A300-57-6006 (Mod. No.

05815H00968). For some aircraft this increases the inspection threshold, for other aircraft it cancels

the requirements of this Inspection Service Bulletin (ISB) depending on the aircraft configuration or

modification embodiment point.

The inspection thresholds and intervals relating to the embodiment of Modification No. 05815H00968

and Modification No. 11133H05409 are now included in the paragraph 1.E (2).

REVISION SEQUENCE

ORIGINAL: Aug 18/86

REVISION No. : 01 - Feb 26/93

REVISION No. : 02 - Dec 01/93

REVISION No. : 03 - Nov 25/97

REVISION No. : 04 - Oct 25/99

REVISION No. : 05 - Apr 25/13

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 2

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REVISION TRANSMITTAL SHEET

REVISION No. : 06 - Nov 14/13

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 3

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REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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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- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE

MEMBERS.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Calculations, confirmed by fatigue and fail safe testing, show that on flap beam 2, transverse cracking

may occur at the bolt holes of the flap beam base members and light alloy side members.

During fatigue testing, the flap beam 2 developed cracks at the steel base member and light alloy side

members lower flanges at approximately 43,000 simulated flights and failure occurred at approximately

48,000 simulated flights.

For aircraft with an average flight time (AFT) greater than or equal to 1.5 hours Service Bulletin No.

A300-57-6005 requires the flap beam 2 to be inspected upon completion of 15,000 Flight Cycles (FC).

Repeat inspections are required at intervals of 1,500 flights as long as cracks are not found.

Modification No. 05815H00968 (Service Bulletin No. A300-57-6006) introduces oversized interference fit

bolts in cold expanded holes in order to increase the fatigue life of the flap beam base and side

members. If no cracks are found, it is recommended that the modification should be embodied at the

following aircraft lives:

For aircraft with an AFT greater than or equal to 1.5 hours:

- 15,000 FC / 32,400 FH (whichever occurs first).

For aircraft with an AFT less than 1.5 hours:

- 16,200 FC / 24,300 FH (whichever occurs first).

The objective of this Service Bulletin requires the flap beam 2 to be inspected using ultrasonic

techniques to detect cracks that extend from the bolt holes in the steel base member and aluminium

side members.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 1

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SERVICE BULLETIN

SUMMARY

This Service Bulletin can detect signs of cracks at a sufficiently early stage of life to prevent the need to

do expensive and time consuming repairs.

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.

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

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

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

MNB MON MSR MXU OHY QTR SUD TAR THA 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 576005-832-895-001: INSPECTION

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 5.00

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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SERVICE BULLETIN

SUMMARY

APPENDICES

None

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 3

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SERVICE BULLETIN

SUMMARY

**CONF ALL

D_SB_576005_7_SAAA_01_00

A Z532 (Z632)

A

AREA OF INSPECTION

NOTE:

LH SHOWN

RH SIMILAR

Figure A-USAAA - Sheet 01

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 4

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@A300-600

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE

MEMBERS.

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

NOTE: This Service Bulletin is applicable to all A300-600 aircraft, all certified models

and all MSNs, except:

- A300F4-622R aircraft on which the following AIRBUS modifications

(Mod.) have been embodied: 11133H5409, 12047S21726, 12048S21727

and 12050S21744.

- A300F4-650R and A300F4-622R aircraft on which both AIRBUS Mod.

Nos. 11133H5409 and 12699S22372 have been embodied.

(1) Models

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

(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

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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SERVICE BULLETIN

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

0777-0794 0797 0799-0804 0836-0838

(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.

OPERATOR MSN

ABD 0529 0557

ABR 0683 0770

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

0737 0740 0753 0783

CES 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

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 0525 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

URS 0733

UZB 0717 0722

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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SERVICE BULLETIN

(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 0836 0837 0838

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

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Calculations, confirmed by fatigue and fail safe testing, show that on flap beam 2,

transverse cracking may occur at the bolt holes of the flap beam base members and

light alloy side members.

During fatigue testing, the flap beam 2 developed cracks at the steel base member and

light alloy side members lower flanges at approximately 43,000 simulated flights and

failure occurred at approximately 48,000 simulated flights.

For aircraft with an average flight time (AFT) greater than or equal to 1.5 hours Service

Bulletin No. A300-57-6005 requires the flap beam 2 to be inspected upon completion of

15,000 Flight Cycles (FC). Repeat inspections are required at intervals of 1,500 flights

as long as cracks are not found.

Modification No. 05815H00968 (Service Bulletin No. A300-57-6006) introduces oversized

interference fit bolts in cold expanded holes in order to increase the fatigue life of the

flap beam base and side members. If no cracks are found, it is recommended that the

modification should be embodied at the following aircraft lives:

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 3

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SERVICE BULLETIN

For aircraft with an AFT greater than or equal to 1.5 hours:

- 15,000 FC / 32,400 FH (whichever occurs first).

For aircraft with an AFT less than 1.5 hours:

- 16,200 FC / 24,300 FH (whichever occurs first).

(2) Objective/Action

The objective of this Service Bulletin requires the flap beam 2 to be inspected using

ultrasonic techniques to detect cracks that extend from the bolt holes in the steel base

member and aluminium side members.

(3) Advantages

This Service Bulletin can detect signs of cracks at a sufficiently early stage of life to

prevent the need to do expensive and time consuming repairs.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 576005-832-895-001: INSPECTION

(1) ULTRASONIC INSPECTION OF THE STEEL BASE MEMBER AND ALUMINIUM

SIDE MEMBER ON FLAP BEAMS 2 (LH/RH)

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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CONDITION CONFIGURATION INSPECTION

THRESHOLD

INSPECTION

INTERVAL

GRACE

PERIOD

Pre-Modification

05815H00968 or PreModification

11133H05409

15,000 FC / 32,400 FH

Post Modification

05815H00968 or PreModification

11133H05409 and bolts

less than 11.11 mm

(0.438 in) diameter

**33,000 FC / 71,200 FH

Post Modification

05815H00968 or PreModification

11133H05409 and bolts

not less than 11.11 mm

(0.438 in) diameter

**22,000 FC / 47,500 FH

For aircraft with

an average

flight time (AFT)

equal to or

more than 1.5

hours

Post Modification

11133H05409 33,000 FC / 71,200 FH

1,500 FC /

3,200 FH

300 FC /

640 FH

Crack found Contact Airbus Before next flight

Table 1: For aircraft with an average flight time (AFT) equal to or more than 1.5 hours

**NOTE: FC / FH from modification embodiment.

CONDITION CONFIGURATION INSPECTION

THRESHOLD

INSPECTION

INTERVAL

GRACE

PERIOD

Pre-Modification

05815H00968 or PreModification

11133H05409

16,200 FC / 24,300 FH

Post Modification

05815H00968 or PreModification

11133H05409 and bolts

less than 11.11 mm

(0.438 in) diameter

**35,600 FC / 53,400 FH

Post Modification

05815H00968 or PreModification

11133H05409 and bolts

not less than 11.11 mm

(0.438 in) diameter

**23,700 FC / 35,600 FH

For aircraft with

an average

flight time (AFT)

less than 1.5

hours

Post Modification

11133H05409 35,600 FC / 53,400 FH

1,600 FC /2,400

FH

300 FC /

640 FH

Crack found Contact Airbus Before next flight

Table 2: For aircraft with an average flight time (AFT) less than 1.5 hours

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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**NOTE: FC / FH from modification embodiment.

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 576005-832-895-001: INSPECTION

Get Access 2.00

On Aircraft

ULTRASONIC INSPECTION OF THE STEEL BASE

MEMBER AND ALUMINIUM SIDE MEMBER ON FLAP

BEAMS 2 (LH/RH)

2.00

Close-Up 2.00

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 5.00

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-41-00 20-16-00

24-00-00 27-50-00 27-50-21

57-20-35

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 57-20-11

K. PUBLICATION AFFECTED

None

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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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

None

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 576005-832-895-001 - INSPECTION

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

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

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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.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

Task Associated Data

Zone

532 632

Access

Door 575FB 675FB AL AR

Panel AL AR

Manpower

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 5.00

A. GENERAL

(1) Subtask 576005-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-00, Page Block 001

20-16-00, Page Block 201

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 57-20-11

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

the Consumable Materials List (CML).

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the circuit breaker safety precautions, refer to AMM 20-16-00, Page Block 201.

(e) For ultrasonic evaluation of crack lengths (Refer to NTM 57-20-11).

(2) Subtask 576005-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills NON SPECIFIC

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 12

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@A300-600

SERVICE BULLETIN

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

Service Bulletin.

B. PREPARATION

(1) Subtask 576005-941-401-001 - GET ACCESS TO THE FLAP BEAMS

Work Zones and Access Panels

Zone Access/Work location

532 Access Door 575FB, Door AL

Work location Panel 133VU

632 Access Door 675FB

Panel AR

Work location Panel 133VU

Manpower Resources

Skills AIRFRAME

References

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

27-50-00, Page Block 301

27-50-21, Page Block 401

57-20-35, Page Block 401

Consumable Material List (CML)

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Remove the fixed fairings from flap beam 2 (Refer to AMM 57-20-35, Page Block

401).

(c) Fully extend the flap (Refer to AMM 27-50-00, Page Block 301).

(d) Remove the moveable fairings from flap beam 2 (Refer to AMM 27-50-21, Page

Block 401).

(e) Put the access platform(s) in position below the flap beam 2.

C. PROCEDURE

(1) Subtask 576005-832-401-001 - ULTRASONIC INSPECTION OF THE STEEL BASE

MEMBER AND ALUMINIUM SIDE MEMBER ON FLAP BEAMS 2 (LH/RH)

Work Zones and Access Panels

Zone Access/Work location

532 Access Door 575FB

Panel AL

Work location Panel 133VU

632 Access Door 675FB

Panel AR

Work location Panel 133VU

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 13

7

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@A300-600

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-11 Part 4, Procedure A

57-20-11 Part 4, Procedure B

Fig. A-UBAAA

FLAP TRACK 2 SIDE MEMBER

ASSEMBLY

Sheet 01

Fig. A-UCAAA

FLAP TRACK 2 BASE MEMBER

ASSEMBLY

Sheet 01

Fig. A-UDAAA

FLAP TRACK 2 SIDE MEMBER

ASSEMBLY AREA OF INSPECTION

Sheet 01

Fig. A-UEAAA

SECTION THROUGH FLAP BEAM 2

ASSEMBLY

Sheet 01

Fig. A-UFAAA

FLOWCHART

Sheet 01

Refer to Fig. A-UFAAA Sheet 01 for the ultrasonic inspection procedure.

(a) Do an ultrasonic inspection of the steel base member of the flap beam 2 for cracks

that extend from the bolt holes (Refer to NTM 57-20-11 Part 4, Procedure A, Fig.

A-UBAAA Sheet 01, Fig. A-UCAAA Sheet 01, Fig. A-UDAAA Sheet 01 and Fig. AUEAAA Sheet 01).

(b) Do an ultrasonic inspection of the aluminium side members of the flap beam 2 for

cracks that extend from the bolt holes (Refer to NTM 57-20-11 Part 4, Procedure B,

Fig. A-UBAAA Sheet 01, Fig. A-UCAAA Sheet 01, Fig. A-UDAAA Sheet 01 and Fig.

A-UEAAA Sheet 01).

(c) If cracks are found in either of the side members or the base member that are to

the edge, or extend as much as 4.0 mm (0.157 in.) beyond the bolt hole, a repeat

inspection must be done every 250 FC.

(d) If cracks are found in either of the side members or the base member that are

more than 4.0 mm (0.157 in.) beyond the bolt hole, the flap beam must be replaced

before the next flight.

(e) If no cracks are found, refer to SUBTASK 576005-942-401 001 CLOSE-UP .

(f) All inspection results, including nil findings, should be sent to AIRBUS with a copy

of Fig. A-UCAAA Sheet 01 as a reporting form.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 14

7

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@A300-600

SERVICE BULLETIN

D. TEST

None

E. CLOSE-UP

(1) Subtask 576005-942-401-001 - CLOSE-UP

Work Zones and Access Panels

Zone Access/Work location

532 Access Door 575FB, Door AL

Work location Panel 133VU

632 Access Door 675FB, Door AR

Work location Panel 133VU

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 301

27-50-21, Page Block 401

57-20-35, Page Block 401

(a) Install the moveable fairings on flap beam 2 (Refer to AMM 27-50-21, Page Block

401).

(b) Fully retract the flaps (Refer to AMM 27-50-00, Page Block 301).

(c) Install the fixed fairings on flap beam 2 (Refer to AMM 57-20-35, Page Block 401).

(d) Restore the systems and the aircraft to the normal operating conditions.

(e) Report all findings, including nil finding to AIRBUS on the form provided in this

Service Bulletin.

(f) Remove the access platforms from flap beam 2 area.

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

equipment.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 15

7

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

SERVICE BULLETIN

**CONF ALL

AREA OF INSPECTION

AREA OF INSPECTION

FOR DETAILS SEE A−UCAAA

D_SB_576005_7_BAAA_01_00

A Z532 (Z632)

FWD

C/L

DUPLEX

DRIVE

LH SHOWN

RH SIMILAR

A

A

A

AREA OF INSPECTION

FOR DETAILS SEE A−UCAAA

A A

Figure A-UBAAA - Sheet 01

FLAP TRACK 2 SIDE MEMBER ASSEMBLY

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 16

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

A Z532 (Z632)

A

B

LH SHOWN

RH SIMILAR

TYPICAL

CRACK PROPOGATION

DIRECTION OF

F

W

D

VIEW ON UNDERSIDE OF

FLAP BEAM 2 ASSEMBLY

NOTE:

01 RECORD THE CRACK POSITIONS AND LENGTHS

01

IN BASE MEMBERS ON THIS FIGURE AND RETURN

THE INFORMATION BACK TO AIRBUS. D_SB_576005_7_CAAA_01_00

B

B

Figure A-UCAAA - Sheet 01

FLAP TRACK 2 BASE MEMBER ASSEMBLY

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 17

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

B

TYPICAL

CRACK PROPOGATION

A Z532 (Z632)

A

B

D_SB_576005_7_DAAA_01_00

LH SHOWN

RH SIMILAR

DIRECTION OF

Figure A-UDAAA - Sheet 01

FLAP TRACK 2 SIDE MEMBER ASSEMBLY AREA OF INSPECTION

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 18

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

LIGHT ALLOY

SIDE MEMBER

STEEL

STRAPS

STEEL

STRAPS

STEEL

BASE MEMBER

SECTION THROUGH FLAP BEAM 2 ASSEMBLY

THE LOWER HALF OF THE FLAP BEAM STRUCTURE CONSTITUTES A TENSION BOOM

ASSEMBLY MADE FROM THE FOLLOWING ELEMENTS: TWO LIGHT ALLOY SIDE MEMBERS,

A STEEL BASE MEMBER AND FOUR STEEL STRAPS, TWO EACH SIDE AS ILLUSTRATED ABOVE.

WHEN CRACKS ARE FOUND THE FOLLOWING LIMITATIONS APPLY:

DESCRIPTION REPEAT INSPECTIONS

A CRACK IN EITHER SIDE MEMBER

OR BASE MEMBER TO EDGE OR UP TO

4.000 mm (0.157 in) BEYOND BOLT HOLE.

CRACK IN EITHER SIDE MEMBER

OR BASE MEMBER GREATER THAN

4.000 mm (0.157 in) BEYOND BOLT HOLE.

250 FLIGHTS

REPLACE IMMEDIATELY

1.

2.

LIGHT ALLOY

SIDE MEMBER

D_SB_576005_7_EAAA_01_00

Figure A-UEAAA - Sheet 01

SECTION THROUGH FLAP BEAM 2 ASSEMBLY

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 19

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

YES NO

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

REPEAT INSPECTIONS AT

INTERVALS IN ACCORDANCE

D_SB_576005_7_FAAA_01_00

ULTRASONIC INSPECTION OF THE STEEL BASE MEMBER

OF THE FLAP BEAM 2 FOR CRACKS EXTENDING FROM

THE BOLT HOLES AND ULTRASONIC INSPECTION OF THE

ALUMINUM SIDE MEMBERS OF THE FLAP BEAM 2.

THRESHOLD IN ACCORDANCE WITH PARAGRAPH 1.E(2) 

ARE

THERE ANY

CRACKS?

WITH PARAGRAPH 1.E(2)

THE LENGTH

YES LESS THAN 4.000 mm NO

REPEAT INSPECTIONS

EVERY 250 FLIGHT

CYCLES

REPLACE FLAP BEAM

BEFORE NEXT FLIGHT

REPEAT INSPECTIONS AT

INTERVALS IN ACCORDANCE

WITH PARAGRAPH 1.E(2)

IS

(0.157 in) ?

Figure A-UFAAA - Sheet 01

FLOWCHART

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 20

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@A300-600

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE

MEMBERS.

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: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 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: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005

REVISION No.: 06 - Nov 14/13 Page: 1

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