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- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2013

- 0234 R 2

Date: 0 7 October 2013

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, Part 21

. A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requ irements of that AD, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exempt ion]. 

### Design Approval Holder’s Name:

AIRBUS Type/ Mod el designation(s ):

A300 and A300

- 600 aeroplanes

TCDS Number: France No. 145

F oreign AD: Not applicable

Revision : This AD revises EASA AD 2013

- 0234 R1 dated 02 October 2013.



### ATA 57 Wings

– Flap B eam B ase
– Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A irbus A300 aeroplanes, all certified mod els, all manufacturer serial numbers (MSN) , and

Airbus A300

- 600 aeroplanes, all certified mod els, all MSN

, except :

- A300F4

- 622R aeroplanes on which all of the following Airbus modifications (Mod

. ) have been embodied : 11133, 12047, 12048 and 12050

.

- A300F4

- 605R and A300F4

- 622R aeroplanes on which both Airbus Mod. 11133 and 12699 have been embodied.

Reason: Fatigue and "fail safe" tests developed on a test specimen confirmed that cracks may appear and propagate from the bolt holes of the base member and the side members of flap beam No. 2. The development of such cracks , if not detected, could result in a rupture of flap beams No. 2 , which c ould adversely affect the structural inte grity of the airframe. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300

- 57

- 0 11 6 and SB A300

- 57

- 6005 and D GAC France issued AD 1986

- 187

- 076(B ) , later revised, to require a repetitive inspection programme for A300 and A300

- 600 aeroplane s

. For A300 aero planes

, and in the frame of the Extended Service G oal (ESG) exercise, it was sh own that design change s ( Airbus Mod

. 47 4 0 / Airbus SB A300

- 57

- 0128 or Airbus Mod. 5815 /Airbus SB A300

- 57

- 0141 ) were not sufficient to enable full ESG life without inspections.E ASA AD No.: 20 13

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- Internet/Intranet. For A300

- 600 aeroplanes, s ince DGAC France AD 1986

- 187

- 076(B ) was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substa ntiate the second A300

- 600 ESG2 exercise. Airbus SB A300

- 57

- 6005 has been revised accordingly to decrease the inspection thresholds and intervals.

For the reasons described above

, this AD retains the requirements of DGAC France AD 1986

- 187

- 076(B) R4

, which is superseded, and requires those inspections to be accomplished at reduced thresholds and intervals.

This AD has been revised to correct typographical errors in some compliance times defined in Appendix 1, Tables 1 and 2.

Effective Date: 08 October 2013 (same as original)

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the compliance time defined in T able 1 o r in T able 2 of Appendix 1 of this AD

, as applicable to aeroplane model

, and

, thereafter

, at intervals not to exceed those defined in T able 3 or in T able 4 of Appendix 1 of this AD , as applicable, accomplish an ultrasonic inspection of the steel base member and the aluminium side members ’ flap beam on the left hand (LH) and right hand (RH) side in accordance with the instructions of Airbus SB A300

- 57

- 0116 Revision 07 or SB A300

- 57

- 6005 Revision 05

, as applicable to aeroplane model

. (2) I f

, during any inspection as required by paragraph (1) of this AD

, a crack is found in the base member or a side member , and that crack extends to the edge of or up to 4 mm beyond the bolt hole

, within 250 flight cycles ( FC ) and, thereafter, at intervals not to exceed 250 FC, accomplish an ultrasonic inspection of the steel base member and the aluminium side

m embers’ flap beam on the LH and RH side in accordance with the instructions of Airbus SB A300

- 57

- 0116 Revision 07 or SB A300

- 57

- 6005 Revision 05, as applicable to aeroplane model

. (3) If

, during any inspection as required by paragraph (1) of this AD

, a crack is found in the base member or a side member , and that crack extends more than 4 mm beyond the bolt hole, before next flight

, replace the flap beam in accordance with the instructions of the applicable Structural Repair Manual / Aircraft Maintenance Manual, as applicable to aeroplane model

. (4) Replacement of the flap beam as required by paragraph (3) o f this AD does not constitute terminating action for the inspection s required by paragraph (1) of this AD. (5) Inspection s , accomplished before the effective date of this AD in accordance with any previous issue of Airbus SB A300

- 57

- 0116 or SB A300

- 57

- 6005

, as applicable to aeroplane model , are acceptable for compliance with the initial requirements of paragraph s (1) and (2) of this AD.

Ref. Public ations: Airbus SB A300

- 57

- 0116 Revision 07 dated 19 September 2011

. Airbus S B A300

- 57

- 6005 Revision 05 date d 25 April 2013

. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. The original issue of t his AD was posted on 20 August 2013 as PAD 13

- 121 for consultation until 17 September 2013

. The Comment Response Document can be found at http://ad.easa.europa.eu

.E ASA AD No.: 20 13

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- Internet/Intranet. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office) E

- mail: continued.airworthiness

- wb.external@airbus.com

.E ASA AD No.: 20 13

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- Internet/Intranet. 

### APPENDIX 1

Table 1: Inspection t hresholds for A300 (whichever occurs first, FC or FH)

Aeroplane configuration Compliance Time Average Flight Time (AFT) < 1,5 AFT ≥ 1,5

Aeroplanes on which Airbus Mod

. 4740 and Airbus Mod

. 5815 have not been embodied A300B2 15 000 Flight cycles (FC) or 16 900 Flight h ours (FH)

s ince first flight

A300B4

- 100 15 000 FC or 20 500 FH

s ince first flight A300B4

- 200

, A300C4

- 200, A300F4

- 200 16 200 FC or 22 200 FH

s ince first flight 15 000 FC or 34 000 FH

s ince first flight

Aeroplanes on which Airbus Mod

. 4740 has been embodied A300B2 12 000 FC or 13 500 FH

s ince M od

. 4740 embodiment

A300B4

- 100 12 000 FC or 16 400 FH

s ince M od

. 4740 embodiment

A300B4

- 200

, A300C4

- 200, A300F4

- 200 12 900 FC or 17 700 FH

s ince M od

. 4740 embodiment 12 000 FC or 27 2 00 FH

s ince M od

. 4740 embodiment

Aeroplanes on which Airbus Mod

. 5815 has been embodied and no bolt larger than 7/16 inch diameter is fitted A300B2 33 000 FC or 37 200 FH

s ince M od

. 5815 embodiment

A300B4

- 100 33 000 FC or 45 200 FH

s ince M od

. 5815 embodiment

A300B4

- 200

, A300C4

- 200, A300F4

- 200 35 600 FC or 48 800 FH

s ince M od

. 5815 embodiment 33 000 FC or 74 900 FH

s ince M od

. 5815 embodiment

Aeroplanes on which Airbus Mod

. 5815 has been embodied and at least one bolt 15/32 inch diameter is fitted A300B2 22 000 FC or 24 800 FH

s ince M od

. 5815 embodiment

A300B4

- 100 22 000 FC or 3 0 1 00 FH

s ince M od

. 5815 embodiment

A300B4

- 200

, A300C4

- 200, A300F4

- 200 23 700 FC or 32 500 FH

s ince M od

. 5815 embodiment 22 000 FC or 49 900 FH

s ince M od

. 5815 embodimentE ASA AD No.: 20 13

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- continued

Table 2 : Inspection t hresholds for A300

- 600 ( whichever occurs first, FC or FH )

Aeroplane configuration Compliance Time AFT < 1,5 AFT ≥ 1,5
Aeroplanes on which Airbus Mod

. 5815 and Airbus Mod 11133 have not been embodied 16 2 00 FC or 24 300 FH

s ince first flight 15 000 FC or 32 400 FH

s ince first flight
Aeroplanes on which Airbus Mod

. 5815 has been embodied and no bolt larger than 7/16

inch diameter is fitted 35 600 FC or 53 400 FH

s ince M od

. 5815 embodiment 33 000 FC or 71 200 FH

s ince M od

. 5815 embodiment
Aeroplanes on which Airbus Mod

. 5815 has been embodied and at least one bolt 15/32 inch

diameter is fitted 23 700 FC or 35 600 FH

s ince M od

. 5815 embodiment 22 000 FC or 47 500 FH

s ince M od

. 5815 embodiment
Aeroplanes on which Airbus Mod

. 11133 has

been embodied 35 600 FC or 53 400 FH

s ince first flight 33 000 FC or 71 200 FH

s ince first flight

Note : For A300

- 600 aeroplanes, a grace period of 300 FC or 640 FH , whichever occurs first after the effective date of this AD , may be applied for the initial inspection as required by paragraph (1) of this AD.

Table 3: I nspection i ntervals for A300 (whichever occurs first, FC or FH)

Aeroplane Compliance Time AFT < 1,5 AFT ≥ 1,5

A300B2 1 500 FC or 1 600 FH

A300B4

- 100 1 500 FC or 2 000 FH
A300B4

- 200

, A300C4

- 200, A300F4

- 200 1 600 FC or 2 200 FH 1 500 FC or

3 400 FH

Table 4 : Inspection intervals for A300

- 600 (whichever occurs first, FC or FH)

Aeroplane Compliance Time AFT < 1,5 AFT ≥ 1,5

A300

- 600 1 600 FC or 2 400 FH 1 500 FC or

3 200 FH

Note: For A300

- 600 aeroplanes, a grace period of 300 FC or 640 FH , whichever occurs first after the effective date of this AD , may be applied for the repetitive inspections as required by paragraph (1) of this AD.