EASA AD No.: 2013-0234R2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0234R2

Date: 07 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 operate 

an aircraft to which an AD applies, except in accordance with the requirements 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) exemption].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300 and A300-600 aeroplanes

TCDS Number: France No. 145

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2013-0234R1 dated 02 October 2013.

ATA 57 Wings – Flap Beam Base – Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300 aeroplanes, all certified models, all manufacturer serial numbers

(MSN), and

Airbus A300-600 aeroplanes, all certified models, 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 could adversely affect the structural integrity of 

the airframe.

To address this potential unsafe condition, Airbus issued Service Bulletin 

(SB) A300-57-0116 and SB A300-57-6005 and DGAC France issued AD 

1986-187-076(B), later revised, to require a repetitive inspection 

programme for A300 and A300-600 aeroplanes.

For A300 aeroplanes, and in the frame of the Extended Service Goal 

(ESG) exercise, it was shown that design changes (Airbus Mod.

4740/Airbus SB A300-57-0128 or Airbus Mod. 5815/Airbus SB A300-57-

0141) were not sufficient to enable full ESG life without inspections.
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For A300-600 aeroplanes, since 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 substantiate 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 Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time defined in Table 1 or in Table 2 of Appendix 1 

of this AD, as applicable to aeroplane model, and, thereafter, at intervals 

not to exceed those defined in Table 3 or in Table 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) 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 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 

members’ 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) of this AD 

does not constitute terminating action for the inspections required by 

paragraph (1) of this AD.

(5) Inspections, 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 paragraphs (1) and (2) of this 

AD. 

Ref. Publications: Airbus SB A300-57-0116 Revision 07 dated 19 September 2011.

Airbus SB A300-57-6005 Revision 05 dated 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 this 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.
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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.
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APPENDIX 1

Table 1: Inspection thresholds 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 hours (FH)

since first flight

A300B4-100

15 000 FC or

20 500 FH

since first flight

A300B4-200, 

A300C4-200,

A300F4-200

16 200 FC or

22 200 FH

since first flight

15 000 FC or

34 000 FH

since first flight

Aeroplanes on which 

Airbus Mod. 4740 

has been embodied

A300B2

12 000 FC or

13 500 FH

since Mod. 4740 embodiment

A300B4-100

12 000 FC or

16 400 FH

since Mod. 4740 embodiment

A300B4-200, 

A300C4-200,

A300F4-200

12 900 FC or

17 700 FH

since Mod. 4740 

embodiment

12 000 FC or

27 200 FH

since Mod. 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

since Mod. 5815 embodiment

A300B4-100

33 000 FC or

45 200 FH

since Mod. 5815 embodiment

A300B4-200, 

A300C4-200,

A300F4-200

35 600 FC or

48 800 FH

since Mod. 5815 

embodiment

33 000 FC or

74 900 FH

since Mod. 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

since Mod. 5815 embodiment

A300B4-100

22 000 FC or

30 100 FH

since Mod. 5815 embodiment

A300B4-200, 

A300C4-200,

A300F4-200

23 700 FC or

32 500 FH

since Mod. 5815 

embodiment

22 000 FC or

49 900 FH

since Mod. 5815 

embodiment
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APPENDIX 1 - continued

Table 2 : Inspection thresholds 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

16 200 FC or

24 300 FH

since first flight

15 000 FC or

32 400 FH

since 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

since Mod. 5815 

embodiment

33 000 FC or

71 200 FH

since Mod. 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

since Mod. 5815 

embodiment

22 000 FC or

47 500 FH

since Mod. 5815 

embodiment

Aeroplanes on which Airbus Mod. 11133 has 

been embodied

35 600 FC or

53 400 FH

since first flight

33 000 FC or

71 200 FH

since 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: Inspection intervals 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.