EASA AD No.: 2013-0295

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0295

Date: 11 December 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 Change Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300-600 aeroplanes

TCDS Number: France No. 145

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD F-2004-002 (EASA approval 2003-2108)

dated 07 January 2004.

ATA 53

Fuselage – Center Section Frames and Stringers – Inspection / 

Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 aeroplanes, all certified models except model A300F4-622R, 

all manufacturer serial numbers.

Reason: During a scheduled inspection of the fuselage frame feet of an in-service 

A300-600 aeroplane, cracks were observed in Frame (FR) 43, FR 44, FR 45 

and FR 46 between stringer (STGR) 24 and STGR 30.

This condition, if not detected and corrected, could affect the structural integrity 

of the aeroplane.

To address this unsafe condition, DGAC France issued AD 2000-060-303 (later 

revised) to require repetitive inspections of the affected frames and stringers on 

both sides of the fuselage and, depending on findings, repairs, as specified in 

Airbus Service Bulletin (SB) A300-53-6122.

Subsequently, DGAC France issued AD F-2004-002 (EASA approval 2003-

2108), retaining the requirements of AD 2000-060-303R1, which was 

superseded, and required the embodiment of Airbus SB A300-53-6125 (Airbus 

modification 12168) in order to improve the life of the frame foot attachment.

Since DGAC France AD F-2004-002 was issued, a fleet survey and updated 

Fatigue and Damage Tolerance analyses were performed in order to 

substantiate the second A300-600 Extended Service Goal (ESG2) exercise. 

It was highlighted that the frame feet material change from 2024T3511 

(A300B4) to 7175T7351 (A300-600) had an impact on the frame feet fatigue life 

duration. Airbus SB A300-53-6122 was revised accordingly to decrease the 
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inspection thresholds and intervals. Subsequent SB revision introduced a 

second structural modification point (SMP2) for aeroplanes that embody Airbus 

SB A300-53-6125 (modification 12168).

For the reasons described above, this new AD retains the requirements of 

DGAC France AD F-2004-002, which is superseded, but requires those actions 

within the new thresholds and intervals as specified in Revision 04 of Airbus 

SB A300-53-6122.

Effective Date: 25 December 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless previously accomplished:

INSPECTION:

(1) Within the compliance time defined in Table 1 of this AD, as applicable 

depending on aeroplane configuration and Average Flight Time (AFT), and, 

thereafter, at intervals not to exceed those defined in Table 2 of this AD, 

accomplish a rotating probe inspection of the frame feet attachment holes 

of FR 41 to FR 46 in accordance with the instructions of Airbus SB 

A300-53-6122.

Note: For the purpose of this AD, the AFT shall be established as follows for 

the determination of: 

- The inspection threshold (TH), as the total accumulated flight hours (FH), 

counted from take-off to touch-down, divided by the total accumulated flight 

cycles (FC) at the effective date of this AD. 

- The first inspection interval (INT), as the total accumulated FH divided by the 

total accumulated FC at the time of the TH inspection.

- The second inspection INT onwards, as the FH divided by the FC 

accumulated between the last two inspections. 

Table 1: Inspection thresholds 

(whichever occurs first, FH or FC)

Aeroplane configuration AFT > 1,5 

FH/FC

AFT ≤ 1,5 

FH/FC

Aeroplanes on which 

Airbus SB A300-53-6125 

has not been accomplished

(threshold counted since 

aeroplane first flight) 

14 800

FH

6 800

FC

11 100

FH

7 400

FC

Aeroplanes on which 

Airbus SB A300-53-6125 

has been accomplished

(threshold counted from the 

date of accomplishment of 

SB A300-53-6125)

56 400 

FH 

26 100 

FC

42 300 

FH

28 200 

FC

Aeroplanes on which 

Airbus SB A300-53-6125 SMP2 

has been accomplished

(threshold counted from the 

date of accomplishment of 

SB A300-53-6125) 

69 400 

FH

32 100 

FC

52 000 

FH

34 700 

FC
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Table 2: Inspection intervals

(whichever occurs first, FH or FC)

Aeroplane configuration AFT > 1,5 

FH/FC

AFT ≤ 1,5 

FH/FC

All aeroplane configurations

(interval counted from the date 

of the last inspection)

7 800 

FH

3 600 

FC

5 800 

FH

3 900 

FC

(2) For an aeroplane which, on the effective date of this AD, has exceeded the 

applicable threshold and/or interval as specified in Table 1 or Table 2 of 

this AD, as applicable to aeroplane configuration, the initial compliance 

time (or Grace Period) is 1 000 FC counted from the effective date of this 

AD. However, this new compliance time must not exceed the compliance 

time as specified in Airbus SB A300-53-6122 at Revision 02.

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

discrepancies are detected, before next flight, accomplish the applicable 

corrective actions in accordance with the instructions of Airbus SB 

A300-53-6122 Revision 04.

(4) Corrective actions, as required by paragraph (3) of this AD, do not 

constitute terminating action for the repetitive inspections required by 

paragraph (1) of this AD. 

(5) Inspections and corrective actions, accomplished before the effective date 

of this AD in accordance with the instructions of Airbus SB A300-53-6122 

at original issue up to Revision 03, are acceptable to comply with the initial 

requirements of paragraphs (1) and (3) of this AD.

After the effective date of this AD, all repetitive inspections and corrective 

actions must be accomplished in accordance with the instructions of Airbus 

SB A300-53-6122 Revision 04.

MODIFICATION:

(6) Within the compliance time defined in Table 3 of this AD, as applicable 

depending on AFT, reinforce the upper frame feet fittings in accordance 

with the instructions of Airbus SB A300-53-6125 Revision 03.

Table 3: Compliance time for modification

(whichever occurs first, FH or FC)

AFT Compliance time (since 

aeroplane first flight)

Aeroplanes with 

AFT >1,5 FH/FC 18 200 FH or 8 400 FC

Aeroplanes with 

AFT ≤1,5 FH/FC 13 700 FH or 9 100 FC

(7) For aeroplanes which, before the effective date of this AD, have already 

been modified in production by Airbus modification 12168 or in-service 

through Airbus SB A300-53-6125 (at original issue up to Revision 02), 

not later than 6 months before reaching the action threshold defined in 

Table 4 of this AD, as applicable, depending on AFT, contact Airbus for 

further instructions and accomplish those instructions accordingly.
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Table 4: Action threshold for aeroplanes modified prior to this AD

(from the date of accomplishment of the modification

in production or in service, as applicable)

AFT Compliance time

AFT > 1.5 FC 32 100 FC

AFT ≤ 1.5 FC 34 700 FC

(8) For an aeroplane which, on the effective date of this AD, has exceeded the 

applicable compliance time as specified in Table 3 and/or the action 

threshold as specified in Table 4 of this AD, as applicable, depending on 

AFT, the initial compliance time (or Grace Period) is 1 000 FC counted 

from the effective date of this AD. However, this new compliance time must 

not exceed the compliance time as specified in Airbus SB A300-53-6125 at 

Revision 02.

(9) Modification of an aeroplane as required by paragraph (6) or (7) of this AD 

does not constitute terminating action for the repetitive inspections required 

by paragraph (1) of this AD.

Ref. Publications: Airbus SB A300-53-6122 original issue dated 09 February 2000, or Revision 01 

dated 05 September 2001, or Revision 02 dated 17 June 2002, or Revision 03

dated 25 August 2011, or Revision 04 dated 27 February 2012.

Airbus SB A300-53-6125 original issue dated 08 November 2000, or Revision 

01 dated 25 February 2005, or Revision 02 dated 13 September 2011, or

Revision 03 dated 13 September 2011.

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 01 October 2012 as 

PAD 12-124 for consultation until 29 October 2012. The Comment 

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

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.