EASA AD No.: 2013-0048

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0048

Date: 04 March 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):

A300-600 aeroplanes

TCDS Number: France n° 145

Foreign AD: Non applicable

Supersedure: This AD supersedes DGAC France AD 94-269-171(B)R2 dated 11 March 1998.

ATA 53 Fuselage – Lower Corner of the Horizontal Stabilizer Cut-out 

Longeron in the Tail Cone – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 aeroplanes, all models, all manufacturer serial numbers,

except aeroplanes on which Airbus modification 6146 has been embodied in 

production.

Reason: During a full scale fatigue test, a crack was found at the lower corner of the 

assembly of the horizontal stabilizer cut-out, between Frame (FR)87 and FR89 

and between Stringer (STGR)24 and STGR27, Left Hand (LH) and Right Hand 

(RH) sides.

This condition, if not detected and corrected, could reduce the structural 

integrity of the aeroplane.

DGAC France issued AD 94-269-171 to require repetitive visual and High 

Frequency Eddy Current (HFEC) rotating probe inspections of the affected 

areas and subsequent corrective action, in case of cracks.

Since that AD was issued, a fleet survey and updated Fatigue and Damage 

Tolerance analyses have been performed to substantiate the second A300-600 

Extended Service Goal (ESG2) exercise. The results of these analyses have 

shown that the risk of cracks for these aeroplanes is higher than initially 

determined and that, consequently, the thresholds and intervals must be 

reduced to allow timely detection of these cracks and accomplishment of an 

applicable corrective action.

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

France AD 94-269-171(B) R2, which is superseded, and requires the 

accomplishment of these actions within the new thresholds and intervals 
EASA AD No.: 2013-0048

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

defined in Revision 03 of Airbus Service Bulletin (SB) A300-53-6042.

Effective Date: 18 March 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) After 17 December 1994 [the effective date of the original issue of DGAC 

France AD 94-269-171(B)R2], accomplish the following actions in 

accordance with the instructions and within the thresholds and intervals 

defined in Airbus SB A300-53-6042 Revision 03:

(1.1) A visual inspection of the lower horizontal-stabilizer cut-out 

longeron, the corner fitting, the skin strap and the skin between 

FR87 and FR89 and between STGR24 and STGR27, LH and RH

sides.

(1.2) An HFEC inspection of the flanges of the lower corner fittings and 

the edges of the outer skin and the edges of the longeron, the skin 

strap and the skin at the run-out of the corner fitting above the last 

eight fasteners.

(1.3) Removal of fasteners from the assembly of the lower corner fittings, 

longerons, skin straps and skin, a rotating probe inspection and, if 

no cracks are found, a cold expansion of the fastener holes.

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

cracks are found, before next flight, accomplish the applicable corrective 

actions in accordance with the instructions of Airbus SB A300-53-6042 

Revision 03.

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

of this AD in accordance with the instructions of Airbus SB A300-53-6042 

at original issue up to Revision 2, are acceptable to comply with the initial 

requirements of paragraphs (1) and (2) of this AD. After the effective date 

of this AD, the repetitive inspections required by paragraph (1) and the 

corrective actions required by paragraph (2) of this AD must be 

accomplished in accordance with the instructions of Airbus SB A300-53-

6042 Revision 03.

Ref. Publications: Airbus Service Bulletin A300-53-6042 Revision 03 dated 30 August 2012.

The use of later approved revisions of this document 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. This AD was posted on 25 January 2013 as PAD 13-021 for consultation 

until 22 February 2013. No comments were received during the 

consultation period.

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), 

Telephone: + 33 (0)5 6118-4139, Fax: + 33 (0)5 6193-4451