EASA AD No.: 2013-0310

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0310

Date: 20 December 2013

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, 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, P art 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 ac complishing any applicable ADs. Consequently, no pe rson 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): A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage – Tack and Rivet Holes in Fitting Brackets at Frame 50 to

Frame 63 – Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-211, A320-212, A320-214, A 320-215, A320-216, A320-231, A320-232, A320-233, A321-111, A321-112, A 321-131, A321-211, A321-212, A321-213, A321-231 and A321-232 aeroplane s, all manufacturer serial numbers.
Reason: During a full scale fatigue test, several b roken frames in the cargo compartment area between Frame (FR) 50 and FR 63, have been fou nd, especially on the cargo floor support fittings and open tack holes on left hand side. This condition, if not detected and corrected, coul d affect the structural integrity of the aeroplane. For the reason described above, this AD requires re petitive inspections of the frames in the cargo compartment area and of the car go floor support fittings and open tack holes on the left hand (LH) side and, dep ending on findings, the accomplishment of applicable corrective action(s). This AD also requires a modification, which constitutes terminating action for the repetitive inspections required by this AD.

Effective Date: 03 January 2014EASA AD No.: 2013-0310

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within the compliance time(s) defined in Table 1 of this AD, as applicable, and, thereafter, at intervals not to exceed 5 000 f light cycles (FC) or 10 000 flight hours (FH), whichever occurs first, accompli sh a rototest inspection of open tack holes and rivet holes at the cargo floor support fittings between frame (FR) 50 and FR 63 (LH side only) for A320/A32 1 aeroplanes, and between FR 53 and FR 63 (LH side only) for A319 aer oplanes, as applicable, in accordance with the instructions of Airbus SB A3 20-53-1257. Table 1 - Initial inspection

Time accumulated on the effective date of this AD (whichever occurs first since aeroplane first flight) Compliance Time (whichever occurs first)

Equal to or more than 45 000 FC or 90 000 FH Within 1 000 FC or 2 000 FH after the effective date of this AD Equal to or more than 36 200 FC or 72 400 FH, but less than 45 000 FC or 90 000 FH Within 2 000 FC or 4 000 FH after the effective date of this AD, but not exceeding 46 000 FC or 92 000 FH since aeroplane first flight Less than 36 200 FC or 72 400 FH Before exceeding 3 8 200 FC or 76 400 FH since aeroplane first flight (2) If, during any inspection as required by paragr aph (1) of this AD, a crack is detected, before next flight, contact Airbus for ap proved repair instructions and accomplish those instructions accordingly. (3) Before exceeding 48 000 FC or 96 000 FH, whiche ver occurs first since first flight, modify the aeroplane in accordance with the instructions of Airbus SB A320-53-1261. (4) Modification of an aeroplane as required by par agraph (3) of this AD constitutes terminating action for the repetitive i nspections required by paragraph (1) of this AD for that aeroplane.
Ref. Publications: Airbus SB A320-53-1257 original Issue dated 21 December 2012. Airbus SB A320-53-1261 original Issue dated 21 Dece mber 2012, or Revision 01 [to be issued]. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 06 February 2013 as PASD 1 3-030 for consultation until 06 March 2013, and re-published on 07 August 2013 as PAD 13-030R1 for additional consultation until 04 September 2013 . The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS - Airworthiness Office - EIAS. Fax +33 5 61 93 44 51. E-mail: account.airworth-eas@airbus.com

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