EASA AD No.: 2013-0310

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0310 

Date: 20 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 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, A320-215, A320-216, 

A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, 

A321-212, A321-213, A321-231 and A321-232 aeroplanes, all manufacturer serial 

numbers. 

Reason: During a full scale fatigue test, several broken frames in the cargo compartment 

area between Frame (FR) 50 and FR 63, have been found, especially on the 

cargo floor support fittings and open tack holes on left hand side. 

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

the aeroplane. 

For the reason described above, this AD requires repetitive inspections of the 

frames in the cargo compartment area and of the cargo floor support fittings and 

open tack holes on the left hand (LH) side and, depending 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 2014 
EASA AD No.: 2013-0310

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Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

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

and, thereafter, at intervals not to exceed 5 000 flight cycles (FC) or 10 000 

flight hours (FH), whichever occurs first, accomplish 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/A321 aeroplanes, and 

between FR 53 and FR 63 (LH side only) for A319 aeroplanes, as applicable, 

in accordance with the instructions of Airbus SB A320-53-1257. 

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 38 200 FC or 

76 400 FH since aeroplane first 

flight 

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

detected, before next flight, contact Airbus for approved repair instructions 

and accomplish those instructions accordingly. 

(3) Before exceeding 48 000 FC or 96 000 FH, whichever 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 paragraph (3) of this AD 

constitutes terminating action for the repetitive inspections 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 December 2012, or Revision 01 

[to be issued]. 

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. This AD was posted on 06 February 2013 as PASD 13-030 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 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 - Airworthiness Office - EIAS. 

Fax +33 5 61 93 44 51. E-mail: account.airworth-eas@airbus.com.