EASA AD No.: 2013-0203

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0203

Date: 06 September 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):

A320 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not Applicable

Supersedure: None

ATA 53 Fuselage – Frame 47 Splice Plate Butt Joint Crossing Area –

Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A320-211, A320-212, A320-214, A320-215, A320-216, A320-231,

A320-232 and A320-233 aeroplanes, all manufacturer serial numbers, except 

those on which Airbus Modification (Mod) 31012 has been embodied in 

production.

Reason: During the full scale fatigue test on A320-200, cracks were reported at the 

splice plate of the frame (FR) 47 butt joint crossing area, both sides.

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

of the aeroplane.

Prompted by these findings, Airbus developed Mod 31012 and introduced this 

on the production line to modify the current 2 fastener row butt joint into a 3 

fastener row butt joint to prevent further damage. For in-service aeroplanes, a 

corresponding modification was developed and published as Airbus Service 

Bulletin (SB) A320-53-1271.

For the reason describe above, this AD requires repetitive special detailed

inspections (SDI) of the splice plate of the FR47 butt joint crossing area and, 

depending on findings, accomplishment of applicable corrective action(s).

This AD also introduces an optional modification, which constitutes terminating 

action for the repetitive SDI required by this AD.

Effective Date: 20 September 2013
EASA AD No.: 2013-0203

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

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

and, thereafter, at intervals not to exceed 14 800 flight cycles (FC) or

29 600 flight hours (FH), whichever occurs first, accomplish a SDI of the 

splice plate of FR47 butt joint crossing area (both sides) in accordance with 

the instructions of Airbus SB A320-53-1260.

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 44 000 FC or 

88 000 FH

Within 1 500 FC or 3 000 FH 

after the effective date of this 

AD

Equal to or more than 27 700 FC or 

55 400 FH, but less than 44 000 FC 

or 88 000 FH

Within 3 000 FC or 6 000 FH 

after the effective date of this 

AD, without exceeding

45 500 FC or 91 000 FH since 

aeroplane first flight

Less than 27 700 FC or 55 400 FH Before exceeding 30 700 FC 

or 61 400 FH since aeroplane 

first flight

(2) If, during any SDI as required by paragraph (1) of this AD, damage is

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

and accomplish those instructions accordingly.

(3) Modification of an aeroplane in accordance with the instructions of Airbus 

SB A320-53-1271 constitutes terminating action for the repetitive SDI

required by paragraph (1) of this AD.

Ref. Publications: Airbus SB A320-53-1260 original issue, dated 19 December 2012.

Airbus SB A320-53-1271 original issue, dated 18 December 2012.

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 02 July 2013 as PAD 13-091 for consultation until 

30 July 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 - Airworthiness Office – EIAS,

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