EASA AD No.: 2013-0149

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0149

Date: 16 July 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 57 Wings – Centre Wing Box Struts – Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A320-111, A320-211, A320-212 and A320-231 aeroplanes, all 

manufacturer serial numbers (MSN) up to MSN 0136 inclusive.

Reason: Two cases of broken Centre Wing Box (CWB) struts have been reported on A320 

aeroplanes. Investigation results indicated that strut thickness in the crack 

initiation area was lower than specified in the production drawings. Only a limited 

batch of aeroplanes is affected by this manufacturing defect.

This condition, if not corrected, could result in strut failure, reducing the residual 

life of the remaining struts to below the initial Design Service Goal, which would 

deteriorate the structural integrity of the aeroplane.

For the reasons described above, this AD requires repetitive Detailed Visual 

Inspections (DVI) of the lower and upper ends of the CWB struts to detect cracks 

and, depending on findings, accomplishment of associated corrective actions.

Effective Date: 30 July 2013
EASA AD No.: 2013-0149

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the threshold indicated in Table 1 of this AD, as applicable, and 

thereafter at intervals not to exceed 16 800 flight cycles (FC) or 33 600 flight 

hours (FH), whichever occurs first, accomplish a DVI of the 38 struts of the 

CWB to detect any crack, in accordance with the instructions of Airbus 

Service Bulletin (SB) A320-57-1149 Revision 01.

Table 1 – Inspection Threshold

Compliance Time, whichever occurs later, A, B or C:

A Before accumulating 31 700 FC or 63 400 FH, whichever occurs 

first since aeroplane first flight 

B Before accumulating 16 800 FC or 33 600 FH, whichever occurs 

first since last inspection per Airbus SB A320-57-1149 original 

issue or Revision 01

C Within 1 250 FC or 2 500 FH, whichever occurs first after the 

effective date of this AD

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

discrepancies (as defined in Airbus SB A320-57-1149 Revision 01) are 

detected, before next flight, contact Airbus to obtain approved repair 

instructions and accomplish those instructions, including any follow-on 

actions, as applicable, accordingly.

Ref. Publications: Airbus SB A320-57-1149 at original issue dated 01 April 2008, or Revision 01

dated 12 February 2013.

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 22 August 2011 as PAD 11-091 for consultation until 

19 September 2011 and republished on 13 June 2013 as PAD 11-091R1 for 

additional consultation until 11 July 2013. No comments were received during 

the additional 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.