EASA AD No : 2011-0035

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0035

Date: 02 March 2011

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 participat e in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft s hall be ensured by accomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [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) exemptio n].


### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A321 aeroplanes

TCDS Number : EASA.A.064

Foreign AD : Not applicable

Supersedure : None



### ATA 57 Wings – Centre Wing Box Lower Panel – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A321-131, A321-2 11, A321-212 and A321-231 aeroplanes, manufacturer serial numbers (MSN) 1293, 1299, 1307, 1333, 1356 and 1366.
Reason: During removal of one centre wing box (CWB) lower aft panel during production, the following defects were found : - an excessive layer of sealant in bet ween the lower panel and the rib pads,

and - small metal chips between the panel and rib pads. Investigations revealed that the me tal chips trapped between parts (panels and stiffeners) have a possible impa ct on fatigue life of CWB panels. Consequently, cracks in the bore holes of the CWB lower panel may occur in service, thereby reducing the st ructural integrity of the aeroplane. For the reasons describe above, this AD requires a special detailed inspection of CWB lower panel bore holes to detect any defect or crack and, depending on findings, associated corrective actions.

Effective Date: 16 March 2011EASA AD No : 2011-0035

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Before the accumulation of 24 000 flight cycles or 40 000 flight hours, whichever occurs first since the aerop lane first flight, perform a special detailed inspection of CWB lower panel bore holes and apply the associated corrective actions, in accordance with the instructions of Airbus Service Bulletin A320-57-1120 Revision 01.

Ref. Publications: Airbus Service Bulletin A320-57-1120 at Revision 01. 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 31 January 2011 as PAD 11-010 for consultation until 28 February 2011. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAS, Fax +33 5 61 93 44 51; account.airworth-eas@airbus.com

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