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 participate 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 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]. 

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, A321-211, 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 between the lower panel and the rib pads, 

and 

- small metal chips between the panel and rib pads. 

Investigations revealed that the metal chips trapped between parts (panels 

and stiffeners) have a possible impact on fatigue life of CWB panels. 

Consequently, cracks in the bore holes of the CWB lower panel may occur 

in service, thereby reducing the structural 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 2011 
EASA 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 aeroplane 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 & Research Section, Certification 

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 – EAS, 

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