EASA AD No : 2011-0120R1

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0120R1

Date: 13 July 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.3 B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any app licable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance wi th the requirements of that AD, unless otherwise specified b y 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) :
A318, A319, A320 and A321 aeroplanes

TCDS Number : EASA.A.064

Foreign AD : Not applicable

Revision : This AD revises EASA AD 2011-0120 dated 29 June 2011.



### ATA 53 Fuselage – Nuts – Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A3 18-112, A318-121, A319-111, A319-112, A319-115, A319-132, A319-133, A320-214, A320-216, A3 20-232, A320-233, A321-211, A321- 212, A321-213 and A321-231 aeroplane models, manufacturer serial numbers (MSN): 3339, 3340, 3350, 3355, 3360, 3367, 3369, 3372, 3380, 3382, 3385, 3387, 3388, 3390, 3393, 3395, 3397 to 3508 inclusive, 3510 to 3519 inclusive, 3522, 3523, 3525, 3527, 3529, 3530, 3537, 3539, 3542, 3544, 3546, 3548, 3552 and 3555.

Reason: During structural part assembly in Airbus production line, some nuts Part Number (P/N) ASNA2531-4 were found cracked. Investigations were performed to determine the batches of the affected nuts and had revealed that these nuts have been installed in production on the fuselage of aeroplanes listed in the applic ability section of this AD. Static, fatigue and corrosion tests were performed, which demonstrated that no immediate maintenance action is necessary. However, a large number of these nuts are fitted on primary struct ural elements, which could have longterm consequences. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes. For the reasons described above, this AD requires a detailed inspection of the affected nuts, associated corrective actions, depending on findings, and replacement of the affected P/N ASN A2531-4 nuts with new ones, having the same P/N. This AD has been revised to reduce the Applicability. Since no spare nuts have been delivered to operators for installation on Airbus aeroplanes, only the Models and MSN listed in the Airbus SB are affected by this AD.EASA AD No : 2011-0120R1

EASA Form 110 Page 2/2 Effective Date: Revision 1: 27 July 2011 Original issue: 13 July 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished: (1) For nuts P/N ASNA2531-4 located in the fuselage, within 6 years after the aeroplane first flight, perform a detailed inspection of these nuts, apply the associated corrective actions, depending on findings, and replace all nuts by new ones having the same P/N, in accordance with the instructions of Airbus SB A320-53-1218. (2) Within 90 days after the accomplishment of the inspections required by paragraphs (1) of this AD, report to Airbus the inspection results, in accordance with the instructio ns of Airbus SB A320-53-1218.

Ref. Publications : Airbus Service Bulletin A 320-53-1218 at original issue dated 08 February 2010, or Revision 01 dated 17 June 2010. 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. The original issue of this AD was posted on 04 May 2011 as PAD 11- 047 for consultation until 01 June 2011. The Comment Response Documents can be found at http://ad.easa.europa.eu/

. 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 te chnical 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

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