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.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) : 

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 A318-112, A318-121, A319-111, A319-112, A319-115, A319-132, 

A319-133, A320-214, A320-216, A320-232, 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 applicability 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 structural 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 ASNA2531-4 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 instructions of Airbus SB A320-53-1218. 

Ref. Publications : Airbus Service Bulletin A320-53-1218 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 & 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 – EIAS, 

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