EASA AD No.: 2014-0276

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0276

Date: 19 December 2014

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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 71 Power Plant – Fan Cowl Door Hinge Nuts – Inspection / 

Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A319-111, A319-112, A319-115, A320-214,

A320-215, A320-216, A321-111, A321-112, A321-211, A321-212 and

A321-213 aeroplanes, all manufacturer serial numbers.

Reason: In-service findings have been reported of cracked cadmium plated lock nuts. 

This cracking occurs shortly after installation. Investigation results attribute the 

cause to an improper manufacturing procedure of the nuts. It was determined 

that the affected batch of lock nuts was used on the fan cowl to attach hinges to 

the cowl doors on CFM56-5B engines only. 

This condition, if not corrected, could lead to separation of the hinge from the 

fan cowl door, possibly resulting in in-flight loss of a fan cowl door, with 

consequent damage to the aeroplane and/or injury to persons on the ground.

For the reasons described above, this AD requires identification of the affected 

fan cowl doors, a one-time inspection of the fan cowl door hinge nuts and, 

depending on findings, replacement of the affected nuts. 

Effective Date: 02 January 2015
EASA AD No.: 2014-0276

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 24 months after the effective date of this AD, inspect each

engine fan cowl door to determine the serial number (s/n) in accordance 

with the instructions of Airbus Service Bulletin (SB) A320-71-1062, or

Goodrich Aerostructures SB RA32071-151.

A review of the aeroplane records is acceptable in lieu of the required 

inspection, provided those records are reliable and the s/n of the engine 

fan cowl door can be positively determined from that review.

(2) For an aeroplane with a fan cowl door, identified as required by

paragraph (1) of this AD, having a s/n between 10029001 and 11092003 

(inclusive), within 24 months after the effective date of this AD, accomplish 

a special detailed inspection (SDI) of the engine fan cowl door hinge nuts 

in accordance with the instructions of Airbus SB A320-71-1062, or 

Goodrich Aerostructures SB RA32071-151.

(3) If, during the SDI as required by paragraph (2) of this AD, any fractured nut 

is detected, before next flight, replace each affected nut in accordance with 

the instructions of Airbus SB A320-71-1062, or Goodrich Aerostructures 

SB RA32071-151.

Ref. Publications: Airbus SB A320-71-1062, original issue dated 28 July 2014.

Goodrich Aerostructures SB RA32071-151, original issue dated 11 June 2014.

The use of later approved revisions of these documents 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 13 October 2014 as PAD 14-148 for consultation 

until 10 November 2014. The Comment Response Document can be found 

at http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the Safety Information 

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.