EASA AD No.: 2014-0154

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0154

Date: 02 July 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 54 Nacelles / Pylons – Pylon Aft Fixed Fairing – Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A319-111, A319-112, A319-113, A319-114,

A319-115, A320-211, A320-212, A320-214, A320-215, A320-216, A321-111, 

A321-112, A321-211, A321-212 and A321-213 aeroplane models, all 

manufacturer serial numbers on which Airbus modification (mod) 33844 

(improvement of aerodynamic shape for CFM pylon) has been embodied in 

production.

Reason: On aeroplanes equipped with post-mod 33844 CFM pylons, several operators 

have reported cracks on the Aft Fixed Fairing (AFF). After material analysis, it 

appears that the pylon AFF structure, especially on this configuration, is subject 

to fatigue constraint damage which could lead to pylon AFF cracks. 

Further to these findings, Airbus released Alert Operators Transmission (AOT) 

A54N002-12 which provides instructions to inspect the pylon AFF, applicable 

only to aeroplanes incorporating Airbus production mod 33844 on CFM pylons. 

More recently, Airbus issued Service Bulletin (SB) A320-54-1027, superseding

AOT A54N002-12.

This condition, if not detected and corrected, could lead to detachment of a 

pylon AFF from the aeroplane, possibly resulting in injuries to persons on the 

ground. 

For the reasons described above, this AD requires repetitive detailed

inspections (DET) of the pylon AFF and, depending on findings, 

accomplishment of applicable corrective action(s).

Effective Date: 16 July 2014
EASA AD No.: 2014-0154

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance times defined in Table 1 of this AD, and, thereafter, 

at intervals not to exceed 3 750 flight hours (FH) or 2 500 flight cycles 

(FC), whichever occurs first, accomplish a DET of the pylon AFF in 

accordance with the instructions of Airbus SB A320-54-1027.

Table 1 – Initial DET

Affected 

aeroplanes

Compliance time

(as applicable, whichever occurs later,

A, B or C)

All A

Before exceeding 5 000 FC or 7 500 FH, 

whichever occurs first since aeroplane first 

flight

Inspection per AOT 

A54N002-12 

accomplished

B

Within 2 500 FC or 3 750 FH, whichever 

occurs first since the latest accomplishment 

of MPD task ZL 471-01, or since AOT 

A54N002-12 inspection

Inspection per AOT 

A54N002-12 not

accomplished

C

Within 750 FC or 1 500 FH, whichever 

occurs first after the effective date of this 

AD.

(2) If, during any DET as required by paragraph (1) of this AD, a crack is 

found, before next flight, accomplish the applicable corrective action(s) in 

accordance with the instructions of Airbus SB A320-54-1027.

(3) Accomplishment of corrective action(s) as required by paragraph (2) of this 

AD does not constitute terminating action for the repetitive DET required by 

paragraph (1) of this AD. 

Ref. Publications: Airbus AOT A54N002-12 dated 30 October 2012.

Airbus SB A320-54-1027 original issue dated 10 April 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 26 May 2014 as PAD 14-087 for consultation until 

23 June 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, Executive 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.