EASA AD No : 2011-0202 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0202 

Date: 13 October 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 

Supersedure: None 

ATA 32 Landing Gear – Landing Gear Control and Interface Unit (LGCIU) 

Wiring – Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, 

A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, 

A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, 

A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, 

A321-231 and A321-232 aeroplanes, all manufacturer serial numbers, except 

aeroplanes on which Airbus modification 37866 has been embodied in 

production. 

Reason: After a push back from the gate, an A320 aeroplane was preparing to initiate 

taxi, when an uncommanded nose landing gear (NLG) retraction occurred, 

causing the nose of the aeroplane to hit the ground. Investigations revealed 

that the retraction was caused by a combination of a power interruption to 

LGCIUs and an internal hydraulic leak through the landing gear (LG) selector 

valve 40GA. 

Deeper investigations have revealed that LGCIU power interruption appears 

during engine start at each flight. Even though no incident has been reported 

in service, it has been determined that a non compliance to the safety 

objective exists when combined with a dormant single failure of the selector 

valve seal leaking. 

This condition, if not corrected, could lead to further incidents of untimely 

unlocking and/or retraction of the NLG which, while on the ground, could 

result in injury to ground personnel and damage to the aeroplane. 

To address the possible hydraulic leak of the LG selector valve, EASA issued 

AD 2007-0065, currently at Revision 2. 
EASA AD No : 2011-0202 

EASA Form 110 Page 2/2 

For the reasons described above, this AD requires installation of a power 

interruption protection circuit to the LGCIU and the accomplishment of 

associated modifications. 

Effective Date: 27 October 2011 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the compliance time specified in Table 1 of this AD, as applicable 

to aeroplane configuration, modify the aeroplane in accordance with the 

accomplishment instructions of Airbus SB A320-32-1346 Revision 04 or, 

for Corporate Jet (A319CJ) aeroplanes, in accordance with the 

accomplishment instructions of Airbus SB A320-32-1349 Revision 02, as 

applicable to the aeroplane model. 

Table 1 

Aeroplane Configuration Compliance time, after the 

effective date of this AD 

Modified in accordance with Airbus 

mod 38947 in production, or in 

accordance with Airbus SB A320-32-

1348 in-service 

Within 72 months 

All other aeroplanes Within 60 months 

(2) For aeroplanes that have already been modified, before the effective date 

of this AD, in accordance with the instructions of Airbus A320-32-1346 at 

original issue, within the threshold indicated in Table 1 of this AD, as 

applicable to the aeroplane configuration, accomplish the actions 

identified as ‘additional work’ in accordance with the instructions of Airbus 

SB A320-32-1346 Revision 04. 

(3) Aeroplanes modified, before the effective date of this AD, in accordance 

with the instructions of Airbus SB A320-32-1346 Revision 01, or Revision 

02, or Revision 03, or in accordance with the accomplishment instructions 

of Airbus SB A320-32-1349 Original issue or Revision 01, as applicable 

to the aeroplane model, are compliant with the requirements of paragraph 

(1) of this AD. 

Ref. Publications: Airbus SB A320-32-1346 Revision 04 dated 22 April 2011. 

Airbus SB A320-32-1349 Revision 02 dated 16 June 2010. 

Airbus SB A320-32-1348 original issue dated 03 December 2008. 

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 28 July 2011 as PAD 11-079 for consultation until 

25 August 2011. 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.