EASA AD No : 2012-0034 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0034 

Date: 29 February 2012 

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) : 

A330 and A340-200/-300 aeroplanes 

TCDS Number : EASA.A.004, EASA A.015 

Foreign AD : Not applicable 

Supersedure : None 

ATA 32 Landing Gear – Nose Landing Gear (NLG) Retraction Actuator– 

Overhaul 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, 

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, 

A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial 

numbers (MSN), and 

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313 

aeroplanes, all MSN. 

Reason: An A330 aeroplane experienced an in-flight turn back due to inability to retract 

the NLG after take-off. 

The subsequent technical investigations revealed that the NLG retraction 

actuator eye-end fitting was detached from the retraction actuation rod, that 

both the eye-end male threads and piston rod female threads were almost 

completely stripped, and that there was evidence of significant corrosion on 

these parts. Further investigations have shown that corrosion caused the 

retraction actuator eye failure. 

This condition, if not corrected, could lead to NLG collapse after touchdown, 

potentially resulting in damage to the aeroplane and injury to its occupants. 

For the reasons described above, this AD requires accomplishment of an 

overhaul of the NLG retraction actuator. This AD also defines the Time Between 

Overhaul (TBO) for the NLG retraction actuator to be 10 years.

Effective Date: 14 March 2012 
EASA AD No : 2012-0034 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the compliance time indicated in Table 1 of this AD, whichever of A 

or B occurs later, and thereafter at intervals not to exceed 10 years (TBO), 

perform an overhaul of the NLG retraction actuator in accordance with the 

instructions of Airbus Service Bulletin (SB) A330-32-3255 or SB A340-32-

4291, as applicable to aeroplane type. 

Table 1 - Initial NLG Retraction Actuator overhaul

Compliance Time 

A Upon accumulation of 10 years by the NLG retraction

actuator from its first flight on an aeroplane or from its 

first flight following its last overhaul 

B If, on the effective date of 

this AD, the NLG 

retraction actuator has 

accumulated more than 8 

years and less than 14 

years from its first flight 

on an aeroplane 

Within 24 months after the 

effective date of this AD 

without exceeding 15 years 

from the NLG retraction 

actuator first flight on an 

aeroplane 

If, on the effective date of 

this AD, the NLG 

retraction actuator has 

accumulated 14 years or 

more from its first flight 

on an aeroplane 

Within 12 months after the 

effective date of this AD 

(2) After the effective date of this AD, do not install on an aeroplane any NLG 

retraction actuator, unless in compliance with the requirements of this AD. 

Ref. Publications : Airbus SB A330-32-3255 original issue, dated 13 October 2011. 

Airbus SB A340-32-4291 original issue, dated 13 October 2011. 

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 30 January 2012 as PAD 12-005 for consultation 

until 27 February 2012. No comments were received during the consultation 

period. 

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 SAS –Airworthiness Office – EIAL, 

E- mail: airworthiness.A330-A340@airbus.com.