EASA AD No : 2010-0034 

EASA Form 110 Page 1/3 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0034 

[Correction: 08 March 2010] 

Date: 05 March 2010 

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) Main Fitting and 

Sliding Tube - Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, -

303, -321, -322, -323, -341, -342 and -343, all manufacturer serial 

numbers (MSN), and 

Airbus A340 aeroplanes, models -211, -212, -213, -311, -312, -313, all 

MSN, 

if fitted with the following Nose Landing Gears : 

Part Number Serial Number 

D23285200 B2 

D23285101-7 B58

D23285101-10 B75

D23581100-1 B124

D23581100-1 B159

D23581100-7 B386
EASA AD No : 2010-0034 

EASA Form 110 Page 2/3 

 

D23581100-7 B398

D23581100-7 B400

D23581100-7 B403

Reason: During the overhaul of two different Nose Landing Gears (NLG), cracks were 

found on the main fitting of one and the sliding tube of the other. Investigations 

concluded that the cracks initiated as a result of residual stress in the parts 

following damage due to impact during towing incidents. 

A subsequent review of the reported incidents has led to conclude that an 

inspection of the main fitting and sliding tube is required on those NLG that 

have sustained impacts as result of towing incidents. 

The failure of the main fitting or sliding tube could lead to NLG collapse. 

To prevent the above unsafe condition, this AD requires a one- time 

inspection followed by repetitive inspections of the main fitting and sliding 

tube of the NLG serial numbers listed in the Applicability section of this 

AD: 

- One time Magnetic Particle Inspection (MPI) of the affected areas to 

detect any crack, 

- Repetitive Detailed Visual Inspections (DVI) of the affected areas to 

detect any damage of the surface protections or corrosion. 

This AD also requires the accomplishment of the associated corrective 

actions, as necessary. 

This correction is issued to add NLG serial number B403 in the 

Applicability section of this AD.

Effective Date: 19 March 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated: 

(1) In accordance with instructions defined in Airbus Service Bulletin (SB) 

A330-32-3233 or SB A340-32-4275, as applicable, unless already 

accomplished, within 900 Flight Hours (FH) after the effective date of 

this AD, and depending on impacted areas: 

(1.1) perform a detailed visual inspection of the main fitting and/or 

sliding tube of the NLG, and 

(1.2) perform MPI inspection of the main fitting and/or sliding tube of 

the NLG. 

(2) If any crack is detected during the MPI inspection defined in 

paragraph (1.2) of this AD, before next flight, replace the damaged 

part in accordance with the instructions defined in SB A330-32-3233 

or SB A340-32-4275, as applicable. 

(3) If NO crack is detected during the MPI inspection defined in paragraph 

(1.2) of this AD : 

(3.1) do flap peening to introduce compressive residual stress and 

corrosion protection, in accordance with the instructions of SB 

A330-32-3233 or SB A340-32-4275, as applicable, and 

(3.2) repeat the inspection defined in paragraph (1.1) of this AD at 

intervals not exceeding 900 FH from the last inspection and 

apply the associated corrective actions. 
EASA AD No : 2010-0034 

EASA Form 110 Page 3/3 

 

Ref. Publications: Airbus Service Bulletin A330-32-3233 at original issue; 

Airbus Service Bulletin A340-32-4275 at original issue. 

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 17 December 2009 as PAD 09-142 for 

consultation until 14 January 2010. The Comment Response 

Document 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 SAS – Airworthiness Office – EAL. 

Fax: + 33 5 61 93 45 80 or + 33 5 61 93 44 51. 

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