EASA AD No.: 2013-0179

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0179

Date: 07 August 2013

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) :

A330 and A340-200/-300 aeroplanes

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

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2010-0034 dated 05 March 2010, including its 

correction dated 08 March 2010.

ATA 32 Landing Gear – Nose Landing Gear Main Fitting and Sliding Tube 

– Inspection

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, A340-313

aeroplanes, all MSN.

Reason: During the overhaul of two different Nose Landing Gear (NLG) units, 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 identified a specific group of

NLG main fittings and sliding tubes that may have sustained impact damage

as a result of towing incidents.

This condition, if not detected and corrected could lead to NLG collapse.

To address this potential unsafe condition, EASA issued AD 2010-0034 to

require accomplishment of a one-time Magnetic Particles Inspection (MPI),

followed by repetitive Detailed Visual Inspections (DVI) of the main fittings and 

sliding tubes of the affected NLG units identified by Part Number (P/N) and 

Serial Number (S/N) in the Applicability section of that AD and, depending on 

findings, accomplishment of applicable corrective actions.

Since that AD was issued, it has been found necessary to address the issue at
EASA AD No.: 2013-0179

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the level of NLG detail parts and no longer at NLG assembly level, as some 

detail parts have been transferred from an aeroplane to another. Airbus 

revised the applicable Service Bulletins (SB), which now list the affected NLG 

main fittings and sliding tubes.

For the reasons described above, this AD retains the requirements of EASA 

AD 2010-0034 which is superseded and requires a one-time MPI, followed by 

repetitive DVI of the affected NLG main fittings and sliding tubes and, 

depending on inspection results, accomplishment of corrective actions. This 

AD also extends the applicability to A330 freighters.

Effective Date: 21 August 2013

Required action(s) 

and Compliance 

Time(s):

Required as indicated, unless already accomplished:

(1) Within 1 000 FH after the effective date of this AD, identify the P/N and 

S/N of the NLG main fitting and NLG sliding tube installed on an 

aeroplane in accordance with the instructions of Airbus SB A330-32-3233 

Revision 01 or SB A340-32-4275 Revision 01, as applicable.

A review of the applicable maintenance records is acceptable to identify 

the NLG main fitting and NLG sliding tube as specified in this paragraph, 

provided those records can be relied upon for that purpose, and the 

affected NLG main fitting and NLG sliding tube can be conclusively 

identified from that review.

(2) If, as a result of identification as required by paragraph (1) of this AD, it is 

determined that P/N and S/N of the NLG main fitting and NLG sliding tube 

as listed in Airbus SB A330-32-3233 Revision 01 or SB A340-32-4275 

Revision 01, as applicable, are installed:

Within 1 000 FH after the effective date of this AD, accomplish a MPI of 

the affected parts in accordance with the instructions of Airbus SB A330-

32-3233 Revision 01 or SB A340-32-4275 Revision 01, as applicable.

(3) If, during the MPI as required by paragraph (2) of this AD, a crack is 

detected, before next flight, replace the cracked part(s) with serviceable 

one(s).

(4) If, during the MPI as required by paragraph (2) of this AD, no crack is 

detected, before next flight after this MPI, accomplish flap peening to 

introduce compressive residual stress and corrosion protection in 

accordance with the instructions of Airbus SB A330-32-3233 Revision 01 

or SB A340-32-4275 Revision 01, as applicable.

(5) Within 900 FH after accomplishment of the actions as required by 

paragraph (4) of this AD and, thereafter, at intervals not to exceed 900 

FH, accomplish a DVI of the affected parts in accordance with the 

instructions of Airbus SB A330-32-3233 Revision 01 or SB A340-32-4275

Revision 01, as applicable.

(6) If, during any DVI as required by paragraph (5) of this AD, damage to 

paint, sealant around the labels, cadmium and/or base metal is detected, 

before next flight, accomplish a MPI of the affected parts in accordance 

with the instructions of Airbus SB A330-32-3233 Revision 01 or SB A340-

32-4275 Revision 01, as applicable.

(7) If, during any DVI or MPI as required respectively by paragraphs (5) and 

(6) of this AD, any crack is detected, before next flight, replace the 

cracked part(s) with serviceable one(s).

(8) Replacement of a part as required by paragraph (3) or (7) of this AD 

constitutes terminating action for the repetitive DVI as required by 

paragraph (5) of this AD for that part, provided the P/N and S/N of the 

replacement part is not listed in Airbus SB A330-32-3233 Revision 01 or 

SB A340-32-4275 Revision 01, as applicable.
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(9) Inspections and flap peening actions of an affected part, accomplished 

before the effective date of this AD, in accordance with the instructions of 

Airbus SB A330-32-3233 original issue or SB A340-32-4275 original 

issue, are acceptable to comply with the requirements of paragraphs (2) 

and (4) of this AD, and to plan the DVI of the affected parts as required by 

paragraph (5) of this AD, as applicable.

(10) From the effective date of this AD, installation on an aeroplane of an 

affected part is allowed, provided this part has not accumulated more 

than 900 FH since the last inspection accomplished in accordance with 

the instructions of Airbus SB A330-32-3233 Revision 01 or SB A340-32-

4275 Revision 01, as applicable.

Ref. Publications: Airbus SB A330-32-3233 at original issue dated 22 October 2009 or Revision 

01 dated 05 July 2013;

Airbus SB A340-32-4275 at original issue dated 22 October 2009 or Revision 

01 dated 05 July 2013.

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

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 – EAL. Fax: 

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

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