EASA AD No.: 2010-0028 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0028 

Date: 23 February 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 Airworthiness Directive applies, except in accordance with the requirements of that 

Airworthiness Directive 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) : 

A340-500/-600 aeroplanes 

TCDS Number : EASA.A.015

Foreign AD : Not applicable 

Supersedure : None 

ATA 52 Doors – Nose Landing Gear (NLG) Aft Doors – Aft Hinge 

Forward (FWD) Attachment Fittings – Inspection/Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A340 model -541, -542, -642 and -643 aeroplanes, all 

manufacturer serial numbers. 

Reason: An operator has reported cracks on the aft hinge FWD fittings of the NLG 

aft doors (Right Hand (RH) side or Left Hand (LH) side). The cracks 

extended by approximately 15 millimetres from the upper hole to the edge 

of the fittings. 

Investigation has revealed that these cracks have initiated due to fatigue 

loads and propagated under bending load. 

Cracks on the NLG aft door fittings, if not corrected, could lead to the loss 

in flight of the door, possibly resulting in injury to persons on the ground or 

aeroplane damages. 

Consequently, in order to maintain the structural integrity of the NLG aft 

door aft hinge attachment fittings, this AD requires repetitive inspections of 

the area and fittings replacement in case of finding. 

Effective Date: 09 March 2010 
EASA AD No.: 2010-0028 

EASA Form 110 Page 2/3 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, 

(1) Unless accomplished previously, 

Before the accumulation of 1 000 Total Flight Cycles (FC) after the 

aeroplane first flight, or 

within 100 FC after the effective date of this AD for aeroplanes having 

accumulated between 1 000 total FC and 2 500 total FC after the 

aeroplane first flight, or 

within 50 FC after the effective date of this AD for aeroplanes having 

exceeded 2 500 total FC after the aeroplane first flight, 

perform a detailed visual inspection of the FWD attachment fittings of 

the NLG Aft door aft hinge, LH and RH side doors, in accordance with 

the instructions defined in Airbus Service Bulletin (SB) A340-52-5016. 

(2) In case of no crack finding, repeat the inspection required in 

paragraph (1) of this AD at intervals not to exceed 500 FC from the 

last inspection. 

(3) In case of crack finding during the initial or repetitive inspection, 

before further flight, perform High Frequency Eddy Current (HFEC) 

inspection of FWD and AFT attachment fittings of the aft hinge on the 

affected NLG aft door, in accordance with the instructions defined in 

Airbus SB A340-52-5016. 

(3.1) In case of additional crack finding, before further flight, replace 

both fittings FWD and AFT by new ones on the aft hinge of the 

affected NLG aft door. 

(3.2) In case of no additional crack finding, and in accordance with the 

instructions defined in Airbus SB A340-52-5016: 

- repeat the HFEC inspection required by paragraph (3) of this 

AD at intervals not to exceed 10 FC from the last inspection, or 

- perform a Fluorescent Penetrant Inspection at intervals not to 

exceed 3 FC from the last inspection, 

up to the limit of 20 FC after the crack identification, when the 

FWD and AFT fittings replacement is required on the aft hinge of 

the affected NLG aft door. 

(4) At each replacement of the FWD fitting of the NLG aft door aft hinge 

as required by paragraphs (3.1) and (3.2) of this AD: 

Before the accumulation of 1 000 FC by the FWD fitting on an 

aeroplane, perform the initial inspection defined in paragraph (1) and 

thereafter the repetitive inspections defined in paragraph (2) of this 

AD, and apply the associated corrective actions defined in paragraph 

(3) of this AD. 

Ref. Publications: Airbus Service Bulletin (SB) A340-52-5016 at original issue. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 
EASA AD No.: 2010-0028 

EASA Form 110 Page 3/3 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

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 – Airworthiness Office – EAL; 

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