EASA AD No : 2011-0088 

EASA Form 110 Page 1/3 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0088 

Date: 13 May 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) : 

A340-500/-600 aeroplanes 

TCDS Number : EASA.A.015 

Foreign AD : Not applicable 

Supersedure : None 

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

Attachment Fittings and Swan Neck – 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 forward (FWD) fittings 

(hinge #5) 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 inflight detachment of the door, possibly resulting in injury to persons on the 

ground or damage to the aeroplane. 

In order to maintain the structural integrity of the NLG aft door aft hinge 

attachment fittings, EASA issued EASA AD 2010-0028, which requires 

repetitive inspections at hinge #5. 

Additional investigations have shown that inspections are also necessary 

for the hinge #4. 

For the reasons described above, this AD requires repetitive inspections of 

the FWD and AFT attachment fittings and of the swan neck at the forward 

hinge #4 and their replacement, as necessary. 
EASA AD No : 2011-0088 

EASA Form 110 Page 2/3 

 

Effective Date: 27 May 2011 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously : 

(1) FWD and AFT attachment fittings of the NLG aft door forward

hinge (#4)

(1.1) Before the accumulation of 4 500 total Flight Cycles (FC) after the 

aeroplane first flight, or within 50 FC after the effective date of this 

AD, whichever occurs later, do a detailed visual inspection of the 

FWD attachment fittings of the NLG aft door forward hinge (#4), 

LH and RH side doors to find any crack, in accordance with the 

instructions of Airbus Service Bulletin (SB) A340-52-5017. 

(1.2) If no crack is found, repeat the inspection required in paragraph 

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

inspection. 

(1.3) If any crack is found during the initial or repetitive inspections 

required by paragraphs (1.1) and (1.2) of this AD, before further 

flight, perform High Frequency Eddy Current (HFEC) inspection of 

FWD and AFT attachment fittings of the forward hinge (#4) on the 

affected NLG aft door, in accordance with the instructions of 

Airbus SB A340-52-5017. 

(1.3.1) If any additional crack is found, before further flight, replace 

both FWD and AFT fittings by serviceable ones on the forward 

hinge (#4) of the affected NLG aft door in accordance with the 

instructions of Airbus Service Bulletin (SB) A340-52-5017. 

(1.3.2) If no additional crack is found: 

- repeat the HFEC inspection required by paragraph (1.3) of 

this AD at intervals not to exceed 10 FC from the last 

inspection, or 

- perform a Penetrant Inspection at intervals not to exceed 3 FC 

from the last inspection, in accordance with the instructions of 

Airbus SB A340-52-5017 

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

where the FWD and AFT fitting replacement is anyhow required 

on the forward hinge (#4) of the affected NLG aft door. 

(1.3.3) If any additional crack is found during any inspection required 

by paragraph (1.3.2) of this AD, before further flight, replace 

both FWD and AFT fittings by serviceable ones on the forward 

hinge (#4) of the affected NLG aft door, in accordance with the 

instructions of Airbus SB A340-52-5017. 

(1.4) After each replacement of the FWD and AFT attachment fittings of 

the NLG aft door forward hinge (#4) as required by paragraphs 

(1.3.1) and (1.3.2) of this AD: 

Before the accumulation of 4 500 FC by the FWD fitting on the 

aeroplane, perform the inspection required by paragraph (1.1) of 

this AD and do the applicable actions required by paragraph (1.2) 

or (1.3) of this AD. 

(2) Swan Neck of the NLG aft door forward hinge (#4)

(2.1) Before the accumulation of 4 500 Total FC after the aeroplane first 

flight, or within 50 FC after the effective date of this AD, whichever 

occurs later, perform HFEC inspection of the swan neck of the 
EASA AD No : 2011-0088 

EASA Form 110 Page 3/3 

 

NLG Aft door forward hinge (#4), LH and RH side doors to find 

any crack, in accordance with the instructions of Airbus SB 

A340-52-5017. 

(2.2) If no crack is found, repeat the inspection required in paragraph 

(2.1) of this AD at intervals not to exceed 500 FC from the last 

inspection. 

(2.3) If any crack is found during the initial or repetitive inspections 

required by paragraphs (2.1) and (2.2) of this AD, before further 

flight, replace the swan neck by a serviceable one on the forward 

hinge (#4) of the affected NLG aft door. 

(2.4) After each replacement of the swan neck of the NLG aft door 

forward hinge (#4) as required by paragraph (2.3) of this AD: 

Before the accumulation of 4 500 FC by the swan neck on an 

aeroplane, perform the inspection required by paragraph (2.1) of 

this AD and do the applicable actions required by paragraph (2.2) 

or (2.3) of this AD. 

Ref. Publications: Airbus Service Bulletin (SB) A340-52-5017 at original issue. 

The use of later approved revisions of this document 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 03 March 2011 as PAD 11-027 for 

consultation until 31 March 2011. No comments were received during 

the consultation period. 

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