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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0166

Date: 16 July 2014

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):

A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD F-2003-434 dated 10 December 2003 (EASA 

approval 2003-1436).

ATA 52 Doors – Main Landing Gear Door Actuator Fittings – Inspection / 

Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319-111, A319-112, A319-113, A319-114, A319-115, A319-131,

A319-132, A319-133, A320-211, A320-212, A320-214, A320-215, A320-216, 

A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, 

A321-212, A321-213, A321-231 and A321-232 aeroplanes, all manufacturer 

serial numbers.

Reason: On one A320 aeroplane, it was reported that one of the main landing gear (MLG)

doors could not be closed. Investigations revealed the rupture of the actuator 

fitting at the actuator attachment area on the door side. The MLG door is attached

to the aeroplane by 2 hinge fittings.

This condition, if not corrected, could, under certain circumstances, lead to 

detachment of a MLG door from the aeroplane, possibly resulting in damage to 

the aeroplane, and/or injury to persons on the ground.

Prompted by these findings, DGAC France issued AD 1999-243-133 (later revised 

to R1), to require a MLG door actuator fitting inspection for cracks and to check 

the grain direction on a batch of aeroplanes.

Subsequently, DGAC France issued AD 2000-257-149, retaining the requirement 

of DGAC France AD 1999-243-133R1, which was superseded, to require an 

inspection of the lower part of the MLG door actuator fitting.

After that AD was issued, additional investigations revealed that damage could 

also appear on the nerve area, in the upper part of the MLG door actuator fitting in 
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the area of the hinge.

Consequently, DGAC France issued AD F-2003-434 (EASA approval 2003-1436),

retaining the requirements of DGAC France AD 2000-257-149, which was 

superseded, to require additional repetitive inspections. That AD also included an 

optional terminating action, by replacing the MLG door actuator fittings in 

accordance with the instructions of Airbus Service Bulletin (SB) A320-52-1073.

Since that AD was issued, in the framework of the extended service goal 

campaign, it has been decided to make replacement of the MLG door actuator 

fittings a required modification.

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

France AD F-2003-434, which is superseded, and requires replacement of the 

MLG door actuator fittings with new monoblock fittings, which constitutes 

terminating action for the repetitive inspections.

Effective Date: 30 July 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Restatement of the requirements of DGAC France AD F-2003-434:

(1) For aeroplanes equipped with MLG door fittings Part Number (P/N)

D52880224 000/001 that were installed at the time of aeroplane first 

delivery on MLG doors with serial numbers (S/N) as specified in Table 1 of 

this AD, within 500 flight hours (FH) from the last inspection in accordance 

with the instructions of Airbus SB A320-52A1086 Revision 01, and,

thereafter, at intervals not exceeding 500 FH, accomplish a high frequency 

eddy current (HFEC) inspection in accordance with the instructions of 

Airbus SB A320-52A1086 Revision 01.

Table 1 – MLG Doors

Location S/N

LH

1206 to 1237 inclusive, 1239 to 1247 inclusive, and 

1249 to 1251 inclusive

RH

1208 to 1239 inclusive, 1241 to 1249 inclusive, and 

1251

(2) If, during any HFEC inspection as required by paragraph (1) of this AD, any

crack is found, within the compliance time (threshold) specified in Airbus SB 

A320-52A1086 Revision 01, replace the MLG door actuator fittings in 

accordance with the instructions of Airbus SB A320-52-1073 Revision 05.

(3) If, during any HFEC inspection as required by paragraph (1) of this AD, no

crack is detected, accomplish a low frequency eddy current (LFEC) 

inspection to determine the grain direction of the raw material of each

actuator fitting in accordance with the instructions of Airbus SB

A320-52A1086 Revision 01.

(3.1) If, during the LFEC inspection as required by paragraph (3) of this 

AD, the grain direction of the raw material of the fitting is found to be 

correct, the repetitive inspections of paragraph (1) of this AD can be 

terminated.

(3.2) If, during the LFEC inspection as required by paragraph (3) of this 

AD, the grain direction of the raw material of the fitting is found to be 

incorrect, continue the HFEC inspections as required by paragraph 

(1) of this AD or, before next flight, replace the MLG door actuator 

fittings in accordance with the instructions of Airbus SB

A320-52-1073 Revision 05.
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(4) For aeroplanes equipped with MLG door fittings P/N D52880224 000/001 or 

P/N D52880235 000/001, within 400 flight cycles (FC) after 20 December 

2003 [the effective date of DGAC France AD F-2003-434], or before

exceeding 9 000 FC since aeroplane first flight, whichever occurs later, and,

thereafter, at intervals not exceeding 800 FC, accomplish a HFEC 

inspection in both hinge and nerve areas in accordance with the instructions 

of Airbus SB A320-52-1096 Revision 02.

(5) If, during any HFEC inspection as required by paragraph (4) of this AD, any 

crack is found on the hinge area, or on the nerve area, within the 

compliance time (threshold) specified in Airbus SB A320-52-1096 Revision 

02, replace the MLG door actuator fittings in accordance with the 

instructions of Airbus SB A320-52-1073 Revision 05.

(6) If, during any HFEC inspection as required by paragraph (4) of this AD,

any crack is found on both hinge and nerve areas, before next flight, 

replace the affected fitting(s) in accordance with the instructions of Airbus

SB A320-52-1096 Revision 02 or, within the compliance time (threshold) 

specified in Airbus SB A320-52-1096 Revision 02, replace the MLG door 

actuator fittings in accordance with the instructions of Airbus SB

A320-52-1073 Revision 05.

(7) Inspections and corrective actions, accomplished before the effective date 

of this AD in accordance with the instructions of Airbus SB A320-52-1096 

Revision 01 are acceptable to comply with the initial requirements of 

paragraphs (4) and (6) of this AD.

New requirements of this AD:

(8) For all aeroplanes equipped with MLG door fittings with a P/N as listed in 

Table 2 of this AD, before exceeding 48 000 FC or 96 000 FH, whichever 

occurs later since aeroplane first flight, replace the MLG door actuator 

fittings in accordance with the instructions of Airbus SB A320-52-1073 

Revision 05.

Table 2 – MLG Door Actuator Fittings P/N

D52880102000

D52880102001

D52880220000

D52880220001

D52880224000

D52880224001

D52880235000

D52880235001

(9) Modification of an aeroplane, prior to the effective date of this AD in 

accordance with the instructions of Airbus SB A320-52-1073 (at any 

revision) is acceptable to comply with the requirements of paragraph (8) of 

this AD for that aeroplane.

(10) An aeroplane on which Airbus modification (mod) 24903, or mod 25372, or 

mod 36979 has been embodied in production is not affected by the 

requirements of this AD, except as specified below, provided that no MLG 

door actuator fitting with a P/N as listed in Table 2 of this AD has been 

reinstalled on that aeroplane since first flight.

Paragraph (13.1) of this AD remains applicable to post-mod 24903, postmod 25372 and post-mod 36979 aeroplanes.

(11) Modification of an aeroplane in accordance with the instructions of Airbus 

SB A320-52-1073 (at any revision) to install fittings with P/N D52880246002
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and P/N D52880246003 is acceptable to comply with the requirements of 

paragraph (8) of this AD for that aeroplane.

(12) Modification of an aeroplane as required by paragraph (2) or (5) or (8) of 

this AD, as applicable, or as specified in paragraph (3.2) or (6) of this AD, 

as applicable, constitutes terminating action for the repetitive inspections

required by this AD for that aeroplane.

(13) Do not install on any aeroplane a MLG door actuator fitting with a P/N as 

listed in Table 2 of this AD, as required by paragraph (13.1) or (13.2) of this 

AD, as applicable.

(13.1) For an aeroplane that, on the effective date of this AD, has fittings

installed with a P/N not listed in Table 2 of this AD: From the 

effective date of this AD.

(13.2) For an aeroplane that, on the effective date of this AD, has fittings 

installed with a P/N as listed in Table 2 of this AD: After modification 

of the aeroplane as required by paragraph (2) or (5) or (8) of this 

AD, or as specified in paragraph (3.2) or (6) of this AD.

(14) Modification of an aeroplane by installing a version (P/N) of the MLG door 

actuator fitting approved after the effective date of this AD is equal to 

compliance with the requirements of paragraph (8) of this AD for that 

aeroplane, provided the conditions, as specified in paragraphs (14.1) and 

(14.2) of this AD, are met.

(14.1) The MLG door actuator fitting (P/N) must be approved by EASA, or 

approved under Airbus DOA; and

(14.2) The modification must be accomplished in accordance with 

instructions approved by EASA, or approved under Airbus DOA.

Ref. Publications: Airbus SB A320-52-1073 original issue dated 02 February 1996, or Revision 01 

dated 26 April 1996, or Revision 02 dated 07 April 1997, or Revision 03 dated

01 October 1998, or Revision 04 dated 10 August 1999, or Revision 05 dated

28 September 2006.

Airbus SB A320-52A1086 Revision 01 dated 10 September 1999.

Airbus SB A320-52-1096 Revision 01 dated 23 October 2003, or Revision 02 

dated 12 July 2006.

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 04 June 2014 as PAD 14-093 for consultation until

02 July 2014. The Comment Response Document can be found at 

http://ad.easa.europa.eu/.

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 – Airworthiness Office – EIAS;

Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com.