EASA AD No.: 2016-0182

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Airworthiness Directive

AD No.: 2016-0182

Issued: 13 September 2016

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) 216/2008 on behalf of the European Union, 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 Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 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 [Regulation (EU) 1321/2014 Annex I,

Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EC) 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A319, A320 and A321 aeroplanes

Effective Date: 27 September 2016

TCDS Number(s): EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2014-0166, dated 16 July 2014.

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, A320-231, 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 (two) 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 
EASA AD No.: 2016-0182

TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

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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 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.

After DGAC France AD F-2003-434 was issued, in the framework of the extended service goal 

campaign, it was decided to make replacement of the MLG door actuator fittings a required 

modification. Consequently, EASA issued AD 2014-0166, retaining the requirements of DGAC France 

AD F-2003-434, which was superseded, and requiring replacement of the MLG door actuator fittings 

with new monoblock fittings, which constitutes terminating action for the repetitive inspections.

After EASA AD 2014-0166 was issued, errors were identified in the compliance time definitions. 

Replacement of the MLG door actuator fittings was required “before exceeding 48 000 flight cycles 

(FC) or 96 000 flight hours (FH), whichever occurs later since aeroplane first flight”, which should 

have been “whichever occurs first”. Furthermore, since the MLG door is an interchangeable part, 

the compliance time must be defined as FC/FH accumulated by the MLG door. Furthermore, it was 

discovered that one of the required inspection is applicable only to a batch of MLG door fittings.

For the reason described above, this AD retains the requirement of EASA AD 2014-0166, which is 

superseded, but requires accomplishment of the terminating action within more stringent 

compliance times, and reduce the applicability of one of the required inspection.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

(1) For aeroplanes equipped with MLG door fittings Part Number (P/N) D52880224000 or 

P/N D52880224001 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 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

Left hand 

(LH)

1206 to 1237 inclusive, 1239 to 1247 inclusive, and 1249 to 1251 inclusive

Right 

hand (RH)

1208 to 1239 inclusive, 1241 to 1249 inclusive, and 1251
EASA AD No.: 2016-0182

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(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, 

before next flight, 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 replace the MLG door actuator fittings in 

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

(4) For aeroplanes equipped with MLG door fittings P/N D52880224000, P/N D52880224001, P/N 

D52880235000 or P/N D52880235001, that were installed at the time of aeroplane first 

delivery on MLG doors with S/N as specified in Table 2 of this AD, within 400 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.

Table 2 – MLG Doors

Location S/N

LH 1206 to 1510 inclusive, 1548, 1564, and 2000 to 2065 inclusive

RH 1208 to 1519 inclusive, 1551, and 2000 to 2065 inclusive

(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 30 July 2014 [the effective date of 

EASA AD 2014-0166] 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.
EASA AD No.: 2016-0182

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(8) For all aeroplanes equipped with a MLG door fitting with a P/N as listed in Table 3 of this AD, 

before that MLG door exceeds 48 000 FC or 96 000 FH, whichever occurs first since first 

installation on an aeroplane (see Note of this AD), replace the MLG door actuator fittings in 

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

Table 3 – MLG Door Actuator Fittings P/N

D52880102000

D52880102001

D52880220000

D52880220001

D52880224000

D52880224001

D52880235000

D52880235001

Note: If no reliable data is available, operators may refer to the guidance specified in ALS Part 1 

Section 1 chapter 5.2 (traceability) to determine the FC and/or the FH accumulated by a MLG door.

(9) Modification of an aeroplane, prior to 30 July 2014 [the effective date of EASA AD 2014-0166]

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 3 of 

this AD has been reinstalled on that aeroplane since first flight.

Paragraph (13.1) of this AD remains applicable to post-mod 24903, post-mod 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 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 3 of 

this AD, as required by paragraph (13.1) or (13.2) of this AD, as applicable.

(13.1) For an aeroplane that, on 30 July 2014 [the effective date of EASA AD 2014-0166], has 

fittings installed with a P/N not listed in Table 3 of this AD: From 30 July 2014.

(13.2) For an aeroplane that, on 30 July 2014 [the effective date of EASA AD 2014-0166], has 

fittings installed with a P/N as listed in Table 3 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 30 July 2014 [the effective date of EASA AD 2014-0166] 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.
EASA AD No.: 2016-0182

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(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 23 June 2016 as PAD 16-093 for consultation until 21 July 2016. The 

Comment Response Document can be found at http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,

Certification Directorate. 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.