EASA AD No.: 2015-0001R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/5

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

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0001R1

Date: 15 January 2015

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 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 

[EU 1321/2014 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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2015-0001 dated 05 January 2015, which superseded

EASA AD 2014-0096 dated 23 April 2014.

ATA 52 Doors – Main Landing Gear Fixed Fairing Assembly – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, 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: Several occurrences of in-flight loss of main landing gear (MLG) fixed and 

hinged fairings were reported. The majority of reported events occurred 

following scheduled maintenance activities. One result of the investigation 

was that a discrepancy between the drawing and the maintenance manuals 

was discovered. The maintenance documents were corrected to prevent misrigging of the MLG fixed and hinged fairings, which could induce fatigue 

cracking.

Airbus issued Service Bulletin (SB) A320-52-1083, providing instructions for a 

one-time inspection of the MLG fixed fairing composite insert and the 

surrounding area, replacement of the adjustment studs at the lower forward 

position and adjustment to the new clearance tolerances. That SB was 

replaced by Airbus SB A320-52-1100 (mod 27716) introducing a re-designed 

location stud, rod end and location plate at the forward upper and lower leg 

fixed-fairing positions. Subsequently, reports were received of post-mod 

27716 / post-SB A320-52-1100 MLG fixed fairing assemblies with corrosion, 

which could also induce cracking.

This condition, if not detected and corrected, could lead to further cases of inflight detachment of a MLG fixed fairing, possibly resulting in injury to persons 
EASA AD No.: 2015-0001R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/5

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

on the ground and/or damage to the aeroplane.

To address this potential unsafe condition, EASA issued AD 2014-0096 to

require repetitive detailed inspections (DET) of the MLG fixed fairings, and, 

depending on findings, accomplishment of applicable corrective actions. That 

AD also prohibited installation of certain MLG fixed fairing rod end assemblies

and studs as replacement parts on aeroplanes incorporating Airbus mod 

27716 in production, or modified in accordance with Airbus SB A320-52-1100 

(any revision) in service.

Since EASA AD 2014-0096 was issued, Airbus developed an alternative 

inspection programme to meet the AD requirements. In addition, a terminating 

action (mod 155648) was developed, which is to be made available for in 

service aeroplanes through Airbus SB A320-52-1165.

Prompted by these developments, EASA issued AD 2015-0001, retaining the 

requirements of EASA AD 2014-0096, which was superseded, and adding an 

optional terminating action for the repetitive inspections. For post-mod 

aeroplanes, i.e. incorporating Airbus mod 155648 in production, or modified 

by Airbus SB A320-52-1165 in service, the only remaining requirement is to 

ensure that pre-mod components are no longer installed.

Since that AD was issued, it was discovered that a certain plate support, Part 

Number (P/N) D5285600620000 as listed in Table 3 of the AD, remains part 

of the post SB A320-52-1165 configuration and is therefore not affected by 

any prohibition of installation – paragraph (11) of the AD. In addition, an error 

was detected in Table 1 of the AD (missing P/N plate support) and paragraph 

(9) was found to be incorrectly worded.

For the reasons described above, this AD is revised to introduce the 

necessary corrections.

Effective Date: Revision 1: 19 January 2015 (same as original issue)

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously: 

(1) For aeroplanes in pre-mod 27716 and pre-SB A320-52-1100 

configuration, having components installed as identified by P/N in

Table 1 of this AD, within the compliance time as specified in Table 2 of 

this AD, and, thereafter, at intervals not exceeding 6 500 flight cycles 

(FC), replace both right hand (RH) and left hand (LH) MLG fixed fairing 

upper and lower attachment studs in accordance with the instructions of 

Airbus SB A320-52-1163.

Table 1 – Pre-mod 27716 (pre-SB A320-52-1100) Components

Part Name P/N

Plate - Support D5284024820000

D5284024820200

Stud - Adjustment D5284024420000

Rod end assembly (lower) D5284000500000

Rod end assembly (upper) D5284000600000
EASA AD No.: 2015-0001R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/5

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

Table 2 – Initial Inspection for Pre-mod 27716 Aeroplanes

Compliance time (whichever occurs later, A, B, C or D)

A Before exceeding 6 500 FC since aeroplane first flight

B

Within 6 500 FC since last installation of the pre-mod 27716 

stud on an aeroplane

C

Within 1 500 FC after 07 May 2014 [the effective date of EASA

AD 2014-0096]

D

Within 8 months after 07 May 2014 [the effective date of EASA

AD 2014-0096]

(2) For aeroplanes in post-mod 27716 (or post-Airbus SB A320-52-1100) 

configuration, having components installed as identified by P/N in Table 

3 of this AD, within the compliance time as specified in Table 4 of this 

AD, and, thereafter, at intervals not exceeding 12 months (except as 

specified in paragraph (4) of this AD), accomplish a DET of each 

forward stud assembly, both RH and LH MLG, in accordance with the 

instructions of Airbus SB A320-52-1163.

Table 3 – Post-mod 27716 (post-SB A320-52-1100) Components

Part Name P/N

Deleted Deleted

Stud – Adjustment D5285600720000

Rod end assembly (lower) D5285600400000

Rod end assembly (upper) D5285600500000

When, following any DET as required by this paragraph, both RH and 

LH MLG forward stud assemblies on an aeroplane are replaced with

new ones, the next DET for that aeroplane can be deferred up to 72 

months after replacement.

Table 4 – Initial Inspection for Post-mod 27716 Aeroplanes

Compliance time (whichever occurs later, A, B, C or D)

A Before exceeding 72 months since aeroplane first flight

B

Within 72 months since last installation of the stud post-mod 

27716 or since Airbus SB A320-52-1100 accomplishment 

C

Within 1 500 FC after 07 May 2014 [the effective date of 

EASA AD 2014-0096]

D

Within 8 months after 07 May 2014 [the effective date of 

EASA AD 2014-0096]

(3) If, during any DET as required by paragraph (2) of this AD, any crack, 

damage or corrosion (except as specified in paragraph (4) of this AD) is 

found, before next flight, replace the upper and lower RH and LH MLG 

fixed fairing forward attachment assemblies in accordance with the 

instructions of Airbus SB A320-52-1163, or in accordance with the 

instructions of SB A320-52-1165.
EASA AD No.: 2015-0001R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 4/5

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

(4) In case corrosion is found on any MLG fixed fairing forward attachment 

stud assembly (upper, lower, LH or RH), but the corroded stud is not 

loose, accomplish the action(s) as specified in paragraph (4.1) or (4.2) 

of this AD.

(4.1) Before next flight, replace the affected assembly in accordance 

with the instructions of Airbus SB A320-52-1163, or in accordance 

with the instructions of SB A320-52-1165.

(4.2) Within 4 months after finding corrosion and, thereafter, at intervals 

not exceeding 4 months, accomplish a DET (same inspection as 

specified in paragraph (2) of this AD – reduced intervals) of the 

forward stud assembly of the affected (RH or LH) MLG in 

accordance with the instructions of Airbus SB A320-52-1163.

(5) If, during any DET as required by paragraph (4.2) of this AD, any crack

or damage is found, before next flight, replace the affected (RH or LH)

MLG fixed fairing forward attachment assembly in accordance with the 

instructions of Airbus SB A320-52-1163, or in accordance with the 

instructions of SB A320-52-1165.

(6) Replacement of components on an aeroplane with components as listed 

in Table 1 or Table 3 of this AD, as required by paragraph (1), (3), (4.1),

or (5) of this AD, as applicable, does not constitute terminating action for 

the repetitive DET required by this AD for that aeroplane, except as 

specified in paragraph (9) of this AD.

(7) Modification of an aeroplane to post-mod 27716 configuration in 

accordance with the instructions of Airbus SB A320-52-1100 constitutes 

terminating action for the repetitive replacements as required by 

paragraph (1) of this AD for that aeroplane. Refer to paragraph (2) of 

this AD to determine the next due DET after modification and the 

applicable repetitive DET interval.

(8) An aeroplane on which Airbus mod 155648 has been embodied in 

production is not affected by the requirements of paragraphs (1) through

(5) of this AD, provided that no affected component, identified by P/N as 

listed in Table 1 or Table 3 of this AD, has been installed on that 

aeroplane since Airbus date of manufacture.

(9) Modification of an aeroplane in accordance with the instructions of

Airbus SB A320-52-1165 constitutes terminating action for the 

requirements of paragraphs (1) through (5) of this AD for that aeroplane.

(10) Do not install on any aeroplane a component as listed in Table 1 of this 

AD, as required by paragraph (10.1) or (10.2) of this AD, as applicable.

(10.1) For aeroplanes in pre-mod 27716 and pre-SB A320-52-1100 

configuration: After optional modification as specified in 

paragraph (7) of this AD.

(10.2) For aeroplanes in post-mod 27716 or post-SB A320-52-1100 

configuration: From the effective date of this AD.

(11) Do not install on any aeroplane a component as listed in Table 1 or

Table 3 of this AD, as required by paragraph (11.1) or (11.2) of this AD, 

as applicable.

(11.1) For aeroplanes in pre-mod 155648 and pre-SB A320-52-1165

configuration: After optional modification as specified in 

paragraph (9) of this AD.

(11.2) For aeroplanes in post-mod 155648 or post-SB A320-52-1165

configuration: From the effective date of this AD.
EASA AD No.: 2015-0001R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 5/5

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

Ref. Publications: Airbus SB A320-52-1100 original issue dated 07 December 1998, or

Revision 01 dated 12 March 1999.

Airbus SB A320-52-1163 original issue dated 04 February 2014.

Airbus SB A320-52-1165 original issue dated 03 November 2014.

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. The original issue of this AD was posted on 17 December 2014 as PAD 

14-176 for consultation until 01 January 2015. 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, 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 – EIAS,

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