EASA AD No.: 2014-0058

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0058

Date: 11 March 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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not Applicable

Supersedure: None

ATA 32 Landing Gear – Main Landing Gear Sliding Tube Axles – 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 (MSN).

Reason: A main landing gear (MLG) sliding tube axle rupture occurred in service. 

Investigation of the affected part showed that this failure was due to an 

abnormal grinding operation during overhaul by a certain maintenance and 

repair organisation located in Singapore. A population of MLG sliding tubes was 

subsequently identified whose axles may have been subject to this grinding 

operation, which may have resulted in areas of residual stress on the axles on 

the MLG sliding tubes. In addition, the MSN of the aeroplanes which are known 

to have had the affected parts installed have been identified.

This condition, if not detected and corrected, could lead to cracks in the axle 

and (partial) detachment of axle and wheel from the sliding tube, possibly 

resulting in failure of a MLG with consequent damage to the aeroplane and 

injury to occupants. 

To address this potential unsafe condition, Messier-Bugatti-Dowty, the MLG 

gear manufacturer, issued Service Bulletin (SB) 200-32-313 and SB 201-32-62, 

providing inspection instructions and criteria for removal from service of the 

affected MLG sliding tubes.

For the reasons described above, this AD requires a one-time Special Detailed

Inspection (SDI) of the axle on the affected MLG sliding tubes and, depending 

on findings, replacement of the MLG sliding tube.
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Effective Date: 25 March 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 3 months after the effective date of this AD, accomplish the 

following actions:

(1.1) Identify the Part Number (P/N) and Serial Number (S/N) of the MLG 

sliding tubes installed on each aeroplane. A review of aeroplane 

maintenance records is acceptable to accomplish the identification 

as required by this paragraph, provided those records can be relied 

upon for that purpose.

An aeroplane with an MSN not listed in Table 1 of this AD is not 

affected by the requirements of paragraphs (1.2) and (2) of this AD,

provided it can be determined that no MLG sliding tube having a P/N 

and S/N as listed in Appendix 1 of this AD has been installed on that 

aeroplane since first entry into service.

(1.2) For each MLG sliding tube, identified as required by paragraph (1.1) 

of this AD, having a P/N and S/N as listed in Appendix 1 of this AD, 

accomplish a SDI of the affected MLG axle and brake flange in 

accordance with the instructions of Messier-Dowty SB 200-32-313 

(A318, A319 and A320) or SB 201-32-62 (A321), as applicable, or in 

accordance with the instructions of Airbus SB A320-32-1416.

(2) If, during the SDI as required by paragraph (1.2) of this AD, any damage is 

detected, before next flight, replace the MLG sliding tube with a 

serviceable one in accordance with the instructions of Messier-Dowty

SB 200-32-313 (A318, A319 and A320) or SB 201-32-62 (A321), as 

applicable, or in accordance with the instructions of Airbus SB

A320-32-1416.

Note: For the purpose of this AD, a serviceable sliding tube is a sliding tube 

having a P/N and S/N not listed in Appendix 1 of this AD, or a sliding tube 

having a P/N and S/N listed in Appendix 1 of this AD which has passed the SDI 

as required by paragraph (1.2) of this AD.

Table 1 – Affected Aeroplanes listed by MSN

0179 0214 0296 0412 0558 0604

0607 0668 0704 0720 0726 0731

0754 0771 0799 0828 0841 0855

0909 0914 0925 0939 0986 1028

1030 1041 1070 1083 1093 1098

1108 1148 1294 1356 2713 2831

(3) Do not install on any aeroplane a MLG sliding tube, having a P/N and S/N 

as listed in Appendix 1 of this AD, as required by paragraph (3.1) or (3.2) 

of this AD, as applicable, unless that sliding tube has passed the SDI as 

required by paragraph (1.2) of this AD.

(3.1) For aeroplanes that have a MLG sliding tube installed, having a P/N 

and S/N as listed in Appendix 1 of this AD: After release to service of 

the aeroplane following the SDI as required by paragraph (1.2) of 

this AD.

(3.2) For aeroplanes that, on the effective date of this AD, do not have a 

MLG sliding tube installed having a P/N and S/N as listed in 

Appendix 1 of this AD: From the effective date of this AD. 
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Ref. Publications: Messier-Dowty SB 200-32-313 dated 25 February 2013.

Messier-Dowty SB 201-32-62 dated 25 February 2013.

Airbus SB A320-32-1416 dated 10 March 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. This AD was posted on 17 January 2014 as PAD 14-012 for consultation 

until 14 February 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.
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Appendix 1 – Affected MLG Sliding Tubes
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Appendix 1 – Affected MLG Sliding Tubes (continued)