EASA AD No.: 2014-0074

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0074

Date: 21 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:

ATR-GIE AVIONS de TRANSPORT 

RÉGIONAL

Type/Model designation(s):

ATR 72 and ATR 42 aeroplanes

TCDS Number: EASA A.084 

Foreign AD: Not applicable 

Supersedure: None 

ATA 32 Landing Gear – Main Landing Gear Hinge Pin – Inspection / 

Replacement 

Manufacturer(s): ATR-GIE Avions de Transport Régional (formerly Aerospatiale – Aeritalia, 

Aerospatiale – Alenia, Aerospatiale ATR – ALENIA, EADS ATR – Alenia) 

Applicability: ATR 42 and ATR 72 aeroplanes, all certified models, all manufacturer serial 

numbers. 

Reason: Prompted by cases of rupture of Main Landing Gear (MLG) rear hinge pin part 

number (P/N) D61000 encountered in service in 1994 and 1996, DGAC France 

issued AD 96-131-064 (B) for ATR 42 aeroplanes and AD 96-096-029 (B) for 

ATR 72 aeroplanes to require inspection and, depending on findings, corrective 

action. 

Since those ADs were issued, new occurrences of cracked rear hinge pin P/N 

D61000 were reported on ATR72 MLG. 

The result of subsequent investigation revealed that the affected pins were 

subjected to a non-detected thermal abuse done in production during grinding 

process. Analysis also showed that other MLG pin P/N’s could be affected by 

the same nonconformity. 

This condition, if not detected and corrected, could lead to MLG structural 

failure, possibly resulting in collapse of the MLG and consequently injury to the 

occupants of the aeroplane. 

For the reasons described above, this AD requires inspection and, depending 

on findings, replacement of affected pins. 
EASA AD No.: 2014-0074

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Effective Date: 04 April 2014 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

For ATR 72 aeroplanes: 

(1) Within 12 months after the effective date of this AD, identify the serial 

number (S/N) of the left hand (LH) and right hand (RH) MLG rear hinge pin 

P/N D61000. 

(2) If, during the identification as required by paragraph (1) of this AD, a MLG 

rear hinge pin P/N D61000 having a S/N listed in Messier Bugatti Dowty 

Service Bulletin (SB) 631-32-213 or SB 631-32-216 Revision 1, as 

applicable, is found to be installed, within 12 months after the effective date 

of this AD, replace the MLG rear hinge pin P/N D61000 with a serviceable 

part in accordance with of Messier Bugatti Dowty SB 631-32-213 or SB 

631-32-216, as applicable. 

Note 1: For the purpose of paragraph (2) of this AD, a serviceable MLG rear 

hinge pin is a part that: 

- is outside of the identified batch as listed in Messier Bugatti Dowty SB 

631-32-213 or SB 631-32-216 Revision 1, as applicable, or 

- has been inspected and reconditioned in accordance with the 

instructions of Messier Bugatti Dowty SB 631-32-213 or 

SB 631-32-216, as applicable. 

(3) Within the compliance time, as defined in Table 1 of this AD, identify all LH 

and RH MLG pins having a P/N and S/N listed in Messier Bugatti Dowty 

SB 631-32-214 or SB 631-32-219, as applicable. 

(4) If, during the identification as required by paragraph (3) of this AD, a MLG 

pin having a P/N and S/N listed in Messier Bugatti Dowty SB 631-32-214 

or SB 631-32-219, as applicable, is found to be installed, within the 

compliance time defined in Table 1 of this AD, replace the affected MLG 

with a serviceable MLG, in accordance with ATR approved maintenance 

instructions. 

Note 2: For the purpose of paragraph (4) of this AD, a serviceable MLG is a 

part incorporating pins that are: 

- outside of the identified batch as listed in Messier Bugatti Dowty SB 

631-32-214 or SB 631-32-219, as applicable, or 

- inspected and reconditioned in accordance with the instructions of 

Messier Bugatti Dowty SB 631-32-214 or SB 631-32-219, as 

applicable. 

Table 1 Compliance time 

A or B, whichever occurs first

A Not later than the next MLG overhaul scheduled after the 

effective date of this AD 

B 

Within 20 000 flight cycles or 9 years, whichever occurs first, 

accumulated since installation of MLG on an aeroplane since 

new or since last overhaul, as applicable 

For ATR 42 aeroplanes 

(5) Within the compliance time, as defined in Table 1 of this AD, identify all LH 

and RH MLG pins having a P/N and S/N listed in Messier Bugatti Dowty 

SB 631-32-215 or SB 631-32-220, as applicable. 

(6) If, during the identification as required by paragraph (5) of this AD, a MLG 

pin having a P/N and S/N listed in Messier Bugatti Dowty SB 631-32-215 

or SB 631-32-220, as applicable, is found to be installed, within the 
EASA AD No.: 2014-0074

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compliance time defined in Table 1 of this AD, replace the affected MLG, 

with a serviceable MLG in accordance with ATR approved maintenance 

instructions. 

Note 3: For the purpose of paragraph (6) of this AD, a serviceable MLG is a 

part incorporating pins that are: 

- outside of the identified batch as listed in Messier Bugatti Dowty SB 

631-32-215 or SB 631-32-220, as applicable, or 

- inspected and reconditioned in accordance with the instructions of 

Messier Bugatti Dowty SB 631-32-215 or SB 631-32-220, as 

applicable. 

(7) A review of MLG maintenance records is acceptable to make the 

identification as required by paragraphs (1), (3) and (5) of this AD, 

provided those records can be relied upon for that purpose, and the P/N 

and S/N of LH and RH MLG pins can be conclusively identified from that 

review. 

Ref. Publications: Messier Bugatti Dowty SB 631-32-213, dated 16 December 2013, 

Messier Bugatti Dowty SB 631-32-214, dated 13 January 2014, 

Messier Bugatti Dowty SB 631-32-215, dated 13 January 2014, 

Messier Bugatti Dowty SB 631-32-216 original issue dated 30 October 2013 

and Revision 1, dated 17 December 2013,

Messier Bugatti Dowty SB 631-32-219, dated 03 March 2014, 

Messier Bugatti Dowty SB 631-32-220, dated 03 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 06 February 2014 as PAD 14-034 for consultation 

until 06 March 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: 

ATR - GIE Avions de Transport Régional, 

Continued Airworthiness Service, 

Tel.: +33 (0)5 62 21 62 21 - Fax: +33 (0) 5 62 21 67 18; 

E-mail: continued.airworthiness@atr.fr.