EASA AD No.: 2014-0074

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0074

Date: 21 March 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 – Inspec tion / Replacement

Manufacturer(s): ATR-GIE Avions de Transport Région al (formerly Aerospatiale – Aeritalia, Aerospatiale – Alenia, Aerospatiale ATR – ALENIA, E ADS ATR – Alenia)

Applicability: ATR 42 and ATR 72 aeroplanes, all ce rtified models, all manufacturer serial numbers.
Reason: Prompted by cases of rupture of Main Landin g 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, depend ing on findings, corrective action. Since those ADs were issued, new occurrences of cra cked rear hinge pin P/N D61000 were reported on ATR72 MLG. The result of subsequent investigation revealed tha t 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, coul d 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 i nspection and, depending on findings, replacement of affected pins.EASA AD No.: 2014-0074

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 04 April 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: For ATR 72 aeroplanes: (1) Within 12 months after the effective date of th is 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 pa ragraph (1) of this AD, a MLG rear hinge pin P/N D61000 having a S/N listed in Me ssier Bugatti Dowty Service Bulletin (SB) 631-32-213 or SB 631-32-216 R evision 1, as applicable, is found to be installed, within 12 mon ths after the effective date of this AD, replace the MLG rear hinge pin P/N D610 00 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 M essier Bugatti Dowty SB 631-32-213 or SB 631-32-216 Revision 1, as applicab le, or - has been inspected and reconditioned in accordanc e 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 Mess ier Bugatti Dowty SB 631-32-214 or SB 631-32-219, as applicable. (4) If, during the identification as required by pa ragraph (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 ins talled, within the compliance time defined in Table 1 of this AD, repl ace the affected MLG with a serviceable MLG, in accordance with ATR appr oved 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 Mess ier Bugatti Dowty SB 631-32-214 or SB 631-32-219, as applicable, or - inspected and reconditioned in accordance with th e instructions of Messier Bugatti Dowty SB 631-32-214 or SB 631-32-21 9, as applicable. Table 1 Compliance time

A or B
, whichever occurs first

A Not later than the next MLG overhaul scheduled afte r the effective date of this AD

B Within 20 000 flight cycles or 9 years, whichever o ccurs first, accumulated since installation of MLG on an aeropla ne 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 Mess ier Bugatti Dowty SB 631-32-215 or SB 631-32-220, as applicable. (6) If, during the identification as required by pa ragraph (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 ins talled, within theEASA AD No.: 2014-0074

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. compliance time defined in Table 1 of this AD, repl ace the affected MLG, with a serviceable MLG in accordance with ATR appro ved 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 Mess ier Bugatti Dowty SB 631-32-215 or SB 631-32-220, as applicable, or - inspected and reconditioned in accordance with th e instructions of Messier Bugatti Dowty SB 631-32-215 or SB 631-32-22 0, as applicable. (7) A review of MLG maintenance records is acceptab le to make the identification as required by paragraphs (1), (3) a nd (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 i dentified 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 Janua ry 2014, Messier Bugatti Dowty SB 631-32-215, dated 13 Janua ry 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 docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA 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 t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t 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 6 7 18; E-mail: continued.airworthiness@atr.fr

.