EASA AD No.: 2014

- 0040

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TE. CAP.0011 1

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No

. : 2014 - 0040 - E

Date: 19 February 2014

Note: This Emergency 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 E U 748/2012 , Part 2 1

. 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 ope rate an aircraft to which an AD applies, except in accordance wi th 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: AGUSTAWESTLAND S.p.A. Type/Model designation(s): AB 412 and AB 412 EP helicopters

TCDS Number: ENAC Italy A 157

F oreign AD: Not applicable Supersedure: None



### ATA 65 Tail Rotor Drive
– Flange d Adapt e r – Inspection / Replacement

Manufacturer(s): AgustaWestland S.p.A. (formerly Agusta S.p.A)

Applicability: AB 412 helicopters S/N 25801 through 25900 and AB 412 EP helicopters S/N 25901 and subs equent

. Reason: A crack has been found d uring a scheduled inspection of a flanged adapter , Part Number ( P/N ) 412

- 040

- 622

- 101 , installed on the tail rotor drive shaft P / N 412

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- 621

- 107 of an AB412EP helicopter

. This condition, if not detected and corrected, could lead to t ail rotor drive shaft failure , possibly resulting in reduced control of the helicopter. To address th i s potential unsafe condition, AgustaWestland issued the Bollettino Tecnico (BT) 412

- 139 , providing instructions to inspect the affected parts

. However , the investigation to determine the root cause of the crack on the flange d adapter is in progress and the instructions of BT 412

- 139 will be updated according to the investigations results. For the reasons described above, this AD requires repetitive inspections of the flanged adapter s, P/N 412

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- 622

- 101 and P/N 412

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- 623

- 101 , installed on the tail rotor drive shaft and , in case cracks are found , replacement of the cracke d part with a serviceable one

. Effective Date: 21 February 2014EASA AD No.: 2014

- 0040

- E

TE. CAP.0011 1

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 5 f light h ours (FH) after the effective date of this AD , and , thereafter, at intervals not to exceed 100 FH, inspect the flanged adapter P/N 412

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- 622

- 101 and P/N 412

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- 623

- 101 , as applicable , depending on helicopter model and S/N, in accordance with the instructions of AgustaWestland BT 412

- 139. (2) If, during any inspection as required by paragraph (1) of this AD, a flanged adapter is found crack ed, before next flight, replace the flanged adapter with a serviceable part in accordance with the instructions of AgustaWestland BT 412

- 13 9

. (3) Within 10 days after removing a cracked flanged adapter from a helicopter, as required by paragraph (2 ) of this AD , r eport the findings and send the cracked part to AugustaWestland for investigation. (4 ) From the effective date of this AD, install ation of a flanged adapter P/N 412

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- 622

- 101 or P/N 412

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- 623

- 101 is allowed , provided the part has passed an inspect ion in accordance with the instructions of the BT 412

- 139 and, following installation, is inspected as required by paragraph (1) of this AD

. Ref. Public ations: AgustaWestland BT 412

- 139 original issue, dated 19 February 2014. The use of later approved revisions of th i s document 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 results of the safety assessment ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 3. Enquiries regarding this A D 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: AgustaWestland S.p.A, Custo mer Support & Services

– Italy, Product Support Enginee ring Dpt., Via del Gregge, 100, 21 015 Lonate Pozzolo (VA)

– ITALY Tel.: +39 0331 664905, Fax: +39 0331 664684

. E

- mail: absereng@agustawestland.com

.