EASA AD No.: 2014-0040-E

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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 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:

AGUSTAWESTLAND S.p.A.

Type/Model designation(s):

AB 412 and AB 412 EP helicopters

TCDS Number: ENAC Italy A 157

Foreign AD: Not applicable

Supersedure: None

ATA 65 Tail Rotor Drive – Flanged Adapter – 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 subsequent.

Reason: A crack has been found during a scheduled inspection of a flanged adapter,

Part Number (P/N) 412-040-622-101, installed on the tail rotor drive shaft P/N

412-040-621-107 of an AB412EP helicopter.

This condition, if not detected and corrected, could lead to tail rotor drive shaft 

failure, possibly resulting in reduced control of the helicopter.

To address this 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 flanged 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 adapters, P/N 412-040-622-101 and P/N 412-040-623-101, installed on 

the tail rotor drive shaft and, in case cracks are found, replacement of the

cracked part with a serviceable one.

Effective Date: 21 February 2014
EASA AD No.: 2014-0040-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/2

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 5 flight hours (FH) after the effective date of this AD, and, thereafter, 

at intervals not to exceed 100 FH, inspect the flanged adapter P/N 412-

040-622-101 and P/N 412-040-623-101, 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 cracked, before next flight, replace the flanged adapter 

with a serviceable part in accordance with the instructions of 

AgustaWestland BT 412-139.

(3) Within 10 days after removing a cracked flanged adapter from a helicopter, 

as required by paragraph (2) of this AD, report the findings and send the 

cracked part to AugustaWestland for investigation.

(4) From the effective date of this AD, installation of a flanged adapter P/N 

412-040-622-101 or P/N 412-040-623-101 is allowed, provided the part 

has passed an inspection in accordance with the instructions of the BT 

412-139 and, following installation, is inspected as required by paragraph 

(1) of this AD.

Ref. Publications: AgustaWestland BT 412-139 original issue, dated 19 February 2014.

The use of later approved revisions of this 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 have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

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:

AgustaWestland S.p.A, Customer Support & Services – Italy,

Product Support Engineering Dpt., Via del Gregge, 100,

21015 Lonate Pozzolo (VA) – ITALY

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

E-mail: absereng@agustawestland.com.