E ASA AD No.: 2013

- 0044

- E

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

. : 2013

- 0044

- E

Date: 2 7 February 2013

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:



### EUROCOPTER Type/Model designation(s):



### AS 350 helicopters

TCDS Number: EASA.R. 008

F oreign AD: Not Applicable

Supersedure: No ne



### ATA 63 Rotor Drive

– Hydraulic Pump

– Inspection / Replacement

Manufacturer(s): Eurocopter (formerly Eurocopter France, Aerospatiale )

Applicability: AS 350 B, AS 350 BA, AS 350 BB, AS 350 B1, AS 350 B2, AS 350 B3 and
AS 350 D helicopters , all serial numbers, if equipped with single hydraulic system (PRE MOD OP3346 or OP3082) and incorporating Eurocopter modification 079566 (new hydraulic pump drive).

Reason: Six events were reported on AS 350 helicopters of hydraulic pump drive belt failure caused by seizure of the hydraulic pump drive pulley bearing.

The preliminary i nvestigation results concluded that the installation of a new hydraulic pump drive (Eurocopter modification 079566) may have cause d
excessive degradation

. For helicopter with a single hydraulic system, t his condition, if not detected and corrected, can lea d to loss of hydraulic servo assistance and increase in pilot work load that requires landing as soon as possible , as specified in the applicable Rotorcraft Flight Manual procedure

. For the reasons described above, this AD requires repetitive inspections and, depending on findings, replacement of the affected hydraulic pump drive assembly

. This AD is considered an interim action and further AD action may follow.

Effective Date: 01 March 2013E ASA AD No.: 2013

- 0044

- 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) Initially, within 165 flight hours ( FH ) since first installation of the h ydraulic

p ump on a helicopter

, or within 10 FH after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 25 FH, inspect the hydraulic pump driv e belt and drive pulley bearing in
accordance with the instructions of S ection 3 of Eurocopter AS350
Eme rgency Alert Service Bulletin ( E ASB) 05.00.72

. (2) If, during any inspection as required by paragrap h (1) of this AD, discrepancies (as defined in AS350 E ASB No. 05.00.72) are found, before next flight, replace th e hydraulic pump drive assembly in accordance with the instructions of Section 3 of Eurocopter AS350 E ASB No. 05.00.72.

(3) After installation of a replacement hydraulic pump drive assembly as required by paragraph (2) of this AD, before exceeding 165 FH since first installation of that hydraulic pump drive assembly on a helicopter, re

- start the initial and repetitive inspectio ns in accordance with the requirements of paragraph (1) of this AD.

Ref. Public ations: Eurocopter AS350 E ASB 05.00.72 dated 2 6 February 201 3

.
The use of la ter 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 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:

EUROCOPTER

- Customer Service Technical Support Department, Aéroport de Marseille, Provence 13725 Marignane Cedex

– France Telephone: + 33 (0)4 42 85 99 51, Fax: + 33 (0)4 42 85 99 66
E

- mail: Directive.technical

- support@eurocopter.com

.