Federal Register of Legislation - Australian Government

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AD/ARRIUS/13 Amdt 2 Airworthiness Directives/Pt 106 — Engines as made
Gas Generator Front Bearing
Administered by: Infrastructure, Regional Development and Cities
Exempt from sunsetting by the Legislation (Exemptions and Other Matters) Regulation 2015 s12 item 15
Registered 01 Jun 2007
Tabling HistoryDate
Tabled HR12-Jun-2007
Tabled Senate12-Jun-2007
Date of repeal 06 Apr 2018
Repealed by CASA ADCX 008/18 - Repeal of Airworthiness Directive AD/ARRIUS/13 Amdt 2



On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/ARRIUS/13 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Turbomeca Turbine Engines - Arrius Series

AD/ARRIUS/13 Amdt 2

Gas Generator Front Bearing

8/2007 DM



ARRIUS 2F Turboshaft engines.

Note 1:  These engines are installed on but not limited to Eurocopter EC 120B helicopters.


Incorporate Turbomeca Modification Tf12 in accordance with paragraph 2 of Turbomeca Mandatory Service Bulletin No. 319 72 4012 update No.1 or later approved revision.

Note 2:  EASA AD 2007-0057 dated 1 March 2007 refers.


Before 30 April 2008, unless previously accomplished.


This Amendment becomes effective on 7 June 2007.


This AD is in response to an uncommanded in-flight shut down which occurred following the seizing of the gas generator.  The seizing of the gas generator was caused by the fracture of the separator cage of the gas generator bearing, due to high-cycle fatigue cracks initiated in the lubrication slots of the separator cage.

Amendment 1 corrects an error in the Service Bulletin number published in the original issue of this AD.

Amendment 2 changes the compliance statement to reflect that detailed in the EASA AD.

Charles Lenarcic
Delegate of the Civil Aviation Safety Authority

29 May 2007