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AD/ARRIEL/17 Amdt 2 Airworthiness Directives/Pt 106 — Engines as made
Engine - Gas Generator Second Stage Turbine
Administered by: DOTARS
Exempt from sunsetting by the Legislative Instruments Act 2003 s 54(2) item 9
Registered 16 May 2007
Tabling HistoryDate
Tabled HR21-May-2007
Tabled Senate12-Jun-2007
Date of repeal 03 Sep 2007
Repealed by AD/ARRIEL/17 Amdt 3 - Engine - Gas Generator Second Stage Turbine

 

AIRWORTHINESS DIRECTIVE

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/ARRIEL/17 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 - Arriel Series

AD/ARRIEL/17 Amdt 2

Engine - Gas Generator
Second Stage Turbine

6/2007

 

Applicability:

ARRIEL 1B engines modified per TU 148 and ARRIEL 1D, 1D1 and 1S1 engines.

Requirement:

1.    Axial Displacement Check.

Carry out a check of the axial displacement of the 2nd stage turbine blades and perform any subsequent rectification following the check in accordance with:

Turbomeca Service Bulletin (SB) A292 72 0807 update 1 or later NAA approved revision for ARRIEL 1B engines,

SB A292 72 0809 update 1 or later NAA approved revisions for ARRIEL 1D and 1D1 engines,

SB A292 72 0810 or later NAA approved revisions for ARRIEL 1S1 engines.

2.    2nd Stage Turbine and/or 2nd Stage Turbine Blade Replacement.

For ARRIEL 1B engines, which have been modified per TU 148, and ARRIEL 1D and 1D1 engines  replace the 2nd stage turbine and/or 2nd stage turbine blades in accordance with SB A292 72 0807 or SB A292 72 0809 as is applicable.

Note:  EASA AD 2007-0018 dated 15 January 2007 refers.  This AD supersedes DGAC AD F-2004-047R1.

Compliance:

1.    Axial Displacement Check.

For ARRIEL 1B engines that have been modified per TU 148, once the 2nd stage turbine has accumulated 1,200 flight hours or 3,500 cycles since new or inspection in accordance with the requirement document:

For 2nd stage turbines that have not been checked or with more than 150 flight hours since the last check was performed in accordance with SB A292 72 0263, check within 50 flight hours.  Thereafter carry out a check at intervals not to exceed 200 flight hours until fitment of a replacement turbine from Turbomeca.

 

 

For 2nd stage turbines that have less than 150 flight hours since a check performed in accordance with SB A292 72 0263, check within 200 flight hours from the last check, thereafter carry out a check at intervals not to exceed 200 flight hours until fitment of a replacement turbine with new blades from Turbomeca.

For ARRIEL 1D and 1D1 engines once the 2nd stage turbine has accumulated 1,200 flight hours or 3,500 cycles since new or inspection in accordance with the requirement document:

For 2nd stage turbines that have not been checked or with more than 100 flight hours since the previous check was performed in accordance with SB A292 72 0263, check within 50 flight hours.  Thereafter carry out a check at intervals not to exceed 150 flight hours until fitment of a replacement turbine from Turbomeca.

For 2nd stage turbines that have less than 100 flight hours since a check performed in accordance with SB A292 72 0263, check within 150 flight hours from the previous check, thereafter carry out a check at intervals not to exceed 150 flight hours until fitment of a replacement turbine with new blades from Turbomeca.

For ARRIEL 1D and 1D1 engines:

At intervals not to exceed 1,500 flight hours following replacement of the turbine from Turbomeca as detailed in Requirement 2 of this AD.

For ARRIEL 1S1 engines:

For 2nd stage turbines that have not been checked or with more than 100 flight hours since the previous check was performed in accordance with SB A292 72 0263, check within 50 flight hours.  Thereafter carry out a check at intervals not to exceed 150 flight hours until fitment of a replacement turbine from Turbomeca.

For 2nd stage turbines that have less than 100 flight hours since a check performed in accordance with SB A292 72 0263, check within 150 flight hours from the previous check, thereafter carry out a check at intervals not to exceed 150 flight hours until fitment of a replacement turbine from Turbomeca.

2.    2nd Stage Turbine and/or 2nd Stage Turbine Blade Replacement.

For ARRIEL 1B engines which have been modified per TU 148:

 

 

 

Remains unchanged as detailed in Amendment 1 of this AD as:  If the 2nd stage turbine blades have accumulated more than 2,200 flight hours since new or since last inspection in accordance with the requirement document, by 31 August 2006.

For 2nd stage turbines fitted with blades having accumulated more than 3,000 flight hours since new, immediately upon receipt of an inspected turbine fitted with blades that have accumulated less than 3,000 flight hours since new or by 30 July 2007, whichever occurs first.

The life limit for 2nd stage turbine blades is to be 3,000 flight hours.

For ARRIEL 1D and 1D1 engines:

Remains unchanged as detailed in Amendment 1 of this AD as: If the 2nd stage turbine blades have accumulated more than 1,500 flight hours since new or since last inspection in accordance with the requirement document, by 31 August 2006.

Thereafter at intervals not to exceed 1,500 flight hours.

The life limit for 2nd stage turbine blades is to be 1,500 flight hours.

 

This Amendment becomes effective on 7 June 2007.

Background:

Several cases of 2nd stage turbine blade release have occurred in service that has resulted in uncommanded in-flight shut down.  This Directive requires inspection of the 2nd stage turbine blades for axial displacement and the replacement of turbine where the displacement exceeds the allowable published limit.

Amendment 1 clarified the engine listed in the applicability section.  It also revised the requirements for 1D and 1D1 engines.  These engines are now grouped together and may require additional work to be carried out.

Amendment 2 introduces a reduction to the life limit of ARRIEL 1B engines 2nd stage turbine blades form 6,000 to 3,000 hours with no change to other requirements.

The original issue of this Airworthiness Directive became effective 8 July 2004.

Amendment 1 of this AD became effective on 16 March 2006.


David Punshon
Delegate of the Civil Aviation Safety Authority

24 April 2007