Commonwealth legislation

AD/ARRIEL/18 Amdt 1 - 2nd Stage Nozzle Guide Vanes

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

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Requires operators of Turbomeca Arriel 1B, 1D and 1D1 engines (with MOD TU 202) to follow paragraph 2.B of Turbomeca Service Bulletin 292 72 0231 Revision 5—unless the engine already has the specified 2nd‑stage nozzle guide vanes. Compliance is at the next deep maintenance, the next occasion the engine goes to a repair centre, or by 31 December 2006. The AD aims to detect/prevent perforation of 2nd‑stage nozzle guide vanes that could cause an aerodynamic wake, turbine blade rupture and an uncommanded engine shutdown; the amendment limits application to engines on single‑engine helicopters.

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Current sections

Direct links to the current provisions in AD/ARRIEL/18 Amdt 1 - 2nd Stage Nozzle Guide Vanes.

AD/ARRIEL/18 Amdt 1 - 2nd Stage Nozzle Guide Vanes

COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source

AIRWORTHINESS DIRECTIVE

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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/18 and issues the following AD under subregulation 39.1 (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/18

Amdt 1

2nd Stage Nozzle Guide Vanes 11/2004 DM

Applicability: TURBOMECA ARRIEL 1B, 1D and 1D1 model engines incorporating MOD TU 202, except those engines having 2nd stage nozzle guide vanes which are detailed in TURBOMECA Service Bulletin (SB) No. 292 72 0231 Revision 5.

Requirement: Action in accordance with paragraph 2.B, operating instructions, of TURBOMECA SB No. 292 72 0231 Revision 5, dated 22 July 2004.

Note: DGAC AD F-2004-088R1 (EASA reference No 2004-8068) refers.

Compliance: Unless previously accomplished in accordance with earlier revisions of TURBOMECA SB 292 72 0231, during the next deep maintenance, or at the next occasion the engine is sent to a repair centre or at the latest before 31 December 2006, whichever occurs first.

This Amendment becomes effective on 30 September 2004.

Background: This Directive is issued to detect and prevent a possible perforation of the 2nd stage nozzle guide vanes (NGV) and the formation of an aerodynamic wake upstream of the 2nd stage NGV. Such a wake may lead to the rupture of a 2nd stage turbine blade followed by an uncommanded engine shutdown.

This amendment clarifies the applicability of the engines affected. The requirements detailed now only apply to those engines fitted to single engine helicopters.

The original issue of this Directive becomes effective on 30 September 2004.

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James Coyne

Delegate of the Civil Aviation Safety Authority 14 September 2004

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The above AD is notified in the Commonwealth of Australia Gazette on 22 September 2004.

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Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/ARRIEL/18 Amdt 1 - 2nd Stage Nozzle Guide Vanes

COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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/18 and issues the following AD under subregulation 39.1 (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/18

Amdt 1

2nd Stage Nozzle Guide Vanes 11/2004 DM

Requirement: Action in accordance with paragraph 2.B, operating instructions, of TURBOMECA SB No. 292 72 0231 Revision 5, dated 22 July 2004.

Note: DGAC AD F-2004-088R1 (EASA reference No 2004-8068) refers.

This Amendment becomes effective on 30 September 2004.

This amendment clarifies the applicability of the engines affected. The requirements detailed now only apply to those engines fitted to single engine helicopters.

The original issue of this Directive becomes effective on 30 September 2004.

James Coyne