Commonwealth legislation

AD/ARRIEL/16 - Gas Generator 2nd Stage Turbine Blades

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

Requires operators of single-engine rotorcraft fitted with Turbomeca Arriel 1B, 1D or 1D1 engines that incorporate modification TU 204 to replace the modified gas-generator 2nd-stage turbine blades by 31 March 2003, following Turbomeca service bulletins. Issued by CASA under CAR 1998 to address increased blade-root stress after TU 204 and reported in-flight shutdowns.

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Current sections

Direct links to the current provisions in AD/ARRIEL/16 - Gas Generator 2nd Stage Turbine Blades.

AIRWORTHINESS DIRECTIVE

View image in the official source

View image in the official source
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 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/16 Gas Generator 2 nd Stage Tu

AD/ARRIEL/16 Gas Generator 2 nd Stage Turbine Blades 8/2002

Applicability: All Arriel 1B, 1D, 1D1 turboshaft engines installed in rotorcraft in single engine configuration, and incorporating modification TU 204.

Requirement: Replace gas generator 2nd stage TU 204 modified blades as per: Turbomeca SB 292 72 0258 update 1 for Arriel 1B engines; or

Turbomeca SB 292 72 0265 update 1 for Arriel 1D, and 1D1 engines.

Note: DGAC 2002-258(A) refers.

Compliance: Unless previously accomplished, prior to March 31 2003.

This Airworthiness Directive becomes effective on 8 August 2002.

Background: Incorporation of Mod TU 204 increased the blade mass and subsequently the stress on the blade root. Failure of the 2nd stage turbine blade has resulted in uncommanded in flight shutdowns.

View image in the official source

Eugene Paul Holzapfel

Delegate of the Civil Aviation Safety Authority 28 June 2002

View image in the official source

Source text

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

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 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/16 Gas Generator 2 nd Stage Tu AD/ARRIEL/16 Gas Generator 2 nd Stage Turbine Blades 8/2002

AD/ARRIEL/16 Gas Generator 2 nd Stage Turbine Blades 8/2002

Applicability: All Arriel 1B, 1D, 1D1 turboshaft engines installed in rotorcraft in single engine configuration, and incorporating modification TU 204.

Requirement: Replace gas generator 2nd stage TU 204 modified blades as per: Turbomeca SB 292 72 0258 update 1 for Arriel 1B engines; or

Turbomeca SB 292 72 0265 update 1 for Arriel 1D, and 1D1 engines.

Note: DGAC 2002-258(A) refers.

Compliance: Unless previously accomplished, prior to March 31 2003.

This Airworthiness Directive becomes effective on 8 August 2002.

Background: Incorporation of Mod TU 204 increased the blade mass and subsequently the stress on the blade root. Failure of the 2nd stage turbine blade has resulted in uncommanded in flight shutdowns.

Eugene Paul Holzapfel

Delegate of the Civil Aviation Safety Authority 28 June 2002