Commonwealth legislation

AD/CT58/16 - Fuel Flow Divider Assemblies - Replacement

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Commonwealth

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legislative instrument

Plain English Summary

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This Airworthiness Directive requires operators of listed GE CT58/T58 turboshaft engines to check the temperature control assembly serial number on two specific fuel flow divider part numbers and to replace the entire fuel flow divider if the serial number begins with 95–99 or cannot be read. It also prohibits installing those part numbers when the temperature control assembly has a serial number starting 95–99. Aircraft owners/operators pay for inspection and replacement; CASA enforces the rule and it takes effect immediately, changing maintenance and parts‑sourcing behaviour.

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AIRWORTHINESS DIRECTIVE

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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.

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General Electric Turbine Engines - CT58 Series

AD/CT58/16 Fuel Flow Divider Assemblies

AD/CT58/16 Fuel Flow Divider Assemblies - Replacement 5/2002

Applicability: Models CT58-140-1, -140-2, and former military T58-GE-5, -8F, -10, -100, and -402 turboshaft engines, with fuel flow divider assemblies Part Numbers (P/N) 4050T82G02, or 5040T77G02.

Requirement: 1. Locate the temperature control assembly, which is mounted on the fuel flow divider assembly and carry out the following:

(a) Read the temperature control assembly Serial Number(S/N), located on the temperature control assembly end cap. The end cap can be identified by a one- inch hex flange and by being threaded into the fuel flow divider body.

(b) If the first two digits of the S/N are 95, 96, 97, 98, or 99, or if the S/N cannot be determined, replace the entire fuel flow divider assembly.

2. Do not install any fuel flow divider assembly with P/N 4050T82G02 or 5040T77G02, that have the first two digits of the temperature control assembly S/N of 95, 96, 97, 98, or 99.

Note: Further information regarding S/N location on the temperature control assembly may be found in GE Alert Service Bulletin CT58 73-A0080, dated 13 February, 2001.

Note: FAA AD 2001-12-07 refers.

Compliance: For Requirements 1 and 2: As from the effective date of this Airworthiness Directive.

This Airworthiness Directive becomes effective on 16 May 2002.

Source text

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

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

General Electric Turbine Engines - CT58 Series

AD/CT58/16 Fuel Flow Divider Assemblies AD/CT58/16 Fuel Flow Divider Assemblies - Replacement 5/2002

AD/CT58/16 Fuel Flow Divider Assemblies - Replacement 5/2002

Applicability: Models CT58-140-1, -140-2, and former military T58-GE-5, -8F, -10, -100, and -402 turboshaft engines, with fuel flow divider assemblies Part Numbers (P/N) 4050T82G02, or 5040T77G02.

Requirement: 1. Locate the temperature control assembly, which is mounted on the fuel flow divider assembly and carry out the following:

(a) Read the temperature control assembly Serial Number(S/N), located on the temperature control assembly end cap. The end cap can be identified by a one- inch hex flange and by being threaded into the fuel flow divider body.

(b) If the first two digits of the S/N are 95, 96, 97, 98, or 99, or if the S/N cannot be determined, replace the entire fuel flow divider assembly.

2. Do not install any fuel flow divider assembly with P/N 4050T82G02 or 5040T77G02, that have the first two digits of the temperature control assembly S/N of 95, 96, 97, 98, or 99.

Note: Further information regarding S/N location on the temperature control assembly may be found in GE Alert Service Bulletin CT58 73-A0080, dated 13 February, 2001.

Note: FAA AD 2001-12-07 refers.

Compliance: For Requirements 1 and 2: As from the effective date of this Airworthiness Directive.

This Airworthiness Directive becomes effective on 16 May 2002.