Document ID: chunk:federal_register_of_legislation:F2006B08674:body:0
Version: federal_register_of_legislation:F2006B08674
Segment Type: other
Provision Reference: 
Character Range: 0–3047

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.

 General Electric Turbine Engines - CT58 Series

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.

 General Electric Turbine Engines - CT58 Series

 AD/CT58/16 (Continued)

            Background: Reports have been received by the FAA of substantial fuel leakage from the end caps of fuel flow divider assemblies. Investigation by the manufacturer revealed that the manufacturer of the temperature control valve assembly end caps did not accomplish the required manufacturing process steps following heat treatment. This caused the end caps to be susceptible to intergranular corrosion, which can result in cracking.
            This Airworthiness Directive is therefore raised to correct a condition that could cause an engine fire, leading to an in-flight engine shutdown and forced landing.

 Eugene Paul Holzapfel
 Delegate of the Civil Aviation Safety Authority 25 March 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 24 April 2002.