Document ID: chunk:federal_register_of_legislation:F2006B08676:body:0:p1
Version: federal_register_of_legislation:F2006B08676
Segment Type: other
Provision Reference: 
Character Range: 20–3042

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 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.

 General Electric Turbine Engines - CT58 Series

AD/CT58/18 Fuel Flow Divider Assemblies 7/2004

 Applicability: General Electric Company (GE) CT58-100-2, CT58-140-1, -140-2, and T58-GE-1,
            -3, -5, -8E, -8F, -10, -100, and -402 turboshaft engines, with fuel flow divider assemblies part number (P/N) 4050T82G02 or 4067T04G02, having temperature control assemblies, P/N 5040T77G02 or 5040T87G02, with serial numbers (SNs) listed in 1.A.(3) of GE Alert Service Bulletin (ASB) No. CT58 S/B 73-A0081, Revision 2, dated August 7, 2003, installed.

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

                  1. Read the SN of the temperature control assembly. The SN is located on the end cap of the temperature control assembly. The end cap has a one-inch hex flange and is threaded into the fuel flow divider body.

b.         If the SN is listed in 1.A.(3) of GE ASB No. CT58 S/B 73- A0081, or if the SN cannot be determined, remove the fuel flow divider assembly from service.

              2. Do not install any fuel flow divider assembly P/N 4050T82G02 or 4067T04G02, that has a temperature control assembly with a SN listed in 1.A.(3) of GE ASB No. CT58 S/B 73-A0081.

            Note: FAA AD 2004-04-06 Amdt 39-13487 refers.

 Compliance: For Requirement 1: Within 120 flight hours after the effective date of this Directive.

            For Requirement 2: From the effective date of this Directive. This Airworthiness Directive becomes effective on 8 July 2004.

 General Electric Turbine Engines - CT58 Series

 AD/CT58/18 (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.

 James Coyne
 Delegate of the Civil Aviation Safety Authority 28 May