Document ID: chunk:federal_register_of_legislation:F2006B08689:body:0
Version: federal_register_of_legislation:F2006B08689
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 General Electric Turbine Engines - CT7 Series

 AD/CT7/5  Rotor Parts 5/94 Applicability:              CT7-5A2,-7A and -9C turboprop engines; and CT7-2A and -6 turboshaft engines. Requirement:               Action in accordance with GE Service bulletins:
            For CT7-5A2, -7A and -9C: SB A72-252 of 31 Aug 1990. For CT7-2A: SB A72-18 of 10 Sep1990.
            For CT7-6: SB A72-17 of 10 Sep 1990.

            Note: FAA AD 93-25-17 refers.

            Compliance: Before exceeding the `Max total allowable cycles' specified in the relevant Service Bulletins.

            Background:  This AD requires the removal from service of certain gas generator rotor assembly parts that were plasma sprayed during manufacture . The requirement arises from results obtained during material testing which indicated that the plasma-spray process reduces the low cycle fatigue capability of the material.