Document ID: chunk:federal_register_of_legislation:F2006B08467:body:0
Version: federal_register_of_legislation:F2006B08467
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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 - CF6 Series

 AD/CF6/23 High Pressure Turbine Rotor Stage 1 Disc/Shaft
                  Inspection and Removal From Service

 Applicability: CF6-80A Series.

 Requirement: Action in accordance with the technical requirements of FAA AD 92-04-08.

            Note: GE Service Bulletin 72-605 refers.

10/92

            Compliance: As specified in the Requirement Document with an effective date of 17 September 1992.

            Background: The FAA AD was prompted by a report of an uncontained separation of a CF6-80A high pressure turbine rotor stage 1 disk/shaft. It requires removal from service of certain disk/shafts that may have surface damage in the bore area and a one time eddy current and fluorescent penetration of other discs/shafts.