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

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B08467 In force Legislative Instrument

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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.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.