AD/CF6/23 - High Pressure Turbine Rotor Stage 1 Disc/Shaft Inspection and Removal From Service
1AD/CF6/23 - High Pressure Turbine Rotor Stage 1 Disc/Shaft Inspection and Removal From Service
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text 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.