AD/CF6/11 - High Pressure Turbine Rotor - Stage 2 Disc Forward Embossment Inner Diameter Fillet Radius
1AD/CF6/11 - High Pressure Turbine Rotor - Stage 2 Disc Forward Embossment Inner Diameter Fillet Radius
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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/CF6/11 High Pressure Turbine Rotor - Stage 2 Disc Forward Embossment Inner Diameter Fillet Radius
Applicability: CF6-50/-45 series engines.
3/89
TX
Requirement: Rework or inspect and rework stage 2 high pressure turbine rotor discs specified by FAA AD 89-01-02 Amendment 39-6082 in accordance with the requirements of paras (a) or (b), (c) and (d) of the AD.
Compliance: Forthwith. The cycle count is to commence on the effective date specified in the AD.
Background: The FAA AD incorporates a manufacturer’s Service Bulletin which states that cracks have been found in a forward embossment inner diameter fillet and these could adversely affect engine durability. The probable cause is an undersized fillet radius which is increased by the rework specified in the AD.