Document ID: chunk:federal_register_of_legislation:F2006B08455:body:0
Version: federal_register_of_legislation:F2006B08455
Segment Type: other
Provision Reference: 
Character Range: 0–1017

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/CF6/11  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.