Document ID: chunk:federal_register_of_legislation:F2006B08472:body:0
Version: federal_register_of_legislation:F2006B08472
Segment Type: other
Provision Reference: 
Character Range: 0–979

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/CF6/29
 Amdt 1

 High Pressure Turbine - Stage 1 Disc Rim Bolt Holes and Stage 2 Disc Rim and Inner Bolt Holes

 13/94

 Applicability: General Electric CF6-45/50/-6 series engines.

            Requirement: Action in accordance with the technical requirements of the September 1994 corrected issue of FAA AD 94-09-18.

            Note: General Electric Service Bulletins 72-1002, 1003, 1057 and 1059 refer.

 Compliance: As specified in the FAA AD with a revised effective date of 8 December 1994.

            Background: The requirement arises from an uncontained high pressure turbine disc failure which resulted in an aborted take-off. This amendment incorporates changes to two sections but does not constitute a major change in the thrust of the overall AD document.