Document ID: chunk:federal_register_of_legislation:F2006B08459:body:0
Version: federal_register_of_legislation:F2006B08459
Segment Type: other
Provision Reference: 
Character Range: 0–1051

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/CF6/15
 Amdt 2

 High Pressure Compressor Rear Shaft Bolt Hole 8/95

 Applicability: All General Electric CF6-45 and CF6-50 series engines.

            Requirement: Action in accordance with the technical requirements of FAA AD 91-10-03 R1 (Amdt. 39-9186).

            Note: GE CF6 Service Bulletin 72-958 Rev. 1 also refers.

            Compliance: Unless previously accomplished, as specified in the Requirement Document with an effective date of 20 July 1995.

            Background:  This Directive currently requires an inspection of the HPC Rear Shaft and a revised bolt configuration to reduce the potential for HPC Shaft fractures. HPC Shaft fractures can result in uncontained engine failures.

            This amendment reflects the requirements of FAA AD 91-10-03 R1 which adds reference to PMA bolts manufactured by Valley-Todeco.