AD/CF6/15 Amdt 2 - High Pressure Compressor Rear Shaft Bolt Hole
1AD/CF6/15 Amdt 2 - High Pressure Compressor Rear Shaft Bolt Hole
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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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.