Commonwealth legislation

AD/CF6/11 - High Pressure Turbine Rotor - Stage 2 Disc Forward Embossment Inner Diameter Fillet Radius

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

Requires immediate rework or inspection-and-rework of the stage‑2 high‑pressure turbine rotor discs on General Electric CF6‑50/‑45 engines to address an undersized forward embossment inner‑diameter fillet radius. The FAA and manufacturer report cracks in that fillet which could reduce engine durability. Operators must follow the FAA AD’s specified procedures; compliance begins on the AD’s effective date and will impose inspection/repair costs and maintenance downtime for affected engines.

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AD/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

View image in the official source 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

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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.