Commonwealth legislation

AD/CF6/17 - Stage 1 Fan Rotor Disc

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This AD requires operators and maintenance organisations of GE CF6-6, -45, -50 and -80A engines to inspect the stage‑1 fan‑disc dovetail post for cracks, following the inspection procedures referenced in FAA AD 91‑01‑04 and GE service bulletins. It responds to discovered dovetail cracks that could cause blade release and uncontained engine failure. Compliance imposes inspection, downtime and repair costs and depends on correctly following the FAA/GE technical instructions.

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AD/CF6/17 - Stage 1 Fan Rotor Disc

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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/CF6/17 Stage 1 Fan Rotor Disc 3/91

Applicability: CF6 - 6, -45, -50, -80A.

Requirement: Inspect the stage 1 fan disc dovetail post for cracks in accordance with the technical requirements of the FAA AD 91-01-04 Amdt 39-6847.

Note: The GE SB 72-999, 965 and 575 covering the -50/-45, -6 and -80A series respectively refer.

Compliance: As specified in the Requirement Document.

Background: Five stage 1 fan discs have been discovered with cracks in the dovetail post area. The defect has the potential for multiple blade release, engine power loss and uncontained engine failure.

Source text

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