Commonwealth legislation

AD/CF6/29 Amdt 1 - High Pressure Turbine - Stage 1 Disc Rim Bolt Holes and Stage 2 Disc Rim and Inner Bolt Holes

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This instrument directs operators and maintenance organisations of aircraft with General Electric CF6‑45/50/‑6 engines to carry out the inspection, repair and replacement actions set out in the corrected September 1994 FAA Airworthiness Directive (AD 94‑09‑18), with reference to GE service bulletins and a compliance date of 8 December 1994.

It aims to prevent uncontained high‑pressure turbine disc failures; CASA enforces compliance by incorporating the FAA AD, leaving operators to shoulder inspection, maintenance and downtime costs.

JSON API

Deep dive

Want the full deep dive?

Zoe can write the in-depth analysis on top of the summary above: how it works, who it affects and what each part actually does.

Current sections

Direct links to the current provisions in AD/CF6/29 Amdt 1 - High Pressure Turbine - Stage 1 Disc Rim Bolt Holes and Stage 2 Disc Rim and Inner Bolt Holes.

AD/CF6/29 Amdt 1 - High Pressure Turbine - Stage 1 Disc Rim Bolt Holes and Stage 2 Disc Rim and Inner Bolt Holes

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/CF6/29

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.

Source text

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

1 AD/CF6/29 Amdt 1 - High Pressure Turbine - Stage 1 Disc Rim Bolt Holes and Stage 2 Disc Rim and Inner Bolt Holes