Commonwealth legislation

AD/CF6/20 - High Pressure Compressor Rotor Stages 11 to 14 Vane to Spool Rubs

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

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This Airworthiness Directive requires operators of certain GE CF6-80A and CF6-80C2 engines to carry out the inspections, repairs or modifications specified in FAA AD 91‑15‑25 (and related GE service bulletins) after reports of high‑pressure compressor spool vane-to-spool rubs. It matters because the condition can lead to uncontained engine failure; compliance therefore falls to engine owners and their maintenance providers and entails locating and implementing the external technical procedures.

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AD/CF6/20 - High Pressure Compressor Rotor Stages 11 to 14 Vane to Spool Rubs

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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/CF6/20 High Pressure Compressor Rotor Stages

11 to 14 Vane to Spool Rubs

Applicability: CF6-80A and CF6-80C2.

Requirement: Action in accordance with the Technical Requirements of FAA AD 91-15-25 Amendment 39-7090.

Note: GE Service Bulletins 72-459 Revision 2 and 72-130 Revision 2 refer.

11/91

Compliance: As specified in the Requirement Document with an effective date of 28 November 1991.

Background: The FAA AD is prompted by reports of HPCR stages 11-14 spool-shafts found in service with spool rub. This condition, if not corrected could result in uncontained engine failure.

Source text

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