Commonwealth legislation

AD/CF6/15 Amdt 2 - High Pressure Compressor Rear Shaft Bolt Hole

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Commonwealth

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legislative instrument

Plain English Summary

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This instrument requires operators and maintainers of General Electric CF6‑45 and CF6‑50 engines to comply with FAA AD 91‑10‑03 R1 — inspecting the HPC rear shaft and changing its bolt configuration — by 20 July 1995 (unless already done). It affects aircraft operators, maintenance organisations and parts suppliers (including Valley‑Todeco PMA bolts). The goal is to reduce HPC rear‑shaft fractures and uncontained failures; compliance costs (inspections, parts, downtime) fall to operators and maintainers.

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Direct links to the current provisions in AD/CF6/15 Amdt 2 - High Pressure Compressor Rear Shaft Bolt Hole.

AD/CF6/15 Amdt 2 - High Pressure Compressor Rear Shaft Bolt Hole

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.

Source text

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

1 AD/CF6/15 Amdt 2 - High Pressure Compressor Rear Shaft Bolt Hole