EASA AD CF-2019-30R1
Compressor Turbine Blade Fracture due to Non-conforming CT Vane Installation
Summary
The Canadian Airworthiness Directive CF-2019-30R1 addresses compressor turbine blade fractures caused by non-conforming compressor turbine (CT) vane installations on Pratt & Whitney Canada PT6A-34, -34B, -34AG, -114, and -114A engines. This directive updates previous information and clarifies affected CT blade part numbers, focusing on engines with CT vanes repaired under Southwest Turbine Inc. repair specification STI 72-50-254. The directive aims to prevent power loss and in-flight shutdowns resulting from CT blade failures.
What Changed
Airworthiness Directive CF-2019-30R1 revises the original AD CF-2019-30 by updating background information and clarifying the specific CT blade part numbers affected. It reinforces the prohibition of installing CT vanes repaired under STI 72-50-254 and specifies replacement requirements for CMSX-6 CT blades operated with such vanes. The revision ensures clearer compliance guidance for affected engine models.
Why It Matters
This directive is critical for aviation professionals because CT blade fractures can lead to power loss or in-flight shutdowns, particularly hazardous for single-engine aircraft. Operators and maintenance organizations must ensure compliance to prevent potential accidents and fatalities. Understanding the specific repair specifications and part numbers involved helps maintain engine reliability and safety.
What To Do
Operators must, within 9 months or 250 hours air time from 2 September 2019, inspect affected engines for CT vanes repaired under STI 72-50-254 and replace them with serviceable non-STI repaired vanes. Additionally, CMSX-6 CT blades used with these vanes must be replaced and discarded within the same timeframe. Installation of CT vanes repaired under STI 72-50-254 on affected engines is prohibited from 2 September 2019 onward.
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