Abstract: A system and method are provided for inspecting cooling holes of a completed, lasered, and deburred turbine airfoil. The cooling holes are covered with a very porous tape before placing the turbine airfoil into an air fixture that has a metered amount of fluorescent liquid dripped into the airline. The atomized fluorescent liquid flows through the turbine airfoil internal cavities, exiting through the open cooling holes, where it is absorbed by the porous tape. A pattern will appear on the tape surface, in the area of the open holes, indicative of the presence of not-through or plugged cooling holes.

Abstract: A system and method are provided for allowing simplified access to the raw vibration data. The signal conditioner, even if mounted on the engine or the engine pylon, digitizes the input signals and can analyze and store a finite amount of raw data. The raw signals are digitized at a high rate of speed, and the digitized values are stored. The stored values can be retrieved after flight. This aircraft vibration processor and recording system allows easy access to the raw vibration waveform, even in configurations where the processor is located on the engine or the engine pylon.