CPC G01M 15/14 (2013.01) [F01D 17/02 (2013.01); F01D 21/003 (2013.01); G06F 16/164 (2019.01)] | 20 Claims |
1. A method for validating component integrity in an engine of an aircraft, comprising:
obtaining, at an engine controller configured for controlling operation of the engine, a measured value indicative of usage experienced by the engine during a period of operation of the engine;
transmitting, from the engine controller to a first presentation device presenting information to an operator of the aircraft, an indication of the measured value;
causing the first presentation device to present to the operator of the aircraft a presented value indicative of the usage experienced by the engine during the period of operation of the engine;
requesting that the operator of the aircraft inputs an operator-input value indicative of the usage experienced by the engine during the period of operation of the engine identical to the presented value via an input device;
receiving, at the engine controller from the operator of the aircraft via the input device, the operator-input value indicative of usage experienced by the engine during the period of operation of the engine;
comparing, at the engine controller, the operator-input value to the measured value; and
based on the comparing, issuing an alert to a second presentation device independent from the first presentation device.
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