Patent ID: 8886438

Claim:
A method of controlling a fuel flow rate for an aircraft-mounted turbine engine, the method comprising: a) supplying fuel at a flow rate corresponding to a commanded engine output power; b) monitoring engine power output by monitoring a differential oil pressure of the engine representing a main output torque of the engine; c) monitoring at least a second engine parameter to determine whether a change in differential engine oil pressure likely corresponds to a decrease in engine power output; and d) upon determining that a decrease in the monitored differential oil pressure has occurred and that the second parameter indicates the change in differential oil pressure does not likely correspond to an actual decrease in engine power output, one of: e) determining a substitute fuel flow rate for the engine and providing a corresponding command signal to an engine fuel flow rate controller for a selected time interval; f) holding a current fuel flow rate constant for a selected time interval, and g) switching to a third engine parameter for determining a desired fuel flow rate to the engine and providing a corresponding command signal to an engine fuel flow rate controller for a selected time interval.