Patent ID: 7262712

Claim:
A helicopter turbine engine over stress warning system comprising: a helicopter; a helicopter turbine engine mounted in said helicopter; a collective and a tactile warning device including a collective shaker operatively connected to said collective; data storage means and means for inputting a safe turbine output temperature profile for startup of the helicopter turbine engine and other safe operating parameters during flight of the helicopter; means for measuring actual turbine output temperature during startup of the turbine engine and for detecting actual turbine output temperatures and other actual parameters during flight of the helicopter; means to activate said tactile warning device when the actual turbine output temperature during startup falls outside of the safe turbine output temperature profile during startup and when the safe turbine output temperature or other safe operating parameters are exceeded during flight operations to thereby warn a pilot to take corrective action; means for increasing the magnitude of the tactile warning when the turbine output temperature reaches its maximum operating temperature; means for determining an impending dangerous condition associated with the other safe operating parameters; and means for increasing the frequency of the tactile warning in response to the impending dangerous condition when the impending dangerous condition is imminent.