Aircraft gas turbine engine with a first rotatable shaft

The aircraft gas turbine (1) has a first rotating shaft (16), through which torque is interchanged between the two units, and a coaxial-arranged second shaft (17), which is rotationally connected to an area near to a shaft end of the first shaft. A second lever arm is connected in an operating manner with a first lever arm engaged in an opening of the shafts with an electrical sensor device. The equivalent sensor signal is generated in an area of the sensor device by preparing the active connection for a defined twisting of the first shaft.