A method of stopping a turboshaft engine in flight. During a power reduction step, a current power of the engine for stopping is reduced to reach zero power, and a current speed of rotation of the gas generator of the engine for stopping is reduced to reach a predetermined intermediate speed when the current power becomes zero. During a temperature stabilization step, the current speed of rotation remains equal to the intermediate speed. During a shutdown step, the current speed of rotation is reduced to reach zero speed.