Method and vibration phenomena monitoring system occurring in a turbine engine operating aircraft gas

The invention relates to a method and a vibratory phenomena occurring monitoring system in a turbine engine in aircraft operating gas. The method includes establishing (E30) a frequency spectrum of a vibratory signal representative of the engine operating state and its components, using a plurality of vibration signatures, each corresponding to a vibratory phenomenon occurring during operation of the engines aircraft of the same type as that to monitor and originating from a fault or abnormal operation of a component of the motors, identifying (E40) in the spectrum of the points of curves that match mathematical functions each defining a vibratory signature for each identified curve corresponding to a fault of engine components, analyzing (E50) the amplitude associated with the points of the curve with respect to predefined amplitude values ​​corresponding to a degree of severity of the fault, and following the exceeding of a amplitude value or the detection of abnormal operation, transmitting (E60) a message associated with the Signature Vibration e.