A method to detect and control detonation phenomena in an internal combustion engine provided with a number of cylinders and with at least two accelerometers (18*, 18**); the method comprising the steps of: acquiring the signal (S*, S**) coming from each accelerometer; determining, for each accelerometer, angular windows associated with each cylinder in which to detect possible detonation phenomena; in particular, determining, for each accelerometer, the beginning instant and the duration of the angular windows associated with each cylinder in order to detect possible detonation phenomena; processing the signal (S*, S**) coming from each accelerometer so as to determine a detonation energy (S el *, S el **) for each accelerometer; determining a first indicator (α) for each accelerometer as a function of the cylinder and of the engine point that is being explored, univocally identified by the revolutions per minute (rpm) and by the load; wherein the first indicator (α) is variable as a function of the observability of the detonation phenomena for each accelerometer and is calculated as a function of a comparison between a threshold value (TV18*, TV18**) and the detonation energy (Sel*, Sel**) for each accelerometer; wherein the threshold value (TV18*, TV18**) is determined as a function of the cylinder and of the engine point that is being explored, univocally identified by the revolutions per minute (rpm) and by the load and wherein the detonation energy (Sel*, Sel**) for each observed combustion by means of the accelerometer is null when the combustion for the considered cylinder at a determined engine point is not observable by means of the accelerometer or when it is observable by means of the accelerometer but the considered cylinder is not detonating and is positive when the combustion for the considered cylinder at a given engine point is observable and is detonating; defining a second global indicator (β) of observability of the combustion at a given engine point for a cylinder, wherein the second global indicator (β) of observability is calculated as a function of the first indicator (α) of each accelerometer; in particular, the second global indicator (β) of observability is determined by adding said first indicators (α) of the accelerometers, in which the combustion can be fully observable by means of both detonation sensors or by means of a preferred detonation sensor, or partially observable by means of the two detonation sensors or not observable by any of the detonation sensors; and controlling the ignition advance implemented for the cylinder in the next combustion cycle, as a function of the second global indicator (β) of observability of the combustion at the given engine point for the cylinder. acquiring the signal (S*, S**) coming from each accelerometer; determining, for each accelerometer, angular windows associated with each cylinder in which to detect possible detonation phenomena; in particular, determining, for each accelerometer, the beginning instant and the duration of the angular windows associated with each cylinder in order to detect possible detonation phenomena; processing the signal (S*, S**) coming from each accelerometer so as to determine a detonation energy (S el *, S el **) for each accelerometer; determining a first indicator (α) for each accelerometer as a function of the cylinder and of the engine point that is being explored, univocally identified by the revolutions per minute (rpm) and by the load; wherein the first indicator (α) is variable as a function of the observability of the detonation phenomena for each accelerometer and is calculated as a function of a comparison between a threshold value (TV18*, TV18**) and the detonation energy (Sel*, Sel**) for each accelerometer; wherein the threshold value (TV18*, TV18**) is determined as a function of the cylinder and of the engine point that is being explored, univocally identified by the revolutions per minute (rpm) and by the load and wherein the detonation energy (Sel*, Sel**) for each observed combustion by means of the accelerometer is null when the combustion for the considered cylinder at a determined engine point is not observable by means of the accelerometer or when it is observable by means of the accelerometer but the considered cylinder is not detonating and is positive when the combustion for the considered cylinder at a given engine point is observable and is detonating; defining a second global indicator (β) of observability of the combustion at a given engine point for a cylinder, wherein the second global indicator (β) of observability is calculated as a function of the first indicator (α) of each accelerometer; in particular, the second global indicator (β) of observability is determined by adding said first indicators (α) of the accelerometers, in which the combustion can be fully observable by means of both detonation sensors or by means of a preferred detonation sensor, or partially observable by means of the two detonation sensors or not observable by any of the detonation sensors; and controlling the ignition advance implemented for the cylinder in the next combustion cycle, as a function of the second global indicator (β) of observability of the combustion at the given engine point for the cylinder.