A control system (50) for a turbopropeller engine (2) of an aircraft (1) having a gas turbine (11) and a propeller assembly (3) coupled to the gas turbine (11), the gas turbine (11) having a compressor (12) coupled to an air intake (13) and a temperature sensor (22) being arranged in the air intake (13) to measure the temperature of engine intake air and provide a sensed temperature (T1sens); the control system envisages: a compensation system (40) to receive the sensed temperature (T1sens) from the temperature sensor (22) and to add to the sensed temperature (T1sens) a compensation quantity (comp) to compensate for a delay introduced by the time constant (τ) of the temperature sensor (22) and generate a compensated temperature (T1comp); and a control unit (20) to perform engine control operations based on the compensated temperature (T1comp). In particular, the compensation quantity (comp) is calculated based on an ISA International Standard Atmosphere—temperature (T1ISA), which is determined as a function of an external pressure (P0) measured by a pressure sensor (35).