A convertiplane comprising: - a fuselage having a first longitudinal axis; - a pair of half-wings; and - a pair of rotors arranged on respective mutually opposite ends of said half-wings; each said rotor comprising a mast rotatable about a second axis and a plurality of blades hinged on said mast with respect to said second axis; said mast of each said rotor being tiltable integrally with said second axis about a third axis transversal to said second axis and with respect to said fuselage so as to transform said convertiplane between a helicopter configuration and an aeroplane configuration of said convertiplane; each said second axis being, in use, transversal to said first axis of said convertiplane in said helicopter configuration and being, in use, substantially parallel to said first axis in said aeroplane configuration; each said rotor being associated with a respective imaginary rotor disc, which is defined by the imaginary circumference described, in use, by the rotation of the free tips of said blades opposite to the respective said second axis; said rotor disc being tiltable about a fourth axis transversal to said second axis; each said rotor further comprising control means for controlling the cyclic pitch and collective pitch of the corresponding said blades; said control means comprising, in turn, for each said rotor: - a first actuator (51, 20) controllable to alter said collective pitch of the corresponding said blades; and - a second actuator controllable to alter the tilt of the corresponding said rotor disc about said fourth axis; wherein said control means comprise, for each said rotor, a rod movable to alter a tilt angle (α, β) of the corresponding said rotor disc about a fifth axis transversal to said corresponding fourth axis and to said second axis; said rod being movable according to the helicopter or airplane configuration of said convertiplane, so as to control said tilt angle (α, β) according to said helicopter or airplane configuration of said convertiplane; characterised in that said convertiplane comprises, for each said rotor, a control member operatively connected to the corresponding said first actuator (51, 20) and to the corresponding said rod, and selectively operable to alter said collective pitch of said corresponding said blades; each said control member is movable: - between a first and a second position, with which are associated respective first and second values of said collective pitch of said blades characteristic of said helicopter configuration; and - between said second and a third position, with which are associated respective second and third values of said collective pitch of said blades characteristic of the transition from said helicopter configuration to said aeroplane configuration and of said aeroplane configuration; said rod and control means of each rotor is configured in such a way that the movement of said control member between the corresponding said second and third positions causes a reversal of said tilt of the corresponding rotor disc with respect to and about said fifth axis. - a fuselage having a first longitudinal axis; - a pair of half-wings; and - a pair of rotors arranged on respective mutually opposite ends of said half-wings; - a first actuator (51, 20) controllable to alter said collective pitch of the corresponding said blades; and - a second actuator controllable to alter the tilt of the corresponding said rotor disc about said fourth axis; - between a first and a second position, with which are associated respective first and second values of said collective pitch of said blades characteristic of said helicopter configuration; and - between said second and a third position, with which are associated respective second and third values of said collective pitch of said blades characteristic of the transition from said helicopter configuration to said aeroplane configuration and of said aeroplane configuration;