A vertical take-off and landing, VTOL, aircraft comprising: a fuselage; first and second forward wings (20, 22) mounted to opposing sides of the fuselage, each wing (20, 22) having a fixed leading edge and a trailing control surface which is pivotal about a generally horizontal pivot axis; each wing (20, 22) having first and second electric motors each having rotors, the electric motors and rotors being secured to and pivotal with the trailing control surface between a first position in which each rotor has a generally vertical axis of rotation, and a second position in which each rotor has a generally horizontal axis of rotation; a control system for controlling each electric motor; characterised in that the first and second electric motors and rotors located on the same wing (20, 22) are mounted to have respectively different thrust lines, and that the control system is configured to selectively operate the first electric motor and rotor and the second electric motor and rotor located on the same wing (20, 22) to generate non-equal thrust forces to generate a turning moment to pivot the control surface about the pivot axis; and either: the thrust line of the first electric motor and rotor is angularly offset relative to the thrust line of the second electric motor and rotor located on the same wing (20, 22); or the first electric motor and rotor are located above the control surface, and the second electric motor and rotor are located below the control surface of the same wing (20, 22), such that the thrust line of the first electric motor and rotor is generally parallel to and offset relative to the thrust line of the second electric motor and rotor. a fuselage; first and second forward wings (20, 22) mounted to opposing sides of the fuselage, each wing (20, 22) having a fixed leading edge and a trailing control surface which is pivotal about a generally horizontal pivot axis; each wing (20, 22) having first and second electric motors each having rotors, the electric motors and rotors being secured to and pivotal with the trailing control surface between a first position in which each rotor has a generally vertical axis of rotation, and a second position in which each rotor has a generally horizontal axis of rotation; a control system for controlling each electric motor; characterised in that the first and second electric motors and rotors located on the same wing (20, 22) are mounted to have respectively different thrust lines, and that the control system is configured to selectively operate the first electric motor and rotor and the second electric motor and rotor located on the same wing (20, 22) to generate non-equal thrust forces to generate a turning moment to pivot the control surface about the pivot axis; and either: the thrust line of the first electric motor and rotor is angularly offset relative to the thrust line of the second electric motor and rotor located on the same wing (20, 22); or the first electric motor and rotor are located above the control surface, and the second electric motor and rotor are located below the control surface of the same wing (20, 22), such that the thrust line of the first electric motor and rotor is generally parallel to and offset relative to the thrust line of the second electric motor and rotor. the thrust line of the first electric motor and rotor is angularly offset relative to the thrust line of the second electric motor and rotor located on the same wing (20, 22); or the first electric motor and rotor are located above the control surface, and the second electric motor and rotor are located below the control surface of the same wing (20, 22), such that the thrust line of the first electric motor and rotor is generally parallel to and offset relative to the thrust line of the second electric motor and rotor.