An aircraft having a vertical takeoff and landing flight mode and a forward flight mode, the aircraft comprising: a fuselage; a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage, the dual tiltwing assembly including a forward wing, an aft wing and a quadrilateral linkage, the quadrilateral linkage coupling the forward wing to the aft wing and the quadrilateral linkage coupling the forward and aft wings to the fuselage, wherein the quadrilateral linkage includes two sets of oppositely disposed quadrilateral linkage sections (70a, 70b); a distributed propulsion system coupled to the dual tiltwing assembly, the distributed propulsion system including a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing; and a flight control system operably associated with the distributed propulsion system and the dual tiltwing assembly, the flight control system operable to independently control each of the propulsion assemblies and operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation; wherein each of the quadrilateral linkage sections (70a, 70b) includes: - a fixed link formed by the fuselage, - an input link (74a, 74b) coupled between the fixed link and one of the forward and aft wings, - an output link (80a, 80b) coupled between the fixed link and the other of the forward and aft wings, and - a floating link (86a, 86b) coupled between the forward wing and the aft wing in a rotational relationship with the wings (20, 22) and in a rotational relationship with the input (74a, 74b) and output (80a, 80b) links; the aircraft further comprising a first rotatable shaft coupling the input links (74a, 74b) of the quadrilateral linkage sections (70a, 70b) and a second rotatable shaft coupling the output links (80a, 80b) of the quadrilateral linkage sections (70a, 70b); wherein each of the quadrilateral linkage sections (70a, 70b) further includes a synchronizing link (88a, 88b) coupled in rotational relationship with the forward wing and the aft wing to maintain an angle of incidence of the forward wing substantially congruent with an angle of incidence of the aft wing during transitions between the vertical lift orientation and the forward thrust orientation of the dual tiltwing assembly. a fuselage; a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage, the dual tiltwing assembly including a forward wing, an aft wing and a quadrilateral linkage, the quadrilateral linkage coupling the forward wing to the aft wing and the quadrilateral linkage coupling the forward and aft wings to the fuselage, wherein the quadrilateral linkage includes two sets of oppositely disposed quadrilateral linkage sections (70a, 70b); a distributed propulsion system coupled to the dual tiltwing assembly, the distributed propulsion system including a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing; and a flight control system operably associated with the distributed propulsion system and the dual tiltwing assembly, the flight control system operable to independently control each of the propulsion assemblies and operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation; wherein each of the quadrilateral linkage sections (70a, 70b) includes: - a fixed link formed by the fuselage, - an input link (74a, 74b) coupled between the fixed link and one of the forward and aft wings, - an output link (80a, 80b) coupled between the fixed link and the other of the forward and aft wings, and - a floating link (86a, 86b) coupled between the forward wing and the aft wing in a rotational relationship with the wings (20, 22) and in a rotational relationship with the input (74a, 74b) and output (80a, 80b) links; - a fixed link formed by the fuselage, - an input link (74a, 74b) coupled between the fixed link and one of the forward and aft wings, - an output link (80a, 80b) coupled between the fixed link and the other of the forward and aft wings, and - a floating link (86a, 86b) coupled between the forward wing and the aft wing in a rotational relationship with the wings (20, 22) and in a rotational relationship with the input (74a, 74b) and output (80a, 80b) links;