The claimed versions belong to tilt rotors nonexpendable aircrafts. In general, the convertiplane has a fuselage, a wing and engine groups. In one embodiment each engine group is designed in the form of at least one engine positioned with the possibility to turn, provided that the engines in groups are designed in view of the condition of thrust change relative to each other and/or groups and engine groups are positioned at the tip of corresponding wing at front fuselage and tail fuselage. In a second embodiment the wing is designed combined in the form of forward-swept wing and aft-swept wing, each engine group is designed in the form of at least one engine positioned with the possibility to turn, provided that the engines in groups are designed in view of the condition of thrust change relative to each other and/or groups and groups are positioned at the tip of corresponding wing. The claimed versions allow simplification and weight reduction of AC structure, increasing of its maneuvering ability at every flight stage, improvement of its aerodynamic quality such as stability and aerodynamic efficiency.