A method of folding a convertiplane (1, 1', 1"), said convertiplane (1, 1', 1"), in turn, comprising: - a fuselage having a first longitudinal axis (A); - a pair of wings ; and - at least a pair of rotors arranged on respective mutually opposite sides of the respective said wings ; each said rotor comprising a mast rotatable about a second axis (B) and a plurality of blades hinged to said mast with respect to said second axis (B); each said wing , in turn, comprising: - a first portion , fixed with respect to said fuselage ; - a second tip portion opposite to said first portion ; and - a third intermediate portion , which is interposed between the associated said first portion and the associated said second tip portion ; said mast of each said rotor being integrally tiltable with said second axis (B) and the associated said second tip portion about an associated third axis (E) transversal to said second axis (B) and with respect to said fuselage , so as to set said convertiplane (1, 1', 1") between a helicopter configuration and an aeroplane configuration; each said second axis (B) being, in use, transversal to said first axis (A) of said convertiplane (1, 1', 1") in said helicopter configuration and being, in use, substantially parallel to said first axis (A) in said aeroplane configuration; said method comprising the step i) of arranging said convertiplane (1, 1', 1") in said helicopter configuration; characterized in that it comprises the step ii) of rotating an assembly of each said wing with respect to said fuselage and the associated said first portion about a respective said fourth axis (I, I', I"), so as to fold said respective said wing and arrange said convertiplane (1, 1', 1") in a stowage configuration; each said assembly being formed by said second tip portion and by the associated said third intermediate portion . - a fuselage having a first longitudinal axis (A); - a pair of wings ; and - at least a pair of rotors arranged on respective mutually opposite sides of the respective said wings ; each said rotor comprising a mast rotatable about a second axis (B) and a plurality of blades hinged to said mast with respect to said second axis (B); each said wing , in turn, comprising: - a first portion , fixed with respect to said fuselage ; - a second tip portion opposite to said first portion ; and - a third intermediate portion , which is interposed between the associated said first portion and the associated said second tip portion ; - a first portion , fixed with respect to said fuselage ; - a second tip portion opposite to said first portion ; and - a third intermediate portion , which is interposed between the associated said first portion and the associated said second tip portion ; said mast of each said rotor being integrally tiltable with said second axis (B) and the associated said second tip portion about an associated third axis (E) transversal to said second axis (B) and with respect to said fuselage , so as to set said convertiplane (1, 1', 1") between a helicopter configuration and an aeroplane configuration; each said second axis (B) being, in use, transversal to said first axis (A) of said convertiplane (1, 1', 1") in said helicopter configuration and being, in use, substantially parallel to said first axis (A) in said aeroplane configuration; said method comprising the step i) of arranging said convertiplane (1, 1', 1") in said helicopter configuration; characterized in that it comprises the step ii) of rotating an assembly of each said wing with respect to said fuselage and the associated said first portion about a respective said fourth axis (I, I', I"), so as to fold said respective said wing and arrange said convertiplane (1, 1', 1") in a stowage configuration; each said assembly being formed by said second tip portion and by the associated said third intermediate portion . <EOS>