Abstract: An aircraft horizontal tail plane (HTP) of the continuous type, wherein the inner-most ribs of the right-hand side and left-hand side torsion boxes are arranged to have one end joined right at the joint zone where both rear spars meet at axis of symmetry of the HTP. In this way, the loads at this central region of the HTP are concentrated at the joint zone where the inner-most ribs and the rear spars converge. The HTP can be manufactured with a reduced number of components.

Abstract: Pivoting coupling system of a large dihedral empennage to the tail fuselage of an aircraft, in which the empennage (1) comprises a right lateral box (la) and a left lateral box (1b) arranged at a large dihedral angle in the tail fuselage (6) of the aircraft, characterised in that it comprises a horizontal central box (1c) joining the lateral boxes (1a, 1b), and which comprises a rear spar (11); and means of linkage (2, 3, 4) for horizontally linking the central box (1c) to a frame structure (7, 8, 9) of the tail fuselage (6) of the aircraft, which allow the empennage (1) to rotate vertically about a horizontal linkage shaft (5) between a negative maximum angle of incidence (??1) and a positive maximum angle of incidence (+?2) in response to the actuation of actuator means which are connected to the empennage (1) and to a structural element of the fuselage of the aircraft.