Abstract: The lifting surfaces comprise a torsion box capable of bearing aerodynamic and inertial loads. The torsion box has lateral parts that are connected together by an attachment comprising a rib, having a central upper part and a central support lower part joined only by angled cross bars, forming a truss structure along the length of the central support upper part and the central support lower part. The angled cross bars are attached to the upper and the lower parts of the central support: alternatively to both sides of a plane of symmetry defined by said upper and lower parts of the central support, dividing the torsion box in the two lateral parts making a zone of access perpendicular to the length of the central supports, where said zone of access is closed with a piece provided with at least one hole for permanent access.

Abstract: Joining structure for aircraft fairing (7), said fairing (7) being arranged between the horizontal stabilizer and the vertical stabilizer or fuselage section (6) of the aircraft, the structure comprising fittings (2) in the shape of angle, the fittings in turn comprising a vertical surface and a horizontal surface, the fittings (2) being joined via their vertical surface to the fairing (7) with removable fixing parts (12), the structure also comprising a deformable resilient element (13) between the fairing (7) and the vertical surface of the fitting (2), such that the resilient element (13) is able to compensate for the necessary deformation play and the manufacturing and assembly tolerances of the fittings (2), the fairing (7), the horizontal stabilizer and the vertical stabilizer or fuselage section (6) with different torques for tightening of the above parts.

Abstract: Joining structure for aircraft fairing (7), said fairing (7) being arranged between the horizontal stabilizer and the vertical stabilizer or fuselage section (6) of said aircraft, said structure comprising fittings (2) in the shape of angle, said fittings in turn comprising a vertical surface and a horizontal surface, the fittings (2) being joined via their vertical surface to the fairing (7) by means of removable fixing parts (12), said structure also comprising a deformable resilient element (13) between the fairing (7) and the vertical surface of the fitting (2), such that said resilient element (13) is able to compensate for the necessary deformation play and the manufacturing and assembly tolerances of the fittings (2), the fairing (7), the horizontal stabilizer and the vertical stabilizer or fuselage section (6) by means of different torques for tightening of the above parts.

Abstract: The lifting surface consists of a torsion box capable of bearing aerodynamic and inertial loads, and the semi-parts (1, 1?) comprising it are connected together with joining means conventionally consisting of a rib in one piece in its plane of symmetry, the final assembly of said lifting surfaces requiring some inspection openings or holes for being able to gain access to the corresponding joints. The invention provides other joining means which avoid that rib and which consist of a plurality of bars (2) modularly arranged in the manner of a lattice, in such a is way that the required amount of said inspection holes is reduced, and a sequential assembly connecting the upper and lower ends of the bars (2) is facilitated.