Abstract: The invention relates to an assembly between a front fitting and the traction coupling of the two lateral boxes of the horizontal stabilizer of an aircraft comprising a front fitting (1, 1a and 1b), a front shear plate (2), an upper shear plate (4), a lower shear plate (5) and a “rib post” union piece (3) in such a way that the loads being transferred to the lateral boxes are minimized, and at the same time it allows a proper trimming of the horizontal stabilizer. Moreover, the present invention describes a compact front fitting, made of one piece, as a whole, and in composite material.

Abstract: A device for coupling a coupling pivot for a trimmable horizontal stabilizer to the tail fuselage of an aircraft, with an inner plate, an outer plate with first fastening holes and first passage holes in the inner plate respectively facing second fastening holes and second passage holes in the outer plate for the passage of a coupling pivot of the horizontal stabilizer, and with an upper lug and a lower lug respectively located above and below a cut-out for the horizontal stabilizer. The lugs are integral with separate reinforced zones of the covering in respective neighboring areas of the cut-out, in such a way that the plates between them clasp the respective reinforced zones in which the lugs are provided.

Abstract: The invention relates to an assembly between a front fitting and the traction coupling of the two lateral boxes of the horizontal stabilizer of an aircraft comprising a front fitting (1, 1a and 1b), a front shear plate (2), an upper shear plate (4), a lower shear plate (5) and a “rib post” union piece (3) in such a way that the loads being transferred to the lateral boxes are minimized, and at the same time it allows a proper trimming of the horizontal stabilizer. Moreover, the present invention describes a compact front fitting, made of one piece, as a whole, and in composite material.

Abstract: Device for coupling a coupling pivot for a trimmable horizontal stabilizer (1b) to the tail fuselage (1a) of an aircraft (1), with an inner plate (10), an outer plate (11) with first fastening holes (10a, 11a) and first passage holes (10c) in the inner plate respectively facing second fastening holes (10b, 11b) and second passage holes (11c) in the outer plate (11) for the passage of a coupling pivot (9) of the horizontal stabilizer (1b); and with an upper lug (12) and a lower lug (13) respectively located above and below a cut-out (2) for the horizontal stabilizer (1b). The lugs (12, 13) are integral with separate reinforced zones (14, 15) of the covering (1f) in respective neighboring areas of the cut-out (2), in such a way that the plates (10, 11) between them clasp the respective reinforced zones (14, 15) in which the lugs (12, 13) are provided.