Abstract: A method for manufacturing a composite part of an aircraft comprising the steps of placing a prepreg preform in a molding die between at least a molding die base part and a molding die upper part, debulking the air trapped in the prepreg, displacing the molding die upper part against the molding die base part in a direction perpendicular to the plane of the prepreg preform such that the molding die upper part presses the laminated perform until it reaches a blocking arrangement defining the position of the upper part relative to the base part for giving the prepreg preform the nominal thickness of the cured part, wherein said displacement is achieved by bolting the different parts of the molding die against each other, providing an elevated temperature to the preform such that it is cured.

Abstract: A method for manufacturing a composite part of an aircraft comprising the steps of placing a prepreg preform in a molding die between at least a molding die base part and a molding die upper part, debulking the air trapped in the prepreg, displacing the molding die upper part against the molding die base part in a direction perpendicular to the plane of the prepreg preform such that the molding die upper part presses the laminated perform until it reaches a blocking arrangement defining the position of the upper part relative to the base part for giving the prepreg preform the nominal thickness of the cured part, wherein said displacement is achieved by bolting the different parts of the molding die against each other, providing an elevated temperature to the preform such that it is cured.

Abstract: Rib-fitting as a component (9) of a torsion box (1, 3) of an aircraft lift surface made of composite material as a single piece, comprising: a substantially planar web (31) with a first part in the form of a lug (33) and a second part in the form of a rib web (35); two flanges (39) to attach the web (31) with the webs of each of the ends of the front or back spar (11, 13) to which it is joined; flanges (43) for being attached to the upper and lower skins (19, 21) of the torsion box; gaps (45) in the areas of intersection with the front or back spar caps (11, 13) to which the component (9) is connected and with the reinforcement stringers (25) of the skins (19, 21). The invention also comprises and assembly process for the rib-fitting in multispar torsion boxes.