Abstract: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

Abstract: A manufacturing procedure of a composite material part (11), with an edge region (13) destined to be joined to another part by rivets, making a change in the geometry of said edge region (13) with respect to an initial surface (41) on the part's external face, comprising the following steps: a) providing a laying-up tool incorporating a modified surface (43) according to said change in the edge region (13) geometry; b) providing the composite material plies needed for the laying-up of the part, with the plies (51, 51?, . . . , 51n) destined for the edge region (13) of the part affected by the geometric modification being already cut so that they finish as they reach said modified surface (43); c) laying-up said plies over said tool and curing the resultant laminate. The invention also refers to a lower skin of an aircraft wing (11) manufactured according to said procedure.

Abstract: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

Abstract: A manufacturing procedure of a composite material part (11), with an edge region (13) destined to be joined to another part by rivets, making a change in the geometry of said edge region (13) with respect to an initial surface (41) on the part's external face, comprising the following steps: a) providing a laying-up tool incorporating a modified surface (43) according to said change in the edge region (13) geometry; b) providing the composite material plies needed for the laying-up of the part, with the plies (51, 51?, . . . , 51n) destined for the edge region (13) of the part affected by the geometric modification being already cut so that they finish as they reach said modified surface (43); c) laying-up said plies over said tool and curing the resultant laminate. The invention also refers to a lower skin of an aircraft wing (11) manufactured according to said procedure.

Abstract: Procedure for the manufacture of large parts of composite material, controlling the thickness of the edges thereof. It relates to the manufacture of a part (11) possessing edge zone (11) in an aeronautical structure through a join with joining plate (23) and backing plate (25) by means of the following stages: a) Definition of interface surface (15) of edge zone (13) to be in contact with joining plate (23); b) Manufacture of first panel (31) possessing the configuration planned for part (11); c) Obtainment of a map of differences between the thickness of first panel (31) and that which it should possess to be coincident with said interface surface (15); d) Manufacture of supplementary panel (33) having a thickness to be coincident with that of said map of differences; e) joining of supplementary panel (33) to first panel (31).