Abstract: A process for assembling portions of an aeronautical wing, in which a wing covering is assembled with carrier structural elements, allows the simultaneous application of all filling tapes on an exposed surface, by speeding-up and making more reliable the process itself. The process includes: placing side by side the structural elements longitudinally, to form the spars, by determining a flat surface, having a plurality of longitudinal junctions, faced upwards; adhering to the longitudinal junctions respective filling tapes; translating and rotating by 180° the structural elements in one single solution, by keeping them fixed in the mutual positions thereof and by transferring them above an inner surface of a wing covering; and translating the structural elements in one single solution, by keeping them fixed in the mutual positions thereof, downwards, by making the flat surface thereof to coincide with said inner surface.

Abstract: A process for assembling portions of an aeronautical wing, in which a wing covering is assembled with carrier structural elements, allows the simultaneous application of all filling tapes on an exposed surface, by speeding-up and making more reliable the process itself. The process includes: placing side by side the structural elements longitudinally, to form the spars, by determining a flat surface, having a plurality of longitudinal junctions, faced upwards; adhering to the longitudinal junctions respective filling tapes; translating and rotating by 180° the structural elements in one single solution, by keeping them fixed in the mutual positions thereof and by transferring them above an inner surface of a wing covering; and translating the structural elements in one single solution, by keeping them fixed in the mutual positions thereof, downwards, by making the flat surface thereof to coincide with said inner surface.

Abstract: A process for assembling aircraft control surfaces (1, 1?), in particular high-lift devices and wing portions, allows implementing smooth control surfaces in short times, wherein the control surface is defined by an upper skin (2) and by a lower skin (9), the upper skin being destined to form the leading edge (4) of the control surface by means of the connection to a front spar (3), wherein the upper skin and the lower skin are made of a laminar composite material which, not yet hardened, is fastened to structural elements (3, 5, 6, 7) of the control surface by means of an adhesive; and wherein the resin of the composite material and the adhesive are hardened simultaneously in autoclave.

Abstract: A process for assembling aircraft control surfaces (1, 1?), in particular high-lift devices and wing portions, allows implementing smooth control surfaces in short times, wherein the control surface is defined by an upper skin (2) and by a lower skin (9), the upper skin being destined to form the leading edge (4) of the control surface by means of the connection to a front spar (3), wherein the upper skin and the lower skin are made of a laminar composite material which, not yet hardened, is fastened to structural elements (3, 5, 6, 7) of the control surface by means of an adhesive; and wherein the resin of the composite material and the adhesive are hardened simultaneously in autoclave.