Abstract: This invention relates to monolithic composite panel, the structure of which comprises a skin (1), a plurality of omega-shaped stiffeners (3), an also omega-shaped element (5) covering said stiffeners (3).

Abstract: Structural component of non-conductive composite material, particularly for aircraft (panel (1), frame (3), stringer (2), etc), that comprises in the surface a metal-type layer (4), such that the mentioned structural component together with the remaining metallized structural components can provide the aircraft with the sufficient conductive metal mass. According to a second aspect of the invention, a metallization method is proposed in the manufacture of a structural component, particularly for aircraft, made of composite material, which method allows the geometric configuration of the add-on by applying it in an extensive or limited manner to predetermined contours by means of using templates. This constructive feature allows creating integrated electric circuits in the airplane structure by means of creating independent tracks with different widths and thicknesses.