Abstract: The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin which is connected to the fibre metal laminate.

Abstract: A multilayer structural element, such as a skin panel for an aircraft fuselage, comprises a plurality of metal webs and a plurality of fiber webs arranged as layers in a sandwich structure, where the metal webs of neighbouring layers form stepped connecting regions. A material strip is provided on an outer surface of the sandwich structure for at least partially covering an outlying connecting region, and the material strip enables the placement of rivets at uniform spacing for fastening a structure to the structural element.

Abstract: A window system and a method for manufacturing a window system, wherein a window frame is mounted on a fibre metal laminate skin of for example an aircraft. The window system comprise a fibre metal laminate skin including a mounting surface portion, e.g., the surrounding of a window opening, and a window frame having a first flange. A first side of the first flange being mounted to at least a part of a surface, e.g., the surrounding of a window opening. The first side is form-fitted to the mounting surface portion of the fibre metal laminate skin. The least a part of the surface of the first side of the first flange and the mounting surface portion of the fibre metal laminate skin are bonded.

Abstract: A multilayer structural element is disclosed, in particular a skin panel for an aircraft fuselage, having a multiplicity of metal webs and fiber webs which are arranged in a number of layers, neighbouring metal webs of a layer respectively forming a stepped connecting region, and a material strip being provided for at least partially covering an outlying connecting region in a circumferential direction of the structural element on an outer surface averted from the inner surface of the structural element.