A loads interface (1), particularly a loads interface (1) of an aircraft door with an edge frame (13), an outer skin (15) and a beam (14). A loads transferring flange (11) is designed to transmit transverse, circumferential and/or longitudinal forces, is provided with at least three flanges (18, 19, 20) for distribution of the loads in the edge frame (13), the outer skin (15) and the beam (14).
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