Abstract: Damages to load supporting structures in an aircraft or spacecraft resulting from an explosive decompression are minimized or avoided by rapidly making available at least one relatively large flow-cross-sectional area. This is accomplished by mounting a decompression panel with a plurality of releasable mounting locks to a frame. The locks are so constructed that the panel along can be blown out in one direction and the panel with the frame and the locks can be blown out in the opposite direction in response to a rapid pressure increase which shears off shearing pins normally holding locking levers in a clamp-down or hold-down position. The frame has support flanges against which the panel and a wall section rest. The locks rest on and are secured to the frame and respond to defined release pressure ratios between the inside and outside in either direction. Each lock has at least one locking or clamp-down lever for the panel and one for a wall section.