Abstract: A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that can be put under an internal pressure, comprises a pressure dome, which is designed with a concave inner surface and a convex outer surface; inspection hatches, which each form an aperture in the pressure dome from the inner surface to the outer surface; and pressure covers for pressure-tight closure of the inspection hatches, wherein the pressure covers each have a cover and a pressure seal, wherein the cover is designed for the repeatedly releasable fixing of the pressure cover on the concave inner surface over the inspection hatch and wherein the pressure seal is formed at the edge of the cover for the pressure-tight closure of the cover with the pressure dome.

Abstract: A decompression device has at least one decompression member which is arranged on a supporting structure and which, in the event of differential pressure of a predetermined level, opens an opening in the supporting structure that acts as a connection between two volumes, wherein the decompression member can move between a retention position, in which the decompression member closes the opening, and a released position, in which the decompression member opens the opening, and has a locking arrangement which, when in use, fixes the decompression member in the retention position. The locking arrangement is provided with at least one locking element, which is arranged on the supporting structure, and the decompression member is kept in the retention position indirectly by the locking element interacting with an air conduction part.

Abstract: A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that can be put under an internal pressure, comprises a pressure dome, which is designed with a concave inner surface and a convex outer surface; inspection hatches, which each form an aperture in the pressure dome from the inner surface to the outer surface; and pressure covers for pressure-tight closure of the inspection hatches, wherein the pressure covers each have a cover and a pressure seal, wherein the cover is designed for the repeatedly releasable fixing of the pressure cover on the concave inner surface over the inspection hatch and wherein the pressure seal is formed at the edge of the cover for the pressure-tight closure of the cover with the pressure dome.

Abstract: A decompression device has at least one decompression member which is arranged on a supporting structure and which, in the event of differential pressure of a predetermined level, opens an opening in the supporting structure that acts as a connection between two volumes, wherein the decompression member can move between a retention position, in which the decompression member closes the opening, and a released position, in which the decompression member opens the opening, and has a locking arrangement which, when in use, fixes the decompression member in the retention position. The locking arrangement is provided with at least one locking element, which is arranged on the supporting structure, and the decompression member is kept in the retention position indirectly by the locking element interacting with an air conduction part.

Abstract: The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling whose rear area can be moved in the axial direction of the engine from a closed forward-thrust position into a rearward moved thrust-reversing position in which a free, substantially annular space to a front and fixed area of the engine cowling is present, where on the engine cowling guide rails are arranged, inside which mounting elements can be moved by means of rolling or sliding elements, with which mounting elements the rear area of the engine cowling is mounted, characterized in that the guide rails have an oval and C-shaped cross-section, provided on a longitudinal side with a slot-like opening, and are mounted using mounting projections arranged centrally and opposite to one another and designed in one piece with the C-shaped cross-section.

Abstract: The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling whose rear area can be moved in the axial direction of the engine from a closed forward-thrust position into a rearward moved thrust-reversing position in which a free, substantially annular space to a front and fixed area of the engine cowling is present, where on the engine cowling guide rails are arranged, inside which mounting elements can be moved by means of rolling or sliding elements, with which mounting elements the rear area of the engine cowling his mounted, characterized in that the guide rails have an oval and C-shaped cross-section, provided on a longitudinal side with a slot-like opening, and are mounted using mounting projections arranged centrally and opposite to one another and designed in one piece with the C-shaped cross-section.