An aircraft including at least one pressure-relief device having: at least one fixed part, at least one deformable mobile wall configured to occupy a closed position in which it blocks an opening, at least one retaining system configured to retain the mobile wall in the closed position as long as the wall is not in a given deformed state, the retaining system including: at least one first slot through the mobile wall opening at the level of one of its edges, for each slot, a first retaining element fastened to the fixed part and configured to cooperate with the slot as long as the mobile part is not in the given deformed state.

A method of installing and replacing a plurality of decompression panels into a sidewall assembly of an aircraft includes coupling a first decompression panel to at least one of a sidewall and a floor panel of the sidewall assembly. The method also includes inserting a tab of the first decompression panel into a slot of a second decompression panel. The slot is defined by a flange extending along a surface of the second decompression panel. The method further includes coupling the second decompression panel to at least one of a sidewall and a floor panel of the sidewall assembly.

The present invention provides a water inflow prevention device for aircraft, working when landing in water, the device including: a blocking body for blocking a flow channel from an outside of the aircraft when landing in water, the flow channel allowing the inside and outside of the aircraft to communicate with each other, and a valve element of a pressure adjusting valve being positioned in the flow channel; and a connection part that is deformed when landing in water, wherein the blocking body is supported by a member constituting an end of the flow channel on a side outside the aircraft through the connection part, and the connection part is deformed in a direction so as to block the flow channel by the blocking body, with use of force of water acting on the blocking body when landing in water.

A pressure relief door assembly includes a pressure relief door, a pressure-actuated latch, and a temperature-actuated lock. The latch is disposable in each of a latched configuration (to retain the pressure relief door in a closed position) and an unlatched configuration (to allow the pressure relief door to move into an open position). The lock is disposable in each of an unlocked configuration (to allow the pressure relief door to move into the open position when the latch is in its unlatched configuration) and a locked configuration (e.g., to lock the latch in its latched configuration, to lock the pressure relief door in its closed position, or both). The lock may include a bimetallic coil, that when exposed to a temperature that satisfies a temperature threshold, expands a sufficient amount to engage a locking pin with a corresponding portion of the latch to retain the latch in its latched configuration.

An aircraft decompression assembly, comprising a cabin lining element, an element opening and an air channel adjacent to an element rear face and connected to the opening. A channel outlet, during normal assembly operation, discharges air exiting a cabin region delimited by the element through the opening into a secluded area between the element and an aircraft outer skin. A first decompression opening has a first decompression flap, which during normal operation, closes the first decompression opening and, in the event of a rapid decompression, opens the first decompression opening equalizing a pressure between the cabin region and the secluded area. A second decompression opening in the lining element has a second decompression flap which, during normal operation, closes the second decompression opening and which, in the event of a rapid decompression, opens the second decompression opening equalizing a pressure between the cabin region and the secluded area.

A decompression assembly for use in an aircraft comprises a cabin lining element, an opening formed in the element, and an air channel arranged adjacent to a rear face of the element and connected to the opening. The air channel is provided with an air outlet which, during normal operation of the assembly, discharges air exiting a cabin region delimited by the element through the opening into an area located between the element and an aircraft outer skin, a first decompression opening, and a first decompression flap which, during normal operation of the decompression assembly, closes the first decompression opening in the air channel and which, in the event of a rapid decompression, opens the first decompression opening to allow a pressure equalization between the aircraft cabin region and the aircraft area located between the cabin lining element and the aircraft outer skin.

A method and apparatus are provided for at least partially environmentally isolating a volume, such as by environmentally isolating the cargo compartment from the passenger compartment of an aircraft. In the context of an apparatus, a barrier curtain is provided that partially defines the volume. The apparatus also includes a cable extending along one or more walls that partially define the volume. The barrier curtain is supported by the cable. The apparatus may also include a cable release mechanism. The cable is held in place by the cable release mechanism and the cable release mechanism is configured to detach the cable at a predetermined load, thereby permitting the barrier curtain to drop in response to a decompression event.

A return air bridge for use in an aircraft assembly includes an inboard portion configured to couple to a sidewall assembly at a bottom edge of the sidewall assembly and an outboard portion configured to couple to a structural member. The return air bridge also includes at least one support coupling the inboard portion to the outboard portion such that a return air flow path is defined between the inboard portion and the outboard portion. The outboard portion comprises a plate configured to direct an air flow along the return air flow path upwardly with respect to the bottom edge of the sidewall assembly.

A pressure relief panel guard for use with a pressure relief ceiling panel having a perimeter and positioned in an aircraft cargo bay ceiling. The panel guard including a mounting structure attachable to the cargo bay ceiling, and having a mounting portion and a guard support portion, and a guard structure releasably supported by the guard support portion of the mounting structure. The guard structure having a perimeter wall and a central opening between the perimeter wall sized such that when supported by the guard support portion of the mounting structure at the pressure relief ceiling panel the pressure relief ceiling panel is vertically aligned with the central opening with the perimeter wall extending about the perimeter of the pressure relief ceiling panel and the perimeter wall does not overlap the pressure relief ceiling panel or otherwise restrict operational access to the pressure relief ceiling panel from below.

A water-inflow prevention device is provided by installing a closing lid 6 for blocking a duct 2 of an air pressure regulating valve 1, which regulates air pressure inside a cabin 101. A buoyant body 9 is attached to the disc-shaped closing lid 6 installed to the duct 2 so as to be rotatable around a rotation shaft 7. The buoyant body 9 receives a buoyant force from water when immersed in the water. Since the side of the closing lid 6 in which the buoyant body 9 is attached is thereby floated in the water, the closing lid 6 automatically rotates around the rotation shaft 7 so as to close a ventilation port 2a.