A locking mechanism for a door panel to be positioned within and out of blocking relationship with an opening. Mechanism includes a deadbolt rotatably connected to the wall and having a curved configuration and a locking bracket connected to the door panel. The locking bracket extends from the door panel in an angular direction with respect to a plane of door panel. With door panel in a closed position and deadbolt in a first position, the locking bracket extends through the curved configuration. Deadbolt is in blocking relationship with the locking bracket in a direction along a plane of the door panel and is not in blocking relationship in a direction along the locking bracket. With door panel in closed position, deadbolt is in a second position not in blocking relationship with the locking bracket permitting door panel to move in a direction along a plane of the door panel.

A decompression panel assembly for use in an aircraft includes a body panel having an opening defined therein and a cover panel positioned within the opening and spaced from the body panel. The decompression panel assembly also includes an annular spacer panel positioned outboard from the cover panel and the body panel. The spacer panel is spaced from the cover panel to define a first annular flow path between the cover panel and the spacer panel, and the spacer panel is spaced from the body panel to define a second annular flow path between the body panel and the spacer panel.

A door assembly includes a door panel having a first pair of bearings secured to a top portion of the door panel and a second pair of bearings secured to a bottom portion of the door panel. A wall having an opening which extends through the wall wherein a first rail track extends along a first end portion of the opening having a first opening and a second rail track extends along a second end portion of the opening having a second opening. At least one hinge blocking assembly includes a first bracket connected to the wall and a second bracket wherein the second bracket is rotatably mounted to the first bracket about a fixed axis of rotation defined by the at least one hinge blocking assembly wherein with the second bracket in a first position the second bracket extends away from the first bracket.

An aircraft cabin floor structure which makes it possible to avoid the appearance of blisters in the carpets covering the floor panels in an aircraft cabin is disclosed. The aircraft cabin floor structure comprises a rigid carpet that is impermeable to air having a top face and a bottom face, an adhesive layer having an adhesive top face and an adhesive bottom face, said top face adhering to the bottom face of the carpet, and a floor panel that is impermeable to air having a top face and a bottom face, the bottom face of the adhesive layer adhering to the top face of the floor panel. The bottom face of the carpet comprises grooves and at least one air evacuation channel over its periphery. The adhesive layer comprises a plurality of through holes.

An aircraft outflow valve with a heat exchanger is disclosed herein. The aircraft outflow valve can include a heat exchanger that includes an air flow path. Air can flow through the air flow path and exit the outflow valve through an opening at the end of the air flow path. Such airflow can regulate the internal pressure of the aircraft and can also dissipate heat from the outflow valve. The outflow valve can further include a liquid coolant flow path. The liquid coolant flow path can be coupled to liquid coolant lines of electronics of the aircraft. Thus, heat from the electronics of the aircraft can be dissipated through heat transfer between the coolant and the outflow valve, which is accordingly cooled by the airflow through the heat exchanger.

A door opening system with a deceleration mechanism may be adapted to control an opening of a door module that includes a door panel and a door frame. Deceleration mechanism may include strap that connects door panel with door frame, spool, and spool. Spool may receive one end of strap, is biased to roll up a first portion of strap, and adapted to perform a first unwinding of the first portion of strap. Spool may receive a second end of strap, is biased to roll up a second portion of strap, and adapted to perform a second unwinding of the second portion of strap from spool. Spool may include a braking apparatus that is adapted to decelerate the second unwinding when a velocity of the second unwinding is above a predetermined threshold.

A method of installing a decompression panel assembly in an aircraft. The decompression panel assembly includes a body portion, a baffle member, and a panel member. The method includes coupling the body portion to the panel member, wherein the body portion includes a plurality of frame members defining a plurality of openings in the body portion. The method also includes coupling the baffle member to the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings. The baffle member is integrally formed with the plurality of frame members and is configured for at least partial displacement from the at least one opening during a decompression event. The decompression panel assembly is then coupled between a sidewall and a floor panel of the aircraft.

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.

A barrier for providing isolation between two internal volumes within an aircraft, comprises: a wall section adapted for location within an aircraft, the wall section having an aperture formed therein; mounting means located on the wall section proximate the aperture; and a substantially planar burst panel member having first and second opposingly-facing sides, the burst panel member adapted for location within the mounting means and dimensioned so as to overlie the aperture when received by the mounting means; the burst panel member comprising a line of weakness provided therein, adapted such that, in use, exposure of the burst panel member to an atmospheric pressure differential between air volumes respectively adjacent the first and second sides exceeding a predetermined value causes the burst panel member to rupture along said line of weakness.

A system for displaying the state of an aircraft cargo door. The cargo door is configured pivot between a closed position and an open position, the closed and open positions defining a pivoting range. The cargo door is lockable both in the closed position and in the open position. The cargo door is in a regular state when locked in the closed position or the open position. The cargo door is in a warning state when in the pivoting range between the closed position and open position. The cargo door is in a faulty state when unlocked in the closed position or unlocked in the open position or when there is an obstacle in the pivoting range. The cargo door comprises at least one indicator configured to display the respective state of the cargo door, the indicator being detectable from a distance of at least 7.5 m.