A door assembly configured to be positioned between a first compartment and a second compartment that includes a main door portion having a first decompression opening defined therein, at least a first panel portion positioned in a first position within the first decompression opening, and a decompression sensor. The first panel portion is movable linearly between the first position and a second position and is pivotable between the second position and a third position. In the third position the first compartment is in fluid communication with the second compartment via the first decompression opening.

An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.

A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.

An electro-mechanical unlocking device that includes a locking state, a holding state and an unlocking state. The unlocking device includes an arming solenoid and a holding solenoid. In the locking state the arming solenoid moves an arming assembly, which moves a crank and which moves a holding armature from a second position to a first position. In the holding state the holding solenoid is energized and the arming solenoid is de-energizing, which allows the arming armature to moves from the first position to the second position. In the unlocking state the holding solenoid is de-energized, which allows the holding armature and the arming link to move from the first position to the second position. In the locking and holding states a sear blocks the path of the striker and in the unlocking state the sear does not block the path of the striker.

An environmental control system for use in an aircraft includes at least one component positioned along a length of the aircraft and a decompression panel assembly comprising an array of apertures. The array of apertures is based on a location of the decompression panel assembly along the length of the aircraft relative to the at least one component.

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.

A fabric barrier for an aircraft compartmental barrier includes a fabric barrier portion and a flexible crosspiece, wherein at least part of one edge of the fabric barrier portion terminates at the flexible crosspiece, wherein the flexible crosspiece is adapted to fit into and be retained within a partially covered groove, wherein the partially covered groove includes a pair of opposing flange portions covering a groove whereby a central longitudinal portion of the groove remains uncovered, wherein the flexible crosspiece is adapted to be released from the partially covered groove by passing between the pair of opposing flange portions during a decompression event. A decompression system for an aircraft compartmental barrier includes said fabric barrier, and a method for isolating two internal volumes within an aircraft using said decompression system.

A latch assembly for a decompression panel in an aircraft includes a base and a swing arm hinged to the base and pivotable relative to the base about a hinge axis between a latched position and an unlatched position. A load pin fixed to the swing arm has a pin axis a fixed distance from the hinge axis. A spring secured to the base is positioned to exert a spring force against the swing arm when the swing arm pivots from the latched position to the unlatched position. A bracket securable to the decompression panel defines a slot retaining the load pin when the swing arm is in the latched position. The load pin is movable in the slot under relative motion of the bracket and the base with the swing arm in the latched position, and exits the slot when the swing arm pivots to the unlatched position.

An aircraft pressure device includes a connection to ambient having a sensor body mounted to a fuselage of an aircraft. The sensor body includes a sense port. A sense line includes a first end connected to the sense port, a second end defining an opening in the fuselage, and an intermediate portion. A valve is arranged in the intermediate portion, the valve being operable to prevent fluid flow between the first end and the second end.

A shock absorber includes a first end configured to be mechanically fastened to a first component, a second end configured to be mechanically fastened to a second component, a main body, a main shaft, and a primary piston. The primary piston configured to move within the main body and further configured to provide a first damping force by movement of a fluid through the primary piston while the main shaft moves a first distance. The shock absorber also includes a deformable solid material arranged in the main body. The primary piston configured to further move within the main body and further configured to provide a second damping force by deforming the deformable solid material after the main shaft moves the first distance.