A rapidly disassembled hinge suitable for use in an aircraft includes a first attachment plate attached to a supported structure, a second attachment plate attached to a supporting structure, and a pin with a notch in an outer surface thereof, which is insertable into portions of the first and second attachment plates for pivotably connecting the first and second attachment plates together. The pin is inserted so that the notch is positioned within the second attachment structure when the hinge is in an assembled state. A key includes a main body and a distal end extending from the main body, the distal end being insertable within the notch of the pin. The key is movable such that the distal end of the key can be inserted into and removed from engagement with the notch of the pin to provide for toolless disassembly of the hinge.

The invention relates to an aircraft door having a support arm (6) connected to a support forearm (9) by a first pivot connection (7) about a first pivot axis (8), the support forearm (9) being connected to the leaf (5) by a second pivot connection (10) about a second pivot axis (11) parallel to the first pivot axis (8). The support arm (6) is connected to the door frame (4) by two hinges (13, 14) each having a pivot (26, 27) for rotating the support arm (6) about a third pivot axis (12) which is parallel to the first pivot axis (8) and to the second pivot axis (11), this pivot (26, 27) being connected to the door frame (4) by an attachment (22, 23) that is translatably adjustable in two directions (35, 37, 43, 47) orthogonal to one another and orthogonal to the third pivot axis (12).

A handle assembly for an aircraft door includes a shaft to open the door, an exterior handle deployable between a stowed position and a deployed position, and a clutch having a driving member coupled to the exterior handle and a driven member coupled to the shaft. The clutch is configurable between a disengaged configuration in which the driving member and the driven member are disengaged, and an engaged configuration in which the driving member and the driven member are engaged so that actuation of the exterior handle rotates the shaft to open the door. Rotation of the exterior handle between the stowed position and the deployed position drives an axial movement of the driving member toward the driven member to configure the clutch to the engaged configuration.

Aircraft door (1) including an opening (4), a frame (3), a hinge structure (5) and a circular translation guide device designed to maintain the orientation of the opening (4) during the opening or closing thereof. The hinge structure (5) is connected to the opening (4) by a lifting arm (8) allowing a lifting movement of the opening (4) relative to the hinge structure (5). The circular translation guide device includes a single link (11) connected to the frame (3) by one of the ends thereof and by the other of the ends thereof to a lever (13) which is attached to the hinge structure (5).

Systems and methods include providing an aircraft with a fuselage having a sliding door system disposed on at least one side of the fuselage. The sliding door system includes a forward sliding door having an upper slide rail and a lower slide rail, a rearward sliding door having an upper slide rail and a lower slide rail, an upper rail coupled to each of the upper slide rail of the forward sliding door and the upper slide rail of the rearward sliding door, a lower rail coupled to each of the lower slide rail of the forward sliding door and the lower slide rail of the rearward sliding door, and a plurality of actuators coupled to each of the upper rail and the lower rail and configured to displace and retract the forward sliding door and the rearward sliding door linearly with respect to the fuselage.

A door roller includes a carriage member comprising a plurality of bores, and a plurality of roller assemblies connected to the carriage member, each roller assembly of the plurality of roller assemblies including a pivot bearing rotatably disposed within a bore of the plurality of bores and a pair of rollers coupled to the pivot bearing. Each wheel assembly is configured to pivot relative to the carriage member.

A latch assembly is provided that includes a latch arm having a rotational axis and an engagement surface on a distal end of the latch arm a length from the rotational axis. The engagement surface is stowed in a stowed state of the latch arm. The latch arm is configured to receive a pushing force to depress the latch arm a predetermined distance along the rotational axis. The latch assembly also includes a turret assembly having a top end with the latch arm mounted thereon. The turret assembly is configured to, in response to the pushing force being applied to the latch arm, raise and rotate the latch arm about the rotational axis to thereby transition the latch arm from the stowed state to a deployed state in which the engagement surface is exposed.

An aircraft fuselage end cargo door mechanism including a hinge rotatably coupling an aircraft fuselage end cargo door to a fuselage. The hinge being coupled to both the aircraft fuselage end cargo door and the fuselage so that an entirety of an axis of rotation of the aircraft fuselage end cargo door, defined by the hinge, relative to the fuselage is located forward of an entirety of a major joint line between the aircraft fuselage end cargo door and the fuselage. An uppermost portion of the major joint line comprises a joint line radius where a portion of the joint line radius formed by the aircraft fuselage end cargo door pivots within another portion of the joint line radius formed by the fuselage.

A pneumatic release system has an inlet arranged to be connected, in use, to a supply of pressurised fluid, and an outlet arranged, to be connected, in use, to an end device. The system defines therethrough, a flow path for fluid from the inlet to the outlet. The system includes a piston mounted in and axially moveable relative to a cylinder, the inlet and outlet defined in the cylinder. The piston has a piston end on which are mounted upper and lower seals and is biased to a first closed position, in which the upper and lower seals define a chamber within the cylinder to retain pressurised fluid from the inlet, the upper seals preventing flow of the fluid from the chamber to the outlet, and wherein an external force applied to the piston moves the upper seals away from sealing engagement with the cylinder.

A track door system for an aircraft includes a door having a first side and a second side opposite the first side. A first roller track and a second roller track are aligned adjacent one another on the first side of the door. A third roller track and a fourth roller track are aligned adjacent one another on the second side of the door. A first motion driver is configured to move the door along the first roller track and the second roller track. A second motion driver is configured to move the door along the third roller track and the fourth roller track. A drive unit is operatively coupled to the first motion driver and the second motion driver to provide electromechanical power for cooperatively moving the door forward to an open position or aft to a closed position.