A system and method for an overwing exit door is provided. The overwing exit door system comprises a door, a handle connected to an inboard surface of the door, a guide track connected to a body of the aircraft, a roller, a first crank connected to the roller and associated with the handle, a first shaft system attached to the first crank, a latch system connected to the first shaft system, and a locking system associated with the latch system. The latch system comprises a rotating stop, a second crank associated with the rotating stop, and a second shaft system connected to the second crank and the rotating stop. These components together control operation of the overwing exit door between an open position and a closed position.

A system for opening a door of an aircraft includes a connection assembly adapted to connect the door to a fuselage section of the aircraft. The connection assembly includes a main hinge pivotally connected to the fuselage section and a link assembly connecting the door to the main hinge and pivotally connected to the fuselage section, the link assembly including one member slidingly and pivotally connected to the door. The system also includes a latch mechanism between the door and the main hinge, the latch mechanism being adapted to be actuated. The system is adapted to move the door upwardly and inwardly along a predetermined path without moving the main hinge through movement of the latch mechanism and, subsequently, to pivot the door around a virtual pivot point located outside of the aircraft by moving the main hinge once the door has reached an end of the predetermined path.

An aircraft emergency exit door (10) with opening mechanisms integrated by a grouping of the mechanisms into a door beam (3) located on a given side of a window (16) of standard dimensions. In the beam, an inner handle (1) is mounted on a main shaft (102) connected with a locking shaft (8A) on which there is mounted, against return springs (83), a door blocking/locking mechanism (8) comprising a lock (81). A mechanism for conditionally opening the door (100) includes a vent flap (110), a pivot connection (12) for coupling the flap (110) to the inner handle (1), and a blocking shaft (120) that has, at each end, a pressure lever (121) equipped with supports for blocking (122) and unblocking (123) the flap (110). Return springs (32) mounted against the conditional opening mechanism (100) are calibrated to allow the opening of the flap (110) by exerting reduced pressure in residual pressure variation conditions, and to prevent it from opening in overpressure conditions.

A plug door assembly for a pressurized aircraft is provided. The door assembly includes a surround and a door, and connector assemblies along the edges that act to transfer in-plane stresses directly across the fuselage opening via the door, as well as stops that react radial loads generated by cabin pressure. The door assembly obviates the need for a separate frame to transmit stresses around the perimeter of the fuselage opening.

The invention proposes a simple system, with small space requirement, without hinge arms or sealing skirt, while providing secure and effective opening. To achieve this, the invention provides a door opening by a lateral guidance defining an integrated doubling-back kinematics, towards the interior then the exterior of the fuselage. An opening system of an emergency door (1) is positioned in an aircraft fuselage (2), the door and the fuselage comprising respective frameworks (11, 21) extending opposite each other. According to the invention, the system comprises a control handle (5) for rotating, combined with a bolt/latch pair, and an opening mechanism (30) equipped, in the upper corner areas (Zs) of the door (1), with a pivoting lever (6) hinged on an upper edge of the fuselage (2) and provided with guide tracks interacting with the bulk/latch pair and with a door attachment fitting (12), upper and lower rollers mounted in the lateral framework of the door (11c) in connection with the guide tracks (20s, 20i) mounted in the opposing fuselage framework (21c), the upper guide tracks (20s) being inclined rising towards the interior of the cabin (I) and the lower guide tracks (20i) being curved.

An articulated hinge assembly for connecting a door to a fuselage of an aircraft includes an articulated hinge arm having a first hinge member pivotably coupled to a second hinge member at an elbow. A fuselage fitting is pivotably coupled to a fuselage bracket and a door fitting is pivotably coupled to a door bracket of the door. The articulated hinge arm is movable from a collapsed position to an expanded position to move the door from a door closed position to a door open position. The articulated hinge assembly includes a linkage assembly coupled to the articulated hinge arm, the fuselage fitting and the door fitting controlling movement of the first hinge member and the second hinge member relative to each other and relative to the fuselage fitting. The linkage assembly controls positioning of the door.

An aircraft door including a retaining device for a deployable evacuation device, the retaining device having at least: a beam; a first retention member fixed on a second end of the beam by a detachable clip, the first retention member being connected to the deployable evacuation device; a second retention member, which can be coupled to the first retention member, mounted on the door frame; retraction devices that moves between: an activated position, in which the second retention member is on the trajectory of the first retention member, and a deactivated position, in which the second retention member is outside the trajectory of the first retention member.

An internal cabin of a vehicle includes a vehicle control area. A first door is coupled to the vehicle control area. The first door is moveable between a first open position and a first closed position. An aisle extends between the vehicle control area and a passenger seating area. A forward section of the aisle is disposed between a first monument and a second monument. A second door is disposed within the aisle between the first monument and the second monument. The second door is moveable between a second open position and a second closed position. A privacy vestibule is defined between the second door in the second closed position, the first monument, the second monument, and the vehicle control area.

An actuating system for an actuatable door and to an actuatable door having such an actuating system are provided. The actuating system comprises first and second rotatable latching shafts, a coupling link, first and second pivotable mechanical transmission elements that are mounted onto first and second rotatable latching shafts, respectively, and first and second latching members. First and second latching members are non-rotatably mounted to the second rotatable latching shaft and adapted for latching the actuatable door in a closed position. A first rotation of the first rotatable latching shaft results in pivoting of the first and second mechanical transmission elements and a second rotation of the second rotatable latching shaft, which causes a third rotation of first and second latching members.

Counterbalance assemblies include a torsion bar spring for counter-balancing the weight of upwardly opening aircraft doors for ease of opening and closing. The torsion bar spring may be linked to the aircraft door through an integrated gear reduction system comprised of two pairs of spur gears and respective shafts as well as a linkage assembly. A cable reel is connected to the output shaft and the input shaft is connected to a four bar linkage system attached to the end of the torsion bar. The cable reel stores the lift cable and provides the output torque to lift the aircraft door. When the aircraft door opens or closes, the center of mass loses or gains height respectively, causing a variation of gravitational potential energy. In such a manner, the gravitational potential energy is exchanged with strain elastic energy from the counter-balance spring therefore reducing the required external source of energy whether it is from a power assisted means or manual operation.