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.

Systems for latching and locking an aircraft door and associated methods are disclosed. The system comprises a latch and a lock. The latch can be configurable between: a latched configuration where the latch interferes with a lift mechanism for causing lifting of the aircraft door to permit opening of the aircraft door; and an unlatched configuration where the lift mechanism is permitted to cause lifting of the aircraft door. The lock can be configurable between: a locked configuration where a configuration change of the latch from the latched configuration to the unlatched configuration is prevented; and an unlocked configuration where the configuration change of the latch from the latched configuration to the unlatched configuration is permitted.

Systems and methods for operating an aircraft door including an airstair are disclosed. In one embodiment, the system comprises a hinge configured to pivotally couple a lower portion of the door to a fuselage of an aircraft, a lift mechanism and an interlock. The lift mechanism causes a movement of the door relative to the hinge between a lowered position and a lifted position. The interlock is configurable between: a locked configuration where the movement of the door relative to the hinge is prevented; and an unlocked configuration where the movement of the door relative to the hinge is permitted.

A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

An actuatable emergency exit door with a door actuating device that comprises at least two connection rods that are pivotally mountable to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the at least two connection rods being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein at least one door-mounted goose neck-shaped structure is mountable to the associated structural frame for enabling an initial translational opening movement and subsequently a swiveling opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening. The invention is further related to an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door.

There is disclosed an emergency door positionable in an exit opening of an aircraft. The door has door supports mountable to the lower wall and each having a pivot point. A first pivot axis is defined between the pivot points. A block is mountable to the lower wall and is offset from a center of the lower wall. A door body is mountable within the opening to the door supporting structure and pivotally mountable to the door supports. The door body is pivotable about the first pivot axis from an initial position in which the door body is within the opening, until the door body is disengaged from the door supports. A bottom portion of the door body abuts against the block to define a removal pivot point. The door body is pivotable about the removal pivot point to remove the door body from the exit opening.

An aircraft that includes a body that defines a cabin interior and a longitudinal axis, and a front row positioned in the cabin interior. The front row includes a first front seat and a second front seat. The first and second front seats are angled away from one another. The first front seat is angled outwardly such that it forms a first acute angle with the longitudinal axis and the second front seat is angled outwardly such that it forms a second acute angle with the longitudinal axis. The first and second acute angles are approximately the same.

An aircraft that includes a body that defines a cabin interior, front and back rows of seats positioned in the passenger zone, a forward door that is pivotable between a closed position and an open position, and an aft door that is pivotable between a closed position and an open position. The cabin interior includes a pilot zone, a passenger zone positioned aft of the pilot zone, and a cargo zone positioned aft of the passenger zone. The pilot zone and the front row of seats are accessible and the back row and cargo zone are inaccessible from an exterior of the body when the aft door is in the closed position and the forward door is in the open position. The back row and cargo zone are accessible and the pilot zone and the front row of seats are inaccessible from the exterior of the body when the aft door is in the open position and the forward door is in the closed position.

In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

An aircraft door arrangement, comprising a door pivotable between closed and open positions, a frame section in a door opening region, and an articulation arrangement connecting the door and frame section. First and second arms are mounted on the frame section, rotatable about first and second axes, respectively. Third and fourth arms are mounted on the door, rotatable about third and fourth axes, respectively. The second arm, at a first position, is rotatably coupled to the fourth arm about a fifth axis, and at a second position, closer to the second axis, is rotatably coupled to the third arm about a sixth axis. The third arm, at a third position, is rotatably coupled to the first arm about a seventh axis, and at a fourth position, closer to the third axis, is rotatably coupled to the second arm about the sixth axis. All axes are oriented substantially parallel.