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.

Apparatus, systems, and methods for selectively locking and unlocking a passenger door. The apparatus includes a first shaft, having a first longitudinal centerline, and a member, connected to the first shaft. A handle is connected to the first shaft via the member, the handle being movable via rotation of the first shaft from a locked position and an unlocked position. A first protrusion extends from the handle and a latch crank is connected to the second shaft. A second protrusion extends from the latch crank and a linkage is connected between the latch crank and the member. When the handle in the locked position, the first protrusion is positioned adjacent to the second protrusion to prevent rotation of the second shaft. When the handle is in the unlocked position, the first protrusion is positioned away from the second protrusion to enable the second shaft to rotate.

A door unit for an aircraft includes a door which is configured, in a closed position, to cover an opening in the vehicle and to delimit a vehicle interior from a vehicle environment; a pressure compensation flap which is configured, in a sealing position, to cover a pressure compensation opening in the door and, in a pressure compensation position, to at least partially release the pressure compensation opening; a locking element which is configured, in a locking state, to lock the door in the closed position and, in an unlocking state, to unlock the door; and a blocking element which is configured, in the sealing position of the pressure compensation flap, to block a movement of the locking element from the locking state into the unlocking state, wherein the blocking element is arranged on the pressure compensation flap.

An aircraft door translation hinge assembly connects a passenger door of an aircraft to the aircraft fuselage structure and enables the passenger door to move through a desired opening motion. The opening motion of the passenger door is controlled by a simplified mechanism that utilizes a pair of linkages connected by a cam surface follower that engages in sliding engagement with a cam surface. The simplified mechanism controls a pivoting movement of the passenger door as the passenger door is first opened, and then controls a translation movement of the passenger door as the passenger door is continued to be opened from a passenger door opening in the aircraft fuselage.

An aircraft door having: a first handling arm and a first forearm; a second handling arm and a second forearm; a holding device movable between: an immobilising position in which the first forearm and the second forearm are immobilised relative to the door panel; and a released position in which the first forearm and the second forearm are free to pivot relative to the door panel in at least one direction of rotation.

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).

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).

A door (3) of an aircraft (1) equipped with an opening/closing mechanism, the movement which is in a main horizontal plane (P) of the aircraft (1) is controlled by coupling between the door (3) and the frame (4) on a control ramp (7) and on two front (AV) and rear (AR) guides (8,9), arranged between the respective front (AV) and rear (AR), and the frame (4) coupled to at least one handling arm (5, 6) hinged in rotation on a front side (AV) of the frame (4) and to the door (3) via a forearm (5b, 6b).

A door assembly (2) for an aircraft is moveable between a closed position and a disengaged position and comprises a door frame (6), a hinge arm (12) pivotally coupled to the door frame (6), and a door (4). A support bracket (14) pivotally supports the door (4) on the hinge arm (12). The door frame (6) and door (4) each comprise at least one stop (8, 10) configured to engage with each other to retain the door (4) within the door frame (6) in the closed position. At least one pin (18, 20; 38) is mounted on each side of the door (4) and at least first and second guides (28, 30; 40) are coupled to the sides of the door frame (6). Each guide (28, 30; 40) comprises a channel (24, 26; 43) receiving a pin (18, 20; 38).

The invention relates to an opening system (10) for an auxiliary door (20) of an airplane in a fuselage (30), the door and the fuselage having skins in the extension of one another. In one exemplary embodiment, the system (10) includes a framing lintel (11) integrated into the fuselage, an upper beam (2S) of the door structure arranged opposite the lintel (11), and a set of three lever links (4A, 4B, 4C). Each link is connected, on the one hand, to the lintel (11) by a lever articulation (5a, 6a) fixed relative to the fuselage (30) and, on the other hand, to the upper beam (2S) by a lever articulation (5b, 6b) mobile with the door (20), the articulations (5a, 5b; 6a, 6b) being connected respectively to the lintel (11) and to the upper beam (2S) by fittings (41, 43; 42, 44). The set of links includes two types of link mounted alternately, in which the mobile articulation (5b, 6b) remains positioned respectively close to the fuselage skin (30) and further from this skin (30), the articulations (5a, 5b; 6a, 6b) of two adjacent levers (4A, 4B; 4B, 4C) forming an evolving quadrilateral.