Abstract: An aircraft door including an external opening/closing lever (7) and an internal opening/closing lever (9) which are coupled by an engaging mechanism (12) which includes: a stop (24) which entrains a counter-stop (23) when the internal opening/closing lever (9) is in its closed position and the external opening/closing lever (7) is pivoted from its closed position to its open position; a lug (22) that rotates as one with the internal opening/closing lever; an engaging pawl (15) which is spaced apart from the path of the lug (22) in a passive position, and disposed on the path of the lug (22) in an active position; a support base (16) designed to push the engaging pawl (15) back into its passive position when the external opening/closing lever (7) is in its closed position.

Abstract: 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).

Abstract: Aircraft door (1) including a safety latch (7) having a first locking element (8) and a complementary second locking element (9) which is movable; a link (11) having at least one electroactive polymer portion (13) and adapted to take up: a lock position in which the electroactive polymer portion (13) is supplied with power and the movable second locking element (9) is engaged with the first locking element (8); and an unlock position in which the electroactive polymer portion (13) is not supplied with power and the movable second locking element (9) is kept away from the first locking element (8); a control unit (16) having a power supply (26) for the electroactive polymer portion (13).

Abstract: An aircraft door including a retaining device for a deployable evacuation device (6), the retain9ng device having at least: a beam (8); a first retention member (10) fixed on a second end (11) of the beam (8) by a detachable clip (16, 17), the first retention member (10) being connected to the deployable evacuation device (6); a second retention member (12), which can be coupled to the first retention member (10), mounted on the door frame (3); retraction devices (22, 23, 25) that can move between: an activated position, in which the second retention member (12) is on the trajectory of the first retention member (10), and a deactivated position, in which the second retention member (12) is outside the trajectory of the first retention member (10).

Abstract: Aircraft door including a support arm (10) connecting a door leaf (5) and a door frame (13), the locking/unlocking mechanism of which includes: a control shaft (17) extending along a substantially vertical axis; a guide track (29); an actuating finger (32) attached to the support arm (10); the locking/unlocking mechanism having: an actuating configuration in which the actuating finger (32) is inserted into the guide track (29), the rotation of the control shaft (17) causing the actuating finger (32) to move along the guide track (29); a release configuration in which the actuating finger (32) is outside the guide track (29).

Abstract: An aircraft pressurized cabin door (1) having an outer panel (2) and a door structure (3) including: two circumferential beams (4) fastened to the lateral edges of the door; a plurality of longitudinal beams (5a, 5b) which are arranged substantially perpendicularly between the circumferential beams (4) and are fastened to the outer panel (2), each longitudinal beam (5a, 5b) extending from one circumferential beam (4) to the other. At least one longitudinal beam (5b) is a beam that has a variable cross-section which increases from the ends (B, M) of the beam to the center (H, L) of the beam, with two bent support bars.

Abstract: An emergency exit door (2) for an aircraft cabin, the door includes an opening-assist mechanism and an opening/closing device having a control lever (7), which can selectively be actuated to either unlock the door (2) and permit the action of the door (2) opening assist mechanism or to lock the door (2). The control lever (7) includes an adaptation mechanism (10) for adjusting the lever arm, the adaptation mechanism (10) being moveable between at least two positions: an opening-action position and a closing-action position, the lever arm (LO) of the control lever (7) in the opening-action position being shorter than the lever arm (LF1, LF2) of the control lever (7) in the closing-action position.

Abstract: 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.

Abstract: An assembly for arming/disarming a slide of an airplane door according to the invention comprises a system with two releasable connection mechanisms (2) linked with the door (1) and a cabin floor of the airplane, each mechanism (2) comprising a releasable connector (21b) secured to the door (1), extending at right angles to the floor on each side of a door bottom, and an anchor fitting (22b) fixed to the cabin floor. Each connector (21b) is equipped with an elastic centering element (70) and a locking/unlocking grab (25b) on the corresponding anchor fitting (22b), the connectors (21b) being linked by a girt bar (5). Each grab (25b) being rotationally mobile, one of the grabs (25b) is driven by a single command (5; 25b) which drives the other grab in rotation via the girt bar (5).

Abstract: 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).

Abstract: The invention concerns an aircraft door having a lever (3) for emergency opening from outside, disposed in a lever window. The lever (3) for emergency opening from outside includes: a main arm (7) having a first aerodynamic surface (9); a profiled cowling (8) with a second aerodynamic surface (10); a driving stop (18) capable of rotating the profiled cowling (8) from its concealing position to its separated position when the main arm (7) passes from its retracted position to its deployed position.

Abstract: 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).

Abstract: An emergency opening device of an aircraft door including a tubular actuating member (2); a resilient compression device; a retaining member for retaining the tubular actuating member (2), having a retaining wire (12) which, when the tubular actuating member (2) is in the retracted position, is held taut between a first attachment (14, 17) and a second attachment (16, 18); a release device which includes a cutting member (22) for transversely cutting the retaining wire (12).

Abstract: Method and device for manufacturing a profile member of composite material, the cross-section of which has three branches, including the steps of: —moving together two opposite edges of a panel (2) of sheet material in such a manner that these two opposite edges are juxtapositioned in one juxtapositioning direction; translating a pair of jaws (20) in a direction perpendicular to the juxta-positioning direction in such a manner that the pair of jaws (20) is positioned on either side of the opposite juxtapositioned edges, this translational movement of the pair of jaws (20) being carried out in the direction of a base (25); —simultaneously pressing the sheet material between the two jaws (20), on the one hand, and between the jaws (20) and the base (25), on the other hand; —finishing the profile member of composite material by hardening with a matrix with which the sheet material is impregnated.

Abstract: An aircraft pressurized cabin door (1) having a fuselage panel (2) and a door structure (3) that includes: two circumferential beams (4) arranged on the lateral edges of the door (1); a plurality of longitudinal beams (5). Each longitudinal beam (5) is an open profile having an outer face to which the fuselage panel (2) is fixed and an inner face, the door structure (3) further including an internal force-absorbing frame (12) fixed to the inner face of each longitudinal beam (5), this internal force-absorbing frame (12) having a plurality of uprights (13) each extending opposite a circumferential beam (4), each upright (13) being fixed to several longitudinal beams (5).

Abstract: Aircraft door (1) having an inside door opening lever (6) coupled to a vent flap (5) by a conditional opening mechanism having two modes and including a flap stop (20) to cooperate with a stop surface (21). The stop (20) has a first trajectory, the stop surface (21) being arranged outside this first trajectory of the flap stop (20). The stop (20) has a second trajectory, the stop surface (21) being arranged on this second trajectory of the flap stop (20).

Abstract: An emergency opening device (1) for an aircraft door having: a tubular operating member (2); elastic compression device (3). The operating member (2) includes a first end element (10) and a second end element (11) that can move in translation with respect to one another. The first end element (10) having a cylindrical retractable rotary stop (20), that can move between a first angular position of transmission and a second angular position of release.

Abstract: An emergency opening device (1) for an aircraft door having: a tubular operating member (2); elastic compression device (3). The operating member (2) has a first end element (10) and a second end element (11) that can move in translation with respect to one another. The first end element (10) includes a removable driving stop (20).

Abstract: 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).

Abstract: 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.