An aircraft door hinge assembly, comprising a door with an outer skin and a frame provided with at least one lug; a fuselage frame provided with at least one clevis configured to be pivotally attached to the lug with a hinge pin so that the door is pivotable relative to the fuselage door frame about a hinge line; a rotatable filler pivotally mounted, at a proximal end, within a gap provided by the clevis; and, a fixed filler having a proximal end fixedly attached to an outermost surface of the lug adjacent to the hinge line, and having a distal end configured to overlap the distal end of the rotatable filler, such that the fixed filler limits rotation of the rotatable filler.

Aircraft pressurized cabin door (1) including an outer panel (2) and a door structure (3). The door structure (3) includes two circumferential beams (4) fastened to the lateral edges of the door (1); a plurality of longitudinal beams (5) arranged substantially perpendicularly between the circumferential beams (4) and fastened to the outer panel (2), each longitudinal beam (5) extending from one circumferential beam (4) to the other. Each longitudinal beam (5) is an open profile of which the opening (18) is directed toward the outer panel (2), this opening (18) being closed by the internal face of the outer panel (2) to which the longitudinal beam (5) is fastened. Each beam includes a structural redundancy element.

A method for aligning a first door and a second door includes steps of: (1) moving the first door and the second door from an opened position toward a closed position; (2) engaging a striker arm with a cam of a follower mechanism; (3) aligning a first mating edge and a second mating edge by moving the cam along a second follower surface of the striker arm; (4) separating the first mating edge from the second mating edge by engaging the cam to an apex of the striker arm; (5) aligning the first mating edge and the second mating edge by moving the cam along a first follower surface of the striker arm; (6) maintaining alignment of the first mating edge and the second mating edge by engaging a convex first rail coupled with a concave second rail; and (7) disengaging the cam from the first follower surface.

A stabilization assembly for a door frame secured to a fuselage skin of an aircraft and positioned about an opening defined in the fuselage skin including a strap, wherein a first end portion of the strap is secured to the fuselage skin with a first fastener which extends through the first end portion of the strap and through at least a portion of the fuselage skin. A second end portion of the strap is coupled to the door frame and a third portion of the strap extends between the first and second end portions of the strap and spaced apart from the fuselage skin.

An evacuation slide may comprise a sliding surface extending from a head end to a toe end of the evacuation slide. An extendable dropdown volume may be configured to increase a height of the sliding surface at the toe end of the evacuation slide. The extendable dropdown volume may be configured to remain in a stowed position at a first sill height and deploy at a second sill height greater than the first sill height.

An aircraft door arrangement includes a door, a door seal, and a door opening. The door opening has an opening edge adjoining the door opening and extending into the aircraft fuselage, at which a seal seat is arranged, which can be brought into flush contact with the door seal. A hollow space, partially covered by the edge region of the door, is formed by the door seal, the seal seat, and the opening edge. A gap (located between the door and the door opening when the aircraft door is closed) is connected with the hollow space. A sound reducing profile is arranged at the opening edge in the hollow space, and it includes a sound reflecting surface oriented oblique with respect to a surface of the door, which is adjacent to the gap. The sound reflecting surface at least partially follows the course of the gap.

Embodiments are directed to systems and methods for a sliding door in a pressurized aircraft. In one embodiment, an aircraft comprises a fuselage having a door opening, and a door configured to slide into the door opening from within the fuselage, the door held in a closed position in the door opening by excess air pressure within the fuselage during operation of the aircraft.

An apparatus comprises a composite sandwich panel, a seal, and a hinge. The composite sandwich panel has a first edge in a first over-crush edge region, wherein a thickness of the composite sandwich panel decreases within the first over-crush edge region in a direction towards the first edge. The seal is bonded to the first over-crush edge region of the composite sandwich panel and extending past the first edge. The hinge is connected to the composite sandwich panel such that an axis of rotation of the hinge is positioned over the first over-crush edge region of the composite sandwich panel.

An emergency escape slide container includes a first portion having a first end wall and a first side wall, the first side wall and the first end wall defining a first storage space that is sized and shaped to receive an emergency escape slide. The first side wall also includes a first rolling mechanism. The emergency escape slide container also includes a second portion having a second end wall and a second side wall, the second side wall and the second end wall defining a second storage space sized and shaped to receive the emergency escape slide. The second side wall also includes a second rolling mechanism. The first portion and the second portion cooperate to define a third storage space therebetween, the third storage space being equal to a combination of the first storage space and the second storage space.

Systems and methods include providing an aircraft with a fuselage, an airframe that provides structural rigidity to the fuselage, and at least one door that allows access to an interior of the fuselage through an opening in the fuselage. The aircraft includes an overlapping, tongue and groove door interface formed between a frame of the door and a portion of the airframe that at least partially borders the opening in the fuselage. At least a portion of the airframe includes a concavity. At least a portion of the door frame includes a complementary shaped profile to the concavity of the airframe. The complementary profile of the door frame and the concavity of the airframe form a seal between the door frame and the airframe when the complementary portion is at least partially received within the concavity by selectively rotating the door to its closed position.