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 aircraft-fuselage structure with an external skin and reinforcement structure, supporting the external skin and includes transverse reinforcement elements and longitudinal reinforcement elements. A door opening is in the external skin, between two transverse reinforcement elements and between two longitudinal reinforcement elements, and a door arrangement is installed therein, the door arrangement having a door frame fastened in the door opening and a door panel fastened on the door frame. The door frame and/or the door panel have/has an outer surface directed towards the surroundings and having a curvature differing from curvature of the external skin adjacent to the door opening, and an adapter arrangement is on the outer surface of the door frame and/or of the door panel and, on a side directed towards the surroundings, has at least one surface element which steadily continues the curvature of the external skin adjacent to the door opening.

A door structure and method of assembling same. The door structure includes a door frame delimiting a door opening. The door frame has a latch housing portion defining a latch housing cavity extending along a length of the door frame. A door is mounted to the door frame and displaceable between an open position and a closed position. The door has a peripheral portion with an outer wall and an inner wall delimiting a cavity of the peripheral portion. A door latch assembly has a first latch member fixedly mounted to the door, and a door manipulator mounted to one of the door and the fuselage and coupled to a second latch member within the latch housing cavity of the door frame. The door manipulator is configured to be manipulated to displace the second latch member to engage and disengage the first latch member.

In order to allow robust assembly in an aircraft between a structural element and a self-stiffened panel comprising a skin and a stiffening structure formed of a network of ribs extending out from a first face of the skin, the structural element comprises at least one end formed of a first closure rib, the stiffening structure comprises at least one end formed of a second closure rib, and a portion the height of which increases progressively as far as the second closure rib, and the structural element being fixed to the self-stiffened panel via first through-fixing elements which fix the first closure rib to the second closure rib. The structural element comprises a sole exhibiting a second face having an inset delimiting a space which accepts an end part of the skin.

A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door assembly also includes a privacy door rotatably coupleable to the first post via a set of hinges, where the privacy door comprises a decompression latch arranged to engage the latch recess when the privacy door is in a closed position within the door frame, and where the decompression latch is configured to disengage from the latch recess in response to a decompression detected on a forward side of the privacy door.

A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door assembly also includes a privacy door rotatably coupleable to the first post via a set of hinges, where the privacy door comprises a decompression latch arranged to engage the latch recess when the privacy door is in a closed position within the door frame, and where the decompression latch is configured to disengage from the latch recess in response to a decompression detected on a forward side of the privacy door.

An aircraft (10) includes a fuselage (12) delimiting a cockpit (14), a passenger entry area (18) and a passenger cabin (16) configured to accommodate passengers during a flight phase. The entry area (18) is interposed longitudinally between the cockpit (14) and the cabin. The cockpit and the entry area are delimited by a front separating element (24) and the entry area and the cabin are delimited by a rear separating element (26). The fuselage delimits a side boarding door (20). A transverse median plane (66) of the boarding door is placed at a distance from the front separating element, considered along the longitudinal axis, greater than 39% of the length between the front separating element and the rear separating element, considered along the longitudinal axis.

A hinge assembly that includes a frame adapter having a curved inner surface with a front portion and a rear portion, a door adapter having a curved outer surface with a front portion and a rear portion, at least one front hinge strip that is secured along a front hinge strip path, and at least one rear hinge strip that is secured along a rear hinge strip path. The front hinge strip path extends from the front portion of the curved outer surface of the door adapter to the rear portion of the curved inner surface of the frame adapter. The rear hinge strip path extends from the rear portion of the curved outer surface of the door adapter to the front portion of the curved inner surface of the frame adapter. The curved outer surface of the door adapter opposes the curved inner surface of the frame adapter and the door adapter is movable relative to the frame adapter between a front open position, a closed position and a rear open position.

A mechanical state indicator system concealed within an enclosure includes a light source for providing light and multiple light paths coupled to the light source for directing the light. Each of the light paths includes a gap configured to receive a mechanical state indicator rigidly coupled to a mechanism. Movement of the mechanism between a first state and a second state moves the mechanical state indicator into and out of the gap. Readouts are coupled to each of the light paths for displaying an indication of mechanical state based on a position of a respective mechanical state indicator. The readouts are co-located for collective viewing.

A rotary wing aircraft with a fuselage that is equipped with at least one rail, comprising at least one sliding element, in particular a sliding door or a sliding window, that is slidably supported by the at least one rail, wherein the at least one sliding element is at least slidable along the at least one rail by means of an opening sliding movement into an opening movement direction from a fully closed position into a fully opened position, wherein a dampening unit is provided that dampens the opening sliding movement of the at least one sliding element upon reaching of the fully opened position.