A locking mechanism for a door panel to be positioned within and out of blocking relationship with an opening. Mechanism includes a deadbolt rotatably connected to the wall and having a curved configuration and a locking bracket connected to the door panel. The locking bracket extends from the door panel in an angular direction with respect to a plane of door panel. With door panel in a closed position and deadbolt in a first position, the locking bracket extends through the curved configuration. Deadbolt is in blocking relationship with the locking bracket in a direction along a plane of the door panel and is not in blocking relationship in a direction along the locking bracket. With door panel in closed position, deadbolt is in a second position not in blocking relationship with the locking bracket permitting door panel to move in a direction along a plane of the door panel.

In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.

Embodiments of the present disclosure provide an entry assist system for an aircraft doorway. The system includes a securement member configured to be secured into at least one aperture of the doorway, a handle portion pivotally attached to the securement member, and a releasable locking feature for locking the handle portion. A mounting device is used for securing the stationary member to an existing aperture in the doorway and for removing the entry assist system when no longer needed. The securement member forms a stationary portion along an inner edge of the doorway. The handle portion includes a hub configured for rotating about an axle that is coupled to an interface of the securement member. The hub and interface interconnect to form the releasable locking feature for locking the handle in a collapsed position adjacent the securement member or in an extended position protruding outside the doorway.

The present disclosure describes a bulkhead assembly for an aircraft interior comprising a pocket door mechanism (48) for supporting and guiding the movement of a pocket door; and a structural member (50) to which the pocket door mechanism is attached. The structural member is attached to a structure of the aircraft and provides support for the pocket door relative to the aircraft structure independently of any decorative member (32, 34) covering the structural member.

Particular embodiments include a mission payload mounting apparatus. The mission payload apparatus includes a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut.

An aircraft including a fuselage with a skin in which is made an opening, the skin delimiting the interior and the exterior of the fuselage. A closure panel is mobile between a closed position in which the panel covers the opening and an open position in which the closure panel uncovers the opening. A support including a base is fastened to the fuselage. At least one bar and an articulation between the bar and the base allow the bar to occupy a position retracted inside the fuselage and a deployed position outside the fuselage. The articulation is a pivoting connection.

A door stop element for an aircraft door has a body which is formed at least approximately L-shaped, and which has at least one contact area on the outer side of one of the legs for fixed contact on the aircraft fuselage, and a stop surface on the inner side of the other leg for the aircraft door. The body has a cavity, on the inner side of which adjacent to the stop surface a rib is provided, which extends through the stop surface symmetrically on both sides of the longitudinal median plane that extends perpendicular to the stop surface.

A latch assembly for a decompression panel in an aircraft includes a base and a swing arm hinged to the base and pivotable relative to the base about a hinge axis between a latched position and an unlatched position. A load pin fixed to the swing arm has a pin axis a fixed distance from the hinge axis. A spring secured to the base is positioned to exert a spring force against the swing arm when the swing arm pivots from the latched position to the unlatched position. A bracket securable to the decompression panel defines a slot retaining the load pin when the swing arm is in the latched position. The load pin is movable in the slot under relative motion of the bracket and the base with the swing arm in the latched position, and exits the slot when the swing arm pivots to the unlatched position.

The present disclosure provides an aircraft security door as well as methods, systems and apparatus for handling an aircraft security door. In one implementation, a method for installing an aircraft security door onto an aircraft is disclosed. The method includes transferring the aircraft security door to an aircraft service stair, supporting the aircraft security door by a bridge crane coupled to the aircraft service stair, positioning the aircraft service stair in proximity to a fuselage of the aircraft adjacent to an opening in the fuselage, positioning the aircraft security door relative to the opening using the bridge crane, and securing the aircraft security door to the opening.

The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.