A handle assembly for an access panel is described and includes a handle connected to a support structure integrated into and covered by a skin of the access panel, the handle comprising a grip portion and upper and lower flanges extending perpendicularly from the grip portion and having first ends connected to the grip portion and second ends connected to the support structure; and a cover disposed over an opening in the access panel skin and selectively transitionable between a closed position and an open position, the opening situated relative to the handle such that the handle is concealed when the cover is in a closed position and accessible via the opening when the cover is in an open position.

An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.

A gooseneck hinge assembly includes a first gooseneck hinge portion having a first portion first end coupled to a first surface, a first portion second end having a first portion aperture to receive a pin, and a first gooseneck curve between the first portion first end and the first portion second end. The assembly further includes a second gooseneck hinge portion being a mirror image of the first hinge portion and having a second portion first end coupled to the first surface, a second portion second end having a second portion aperture to receive the pin, and a second gooseneck curve between the second portion first end and the second portion second end. The assembly further includes the pin coupled to a second surface and to extend through the first portion aperture and the second portion aperture to facilitate rotation of the second surface relative to the first surface.

An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.

Apparatuses and methods for aircraft wings, including fuel tank access panel assemblies, are disclosed. For example, an aircraft wing comprises a skin and a load bearing fuel tank access panel assembly fastened to the skin. The skin comprises a fuel tank access panel hole and a first fastener hole. The load bearing fuel tank access panel is configured to bear at least some of a wing bending load and comprises an access panel, a fastener, and a self-locking fastener mating assembly. The access panel comprises a body portion configured to be received in the fuel tank access panel hole, and a lip portion extending over an interior surface of the skin. The lip portion comprises a second fastener hole, and the fastener extends through the first fastener hole and the second fastener hole into the self-locking fastener mating assembly.

Locking hinge apparatus for aircraft doors are disclosed. An example locking hinge apparatus includes a hinge base to couple to a frame of an aircraft. A hinge gooseneck is to pivotally couple a door to the hinge base. The hinge gooseneck is to allow the door to move between a closed position and an open position relative to the frame. A lever is pivotally coupled to the hinge base. The lever is to pivot relative to the hinge base between a first rotational direction and a second rotational direction opposite the first rotational direction. The lever includes a lock to engage a portion of the hinge gooseneck to prevent rotational movement of the door relative to the frame when the door is in the open position. A biasing element is to urge the lever in the first rotational direction.

A latch for coupling of a first component to a second component, the latch having a base body which includes a first bearing, a second bearing and a third bearing, the latch having a lever which is mounted pivotably on the first bearing about a first pivot axis between a locking position and an unlocking position, the latch having a locking which is mounted pivotably on the second bearing and which includes a spring-loaded locking part, which locking part rests on the lever in order to transmit a predetermined braking force to the lever in the locking position of the lever, the latch further including a release lever which is mounted movably on the third bearing between a blocking position for blocking the locking in the locking position and a release position for releasing the locking from the locking position.

An aircraft nacelle is disclosed and includes a first fan cowl and a second fan cowl. An opening is defined in an exterior surface of the first fan cowl. The aircraft nacelle also includes a blade, a latch mechanism, an arm, and a linkage assembly operably connecting the arm to the blade. The blade is moveable along between a stowed position and a deployed position. The latch mechanism is moveable between a latched position an unlatched position where a portion of the latch mechanism obstructs a path of movement of the blade. The arm is unable to move from an extended position where a portion of the arm extends through the opening in the exterior surface of the aircraft nacelle into a retracted position within an interior volume of the aircraft nacelle when the blade is in the deployed position and the latch mechanism is in the unlatched position.

An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.

An aircraft electric door for a pressurized airframe having a locking system for locking a safety catch, a system for moving a door arm, and an electric motor activated by a door computer to actuate both systems. The system for moving the door arm includes a guideway linked to the door arm. The guideway is in a mobile cylindrical support rotated by the electric motor. A fixed guide is fitted in a cylindrical sleeve around the cylindrical support. The fixed guide includes a vertical camway and a horizontal camway. The door arm pivots around a vertical hinge and is linked with door lifting devices. The door lifting devices are mounted between a shaft of the safety catch and the door arm.