An airframe for a tiltrotor aircraft includes a wing airframe including a rib, a fuselage airframe including a fore-aft overhead beam and a cradle support assembly. The cradle support assembly includes a forward wing support coupled to the fore-aft overhead beam and the wing airframe and an aft wing support coupled to the fore-aft overhead beam and the wing airframe. The rib, the fore-aft overhead beam, the forward wing support and the aft wing support are substantially aligned to form a wing-fuselage integrated airframe beam assembly to support the wing airframe.

One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.

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 lock for an aircraft door. The lock includes an outer shell having an inner cavity. A core is rotatably mounted within the inner cavity to rotate about an axis of the core. The core has a keyhole extending through the core from a first end of the core for receiving a key therein, to an opposed second end of the core. The keyhole defines an air leakage path through the core. A cam has a cam arm mounted about the core and is rotatable therewith. The second end of the core protrudes from the cam. A cover is attached to the second end of the core. The cover blocks the keyhole at the second end of the core and obstructing the air leakage path. An aircraft door, methods, and a retrofit kit are also disclosed.

A hinge apparatus can include a frame component of an aircraft interior component; a door component coupled to an aircraft door assembly; and a hinge assembly coupled to the frame component and the door component. The hinge assembly can be operable between an open configuration, an intermediate configuration, and a closed configuration. The hinge assembly may include a first hinge body, and a second hinge body coupled to the door component, the second hinge body pivotably moving the door component about a first pivot point when the hinge assembly moves from the closed configuration to the intermediate configuration, and the second hinge body moving the door component about a second pivot point that is different from the first pivot point when the hinge assembly moves from the intermediate configuration to the open configuration. Related methods are also provided.

Embodiments of the present disclosure relate generally to the use of the fuel cell systems on board aircraft and other passenger transportation vehicles and to methods of using heat, air, and water generated by such fuel cell systems. The heat may be used to address condensation within the aircraft. The heat may be used to help evaporate excess water that would otherwise condense in the aircraft skin. The excess water collected may be used to create humidification for cabin air. In other examples, the heat, warmed air, or warmed water may be delivered to other locations or heating systems for beneficial use.

A door locking system for a door module that separates compartments in an aircraft. Door locking system has locking element that is adapted to maintain door panel of door module in a closed position. Door locking system further includes first and second mechanisms that are adapted to release door panel from the closed position in a normal and an abnormal mode, respectively. Second mechanism is spatially segregated from and operates independently of first mechanism. Second mechanism includes locking element release actuator, pressure sensor, and controller that directs locking element release actuator to act on locking element when pressure sensor detects a difference in pressure between the compartments that exceeds a predetermined threshold.

Air stair support systems, stair support cable assemblies, and hooks are disclosed herein. A stair support system includes, but is not limited to, an aircraft fuselage, a door seal, a stair door, and a stair support cable assembly. The aircraft fuselage defines a door frame and a stair hook receptacle. The stair door has a retracted position within the door frame and an extended position that forms an entry/exit stairway. The stair support cable assembly includes a cable and two hooks. The first hook includes a curved end portion configured to hook onto the stair hook receptacle, a cable end portion secured to the cable, and an intermediate portion having first and second intermediate legs that extend the intermediate portion away from the door seal when installed on the door frame and the stair door. The second hook is configured to hook on the stair door.

A tunable stay device for an aircraft closure has a mounting base that is mountable to the closure or in an area of the aircraft in close proximity to the closure. The mounting base extends, at least in part, along a mounting axis. A holding element is mounted for movement along the mounting axis and configured to effect, at least in part, a hold force. An adjuster is mounted to at least one of the mounting base and the holding element and is configured and arranged to effect a change in position of the holding element with respect to the mounting base along the mounting axis. When the stay device is mounted to the closure or in the area of the aircraft in proximity to the closure, the hold force biases the closure in one of an open orientation and a closed orientation.

A door alignment system includes a first alignment member secured to one of a first door or a structure connected to the first door, and a second alignment member secured to the other of the first door or the structure. The first alignment member is configured to couple to the second alignment member when the first door is in a closed position relative to the structure in order to prevent the first door from binding in relation to the structure. The first alignment member is configured to be separated from the second alignment member when the first door is in an open position relative to the structure.