Abstract: A hinge assembly for connecting a door to a fuselage of an aircraft includes a hinge arm having a fuselage fitting pivotably coupled to a fuselage rotatable interface and a door fitting pivotably coupled to a door rotatable interface. The hinge assembly includes a programmable gear assembly coupled to the hinge arm allowing the hinge arm to pivot around the fuselage fitting when the door is moved from a door closed position to a door open position and causing the door to maintain in a generally parallel orientation relative to the fuselage between the door closed position to the door open position. The programmable gear assembly includes a fuselage gear coupled to the fuselage fitting, a door gear coupled to the door fitting, and a rack operably coupled between the fuselage gear and the door gear.

Abstract: A stop fitting assembly for an aircraft door is presented. The stop fitting assembly comprises a stop fitting, a connecting bracket, and a number of removable fasteners. The stop fitting has a shaft, a flange extending outward from the shaft, and a number of holes extending through the shaft. The connecting bracket has a stop fitting receptacle configured to receive the shaft of the stop fitting, a number of holes extending through walls of the stop fitting receptacle, the connecting bracket configured to be joined to structural members of the aircraft door. The number of removable fasteners is configured to pass through the number of holes in the stop fitting and the number of holes of the stop fitting receptacle to removably join the stop fitting and the connecting bracket.

Abstract: A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.

Abstract: Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Abstract: Offset drive arm actuation of inboard flaps is disclosed. A disclosed example apparatus includes an inboard flap support for moving an inboard flap. The inboard flap support includes an offset drive arm extending between a first attachment point of the inboard flap and a first pivot of a support, and a linkage extending between a second attachment point of the inboard flap positioned at a different position from the first attachment point and a second pivot of the support.

Abstract: A stop fitting assembly for an aircraft door is presented. The stop fitting assembly comprises a stop fitting, a connecting bracket, and a number of removable fasteners. The stop fitting has a shaft, a flange extending outward from the shaft, and a number of holes extending through the shaft. The connecting bracket has a stop fitting receptacle configured to receive the shaft of the stop fitting, a number of holes extending through walls of the stop fitting receptacle, the connecting bracket configured to be joined to structural members of the aircraft door. The number of removable fasteners is configured to pass through the number of holes in the stop fitting and the number of holes of the stop fitting receptacle to removably join the stop fitting and the connecting bracket.

Abstract: A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.

Abstract: Offset drive arm actuation of inboard flaps is disclosed. A disclosed example apparatus includes an inboard flap support for moving an inboard flap. The inboard flap support includes an offset drive arm extending between a first attachment point of the inboard flap and a first pivot of a support, and a linkage extending between a second attachment point of the inboard flap positioned at a different position from the first attachment point and a second pivot of the support.

Abstract: Example high-fowler flap actuation apparatus and related methods are disclosed. An example apparatus includes a control surface operatively coupled to a wing of an aircraft via a first support arm and a drive arm, the drive arm linearly extendible from a retracted position to a deployed position, the deployed position including the control surface extended away from the wing at a first angle with respect to the wing.

Abstract: Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Abstract: Example high-fowler flap actuation apparatus and related methods are disclosed. An example apparatus includes a control surface operatively coupled to a wing of an aircraft via a first support arm and a drive arm, the drive arm linearly extendible from a retracted position to a deployed position, the deployed position including the control surface extended away from the wing at a first angle with respect to the wing.

Abstract: A hinge assembly for attaching a door structure to an aircraft fuselage is provided. The door structure is linked to the aircraft body structure by way of a programmable mechanical linkage that is attached to the hinge member. The programmable mechanical linkage is actuated along the hinge member so as to maintain the door structure attached thereto in a controlled angular relationship relative to the longitudinal axis of the aircraft fuselage through its attachment to the fixed aircraft frame.