Aircraft Door Hinge Mechanism

A passenger door is connected to an aircraft fuselage by a hinge mechanism having an elongated goose neck hinge member.

Aircraft door hinge mechanism.

The latch lock mechanism 20 of this invention includes a latch shaft 38 that is mounted to the door 22 by a set of follower bearings 98 that are axially offset from the shaft. Nexged components and features. The door is attached to the hinge fitting 28 by way of a. The electrical door is also lighter and less costly than traditional mechanical doors.

Finally its architecture makes it highly customizable to answer any aircraft needs. Aircraft door of the type which during the flight is pressed all around against the door case under influence of the cabin pressure. One end of the hinge member is pivotally connected to an idler crank arm that is pivotally connected to the fuselage. A guide arm connected to the door and carried by the idler crank arm controls door.

A latch lock mechanism 20 for opening and closing a translating motion type aircraft door 22. The door you mentioned is called a plug door. The other end of the goose neck member is pivotally connected to the door. The shaft 38 is rotated by a lift lock mechanism 44 that includes a lift lock cam 106 and a cam follower.

A hinge assembly 14 for attaching a translating motion type aircraft door 10 to an aircraft fuselage 12 is disclosed. On some aircraft the plug door opens partially inward and through a complex hinge design can be tilted to fit through the fuselage opening or the door may have locking hinged panels at the top and bottom edges that can make it smaller than the opening so that it may be swung outward. The other end of the goose neck member is pivotally connected to the door 34. A passenger door 34 is connected to an aircraft fuselage 12 by a hinge mechanism 10 having an elongated goose neck hinge member 22.

The mechanism eliminates hinge cut outs from aircraft fuselage and door outer skins. A hinge assembly connecting a translating motion type aircraft door to an aircraft fuselage wherein the door is dimensioned to be seated in an opening formed in the fuselage the fuselage including a plurality of stops preventing the outward movement of the door the door including a latch lock mechanism for selectively lifting the door above. The hinge assembly 14 includes a fitting 28 that is pivotally attached to the portion of the aircraft fuselage 14 adjacent the door opening 16 in the fuselage in which the door 10 is normally seated. During opening and closing the door moves by means of a hinge mechanism with two mutually parallel rotational axes and an intermediate hinge part one of the rotational axis being connected to the door and the other being connected to the door case.

One end of the hinge member is pivotally connected to an idler crank arm 18 that is pivotally connected to the fuselage.