Aircraft Door Hinge Mechanism

The mechanism eliminates hinge cut outs from aircraft fuselage and door outer skins.

Aircraft door hinge mechanism.

Aircraft door of the type which during the flight is pressed all around against the door case under influence of the cabin pressure. A plug door is a door designed to seal itself by taking advantage of pressure difference on its two sides and is typically used on aircraft with cabin pressurization the higher pressure on one side forces the usually wedge shaped door into its socket making a good seal and preventing it from being opened until the pressure is released non plug doors rely on the strength of the locking. The door is attached to the hinge fitting 28 by way of a. 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 door you mentioned is called a plug door. Finally its architecture makes it highly customizable to answer any aircraft needs. A guide arm connected to the door and carried by the idler crank arm controls door. The other end of the goose neck member is pivotally connected to the door.

One end of the hinge member is pivotally connected to an idler crank arm that is pivotally connected to the fuselage. Nexged components and features. The other end of the goose neck member is pivotally connected to the door 34. 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.

A hinge assembly 14 for attaching a translating motion type aircraft door 10 to an aircraft fuselage 12 is disclosed. The main components of the next generation equipped door are. The electrical door is also lighter and less costly than traditional mechanical doors. 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.

A latch lock mechanism 20 for opening and closing a translating motion type aircraft door 22. This permits the use of a continuous stop on the door and body which simplifies door rigging and reduces structural weight and further increases reliability in service. 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 shaft 38 is rotated by a lift lock mechanism 44 that includes a lift lock cam 106 and a cam follower.

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