The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Mar. 01, 1994

Filed:

Nov. 08, 1991
Applicant:
Inventors:

Eddie D Banks, Renton, WA (US);

Tomio Hamatani, Seattle, WA (US);

Hajime Kishi, Kagamihara, JP;

Richard B Odell, Kirkland, WA (US);

Takayoshi Urasawa, Bellvue, WA (US);

Assignee:

The Boeing Company, Seattle, WA (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
E05D / ; E05D / ; B64C / ;
U.S. Cl.
CPC ...
16366 ; 244905 ; 2441295 ; 49246 ;
Abstract

A hinge assembly (14) for attaching a translating-motion-type aircraft door (10) to an aircraft fuselage (12) is disclosed. 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. The door is attached to the hinge fitting (28) by way of a universal shaft (30) that is rotatably attached to the free end of the hinge fitting (28). A drivebelt (32) is anchored at one end to the aircraft fuselage (12) and is attached at the opposed end to the universal shaft (30) so as to move in unison with the shaft. When the hinge assembly (14) of this invention is opened, the hinge fitting (28) pulls on the drivebelt (32) so as to cause its movement and the subsequent movement of the universal shaft (30). The universal shaft (30) is rotated about the hinge fitting (28) so as to maintain the door (10) attached thereto in a constant angular relationship relative to the longitudinal axis of the aircraft fuselage (12).


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