Quick release hinge

Patent metadata

Field	Value
Publication number	US-2016201371-A1
Application number	US-201514592593-A
Country	US
Kind code	A1
Filing date	Jan 8, 2015
Priority date	Jan 8, 2015
Publication date	Jul 14, 2016
Grant date	—

Abstract

Aspects of the disclosure are directed to a system configured for installing or removing a door from an aircraft, the system comprising: a pin, a hinge comprising a slot that forms a cavity for rotatively coupling the hinge and the pin, a clamp coupled to the pin, and a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

First claim

1 . A system configured for installing or removing a door from an aircraft, the system comprising:
a pin; a hinge comprising a slot that forms a cavity for rotatively coupling the hinge and the pin; a clamp coupled to the pin; and a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

2 . The system of claim 1 , wherein the hinge is configured as a gooseneck hinge.

3 . The system of claim 1 , wherein the door is coupled to the hinge, and wherein the door is a latch access door.

4 . The system of claim 1 , wherein the clamp comprises a through hole that rotatively receives the pin for coupling the clamp and the pin.

5 . The system of claim 1 , wherein the clamp is configured to removably rotate about the pin when the retaining mechanism is disengaged with respect to the hinge.

6 . The system of claim 1 , further comprising:
an attachment mechanism to couple the pin to a structure of the aircraft.

7 . The system of claim 6 , wherein the structure of the aircraft comprises a latch beam on a thrust reverser.

8 . The system of claim 6 , further comprising:
a thermal blanket that is positioned to physically obscure access to the attachment mechanism.

9 . The system of claim 1 , wherein the retaining mechanism comprises at least one of a screw, a nut, or a bolt.

10 . A system comprising:
a hinge comprising a slot that forms a cavity for rotatively coupling the hinge and a pin; a clamp coupled to the pin; and a retaining mechanism that couples the clamp and the hinge when the retaining mechanism is engaged with respect to the hinge and decouples the clamp and the hinge when the retaining mechanism is disengaged with respect to the hinge.

11 . The system of claim 10 , wherein the retaining mechanism is on the clamp and selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

12 . A system comprising:
a door; a hinge coupled to the door, the hinge including a slot configured to form a cavity for receiving a pin.

13 . The system of claim 12 , further comprising the pin.

14 . The system of claim 12 , wherein the hinge is configured as a gooseneck hinge.

15 . The system of claim 12 , wherein the door is a latch access door associated with an aircraft nacelle.

Assignees

• Rohr Inc

Inventors

• Harding David
• Heber William

Classifications

• E05D7/1066 Primary

  requiring a specific angular position · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• E05Y2900/502

  for aircraft or spacecraft · CPC title

• E05D7/1061

  in a radial direction (E05D7/1005 takes precedence) · CPC title