US 2013/0152338 A1 · Aircraft Interior Bushing

Abstract

An aircraft interior bushing is disclosed comprising in one form interoperating bushing portions. Each bushing portion in one form comprising a recessing portion, a radially inner surface operably configured to contact a surface defining a void in a panel, a perimeter portion wherein the perimeter portion is substantially larger than the recessing portion, a support arm receiver, and a support arm. Each support arm comprises a first end coupled to the bushing, and a second end comprising a conduit receiver. In one form, the bushing assembly is operably configured to support a conduit at a distance from the radially inner surface of the interoperating bushings to substantially prohibit contact between the conduit and the bushing assembly once the conduit is installed and fixed to the conduit receiver.

Claims17

Dependent claims

An aircraft interior bushing comprising:

a. a recessing portion,
b. a radially inner surface operably configured to contact a surface defining a void in a panel,
c. a perimeter portion wherein the radial dimension of the perimeter portion is substantially larger than the radial dimension of the recessing portion,
d. a first support arm receiver positioned at a first radial position;
e. a second support arm receiver positioned at a second radial position;
f. a support arm comprising
i. a first end coupled to the bushing at either of the support arm receivers,
ii. a second end comprising a conduit receiver,
iii. a surface defining a clamp receiver, and
g. wherein the bushing is operably configured to support a conduit offset a distance from the surface defining the void in the panel to substantially prohibit contact between the conduit and the surface defining the void in the panel once the conduit is affixed to the conduit receiver.

7 more elements

An aircraft interior bushing assembly comprising:

a. a first bushing comprising
i. a recessing portion,
ii. a radially inner surface operably configured to contact a surface defining a void in a panel,
iii. a perimeter portion wherein the radial dimension of the perimeter portion is substantially larger than the recessing portion,
iv. a support arm receiver;
b. a support arm coupled the first bushing, the support arm comprising
i. a first end coupled to the first bushing,
ii. a second end comprising a conduit receiver,
iii. a clamp receiver, and
c. wherein the bushing assembly is operably configured to support a conduit at a distance from the radially inner surface of the void in the panel to substantially prohibit contact between the conduit and the panel once the conduit is installed and fixed to the support arm.

7 more elements

Dependencies are inferred from the claim text.

Aircraft Interior Bushing

Life of this patent

Aircraft Interior Bushing

Life of this patent

Abstract

Claims17