Transport element support assembly
AssigneeThe Boeing Company
InventorsBenjamin Curtis Cheatham, Michael Leslie Gilbertson
Life of this patent
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Abstract
A transport element support assembly comprises a front plate, a back plate, and a grommet. The front plate has a first opening and a first set of holes. The back plate has a second opening and a second set of holes. A chamber is formed by the first opening and the second opening and is configured to hold a transport element. The grommet is positioned within the chamber. The transport element support assembly formed by the front plate, the back plate, and the grommet is configured to provide electrical isolation between the transport element and an aircraft structure.
Claims20
A transport element support assembly comprising:
- a front plate having a first opening and a first set of holes;
- a back plate having a second opening and a second set of holes;
- a chamber formed by the front plate and the back plate, the chamber interposed between the front plate and the back plate and configured to hold a transport element;
- and
- a grommet positioned within the chamber, wherein the transport element support assembly formed by the front plate, the back plate, and the grommet is configured to provide electrical isolation between the transport element and an aircraft structure;
- wherein a hole pattern formed by an axial alignment of the first set of holes with the second set of holes is split into a plurality of hole pattern sets, wherein each hole pattern set is configured to match a hole pattern in the aircraft structure and each hole pattern set is configured to provide a different centerline position of the transport element.
A fluid system for an aircraft, the fluid system comprising:
- a tube;
- and
- a tube support assembly comprising:
- a front plate having a first opening and a first set of holes;
- a back plate having a second opening and a second set of holes;
- a chamber formed by interfacing the front plate and the back plate, wherein the chamber is interposed between the front plate and the back plate and is configured to hold the tube;
- and
- a grommet positioned within the chamber, wherein the tube support assembly formed by the front plate, the back plate, and the grommet is configured to provide electrical isolation between the tube and an aircraft structure;
- wherein a hole pattern formed by an axial alignment of the first set of holes with the second set of holes is split into a plurality of hole pattern sets, wherein each hole pattern set is configured to match a hole pattern in the aircraft structure and each hole pattern set is configured to provide a different centerline position of the tube.
Dependencies are inferred from the claim text.