Chock for steering mechanism of an aircraft nose landing gear

A device to engage with a steering mechanism of a nose landing gear of an aircraft to limit steering rotation of the nose landing gear, the device comprising:

• a first chock sized to fit within a first space at a first section of a steering mechanism of the nose landing gear;
• a second chock sized to fit within a second space at a second section of the steering mechanism of the nose landing gear;
• the first chock and the second chock each comprising:
• a front contact side;
• a back contact side that opposes the front contact side;
• a bottom side;
• a top side that opposes the bottom side;
• wherein the first chock is sized to fit within the first space and to compress when the steering mechanism turns the nose landing gear in a first direction;
• and
• wherein the second chock is sized to fit within the second space and to compress when the steering mechanism turns the nose landing gear in a second direction.

A method of limiting steering rotation of a nose landing gear of an aircraft, the method comprising:

• inserting a first chock in a first space formed between a first cylinder and the nose landing gear;
• inserting a second chock in a second space formed between a second cylinder and the nose landing gear;
• wherein the first chock is configured to compress and limit steering rotation of the nose landing gear in a first direction;
• and
• wherein the second chock is configured to compress and limit the steering rotation of the nose landing gear in a second direction.