Aircraft brake assembly sensing device

A method of monitoring an aircraft brake assembly comprising:

• providing a housing rigidly attached to the chassis of an aircraft brake assembly, wherein the housing comprises a displacement sensor;
• providing a pin which extends through the housing to a first end which moves with a pressure plate of the aircraft brake assembly so that the pin moves relative to the housing;
• wherein the pin comprises a detectable element portion positioned within the housing and comprising a first end and a second end, wherein the pin comprises a temperature sensing portion located between the first end of the detectable element portion and the pressure plate, and wherein the pin comprises a visual wear detection portion located proximate the second end of the detectable element portion and extending from the housing in a direction away from the pressure plate;
• monitoring a position of the detectable element within the housing using the displacement sensor;
• monitoring a temperature of the pressure plate via the temperature sensing portion;
• and
• monitoring wear of brake discs in the aircraft brake assembly via the visual wear detection portion.

A sensing device for monitoring an aircraft brake assembly, the sensing device comprising:

• a housing configured to be rigidly connected to the chassis of the aircraft brake assembly, the housing comprising a transmitter;
• and
• a pin extending through the housing and comprising a first end configured to contact a pressure plate of the aircraft, wherein in use the pin is configured to move with the pressure plate relative to the housing in a longitudinal direction of the pin;
• wherein the pin comprises a detectable element portion positioned within the housing and comprising a first end and a second end and wherein the displacement sensor is configured to monitor the position of the detectable element portion within the housing,
• wherein the pin comprises a temperature sensor portion located between the first end of the detectable element portion and the pressure plate and configured to monitor a temperature of the pressure plate and wherein the transmitter is configured to receive sensor data from the temperature sensor via a wired connection and to transmit the sensor data to a receiver external to the housing, and
• wherein the pin comprises a visual wear detection portion located proximate the second end of the detectable element portion and extending from the housing in a direction away from the pressure plate and configured to indicate wear of brake discs in the aircraft brake assembly.