An architecture that provides automatic monitoring of brake conditions making use of a wear pin (1) on a brake. The embodiment makes use of the fact that a wear pin is required to be provided on an aircraft brake, by integrating monitoring functions such as displacement sensors (15) and/or temperature sensors (14), into the pin (1). This means that the automatic monitoring components are not taking up more space on the brake than is already taken up by the compulsory wear pin.