US Patent 10421551 Aircraft anti-icing system

An anti-icing system for an aircraft structure includes a cavity that has an exterior surface subject to ice accretion and a bleed source that is configured to provide a fluid to the cavity via a duct. The system includes multiple temperature sensors, disposed at the aircraft structure, with each temperature sensor configured to detect a temperature associated with an aircraft structure location. A controller is in communication with the temperature sensors. The controller is programmed to compare outputs of the temperature sensors and to determine a temperature sensor fault condition.