Abstract: A method of sensing high surface temperatures in aircraft applications is provided. The method includes the steps of applying a temperature indicator material on a surface an object in which monitoring exposure to high temperatures is sought. The temperature indicator material is reactive to a pre-determined temperature threshold. The temperature indicator material is next covered with a heat resistant film to protect the material during exposure to operating temperatures and deleterious environmental conditions. An identified visible change in the temperature indicator material provides confirmation of exposure of the surface of the object to temperatures in excess of the pre-determined temperature threshold.