Abstract: A brake for an aircraft includes a housing, a shaft defining an axis (X) and extending into the housing, a floating brake disk on the shaft, the brake disk fixed for rotation with the shaft and arranged to be axially movable within the housing, a static brake pad arranged on a first side of the floating brake disk, a movable brake pad arranged on a second, opposite, side of the floating brake disk and biasing means for moving the movable brake pad relative to the housing to press the movable brake pad against the floating brake disk. The biasing means press the floating brake disk against the static brake pad to apply braking force to the floating brake disk. The brake also includes a thermal fuse in thermal contact with the static brake pad. The thermal fuse has a fusing temperature, T, above which the thermal fuse fuses.

Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.