Abstract: A resistive and locking system for locking rotation of a shaft. The system includes a housing defining an axis AX therethrough. The housing includes a drive shaft mounted in the housing and extending axially from a bottom end of the housing and a first stage comprising a resistive mechanism provided in the housing. The housing also includes a second stage comprising a locking mechanism arranged in the housing above the first stage. The locking mechanism is biased axially to frictionally engage with and lock the first stage mechanism to prevent rotation of the drive shaft, the locking mechanism including a magnetic unlocking mechanism configured to remove the frictional engagement with the first stage on application of power to the locking mechanism.

Abstract: A resistive and locking system for locking rotation of a shaft. The system includes a housing defining an axis AX therethrough. The housing includes a drive shaft mounted in the housing and extending axially from a bottom end of the housing and a first stage comprising a resistive mechanism provided in the housing. The housing also includes a second stage comprising a locking mechanism arranged in the housing above the first stage. The locking mechanism is biased axially to frictionally engage with and lock the first stage mechanism to prevent rotation of the drive shaft, the locking mechanism including a magnetic unlocking mechanism configured to remove the frictional engagement with the first stage on application of power to the locking mechanism.

Abstract: A pedal cartridge for an aircraft. The pedal cartridge is connectable to a pedal mechanism and includes: a pedal. The pedal includes a pedal axle receiving portion configured to receive a pedal axle of the pedal mechanism such that the pedal is rotatably connectable to the pedal axle. The mechanism also includes a first rotation sensor component, the first rotation sensor component configured to interact with a second rotation sensor component of the pedal mechanism to permit rotation of the pedal about the pedal axle to be detected.

Abstract: A pedal mechanism for an aircraft. The pedal mechanism includes: a pedal arm connectable to a pedal at a pedal connection point, the pedal arm rotatable about a pedal arm rotation point on translation of the pedal; and a stature adjustment mechanism, the stature adjustment mechanism actuatable, during a stature adjustment process, to move the pedal arm rotation point.

Abstract: A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

Abstract: This disclosure provides a heating device. The heating device comprises an electrically conductive fabric and first and second electrical connections. The first and second electrical connections are each connected to the conductive fabric at a first end of the device. When the electrical connections are connected to a power source current flows from the first electrical connection, though the conductive fabric and to the second electrical connection thereby generating heat.

Abstract: A blade comprises a blade body and blade de-icer located on the leading edge of the blade body. The blade de-icer comprises a first heater part bonded to an external surface of a face side of the blade body and a separate second heater part bonded to an external surface of a camber side of the blade body. The first and second heater parts each extend to the leading edge of the blade body. Each heater part comprises an electrical heating element arranged therein sandwiched between an inner layer and an outer layer of the heater part.

Abstract: A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

Abstract: A de-icing apparatus configured to remove ice from a surface part of an aircraft, the de-icing apparatus comprising a heating layer and a conductive surface extending over, and in heat conductive contact with, the heating layer. The conductive surface defines at least a part of the surface part of the aircraft or an aircraft component. The heating layer comprising heating elements defining substantially closed contour zones, each comprising a periphery formed by the heating elements within which an area is defined; the heating layer and the conductive surface configured such that when power is provided to the apparatus the heating elements which fragment ice formed on the surface part of the aircraft according to the shape of the peripheries of the substantially closed contour zones.

Abstract: This disclosure provides a heating device. The heating device comprises an electrically conductive fabric and first and second electrical connections. The first and second electrical connections are each connected to the conductive fabric at a first end of the device. When the electrical connections are connected to a power source current flows from the first electrical connection, though the conductive fabric and to the second electrical connection thereby generating heat.

Abstract: A propeller blade assembly includes an airfoil having a base, a tip and a leading edge and a root extending from the base of the airfoil for attaching the airfoil to a hub. The assembly further comprises an electrically conductive sheath for electrically grounding the airfoil. The electrically conductive sheath is attached to the leading edge of the airfoil and extends from the base to the tip of the airfoil. The assembly further comprises an electrically conductive element for electrically connecting the electrically conductive sheath to the root or hub. Also disclosed is an electrically conductive sheath for grounding an airfoil and a method for assembling a propeller blade assembly.