Abstract: An aircraft gas turbine engine fuel metering unit incorporating a memory device for storing data relevant to that unit, and an electrical connection arrangement whereby data can be read from and/or written to said memory device by an associated electronic engine controller, said stored data including data relating to at least one of the performance, the identification, the health, and the service life of that fuel metering unit. The invention further resides in an aircraft gas turbine engine fuel supply system and a method of operating such a system.

Abstract: A data flow controller comprises two buffers 20 and 22 and a control element 24 for checking for predefined temporal constraints between items of data and for only allowing items of data to be transferred from the first buffer to the second buffer when the data items satisfy the temporal constraints.

Abstract: An apparatus is provided to rotatably support a shaft having an annular worn portion and unworn portions disposed adjacent to axially opposite ends of the worn portion. The apparatus includes a plurality of bearing elements. The bearing elements engage the unworn portion of the shaft at a location adjacent to the worn portion of the shaft. A sleeve encloses the bearing elements and the worn portion of the shaft. Opposite ends of the sleeve are closed by seals which engage unworn portions of the shaft.