Patent ID: 8671998

Claim:
Apparatus for testing an aircraft tank system comprising: a fuel supply device including a fuel reservoir, a fuel supply line for supplying fuel from the fuel reservoir to a fuel outlet of the fuel supply device, and a first isolation valve disposed in the fuel supply line, a fuel transfer line for transferring fuel from the fuel outlet of the fuel supply device to the aircraft tank system, a second isolation valve disposed in the fuel transfer line, a pressure sensor to sense pressure within the aircraft tank system and produce a test parameter signal indicative of the pressure within the aircraft tank system, and an electronic control unit which is adapted to control the first isolation valve and the second isolation valve so as to interrupt the supply of fuel through the fuel supply line and the transfer of fuel through the fuel transfer line, respectively, in response to the test parameter signal provided to the electronic control unit if the pressure within the aircraft tank system sensed by the pressure sensor exceeds a predetermined limit, and an overflow reservoir for receiving overflowing fuel from the aircraft tank system and a level sensor for sensing a fuel level within the overflow reservoir and for providing a test parameter signal indicative of the fuel level in the overflow reservoir, wherein the electronic control unit is adapted to control the first isolation valve and the second isolation valve so as to interrupt the supply of fuel through the fuel supply line and the transfer of fuel through the fuel transfer line, respectively, if the fuel level within the overflow reservoir sensed by means of the level sensor exceeds a predetermined limit.