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An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mounted to an inner surface of the skin layer adjacent to the hole

An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mounted to an inner surface of the skin layer adjacent to the hole in the skin layer; and an access panel which covers the hole and can be removed to gain access to the gauge.

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1. An aircraft skin panel which is a wall of a fluid tank when in use, the skin panel comprising an inner layer and a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; an ultrasonic gauge positioned between the skin layer and the inner layer; and an access

1. An aircraft skin panel which is a wall of a fluid tank when in use, the skin panel comprising an inner layer and a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; an ultrasonic gauge positioned between the skin layer and the inner layer; and an access panel in the skin layer which can be removed to gain access to the gauge from outside the tank. 2. The skin panel of claim 1 further comprising a core having a mass density lower than the inner layer and the skin layer, wherein the core is positioned between the inner layer and the skin layer. 3. The skin panel of claim 2 further comprising a signal wire connected to the ultrasonic gauge, wherein the signal wire is positioned between the inner and skin layers of the skin panel. 4. The skin panel of claim 3 further comprising a wire conduit positioned between the inner and skin layers of the skin panel. 5. The skin panel of claim 4 wherein the wire conduit surrounds the signal wire. 6. The skin panel of claim 4 wherein the wire conduit engages the inner layer and the skin layer. 7. The skin panel of claim 4 wherein the signal wire or the wire conduit is fitted into a hole or recess in the core. 8. The skin panel of claim 1 wherein the gauge comprises a gauge assembly comprising a transducer assembled with one or more fittings. 9. The skin panel of claim 2 wherein the gauge comprises an angled surface which engages the inner layer, and wherein the inner layer forms a ramp where it engages the angled surface. 10. The skin panel of claim 8 wherein the transducer is assembled with the one or more fittings by a threaded connection. 11. The skin panel of claim 2 wherein the gauge is fitted into a hole or recess in the core. 12. The skin panel of claim 2 wherein the gauge engages and is in direct contact with the inner layer and the skin layer. 13. The skin panel of claim 2 wherein the core comprises an array of air cells. 14. The skin panel of claim 2 wherein the core comprises a foam or honeycomb material. 15. The skin panel of claim 1 wherein the access panel is mounted to the ultrasonic gauge. 16. The skin panel of claim 15 wherein the access panel is mounted to the ultrasonic gauge by one or more removable fasteners. 17. The skin panel of claim 1 wherein the ultrasonic gauge engages an inner surface of the skin layer. 18. A method of manufacturing the aircraft skin panel of claim 2, the method comprising placing the core and the gauge on a first one of the layers, and then laying the other layer onto the core and the gauge. 19. An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use, and an inner surface; a hole in the skin layer; an ultrasonic gauge assembly; and an access panel which fills the hole and can be removed to gain access to the ultrasonic gauge assembly from outside the tank, wherein the ultrasonic gauge assembly comprises an ultrasonic transducer, and a housing which is attached to the inner surface of the skin layer around a periphery of the access panel and houses the ultrasonic transducer, the housing comprising a channel which is configured to act as a wire conduit.