Aircraft fuel systems in the Airbus A310 family

Fuel capacity has been progressively increased through the A310 family range. Fuel in the initial A310-200 model is stored inside the wing box, which is divided into five separate fuel tanks. The centre tank contains 5,188US gal (19,6401), the two inner wing fuel tanks hold 3,684US gal (13,9451) each, and the two outer wing tanks 976US gal (3,6951) each, giving a total capacity of 14,491US gal or 12,097Imp gal (54,920 litres).

Water drainage is provided at the low points of each tank and can be performed with up to 2 ° ground slope. All tanks are equipped with manholes to provide access to the interior. The A310-300 has a 1,623US gal or 1,3551mp gal (6,1501) fuel tank in the horizontal stabiliser, bringing total capacity to 16,114USga1 or 13,452Imp gal (61,070 litres).

Computerised fuel transfer systems. 

In addition to increasing the aircraft's range, the computerised fuel transfer systems in the trim tanks also provide active centre of gravity (c.g.) control for more efficient production of lift. The net result is a 1.5 percent reduction in cruise drag and lower fuel burn. One or two ACTs (Optional Additional Centre Tanks) in the aft rear cargo hold of the A310-300 can increase total fuel capacity to 19,913US gal or 16,6231mp gal (75,470 litres).

The usable fuel volume is 1,902US gal (7,2001) in each tank. The ACTs are fed to/from the centre wing tank, with parallel refuelling if both tanks are installed in 45 minutes. Removal/installation of the ACTs can be accomplished overnight.

The aircraft fuel systems are designed for single-point refuelling/defuelling control by one operator from a panel located under the fuselage centre section. Two standard two inch fuelling adaptors are provided under the leading edge of the right hand wing, outboard of the engine, enabling a complete refuel from empty in 24 minutes.

Normally, each engine is supplied with fuel pumped from its own wing by threephase AC booster pumps mounted two per fuel tank for fail safety, but cross-feed and transfer valves permit fuelling of both engines to be fed from one side, or all the fuel to be used by one engine. Each of the aviation fuel pumps can dry-run for about 15 minutes.

In an emergency, the wing tanks can be refuelled by gravity via one over-wing filler point per tank. The fuel tanks are used in the order - centre, inner, outer - with the outer wing tank pumps fitted with sequence valves, so that fuel from these tanks can only be used if there is no supply form the centre or inner tanks.