Fuel is filled in two wing integral fuel tanks, one per each half-wing. Each tank is divided with ribs Nos. 13 and 15 into three sections: alternate, pump and wingtip part of fuel consumed tank pump section together with wingtip - make the fuel consumed tank. Each engine is supplies with fuel from tank of its wing. Fire shut-off valves are installed in engine supply lines. The pipelines of both engines are connected by means of fuel cross-feed line with valve of cross-feed prior fire shut-off valves. It allows, if necessary, to supply fuel from tank of one engine to another one or to supply two engines from one while opening the cross-feed valve. By three non-return valves, being between tanks and installed in lower parts of ribs No. 3 and 15 allow to flow fuel to pump section from two adjacent with itm.

Drainage tanks system. Drainage of each tank is provided by its autonomous system of drainage. The outward venting of tank sections is ensured by drainage section, located in detachable part of wing.

Air intake is installed in drainage section. To protect the tank from damage at closed air intake, the drainage section is vent through vacuum valve and over pressure valve. The drainage section is connected to alternate fuel tank with pipeline and provides its drainage in any position of aircraft. Drainage of pump section is made through hole in upper part of rib No. 15 as well as through non-return valve being between tanks and is installed in three in lower part of ribs No. 13 and 15.

Fuel, getting into the drainage section at changes of aircraft altitude, drains via the pipeline in alternate fuel tank.