ED Decision 2003/18/RM
(a) General. The ability of the fuel system to provide fuel at the rates specified in this paragraph and at a pressure sufficient for proper carburettor operation must be shown in the attitude that is most critical with respect to fuel feed and quantity of unusable fuel. These conditions may be simulated in a suitable mockup. In addition -
(1) The quantity of fuel in the tank may not exceed the amount established as the unusable fuel supply for that tank under CS-VLA 959 plus that necessary to show compliance with this paragraph; and
(2) If there is a fuel flowmeter, it must be blocked during the flow test and the fuel must flow through the meter bypass.
(b) Gravity systems. The fuel flow rate for gravity systems (main and reserve supply) must be 150% of the take-off fuel consumption of the engine.
(c) Pump systems. The fuel flow rate for each pump system (main and reserve supply) must be 125% of the take-off fuel consumption of the engine at the maximum power established for take-off. This flow rate is required for each primary engine driven pump and each emergency pump, and must be available when the pump is running as it would during take-off.
(d) Multiple fuel tanks. If the engine can be supplied with fuel from more than one tank, it must be possible, in level flight, to regain full power and fuel pressure to that engine in not more than 10 seconds after switching to any full tank after engine malfunctioning due to fuel depletion becomes apparent while the engine is being supplied from any other tank.
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