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% Fuel level sensors and fuel quantity probes are installed in both fuel tanks. The right tank has a % transfer pump shut-off switch (low fuel sensor) located at the bottom inner corner. The left tank has % a transfer pump shut-off switch (high fuel sensor) located at the top outer corner. The left tank also % has a switch for the LOW FUEL caution light (low fuel sensor) located at the bottom inner corner.
% The fuel quantity probes go from the bottom inner corner of each tank to the top outer corner. The fuel % level changes the probe electrical properties. The fuel quantity system measures the probe % capacitance. It uses the value as an analogue of fuel quantity. The value for each tank is shown on % the Auxiliary Engine Display (AED) on the right of the instrument panel.
% A fuel temperature sensor is installed in each fuel tank. The LH and RH fuel temperatures are % indicated on the Auxiliary Engine Display (AED).
% Flexible hoses connect the fuel tanks in the wings to the emergency fuel valve and transfer pump in % the center fuselage. A gascolator attaches to the emergency fuel valve. The gascolator has a filter and % a fuel drain valve. A flexible hose connects the gascolator to the engine fuel filter mounted forward % of the firewall.
% Two engine-mounted pumps supply fuel to the engine fuel injection system. A return line from the % engine connects to the right wing tank. A loop of pipe inside the right tank makes a heat exchanger % to cool the return fuel. A flexible hose connects the outlet of the loop to the left tank.
Doc # 6.02.01 Page 3
Rev. 4 09 Jan 2003

28-01-00
AMM

% 3. Operation
% A. Normal Operation
% The engine pumps take fuel from the left fuel tank. Fuel flows through the finger filter to the % emergency fuel valve. From the valve it flows through the strainer in the gascolator. The % gascolator is also a water separator. The fuel flows to the main filter and the engine fuel system.
% The engine fuel pumps always supply more fuel than the fuel injection system can use. The % unwanted fuel is hot. It flows back to the right fuel tank and though the cooling loop. Heat transfers % from the return fuel to the cold fuel in the tank. The return fuel flows from the cooling loop to the % left tank. The return fuel mixes with the fuel in the left tank.
% This process keeps the Diesel fuel warm in both tanks when the airplane operates in cold % conditions.
% As the engine uses fuel, the fuel level in the left tank decreases. Air flows in through the vent % system to fill the space left by the fuel. This prevents the tank pressure from decreasing to less % than atmospheric pressure. It allows the engine pumps to continue to take fuel from the tank.
% B. Fuel Transfer
% As the engine uses fuel, the fuel level in the left tank decreases. The fuel level in the right tank % does not change. To balance the tank contents, the electric transfer pump moves fuel from the % right tank to the left tank. It is operated through a switch (marked FUEL TRANS .) on the left of % the instrument panel. A status light (FUEL TRANS) on the annunciator panel is illuminated as long % as the fuel transfer pump is running.
% The high fuel sensor in the left tank outer top corner automatically switches off the fuel transfer % pump when the fuel level is high in the left tank. The low fuel sensor in the right tank inner bottom % corner automatically switches off the fuel transfer pump when the fuel level is low in the right tank.
% C. Emergency Operation
% In an emergency (for example, the transfer pump fails) you can set the emergency fuel valve to % connect the right tank transfer line to the fuel supply line. This is the EMERGENCY setting. The % engine takes fuel from the right tank. However, the return fuel still flows through the cooling loop % to the left tank. As fuel is used from the right tank, the level of fuel in the left tank will slowly % increase.
Page 4 Doc # 6.02.01 09 Jan 2003 Rev. 4
　
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