DA20-C1 Flight Manual
Description
Doc # DA202-C1 April 06, 2010 Page 7 - 17
7.10. FUEL SYSTEM
The aluminum tank is located behind the seats, below the baggage compartment. The capacity
is specified in Section 2 of this manual. The tank filler on the left side of the fuselage behind the
canopy is connected to the tank with a rubber hose. A grounding stud is located on the under
side of the fuselage near the trailing edge of the left hand wing. The aircraft must be grounded
prior to any fueling operation.
The tank vent line runs from the filler neck through the fuselage bottom skin to the exterior of the
airplane. The vent line is the translucent plastic hose adjacent to the left wing root. The vent
line must be clear for proper fuel system operation. The tank has an integral sump which must
be drained prior to each flight, by pushing up on the brass tube which protrudes through the
underside of the fuselage, forward of the trailing edge of the left hand wing.
Two outlets with finger filters, one left and one right, are installed at the bottom of the tank (see
Figure 7.6). Fuel is gravity fed from these outlets to a filter bowl (gascolator) and then to the
electric fuel pump. The filter bowl must be drained prior to each flight, by pushing up on the
black rubber tube that protrudes through the underside of the fuselage, adjacent to the fuel tank
drain. The electric fuel pump primes the engine for engine starting (Prime ON) and is used for
low throttle operations (Fuel Pump ON). When the pump is OFF, fuel flows through the pump's
internal bypass. From the electric pump, fuel is delivered to the engine's mechanical fuel pump
by the fuel supply line. Fuel is metered by the fuel control unit and flows via the fuel distribution
manifold to the injector nozzles.
Closing the fuel shut-off valve, located either on the aft side of the firewall or at the maintenance
drain manifold, will cause the engine to stop within a few seconds.
A return line from the mechanical pump's fuel vapor separator returns vapor and excess fuel to
the tank.
Fuel pressure is measured at the fuel distribution manifold and displayed on the fuel pressure
indicator, which is calibrated in PSI.
Revision 25
Some DA20-C1 aircraft also have a fuel vapor separator in the distribution manifold. These
aircraft have a second vapor return line from the distribution manifold to the firewall.
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