ROBINSON
MODEL R44
SECTION 7
SYSTEMS DESCRIPTION
REVISED: 21 FEB 2014 7-10
FUEL SYSTEM
The fuel system is gravity-flow (no fuel pumps) and includes
main and auxiliary tanks, a shutoff valve control located
between the front seats, and a strainer (gascolator). The
fuel tanks have flexible bladders in aluminum enclosures.
Fuel tank air vents are located inside the mast fairing.
Plunger-style drain valves are provided for the gascolator
and for each fuel tank sump. The gascolator is located
on the lower right side of the firewall and is drained by
pushing up on the plastic tube which extends below the
belly. Valves for both tanks are located inside the right
cowl door below the auxiliary tank. Fuel samples are taken
by extending the plastic tubes clear of the aircraft and
pushing on the plungers. Fuel should be sampled from all
three locations prior to the first flight of the day and after
refueling to verify no contamination and correct grade.
The fuel gages are electrically operated by float-type
transmitters in the tanks. When the gages read E the
tanks are empty except for a small quantity of unusable
fuel. The low fuel caution light is actuated by a separate
electric sender located on the bottom of the main tank.
The auxiliary tank is interconnected with the main tank and
is located somewhat higher so it will become empty first
while fuel still remains in the main tank. The fuel shutoff
valve controls flow from both tanks to the engine.
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