CESSNA SECTION 7
MODEL 182T AIRPLANE & SYSTEMS DESCRIPTION
Figure 7-5. Fuel Quantity Data in U.S. Gallons
FUEL DISTRIBUTION
Fuel flows by gravity from the two wing tanks through the fuel
manifold (aft pickup only), and to a four position selector valve.
From the selector valve, fuel flows through the auxiliary fuel pump,
the fuel strainer, and to the engine driven fuel pump. A portion of
the fuel (approximately 7 gallons/hour) is returned to the wing tank
currently selected through the use of the fuel return system. From
the engine driven fuel pump, fuel is delivered to the fuel/air control
unit on the bottom of the engine. The fuel/air control unit (fuel servo)
meters fuel flow in proportion to induction air flow. After passing
through the control unit, metered fuel goes to a fuel distribution
valve (flow divider) located on top of the engine. From the fuel
distribution valve, individual fuel lines are routed to air bleed type
injector nozzles located in the intake chamber of each cylinder.
FUEL INDICATING SYSTEM
Fuel quantity is measured by two float-type fuel quantity
transmitters (one in each tank) and displayed by an electrically
operated fuel quantity indicator on the left side of the instrument
panel. The indicators are marked in gallons of fuel. An empty tank is
indicated by a red line and the number "0". When an indicator
shows an empty tank, approximately 2.5 gallons remain in a tank as
unusable fuel. The indicators should not be relied upon for accurate
readings during skids, slips, or unusual attitudes.
FUEL
TANKS
FUEL LEVEL
(QUANTITY
EACH TANK)
TOTAL
FUEL
TOTAL
UNUSABLE
TOTAL USABLE
ALL FLIGHT
CONDITIONS
Two Full (46.0) 92.0 5.0 87.0
Two Reduced
(34.5)
69.0 5.0 64.0
Apr 30/01 7-27
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