CESSNA SECTION 7
MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION
GFC 700 AFCS
U.S.
ENGINE (Continued)
EXHAUST SYSTEM
Exhaust gas from each cylinder passes through a riser or exhaust
collector assembly (on the left or right side below the engine) to a
turbocharger and overboard through a single tailpipe. Outside air is
supplied to a shroud constructed around the exhaust crossover pipe to
form a heating chamber. The air heated by the shroud is then supplied
to the cabin.
FUEL INJECTION SYSTEM
The engine is equipped with a fuel injection system. The system is
comprised of an engine driven fuel pump, fuel/air control unit, fuel
manifold, fuel flow indicator, and air-bleed type injector nozzles.
Fuel is delivered by the engine driven fuel pump to the fuel/air control
unit. The fuel/air control unit correctly proportions the fuel flow to the
induction air flow. After passing through the control unit, induction air is
delivered to the cylinders through the intake manifold tubes and
metered fuel is delivered to a fuel manifold (flow divider). The fuel
manifold, through spring tension on a diaphragm and valve, evenly
distributes the fuel to an air-bleed type injector nozzle in the intake
valve chamber of each cylinder. A turbine-type fuel flow transducer
mounted between the fuel/air control unit and the fuel distribution unit
produces a digital signal that displays fuel flow on the EIS pages.
(Continued Next Page)
T182TPHBUS-00
7-39
To Next Page
Loading...
Need help?
General
