Mahindra GIPPSAERO GA8-TC 320 - Propeller

Section 7
Aircraft & Systems
Model GA8-TC 320 Description
Page 7-8 5 Feb 2009 C01-01-08
element air lter incorporated which removes dust and other foreign matter from the induction
air. In addition a manually operated alternate air system is provided to supply air to the engine
in the event that the air lter becomes severely or completely blocked. This system is manually
operated by the alternate air control beneath the throttle quadrant and provides heated but
unltered air to the engine.
From the intake chamber the air is ducted to the compressor impeller of the turbocharger where
it is compressed and ducted to the fuel injector servo regulator, thence to the engine cylinders
through the intake manifold tubes. The servo regulator monitors air ow passing through it,
and depending on the throttle and mixture lever positions selected by the pilot, meters the fuel
supplied to the fuel injector nozzles.
Exhaust System This engine incorporates one turbocharger which is an integral part of the
exhaust system. The exhaust gases drive a turbine which is coaxial with a compressor impeller.
The function of the turbocharger is to provide constant air density to the fuel injector inlet from
sea level to critical altitude. Regulating the amount of exhaust gas fed to the turbine wheel
controls the air output which in turn determines engine power output. The amount of exhaust gas
fed to the turbocharger is controlled by an exhaust bypass valve (wastegate) which is regulated
by a control system that includes a density controller and differential pressure controller. These
controllers each act independently to regulate the oil pressure that acts on a piston connected
via a linkage to the wastegate buttery.
Two heat exchangers are tted on the exhaust manifold to provide cabin heating and demisting.
The one located at the front of the engine provides hot air to the left hand side of the cockpit,
the other one after the turbocharger, provides hot air to the right hand side of the cockpit. The
exhaust pipe exits vertically out through the lower starboard side of the engine cowl to discharge
the exhaust gases.
Fuel Injection System The engine is equipped with a Bendix RSA fuel injection system that is
composed of two primary components, a servo regulator and a ow divider. The servo regulator
regulates fuel pressure by means of a servo valve using airow signals. When this regulated
pressure is applied across the fuel control jetting this provides a fuel ow that is proportional to
the airow. The air/fuel ratio is controlled, within limits, by the mixture control. The ow divider
is the device that ensures the correct distribution of metered fuel to each cylinder fuel nozzle.
Cooling System Ram air for engine cooling enters through two intakes at the front of the
engine cowl. The cooling air is directed around the cylinders and other areas of the engine by
appropriate bafes and is then exhausted through an opening in the rear of the lower cowl. Air
for oil system cooling enters the lower intake chamber and ows through two oil coolers at the
back of the chamber. The air then exhausts out the lower cowl opening with the engine cooling
air.
7.12 PROPELLER
The aircraft is equipped with a three bladed constant speed Hartzell model HC-C3YR-1RF/
F8068 propeller. The propeller blades are of forged aluminium construction and anodised to
reduce corrosion. The blades are tted to a lightweight forged alloy hub that houses the pitch
changing mechanism. The propeller is operated by engine oil, the ow of which is regulated by
an engine mounted governor. The propeller is 82 inches (2083 mm) diameter.
01 Aug 2011