Cessna TURBO CENTURION T210M 1978 Pilot Operating Handbook page 164

SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
HIGH ALTITUDE ENGINE ACCELERATION
CESSNA
MODELT210M
The engine will accelerate normally from idle to full throttle with full
rich mixture at any altitude below 20,000 feet. At higher altitudes, it is
usually necessary to lean the mixture to get smooth engine acceleration
from idle to maximum power. At altitudes above 25,000 feet, and with
temperatures above standard, it takes one to two minutes for the turbine to
accelerate from idle to maximum RPM although adequate power is
available in 20 to 30 seconds.
PROPELLER
The airplane has an all-metal, three-bladed, constant-speed, governor-
regulated propeller. A setting introduced into the governor with the
propeller control establishes the propeller speed, and thus the engine
speed to be maintained. The governor then controls flow of engine oil,
boosted to high pressure by the governing pump, to or from a piston in the
propeller hub. Oil pressure acting on the piston twists the blades toward
high pitch (low RPM). When oil pressure to the piston in the propeller hub
is relieved, centrifugal force, assisted by an internal spring, twists the
blades toward low pitch (high RPM).
A control knob on the lower center portion of the instrument panel is
used to set the propeller and control engine RPM as desired for -various
flight conditions. The knob is labeled PROP PITCH PUSH !NCR RPM.
When the control knob is pushed in, blade pitch will decrease, giving a
higher RPM. When the control knob is pulled out, the blade pitch increases,
thereby decreasing RPM. The propeller control knob is equipped with a
vernier feature which allows slow or fine RPM adjustments by rotating the
knob clockwise to increase RPM, and counterclockwise to decrease it. To
make rapid or large adjustments, depress the button on the end of the
control knob and reposition the control as desired.
FUEL SYSTEM
The fuel system (see figure 7-7) consists of two vented integral fuel
tanks (one in each wing), two fuel reservoir tanks, a fuel selector valve,
auxiliary fuel pump, fuel strainer, engine-driven fuel pump, fuel/ air
control unit, fuel manifold, and fuel injection nozzles.
NOTE
Unusable fuel is at a minimum due to the design of the fuel
7-28