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SECTION 7
CESSNA
AIRPLANE & SYSTEMS DESCRIPTION
MODEL 182T
ENGINE INSTRUMENTS
Engine operation is monitored by the following instruments: oil
pressure/oil temperature indicator, exhaust gas temperature
indicator (EGT)/cylinder head temperature indicator (CHT),
manifold pressure gauge/fuel flow indicator and tachometer.
The oil pressure/oil temperature indicator unit is located on the
lower left side of the instrument panel. Markings for the pressure
indicator indicate a minimum idling pressure of 20 PSI (red line), a
normal operating range of 50 to 90 PSI (green arc), and a
maximum pressure of 115 PSI (red line). Markings for the oil
temperature gauge indicated a normal operating range of 100 to
245°F (green arc), and a maximum temperature of 245°F (red line).
Oil pressure signals are generated from a pressure
line/transducer combination. An oil pressure line is routed from the
upper front of the engine case to the rear engine baffle. At the
baffle, the oil pressure line is connected to a transducer. This
transducer produces an electrical signal which translates into a
pressure reading at the instrument panel gauge.
Oil temperature signals are generated from a resistance-type
probe located in the accessory case. As oil temperature changes,
the probe resistance changes. This resistance is translated into oil
temperature readings on the cockpit indicator.
In addition, a separate low oil pressure indication is provided
through the panel annunciator. This annunciator is wired to a
pressure switch located on the rear of the engine accessory case.
When oil pressure is below 20 PSI, the switch grounds and
completes the annunciator circuit, illuminating the red OIL PRESS
annunciator. When pressure exceeds 20 PSI, the ground is
removed and the OIL PRESS annunciator extinguishes.
NOTE
The low oil pressure switch is also wired into the Hobbs
(hour) meter. When pressure exceeds 20 PSI, a ground is
supplied to the hour meter, completing the hour meter
circuit.
7-20
Apr 30/01
Summary of Contents for 182T 2001
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