CESSNA SECTION 7
MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION
GFC 700 AFCS
U.S.
ENGINE (Continued)
ENGINE INSTRUMENTS (Continued)
MANIFOLD PRESSURE
Manifold pressure is shown by the MAN IN indicator at the top of all EIS
pages. The manifold pressure indicator uses a circular scale and
moving pointer with a digital value. The pointer moves through a range
of 10 to 35 in.hg. The digital manifold pressure value is shown in white
numerals below the pointer.
Colored arcs on the manifold pressure indicator show different
operating ranges. For operation below 15,000 feet the normal operating
range is from 15 to 28 in.hg. and indicated by the green arc with a red
arc from 32 to 35 in.hg.
When operating above 15,000 feet and below 20,000 feet indicated
altitude, the green arc range changes to 15 to 27 in.hg., which is one
inch less manifold pressure at the top of the green arc.
The maximum manifold pressure at all altitudes is 32 in.hg. When
manifold pressure is 34 in.hg. or more, the pointer will turn red, while
the digital value and label (MAN IN) will turn red and flash to show
manifold pressure is more than the limit.
The manifold pressure indicator includes a white index mark at 25
in.hg. This white index mark and a white index mark on the fuel flow
indicator at 16 gallons per hour (GPH) show manifold pressure and fuel
flow for a normal climb power setting at 2400 RPM.
An absolute pressure transducer, located between the firewall and the
instrument panel, provides a signal to the engine and airframe unit
which processes and outputs the data to the EIS. A red X through the
manifold pressure display shows that the indicating system is
inoperative.
(Continued Next Page)
T182TPHBUS-00
7-31
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