SECTION 7
CESSNA
-.
AIRPLANE AND SYSTEMS DESCRIPTION MODEL
2088
(675 SHP)
OXYGEN SYSTEM
(Continued)
PITOT-STATIC SYSTEM AND INSTRUMENTS
(Continued)
An airspeed pressure switch in the pitot-static system is used to actuate
an airspeed warning horn in the event excessive airspeed is
inadvertently attained. The horn is located behind the headliner in the
area above the pilot, and will sound when airspeed exceeds
VMO (175
KIAS). A warning signal may also be heard in the pilot's headset.
RIGHT FLIGHT INSTRUMENT PANEL PITOT-STATIC
SYSTEM
A second, independent pitot-static system is included for the right flight
instrument panel. The system supplies ram air pressure to the airspeed
indicator and static pressure to the airspeed indicator, vertical speed
indicator, and altimeter utilized in the right flight panel instrument group.
The system is composed of a heated pitot-static tube on the leading
edge of the right wing, a drain valve on the right cabin sidewall beneath
the instrument panel, and the plumbing necessary to connect the
instruments to the sources. The right pitot-static system is not
connected to the pilot's flight instrument pitot-static (left) system.
The pitot-static heat system for the right flight instrument panel consists
of a heating element in the right pitot-static tube, the standard system
two-position toggle switch, labeled
PITOT/STATIC HEAT, on the de-ice/
anti-ice switch panel, a "pull-off' type circuit breaker, labeled RIGHT
PlTOT HEAT, on the left sidewall switch and circuit breaker panel, and
the associated wiring.
The drain valve incorporated into the right flight panel static system
functions identically to the standard system drain valve. Use the right
valve to drain suspected moisture accumulation in the system lines as
indicated by the placard, labeled STATIC SOURCE DRAIN, OPEN,
CLOSED, adjacent to the valve. Make sure the valve is returned to the
CLOSED position prior to flight.
(Continued Next Page)
1
7-104 U.S.
Revision
23
To Next Page
Loading...
