CESSNA SECTION
7
MODEL
2088
(675
SHP) AIRPLANE AND SYSTEMS DESCRIPTION
OXYGEN SYSTEM
Some Cargo Versions are equipped with a two-port oxygen system
having quick-don type masks for the pilot and passenger; other Cargo
Versions can be equipped with a two-port oxygen system utilizing
conventional masks. The Passenger Version can be equipped with a
13-port oxygen system utilizing conventional masks. Refer to Section
9,
Supplements, for complete details and operating instructions.
PITOT-STATIC SYSTEM AND INSTRUMENTS
The pitot-static system supplies ram air pressure to the airspeed
indicator and static pressure to the airspeed indicator, vertical speed
indicator, and altimeter. The system is composed of a heated pitot-
static tube mounted on the leadina edae of the left wina. a static
pressure alternate source valve
loca6d below the de-icelantrke sw~tcn
oanel. a drain valve located on the left s~dewall beneath tne instrument
panel; an airspeed pressure switch located behind the instrument
panel, and the associated plumbing necessary to connect the
instruments and sources.
The pitot-static heat system consists of a heating element in the pitot-
static tube, a two-position toggle switch, labeled
PITOTISTATIC HEAT,
on the de-icelanti-ice switch panel, and a "pull-off' type circuit breaker,
labeled LEFT
PlTOT HEAT, on the left sidewall switch and circuit
breaker panel. When the pitot-static heat switch is turned on, the
element in the pitot-static tube is heated electrically to maintain proper
operation in possible icing conditions.
A static pressure alternate source valve is installed below the
deice1
anti-ice switch panel, and can be used if the static source is
malfunctioning. This valve supplies static pressure from inside the
cabin instead of from the pitot-static tube. If erroneous instrument
.,
readings are suspected due to water or ice in the pressure line going to
the static pressure source, the alternate source valve should be pulled
on. Pressures within the cabin will vary with vents open or closed. Refer
-,
to Sections 3 and
5
for the effect of varying cabin pressures on
airspeed and altimeter readings.
~.>
A drain valve is incorporated into the system and is located on the left
r,
cabin sidewall beneath the instrument panel. The valve is used to drain
suspected moisture accumulation in the system by lifting the drain
r,
valve lever to the OPEN position as indicated by the placard adjacent
=j
to the valve. The valve must be returned to the CLOSED position prior
to flight.
r)
(Continued Next Page)
=,
=.
1
Revision
23
d
*,
U.S.
7-103
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