SOCATA TB20GT, Pilot'S Information Manual, Page: 184 / 213

SECTION 7
DESCRIPTION
SOCATA
MODEL TB 20
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Contents
June 30, 1988
Revision 5
7.51
AIR CONDITIONING
(if installed)
See Section 9 ”Supplements”.
OXYGEN SYSTEM
(if installed)
See Section 9 ”Supplements”.
AIRSPEED INDICATING SYSTEM AND INSTRUMENTS
The airspeed indicating system (see Figure 7.19 ) supplies pitot air pressure
to the airspeed indicator or to the true airspeed indicator and a static air
pressure to the airspeed indicator or to the true airspeed indicator, the vertical
speed indicator and the altimeter.
The system consists of a pitot, which can be heated, located on the lower
surface of the L.H. wing, two static ports located on L.H. and R.H. side of aft
fuselage, a static system drain located on the wings splicing.
The pitot heating system (if installed) is controlled by a switch–breaker
located on the central pedestal.
The alternate static source (if installed) is controlled by a knob located on the
L.H. strip, this knob controls a valve which supplies static pressure from
inside the cabin.
Refer to Sections 3 ” Emergency procedures ” and 5 ” Performance ” of this
manual for the pressure variations influence on instruments indication.
When stopped, protect the static ports and pitot with covers.
TRUE AIRSPEED INDICATOR (if installed)
The true airspeed indicator is fitted with a rotable ring which works in
conjunction with its dial in a manner similar to a flight computer.
To set the indicator, first rotate the ring until pressure altitude is aligned with
outside air temperature.
To obtain pressure altitude, set the barometric scale of the altimeter to
29.92 in.Hg (1013.2 hPa) and read pressure altitude. Pressure altitude
should not be confused with QNH altitude.