SECTION 7
DESCRIPTION
T B M
700 PILOT’S INFORMATION MANUAL
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Page 7.11.1
Rev. 5
7.11 – AIR DATA SYSTEM AND INSTRUMENTS (Figure 7.11.1)
Airplane air data system consists of :
– two separate static pressure systems supplying the altimeters, airspeed
and vertical speed indicators. They also provide a static pressure
reference to the ∆P cabin and to the Autopilot system Air Data Computer
(ADC).
System 1 is backed up by an alternate system which operation is
controlled by a switching valve (normal / alternate) attached to instrument
panel under R.H. control wheel. In case of obstruction or icing of ports, this
selector isolates airplane normal static system. When selector is on
alternate position (pulled rearwards), static pressure is picked from a port
located in airplane rear fuselage.
– two separate dynamic pressure systems supplying the airspeed indicators
systems, V
MO
audio warning detector and the Autopilot system Air Data
Computer (ADC).
STATIC PRESSURE SYSTEMS
Primary systems
Two dual static ports (one on either side of the fuselage tail part) supply a dual
system routed towards the cockpit.
System 1 is connected to the switching valve (normal / alternate) which
supplies the encoding altimeter, the ∆P cabin, vertical speed 1 and
airspeed 1 indicators and the Autopilot system Air Data Computer (ADC).
System 2 is directly connected to the second altimeter and optional
equipment.
Both systems feature a drain valve located under the instrument panel on
R.H. side. On static system 1, an additional drain is installed on ADC system.
It is attached under floor and attainable through emergency landing gear
door.
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