Pilot's Operating Handbook
Section 7
Description
Edition 0 - October 31, 2013
Rev. 6
Page 7.11.1
7.11 - Air data system and instruments - see figure 7.11.1
Air
plane air data system consists of :
- two separate static pressure systems supplying an electronic standby indicator
and air data computers (ADC).
A part of 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 electronic standby
indicator and air data computers.
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 part, which is connected to the switching valve (normal / alternate), supplies
the ΔP cabin and the electronic standby indicator. The system remainder directly
supplies one of the air data computers.
System 2 is directly connected to the second ADC.
Systems feature a drain valve located under the instrument panel on R.H. side.
Alternate static source
The alternate static port located in the rear fuselage supplies a system routed to the
switching valve (normal / alternate) in order to replace static system 1.
The alternate line incorporates a drain plug located under the instrument panel on
R.H. side.
Static pressure from alternate line is only provided to standby instrument.
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