FLIGHT MANUAL
Doc. No. SP2006FMENKT
7 - 14
December 20, 2006
Section 7
Airplane and System
Description
7.14 Pitot-static system
Pitot-static tube for sensing static and total pressure is located
under the left half of the wing. Total pressure is sensed through the
opening in the Pitot-static tube face. Static pressure is sensed
through openings on the tube circumference. System of pressure
distribution to individual instruments are made by means of flexible
plastic hoses. Transparent draining reservoirs are located in the
pressure branch of static and total pressure on the left fuselage
side by the wing leading edge.
Static pressure is led to altimeter, airspeed indicator, variometer
and altitude encoder (if installed). Total pressure is led only to the
airspeed indicator.
Figure 7
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5
Scheme of pitot-static system
