Section 7
Airplane and System
Description
PILOT’S OPERATING HANDBOOK
7-16
2015-07-20
Doc. No. POH-20101308
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 is made by means of
flexible plastic hoses.
Static pressure is led to altimeter, airspeed indicator, vertical speed indicator and
altitude encoder. Total pressure is led to the airspeed indicator.
Transparent draining reservoirs are located in the pressure branch of static and
total pressure on the left fuselage side by the wing leading edge.
It is necessary to keep the system clear to ensure its correct function. Both hose
systems (total and static) are equipped with condensate reservoirs located inside
the cockpit in front of the left pilot's seat under. These reservoirs are visible and
can be checked from outside the fuselage bottom. If water appear in the
condensate reservoirs, unscrew the covers from the reservoirs and slightly blow
into the Pitot-static head. Then screw the covers back and check the packing.
CAUTION
AVOID
BLOWING
INTO
THE
PITOT-STATIC
SYSTEM WITH THE CONDENSATE RESERVOIR
COVER IS CLOSED - IT MAY CAUSE AN
INSTRUMENT MALFUNCTION.
Summary of Contents for SportStar MAX
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