BRISTELL S-LSA, Руководство по техническому обслуживанию и инспекции

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12.CHAPTER
– PITOT–STATIC SYSTEM / INSTRUMENTS
Document: SLSA-MIP-5-4-0-US Date of Issue: 05/2016 Revision: -
12-2
12.1 General
This chapter provides information about pitot
–static system and instruments.
12.2 Description and operation
12.2.1 Pitot
–static system
The Pitot tube to sense total pressure is located under right wing. The total pressure is sensed
through the hole in the pitot
–tube face. Static pressure ports are located on both sides of the
fuselage, at the tail. Pressure distribution to individual instruments is performed by means of
flexible plastic hoses.
Static pressure is lead to the altimeter (ALT), airspeed indicator (ASI), vertical speed indicator
(VSI), and to the altitude encoder. The total pressure is connected just to the ASI.
Fig. 12-1
Scheme of pitot-static system
Fig. 12-2
Pitot
–static system scheme
1 - Pitot tube 2 - Static pressure ports
3 - Instruments
Date of Issue: 12/2016
Revision: 1