Maintenance Manual STEMME S10-VT
Date of Issue: Jan. 01, 1998
Page 3-33
Amendment Nr. 0
Date: --
A4011121_B23.doc
Doc. No. A40-11-121
3.6 Flight Control Instruments, Pitot Static System (Fig. 3.6.a,b)
Instruments: see equipment list.
CAUTION:
For modifications sections 3.8 and 9 must be observed.
Pitot pressure, static pressure and total energy compensation are measured by means of a bar probe in the
propeller dome. The ducts are directed to the instrument panel through the propeller dome sliding tube. Static
pressure measured by the bar probe may not be used for the airspeed indicator!
Static pressure for the airspeed indicating system is exclusively measured on both sides of the tail boom.
This duct is also directed to the instrument panel.
NOTE:
Some instruments, e. g. Bohli-diaphragm-type rate-of-climb indicator, need additional static ports for
proper operation at the widest area of the forward fuselage. These additional static ports are only
installed, if they were required for instrumentation at time of delivery.
All hose lines of the pitot-static system are equipped with a water separator/filter in the front cockpit area
below the instrument panel.
Fig. 3.6.a: Pitot and Static Pressure System
