Airplane Description DA 42 AFM
Page 7 - 68 Rev. 8 15-Dec-2017 Doc. No. 7.01.05-E
7.11 PITOT-STATIC SYSTEM
Total pressure is measured at the leading edge of a Pitot probe under the left wing. Static
pressure is measured at two orifices at the lower and rear edges of the same probe. To
protect against dirt and condensation there are filters in the system, which are accessible
from the wing root. The Pitot probe is electrically heated.
With the alternate static valve, the static pressure in the cabin can be used as static
pressure source in the event of a failure of the Pitot-static system.
If an autopilot system is installed, additional static sources may be installed.
7.12 STALL WARNING SYSTEM
The lift detector of the DA 42 is located on the front edge of the left wing below the wing
chord line. It is supplied electrically and provides a stall warning, before the angle of attack
becomes critical. The stall status is announced to the pilot by a continuous sound in the
cockpit.
The lift detector vane, the mounting plate and the complete housing are heated to prevent
icing. Heating is engaged together with the Pitot heating.
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