Airplane Description
66Diamond
~,p'
AIRCRAFT
DA42AFM
7.11
PITOT-STATIC SYSTEM
Total pressure is measured at the leading edge
of
a Pitot probe und er the left wing. Static
pressure is measured
at
two orifices
at
the lower and rear edges
of
the same probe. To
protee! against dirt and condensation the
re
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
li
ne. lt is supplied electrically and provides a stail warning, before the angle
of
attack
becomes
critical. The stail status is announced to the pilot by a continuous sound
in
the
cockpit.
The
lift detector va ne, the mounting plate and the complete housing are heated to prevent
icing. Heating is engaged together with the
Pitot heating.
Page
7-68
Rev. 8
15-Dec-2017
Doc. No. 7.01 .05-E
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