Diamond DA 40, Flight Manual

Page: 280 / 300

Airplane
Description
DA 40 AFM
Page 7 - 54 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
7.12 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 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.
In addition, some serial numbers have an alternate static valve installed on the underside
of the instrument panel. With this 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 (OÄM 40-267). %
7.13 STALL WARNING
If airspeed drops below approximately 10 to minimum 5 knots above the stalling speed, %
the stall warning horn, located in the instrument panel, will sound. The horn becomes
progressively louder the closer one gets to stalling speed. Suction at an orifice on the
left wing leading edge activates the horn via a hose. The orifice for the stall warning in
the left wing is marked by a red ring.
7.14 AVIONICS
The radio and navigation equipment is located in the central part of the instrument panel.
A transmit switch for the radio is mounted on the end of each control stick. There are
connection facilities for up to 4 headsets between the front seats.