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unit, and GPS antenna.
AIRCRAFT
Navigation
DA 40 Series
AMM
Page 4
20 Sep 2007 34-00-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Navigation
Doc # 6.02.01
Rev. 5 34-10-00 Page 1
20 Sep 2007
Section 34-10
Flight Environment Data
1. General
This Section tells you about the Pitot-static system and the OAT indicating system in the airplane.
Refer to the manufacturers' manuals for more data about the equipment.
2. Description
Figure 1 shows the Pitot-static system schematic diagram. Figures 2 and 3 show the OAT indicators.
Figure 4 shows the equipment locations in the airplane.
% If OÄM-40-267 is carried out, the autopilot system is connected to a separate Static Source System
% in the rear part of the fuselage. Refer to Section 22-10 for more information on the static pressure
% supplied to the autopilot system.
A. Pitot-Static System
The Pitot-static system supplies Pitot pressure and static pressure to the air data instruments.
A Pitot-static probe mounted below the left wing senses Pitot and static pressure. The probe has
a heater element to prevent icing. A switch on the instrument panel controls the Pitot heat. A circuitbreaker
protects the system.
Optionally, an alternate static valve is installed below the instrument panel on the pilot's side. It is
a back-up source for static pressure when the Pitot-static probe fails.
Flexible hoses connect the Pitot-static probe to the air data instruments. Pitot hoses are green and
static hoses are blue/purple. Push-fit plastic connectors make the connections in the flexible hoses.
T-pieces make junctions in the hoses.
Both Pitot and static hoses have a water trap at the lowest part of the hose-run. T-pieces divide the
hose into two-runs. The top run goes directly to the instruments. The bottom run forms a sump
before re-joining the top-run at a tee-piece. The water traps are located below the pilot's seat and
can be accessed through the foot well in the passenger compartment.
AIRCRAFT
Navigation
DA 40 Series
AMM
Page 2
20 Sep 2007 34-10-00 Doc # 6.02.01
Rev. 5
PITOT
STATIC
PITOT
STATIC
Blind
Altitude
Encoder
Alternate
Static
Valve
VSI
A S I Altimeter
Pitot Head
Figure 1: Pitot-Static System Schematic Diagram
AIRCRAFT
DA 40 Series
AMM
Navigation
Doc # 6.02.01
Rev. 5 34-10-00 Page 3
20 Sep 2007
B. Davtron 301F (C) OAT Indicating System
Figure 2 shows the Davtron 301F (C) OAT indicator. It is located in the instrument panel, see
Chapter 31.
The OAT indicator is a digital instrument. The indicator and sensor are one unit. The indicator
operates when the ALT/BAT switch is set to ON. The probe for the OAT indicator is located on the
right side of the fuselage aft of the co-pilot's step.
Figure 2: Davtron 301F OAT Indicator
(Davtron 301C: indicates degrees Centigrade, otherwise identical)
C. Davtron M803 Digital Chronometer with OAT Indication
Figure 3 shows the Davtron M803 digital chronometer with OAT indication. It is located in the
instrument panel, see Chapter 31. Refer to Section 31-20 for the chronometer functions of the unit.
The OAT indicator is a digital instrument, and is included in the Davtron M803 Digital Chronometer.
The indicator operates when the ALT/BAT switch (Lycoming version) or ELECTRIC MASTER key
switch (TAE version) is set to ON. The probe for the OAT indicator is located on the right side of
the fuselage aft of the co-pilot's step.
Figure 3: Davtron M803 Digital Chronometer with OAT Indication
AIRCRAFT
Navigation
DA 40 Series
AMM
Page 4
20 Sep 2007 34-10-00 Doc # 6.02.01
Rev. 5
Blind Altitude
Encoder
Pitot/Static Tube
Water Traps
Pitot Probe
OAT Probe
Figure 4: Component Locations
AIRCRAFT
DA 40 Series
AMM
Navigation
Doc # 6.02.01
Rev. 5 34-10-00 Page 101
20 Sep 2007
Trouble-Shooting
1. General
The table below lists the defects you could have with the flight environment data system. If you have
the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the
repair given in the Repair column.
Trouble Possible Cause Repair
Altimeter lags or reads
incorrectly. VSI reads
incorrectly.
Faulty indicator.
Blocked or kinked static hose.
Water in the system.
Replace the indicator.
Clear the hose.
Drain the water.
Airspeed indicator reads low. Faulty indicator.
Blocked or kinked Pitot hose.
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钻石40系列AMM 2(72)
