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% Section 34-42 for more data about the strike finder system.
%) A stormscope system, consisting of stormscope processor and stormscope antenna. Refer
% to Section 34-45 for more data about the stormscope system.
E. Dependent Positioning Determining
The DA 40 can have the following systems:
) A VOR/LOC/GS system, consisting of NAV receiver, course deviation indicator (CDI), horizontal situation indicator (HSI), and NAV antenna.
) An automatic direction finder (ADF) system, consisting of ADF receiver, ADF indicator and ADF antenna.
) Distance measuring equipment (DME), consisting of DME receiver, remote DME switch, and DME antenna.
) A transponder (XPDR) system, consisting of transponder, blind altitude encoder, and transponder antenna.
) A global positioning system (GPS), consisting of GPS receiver, GPS annunciation control unit, and GPS antenna.
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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.
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 circuit-breaker 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.
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Figure 1: Pitot-Static System Schematic Diagram
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DA 40 Series AMM  AIRCRAFT  Navigation 
%  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. 
　
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