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Navigation
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CHAPTER 34
NAVIGATION
1. General
This Chapter tells you about the navigation systems in the airplane. It only tells you about the installation in the airplane. Refer to the equipment manufacturers' manuals for more data about the equipment and refer to the Wiring Diagrams in Chapter 92 for more data about the electrical wiring for the navigation system.
Refer to Section 23-10 for more data about the NAV system which is part of the speech communication system.
The DA 40 can have these navigation systems. Refer to these Sections for data about the systems:
Section 34-10 Flight Environment Data (Pitot-static, OAT, flight instruments).
Section 34-20 Attitude and Direction (magnetic compass, turn & bank indicator, attitude gyro, directional gyro, gyro-compass system).
Section 34-30 Landing and Taxiing Aids (localizer, glideslope, marker beacon receiver).
% Section 34-40 Independent Position Determining (strike finder, stormscope).
Section 34-50 Dependent Positioning Determining (VOR/LOC/GS, ADF, DME, transponder, GPS).
Note: Equipment which is certified for installation in the DA 40 is listed in Section 6.5 of the Airplane Flight Manual. Such equipment may be installed in accordance with the Airplane Maintenance Manual.
Any equipment which is not listed in Section 6.5 of the Airplane Flight Manual is called "Additional Equipment". The installation of Additional Equipment is a modification which must be handled in accordance with national regulations or a Service Bulletin.
2. Description
A. Flight Environment Data
The DA 40 has the usual flight environmental data systems. It has a Pitot-static system. The Pitot-static system has a Pitot-static probe located under the left wing. The Pitot-static probe has an electric heater. A switch on the instrument panel, left side, controls the Pitot heater. Flexible plastic hoses connect the Pitot-static probe to the airplane instruments.
The airplane has a static system. The static vents are integral with the Pitot probe.
Flexible plastic hoses connect the static vents to the airplane instruments.
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The Pitot-static system connects to these flight instruments:
) Altimeter.
) Airspeed Indicator (ASI).
) Vertical Speed Indicator (VSI).
) Blind Altitude Encoder. The airplane has an electronic outside air temperature (OAT) indicator. The probe for the OAT indicator is located on the right side of the fuselage aft of the co-pilot's step.
B. Attitude and Direction
The DA 40 can have the following systems:
) Magnetic compass.
) Turn & bank indicator.
) Attitude gyro (horizon).
) Directional gyro.
) Gyro compass system, consisting of:
) Slaved directional gyro.
) Magnetic azimuth transmitter.
) Slaving control unit.
) Horizontal situation indicator (HSI).
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Navigation
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C. Landing and Taxiing Aids
The DA 40 can have the following systems:
) A localizer system which is part of the VOR/LOC/GS system. Refer to Section 34-52 for more data about the VOR/LOC/GS system.
) A glideslope system which is part of the VOR/LOC/GS system. Refer to Section 34-52 for more data about the VOR/LOC/GS system.
) A marker beacon receiver which is part of the audio integrating system. Refer to Section 23-50 for more data about the marker beacon receiver functions of the audio integrating system.
% D. Independent Positioning Determining
% The DA 40 can have the following systems:
%) A strike finder system, consisting of strike finder display and strike finder sensor. Refer to
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