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The alternator attaches to the front of the engine. A flexible belt turns the alternator. The alternator supplies power to the airplane. The power supplied by the alternator is controlled by the voltage regulator.
The battery is located on the front side of the firewall, on the right side.
An additional emergency battery system is installed in the IFR model (refer to Section 24-32).
An electrical system with essential bus is optional.
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.
Doc # 6.02.01 Page 1
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DA 40 Series
Electrical Power
AMM

AVIONIC

VOLTAGE REGULATOR
MAIN BUS

BUS

Figure 1: Simplified Schematic Diagram, Electrical System without Essential Bus
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Electrical Power
AMM

Figure 1 shows a simplified schematic diagram of the electrical power system without essential bus. Figure 2 shows a simplified schematic diagram of the electrical power system with essential bus.
The electrical system has a 24 Volt, 11 amp-hour battery. The battery supplies DC to the electrical system when the alternator is not operating. It also supplies power for engine starting. The battery can also supply power when the load is more than the alternator can supply.
The battery supplies heavy current for starting through the battery relay and the starter relay. The circuit has no protection. Circuit-breakers or fuses protect all other circuits. The ALT/BAT switch controls all electrical power sources in the system. Electrical bus bars distribute the power to the consumer systems.
%  When the optional essential bus system is installed, then an ESS BUS switch is installed in the instrument panel. In the event of an electrical failure it can be set to ON. When it is set to ON, only those items of electrical equipment which are needed for the safe continuation of flight are supplied with power.
Doc # 6.02.01 Page 3
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Electrical Power
AMM

AVIONIC
VOLTAGE REGULATOR MAIN BUS
BUS

Figure 2: Simplified Schematic Diagram, Electrical System with Essential Bus
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Electrical Power
AMM

2. Component Identification
All electrical components are identified in accordance with the ATA 100 specification. For example: OV2430-02
) OV  Over voltage sensor. 
) 24:  Chapter 24  Electrical Power. 
) 30:  Section 30  DC Generation. 

3. Component Location
Figure 3 shows the location of the main components in the electrical power system.
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AMM

Figure 3: Component Location Diagram
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Electrical Power
AMM

% Section 24-01 % Electrical Power - TAE 125 Diesel Engine % 1. General
% The DA 40 with the TAE 125 Diesel engine has a 14 VDC electrical system. This section describes % the complete system from the power supplies to the circuit-breakers or other interface with the % consumers.
% This Chapter has only simplified schematic diagrams and location diagrams. Refer to Chapter 92 for % the wiring diagrams. Refer to the related Chapter for data about systems. For example, refer to % Chapter 80 for data about the starter system.
% For Trouble-Shooting and Maintenance Practices for this system, refer to these sections:
　
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