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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.
AIRCRAFT
Electrical Power DA 40 Series
AMM
Page 4
20 Sep 2007 24-00-00 Doc # 6.02.01
Rev. 5
VOLTAGE REGULATOR MAIN BUS
ANNUN. AVIONIC BUS
ALT. PROT.
ALT. CONT.
ALT.
MAIN TIE
ALT
ALTERNATOR CURRENT SENSOR
START
START
BATT
BATT
BATT
EXTERNAL POWER
BATTERY
24 V
11 AMP HRS
STARTER
160 A
ALTERNATOR
28 V / 70 A
OVERVOLTAGE
PROTECTION
AVIONIC
BUS
ESSENTIAL
AVIONIC
BUS
ESS TIE
ESS AVIONIC
ESS BUS
MASTER CONTROL
AVIONIC
ESSENTIAL BUS
Figure 2: Simplified Schematic Diagram, Electrical System with Essential Bus
AIRCRAFT
DA 40 Series
AMM
Electrical Power
Doc # 6.02.01
Rev. 5 24-00-00 Page 5
20 Sep 2007
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.
AIRCRAFT
Electrical Power DA 40 Series
AMM
Page 6
20 Sep 2007 24-00-00 Doc # 6.02.01
Rev. 5
Strobe/Position Light
Strobe/Position Light
Strobe Light Power Supply
Strobe Light Power Supply
Compass Flux Valve
Fuel Probe RH
Fuel Probe LH
Flaps
Hobbs Meter
Door Swich
Canopy Switch
Fuel
Pump
Relay
Box
Regulator
Alternator
Battery
External Power Socket
Pitot
Landing Light
Taxi Light
Figure 3: Component Location Diagram
AIRCRAFT
DA 40 Series
AMM
Electrical Power
Doc # 6.02.01
Rev. 5 24-01-00 Page 1
20 Sep 2007
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:
24-33. Electrical Power Generation.
% 24-34. Battery System.
% 24-35. Emergency Battery System.
24-41. External Power.
24-61. Power Distribution.
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.
AIRCRAFT
Electrical Power DA 40 Series
AMM
Page 2
20 Sep 2007 24-01-00 Doc # 6.02.01
Rev. 5
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Figure 1: 14 VDC Electrical System Schematic Diagram
AIRCRAFT
DA 40 Series
AMM
Electrical Power
　
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