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Rev. 5
VOLTAGE REGULATOR MAIN BUS
ANNUN. AVIONIC BUS
ALT. PROT.
ALT. CONT.
ALT.
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
MASTER CONTROL
AVIONIC
Figure 1: DC Generation (simplified), Electrical System without Essential Bus
AIRCRAFT
DA 40 Series
AMM
Electrical Power
Doc # 6.02.01
Rev. 5 24-30-00 Page 3
20 Sep 2007
2. Description and Operation
Figures 1 and 2 show simplified DC electrical generation schematic diagrams.
A. Alternator
A 70 Ampère alternator attaches to the front of the engine. A flexible belt turns the alternator. A
pulley on the engine crankshaft operates the flexible belt. The alternator is the usual source of
power for the electrical system.
The output voltage from the alternator is controlled by the voltage regulator. The voltage regulator
controls the output voltage at 28 V ± 2.5 %. The output from the alternator supplies the main
electrical bus.
The alternator can supply 70 Ampères continuously at engine speeds above 2100 RPM. The
graph at Figure 3 shows the alternator performance.
The alternator has these connections:
AUX Cable Ident. 24015A20.
F1 Cable Ident. 24014A20.
+ Cable Ident. 24007A6
F2 Cable Ident. 24018A20N
The alternator will come on line when:
) The engine is operating.
) The battery, alternator control, alternator protection, alternator and voltage sense circuitbreakers
are closed.
) The ALT/BAT switch is set to ON.
AIRCRAFT
Electrical Power DA 40 Series
AMM
Page 4
20 Sep 2007 24-30-00 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: DC Generation (simplified), Electrical System with Essential Bus
AIRCRAFT
DA 40 Series
AMM
Electrical Power
Doc # 6.02.01
Rev. 5 24-30-00 Page 5
20 Sep 2007
B. Voltage Regulator
The voltage regulator is located in the engine bay. An in-line connector connects the voltage
regulator to the main cable harness.
The voltage regulator has these functions:
) Provides electrical protection for the alternator in the event of equipment failure.
) Operates a low voltage warning if the alternator voltage falls below 24 Volts.
) Operates a warning if the alternator fails or goes off line.
) Controls the output voltage of the alternator to the main electrical bus.
C. Alternator Control
These components make the alternator control system:
) ALT/BAT switch.
) Alternator control circuit-breaker.
) Voltage regulator.
Refer to Chapter 92 for the wiring diagrams.
% When the ALT/BAT switch is set to ON, a ground is supplied to the battery relay circuit which
closes the battery relay and supplies battery voltage to the main bus or, if installed, to the essential
bus. The ALT/BAT switch also connects the main bus to pin 1 of the voltage regulator. The
alternator comes on line.
The voltage regulator controls and protects the alternator. It also gives signals for the low voltage
warning system, alternator out warning system and voltage sensing.
AIRCRAFT
Electrical Power DA 40 Series
AMM
Page 6
20 Sep 2007 24-30-00 Doc # 6.02.01
Rev. 5
2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27
10
20
30
40
50
60
70
80
RPM / 100
AMPÈRES / VOLTS
volts
ampères
Figure 3: Alternator Performance Graph
AIRCRAFT
DA 40 Series
AMM
Electrical Power
Doc # 6.02.01
Rev. 5 24-30-00 Page 7
20 Sep 2007
D. Alternator Indication
These components make the alternator indicating system:
) Alternator load indicator (Integral with the integrated engine instrument).
) Alternator voltage indicator (Integral with the integrated engine instrument).
) Alternator out warning.
) Low voltage warning.
The alternator load indicator is integral with the integrated engine instrument. It shows the current
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钻石40系列AMM 1(112)
