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mounting position and connect the cables to
the relay connector.
(2) Connect the external power relay to the
firewall:
− Install the bolt, washer, and nut that
attach the relay to the firewall.
(3) Connect the cable to the external power
relay:
− Move the cables into position at the
external power relay.
− Install the nuts and washers that attach
the cables to the electrical power relay.
(4) Connect the main battery. Refer to Chapter 24-31.
(5) Do a test for the correct operation of the
external power relay.
DA20-C1 AMM
Electrical Power
Doc # DA201-C1
Rev. 4 24-60-00 Page 1
12 Jan 2001
CHAPTER 24-60
DC ELECTRICAL LOAD DISTRIBUTION
1. General
The DC electrical load distribution system has these components:
Component Identification
− Avionic master relay AM2460-03
− AVIONIC MASTER switch AM2460-04
− Battery relay BB2430-02
− Circuit-breakers
− GEN/BAT switch (See also Chapter 24-30) GC2430-02
See Chapter 24-30 for the generator system.
Electrical Power
DA20-C1 AMM
Page 2
19 Dec 1997 24-60-00 Doc # DA201-C1
Rev. 0
Figure 1 - DC Electrical Load Distribution Simplified Schematic Diagram
DA20-C1 AMM
Electrical Power
Doc # DA201-C1
Rev. 13 24-60-00 Page 3
30 Apr 2008
2. Description
A. Main Bus
The main bus has 3 parts: 3 copper bars are joined by a hard-wired connection. The generator
supplies the main bus through the GEN circuit-breaker. The battery supplies the main bus
through the battery relay, ammeter and BATTERY circuit-breaker.
The battery supplies a positive voltage to the coil of the battery relay. The GEN/BAT switch
connects to the other side of the battery relay and to ground.
The main bus supplies the airplane electrical systems through circuit-breakers.
B. Avionic Bus
The normally-closed contacts of the avionics master relay connect the main bus to the avionic
bus. A 20 amp circuit-breaker protects the system. A 1 amp circuit-breaker protects the control
circuit for the relay. The control circuit of the avionics master relay connects to the AVIONIC
MASTER switch.
C. Circuit-Breakers
Reference: Figure 2 and Figure 3.
Note: Figure 2 and Figure 3 illustrate typical instrument panel configurations. For aircraft
with installed optional equipment refer to the specific aircraft’s wiring diagram.
Circuit-breakers protect the wiring in each circuit from too much current. The circuit-breakers
are located on the right side of the instrument panel. You can open and close all of the circuitbreakers
manually. If too much current flows in a circuit, the related circuit-breaker opens
automatically.
As an option some aircraft may be equipped with a “Reversed Panel” in which the circuit
breakers are located on the left side of the panel.
3. Operation
When the GEN/BAT switch is ON, it gives a ground to the battery relay coil. The battery relay
closes and connects the battery to the main bus through the circuit-breaker.
When the AVIONIC MASTER switch is OFF, the control circuit is closed. If there is power on the
Main bus, the avionics master relay energizes. The avionics master relay contacts open. The
avionic bus disconnects from the main bus.
Electrical Power
DA20-C1 AMM
Page 4
12 Jan 2001 24-60-00 Doc # DA201-C1
Rev. 4
Figure 2 - Typical Circuit-Breaker locations on the Instrument Panel
DA20-C1 AMM
Electrical Power
Doc # DA201-C1
Rev. 4 24-60-00 Page 5
12 Jan 2001
Intentionally left blank
Electrical Power
DA20-C1 AMM
Page 6
12 Jan 2001 24-60-00 Doc # DA201-C1
Rev. 4
Figure 3 - Typical Reversed Instrument Panel Circuit–Breaker Locations
AVIONICS
CONTROL
GEN.
MARKER DME
ELECTRICAL
GEN. BATTERY
ADF HSI
OIL PRESS
FUEL PRESS
ENGINE
POSITION
NAV/COM
STROBE
LIGHTS
TAXI/MAP
CONTROL ICS
MASTER MASTER
LANDING
ATC
AVIONICS
2
INST.
FLAPS TRIM
SLIP
SYSTEM
O.A.T.
FUEL QTY. TURN
&
START
SYSTEM
1
GPS/COM
HORIZON DG
PUMP
FUEL
HEAT
PITOT
75.4L/19.7 US gal.
Usable
EGT
OIL TEMP TACH.
12:45
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