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AFT JBOX LMT L-R
Figure 2-1. Electrical System Schematic
DESCRIPTION
The Mustang electrical system primarily provides
28-VDC power to operate electrical devices
throughout the aircraft.
A starter-generator is used to start its respective
engine, with starting power coming from
the battery or from a GPU. Additionally, the
starter-generator of a functioning engine (with
battery assistance) can be used to start the opposite
side engine.
One generator is capable of supplying all standard
electrical requirements if a generator fails.
DC power is routed from each J-box feed bus
through individual circuit breakers to each of
the circuit-breaker buses in the cockpit CB
panels. Cockpit circuit breakers control power
to individual systems. Battery power is supplied
to a hot battery bus and then through the
battery relay to the crossfeed bus and the left
and right feed buses.
Emergency DC power is supplied from the
battery bus through the emergency power relay,
to emergency bus circuit breakers on each
cockpit CB panel when the battery switch is
in the EMER position. If the battery switch is
in the BATT position, generator power is supplied
through the battery relay to the hot battery
bus to charge the battery and from the
crossfeed bus through the emergency relay to
the emergency power buses.
The external power receptacle is underneath
the right engine nacelle.
First engine start is performed from the battery
unless using external power. The second engine
start may be powered three different ways:
• With external power (if the first generator
switch is OFF)
• From the battery (if the first generator
switch is OFF and external power is not
connected)
• From the battery with assistance from
the first generator (ground only) if the
first generator is online
Normally, when both engines are operating, the
starter-generator in each engine provides 28-
VDC power to the main bus system in the tail
cone. This bus system and its associated relays
provide connections and power management
for the battery and provide for connection to
GPUs. This bus system also allows either startergenerator
to assist the other during starting and
allows the two starter-generators to operate “in
parallel” to share the electrical load evenly.
From the main bus system in the tail cone, power
is distributed through circuit breakers in the
tail cone directly to a few electrical devices in
or near the tail cone. More power is routed forward
from the main buses through feeder cables
to the cockpit buses. Buses on each side of the
cockpit (behind the CB panels) supply power
through the cockpit circuit breakers and panel
controls to most of the aircraft electrical devices.
Cockpit indicators monitor electrical system
status and performance. Cockpit panel controls
allow the crew to directly manage the generation
and distribution of electrical power.
Relays, solid state relays (SSRs), circuit breakers,
current limiters, and generator control
units (GCUs) protect the electrical system,
and assist the crew in managing the supply and
flow of electrical power.
COMPONENTS
BATTERY
A standard lead acid battery provides 24 volts
rated at 28 amp hours. An optional NiCad battery
provides 24 volts rated at 28 amp hours.
The battery is in the tail cone compartment
(Figure 2-2). It has a manual quick-disconnect,
and is accessible through the tail cone door.
The battery connects to the battery bus. A battery
disconnect relay between the battery and
its ground provides an electrical disconnect
during certain conditions. A BATTERY disconnect
switch (Figure 2-3) is in the cockpit
on the left side console panel. This switch
opens the battery disconnect relay. Use this
CITATION MUSTANG OPERATING MANUAL
510OM-00 2-3
switch in case of a battery overheat or stuck
start relay.
NOTE
The optional NiCad battery is susceptible
to, and must be protected
from, overheat due to excessive
charging or discharging.
During an external power start cycle, to prevent
battery discharge, the battery disconnect relay
automatically disconnects the battery from its
ground. A GPU start is not a battery start.
Starting the engines with an external power
source is recommended practice to prolong
the life of the batteries and conserve battery
power for times when battery starts must be
accomplished. When it is anticipated the aircraft
will be idle for more than 2 days, it is
　
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