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2-1 Electrical System Schematic .................................................................................... 2-2
2-2 Battery ...................................................................................................................... 2-4
2-3 Battery Disconnect Switch....................................................................................... 2-4
2-4 GPU Receptacle ....................................................................................................... 2-5
2-5 Aft J-Box .................................................................................................................. 2-6
2-6 CB Panels ................................................................................................................. 2-8
2-7 Battery, Generator, and Ignition Switches ............................................................. 2-10
2-8 CAS Messages ....................................................................................................... 2-12
2-9 Electric Display (Normal)...................................................................................... 2-12
TABLE
Table Title Page
2-1 Emergency Bus Items............................................................................................... 2-7
CITATION MUSTANG OPERATING MANUAL
CITATION MUSTANG OPERATING MANUAL
2-iv 510OM-00
INTENTIONALLY LEFT BLANK
INTRODUCTION
This chapter provides a description of the electrical power system on Citation Mustang
aircraft (Figure 2-1). The DC system consists of storage, generation, distribution, and
system monitoring. Provision is also made for a limited supply of power during emergency
conditions in flight and connection of a ground power unit (GPU) while on the
ground.
GENERAL
Direct current provides the principal electrical
power for the Citation Mustang. Normal
aircraft system voltage is 28.5 VDC. Two generators
are the primary power sources (one
generator is capable of supplying all standard
requirements). Secondary sources (battery or
external power) may also be used.
Normal distribution of DC power is via a left
and right feed bus connected by a crossfeed
bus. This arrangement allows either generator
to power the entire system or, working in
parallel, to share the system load.
The battery and emergency buses normally
tie to the main system, but they may isolate to
only the battery or external power sources.
When the aircraft is on the ground, an external
DC power unit may supply electrical power
to all buses.
#1 SERVO
SYSTEM
BATT HOT BAT OFF
AC
GEN
#1 DC
GEN
#1 ENG
OIL PL
CITATION MUSTANG OPERATING MANUAL
CHAPTER 2
ELECTRICAL POWER SYSTEMS
510OM-00 2-1
CITATION MUSTANG OPERATING MANUAL
2-2 510OM-00
R
SHUNT
BUS
R
START
#1
R
START
#
2
EMERG PWR
CB BUS
R AVN EMERG
R FEED BUS #1
R ELE #2 R ELE #1
R FEED BUS #2
R SSR #1 BUS BAR
R ELE EMERG
MASTER
INTERIOR
SSR
R AVN
#1 SSR
L AVN
SSR
R AVN
#2 SSR
L
BOOST
SSR
R
BOOST
SSR
INTERIOR BUS
R AVIONICS #1 R AVIONICS #2
BATTERY
BATTERY BUS
L FEED BUS #1
L FEED BUS #2
L ELE #1 L ELE #2
AVN EMER
SSR LEFT
L SSR #1 BUS BAR
L AVIONICS
L AVN EMERG
L ELE EMERG
L
SHUNT
BUS
L
ST
A
RT
#1
R SSR #2 BUS BAR
CROSSFEED BUS
STANDBY
BATTERY
PACK
L
START
#
2
T
A A
A
V
V V
L GEN
RELAY
R GEN
RELAY
L DC
AMPS
R DC
AMPS
100 AMP
A/C COMP
100 AMP
W/S DEICE
50 AMP
FLAPS
50 AMP
HYD PUMP
100 AMP
W/S DEICE
START
RELAY
START
RELAY
AFT J-BOX
CIRCUIT BREAKERS
L CB
PANEL
R CB
PANEL
EXT PWR
RELAY
EXT PWR
CONNECTOR
L STARTERGENERATOR
R STARTERGENERATOR
INT
DISC
NORM
STANDBY
INST
SWITCH
BATT
DISC
RELAY
BATT
AMPS
BATT
VOLTS
R GEN
VOLTS
L GEN
VOLTS
BATT
TEMP
SENSOR
STBY INST
OFF
BATT TEST
EMER BUS
RELAY
BATT
POWER
RELAY
200
AMP
200
AMP
LEGEND
BATTERY POWER
GROUND
BATT O’TEMP
GEN OFF L–R
BATT TEMP FAIL
AFT JBOX CB L-R
　
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