INTRODUCTION
This chapter contains a description of the electrical power system used on the Hawker 800 XP,
including information on the DC and AC systems. The DC system consists of storage, genera-
tion, distribution, and monitoring DC power. The AC system consists of generation, distribu-
tion, and monitoring of the constant-frequency (inverter) and the variable-frequency (alternator)
AC systems. Also included in this chapter are specific limitations.
GENERAL
Basic electrical power of the Hawker 800 XP
is provided by the DC system. This system
consists of two 30-volt, 400-ampere brush-
type starter-generators, one on each engine.
An additional starter-generator is available
from the auxiliary power unit (APU). Two
main airplane batteries are provided. Two
additional batteries are also provided, one
for standby instrument power and the other
for emergency avionics power. The DC sup-
ply from the generators and batteries has a
positive polarity and uses the low-resistance
bonded airframe as a return current path.
Power from the two main generators and the
APU generator is distributed to the airplane
systems via a split bus bar system. A gener-
ator control unit (GCU) in each generator
circuit stabilizes the bus bars at 28.0 volts.
With the generators on line, manual selection
of a BUS TIE switch enables the system to be
paralleled or split into two single-channel
systems. Automatic splitting occurs when a
bus bar protection unit voltage sensor de-
tects undervoltage or overvoltage conditions.
#1 SERVO
SYSTEM
BATT HOT
BAT OFF
AC
GEN
#1 DC
GEN
#1 ENG
OIL PL
CHAPTER 2
ELECTRICAL POWER SYSTEMS
2-1
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
Summary of Contents for 800 XP
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