FlightSafety LEARJET 45 - INTRODUCTION

INTRODUCTION
Primary DC electrical power is provided by two engine-driven starter/generator units
rated at 30 volts, and limited to 300 amperes each. These generators supply 28 VDC power
to a split bus electrical system. An automatic electrical load shedding system has been
incorporated to prevent generator overloading and prolong battery discharge in the event
of a single or dual generator failure. Secondary DC electrical power is supplied by two
main airplane batteries that will power essential avionics, communication and instru-
mentation. A single emergency battery is provided to power standby equipment in case
of airplane electrical system failure and to power certain voltage sensitive equipment
that must remain powered during engine start.
A ground power unit can provide electrical power for system operation prior to engine
start, to assist in engine start and to charge aircraft batteries. Additionally, an optional
APU may be installed to provide for systems operation on the ground and for engine start.
AC electrical power is provided by two engine-driven alternators for the sole purpose
of powering the windshield ice and fog protection system. The alternators are rated at
200 VAC, 200-400 Hz, 5KVA.
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AMPS
R
R
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AMPS
GEN
R
AMPS
APUEXT PWR
A
28.0
38
GEN
C
28.0
100AMPS
L
35
28.2
L ESS VOLT EMER BUS VOLTS
R ESS VOLT
BATT TEMPS
0
100
LEARJET 45 PILOT TRAINING MANUAL
CHAPTER 2
ELECTRICAL POWER SYSTEMS
2-1
FOR TRAINING PURPOSES ONLY
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