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Navigation Lights................................................................................ 4-36
Anti-Collision Lights (Beacon/Strobe)............................................. 4-37
Wing Inspection Light ........................................................................ 4-37
Exterior Convenience Lights (Optional) .......................................... 4-38
Tail Logo Lights (Optional)................................................................ 4-38
Pilot’s Manual
PM-132A 4-1
ELECTRICAL POWER SYSTEMS
INTRODUCTION
Primary dc electrical power is provided by two engine-driven starter/
generator units supplying 28-vdc power to a split bus electrical system.
The generators are limited to 300 amps. An automatic electrical load
shedding system has been incorporated to prevent generator overloading
and prolong battery duration 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 instrumentation. A single emergency battery is provided to power
standby equipment in case of airplane electrical system failure and to
power certain 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 airplane
batteries.
The 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.
GENERAL
The electrical system incorporates a split, multiple bus system for
power distribution interconnected by contactors, fuses, and circuit
breakers which react automatically to isolate a malfunctioning circuit.
Manual isolation is also possible by turning off power to an affected
bus via the electrical control panel or by opening the appropriate circuit
breakers.
SECTION IV
ELECTRICAL & LIGHTING
Pilot’s Manual
4-2 PM-132A
In the event of a dual generator failure, the main airplane batteries may
be used to power the essential, essential avionics and hot bus
components for a limited period of time. An emergency battery is also
provided to operate equipment connected to the emergency battery
bus and emergency hot bus.
It is possible to power the dc electrical systems from the airplane
batteries, engine driven generators, or a Ground Power Unit (GPU).
MAIN BATTERIES
Two main electrical system batteries are located, one above the other, in
the tailcone. The upper battery is connected to the left generator bus
when selected On via the L BATT switch and the lower battery is
connected to the right generator bus when selected On via the R BATT
switch. The main batteries provide a source of electrical power for
engine starting and for emergency operation in the event of dual
generator failure. They also provide power to three hot buses and two
emergency hot buses even when the batteries are selected off.
The standard batteries installed are 24-vdc nickel-cadmium (NICAD)
rated at 27-amp-hours. Optional 38-amp-hours NICAD batteries may
also be installed.
Gases produced by the main batteries are vented overboard through
two tubes. The end of the tubes are cut at an angle so that one tube takes
air in and the other exhausts the gases from the battery cases.
Electrical power from each battery is used to close the corresponding
battery contactor when the L and R BATT switches are selected On.
When the battery contactors are closed, the main batteries are
connected to the respective generator bus. When the airplane is on the
ground, the battery contactors are controlled by voltage sensors to
prevent discharge below 14 volts. If a battery is below 14 volts, the
contactor will not close when the BATT switch is selected On. If the
battery voltage falls below 14 volts for more than 10 seconds while on
the ground, the contactor will open. Battery depletion protection is
inhibited when airborne and during engine starting on the ground. If
the batteries are above 14 volts, they can be connected and recharged
from a GPU, or aircraft generator.
Pilot’s Manual
PM-132A 4-3
Individual battery voltages can be read on the SUMRY or ELEC
schematic displays which are selectable on the EICAS or MFD display
units.
Battery temperature monitoring and overtemperature warning for
NICAD batteries are provided via the EICAS/MFD displays and the
Crew Warning Panel (CWP). The above is described further under
ELECTRICAL SYSTEM INDICATORS in this section and under
　
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