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remains open, so the left battery will power the left essential bus and
left essential avionics bus, and the right battery will power the right
essential bus and the right essential avionics bus. The AFM procedure
for L and R GEN FAIL is to turn off the AV MSTR switches which will
also cause the loss of the left and right essential avionics buses.
The duration of the standard main batteries (27-amp-hour) is a
minimum of 30 minutes and the optional main batteries (38-amp-hour)
is a minimum of 60 minutes. The duration of the emergency battery
(10-amp-hour) is approximately 1 hour. Expected duration assumes
the electrical load is reduced in accordance with the L R GEN FAIL procedure
in the Emergency Section of the AFM.
Indications of a dual generator failure would be OFF captions on the
left and right MAIN bus switches, NON-ESS bus switches and GEN
switches. Also, the EMER captions on the EMER BATT switch would
be illuminated indicating the emergency battery is powering the
emergency battery bus. The OFF captions in the L and R AV MSTR will
also be illuminated when the AV MSTR switches are selected OFF per
the AFM procedure.
During a dual generator failure, both essential avionics buses, both
main buses and both main avionics buses are available by manual
selection if desired; however, this will significantly reduce the main
battery duration.
Pilot’s Manual
4-26 PM-132A
BATTERY OVERHEAT
If either nickel-cadmium main battery exceeds the established
temperature values, the crew is alerted in several different ways. First,
the Master Caution or Master Warning annunciators, depending on
battery temperature, is activated. A corresponding CAS message is
generated for a battery overheat. An amber L or R BATT OVHT
message is displayed for battery temperature exceeding 60° C and a red
message is displayed if the battery temperature exceeds 70° C. Also, if
battery temperature exceeds 70° C, a red L or R BATT OVHT annunciator
on the CWP will illuminate and the corresponding battery is automatically
switched OFF if not already switched OFF by the crew. The
battery temperature must be less than 60° C before it can again be
turned on.
If the SUMRY or ELEC system schematic is being displayed on the
EICAS or MFD displays, the digital readout of the battery temperature
for the affected battery will change color and flash. If the battery
temperature exceeds 60° C (140° F) the digital battery temperature
display will change from white to a boxed amber and if the
temperature exceeds 70° C (160° F) it will change to boxed red.
AC POWER
As part of the anti-ice protection system, left and right windshield
heaters are powered by two, left and right engine-driven alternators.
The alternators are mounted to the front of the engine accessory
section, next to the starter/generator, and operate from 6,000 to
12,000 rpm.
These alternators will supply 200-vac, 200-400 Hz at a maximum of
5kva single phase output. The alternator output is controlled by a
separate control unit that contains the monitor circuitry for the
windshield. There are no provisions for directly monitoring alternator
output on the EICAS displays, but loss of ac power from an alternator
would be detected by failure of windshield anti-ice.
The output of the alternators is only used by the windshield anti-ice.
See Section VI, ANTI-ICE & ENVIRONMENTAL for additional
information.
Pilot’s Manual
PM-132A 4-27
LIGHTING
INTRODUCTION
Lighting is used to illuminate the cockpit area and all flight
instruments. The majority of the instruments are internally lighted. For
general illumination and floodlights, Light Emitting Diodes (LEDs) are
used. Rheostatic controlled goose-neck map lights are installed on both
the left and right side panels. The standard warning lights are available
for the cabin area, and emergency lights are provided to illuminate the
exits in the event of an emergency. Exterior lighting consists of landing,
taxi, recognition, strobe, navigation, beacon, and a wing inspection
light. Optional exterior lighting consists of tail logo lights and exterior
convenience lights that illuminate the single-point pressure refueling
and baggage door areas.
GENERAL
Cockpit lighting consists of map lights, glareshield floodlights,
instrument/indicator lights, panel lights, dome lights and two cockpit
switch panels to control the lights.
Cabin lighting consists of entry, overhead, passenger table and reading
lights, galley, and lavatory lights.
Tailcone baggage lighting is provided within the baggage compartment.
　
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