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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
PM-126A 4-25
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
4-26 PM-126A
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, floodlights, of the fluorescent, incandescent or
Light Emitting Diodes (LEDs) type, 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.
Tailcone maintenance lighting consists of lighting within the tailcone
equipment compartment.
Additional interior lighting consists of an emergency cabin lighting
package and optional illuminated lavatory mirror. The emergency
cabin lighting package utilizes existing overhead lights, additional exit
lights and seat base mounted floor proximity lights. The optional illuminated
lavatory mirror utilizes additional lights installed behind the
mirror.
Optional exterior lighting is available to illuminate the general areas
around the baggage compartment and the Single-point Pressure
Refueling (SPPR) area.
Pilot’s Manual
PM-126A 4-27
COCKPIT LIGHTING
Cockpit lighting is controlled through two cockpit control panels and
two Light Control Units (LCUs) that are located within the forward
avionics bay. Each LCU (pilot LCU and copilot LCU) has four separate
　
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