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However, if the #1 RMU is displaying engine information due to an
automatic selection, that RMU will return to page 1 of the backup
engine display 20 seconds after the last pilot selection on the RMU.
The display of volts, amps and battery temperature on the EICAS/
MFD are color coded. As limits are exceeded, the digital data changes
color (amber or red). When the data is in its normal operating range, the
data is displayed in white. If any of the data exceeds a limit, the data
changes to the appropriate color and is boxed in that same color. The
exception to the display is when the actual battery temperature is below
-23° C (-9.4° F). Below this temperature, the EICAS/MFD will display
a flashing amber numeric display. If the actual battery
temperature falls below -25° C (-13° F), the numeric digits will be replaced
by amber dashes in a cyan box. This indicates the battery temperature(
s) is/are below the valid indicating system range, it is not a
system failure.
Pilot’s Manual
PM-126A 4-13
In certain cases, to alert the operator to a parameter exceedance or
malfunction, a color coded message will be presented in the upper right
corner of the EICAS. This section of the EICAS is known as the Crew
Alerting System (CAS). Warning messages will be in red and caution
messages will be in amber. A red or amber message will be
accompanied by flashing Master Warning (red) or Caution (amber)
light, while advisory messages will only flash in white lettering for 5
seconds and then go steady.
The crew is also alerted to certain malfunctions or conditions with
illumination of a red or white annunciator on the Crew Warning Panel
(CWP). The following annunciators relating to the electrical system are
located on the CWP:
L & R BATT OVHT (red) — Illuminates if the corresponding battery
temperature exceeds 70 degrees Celsius ( 160 degrees Fahrenheit).
GEN FAIL (red) — Illuminates if both generators are inoperative or off
line.
EMER BATT (white) — Illuminates when the emergency battery is on
and is discharging.
DISTRIBUTION
Basic dc power distribution is illustrated in Figure 4-1. With the main
airplane batteries installed, power from the left and right batteries,
through two 40-amp fuses, is always available to the “hot wired” items
connected to the rear hot bus, the left and right hot buses, and the left
and right emergency hot buses. Battery power to the left and right hot
buses also passes through a single 20-amp fuse and 15-amp circuit
breakers for each bus.
The left and right fire extinguishers and the left and right Firewall Shutoff
Valves (FWSOVs) receive power through the left and right
emergency hot buses, respectively. These items can also receive power
from the emergency battery, either engine generator, or external power
source. The tailcone utility light, Single-Point Pressure Refueling
(SPPR) and baggage compartment lights are powered through the rear
hot bus. Additional hot bus items include the cockpit overhead lights
and entry lights. The hot buses are connected directly to both of the
main batteries and to the external power connector through the left
generator bus.
Pilot’s Manual
4-14 PM-126A
Power to the radio control hot bus is controlled with a momentary action
switch on the center pedestal, just forward of the throttle quadrant.
The radio control hot bus can only be selected ON when the airplane
batteries are OFF. If the radio control hot bus is selected ON and the batteries
are subsequently selected ON, the radio control hot bus will automatically
be turned off and the ON annunciator on the switch will
extinguish. The switch is labeled RADIO CONTROL HOT BUS. When
this switch is depressed, the ON annunciator on the switch will illuminate
and main battery power through the right forward hot bus will
power the following (normal power source shown in parenthesis):
- Left audio control unit (L ESS)
- Clearance delivery radio (L ESS)
- Comm sections of the integrated communication unit #1 (L ESS)
- Nav section of the integrated navigation unit #1 (L ESS)
Pilot’s Manual
PM-126A 4-15
Ground power can be connected to the airplane as previously
described in this section under GROUND POWER UNIT. With ground
power connected, the bus-tie will automatically close and the output of
the GPU is applied to the left and right generator buses and nonessential
buses. With the main and emergency batteries selected On,
external power is distributed to the rest of the dc electrical system. The
airplane batteries (main and emergency) will then be charged from the
　
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