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C. Batteries:
(See Figure 6 Sheet 8, Figure 13, Figure 14, Figure 15 and Figure 17.)
Two 24 VDC, 40 ampere-hour rated, nickel-cadmium (nicad) batteries
provide supplementary DC power to the aircraft. Each battery is installed
inside its own fireproof stainless steel enclosure in the aft equipment
compartment. Access to the batteries is from outside the aircraft through a
removable panel; this same panel having two smaller access doors for
visual inspection and quick access to the terminal connectors and sense/
control cables.
The 20 internal cells inside each battery are designed to prevent spillage in
any position and will vent any gases to the battery casing. Each casing in
turn vents to the atmosphere through its own venting system.
A cooling and circulation fan is installed in each battery compartment. Both
fans receive power from an inverter unit through a thermal switch in the
battery compartment. The inverters receive power from the batteries when
either or both battery switches are on or from the battery chargers when
they are receiving power from the Left and Right Main AC buses. When
battery compartment temperature reaches 90°F (32° C), the thermal switch
closes and the cooling and circulation fan operates. As temperature drops
to 75° F (24° C), the thermal switch opens and the fan stops.
The batteries are controlled from the cockpit by BATT 1 and BATT 2
switchlights, located on the EPMP, on the cockpit overhead panel. From
outside the aircraft, the batteries are controlled by the OUTSIDE BATTERY
switch, located below the battery access panels. They may also be
controlled from an EXTERNAL BATTERY switch, located in the forward
external switch panel, if installed. Selection of any battery switch connects
the batteries to the Battery Tie bus and their respective battery bus.
Selection of the OUTSIDE BATTERY switch (or EXTERNAL BATTERY
switch, if installed) to ON provides battery power to operate the auxiliary
hydraulic pump, in order to close the main entrance door, or operate the
landing gear wheel well doors. It also provides power to operate the engine
oil replenisher pump or start the APU. Whenever either of the external
switches is selected ON, a blue EXT BATT SW annunciator on the cockpit
overhead panel will illuminate. If CAS is operating, a blue EXT BATT
SWITCH ON message will be displayed. In addition, the lower anti-collision
beacon is illuminated as an exterior visual reminder that the batteries are
on.
From inside the aircraft, the batteries are controlled by the BATT 1 and
BATT 2 switchlights. Both switches normally remain selected ON during all
phases of flight, capable of providing power to the Essential DC bus if no
other power source is available (DC external power, TRU or converter). If
CAS is operating, selection of either BATT switchlight to OFF causes an
amber EPMP BATT SW OFF message to be displayed.
OPERATING MANUAL
2A-24-00 PRODUCTION AIRCRAFT SYSTEMS
Page 50
May 30/02
Revision 7
Selection of the BATT 1 and/or BATT 2 switchlight to ON powers the
respective battery bus and connects it to the Battery Tie bus. In addition,
the associated battery charger is activated. If AC power is not available, the
associated amber CHGR FAIL light illuminates on the EPMP (Figure 6). If
CAS is operating, an amber BATT 1-2 CHGR FAIL message is displayed.
Aircraft SN 1465 and subsequent and aircraft with ASC 54 incorporated
have individual control over batteries and chargers.
As mentioned previously, power from the Battery Tie bus can be supplied
to the Essential DC bus, if necessary. Automatic connection will take place
provided the following conditions are present:
• Left and Right Main AC buses unpowered
• Left and Right Main DC buses unpowered
• No other power source available
• All EPMP AUTO/SEL switchlights in AUTO
In this configuration, the Essential DC bus will be powered by the Battery
Tie bus and Phase A of the Essential AC bus will be powered by the
E-inverter.
In situations where the EPMP is manually configured, hard selection of the
ESS DC BUS BATT switch (Figure 0) to ON will also connect the Battery
Tie bus to the Essential DC bus.
In situations where the main batteries are the only source of power to the
Essential DC bus, an amber BATT ON BUS caution message will be
displayed on CAS. On SPZ-8000 equipped airplanes with ASC 415
incorporated, an amber DC ESS ON BATT caution message will be
displayed on CAS.
D. Battery Chargers:
(See Figure 1, Figure 6, Figure 13 and Figure 14.)
Each battery has its own dedicated charger in the aft equipment
compartment. The No. 1 battery charger is powered by the Left Main AC
　
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