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The emergency power system provides electrical power to the emergency
buses to power flight instruments and other equipment essential for flight
safety in the event of total loss of electrical power. The amount of time the
emergency power system can operate is dependant upon the load placed
on the emergency buses, however, a minimum of forty (40) minutes can be
expected.
The emergency power system consists of two emergency battery units,
each composed of a power module, battery and control module. The power
module contains a battery charger, heater switching circuits and charger
fault circuits. The battery module consists of a battery, battery heater and
temperature sensor. The control module has circuitry that controls both
charger and heater operation, provides fault monitoring and drives the
output signals. The forward emergency battery unit (No. 1) is located in the
right avionics rack and the aft emergency battery unit (No. 2) is located in
the tail compartment.
When the aircraft electrical system is operating normally, the Essential DC
bus supplies power to the emergency battery charging system. If both Main
DC buses are lost, charging current is inhibited.
If the Essential DC bus is lost, the emergency batteries will automatically
power the Emergency buses, wing leading edge evacuation lighting and
external overwing evacuation lighting, provided the EMERG POWER ARM
switchlight, located on the cockpit overhead panel (Figure 18), was
selected to ARM. ARM selection is verified by the switchlight’s 1NOT/2NOT
amber legends being extinguished. (The adjacent 1ON/2ON and 1OFF/
2OFF amber legends are also extinguished.) An impact switch will
automatically activate the emergency power system, regardless of any
switchlight’s position, when it senses a 2.5G or greater force.
Manual selection of the EMERG POWER ON switchlight will switch on the
emergency batteries at any time. ON selection is verified by the
switchlight’s 1ON/2ON amber legends being illuminated. Manual selection
of the EMERG POWER OFF switchlight will switch off the emergency
batteries, but the Essential DC bus must be powered during the shutdown.
OFF selection is verified by the switchlight’s 1OFF/2OFF amber legends
being illuminated.
When emergency battery temperature is below 60°F (16°C), trickle charge
mode is enabled and electric heaters warm the batteries. When battery
temperature reaches 60°F (16°C), the heaters shut off automatically and
the main charge mode is enabled.
Emergency batteries No.1 and 2 are connected to Data Acquisition Units
(DAUs) No. 1 and 2, respectively. If an emergency battery discharges
completely, a blue E BATT 1-2 DISCH message is displayed on CAS. If an
emergency battery fails, a blue E BATT 1-2 FAIL message is displayed on
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
Page 53
May 30/02
Revision 7
CAS.
Two other emergency batteries are installed on the aircraft: IRS-1 and
IRS-2. They are located in the left and right avionics racks, respectively,
and are identical to the forward and aft emergency batteries. Each IRS
battery supplies power to the associated IRS and memory keep-alive for
the associated navigation computer.
A table listing the components powered by the emergency batteries is
shown in the Controls and Indications topic of this section.
H. Emergency Power System (SN 1467 and Subsequent):
The emergency power system provides electrical power to the emergency
buses to power flight instruments, interior emergency lighting and other
equipment essential for flight safety in the event of total loss of electrical
power.
The emergency power system consists of four emergency battery units,
each composed of a power module, battery module and control module.
The power module contains a battery charger, heater switching circuits and
charger fault circuits. The battery module consists of a battery, battery
heater and temperature sensor. The control module has circuitry that
controls both charger and heater operation, provides fault monitoring and
drives the output signals. The forward emergency battery units (No. 1 and
3) are located in the right avionics rack and the aft emergency battery units
(No. 2 and 4) are located in the tail compartment. When operating, each
battery is capable of delivering 200 watts for 15 minutes and 6 amp-hours
if fully charged.
When the aircraft electrical system is operating normally, the Essential DC
bus supplies power to the emergency battery charging system. If both Main
DC buses are lost, charging current is inhibited.
If the Essential DC bus is lost, emergency batteries No. 1 and 2 will
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湾流4操作手册 Gulfstream IV Operating Manual 1(75)
