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NOTE: The conditions just described assume that both
BATTERY switches are in theOn position.
If only the BATTERY 1 switch is On, the auxiliary
hydraulic pump will not be available and the DC
voltmeter will display the voltage of the LH (#1)
battery. All other conditions will be as described.
If only the BATTERY 2 switch is On, Primary
Pitch Trim will not be available and the DC voltmeter
will display the voltage of the RH (#2) battery.
All other conditions will be as described.
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Learjet 31A
Pilot's Manual
AVIONICS POWER SYSTEM
An avionics power system is installed to allow selected DC powered
avionics systems to be powered up through the use of two master
switches. The system consists of a LEFT MASTER and RIGHT MASTER
switch, and two control relays. The control relays operate on 28
VDC supplied through the corresponding 1-amp AV MASTER circuit
breaker in the associated circuit breaker panel. The AVIONICS MASTER
switches have no effect when EMER BUS is selected and the generators
are off-line.
AVIONICS MASTER SWITCH
The LEFT MASTER switch is installed in the pilot's switch panel and
the RIGHT MASTER switch is installed in the copilot's switch panel.
These two switches allow the crew to turn certain avionic equipment
off and on without using the individual systems' switches.
Refer to the Airplane Flight Manual for a listing of equipment controlled
by the MASTER switches. The actual equipment affected may
vary with customized wiring options.
EMERGENCY POWER SYSTEM
The aircraft is equipped with an emergency power system to supply
electrical power to selected equipment in the event of a normal electrical
power system failure. Power for the emergency power system is
supplied by two emergency power units located in the nose avionics
compartment. Each emergency power unit contains a 12-cell lead-acid
battery to provide electrical power. The emergency power supply batteries
are trickle charged from the aircraft normal electrical system
through the 7.5-amp EMER BATcircuit breakers on the pilot's and copilot's
circuit breaker panel.
The emergency power system will provide electrical power for the
standby attitude gyro, fan speed (N1) indicators, landing gear position
lights, and selected instrument lights (standby attitude gyro, N1 indicators,
standby airspeed indicator, standby altimeter, standby HSI and
magnetic compass) . Operating times of equipment powered by EMER
BAT 1 power supply is presented in the Airplane Flight Manual. The
EMER BAT 2 power supply provides 2 - 11 minutes of backup power
for the Attitude Heading Reference System (AHS 1 & 2). The system is
controlled through the EMER BAT 1 and EMER BAT 2 switches on the
pilot's switch panel. An amber EMRPWR 1 and EMR PWR 2 annunciator
on the center instrument panel will illuminate whenever electrical
power from the associated emergency power supply is being used.
PM-121
4-21
Change 3
Pilots :Manual
Learjet 31A
EMER BAT SWITCH
The EMER BAT switches have two positions: On (EMER BAT 1 or 2)
and OFF. With the switch in the On position, electrical power from the
emergency power supply is applied to the standby attitude gyro and
　
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