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the aircraft DC distribution system in the event the external power
source exceeds approximately 33 volts. Ground power unit amperage,
must be limited to a maximum of 1000 amps.
4-10
PM-121
Change 3
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Learjet 31A
Pilot's Manual
AC POWER DISTRIBUTION
*Aircraft 31-035 fihru 31-060,31-062 thru 31-065
Electrical power for aircraft and avionics systems requiring AC current
is supplied through two 115-volt, 400-Hz, 1000 VA solid-state inverters.
During normal operation, the left and right inverter output
voltages are applied to the left and right AC buses respectively. The
left and right AC buses may be interconnected through the 10-amp
AC BUS TIE circuit breaker/switch on the copilot's circuit breaker
panel. An optional auxiliary (third) inverter may be installed. The
auxiliary inverter (if installed) output voltage may be applied to either
the left or right AC bus. The normal operating configuration is:
1) L and RAC buses are separated (ACBUS TIE Open); 2) L and Rinverters
are On, 3) auxiliary inverter (if installed) is Off. The auxiliary
inverter is used as a standby unit in case the left or right inverter malfunctions.
Each AC bus is intended to be powered by only one inverter.
Therefore, the AC BUS TIE switch should only be closed after removing
power from one of the buses and setting the respective
INVERTER switch to OFF. Also, the auxiliary inverter (if installed)
should only be switched into an AC bus after setting the applicable
INVERTER switch to OFF. The inverter interlock box will not allow
two operating inverters to connect to one bus. Likewise, if the Land R
AC buses are powered up and the AC BUSTIE is then closed, the interlock
box does not allow the two buses to tie together. A phase lock
box keeps the output of each inverter in-phase. Each inverter also has
a separate 163-volt output which is used to power the windshield defog
system . Input power to operate the left and right inverters is 28
VDCsupplied from the left and right generator buses respectively. Input
power for the auxiliary inverter is supplied from the battery
charging bus.
Overload sensors are installed for each inverter to protect the associated
inverter from damage due to an overload . Basically, each overload
sensor is a 60-amp, thermal-type circuit breaker, mechanically
connected to a switch. Should an overload condition occur, the circuit
breaker will reposition the switch to de-energize the power relay
thereby removing DC input power to the affected inverter . Additionally,
the switch will apply a ground to trip the affected inverter's control
circuit breaker. When the overload sensor circuit breaker cools,
the switch will reset; however, the power relay will not energize due
to the open control circuit breaker. After the malfunction has been
corrected and the affected inverter control circuit breaker has been reset,
the power relay will energize and the affected inverter will come
back on line.
Autotransformers are installed to provide power for aircraft and avionic
systems requiring 26 VAC. The autotransformers are supplied
115 VAC through the respective 2-amp 26 VAC BUS circuit breaker
on the pilot's or copilot's circuit breaker panels.
PM-121
4-13
Change 2
Pilot's Manual
Learjet 31A
*Aircraft 31-061, 31-066 & subsequent
Electrical power for aircraft and avionics systems requiring AC power
is supplied through two 115-volt, 400 Hz, 1500 VA, solid state inverters.
During normal operation, the left and right inverter output voltages
are applied to the left and right AC buses respectively. The left
and right AC buses may be interconnected through the 15-amp AC
BUS TIE circuit breaker/switch on the copilot's circuit breaker panel.
Each AC bus is intended to be powered by only one inverter. Therefore,
the AC BUS TIE switch should only be closed after removing
power from one of the buses and setting the respective INVERTER
switch to OFF. If the L and R AC buses are powered up and the AC
BUSTIE is then closed, a relay located in the copilot's circuit breaker
panel does not allow the two buses to tie together . A phase lock function
　
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