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within the right inverter keeps the output of each inverter inphase.
Each inverter also has a separate 163-volt output which is used
to power the windshield defog system, Power for aircraft and avionic
systems requiring 26-volt input is provided by each inverter through
the inverter interlock box to each corresponding 26 VAC bus. Input
power to operate the left and right inverters is 28 VDC supplied from
the left and right generator buses respectively.
Overload sensors are installed for each inverter to protect the associated
inverter from damage due to an overload. Basically, each overload
sensor is an 80-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 inverters 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.
INVERTER SWITCHES
Left and Right Inverters. Operation of the left and right inverters is
controlled through the two INVERTER switches on the pilot's switch
panel. The switch controlling the left inverter is labeled L-OFF and
the switch controlling the right inverter is labeled R-OFF. When either
switch is moved to the On (L or R) position, the associated power relay
is energized to supply input power to the associated inverter . The
inverter control circuits operate on 28 VDC supplied through the 2-
ampL INV and R INV circuit breakers on the pilot's and copilot's circuit
breaker panels respectively.
4-14
PM-121
Change 2
Learjet 31A
Pilot's Manual
Auxiliary Inverter (if installed): Operation of the auxiliary inverter (if
installed) is controlled through the AUX INV switch on the pilot's
switch panel. The switch has three positions: L, R, and OFF. When the
switch is set to L or R, the auxiliary inverter power relay will be energized
to supply input power to the inverter. Inverter 115 VAC output
will be directed to the LAC BUSor RAC BUS through the inverter interlock
box and the LAUXAC BUS or RAUX AC BUS circuit breaker
depending upon whether L or R was selected. The auxiliary inverter
control circuits operate on 28 VDC supplied through the 2-amp AUX
INVcircuit breaker on the copilot's circuit breaker panel.
AC CIRCUIT BREAKERS
The aircraft AC electrical circuits are protected by push-to-reset magnetic-
type circuit breakers. Aircraft 31-035 thru 31-060, 31-062 thm 31-
065, AC circuit breakers are denoted by a white ring on the panel overlay.
Aircraft 31-061, 31-066 and subsequent, white rings on the overlay denote
AC circuit breakers not on the EMER BUS, and segmented red/
white rings on the overlay denote AC circuit breakers on the EMER
BUS. The copilot's circuit breaker panel also contains theAC BUS TIE
circuit breaker/switch which is used to tie theLAC BUS andRAC BUS
together in the abnormal situation of single inverter operation. Circuit
breakers are grouped together into system types (e.g. ELECTRICAL,
LIGHTS, AVIONICS).
ELECTRIC POWER MONITOR
An electric power monitor is installed on the pilot's instrument panel
to monitor left and right AC bus voltage, left and right DC generator
load, and the DC charging bus voltage. Digital displays are used for
voltage and amperage readouts. Each parameter being monitored is divided
into Normal, Caution and Warning ranges . Refer to airplane
Flight Manual for instrument range description. Whenever any parameter
goes from the normal range to the caution range, the indicator's
amber light and affected parameter will flash. If the parameter
progresses into the warning range, the indicator's red light and affected
parameter will flash. The amber ELEC PWR light (annunciator panel)
will illuminate (steady or flashing) anytime an amber or red light on the
indicator is illuminated (steady or flashing). Whenever any parameter
goes into the warning range, the MSTR WARN lights will flash. Depressing
the amber or red light, as applicable, will cause the lights and
displays to stop flashing. Depressing either MSTR WARN light will
cancel the flashing of red warnings, the affected parameter, and the amber
ELEC PWR light. The amber or red light will remain illuminated
(steady) until the affected parameter returns to the normal range. Cau-
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