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two shielded cables, two igniter plugs, and associated aircraft wiring .
The ignition unit is a solid-state, high-voltage, capacitor-discharge
unit which provides a spark rate of 1 to 5 sparks per second at an output
of 18,000 to 24,000 volts. The igniter plugs are mounted at six and
seven o'clock positions in the turbine plenum. The plugs are operated
by separate cables and spark when pulsed by the ignition unit. During
the start cycle, the ignition system is automatically energized
when the thrust levers are placed in the IDLE position and automatically
deenergized at approximately 45% Turbine Speed (N2). The ignition
system maybe operated continuously through the corresponding
IGNITION switch. During the start cycle, the ignition system is
powered by 28 VDC supplied through the 7.5-amp L and R IGNSTART
circuit breakers on the pilot's and copilot's circuit breaker
panels respectively. During continuous operation, the ignition system
is powered by 28 VDC supplied through the 7.5ampLand R IGNcircuit
breakers on the pilot's and copilot's circuit breaker panels respectively.
Continuous operation is available during EMER BUS mode.
IGNITION SWITCHES
The IGNITION switches, located on the pilot's switch panel, are used
to obtain continuous engine ignition. The switch controlling the left
engine ignition system is labeled L-OFF. The switch controlling the
right engine ignition system is labeled R-OFF. When an IGNITION
switch is placed in the On (L or R as applicable) position, 28 VDC
from the corresponding L or R IGN circuit breaker is directly applied
to the corresponding engine ignition unit.
IGNITION LIGHTS
Amber lights above each IGNITION switch are installed to indicate
ignition system operation. The corresponding light will be illuminated
whenever the associated ignition system is operating either continuously
(IGNITION On) or automatically (Start cycle).
PM-121
2-9
Change 1
Pilot's Manual
Learjet 31A
ENGINE INDICATING
OIL TEMPERATURE INDICATOR
The OIL TEMP indicator is a circular-scale, dual-reading instrument
and is located on the center instrument panel. The instrument face is divided
into two semi-circular scales marked from 30°C to 180°C in 10°
increments. Each scale has a separate pointer; one for the left engine
and one for the right engine. Each pointer is operated by a resistancetype
temperature sensor in an oil supply line on the respective engine.
Electrical power for system operation is 28 VDC supplied through the
2.0-amp L and ROIL TEMP circuit breakers on the pilot's and copilot's
circuit breaker panels respectively. Refer to Airplane Flight Manual for
instrument limit markings.
OIL PRESSURE INDICATOR
The OIL PRESS indicator is a circular-scale, dual-reading instrument
and is located on the center instrument panel. The instrument face is divided
into two semi-circular scales marked from 0 to 75 PSI in 5 PSI increments.
Each scale has a separate pointer and is labeled either L or R
for the respective engine . Each pointer is operated by an oil pressure
transmitter located in an oil supply line on the respective engine . Electrical
power for system operation is 26 VAC supplied through the 0.5-
amp Land R OILPRESScircuit breakers located on the pilot's and copilot's
circuit breaker panels respectively. Refer to Airplane FlightManual
for instrument limit markings.
OIL PRESSURE LIGHTS
Red L OIL PRESS and R OIL PRESS pressure warning lights are installed
in the glareshield annunciator panel. In the event that either engine's
oil pressure drops below approximately 25 PSI (172 kPa), a
pressure switch located in the oil supply line of the affected engine will
illuminate the respective light. Also, the respective light will be illuminated
whenever electrical power is on the aircraft and the affected engine
is not operating. Electrical power for system operation is 28 VDC
supplied through the 7.5-amp WARN LTS circuitbreakers on the pilot's
and copilot's circuit breaker panels .
ENGINE CHIP LIGHTS
Illumination of either amber LENG CHIP or RENG CHIP light on the
glareshield annunciator panel indicates the presence of magnetically
permeable material in the corresponding engine's oil system. The lights
are activated by a magnetic chip detector installed in each engine's oil
pump.
2-10
PM-121
Change 3
Learjet31A
Pilot's Manual
FUEL FILTER LIGHT (AIRCRAFTEQUIPPED WITH FUEL HEATERS)
Illumination of the amber FUEL FILTER light on the glareshield annunciator
panel indicates that either an engine fuel filter or an aircraft
fuel system fuel filter is dogged or dogging and is bypassing fuel.
　
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