曝光台 注意防骗
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deceleration, and the third mode prevents engine flameout
during rapid deceleration.
The ignition unit is a solid-state, high-voltage, capacitor-discharge unit
mounted on the fan bypass duct of each engine. The unit provides a
spark rate of 2 sparks per second at an output of 18,000 to 24,000 volts
through the ignitor plugs. The ignitor plugs are located on the combustor
plenum at the 4 and 8 o’clock positions. These iridium plugs are
linked to the ignition unit by separate high-voltage cables and spark
when pulsed by the ignition unit.
The ignition system is powered by 28-vdc from the L and R ESS buses
through the CH A and CH B circuit breakers located within the ENGINE
groups (respective L and R IGN) of the pilot’s and copilot’s circuit
breaker panels.
IGN SWITCHES
The L and R IGN switches, located in the respective ENGINE panel of
the pedestal, are used to obtain continuous engine ignition. The switch
controlling the left engine ignition system is labeled L IGN. The switch
controlling the right engine ignition system is labeled R IGN. When an
IGN switch is placed in the ON position, 28-vdc is applied to the engine
ignition unit.
IGN INDICATIONS
The EI will display a green, white, and amber IGN. The green EI represents
normal ignition activity. A white EI is generated if one ignitor
plug is not firing. The amber EI alerts the pilot of dual ignitor plug
failure.
Pilot’s Manual
2-14 PM-126A
ENGINE START SYSTEM
A combined starter/generator is mounted on the front of the accessory
gearbox. For normal starts, the DEEC provides for automatic starting
which allows the thrust lever to be moved into the IDLE position before
activating the starter. When the respective L or R START switch is momentarily
depressed, the DEEC begins the start sequence by activating
the corresponding standby fuel pump and energizing the starter relay
closed. The starter relay connects electrical power to the starter from
the respective L or R GEN bus. Power to the GEN buses is supplied
from the aircraft batteries, an external power source, or an Auxiliary
Power Unit (APU) (if installed).
An external power source or APU is recommended for starts when ambient
temperature is 32° F (0° C) or below. Ensure an external power
source supply is regulated to 28-vdc, has adequate capacity for engine
starting and is limited to 1500 amps maximum. Allow the operating
generator amperage to decrease below 300 amps prior to a generator
cross-start. Refer to Cold Weather Operation, AFM, for additional information
when operating in extremely cold weather.
START SWITCHES
The L and R START switches, located in the respective ENGINE panel
of the pedestal, are guarded momentary action switches that illuminate
ON when depressed indicating the starter relay is energized.
START INDICATIONS
During engine starts, a vertical START green or amber EI will appear.
The green EI represents normal starter activity. The amber EI represents
an engine starter engaged with N2 greater than 51%.
Pilot’s Manual
PM-126A 2-15
ENGINE INDICATING (EI)
ENGINE VIBRATION MONITOR
The engine vibration monitor system consists of an accelerometer
mounted on each engine and a tailcone-mounted engine vibration
monitor signal conditioner. The vibration monitor signal conditioner
consists of two identical independent channels.
Each channel is powered by the corresponding 3-amp L or R VIB MON
circuit breaker located within the ENGINE group of the respective pilot’s
or copilot’s circuit breaker panels.
The following CAS illumination is specific to the engine vibration monitor
system:
OIL TEMPERATURE INDICATOR
Oil temperature is displayed for each engine as a white digital readout.
The display consists of an OIL ° C legend with temperature readouts to
the left and right. An engine-mounted transducer transmits oil temperature
signals to the DAU. The DAU then provides an oil temperature
value for EICAS. Refer to the following table for temperature ranges
and corresponding color displays during normal engine operation:
CAS Color Description
ENG VIB MON White Vibration level, in the associated (L or R)
engine, is higher than normal.
ALTITUDE
FT
WHITE
°C
AMBER
°C
RED
°C
<30,000 30 to 127 -53 to 29
-60 to -54
and
128 to 175
>30,000 30 to 140 -53 to 29
-60 to -54
and
141 to 175
Pilot’s Manual
2-16 PM-126A
OIL PRESSURE INDICATOR
Oil pressure is displayed for each engine as a digital readout on EICAS.
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