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switch to indicate when the oil filter is clogged or clogging. In the event
of an impending bypass, an L or R OIL FILTER white CAS will illuminate.
The bypass valve will open when the pressure differential across
the filter reaches 35 psi (241 kPa) allowing oil to bypass the filter. Under
cold oil conditions, such as engine start, the bypass indication is inhibited
when the oil temperature is less than approximately 100° F (38° C);
however, the bypass valve will still open. This function prevents nuisance
indications during engine start due to high oil viscosity at cold
temperatures.
The following CAS illumination is specific to the engine oil system:
CAS Color Description
OIL FILTER White The associated (L or R) engine oil filter is
becoming clogged.
Pilot’s Manual
PM-132A
VENT TO
AMBIENT
BREATHER
PRESSURIZING
VALVE
OIL
RESERVOIR
OIL LEVEL
SIGHT PLUG
FILL PORT
AUX FILL
PORT
FILTER
BYPASS
VALVE OIL
FILTER
PRESSURE
REGULATOR
OIL TEMPERATURE
TRANSDUCER
OIL PRESSURE
TRANSDUCER
80 OIL PSI 80
OIL-TO-AIR
COOLERS
OIL-TO-AIR
COOLER
FUEL TEMP LIMIT
AND OIL PRESSURE
BYPASS VALVE
ALTITUDE
OIL FLOW
REDUCTION
VALVE
ENGINE DRIVEN
OIL PUMP
FUEL HEATER/ OIL COOLER ASSEMBLY
DRAIN PLUG
OIL TEMPERATURE
AND PRESSURE
BYPASS VALVE
ACCESSORY
DRIVE GEARBOX
NO. 4 AND NO. 5
BEARING CAVITY
TRANSFER
GEARBOX
FAN REDUCTION
GEARBOX
NO. 6 BEARING
SUMP
NO.1
BEARING
PLANETARY
GEARBOX
NO. 2
BEARING
NO.3
BEARING
NO. 4
BEARING
NO. 5
BEARING
ACCESSORY
DRIVE GEARBOX
ENGINE
DRIVEN PUMP
MAGNETIC
CHIP DETECTOR
OIL
RESERVOIR
NO. 6
BEARING
TRANSFER
GEARBOX
FUEL
IN
FUEL
OUT
CAS MESSAGES
OIL SUPPLY LINE
OIL PRESSURE LINE
OIL SCAVENGE LINE
VENT LINE
ELECTRICAL LINE
1. L OIL PRESS LOW (red)
2. R OIL PRESS LOW (red)
3. L ENGINE CHIP (white)
4. R ENGINE CHIP (white)
5. L OIL FILTER (white)
6. R OIL FILTER (white)
3
4
5
6
2
60 OIL C 60 1 o
OIL
FILTER
CHECK VALVE
MAGNETIC CHIP
DETECTOR AND
OVERVIEW
OIL-TO-AIR
COOLER
FUEL HEATER/
OIL COOLER
ENGINE OIL SYSTEM SCHEMATIC
Figure 2-2
2-11/2-12 (Blank)
Pilot’s Manual
PM-132A 2-13
ENGINE IGNITION AND START SYSTEMS
IGNITION SYSTEM
The engine ignition system is an integral sub-system of the engine.
Each engine consists of an ignition unit, two ignitor plugs, two shielded
high-voltage output cables and associated aircraft wiring. During normal
engine operation the system is controlled by the DEEC and is capable
of continuous operation. The DEEC powers the ignition system for
three modes of operation. The first is for normal engine start. During
normal engine start the DEEC commands ignition at >6.0% N2 and
turns ignition off when N1 = 0.7 of idle N1. The second mode is for uncommanded
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
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