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to the planetary gearbox. The fuel heater/oil cooler is of a liquid-to-liquid
design utilizing the engine lubricating oil as a source of heat to
warm the fuel. This heat transfer conversely cools the oil.
Fuel heater/oil cooler faults are detected by the Data Acquisition Unit
(DAU). The DAU interprets the temperature as a function of engine oil
temperature and uses the result to illuminate a CAS message.
The following CAS illuminations are specific to the fuel heater/oil
cooler:
CAS Color Description
FUEL HEATER Amber The fuel heater, on the associated (L or R)
engine, is not keeping the fuel warm enough.
FUEL HEATER White The fuel heater, on the associated (L or R)
engine, is heating the fuel too much.
Pilot’s Manual
2-10 PM-126A
ENGINE OIL SYSTEM
Oil for engine lubrication is drawn from the engine oil tank by the oil
pump. The oil is output from the pump through a filter, a pressure regulator
valve, an oil-to-air cooler, and a fuel heater/oil cooler. The oil-toair
cooler is a three-segment, finned cooler that forms the inner surface
of the fan duct. From the oil-to-air cooler, the oil flow is divided so that
part of the oil is directed to the accessory drive and transfer gearboxes,
and the engine shaft bearings. The remaining oil is diverted to a fuel
heater/oil cooler and then to the planetary gearbox.
The oil filter assembly incorporates a bypass valve and an electrical
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 plugged.
Pilot’s Manual
PM-126A 2--11
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
A79-0001
ENGINE OIL SYSTEM SCHEMATIC
Figure 2-2
2-11/2-12 (Blank)
Pilot’s Manual
PM-126A 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
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