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the fuel entering the fuel filter element. Operation of the fuel heater is
automatic and no crew action is required.
ENGINE SYNCHRONIZER
The engine synchronizer system consists of theR ENG indicator, two
ENG SYNC switches, an amber ENG SYNC light, and an engine synchronizer
control box. During flight, the engine synchronizer, if selected,
will maintain the right engine Fan Speed (Nl) or Turbine
Speed (N2) in sync with left engine Fan Speed (Nl) or Turbine Speed
(N2). The engine synchronizer may be used whenever both fuel computers
are operating. However, the engine synchronizer must not be
used during takeoff, landing, or single-engine operations . Engine synchronizer
authority at takeoff and idle power settings is zero. Engine
synchronizer authority at all other power settings is limited to approximately
2.5%; therefore, the engines must be manually synchronized
to within approximately 2.5% before selecting SYNC. Electrical
power for the engine synchronizer is 28 VDC supplied through the 5-
amp R FUEL CMPTR circuit breaker on the copilot's circuit bmaker
panel.
ENG SYNC SWITCHES
Two ENG SYNC switches are installed on the pedestal immediately
below the thrust levers . The ENG SYNC control switch is labeled
SYNC-OFF and the ENG SYNC selector switch is labeled TURB-FAN.
With both FUEL CMPTR switches On, the ENG SYNC control switch
will activate the engine synchronizer when moved to SYNC. When
SYNC is selected, Fan Speed (Nl) or Turbine Speed (N2) synchronization
is selected by moving the ENG SYNC selector switch to TURB or
FAN as desired. When the engine synchronizer is OFF, the selector
switch controls the display parameter of the R ENG indicator.
L.eazjet 31A
Pilot's Manual
R ENGINDICATOR
TheR ENG indicator, on the instrument panel, provides an indication
of right engine synchronization with left engine Fan (Nl) or Turbine
(N2) speed. The indicator indicates fan sync when the ENG SYNC selector
switch is in the FAN position and turbine sync when the ENG
SYNC selector switch is in the TURB position . The indicator can be
used to manually synchronize the engines when the ENG SYNC control
switch is OFF or to monitor the engine synchronizer when the
ENG SYNC control switch is in SYNC. The RENG indicator is operative
whenever the right fuel computer is operating.
ENG SYNC LIGHT
The amberENG SYNC light on the glareshield annunciator panel will
be illuminated whenever the nose gear is down and the SYNC-OFF
switch is in theSYNC position. The light will alert the pilot to deenergize
the engine synchronizer for takeoff and landing.
ENGINE OIL SYSTEM
Oil for engine lubrication is drawn from the engine oil tank by the engine-
driven oil pressure pump. The oil is output from the pump
through a pressure-regulating valve, a filter, a fuel heater (optional),
and to the oil-to-air heat exchanger. The exchanger is a three-segment,
finned cooler that forms the inner surface of the fan duct. From the
oil-toair heat exchanger, the oil flow is divided so that part of the oil
is directed to the accessory and transfer gearboxes and the engine
shaft bearings. The remaining oil is diverted to an oil temperature
regulator (oil-to-fuel heat exchanger) and then to the fan gearbox. The
oil filter assembly incorporates a bypass valve and indicator to indicate
when the oil filter is clogged or clogging. In the event the filter
becomes clogged, the red bypass indicator button will pop out and
the bypass valve will open, allowing oil to bypass the filter. Under
cold oil conditions, such as engine start, the bypass indicator button is
locked in; however, the bypass valve will still open. The oil bypass indicator
button is visible through a small, circular, push-to-open door
on the engine nacelle.
Pilot's Manual
Learjet 31A
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Learjet 31A
Pilot's Manual
ENGINE IGNITION SYSTEM
Each engine ignition system consists of an IGNITION switch, an amber
ignition light, a thrust lever idle position switch, an ignition unit,
　
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