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Windshear warnings are given for decreasing headwind/increasing
tailwind and/or down-draft.
The system consists of the GPWS computer, a biaxial accelerometer, a
set of annunciator light/switches on the instrument panel at each crew
position, "FAIL" annunciators on the center instrument panel, a flap
position override switch, and associated aircraft wiring . Voice warnings
are made through the cockpit speakers and the headphones. The
system receives inputs from the #1 air data computer, #1 AHRS,Lstall
warning vane, radio altimeter, #1 nav receiver (G/S), nose gear down
and locked switch, and the left flap 13° and 25° switch . The system operates
on 115 VAC supplied through the 1-amp GPWS/WNDSHR circuit
breaker on the pilot's circuit breaker panel.
Refer to the applicable AFM supplement for further details and operating
instructions.
5-813 PM-121
Change 4
Learjet 31A
Pilot's Manual
ENHANCED GROUND PROXIMITY WARNING SYSTEM WITH
WINDSHEAR WARNING (EGPWS) (OPTIONAL)
The AlliedSignal Enhanced Ground Proximity Warning System
(EGPWS) provides the pilot with aural and visual warnings of possible
terrain (or obstacle) proximity, excessive deviation below ILS glideslope,
and for detection of severe windshear conditions. The EGPWS
also provides aural alerts for descent below pre-defined altitudes during
final approach, including a minimum descent altitude awareness
callout and excessive bank angle alerting.
The EGPWS extends the Ground Proximity Warning (including Altitude
Awareness Callouts and Bank Angle Alerting) and Windshear Detection
functionality of previous GPWS systems by adding Terrain (or
Obstacle) Awareness Alerting and Display (TAAD) (including "Peaks
Mode") and Terrain Clearance Floor (TCF) functions.
The system consists of: the EGPWS computer; a set of annunciator
light/switches located on the instrument panel at each crew position; a
flap override switch, an inhibit terrain switch, an inhibit glideslope
switch and a test switch (all located in the pedestal); terrain not available,
TCAS fail, TCAS standby annunciators and terrain display on
switch (all located on the center instrument panel); and the associated
aircraft wiring. Voice warnings are made through the cockpit speakers
and the headphones. Voice warnings generated by the EGPWS will
have priority over voice warnings generated by the TCAS (if installed).
Terrain data may be displayed on the MFD. The system receives inputs
from ADC, AHRS, stall warningvane, NAV receiver, the FMS, the radio
altimeter, the nose gear down and locked switch, and the left flap 13°
and 25° switches . The system operates on 28 VDC supplied through the
5-amp GPWS/WNDSHR circuit breaker on the pilot's circuit breaker
panel.
Refer to the applicable AFM supplement for further details and operating
instructions.
PM-121
Change 4
5-8C
Learjet 31A
Pilot's Manual
MACH TRIM SYSTEM
The Mach trim system provides automatic pitch trim in response to
Mach changes to increase longitudinal stability and counteract the
center-of-lift movement at speeds above approximately 0.70 MI if the
autopilot is disengaged or inoperative. The system consists of a computer,
a trim followup, MACHTRIM annunciator and associated aircraft
wiring. The Mach trim system utilizes the primary motor of the
horizontal stabilizer pitch trim actuator to effect trim changes. The
Mach trim computer operates on 115 VAC supplied through the lamp
MACHTRIM circuit breaker on the pilot's circuit breaker panel
and 28 VDC supplied through the 20-amp primary pitch trim current
limiter.
During flight, with neither autopilot engaged, the Mach trim system
will automatically engage at approximately 0.70 MI. As the aircraft
Mach number changes, the change is sensed by the air data computers
and transmitted to the Mach trim computer. If the aircraft is not
retrimmed to compensate for the Mach change, the Mach trim computer
will command the appropriate pitch trim change (nose up for
increased Mach and nose down for decreased Mach ) through the horizontal
stabilizer pitch trim actuator. A followup on the horizontal
stabilizer will transmit a horizontal stabilizer position signal to the
Mach trim computer. Stabilizer trim motion will cease as the followup
stabilizer position signal cancels the pitch trim signal from the Mach
trim computer. A monitor is installed to disengage Mach trim in the
event of a malfunction. If the monitor disengages Mach trim and
Mach is above 0.78 My the overspeed warning horn will sound. The
Mach trim system is resynchronized whenever either pilot manually
　
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