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SYSTEM TEST Switch-ADC Function ......... ................................ 5-44
Takeoff Configuration Monitor System .............................................. 5-44
Audio Control System ........................................................................... 5-45
Audio Control Panel .......................................................................... 5-45
TRANSMIT SELECT Switch .......................................................... 5-45
MIC SELECT Switch ....................................................................... 5-46
Volume Controls .............................................................................. 5-46
Speaker Switch ................................................................................5-46
Mixer Switches ................................................................................5-47
BOTH/VOICE/IDENT Switch .....................................................5-48
MICRHI/LO Switch .......................................................................5-48
Audio Control-Flight Operation ..................................................5-48
Flight Management System ..................................................................5-49
UNS-1B Flight Management System/
KFC 3100 Flight Control System Interface .................................. 5-49
Enroute .............................................................................................5-49
Enroute VNAV .................................................................................5-50
Approach Mode (Lateral) ..............................................................5-50
Approach Mode (Vertical) .............................................................5-51
Learjet 31A
Pilot's Manual
FLIGHT CONTROLS
The primary flight controls (ailerons, elevator, and rudder) are mechanically
operated through the control columns, control wheels, and
rudder pedals. The flaps and spoilers are hydraulically operated and
electrically controlled . Aircraft trim systems (pitch, roll, and yaw) are
electrically operated and controlled.
AILERON AND ELEVATOR
Movement of the control columns and control wheels is mechanically
translated into elevator and aileron control surface movement
through systems of cables, pulleys, and push-pull rods. In addition to
aileron control, the control wheels incorporate switches that control
normal trim, pitch-axis interrupt, rudder boost interrupt, autopilot
and yaw damper disconnect, autopilot control wheel steering (CWS)
function, flight director dear, microphone keying, transponder ident
function, and nose-wheel steering engage and disengage circuits.
Control wheel switch functions are discussed under the applicable
system.
RUDDER
FLIGHT SYSTEMS
Rudder pedal movement is mechanically translated into rudder control
surface movement through a system of cables, pulleys, and bellcranks.
Nose-wheel steering, when engaged, is electronically controlled
by the pedals and braking maybe accomplished by depressing
the upper portion of the pedals .
PM-121
5-1
Original
Pilot's Manual
Learjet 31A
CONTROLS GUST LOCK
Acontrols gust lock is provided to help prevent wind gust damage to
the mvable control surfaces. When installed, the lock provides security
by holding full rudder, full aileron, and full down elevator.
CONTROLS GUST LOCK
Rgure S-1
141LSA
5-2
PM-121
Original
Learjet 31A
Pilots Manual
FLAPS
The hydraulically-actuated, electrically-controlled flap system provides
flap settings of UP V), 8°, 20°, and DN (40°). The single-slotted
flaps are attached to the rear wing spar with tracks, rollers, and hinges.
The flap selector switch controls a solenoid-operated hydraulic
control valve that meters hydraulic pressure to the flap actuators. The
actuators mechanically rotate sectors attached to the flaps through adjustable
push-pull tubes. Interconnecting cables and pulleys synchronize
flap movement throughout the range of travel . A flap position
switch is mechanically connected to each flap sector. These
switches provide flap position information to the landing gear warning,
stall warning, spoiler warning, trim-in-motion warning, takeoff
configuration monitor system, and rudder boost systems. A flap limit
switch is mechanically connected to each sector to automatically
maintain flap position at the selected setting. The flap control system
operates on 28 VDC supplied through the 3-amp FLAPS circuit breaker
on the copilot's circuit breaker panel. The flap control system is operative
during EMER BUS mode.
FLAP SELECTOR SWITCH
The flap selector switch is located on the right side of the pedestal
　
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