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switch to any of the four positions (LWD, RWD, NOSE UP, or NOSE
DN) with the trim arming button depressed will disengage the autopilot
if an autopilot CWS switch is not depressed.
AILERON TRIM INDICATOR
Aileron trim tab position indication is provided by the AIL TRIM indicator
located in the trim indicator panel on the pedestal . Two semicircular
scales and pointers present the trim tab position in terms of
LWD (left wing down) and RWD (right wing down). The scale markings
represent increments of trim tab travel. The indicator receives
aileron trim tab position inputs from a potentiometer in the roll trim
actuator. The indicator operates on 28 VDC supplied through the tamp
TRIM-FLAP IND circuit breaker on the copilot's circuit breaker
panel.
TRIM INDICATOR PANEL
Figure 5-4
5- 16
PM-121
Change 1
Learjet 31A
Pilot's Manual
YAWTRIM SYSTEM
Yaw trim is accomplished by positioning the rudder trim tab on the
lower trailing edge of the rudder through actuation of the yaw trim
actuator . The yaw trim actuator is an electrically-operated, rotarytype
actuator connected to the rudder trim tab by a push-pull rod.
Yaw trim is pilot controlled through the RUDDER TRIM switch on
the pedestal. Trim tab position information is displayed on a pedestal
mounted indicator. The yaw trim system operates on 28 VDC supplied
through the 7.5-amp YAW TRIM circuit breaker on the pilot's
circuit breaker panel.
RUDDER TRIM SWRCH
Yaw trim is pilot controlled through the RUDDER TRIM switch located
on the pedestal trim control panel. The switch has three positions:
NOSE LEFT, OFF, and NOSE RIGHT. The switch knob is split and
both halves must be rotated simultaneously to initiate yaw trim motion.
When the switch is released, both halves will return to the center
OFFposition. Actuation of theRUDDER TRIM switch to NOSE LEFT
or NOSE RIGHT will signal the yawtrim actuator to move the rudder
trim tab in the appropriate direction.
PEDESTAL TRIM CONTROL PANEL
Figure 5-5
PM-121
5-17
Original
Pilot's Manual
Learjet 31A
RUDDER TRIM INDICATOR
Rudder trim tab position indication is provided by the RUDDER
TRIM indicator located in the trim indicator panel on the pedestal. A
semi-circular scale and pointer indicates the direction (L or R) of yaw
trim. The scale markings represent increments of rudder trim tab travel.
The indicator receives rudder trim tab position inputs from a potentiometer
in the rudder trim actuator. The indicator operates on 28
VDC supplied through the 2-amp TRIM-FLAP IND circuit breaker on
the copilot's circuit breaker panel.
AUTOPILOT/FLIGHT DIRECTOR SYSTEM
The Bendix/King KFC 3100 Flight Control System is installed to provide
automatic flight control and/or flight guidance for climb, cruise,
descent and approach. The system is fully integrated with the aircraft's
air data system, attitude heading reference system (AHRS),
and electronic flight instrument system (EFIS) . The system's dual
flight computers provide separate pilot and copilot flight guidance in
the pitch and roll axes. Either pilot's or copilot's flight guidance steering
commands may be coupled to the autopilot. Pitch and roll axis
change, when commanded by the autopilot, is effected through elevator
and aileron servos. The autopilot also provides pitch trim commands
to the secondary trim system motor of the horizontal stabilizer
pitch trim actuator. The system's pitch authority is limited to 10° nose
down and 20° nose up and roll authority is limited to 25° bank. The
autopilot controller, located on the glareshield, provides for engagement,
mode selection and status annunciation. Pilot inputs to the
flight control system are accomplished through the autopilot controller,
control wheel switches, Altitude/Vertical Speed Indicator, and
the EFIS controls . The pilot's autopilot/flight guidance system operates
on 28 VDC supplied through the 5-amp AP 1, and 5-amp FLT
DIR 1 circuit breakers, and 115 VAC supplied through the 1-amp AP
1 MON circuit breaker on the pilot's circuit breaker panel. The copilot's
autopilot/ flight guidance system operates on 28 VDC supplied
through the 5-amp AP 2, and 5-amp FLT DIR 2 circuit breakers and
115 VAC supplied through the 1-amp AP 2 MON circuit breaker on
the copilot's circuit breaker panel. Yaw damper and rudder boost systems
are also integrated into the KFC 3100 Flight Control System . Refer
to YAW DAMPER SYSTEM and RUDDER BOOSTSYSTEM.
5- 18
PM-121
Chance 2
Learjet 31A
Pilot's Manual
The system initiates a self-test sequence when the system is powered
　
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