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the ground. The light will be extinguished whenever the indicator
pointer is set within the T.O. segment. The light is disabled during
flight operations.
SYSTEM TEST SWITCH -TRIM MONITOR FUNCTION
The rotary-type system test switch, located on the pilot's instrument
panel, is used to test the trim system monitor. The monitor is tested
by rotating the system test switch to TRIM MON and depressing the
switch PRESS TEST button. When the PRESS TEST button is depressed,
a signal simulating an electrical ground fault to the pitch
trim actuator is applied to the trim monitor and the monitor will illuminate
the PITCH TRIM light.
SYSTEM TEST SWITCH -TRIM OVERSPEED FUNCTION
The rotary-type system test switch, located on the pilot's instrument
panel, is used to test the trim speed monitor. The monitor test is initiated
by rotating the system test switch to TRIM OVRSPD, initiating
primary pitch trim through either control wheel trim switch, and then
depressing the switch PRESS TEST button. When the PRESS TEST
button is depressed, a flaps down signal is applied to the trim speed
controller and a flaps up signal is applied to the trim speed monitor
simulating the high trim rate with the trim speed monitor in the low
trim rate mode. This will cause the trim speed monitor to illuminate
the PITCHTRIM light.
PITCH TRIM INDICATOR
Horizontal stabilizer position is indicated by the PITCH TRIM indicator
located in the trim indicator panel on the pedestal . The indicator
face has markings for 2° to 11° of horizontal stabilizer travel; however,
only the T.O. range markings are labeled. N DN and NUP mark-
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Learjet 31A
Pilot's Manual
ings indicate the direction of trim travel for airplane nose down and
airplane nose up respectively. The T.O. (takeoff) segment is marked
from 5.75° to 8.75°. The indicator receives horizontal stabilizer position
inputs from a potentiometer installed in the horizontal stabilizer
pitch 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.
TRIM-IN-MOTION AUDIO CLICKER
A trim-in-motion audio clicker system is installed to alert the crew of
horizontal stabilizer movement. The system will annunciate continuous
movement of the horizontal stabilizer by producing a series of
audible clicks through the headsets and cockpit speakers. The system
consists of a potentiometer in the horizontal stabilizer pitch trim actuator,
a trim-in-motion detector box, and associated aircraft wiring. As
the horizontal stabilizer actuator drives the stabilizer, the output signal
from the potentiometer is altered. The change in potentiometer
signal is sensed by the detector box. After approximately 1/4 second
of continuous stabilizer movement, the detector box will produce the
speaker and headset clicks. The trim-in-motion audio clicker system
is wired through the flap position switches and will not sound if the
flaps are lowered beyond 3°. The trim-in-motion audio clicker may or
may not sound during mach trim or autopilot trim due to the duration
of the trim inputs . Power for system operation is 28 VDC derived
from the 5-amp WARN HORNS circuit breaker on the copilot's circuit
breaker panel.
ROLL TRIM SYSTEM
Roll trim is accomplished by positioning the aileron trim tab on the
inboard trailing edge of the left aileron through actuation of the roll
trim actuator. The roll trim actuator is an electrically-operated, rotarytype
actuator connected to the aileron trim tab by a push-pull rod.
The system is controlled through the pilot's and copilot's control
wheel trim switches. Trim tab position information is displayed on a
pedestal mounted indicator. The roll trim system operates on 28 VDC
supplied through the 7.5-amp ROLL TRIM circuit breaker on the pilot's
circuit breaker panel.
CONTROL WHEEL TRIM SWITCHES -ROLL FUNCTION
Each control wheel trim switch is a dual-function (trim and trim arming)
switch which controls roll trim and primary pitch trim. One
switch is located on the outboard horn of each control wheel. Each
switch has four positions: LWD, RWD, NOSE UP, and NOSE DN. The
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Learjet 31A
arming button on top of the switch must be depressed for trim motion
to occur. Actuation of either control wheel trim switch to LWD or
RWD will signal the aileron trim tab actuator to move the tab as required
to lower the appropriate wing. Actuation of the pilot's switch
will override actuation of the copilot's switch. Actuation of either
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