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ELEVATOR DISCONNECT
Figure 5-2
Pilot’s Manual
5-4 PM-126A
The elevator aft disconnect is an electro-mechanical device located in
the top of the vertical stabilizer. When the ELEV DISC T-handle is
pulled, a two-position linear actuator on the elevator aft disconnect assembly
is energized to the extended position (disconnected position),
separating operation of the two elevators. The linear actuator will remain
in the extended position. When the elevator aft disconnect is actuated,
the elevator disconnect sensor will send a signal to display a
message on the Crew Alerting System (CAS). Do not reconnect. Obtain
maintenance prior to next flight. Electrical power used by the elevator
disconnect system is through the ELEV DISC circuit breaker located on
the pilot’s circuit breaker panel (FLIGHT group).
The following CAS illuminations are specific to the elevator disconnect:
RUDDER
Directional control is provided by a dual closed-loop cable system with
separate parallel paths in the engine area for rotor burst considerations.
Rudder pedal movement is mechanically translated into rudder control
surface movement through cables, pulleys, and bellcranks. There is an
electrically driven rudder boost system to provide additional rudder
control power in the event of an engine-out on takeoff.
RUDDER PEDAL ADJUSTMENT SWITCHES
The pilot’s and copilot’s rudder pedals are individually adjustable with
a spring-loaded toggle switch to accommodate differences in crew size.
The pilot operated toggle switch controls a linear actuator which provides
forward and aft pedal adjustment. This toggle switch is labeled
RUDDER PEDAL, and located on the lower outboard corner of the pilot’s
and copilot’s switch panel. Each switch has three positions: FWD,
Off, and AFT. Only the FWD and AFT positions are labeled. The rudder
pedal adjustment is powered by 28-vdc supplied through two 3-amp
circuit breakers, L RUD ADJUST and R RUD ADJUST, on the pilot’s
and copilot’s circuit breaker panels (FLIGHTgroup).
CAS Color Description
ELEVATOR DISC Amber Elevator disconnect has split the elevator
controls on the ground. Obtain maintenance
prior to flight.
ELEVATOR DISC White Elevator disconnect has split the elevator
controls during flight. Do not reconnect.
Pilot’s Manual
PM-126A 5-5
RUDDER BOOST
The rudder boost system is provided to reduce rudder forces. Signals
from force sensors in both sets of rudder pedal mechanisms are read by
the ICs. The ICs then send rudder boost signals to the yaw damper servo.
Rudder boost provides yaw servo torque proportional to rudder
pedal force, when either the pilot’s or copilot’s rudder pedal force or
the sum of their forces reaches 50 pounds. The rudder boost will override
the yaw damper (if engaged) when this threshold is reached. When
the force on the rudder pedals is released, the yaw damper will resume
operation. The rudder boost system is armed when flap extension is
greater than 3° and the RUD BOOST switch is selected to On. The RUD
BOOST switch is located on the forward pedestal. When selected On,
the switch is dark and when selected OFF, OFF will be displayed in the
center of the switch. A white CAS illuminates when the switch is OFF
or the system is disabled by the IC or the yaw force interface box. An
amber CAS illuminates when the system is inoperative and not selected
OFF.
Dual, redundant power inputs are provided via the RUD FORCE circuit
breaker on the right essential bus and the NOSE STEER COMPUTER
circuit breaker on the left essential bus. If both these power sources
should fail, the #2 IC-600 will disable rudder boost and provide appropriate
annunciation.
The following CAS illuminations are specific to the rudder boost
system:
CAS Color Description
RUD BOOST INOP Amber Rudder boost is inoperative and not selected
OFF. Do not takeoff.
RUD BOOST INOP White Rudder boost is selected OFF. Do not takeoff.
　
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