TM 55-1520-228-10
NOTE
Removal of copilot cyclic stick can
cause pilot cyclic stick to creep
slightly aft.
a. Copilot Cyclic Stick Stowage.
NOTE
Force trim will be lost when the
electrical connector is disconnected
when stowing or removing the
copilot cyclic stick Removal is
authorized by the pilot and/or
commander (Fuel quantity gage
cannot be monitored with cyclic stick
stowed
C ).
(1) Unscrew retaining nut on cyclic stick.
(2) Secure cyclic stick on stowage pin and strap
located on the left outboard side of the center console.
b. Copilot Cyclic Stick Installation.
(1) Remove cyclic stick from stowage.
(2) Insert cyclic stick into pivot assembly on
torque tube.
(3) Secure cyclic stick in pivot assembly with
knurled nut.
(4) Ensure electrical connector is installed.
2-27. COLLECTIVE PITCH CONTROL.
WARNING
Do not use deck under collective for
storage. This could cause interfer-
ence in the full down position.
The pilot collective pitch control is located to the left of
the pilot position and controls the vertical mode of flight.
A rotating grip-type throttle and a switch box assembly
are located in the forward end of the pilot collective pitch
lever (figure 2-3 and figure 2-4). The switch box
assembly contains the starter, governor engine idle
release and landing lights switches. Friction can be
induced into the collective system by rotating a friction
device located between the pilot and copilot seats. The
copilot collective lever, located on the left of the copilot
position, contains only a twist type throttle at the forward
end of the control.
a. Copilot Collective Pitch Control Stowage.
(1) Remove the boot around copilot stick shaft.
(2) Loosen knurled nut at base of copilot stick
Remove stick.
(3) Stow stick in clips located on forward side of
copilot seat.
b. Copilot Collective Pitch Control Installation.
(1) Remove stick from stowage clips and insert
stick in jackshaft elbow assuring engagement of throttle
tube.
(2) Secure stick in elbow with knurled nut.
(3) Secure boot around stick shaft.
2-28. ANTI-TORQUE (DIRECTION) CONTROL.
Anti-torque control pedals (figure 2-3 and figure 2-4)
alter the pitch of the tail rotor blades and thereby provide
the means of directional control. Pedal adjustments are
located at the base of the pedals at floor level. Adjuster
knobs enable adjustment of pedal distance for individual
comfort.
a. Deleted.
b. Deleted.
2-29. FORCE TRIMS (FORCE GRADIENT).
Force gradient devices are incorporated in the controls.
These devices are installed in the flight control system
between the cyclic stick and the hydraulic power cylinder
(servo). The devices act to furnish a force gradient of
feel to the cyclic control stick. However, these forces
can be reduced to zero by depressing the force trim
button on the cyclic stick (figure 2-3 and figure 2-4). The
gradient is accomplished by means of springs and
magnetic brake release assemblies which enable the
pilot to trim the controls, as desired, for any condition of
flight. A FORCE TRIM toggle switch is installed in the
control panel to activate the force trim system.
Change 10 2-31
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