Section V. FLIGHT CONTROLS
2-34. FLIGHT CONTROL SYSTEM.
The aircraft's primary flight control system
consists of conventional rudder, elevator, and aileron
control surfaces. These surfaces are manually operated
from the cockpit through mechanical linkage using a
control wheel for the ailerons and elevators, and
adjustable rudder/brake pedals for the rudder. Both the
pilot and copilot have flight controls. Trim control for the
rudder, elevators, and ailerons is accomplished through
a manually actuated cable-drum system for each set of
control surfaces. The autopilot has provisions for
controlling the position of the ailerons, elevators,
elevator trim tab, and rudder.
2-35. CONTROL WHEELS.
operated by manually actuating either the pilot's or
copilot's control wheel (fig. 2-24). A control wheel is
installed on each side of the instrument panel. Switches
are installed in the outboard grip of each wheel to
operate the elevator trim tabs. A microphone switch,
DISPENSE switch, and an autopilot/yaw
damp/electric trim disconnect switch are also installed in
the outboard grip of each control wheel. A FLARE
DISPENSE switch is installed on top of the inboard grip
of each control wheel. A transponder ident switch is
installed on the forward side of the inboard grip of each
control wheel. Installed in the center of each control
wheel is a digital electric clock. A map light switch, and
TCS (touch control steering) switch are located adjacent
to each digital clock.
2-36. RUDDER SYSTEM.
a. Rudder Pedals. Aircraft rudder control and
nose wheel steering is accomplished by actuation of the
rudder pedals from either the pilot's or copilot's station
(fig. 2-10). The rudder pedals may be individually
adjusted, forward or aft;,' to provide adequate leg room
for the pilot and copilot. Adjustment is accomplished by
depressing the lever alongside the rudder pedal arm and
moving the pedal, forward or aft, until the locking pin
engages in the selected position.
b. Yaw Damper System. A yaw damper system
is provided to aid the pilot in maintaining directional
stability and increase ride comfort. The system may be
used at any altitude, but is required for flight above
17,000 feet. It must be deactivated for takeoff and
landing. The yaw damper system is a part of the
autopilot. The system is controlled by a YAW DAMP
switch located on the autopilot control panel. Operating
instructions for this system are contained in Chapter 3.
c. Rudder Boost System. The rudder boost
system is a torque sensing, linear actuating system. The
system utilizes a pressure transducer on each engine to
augmentation computer to monitor torque levels, and a
rudder servo to apply boost to aid the pilot.
The stability augmentation computer monitors
torque levels and airspeed to determine if boost is
required. The level of boost is proportional to the
difference in torque between each engine and inversely
approximately 50% torque differential and increases to
maximum at 100% torque differential. The level of boost
available is inversely proportional to airspeed such that
maximum rudder boost is obtained at 100% differential
and low airspeed (80 knots), while no rudder boost is
available at high airspeeds (above 180 knots).
The rudder boost system is controlled by a
switch, placarded RUDDER BOOST - OFF - YAW
CONTROL TEST, located on the pedestal extension
(fig. 2-14). The rudder boost system is powered through
BOOST, located on the overhead circuit breaker panel
2-37. FLIGHT CONTROL LOCKS.
Remove control locks before towing the
aircraft or starting engines. Serious damage
could result in the steering linkage if towed
by a tug with the rudder lock installed.
Positive locking of the rudder, elevator and
aileron control surfaces, and engine controls (POWER
levers, PROP levers, and CONDITION levers) is
provided by a removable lock assembly (fig. 2-25)
consisting of two pins, and an elongated U-shaped strap
interconnected by a chain. Installation of the control
locks is accomplished by inserting the U-shaped strap
around the aligned control levers from the copilot's side;
then the aileron/elevator locking pin is inserted through a
guide hole in the top of the pilot's control column
assembly. The rudder is held in a neutral position by an
L-shaped pin which is installed through a guide hole in
the floor aft of the pilot's rudder pedals. The rudder
pedals must be centered to align the hole in the rudder
bellcrank with the guide hole in the floor. Remove the
locks in reverse order (rudder pin, control column pin,
and power control clamp).
2-38. TRIM TABS.
Trim tabs are provided for all flight control
surfaces. These tabs are manually actuated, and
mechanically controlled by a cable-drum and jack-screw