Table 2-3. Fuel Sump Drain Locations
Leading Edge Tank
Outboard of nacelle, underside of wing
Underside of wing, forward of aileron
Firewall Fuel Filter
Underside of cowling forward of firewall
Bottom center of nacelle forward of wheel well
Gravity Feed Line
Aft of wheel well
At wing root, just forward of the flap
Section V. FLIGHT CONTROLS
The aircraft's primary flight control systems
consist 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 con-trol for
the rudder, elevator 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.
2-36. CONTROL WHEELS.
Elevator and aileron control surfaces are operated
by manually actuating either the pilot's or copilot's
control wheel. These control wheels (fig. 2-20) are
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,
damp/electric trim disconnect switch are also installed in
the outboard grip of each control wheel. In addition, a
transponder ident switch is installed on top 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.
2-37. RUDDER SYSTEM.
a. Rudder Pedals. Aircraft rudder control and
nose wheel steering is accomplished by actuation of the
rudder pedals from either pilot's or copilot's station (fig.
2-7). The rudder pedals may be individually adjusted, in
either a forward or aft position, 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 damp system is a part of the
autopilot. Operating instructions for this system are
contained in Chapter 3. The system is controlled by a
YAW DAMP switch located in the autopilot control head.
An annunciator placarded ELEC TRIM OFF in the
caution/advisory annunciator panel indicates failure or
disconnect of the electric trim system.
c. Rudder Boost System. The RC- 12K Rudder
Boost System is a torque sensing, linear actuating
system. The system utilizes a pressure transducer on
each engine to sense engine torque oil pressure, a
stability augmentation computer to monitor torque levels
and the 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
proportional to airspeed. Boost commences at about
60% torque differential and increases to maximum
torque at 100% 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).