Specifications

SECTION II
MODEL 560 AIRPLANE AND SYSTEMS
RUDDER
Rudder control is effective at all flight speeds. Full rudder deflection is 22°, ±1° either side of
center. The rudder trim is mechanically operated by the rudder trim wheel on the center pedestal. With the
rudder in the trail position, the trim tab will deflect 10° , ±1° left and right. In addition to mechanical
actuation, the rudder trim is servo-connected to assist in rudder movement. When the rudder moves to the
left, the trim tab will servo to the right, assisting in pushing the rudder trailing edge to the left. When the
rudder moves to the right, the trim tab will servo to the left, assisting in pushing the rudder trailing edge to
the right. For each degree of angular displacement of the rudder, the trim tab will move approximately one-
half degree in the opposite direction. A rudder-aileron interconnect operates in conjunction with the primary
controls. When the pilot inputs left rudder command, the torsion bungee imposes a left roll torque to the
aileron system. A left roll input likewise produces a left yaw response. Right inputs effect corresponding
responses to the right.
NOSE GEAR STEERING
The nose gear is mechanically steered by the rudder pedals to 20° either side of center. Steering is
accomplished through a mechanical linkage that allows the nose gear to center before entering the wheel
well on retraction. Additional castering of the nose wheel can be achieved against a bungee in the steering
linkage by application of differential power and braking. For ground handling and towing, maximum
deflection of the nose wheel is 95° either side of center.
SPEED BRAKES
The speed brakes are installed on the upper and lower surfaces of each wing to permit rapid rates of
descent without exceeding V
MO
/M
MO
and to spoil lift during landing roll. The speed brakes are electrically
controlled and hydraulically actuated by a switch located on the throttle quadrant and may be selected to
the fully extended or fully retracted positions. The angular travel for the upper speed brake panels is 58°,
±2°. The lower speed brake panels extend and retract through a interconnecting linkage with the upper
panels.
When the speed brakes switch is positioned to EXTEND, electrical power is applied to close the
bypass valve in the hydraulic system return line and open the speed brake control valve. This allows
hydraulic fluid at 1500 PSI to flow to the extend side of the speed brake actuators. Once the speed brakes
are extended, the speed brake control valve closes to create a hydraulic lock and hold the speed brakes
extended. The bypass valve opens and the hydraulic system returns to an open center condition. Moving
the speed brakes switch to RETRACT again pressurizes the system, and the speed brake control valve
allows fluid to go to the retract side of the speed brake actuators.
Figure 2-17. Flight Controls
I 56OMB-01 Configuration AA 2-33