RUDDER CONTROL SYSTEM
The rudder is hinged from the rear of the ver-
tical stabilizer and extends from the rear cone
of the fuselage to just below the undersurface
of the horizontal stabilizer (Figure 15-3).
In the flight compartment, each pilot is pro-
vided with a pair of rudder pedals which in-
corporate adjustment for reach.
Movement of the rudder pedals is transmitted
by connecting rods and a bellcrank to a pul-
ley drum under the flight compartment floor.
Cables transmit the movement of the pulley
drum to a quadrant fitted to the bottom of the
rudder torque tube.
A spring strut connected to the lower portion
of the rudder torque tube provides a centering
force at the extreme travel. An autopilot ser-
vomotor is also connected to the base of the
torque tube.
Primary stops are located at the rudder lower
hinge to determine the range of movement in
both directions. Secondary stops are located
at each rudder pedal assembly.
Flow separation triggers have been installed
on both sides of the rudder to reduce the pos-
sibility of too much rudder application during
rudder bias operation (Figure 15-3A).
Rudder Geared and Trim Tabs
Two separate tabs are hinged at the trailing
edge of the rudder. The upper tab is linked to
the rudder by two connecting rods, the lower
tab is linked by rods to a screw trim actuator
unit. Both tabs provide an antiservo action.
The position of the lower tab may be controlled
manually by the rudder trim handwheel in the
flight compartment (Figure 15-4).
Rudder Bias System
Two air-powered struts are connected between
the fuselage and the rudder torque tube quad-
rant providing an automatic application of
rudder bias to counteract asymmetric thrust
caused by failure or malfunction of one engine
(Figure 15-5).
Revision 1
15-5
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
Figure 15-3A. Rudder
Summary of Contents for 800 XP
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