Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

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Page 6-8
P/N 140-590032-0007
Revision A4: Sep, 2010
Section III Sub-section 6
FLIGHT CONTROLS
Pilot’s Operating Manual
Both tabs provide an anti-servo action while the position of the lower tab may be controlled manually by
the rudder trim handwheel mounted on the center control pedestal, immediately above the aileron trim
handwheel.
Rudder Bias System (Figure 4)
Two air powered struts are connected between the fuselage and the rudder torque tube quadrant to
provide an automatic application of rudder bias to counteract asymmetric thrust caused by failure or
malfunction of one engine.
The engine bleed air system is interconnected to the struts in such a manner that each engine supplies
air to opposing sides of the strut pistons with a solenoid valve installed in each strut.
The solenoid valves are normally in the closed position when the RUDDER BIAS selector switches (A
and B) are set to their ON positions. Accidental operation of the switches is prevented by a guard on
each switch.
Should a leak occur in one supply line to a strut, the resulting loss of air would create an imbalance of
forces which would bias the rudder to one side.
The rudder bias switches are located in the upper left area of the center control pedestal immediately
above the elevator trim mechanical indication.
Selecting the RUDDER BIAS switch on the affected side to OFF, equalizes the pressures on both sides
of the strut. The strut on the good side then maintains a balance of forces on the rudder.
An amber MWS warning, RUDDER BIAS illuminates when either RUDDER BIAS switch (A or B) is set
to the OFF position.
AILERON TRIM
RUDDER TRIM
Center Control Pedestal
Top View
Rudder Trim Handwheel
Top View