ELEVATOR CONTROL SYSTEM
The elevator control surfaces are hinged from
the rear of the horizontal stabilizer. Each is fit-
ted with a mass balance weight to prevent flut-
ter and a horn balance to reduce the aerodynamic
loads felt by the pilot (Figure 15-9).
A spring and a G-weight are connected to the
left control circuit to provide acceptable stick
force characteristics.
A stick shaker motor is attached to each control
column and is operated by the stall warning
system. A stick pusher unit is connected to the
elevator cable system to provide a positive push
forward (pitch down) at the onset of stall iden-
tification. See section titled,
Stall Warning and
Identification System
.
The cable circuit also provides an input for the
autopilot servo unit.
Primary stops controlling the range of elevator
movement are located on the middle hinge of
each control surface. Secondary stops are lo-
cated at the pulley drums under the flight
compartment floor.
Elevator Trim Control System
A trim tab is fitted to each elevator and is
manually controlled from an elevator trim
handwheel on the central control pedestal
(Figure 15-10). Operation of the elevator
moves the trim tab to give servo action.
The autopilot servomotor is used to provide
pitch trim, Mach trim and electric trim functions.
If necessary these functions can be overridden
by arresting the movement of the elevator trim
handwheel. The handwheel turns as the auto-
matic system applies trim via the servo.
Elevator Out-Of-Trim Warning
When an elevator is out of trim at takeoff, a
warning is given by the ELEV/AIL TRIM an-
nunciator illuminating on the main MWS
panel (Figure 15-10) if the following condi-
tions apply:
• Aircraft weight is on wheels.
• Both engine thrust levers are advanced
to more than 40–60% N
1
power.
Mach Trim
The Mach trim system uses a Mach trim com-
puter and the same pitch trim servomotor as
the manual electric trim and the autoelectric
trim systems. The Mach trim computer accepts
Mach number data from the air data comput-
ers and computes trim tab deflection, in-
c r e a s i n g l o n g i t u d i n a l s t a b i l i t y a t M a c h
numbers above 0.73 Mach when the autopi-
lot is not engaged.
15-11
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
Summary of Contents for 800 XP
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