Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

Страница: 158 / 923

Page 6-3
P/N 140-590032-0007
Revision A4: Sep, 2010
Section III Sub-section 6
FLIGHT CONTROLS
Pilot’s Operating Manual
GENERAL
The aileron, elevator and rudder are primary controls operated manually by cable-activated circuits from
dual ram’s-horn type control columns and adjustable rudder pedals.
Trim tabs are installed on the rudder, elevator and left aileron. The elevator trim tab may also be
operated by a servo motor which is controlled by the pilot using the electric trim switches or by the
autopilot and mach trim system.
The airbrakes, powered by the main hydraulic system, are selected by the AIRBRAKE selector lever,
which is labelled SHUT and OPEN with an infinite selection of intermediate positions. A third position,
labelled DUMP, is available after lifting the selector lever through a baulk at the OPEN position.
Wing flaps, which are hydraulically powered, are installed at the wing trailing edge. Labelled selection
positions are 0
°
(UP), 15
°
, 25
°
and 45
°
(FULLY DOWN). A lift dump position at 75
°
is available via the
airbrake DUMP selection.
Emergency lowering is available via the auxiliary hydraulic system. A flap position indication is displayed
on the Copilot’s Multifunction Display (MFD). A rudder bias system, powered by engine bleed air,
automatically applies opposite rudder to counteract the effect of asymmetric thrust resulting from a
single engine failure. A stall warning (stick shake) and identification system (stick push) is also provided.
(Refer to Sub-section 7 STALL WARNING/IDENTIFICATION)
Internal gust locks are provided to lock the control surfaces when the airplane is parked or moored. The
internal gust locks are also linked to a throttle baulk which prevents both throttles being advanced
beyond 60% N
1
when the gust locks are engaged. A single throttle can be advanced to full power, but
the other throttle is then baulked at 55-60% N
1
. The gust locks are rated for wind gusts of up to 80 knots.
PRIMARY CONTROLS
AILERON CONTROL SYSTEM (Figure 1)
Movement of the ram’s-horn type handwheel on either control column operates the ailerons
differentially. Each handwheel operates a lever at the bottom of the column through chains and cables.
A connecting rod interconnects the levers of each column. The left column lever is also connected to a
pulley drum. From the pulley drum a combination of cables and tie-rods operate a pulley in each wing,
which are connected to the aileron by levers and links. Each aileron control surface has a mass balance
weight installed to prevent flutter and a horn balance to reduce the aerodynamic loads felt by the pilot.
Primary stops, located at the left and right aileron inboard hinges, limit the aileron range of movement.
The stop bolt in the aileron hinge contacts a fixed stop in the wing structure and limits the upward
movement of the aileron.
Downward movement of the aileron is halted when the primary stop of the opposite aileron takes effect.
Secondary stops are located at the bottom of each control column.