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Rudder
control (non-boosted) is provided by using of spring trim tab of
balance tab and pedals via mechanical linkage. Mechanical linkage
is combined one; in fuselage is cable one in fin it is made with
using rods. Trim tab control is fly-by wire at pushing of switch
“Rudder trim tab” on the central panel. The neutral £ £ £ position
of trim tab-balance tab is monitored by lighting of annunciator
“neutral rudder trim” on the central panel. The annunciator “check
rudder trim” will light on the lower panel of the upper control
panel on the ground at deflected trim tab-balance tab.
The
actuator, limiting the travel of trim-tab - balance tab and servicing
the function of changes of gear ratio of rudder channel control
is installed in control channel of rudder.
Actuator
control, limiting the travel of trim tab - balance tab is fly-by-wire.
In
automatic mode the control of actuator, limiting the travel of trim
tab - balance tab (two-position switch “Reserve rudder control columns”
set in position OFF) take places at installation of flaps in position
d 3 £ 50. In standby mode (switch “Reserve
rudder control columns” will set to position ON), the control of
travel of trim tab - balance tab limiting travel is performed by
deflection of pushing switch “Reserve rudder control column” to
sides “Take off/POOS and cruise.
Rudder
locking on ground is fly-by-wire, from lever “Gust locks” on the
left wall of center panel. Rudder locked position is warned by annunciator
“Gust locks OFF” on the lower panel of the upper control panel.
Elevator
control (non-boosted) is provided by control columns via mechanical
linkage. Mechanical linkage is combined: in fuselage - a cable linkage,
in vertical stabilizer it is mode with using rods “Each section
of elevator is equipped with trim tab and trim-tab - balance tab.
The trim tabs of both sections of elevator are deflected by unique
transmission driven by two electric actuators (consecutively installed)
of trimming (main and standby). Each trim tab - balance tab, except
the geared linkage with own elevator section, can be displaced with
individual electric actuator of trimming.
Elevator
trim tab control is fly-by-wire. In main mode (from buttons “dive
- pitching up” on the left and right control columns) the trimming
is performed by pulse switching the main electric actuator of trimming.
The
first standby mode of elevator trimming (from press switch “1 Reserve
elevator trim” on the central panel) is used to switch the standby
electric actuator of trimming while pressing switch button.
The
second standby mode of elevator trimming (from double press switch
“2 reserve elevator trim” on the central control panel) is used
for switching trimming electric actuator of trim-tab balance tabs
at pressing the switches button.
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The
trim tab - balance tab electric actuator activation is monitored
by light of annunciator “Left is not neutral” or “Right is not neutral”
on the central control panel.
Annunciator
“No neutral” on the center control panel and “Check elevator trim”
on the upper control panel is monitored by activation of trim tab
electric actuators and trim tabs-trim-balances.
Disconnection
the boards of mechanical linkage of elevator control by means of
switch “Boards disconnection elevator” on the central control panel
is provided. Control of actuator for boards wiring disconnection
is fly-by-wire, there is an annunciator “Boards disconnection elevator”
on the upper control panel. Connection of boards wiring is ensured
only on the ground by means of control panel of elevator control
wiring connection installed on starboard, on frame No. 38.
Elevator
control in mode of automatic flight control is performed by means
of autopilot servo unit, geared by mechanical linkage with portside.
The manual trimming is locked at switching of automatic flight control.
The
elevator locking on the ground is provided only by elevator deflected
down. Locking control is fly-by-wire, from lever “Gust locks on”
on the left wall of the central control panel. The elevator locking
position is signaled by lighting of annunciator “Gust locks OFF”
on the upper control panel.The
flaps control system provides synchro, fly-by-wire control of symmetrical
pair of flaps sections, connected to rotating cardan shafts with
power drive KPM-02. The retraction preventive brakes PUT and transmitters
of flaps position asymmetry (BR-48 units) are installed on the transmission
ends. The power drive KPM-02 is combined, it includes the hydraulic
motor and DC current electric motor. Two modes of system operation
in flight (main and standby) are provided.
In
main (tracking) mode of system operation the hydraulic motor of
drive KPM-02 and PUT are monitored by control monitor BUK3-400,
connected to transmitters of Flaps control lever position on the
central control panel.
Position
of flaps is monitored by indicators UPZ-72PP on the middle panel
of instrument panel. At flaps asymmetry more than allowable, the
automatic stop of drive and transmission fixation by means of PUT
takes place and annunciators “flaps-asymmetry”, “Flaps-main control
failure” on the lower panel of the upper control panel light. At
this it is not allowable the continuation of extension and retraction
of flaps in any mode. If the flaps were not installed on the ground
in take-off position then at declination of engine control lever
to position corresponding to mode of the most maximum continuous,
the annunciators “Check flaps” on the lower panel of the upper control
panel and “Take off is not allowed” on the left and right panels
of instrument panel will right.
In
standby mode of the discrete extension (retraction) of flaps from
press switches on control panel of “Reserve, flaps”, controlled
by work of drive electric motor KPM-2, is performed.
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