Saab 340B, Руководство по эксплуатации

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FLIGHT CONTROLS
Description
Aircraft Operations Manual
8.1
PAGE 4
The gust lock handle also controls the following
electrical functions.
With the gust lock engaged the following is pos-
sible:
− Operation of the right engine propeller brake
− Erasing of cockpit voice recorder.
Should any disconnection occur in the gust lock
control link system, the system fails in the disen-
gaged position.
If the gust lock handle is in off position but the rud-
der gust lock remains engaged, the GUST lock light
on the CWP illuminates.
2.6 Trim systems
Main roll trim is accomplished by operating the
ROLL trim switches to actuate the left aileron trim
tab.
Standby roll trim is accomplished by operating the
STBY ROLL trim switches to actuate the right aile-
ron trim tab.
Yaw trim is accomplished by operating the YAW
trim switches to actuate the rudder tab.
All these switches are located in the trim panel on
the center pedestal in the cockpit.
Main pitch trim is accomplished by operating the
trim switches on either control wheel to actuate the
left elevator trim tab, and via a synchronization sys-
tem, the right trim tab. The left pilot’s switches over-
ride the right pilot’s switches.
Built − in monitoring circuits deactivate the synchro-
nization in case of a discrepancy, and illuminate the
PITCH TRIM light on the CWP.
Standby pitch trim is accomplished by operating the
STBY PITCH trim switches on the center pedestal.
These switches actuate the right elevator trim tab
only.
Standby pitch trim also deactivates the synchro-
nization. In this case it can be reset with the PITCH
RESET switch on the trim switch panel.
With the pitch trim synchronization deactivated both
main (left) and standby (right) trim tabs can be op-
erated individually by the control wheel trim
switches and the STBY PITCH trim switches re-
spectively.
All trim switches are dual switches to prevent run-
away trim, and must be operated together to com-
plete the necessary electrical circuit.
A common trim tab position indicator is located on
the center instrument panel.
2.7 Takeoff configuration warning
The trim and flap positions are fed into the CONFIG
(configuration) warning circuit of the master warning
system. With the aircraft weight on the wheels,
flaps at takeoff position (within 0 to 15 degrees
range), pitch trim in the normal takeoff range (green
band), and condition levers set for maximum PROP
RPM, the configuration for takeoff is correct. The
power levers can then be advanced to maximum
power for takeoff without a CONFIG warning. How-
ever, if any of these conditions are not met, the
master warning is activated. The CONFIG warning
light on the center warning panel flashes bright red,
an intermittent horn sounds and the red master
warning light come on flashing.
Pressing the master warning light cancels the horn,
the light goes off, and the CONFIG light changes to
steady.
2.8 Landing configuration warning
The flap warning system is part of the Ground Prox-
imity Warning System (GPWS). See AOM 19/2.1
Dec 01/20