Super 80 Professional – AOM
FLIGHT CONTROLS
Section 13 Page 5
Super 80 Professional – Aircraft Operating Manual
Coolsky, 2018
Leading Edge Slat System
The leading edge slat system provides wing
lift augmentation. There are six slat segments
on the leading edge of each wing. The
segments are interconnected to form one
slat on each wing. The slats are hydraulically
operated.
The slats are actuated by the flap/slat
handle. Three slat positions may be selected:
•
Retracted
•
Mid-sealed
•
Extended
Note: The Super 80 Pro only simulates the
retracted and extended slat positions.
When the flap/slat handle is in the UP/RET
position, the slats are retracted. When the
flap/slat handle is positioned in the 0° to 13°
range, the slats are in the mid-sealed
position. When the flap/slat handle is
position in the 15° to 40° range, the slats are
in the extended position.
Maximum airspeed with the slats in the
extended position is 240 KTS.
Maximum airspeed with the slats in the mid-
sealed position is 280 KTS.
Maximum airspeed with the slats in the
retracted position is V
mo
or M
mo
.
The aural and vocal warning system will be
activated if the throttles are advanced for
take-off and the slats are not extended.
Horizontal Stabilizer
A movable horizontal stabilizer provides
longitudinal trim. The stabilizer is moved by a
jackscrew driven by an electric motor. The
stabilizer trim is operated by moving the trim
control handle on the pedestal. Operation
of the trim control handle will cause the
autopilot to disengage.
A cable operated indicator moves fore and
aft along a track on the pedestal to indicate
the current nose up or nose down trim
setting.
When the horizontal stabilizer is moved, an
audio signal will sound for every 2° of
stabilizer movement. A vocal warning will be
sounded whenever the stabilizer is moved
by the autopilot at a rate greater than 20° in
30 seconds. A switch on the aft pedestal is
used to stop a primary-trim runaway
stabilizer condition.
Note: In the real airplane the warning
sounds are for every 1° of stabilizer
movement and rate greater that 2° in 30
seconds. These values have been increased
as the P3D autopilot is very active on the
stabilizer trim. This would have generated
quite a bit of noise in the cockpit if the real
values had been used.
The stabilizer trim is electrically operated,
thus stabilizer trim will be unavailable if a
total loss of electric power occurs. The
stabilizer will then be locked in the position it
had at the time the electrical power was
lost.
Take-Off Condition Computer
The Take-off Condition Computer (TCC) is
used to determine the take-off trim setting.
The TCC is a geared computer device that
display a trim setting based upon crew input
of CG and flap setting. The take-off trim
setting is displayed numerically and by a
green pointer. The crew will trim the stabilizer
until the white Stabilizer Position Indicator is
adjacent to the centerline of the green
pointer.