Super 80 Professional – AOM
FLIGHT CONTROLS
Section 13 Page 2
Super 80 Professional – Aircraft Operating Manual
Coolsky, 2018
GENERAL
The primary flight controls of the airplane
consist of aileron, rudder and elevator
control systems. Secondary flight controls
consist of leading-edge slats, flight and
ground spoilers, inboard and outboard flaps,
and horizontal stabilizer.
PRIMARY FLIGHT CONTROLS
Lateral Control System
The ailerons provide the primary roll control
and are augmented by the flight spoilers
when increased roll control is required.
The control column in the cockpit is cable
connected to an aileron control tab which
controls aileron movement. In flight, the
deflecting control tab will cause the aileron
to aerodynamically position.
Aileron trim is provided by a separate tab on
each aileron. The trim tab is cable controlled
by the Aileron Trim knob on the aft pedestal.
Longitudinal Control System
Each elevator operates independently.
Each elevator is controlled by a single
control tab located inboard on the elevator.
The control tabs are cable connected to the
control column.
A gear tab is installed outboard of the
control tab on the elevator. The gear tab is
linked to move in the opposite direction of
the elevator. Thus, the gear tab always
assists the operation of the control tab.
An anti-float tab, geared to horizontal
stabilizer movement, is installed outboard of
the gear tab. The purpose of the anti-float
tab is to fly the elevator up when the
horizontal stabilizer is trimmed nose up.
Without this tab, the elevators tend to float
at extreme nose-up trim settings.
Stabilizer trim is accomplished by actuation
of the LONG TRIM handle on the pedestal.
Engine strakes are added to the engine
nacelles to enhance longitudinal control for
stall recovery.
The elevators normally operate
aerodynamically. However, for extreme high
angle of attack flight conditions, a 3000 PSI
hydraulic power augmentation system is
installed for additional nose down
capability. This feature is called Elevator
Augmentation. The main purpose for the
Elevator Augmentation system is to allow the
airplane to recover from a deep stall when
natural airflow across the tail is insufficient to
“fly” the elevators.
A Mach Trim Compensator is installed on the
First Officer’s control column. The Mach Trim
Compensator provides force to move the
columns slightly aft when the airspeed is
above M.80. This action offsets the effects of
Mach Tuck that occurs at high speeds.
When the airplane is parked, it is possible for
the elevators to split due to tail winds. When
this occurs, the flight crew may notice the
control columns feel locked in position. The
condition is removed as soon as the airplane
is taxied and the natural airflow of the tail
“flies” the elevator toward the neutral
position.