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The main wheels are equipped with disk brakes. Brakes are activated by a common lever at the
cockpit center console and by toe brakes also.
Nose landing gear
. The gear leg is made of aeronautical grade alloy. Steering is direct controlled
by the rudder pedals. The landing gear incorporates the air/oil damper system. Nose wheels are of
the size 4.00-
4”.
Maintenance of both groups is described into many operational sheets collected into ANNEX A
(Retractable Landing Gear group).
3.1.5 Control system and aerodynamic surfaces
A brief discussion about the control systems and aerodynamic surfaces is given here below.
Maintenance procedures are described by operational sheets provided into ANNEX A (Wings and
Control Surfaces group).
•
The
rudder control system
consists of a closed loop made up of steel cables which are
preloaded to keep them taut.
•
The
aileron control system
is actuated by push rods so it i
s “rigid” and directly connected to
the control surface without any cable interface but connected with Uni Balls.
•
The
Elevator control system
consists of a closed loop of steel cables that run between the
control sticks and the aft relay bellcrank. There is a single push pull rod connecting the aft
relay bellcrank to the elevators.
•
The
Flap control system
is an electromechanical actuator motor which simultaneously
controls both flap. It is electronically controlled by the pilot using an accurate switch. The
installed configuration includes a flap computer that permits to set the flaps in stages at pre-
configured values.
•
The
Trim control system
consists of two trims in the standard configuration while a third one
(the rudder) that is optional. All the trim tabs are actuated by an electrical push-pull actuator
controlled by the pilot through a suitable switch located in the center tunnel inside the cockpit.
•
The
braking system
refers to the toe brake control configuration inside the cockpit. The
system allows individual control of the brakes through the toe brakes located only on the left
rudder pedals and also allows simultaneously locking of both brakes using the locking valve
inside the cockpit. Additionally, the system includes a T-handle in the center console which
permits the co-pilot to apply the brakes either simultaneously (with the T-handle) or separately
using toe brakes.
4 Engine
Maintenance operations about engine components described below are illustrated in the
Operational Sheets of ANNEX A (Fuselage Body and Engine groups).
4.1 Engine & Engine Mount
The Pioneer 300 aircrafts are powered by a single Rotax engine with 4 cylinders, liquid cooled
cylinder heads with an integrated water pump and expansion tank. The engine power is regulated
by a throttle that controls the engine RPM.
If the installed engine, such as a Rotax 912 ULS, has a carburetor there is the possibility to apply a
choke for the regulation of the cold start-up.
The engine mount structure is made of high-strength steel and the engine is attached to the engine
mount through rubber mounts that help reduce vibration.
