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The pitch control system consists of :
- the control wheel assembly,
- the pylon assembly,
- the rods and levers,
- the input rod,
- the elevator trim tab control,
- the stall warning device,
- the electrical pitch trim (option),
- the elevator - refer to 55-20-01.
The system also uses the aural warning system - refer to 31-50-00.
The system can be interconnected with the autopilot (option) - refer to 22-10-00.
NOTE : This does not apply to aircraft with electrical pitch trim option.
2. LOCATION
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Control wheel assembly 1 250 / 27-30-01
Pylon assembly 1 250 235L, 235R, 236 27-30-02
Rods and levers 3 200 235L, 235R, 252,
253,236,218,242 27-30-00
Input rod 1 220 222 27-30-00
Elevator trim tab control 1 330 222 27-30-03
Stall warning device 1 510 / 27-30-04
Pitch trim servo-actuator 1 230 219,242 27-30-06
3. DESCRIPTION A. Control wheel assembly (Figure 1)
The control wheel assembly is the mechanical element which controls the elevator. The R.H. and L.H. control wheels are linked by a tube and rods.
B. Pylon assembly (Figure 1)
The pylon assembly is the system of rods and levers connecting the control wheels to the aileron and elevator control rods.
C. Rods and levers (Figure 2)
The levers hinged on the supports common to the rudder control are located :
- aft of frame C3 (under the rear bench seatpan),
- forward of frame C7 (in the rear fuselage),
- forward of frame C9 (in the rear fuselage). The rudder pedals and the levers are interconnected via non-adjustable control rods.
D. Input rod (Figure 2)
Located at the level of frame C9, the input rod connects the elevator to the lever located in the front of frame C9. It is equipped (on the elevator side) with an adjustable end.
E. Elevator trim tab control (Figures 3 and 4)
The elevator trim tab is located on the control surface trailing edge. It is controlled by a vertical control wheel mounted on the L.H. side of the pedestal.
The control wheel actuates the tab via cables and an actuator. A pointer indicator, located close to the wheel, indicates the position of the tab.
The actuator is equipped with a reel around which the control cable is wound. The worm screw crossing the reel converts reel rotative motion into vertical motion. AT-lever connecting the worm screw to the input rod converts vertical motion into longitudinal motion. The input rod is linked to both half-tabs by two levers. This rod is equipped (on tab side) with an adjustable end.
The aircraft can be equipped with an electrical pitch trim - see Figure 4. The electrical control consists of :
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本文链接地址：TB20 MAINTENANCE MANUAL 27 FLIGHT CONTROLS TB20飞机维护手册 飞行操纵(27)
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