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Wing flap control 1 250 252 27-50-02
Relays 2 210 218 27-50-00
Control linkage / 210
500 / 600 218 27-50-00
Aural warning unit 1 210 / 240 218 / 241 27-50-00
Circuit breaker CB 34 1 230 232L WM
Fuse 1 200 212L WM
3. DESCRIPTION
A. Flap actuator (Figure 1)
The flaps are actuated by an actuator located below the fuselage. The actuator consists of a mechanical section which drives a longitudinal motion screw and an electric motor. This electro-mechanical assembly is secured under the cabin floor.
B. Wing flap control (Figure 2) The wing flap control is located at the top of the pedestal.
This control consists of an inverter provided with a three-position plate allowing the pilot to extend or to retract the flaps. By operating the plate, the pre-set positions "retracted" (0°), "take-off" (10°) and "landing" (40°) are obtained.
NOTE : The flap displacement continues up to the position selected through the plate. The control has no intermediate "OFF" position.
AGAB
Validity : S / N 1 - 9999 Post-MOD. 151
27-50-00 (FM) Page 1
MAR 00
The selector assembly plate is positioned on the inverter lever and is hinged on two bolts, through the protective device. The protective device prevents risks of impacts or unwanted actuation.
A pointer indicator is located on the left of the control.
This indicator, illuminated for night flights, allows the pilot to determine the flap position. The "retracted", "take-off" and "landing" positions are marked on the indicator. The latter receives information about the position of the flap main bellcrank through a potentiometer integrated into the actuator and a printed circuit. The latter is secured on the R.H. inspection door under the rear bench seatpan.
C. Relays (Figure 1)
Two relays, located under the fuselage and attached under the rear bench seatpan or on frame C3, circuit breaker CB 34, marked "FLAPS" (located on the L.H. side circuit breaker panel) and a fuse (located on the fuse panel) protect the flap electrical circuit.
D. Aural warning unit
The flap system also consists of an aural warning microswitch. The aural warning unit is activated when the landing gear is in "retracted" position and the flaps are extended beyond 15°. The microswitch is connected to the landing gear aural warning circuit. It triggers a continuous aural signal diffused by the warning loudspeaker located on the upper duct.
1 - Flap indicator and control
2 - Warning microswitch
3 - Flap actuator
4 - Main bellcrank
5 - Outboard bellcrank
6 - Input rod
7 - Relay
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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(59)
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