曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Conform to procedures given in aircraft "Pilot's Operating Handbook".
AAAA
Validity : S / N 1 - 822, 850 - 887, 889 - 947 With electrical pitch trim 27 30 06 Page 204
(BA) MAR 00
Pitch trim servo-actuator - Adjustment / Test
Figure 202 (1/2)
AAAA
Validity : S / N 1 - 822, 850 - 887, 889 - 947 With electrical pitch trim 27 30 06Page 205
(BA) MAR 00
Pitch trim servo-actuator - Adjustment / Test
Figure 202 (2/2)
WING FLAPS (CONTROL)
DESCRIPTION AND OPERATION
1. GENERAL
The two flaps are connected and controlled by an electro-mechanical assembly. The wing flap control consists of :
- flap actuator,
- wing flap control,
- relays,
- control linkage,
- aural warning unit,
- wing flaps - refer to 57-50-00.
The system is electrically supplied by "BUS 1" bar.
2. LOCATION
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Flap actuator 1 210 218 27-50-01
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.
S / N 1 - 499, 501 - 547, 553, 556, 560 - 579 Pre-Kit OPT10 911600 (Detail A) The selector assembly plate is secured by two bolts on the rotary switch pin.
A protective device prevents risks of impacts or unwanted actuation.
S / N 500, 548 - 552, 554, 555, 557 - 559. 580 - 9999 and S / N 1 - 499, 501 - 547, 553, 556, 560 - 579 Post-Kit OPT10 911600 (Detail B)
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.
S / N 1 - 9999
A pointer indicator is located on the left of the control.
中国通航网 www.ga.cn
通航翻译 www.aviation.cn
本文链接地址：TB20 MAINTENANCE MANUAL 27 FLIGHT CONTROLS TB20飞机维护手册 飞行操纵(57)
|
