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- servo-actuator (7), located in the fuselage forward of frame C7, - electronic box (2), located under the front table, on the L.H. side, - trim disarming inverter (3), located on the control wheel horn, on pilot station side, - master switch (1), located on the instrument panel strip, on the R.H. side of the pilot control wheel, - "TRIM" circuit breaker (5), located on the circuit breaker panel, down, on the L.H. side of the pilot. F. Stall warning device (Figure 3) The aircraft is equipped with a vane-type stall warning detector mounted in the L.H. wing leading edge. The vane is electrically connected to an aural warning unit. The vane in the wing senses any variation in the air flow over the wing and triggers the warning unit which then sounds a discontinuous tone on the buzzer on upper duct. 4. OPERATION A. Electrical pitch trim (option) (Figure 4) If the aircraft is equipped with the electrically-controlled pitch trim, the elevator trim tab may be operated either electrically or manually. ACAC Validity : S / N 1 - 9999 mPAa e2 27 30 00 (DA) Rg 00 When master switch (1) is set to "ON", the circuit is energized. Thus, the pilot can select the operating mode of the elevator trim tab by means of trim disarming inverter (3) : - manual mode by means of control wheel (6), - electrical mode by means of "TRIM UP/DN" inverter (4) : . inverter forward : aircraft in nose down attitude, . inverter backward : aircraft in nose up attitude. Via electronic box (2), "TRIM UP/DN" inverter (4) operates the servo-actuator which transfers the movement to actuator (9) (non reversible) via cables (8). Actuator (9) controls elevator trim tab (10). NOTE : The three-position "ON-OFF-ON" trim disarming inverter (3) is a nonlocking inverter. To operate the Nose up or Nose down mode, simultaneously actuate and hold "TRIM UP/DN" inverter (4) and trim disarming inverter (3) to "ON". The pilot can, at any time, override the electical control by actuating control wheel (6). ACAC Validity : S / N 1 - 9999 27-30 00Page 3 (DA) MAR 00 1 - Control wheel 2 - Elevator control rod 3 - Aileron control rod 4 - Pylon assembly Pitch control - Control wheel and pylon assemblies Figure 1 ACAC Validity : S / N 1 - 9999 27 30 00Page 4 (DA) MAR 00 1 - Pylon 2 - Control rod 3 - Input rod 4 - Lever (frame C9) 5 - Lever (frame C7) 6 - Lever (frame C3) 7 - Tightness bellows (frame C3) Pitch control - Rods and levers Figure 2 ACAC Validity : S / N 1 - 9999 27 30 00Page 5 (DA) MAR 00 1 - Control wheel 2 - Cable 3 - Actuator 4 - Rod 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(28) |
