Autopilot Disengage Switch Installation 500
22-11-411 Figure 401 Jun 20/89
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Autopilot Disengage Switch Wiring Configuration
Jun 20/89 Figure 402 (Sheet 1) 22-11-411
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Autopilot Disengage Switch Wiring Configuration 500
22-11-411 Figure 402 (Sheet 2) Jun 20/89
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AUTOPILOT DISENGAGE SWITCH - ADJUSTMENT/TEST
1. General
A. The autopilot disengage switches, one on each outboard horn, are located on the pilots' control wheel.
B. The switch must be tested whenever it is replaced.
2. Test Autopilot Disengage Switch
A. Provide electrical and hydraulic power.
B. Provide attitude valid and compass valid signals.
C. Ensure that all autopilot circuit breakers P6 and P18 panels are closed.
D. Engage autopilot. Operate autopilot disengage switch. Check that autopilot disengages and A/P warning lights flash. Reset A/P warning lights.
E. Remove electrical and hydraulic power if no longer required.
500
Jun 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-411 Page 501
YAW DAMPER SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
Except aircraft with coupler P/N 4084042
1. General
NOTE: For aircraft with coupler P/N 4084042 installed (incorporating SB 27A1206), see 22-12-01.
A. Yaw axis control is provided by the yaw damper. The yaw damper minimizes dutch roll during manually and automatically controlled flight by providing rudder displacement proportional to, and opposing, the yaw rate of the airplane. Since a series hydraulic actuator tie-in is used, there is no damper control feed back to the rudder pedals. This allows the pilot to maneuver the airplane in a normal manner without having an opposing force from the yaw damper.
B. The yaw damper system consists of a yaw damper engage switch, a test switch, a yaw damper coupler, yaw damper engage solenoid, transfer valve and position transducer on the rudder power control unit, and a rudder position indicator.
C. Yaw damper power is supplied through two circuit breakers located on main load control center P18. One circuit breaker is for 115 volts ac and the other is for 28 volts dc. The B hydraulic system powers the yaw damper actuator portion of the rudder power control unit (Ref Chapter 27).
2. Yaw Damper Coupler
A. The yaw damper coupler is installed on the E1-1 shelf of the electronic equipment racks in the electrical and electronic compartment.
B. The yaw damper coupler contains solid-state components on modern plug-in cards with printed circuit boards. The cards and subassembly installed in the yaw coupler rack are: yaw computation, BITE, and power supply cards and a rate sensor with yaw BITE panel subassembly. The front panel of the computer (Fig. 3) contains 2 lights (FAIL, PASS), a GO pushbutton for initiating each BITE test which is annunciated by a digital indicator, a LAMP TEST pushbutton for checking lamp continuity and a 2-position BITE toggle switch labeled OFF and ARM. Test points are on the lower portion of the panel.
C. The rate gyro senses the rate of change of the airplane yaw attitude. It generates an ac output voltage with the magnitude and phase a function of the angular yaw rate and direction of the motion. The gyro consists of a small, viscous-damped, single degree-of-freedom gyro composed of a motor and rotor, gimbal, signal pickoff, torsion bar and viscous damper. With a yaw rate, a precessional torque is developed by the gyro which displaces the gimbal. The torsion bar and viscous damper, attached to the gimbal, try to restrain it. The pickoff rotor, also attached to the gimbal, rotates within a stator which contains both primary (excitation) and secondary (output) windings. The angular position of the pickoff rotor due to the yaw rate provides the magnitude and sense of the output voltage.
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