1 second.

(i)  
Return BITE switch to OFF.

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(3)  Yaw Damper (Coupler P/N 4030952-906) STEP         OBSERVE 
TEST  LIGHTS 
NO.  PASS  FAIL 
(a) (b)  BITE Self Test Arm 1) Ensure yaw damper is disengaged. 2) Set BITE switch to ARM. 3) Press LAMP TEST switch and hold. 4) Release LAMP TEST switch. Test 1 - Rate Gyro Filter 1 1) Engage yaw damper and ensure hydraulics are on. 2) Press GO switch. Observe after 1 second.  8 0 1  ON ON ON ON  OFF ON OFF OFF 
(c)  Test 2 - Engage Null 1) Engage yaw damper and ensure hydraulics are on (from Test 1). 2) Press GO switch. Observe after 5 seconds.  2  ON  OFF 
(d)  Test 3 - Rate to Rudder (Displacement) 1) Ensure yaw damper is engaged and hydraulics are on (from Test 2). 2) Press GO switch. Observe after 1 second.  3  ON  OFF 
(e)  Test 4 - Rate to Rudder (Integral) 1) Ensure yaw damper is engaged and hydraulics are on (from Test 3). 2) Press GO switch. Observe after 40 seconds.  4  ON  OFF 
(f)  Test 5 - Disengage Synchronization 1) Disengage yaw dampers and ensure hydraulics are off. 2) Press GO switch. Observe after 5 seconds.  5  ON  OFF 

5C1 
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STEP OBSERVE TEST LIGHTS NO. PASS FAIL
(g)  
Test 6 - Derived Accel. First Stage
1) Ensure yaw damper is disengaged and
hydraulics are off (from Test 5).

2)  Press GO switch. Observe 6 ON OFF after 1 second.

(h)  
Test 7 - Rate Gyro Filter 2
1) Ensure yaw damper is disengaged and
hydraulics are off (from Test 6).

2)  Press GO switch. Observe 7 ON OFF after 1 second.

(i)  
Test 8 - Rate Gyro

1)  Ensure yaw dampers are
disengaged and hydraulics are
off (from Test 7).

2)  Press GO switch. Observe after 8 ON OFF 1 second.
(j)  Return BITE switch to OFF.
H.  Restore Airplane to Normal Configuration
(1)  
Disengage yaw damper.

(2)  
Disconnect pressure source from pitot static system. Refer to Chapter 34, Air Data Instruments.

(3)  
Determine whether there is further need for electrical power on airplane; if not, remove external power.

5C1 
22-12-0 Page 506  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/85 

YAW DAMPER SYSTEM - DESCRIPTION AND OPERATION

EFFECTIVITY
Aircraft with Yaw Damper Coupler P/N 4084042 (after SB 27A1206)
1.  General
A.  Yaw axis stability augmentation is provided by the yaw damper system. The yaw damper system stabilizes the airplanes yaw motions during manual and autopilot 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 system.
B.  The yaw damper system consists of a solenoid held yaw damper engage switch, yaw damper disengage light, Flight Control B switch, yaw damper coupler (YDC), yaw damper actuator with transfer and solenoid valves and position transducer located in the rudder power control unit, yaw damper actuator position indicator, autopilot warning light, and the YDC BITE control panel.
C.  Yaw damper electrical power is supplied through two circuit breakers located on the main load control center P18. One circuit breaker supplies 115 volts ac and the other 28 volts dc. 
D.  The B hydraulic system powers the yaw damper actuator portion of the rudder power control unit (Ref Chapter 27).
E.  The YDC performs monitoring of the yaw damper system and provides passive response or automatic disengagement of the yaw damper system upon detection of system failures or malfunctions.
May 01/00 22-12-01 Page 1
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K06793
Yaw Damper Component Locations  500 
22-12-01  Figure 1  May 01/99 
Page 2 
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L19607
Yaw Damper System Functional Schematic DiagramSep 01/00 (With Ride Quality) 22-12-01 Figure 2 (Sheet 1) Page 2A/2B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
　
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