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 A.  The yaw damper coupler provides control and monitoring of the main rudder PCU pressure reducer (RPR) system. The yaw damper coupler provides control signals to the RPR solenoid, provides pressure sensor excitation, and receives signals from the pressure sensor to measure the A system hydraulic pressure to the main rudder PCU. The yaw damper coupler interfaces to radio altimeter 1 and radio altimeter 2 to determine when the airplane transitions above 1,000 feet and below 700 feet to activate and deactivate the RPR solenoid. The yaw damper coupler interfaces to the flight control system B pressure switch and deactivates the rudder pressure reducer solenoid when the B hydraulic system is depressurized. The yaw damper coupler interfaces to the flight control system A low pressure light and provides illumination when the A system pressure to the main rudder PCU is below 500 psi or when full pressure is commanded to the RPR and system pressure is below 2,200 psi.
 9.  Operation_________
 A.  Functional Description (Fig. 2)
 (1)  
The yaw damper system is turned on by placing the yaw damper switch to ON. Hydraulic power must be available and the flight control B switch ON. Two seconds after the yaw damper is on, the disengage warning light extinguishes. The engagement is monitored by a power monitor circuit. If ac power is lost for over 2 seconds, the disengage warning light illuminates and the yaw damper switch returns to OFF.

 (2)  
The yaw rate sensors detect motion in the yaw axis. The signal is filtered, modified according to changes in airspeed, and amplified. It is then applied to the transfer valve. The transfer valve ports hydraulic pressure to move the yaw damper actuator. The yaw damper actuator output is summed with rudder pedal input to move the main actuator which controls the rudder, but there is no mechanical feedback to move the rudder pedals.

 (3)  
As the yaw damper actuator moves, the LVDT supplies the feedback signal to cancel the signal from the yaw rate sensors. The feedback signal is also applied to the position indicator by the yaw damper coupler . However, during normal operation, the signals are too small to be monitored by the position indicator.

 B.  Control
 (1)  Do these steps to put the system into operation:
 (a)  
Supply electrical power.

 (b)  
Supply hydraulic power.

 (c)  
Make sure the flight control B switch is ON.

 (d)  
Set the yaw damper switch to ON.

 (e)  
Make sure the yaw damper disengage warning light goes out.

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 22-12-01
 COUPLER  ú
 ú 02 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.  Page 6Jul 12/99 

A 737-300/400/500MAINTENANCE MANUAL

Yaw Damper System Block Diagram
Figure 2

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH 10-62253 YAW DAMPER ú

 22-12-01
 COUPLER  ú ú 01 Page 7 ú Jul 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
K01713
A
737-300/400/500MAINTENANCE MANUAL
 10. Yaw Damper BITE_______________
 A.  Yaw damper BITE is structured in the form of multi-leveled menus. Each level has a sequential set of menus that can be selected individually to access the next lower level under the selected category.
 B.  This commonly used method begins with the familiar main menu, and successively works its way down to the desired function. The selections on the main menu are Existing Faults, Fault History, Ground Tests, and Other Functions. This is the menu structure of yaw damper BITE:
 (1)  
Existing Faults

 (a)  
Fault messages
 1) Fault details

 (b)  
Reset latches

 

 (2)  
Fault History

 (a)  Power cycle
 1)  Fault messages
 a) Fault details

 (3)  
Ground Tests

 (a)  
Self-test

 (b)  
Servo test

 (c)  
Pressure reducer test

 (d)  
Program pin test
　
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