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A
737-300/400/500MAINTENANCE MANUAL
 YAW DAMPER SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________
 1.  General (Fig. 1)_______
 A.  The yaw damper system provides airplane stabilization about the yaw axis. The yaw damper minimizes dutch roll during flight by providing rudder displacement proportional to, and opposing, the yaw rate of the airplane.
 B.  The yaw damper system is engaged by a switch on the flight control module. When the system is engaged, a solid state rate sensor in the coupler senses yaw rate of the airplane. The yaw rate signal is processed to generate a command to the rudder power control unit which moves the rudder. The signal is translated from electrical to mechanical in the rudder power control unit by a transfer valve. Position feedback is accomplished by an LVDT. A position indicator in the flight compartment indicates rudder movement due to yaw damper inputs. There is no feedback to the rudder pedals since a series hydraulic actuator is used in the power control unit.
 C.  The yaw damper system consists of a yaw damper engage switch and disengage warning light, a yaw damper rudder position system indicator, a yaw damper coupler, a rudder pressure reducer system, an autopilot warning light, and a yaw damper engage solenoid, transfer valve, and position transducer on the rudder power control unit.
 D.  Yaw damper components are located in the flight compartment, in the electrical and electronics compartment, in the lower portion of the vertical stabilizer, and in the tail compartment (Fig. 1).
 (1)  
The yaw damper engage switch and disengage warning light are located on the flight control module which is installed on the overhead panel (P5).

 (2)  
The yaw damper coupler and AFC accessory unit (or IFSAU) are installed on the E1-3 rack in the electrical and electronic equipment compartment. The AFC accessory unit (or IFSAU) is discussed in the Digital Flight Control System - Description and Operation (AMM 22-11-00/001).

 (3)  
The yaw damper rudder position indicator is installed on the center (P2) instrument panel.

 (4)  
The yaw damper engage solenoid, transfer valve, and position transducer are mounted on the rudder power control unit (PCU), which is located in the lower portion of the vertical stabilizer.

 (5)  
The rudder pressure reducer system is located in the tail compartment.

 E.  The yaw damper power is supplied through two circuit breakers located on main load control center P18-1. 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 (AMM 27-21-00/001).
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 22-12-01
 COUPLER  ú
 ú 02 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.  Page 1Jul 12/99 

A
737-300/400/500MAINTENANCE MANUAL
CENTER PANEL, P2
. YAW DAMPER POSITION

YAW DAMPER DISENGAGE WARNING LIGHT YAW DAMPER COUPLER
AND YAW DAMPER ENGAGE SWITCH

C

B
Yaw Damper System - Component Location Figure 1 (Sheet 1)
K01647
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH 10-62253 YAW DAMPER ú

 22-12-01
 COUPLER  ú
 ú 01 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.  Page 2Jul 12/99 

A 737-300/400/500MAINTENANCE MANUAL
YAW DAMPER ENGAGE SOLENOID
SEE D
FWDTRANSFER VALVE
POSITION TRANSDUCER
RUDDER POWER CONTROL UNIT D
Yaw Damper System - Component Location Figure 1 (Sheet 2)
K01724
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH 10-62253 YAW DAMPER ú

 22-12-01
 COUPLER  ú
 ú 01 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.  Page 3Mar 15/99 

A 737-300/400/500MAINTENANCE MANUAL
　
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