(m)
Disengage the autopilot.
(n)
Do the steps (b) thru (n) again but use the autopilot channel
B.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
F. Pitch Force Transducer Interface Test - DFCS BITE
S 715-049
(1)
Do the preparation for the DFCS BITE test in this task: "Operational Test - Digital Flight Control System" (Ref 22-11-00/501 or 22-11-01/501).
S 745-032
(2)
Do the transducer interface test:
(a)
Push the INIT REF key on the CDU keyboard.
(b)
Push the LSK adjacent to <INDEX.
(c)
Push the LSK adjacent to MAINT>.
(d)
Push the LSK adjacent to <DFCS.
(e)
Push the LSK adjacent to <LRU INTERFACE.
(f)
Push the LSK adjacent to <CHANNEL A AND B.
(g)
Push the NEXT PAGE key on the CDU keyboard.
(h)
Push the LSK adjacent to ACT POS SENS>.
(i)
Do the preparation steps as shown on the CDU.
(j)
Push the LSK adjacent to <CONTINUE.
(k)
Make sure that the test is completed with no failure.
(l)
Push the INIT REF key on the CDU keyboard to get out of the BITE.
S 085-046
(3) Remove the spring scale from the control wheels.
G. Put the Airplanes Back to Its Initial Condition
S 865-039
(1)
Remove hydraulic power if it is not necessary (Ref 29-15-00/201).
(2)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 865-040
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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 through the AFC accessory unit (or IFSAU). When the system is engaged, a rate gyro 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 warning annunciator, a yaw damper coupler, a yaw damper engage solenoid, transfer valve and position transducer on the rudder power control unit, and a yaw damper rudder position indicator.
D. AIRPLANES WITH IFSAU; You will find the TE flap up limit switch at station 715 in the right main wheel well (AMM 27-51-87/401).
E. Yaw damper components are located in the flight compartment, in the electronic equipment area, and in the lower portion of the vertical stabilizer (Fig. 1).
(1)
The yaw damper engage switch and warning annunciator are located on the flight control module which is mounted 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 22-11-XX/ Digital Flight Control System - Description and Operation.
(3)
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.
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