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D633A101-GUN Oct 10/2005
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-21-00-012
RUDDER CONTROL SYSTEM - MAIN RUDDER PCU - FUNCTIONAL DESCRIPTION
RUDDER AND RUDDER TRIM CONTROL SYSTEM - MAIN RUDDER PCU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
GUN 006-099, 101-115; GUN 001-005, 201-999 POST SB 737-27-1253 27-21-00
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D633A101-GUN Jun 10/2006
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-21-00-012
THIS PAGE IS INTENTIONALLY LEFT BLANK
RUDDER AND RUDDER TRIM CONTROL SYSTEM - MAIN RUDDER PCU - FUNCTIONAL DESCRIPTION
27-21-00
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D633A101-GUN Jun 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The standby rudder power control unit (PCU) uses alternate
hydraulic power to move the rudder.
Location
The standby rudder PCU is above the main rudder PCU in the
vertical stabilizer.
Physical Description
The standby rudder PCU has these parts:
* Housing connected to structure
* Piston connected to the rudder
* Input and summing cranks
* Solenoid valve
* EHSV.
Functional Description
The standby rudder PCU gets alternate hydraulic power from
the standby hydraulic pump. The standby hydraulic pump
supplies power when system A or system B flight control switch
is in the STDBY RUD position. The standby rudder shutoff valve,
on the standby hydraulic system module, controls pressure to
the standby rudder PCU. See the standby hydraulic system
section for more information. (SECTION 29-22)
The standby hydraulic pump automatically supplies pressure to
the standby rudder PCU when these conditions are present:
* System A or system B low pressure
* Airplane is in the air or wheel speed greater than 60 knots
* TE flaps are not up.
* Either system A or system B flight control switches are ON.
GUN 001-005, 201-999 PRE SB 737-27-1253
When the pilot moves the rudder pedals, the rudder input rod
moves. This moves the external summing lever and the input
crank. This causes the PCU piston to move the rudder. As the
PCU piston moves, the summing lever moves the input crank to
null out the input. This stops the PCU movement at the correct
position.
GUN 006-099, 101-115; GUN 001-005, 201-999 POST SB
737-27-1253
When the pilot moves the rudder pedals, the rudder input rods
moves. This moves the external summing lever and the input
crank. This causes the PCU piston to move the rudder. As the
PCU piston moves, the summing lever moves the input crank to
null out the input. This stops the PCU movement at the correct
position.
GUN ALL
The solenoid valve sends pressure to the EHSV when WTRIS is
engaged. The EHSV sends pressure from the solenoid valve to
the yaw damper actuator.
RUDDER AND RUDDER TRIM CONTROL SYSTEM - STANDBY RUDDER POWER CONTROL UNIT
EFFECTIVITY
GUN ALL 27-21-00
Page 36
D633A101-GUN Jun 10/2006
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-21-00-008
RUDDER AND RUDDER TRIM CONTROL SYSTEM - STANDBY RUDDER POWER CONTROL UNIT
RUDDER AND RUDDER TRIM CONTROL SYSTEM - STANDBY RUDDER POWER CONTROL UNIT
EFFECTIVITY
GUN ALL 27-21-00
Page 37
D633A101-GUN Jun 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-21-00-008
Physical Description
The PCU contains these components:
* Bypass valve
* Filter
* Control valve, integrated with the yaw damper actuator
* Yaw damper LVDT
* Solenoid valve
* Shuttle valve
* Servo valve.
Functional Description
When standby hydraulic pressure is on, it opens the bypass
valve and connects the actuator chambers to separate control
ports.
When the pilot moves the rudder pedals, the rudder input rod
moves. This moves the external summing lever and the input
crank. This positions the control valve to apply pressure to one
chamber and open the other to return. The standby rudder PCU
piston moves the rudder. This also moves the control valve to
reset when the rudder moves to the position that the pilot
selected.
Wheel-To-Rudder Interconnect System (WTRIS)
The WTRIS system gives input to the standby PCU to help in a
manual reversion turn. The WTRIS engages when the flight
　
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