27-21-96
 ú ú 01 Page 403 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 (5)  S 864-013Remove the DO-NOT-CLOSE tags and close these circuit breakers: (a) P6-2 panel 1) STABILIZER TRIM ACTUATOR 2) STABILIZER TRIM CONT
 (6)  S 614-014Fill the hydraulic reservoirs if it is necessary (AMM 12-12-00/301).
 (7)  S 714-015Do the "yaw damper coupler test of the rudder pressure reducer" (AMM 22-12-32/501).

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 27-21-96
 ú ú 01 Page 404 ú Jul 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 ELEVATOR AND TAB CONTROL SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________________
 1.  General_______
 A.  The elevators provide primary pitch control of the airplane about the airplane lateral axis and respond to control column inputs through two independent hydraulic systems. In the event of dual hydraulic failure, a manual reversion mode will allow the elevators to be driven directly through a mechanical control system. Aerodynamic elevator tabs are provided to assist elevator movement. Air loads on the system are further reduced by aerodynamic balance panels attached to each elevator.
 B.  The elevator control system is activated by fore and aft motion of the captain's and first officer's control columns. A torque tube, with a forward control quadrant mounted at each end, interconnects the control columns. A pair of elevator control cables attach to each forward control quadrant. The elevator up cables (EB) are secured at the quadrants and then routed aft under the floor to the aft control quadrants (Fig. 1). The elevator down cables (EA) are routed forward from the control quadrants, around a pair of pulleys, then aft along the fuselage to the aft control quadrants. The control cables are rigged over pulleys to minimize flexing and prevent chafing. The aft quadrants are mounted on the input torque tube in the empennage aft of the stabilizer rear spar. The elevator hydraulic power control units for left and right elevators are linked between the input torque tube and the output torque tube and provide power to rotate the elevators during power mode.
 C.  The elevator control system is also activated by the autopilot (Ref Chapter 22, Autoflight).
 D.  Hydraulic power is supplied to the elevator control system from hydraulic systems A and B at a pressure of 3000 psi. Hydraulic fluid flow is controlled by flight control shutoff valves located in the flight controls modular packages in the main wheel well.
 E.  Elevator feel is provided by a feel computer and a feel and centering unit. The feel computer provides varying hydraulic system A and hydraulic system B pressure inputs to the feel and centering unit. The feel and centering unit then applies a resistance at the aft control quadrants to simulate elevator areodynamic forces.
 F.  The power control units respond to control system inputs to rotate the elevators. The control units provide the stops which limit elevator rotation and tab displacement and also provide snubbing action on the ground to protect the elevators from wind gust damage.
 G.  A tab control mechanism acts to assist elevator movement with a different gear ratio.
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 27-31-00
 ALL  ú ú 01 Page 1 ú Feb 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
SEE A
EA EB
AUTOPILOT B ACTUATOR
ELEVATOR FORWARD CONTROL QUADRANT MACH TRIM ACTUATOR
AUTOPILOT A ACTUATOR
ELEVATOR
ELEVATOR
A PCU

ELEVATOR FEEL AND CENTERING UNIT
STABILIZER POSITION SENSOR
INPUT TORQUE TUBE
ELEVATOR AFT CONTROL QUADRANTS
FWD
A
Elevator Control System Component Location Figure 1
ELEVATOR TAB
ELEVATOR
OUTPUT
TORQUE TUBE

NEUTRAL
SHIFT SENSOR

ELEVATOR B PCU
ELEVATOR POSITION SENSOR
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