757 MAINTENANCE MANUAL
D. Put the Airplane Back to Its Usual Condition
S 412-011
(1) Close Access Panels 324BL and 324CL (Ref 06-42-00).
S 092-012
WARNING: STAY AWAY FROM THE NOSE WHEELS WHEN THE LOCKPIN IS REMOVED.
_______ THE WHEELS CAN TURN TO THE CENTER POSITION QUICKLY, AND CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(2)
Make sure the nose wheels are in their center position and remove the towing lever lockpin from the nose gear.
S 862-013
(3)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:
(a)
11H17, FLT CONT SHUTOFF TAIL LEFT
(b)
11H18, FLT CONT SHUTOFF TAIL CTR
(c)
11H28, FLT CONT SHUTOFF TAIL RIGHT
(d)
11J16, RUDDER POS
S 862-014
(4)
Remove the DO-NOT-OPERATE tags and move the FLT CONTROL SHUTOFF switches L, C, and R on the right side panel, P61, to ON.
(5)
Remove electrical power if it is not necessary (Ref 24-22-00).
S 862-015
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757 MAINTENANCE MANUAL
ELEVATOR CONTROL SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________
1. General (Fig. 1, 2 and 3)_______
A. The elevator control system controls airplane pitch attitude by movement of two elevator surfaces which are hinged on the rear spar of the horizontal stabilizer. The elevator is used for primary pitch control. Pitch trim is provided by the horizontal stabilizer.
B. Primary control of the elevators is through pilot or autopilot inputs. Additional elevator positioning is provided by stabilizer motion which changes the elevator neutral position. The elevator control system is fully powered with no manual reversion capability.
C. Each elevator surface is positioned by three hydro-mechanical power control actuators (PCAs). Each actuator is powered by an independent hydraulic system. The actuators provide surface restraint for flutter suppression. Control system feel forces are provided by a dual hydro-mechanical feel system.
PILOT CONTROLLED INPUTS
Elevator Control Modes
Figure 1
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757
MAINTENANCE MANUAL
CAPTAIN'SFIRST OFFICER'SCONTROL COLUMN CONTROL COLUMN ELEV PCU
ELEV FEELEICAS STATUS
ELEV ASYMMESSAGES AND
CAUTION/
INDICATIONADVISORY
ANGLE OF ATTACK
STICK SHAKER (2)
FLAP POSITION
COMPUTER
COLUMN
OVERRIDE ELEV
AUTOMATIC 1
FLIGHT CONTROL
FORCE TRANSDUCER (2)
COMPUTER
TENSION REGULATORFEEL COMPUTER DYNAMIC PRESSURE Q INPUT (2)R
C STABILIZER POSITION INPUT (2)
E1B E1A
E2B E2A
FEEL &CENTERINGUNIT AFT QUADRANT (2)
AUTOPILOT PITCH
CONTROL SERVO
ACTUATOR (3)
AFT QUADRANT OVERRIDE LCR
HYDRAULIC SYSTEMS
STABILIZER
NEUTRAL SHIFT
AND OVERRIDE
MECHANISM
POWER CONTROL
ACTUATOR (6)
POSITION TRANSMITTER
POSITION
TRANSMITTER
(2)
LEFT ELEVATOR RIGHT ELEVATOR
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1GUN 001-010
Elevator Control System OperationFigure 2
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757
MAINTENANCE MANUAL
E1A
E1B ELEVATORFEEL COMPUTER
SEE A FORCE
TRANSDUCER
E1B E1A
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