CONTROL COLUMN E2B
E1B OVERRIDE MECHANISM AUTOPILOT PITCH
E2A ASYMMETRY
E2A
CONTROL SERVO (APCS)REGULATOR ACTUATOR CABLE TENSION LIMITER
E2B (3 LOCATIONS)RIGHT AFT
QUADRANT OUTPUT
RIG PIN E/ST6 CONTROL RODLOCATION
AFT MECHANISME1A
TORQUE BOX
CAPTAIN'S E1B E1A A A
FORWARD QUADRANT
NEUTRAL SHIFT ANDOVERRIDE MECHANISME1B
B
LEFT AFTQUADRANT OUTPUTCONTROL ROD RIG PIN E/ST10LOCATION UP ELEVATOR FWD AFT QUADRANTELEVATOR FEEL
B
TO LEFT INDEXER AND CENTERING
ELEVATOR
UNITRIG PIN E/ST7LOCATION
1GUN 001-010
Elevator Control System Schematic (Mechanical)
Figure 3 (Sheet 1)
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27-31-00
ALL ú ú 09 Page 3 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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757
MAINTENANCE MANUAL
CENTERING SPRING
PCA INPUT CRANK
R OUTBD PCA POGO ROD R MIDDLE PCA
REACTION LINK STABILIZERRIG PIN LOCATION FRONT SPAR
RIGHT (E/ST8 LEFT ELEVATOR)
INBOARD PCA (E/ST9 RIGHT ELEVATOR)
FWD OUTBD
UP
R ELEVELEV
POS XMTRAFT QUADRANTOUTPUTCONTROL RODRIG PIN E/ST11
(SHEET 1) LOCATIONPCA INPUTCONTROL ROD FWD
RIGHTELEVATOR(LEFT ELEVATORELEVATORSIMILAR) FEEL COMPUTER
A
CC
NEUTRAL SHIFTNEUTRAL SHIFTAND OVERRIDEPOGO RODMECHANISM
ASYMMETRY LIMITER(TO STABILIZER)
ACTUATOR FORK
(INSERTED AT HIGH SPEED)
RIG PIN E/ST10 UPPER
NEUTRAL SHIFT
LOCATION HORIZONTAL
CONTROL ROD STABILIZER(AFT END) FIRST OFFICER'S
RIG PIN E/ST10AFT QUADRANTFIRST OFFICER'SCAPTAIN'S LOCATION AFT QUADRANT AFT QUADRANT
CAPTAIN'S
AFT QUADRANT
LOWERNEUTRAL SHIFTCONTROL ROD LOW SPEED
ASYMMETRYNEUTRAL
STOPSSHIFT LINK
HIGH SPEED
FEEL AND CENTERING
STOPS
ASYMMETRYUNIT CONTROL ROD (2) FWD FWD
FWD
ELEVATOR NEUTRAL SHIFTELEVATOR ASYMMETRY LIMITER
ELEVATOR FEEL AND CENTERING UNIT AND OVERRIDE MECHANISMA-A
B-B C-C
Elevator Control System Schematic (Mechanical)
Figure 3 (Sheet 2)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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MAINTENANCE MANUAL
D. Elevator positioning is achieved by manual inputs from the captain's or first officer's control column. The two columns are mechanically slaved together through a spring-loaded override mechanism. Dual cable systems with tension regulators installed in the forward quadrants are used to transmit pilot inputs to the dual aft quadrants. The aft quadrants are also mechanically slaved together through a spring-loaded override mechanism. The override mechanisms allow separation of the column inputs in the event of a jam in one system. A force of approximately 65 pounds (289 newtons) is required to separate the systems.
E. An elevator asymmetry limiter actuator limits the asymmetric motion between the captain's and first officer's aft quadrants. The amount of asymmetric motion allowed is less at high than at low speeds. This assures that the pilots cannot command enough asymmetric motion to cause excessive loads.
F. An elevator feel and centering unit is connected to both aft quadrants, to provide the desired control column feel and centering characteristics. The feel force is generated by a combination of mechanical and hydraulic devices. The feel and centering unit is positioned by a neutral shift and override mechanism which allows the stabilizer trim to introduce a shift of the neutral position in the airplane nose down direction. An override in the neutral shift mechanism allows the control system to override a jam in the feel and centering mechanism.
G. Three autopilot servos are connected in parallel to the aft quadrant. Autopilot operation causes the entire control system to move, including both control columns.
H. A stick shaker is provided on each control column to warn the pilots of an approaching airplane stall condition. The stick shakers, which are activated by signals from the stall warning system, consist of an electric motor driving an unbalanced mass. Refer to 27-32-00 for stall warning system operation.
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本文链接地址：757 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(119)
