TRAVEL WITH THE PCAS SUPPLIED WITH POWER.
ELEVATOR DOWN TRAVEL IS THE STRAIGHT LINE
DISTANCE FROM THE TOP EDGE OF THE INDEX
4 THE FINGER REFERENCE POINT IS 1.0 INCH PLATE TO THE INBOARD CORNER OF THE UPPER (25 mm) BELOW THE CENTER OF THE CONTROL SURFACE OF THE ELEVATOR TRAILING EDGE WHEEL HUB.
Elevator Control System Travel Measurements
Figure 505 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-00
 ALL  ú ú 02 Page 510 ú May 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

B
ASYMMETRY
LIMITER

CAPTAIN'S
ACTUATOR AFT QUADRANT
FIRST OFFICER'S
AFT QUADRANT

B
FWD
TORQUE BOX
LOWER ARM

ELEVATOR AFT MECHANISM
FIRST OFFICER'S STOP BOLT
AFT QUADRANT

C
SEE D
STOPS (2 LOCATIONS) TORQUE BOX UPPER ARM

(NOT SHOWN IN DETAIL C)SEE D
CAPTAIN'S AFT QUADRANT
AFT MECHANISM
ASYMMETRY TORQUE BOX
LIMITER ACTUATOR LOCKWIRE 1
FIRST OFFICER'S AIRPLANEAFT QUADRANT CENTERLINE WASHER
CAPTAIN'S
AFT QUADRANT STOP BOLT HEAD
STOPS (2 LOCATIONS)  AUTOPILOT SERVO
STOP BOLT
FWD
D
B-B 1  LOCKWIRE MUST NOT PASS OVER THE HEAD OF THE BOLT
Elevator Control System Travel Measurements
Figure 505 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-00
 ALL  ú ú 02 Page 511 ú Mar 20/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

OUTPUT CONTROL ROD FOR
THE RIGHT AFT QUADRANT

OUTPUT CONTROL ROD FOR THE LEFT AFT QUADRANT
APCS CONTROL
ROD (3 LOCATIONS)

CAPTAIN'S SEE AFT QUADRANT OUTPUT CONTROL ROD FOR
A THE RIGHT AFT QUADRANT
A
FIRST OFFICER'S
AFT QUADRANT
FEEL AND CENTERING
UNIT CONTROL ROD

OUTPUT CONTROL ROD FOR THE LEFT AFT QUADRANT
TORQUE BOX
LOWER ARM
TORQUE BOX
LOWER ARM
AFT QUADRANT
A
INDEXER SEE B DECENTERING SPRING
FWD (4 LOCATIONS)
ELEVATOR AFT MECHANISM
E/ST7
A
RIG PIN
HOLE
AFT QUADRANT INDEXER
AFT QUADRANT INDEXER
B
Elevator Control Aft Mechanism Figure 506 (Sheet 1)
AUTOPILOT PITCH CONTROL SERVO (APCS) (3 LOCATIONS)
AFT MECHANISM TORQUE BOX
NEUTRAL SHIFT AND OVERRIDE MECHANISM
NEUTRAL SHIFT OVERRIDE SPRINGS
E/ST10 RIG PIN HOLE
NEUTRAL SHIFT GROUNDING SPRINGS
NEUTRAL SHIFT CONTROL ROD (2 LOCATIONS)
ELEVATOR FEEL AND CENTERING
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-00
 ALL  ú
 ú  02  Page 512
 ú  Mar 20/95 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
B B
CAPTAINS'S
AFT QUADRANT
FIRST OFFICER'S AFT QUADRANT
OUTPUT CONTROL ROD FOR THE RIGHT AFT QUADRANT C
C
OUTPUT CONTROL ROD FOR THE LEFT AFT QUADRANT
FWD ASYMMETRY LIMITER E/ST7
ACTUATOR FORK RIG PIN
HOLE
A-A
FIRST OFFICER'S AFT QUADRANT
OUTPUT ARM 
CAPTAIN'S  FOR THE RIGHT 
AFT QUADRANT  AFT QUADRANT 
LOW SPEED 
ASYMMETRY 
HIGH SPEED  STOPS  OUTPUT ARM 
ASYMMETRY  1  FOR THE LEFT 
STOPS  AFT QUADRANT 
1 
FWD  OUTPUT CONTROL 
ROD FOR THE LEFT 
B-B  AFT QUADRANT 

1
THE ASYMMETRY LIMITER ACTUATOR FORK WILL MOVE BETWEEN THE CAPTAIN'S AND FIRST OFFICER'S AFT QUADRANTS AT HIGH SPEED (THE ASYMMETRY ACTUATOR IS EXTENDED). THE ASYMMETRY ACTUATOR WILL WITHDRAW FROM BETWEEN THE CAPTAIN'S AND FIRST OFFICER'S AFT QUADRANTS AT LOW SPEEDS (THE ASYMMETRY ACTUATOR IS RETRACTED).
Elevator Control Aft Mechanism Figure 506 (Sheet 2)
AFT MECHANISM
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(7)