QUADRANT
CRANK
ROD METERING SPRINGCLUTCH VALVENGPPB
CARTRIDGE CAPTAIN'S
NGPPA TILLER AND TORSIONGEARBOX
LINKS NWSB FRAME
ROD SUMMING
ECCENTRIC
ECCENTRIC LEVER
ARM DRUM MECHANISM
NWSA NOSE QUADRANT AND LANDING TORQUE LIMITER GEAR
NOSE WHEEL STEERING SYSTEM WITH CAPTAIN'S TILLER ONLY 1
RUDDER PULLEY
JACKSHAFT INTERCONNECT (EXAMPLE)
MECHANISM MECHANISM
TURNBUCKLE (4 LOCATIONS)
FIRST CAPTAIN'S
OFFICER'S RUDDER
QUADRANT
TILLER AND PEDALS CRANK
GEARBOX
ROD
METERING
CLUTCH
VALVENGPPA
SPRING NWSBB
CARTRIDGECAPTAIN'S NGPPB
TILLER AND
GEARBOX
T0RSION FRAME
LINKS
ROD
NWSBA
ECCENTRIC QUADRANT ECCENTRIC
ARM DRUM SUMMING NOSENWSB LEVER
LANDING QUADRANT AND NWSA MECHANISM
GEAR TORQUE LIMITER
NOSE WHEEL STEERING SYSTEM WITH CAPTAIN'S AND FIRST OFFICER'S TILLER 2
1 ALL EXCEPT GUN 051
2GUN 051
Nose Wheel Steering System - Component Location
Figure 1
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MAINTENANCE MANUAL
RUDDER CABLE
FIRST OFFICER'S
TILLER AND
|15` QUADRANT
GEARBOX
1
FULL TRAVEL
RUDDER SYSTEM
RIG PIN 2
CAPTAIN'S
RUDDER
INPUT ROD FOR PEDALS RUDDER PEDALRUDDER PEDAL
NR
STEERING STEERING U
T
INTERCONNECT T
FE
MECHANISM L D
NET
C X
L E
RAE
G|360`
NWSB QUADRANT
NWSA 1
NOSE GEAR TILLER INPUT CAPTAIN'S |65`
CONTROL ROD
STEERING NOTE: THE ARROWS SHOW TILLER A LEFT TURN. AND GEARBOX
METERING VALVE
NOSE GEAR
ACTUATORS
TRAVEL RUDDER PEDAL INPUT 5` +2`/-1`
1
GUN 051
Nose Wheel Steering System
Figure 2 (Sheet 1)
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LEFT HYDRAULIC SYSTEM (REF 29-00-00) 1
LANDING GEAR
SELECTOR VALVE
EXTENSION AND RETRACTION TO LANDING GEAR POSITION SHOWN) (GEAR DOWN
SYSTEM (REF 32-30-00)
P R
TOWING
LEVER
TOWING SHUT-
OFF VALVE
BYPASS
VALVE
SERVO VALVE
RL
VALVE SWIVEL DYNAMIC LOAD DAMPER VALVE SWIVEL
METERING VALVE
L R
R L
1 RIGHT ACTUATORS STEERING SELECTOR VALVE SHOWN DOWNSTREAM OF LANDING GEAR ONLY HYDRAULIC POWER DISTRIBUTION Nose Wheel Steering System Figure 2 (Sheet 2) PRESSURERETURN METERING VALVE NOSE GEAR STEERING
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MAINTENANCE MANUAL
F. The two system centering springs keep the nose gear centered when there is no control input force. The springs also return the steering mechanism to neutral control position whenever the control input force is removed from the tiller.
G. A towing lever on the steering metering valve module permits towing without physically disconnecting the shock strut torsion links.
H. The nose gear steering system is automatically deactivated when the nose gear is retracted by removing hydraulic pressure from the system.
I. Cams internal to the nose gear shock strut are provided to hold the gear centered if hydraulic power is not available. The cam is disengaged upon landing when the nose gear strut is compressed 3.0 inches or more.
2. Component Details
_________________
A. ALL EXCEPT GUN 051;
Tiller, Gearbox, and Torque Limiter (Fig. 3)
___________________________________
B. GUN 051;
Tillers, Gearboxes, and Torque Limiter (Fig. 3)
______________________________________
(1)
ALL EXCEPT GUN 051; The steering tiller allows the captain to manually steer the airplane (Details A and B, Fig. 3).
(2)
GUN 051; The steering tillers allow the captain and/or first officer to manually steer the airplane (Details A, C and D, Fig. 3).
(3)
The tiller handle can be turned 360 degrees (maximum) in either direction from center. A geared nose wheel position indicator is installed at the base of the tiller handle to show the angle of the nose wheels from center.
(4)
A gearbox provides a 2.7 to 1 reduction ratio which in effect raises the input torque to the cable loop by the same ratio (Section A-A, Fig. 3)
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本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 3(94)
