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S Aileron trim
S Rudder trim
S Horizontal stabilizer trim
S Flight spoilers
S Ground spoilers (inboard and outboard).
Lateral (roll) control of the aircraft is provided by the ailerons, assisted by the spoilerons.
Directional (yaw) control of the aircraft is provided by the rudder, assisted by yaw dampers.
Longitudinal (pitch) control of the aircraft is provided by the elevators, assisted by a
moveable horizontal stabilizer.
REV 56, Jan 31/03
Vol. 1 11--10--2
FLIGHT CONTROLS
Introduction
Flight Crew Operating Manual MASTER
CSP A--013
Flight Controls --- General Arrangements
Figure 11---10---1
HORIZONTAL STABILIZER
RUDDER
ELEVATOR
SPOILERON
AILERON
AUTOPILOT
SERVO
ACTUATOR
GROUND
SPOILERS
FLIGHT
SPOILER
INBOARD
FLAP
OUTBOARD
FLAP
PILOT
CONTROL
WHEEL
PILOT
CONTROL
COLUMN
PILOT
RUDDER
PEDALS
COPILOT
RUDDER
PEDALS
CENTER
PEDESTAL
COPILOT
CONTROL
COLUMN
COPILOT
CONTROL
A WHEEL
A
Vol. 1 11--10--3
REV 56, Jan 31/03
FLIGHT CONTROLS
Introduction
Flight Crew Operating Manual
CSP A--013
MASTER
The primary flight controls are controlled by a network of cables, pulleys, push/pull rods and
levers that transmit control and pedal inputs to hydraulic power control units. Each aileron
and spoileron is powered by two hydraulic systems. The rudder and elevators are power
from all three hydraulic systems.
The aileron and elevator controls are equipped with control disconnects which permit the
pilot or the copilot to maintain sufficient lateral and longitudinal control in the event of a
control jam. The rudder control is equipped with two anti-jam mechanisms that permit both
pilots to maintain sufficient directional control, however, additional force is required to obtain
surface travel.
In the event of a total electrical power failure, the primary flight controls will remain powered
from AC motor pump (ACMP) 3B which will be powered by the ADG in an emergency.
The flight spoilers provides the aircraft with lift dumping and speed control as commanded
from the spoiler control lever in the flight compartment.
The ground spoilers only deploy on the ground as part of the ground lift dumping function to
slow the aircraft during landing. The spoilerons and flight spoilers also deploy on the ground
to assist in the ground lift dumping function.
Flight control status and surface positions are displayed on the EICAS primary page, status
page and FLT CONTROL synoptic page.
A stall protection system is provided to warn the flight crew of an impending stall when the
aircraft attitude approaches a high angle--of--attack (AOA) and to prevent a stall penetration
when the aircraft nears the computed stall angle.
Hydraulic power distribution to the flight controls is as follows:
HYDRAULIC SYSTEM 1 HYDRAULIC SYSTEM 3 HYDRAULIC SYSTEM 2
Left Aileron Left and Right Aileron Right Aileron
Rudder Rudder Rudder
Left Elevator Left and Right Elevator Right Elevator
Left and Right Flight Spoilers Left and Right Spoilerons Left and Right Flight Spoilers
Left Spoileron Right Spoileron
Left and Right Outboard
Ground Spoilers
Left and Right Inboard
Ground Spoilers
REV 56, Jan 31/03
Vol. 1 11--10--4
FLIGHT CONTROLS
Introduction
Flight Crew Operating Manual MASTER
CSP A--013
Flight Control Systems --- Hydraulic Supply
Figure 11---10---2
NO.1 HYDRAULIC SYSTEM
NO.2 HYDRAULIC SYSTEM
NO.3 HYDRAULIC SYSTEM
LEGEND
SPOILERON
3 1
OUTBD
GROUND
SPOILER
1
Vol. 1 11--20--1
REV 56, Jan 31/03
FLIGHT CONTROLS
Ailerons
Flight Crew Operating Manual
CSP A--013
MASTER
1. AILERONS
Lateral control of the aircraft is provided by the ailerons with assist from the spoilerons.
The aileron control systems consist of two control circuits and both systems are similar in
operation. The pilot operates the left aileron system and the copilot operates the right
aileron system. Normally, the two systems are interconnected and there is simultaneous
movement of both aileron surfaces. In the event of a jam in either circuit, the system can be
separated through a roll disconnect mechanism. The autopilot is connected to the copilots
control system only.
Each aileron is hydraulically powered by two power control units (PCUs) and mechanically
controlled by rotation of either control wheel. The left aileron PCUs are powered by
hydraulic systems 1 and 3 and the right aileron PCUs are powered by hydraulic systems 2
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