曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

EFFECTIVITY 27-00-00 Page 6
Mar 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 20
ALL
27 - FLIGHT CONTROLS
27-00-00 EFCS PRESENTATION
CONTENTS:
Surfaces
Actuators
Computers
Active servo controls
Reconfiguration Priorities
Self examination
TMUFCLD02 LEVEL 1
EFFECTIVITY 27-00-00 Page 1
Mar 31/94
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 21
ALL
EFCS PRESENTATION
SURFACES
All the flight control surfaces are hydraulically
operated by actuators which receive electrical signals
from the computers. The rudder and the Trimmable
Horizontal Stabilizer (THS) can also be mechanically
controlled.
ACTUATORS
All the actuators are hydraulically powered by one of
the three hydraulic circuits, except the rudder trim
actuator, the rudder travel limitation actuator and
the THS servo-motors which are electrically driven.
COMPUTERS
The relationship between actuators and computers is
indicated on the schematic. The left or right elevator
actuators are connected to two computers, one ELAC and
one SEC
- ELAC: ELevator Aileron Computer
- SEC: Spoiler Elevator Computer
ACTIVE SERVO CONTROLS
There are two servo controls for each aileron, for
each elevator and for the yaw damping function. In
normal configuration, one servo control actuates the
surface. It is called active servo control. The second,
which follows the surface deflection, is in damping
mode.
When only manual pitch trim is available, the centering
mode is applied to the elevators. The actuators are
hydraulically maintained in neutral position.
RECONFIGURATION PRIORITIES
In case of failure, the damping servo control and
related computer are set to the active mode.
TMUFCLD02-T01 LEVEL 1
EFFECTIVITY 27-00-00 Page 2
Mar 31/94
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 22
ALL
EFCS PRESENTATION
TMUFCLD02-P01 LEVEL 1
EFFECTIVITY 27-00-00 Page 3
Mar 31/94
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 23
ALL
SELF EXAMINATION
Which surfaces can be mechanically controlled ?
A - Elevators and THS.
B - Ailerons and THS.
C - Rudder and THS.
TMUFCLD02 LEVEL 1
EFFECTIVITY 27-00-00 Page 4
Mar 31/94
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 24
ALL
27 - FLIGHT CONTROLS
27-90-00 CONTROL LAW PRESENTATION
CONTENTS:
Normal Laws
Law Reconfigurations
Alternate laws
Direct law
Mechanical Back-up
Self Examination
TMUFCBC01 LEVEL 1
EFFECTIVITY 27-90-00 Page 1
May 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 25
ALL
CONTROL LAW PRESENTATION
NORMAL LAWS
In normal conditions, the normal laws are used to
compute the surface deflection orders.
Normal laws provide a FULL FLIGHT ENVELOPE PROTECTION.
TMUFCBC01-T01 LEVEL 1
EFFECTIVITY 27-90-00 Page 2
May 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 26
ALL
CONTROL LAW PRESENTATION - NORMAL LAWS - BASIC PRINCIPLE
TMUFCBC01-P01 LEVEL 1
EFFECTIVITY 27-90-00 Page 3
May 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
EFFECTIVITY Page 27
ALL
CONTROL LAW PRESENTATION
NORMAL LAWS (CONTINUED)
There are three principal control modes:
- the ground mode,
- the flight mode,
- and the flare mode.
During the ground mode, a direct relationship exists
between the stick, elevators and roll control surfaces.
Also, the rudder is mechanically controlled by the
pedals and the yaw damper function is available.
The ground mode is activated after the flare mode when
the main landing gear shock absorbers are compressed
with pitch attitude confirmation.
In flight mode, the NORMAL LAWS are:
- Nz law for the pitch control, including load
factor protection,
- lateral normal law for the lateral
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：ATA 27 FLIGHT CONTROLS(5)