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UF94200
EFFECTIVITY Page 95
ALL
SELF EXAMINATION
In manual mode (AP not engaged), the yaw damper
orders are normally computed by the:
A - FMGCs.
B - FACs.
C - ELACs.
How is the yaw damper power loop monitored?
A - By the comparator between command part
and monitor part of the FAC.
B - By the comparator between the yaw order
and the rudder position feedback.
C - By the changeover logic.
Does the yaw damper actuator move the rudder pedals?
A - Yes, if hydraulic power is available.
B - Yes, in manual mode.
C - No, it does not move the rudder pedals.
TMUFACD01 LEVEL 3
EFFECTIVITY 22-63-00 Page 6
Oct 31/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 22 AUTO FLIGHT SYSTEM
UF94200
EFFECTIVITY Page 96
ALL
22 - AUTO FLIGHT SYSTEM
22-64-00 FLIGHT ENVELOPE PROTECTION
CONTENTS:
General
Speed Computation Display
Speed Computation
Alpha-Floor and Windshear Protection
Low Energy Awareness
Self Examination
TMUFACH06 LEVEL 3
EFFECTIVITY 22-64-00 Page 1
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 22 AUTO FLIGHT SYSTEM
UF94200
EFFECTIVITY Page 97
ALL
FLIGHT ENVELOPE PROTECTION
GENERAL
The function of the Flight Augmentation Computer is
independent of the FAC engagement pushbutton.
This function provides :
- characteristic speeds on the PFDs through the
Display Management Computers,
- the speed limits to the FMGCs for autoflight,
- the alpha-floor detection to the FMGCs for
autothrust engagement, if it is not engaged,
- low energy awareness.
In addition, the FAC computes the weight and the center
of gravity.
SPEED COMPUTATION DISPLAY
The speeds computed by the Flight Augmentation Computer
are sent to the Primary Flight Display and the speed
limits to the Flight Management and Guidance Computers.
In normal operation, FAC 1 data are displayed on the
CAPT PFD and the FAC 2 data on the F/O PFD.
If a parameter or the computer fails, the associated
PFD is automatically switched to the opposite FAC by
the DMC.
If the air data source used by the FAC is different
from that used by the DMC for speed display, the message
ADR DISAGREE appears on the ECAM.
SPEED COMPUTATION
Aerodynamic laws and the aircraft configuration
parameters are used for the characteristic speed
computation.
The computation principle is based on the fact that
most of the speed data are a function of the aircraft
weight.
In flight, the FAC computes the weight with the ADIRS,
FMGC and SFCC parameters and then, from the weight,
it computes the characteristic speeds and the center
of gravity.
On the ground, the FAC uses the weight provided by the
FMGC.
TMUFACH06-T01 LEVEL 3
EFFECTIVITY 22-64-00 Page 2
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 22 AUTO FLIGHT SYSTEM
UF94200
EFFECTIVITY Page 98
ALL
FLIGHT ENVELOPE PROTECTION - GENERAL / SPEED COMPUTATION DISPLAY / SPEED COMPUTATION
TMUFACH06-P01 LEVEL 3
EFFECTIVITY 22-64-00 Page 3
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 22 AUTO FLIGHT SYSTEM
UF94200
EFFECTIVITY Page 99
ALL
FLIGHT ENVELOPE PROTECTION
ALPHA-FLOOR AND WINDSHEAR PROTECTION
Alpha-floor detection and windshear protection are
computed by the FAC or the ELAC and sent to the FMGC.
This function protects the aircraft against excessive
angle-of-attack.
The FAC compares the aircraft alpha (AOA) with the
predetermined threshold (function of the slat/flap
configuration). This threshold is decreased in case
of windshear. Beyond this threshold, the FAC transmits
a signal to the FMGC to engage the autothrust function
and apply full thrust.
If the aircraft is in clean configuration, the
windshear compensation function is not available. The
ELAC will trigger alpha-floor in two cases : alpha
protection condition + side stick deflection > 14
degrees, or pitch angle > 25 degrees + side stick
deflection > 14 degrees.
A dual ADIRS failure results in the total loss of
alpha-floor detection.
LOW ENERGY AWARENESS
Energy awareness is a software device which provides
the crew with an aural warning which indicates that
it is necessary to increase thrust to recover a
positive flight path angle through pitch control.
The audio warning, "SPEED SPEED SPEED", is triggered
　
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