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October 2004
Presented by
Brian EndersbyManager Electromechanical Systems
Airbus Fly-By-Wire OverviewA318/A319/A320/A321
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Monday, February 27, 12
Agenda Why Fly-By-Wire Airbus Fly-By-WireDesign
Objectives Design implementation Redundancy Dissimilarity Computer architecture
Fly-By-Wire control LawsPrinciple Pitch AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
control normal law Lateral control normal law
Fly-By-Wire protection Fly-By-Wire control law reconfiguration Control and indicatingAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Why Fly-By-WireIn 1983, Airbus launched the A320 with Fly-By Wire For Airbus Fly by Wire aircraftDifferent aircraft types have similar handling characteristics Flight envelope protection available Architecture simplified reduced maintenance, weight, cost
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Why Fly-By-WireIn 1983, Airbus launched the A320 with Fly-By Wire For Airbus Fly by Wire aircraftDifferent aircraft types have similar handling characteristics Flight envelope protection available Architecture simplified reduced maintenance, weight, cost
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Difficult to deliver with mechanical Flight Control systemsAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Airbus Fly-By-Wire Design Objectives
Safety objectivesloss of roll control: loss of pitch control: loss of elevator control: THS runaway: extremely improbable extremely improbable extremely remote extremely improbable
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Availability objectivesDispatch of the aircraft with one computer failed. One spoiler or one aileron servo control GO
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementationRedundancy at all levels(surfaces, power supplies, monitoring)
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementationRedundancy at all levels(surfaces, power supplies, monitoring)
Dissimilarity
hardware and software(avoid common mode failures)
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Computer architecture
for failure detection/reconfiguration(Command Monitor )
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design considerationAll the surfaces are hydraulically actuated and electrically signalled Elevator Ailerons Slats Flaps * Rudder* Rudder & stabilizerhave back-up mechanical control
Spoilers AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
* Horizontal stabilizer
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation Redundancy (A318-A319-A320-A321)Electrical generation and distribution
Generation
Two engine-driven generators One APU generator Two batteries One CSM / G (constant speed
motor/generator) driven by hydraulic circuit (Blue), powered by its dedicated pump or RAT
In case of electrical emergency configuration, two Fly-By AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Wire computers are still powered and provide high level control law applied to minimise common point risks.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Additionally, extensive segregation rules have beenOctober 2004 Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation Redundancy (A318-A319-A320-A321)Hydraulic generation and distribution
Three Hydraulic circuits (Green , Blue, Yellow)
Green pressurized by an engine driven pump Yellow pressurized by an engine driven pump
electrical pump. Blue pressurized by an electrical pump and RAT. Green and yellow circuit can drive each other by means of the Power Transfer Unit (PTU)
and an
Two electro-hydraulic servo-controls per surface. AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
In case of double hydraulic failure, high level control lawstill available with remaining flight controls.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation Redundancy (A318-A319-A320-A321)Computer to actuator repartition
The electrical signalling of the flight control surfaces is achieved by 7digital computers.2
ELevator and Aileron Computers (ELAC) 3 Spoiler and Elevator Computers (SEC) 2 Flight Augmentation Computers (FAC)
Four computers available on elevator AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Two specific computers are dedicated to manage the data from theflight control computers for indication, warnings, maintenance and recording purposes.2
Flight Control Data Concentrator (FCDC)October 2004 Page
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation Redundancy (A318-A319-A320-A321)
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation Dissimilarity (A318-A319-A320-A321) Different types of computer to control the surfacesTwo Three Two
ELAC SEC FAC
Different micro-processors usedELAC: SEC: FAC:
3 Motorola 68000 2 Intel 80C86 2 Intel 80C286
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Different software languages used for each computerchannel.C Assembler Dedicated one,
specifically developOctober 2004 Page
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation computer architecture Each computer which controls the surfaces has two functions:Flight control laws computation Surface servo loops control
Each computer is able:To To To
detect its internal failures inhibit its surface control signal its status
For each function (e.g. elevator control,etc) a priority order AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
exists between the computers for post failure reconfiguration logic.
All the computers are simultaneously activated to preventhidden failures , but only one command per function.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implmentation computer architectureEach computer is has two independent, symmetrical and self monitoring channelsCOMMAND channel MONITOR channel
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implmentation computer architectureEach computer is has two independent, symmetrical and self monitoring channelsCOMMAND channel MONITOR channel
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Each channel : Computes the flight control laws Calculates the deflection commands Controls the actuator deflection Ensures engagement of post failure reconfiguration logic Performs monitoring Provides Power supply for transducers
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implmentation computer architectureEach computer is has two independent, symmetrical and self monitoring channelsCOMMAND channel MONITOR channel
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Each channel : Computes the flight control laws Calculates the deflection commands Controls the actuator deflection Ensures engagement of post failure reconfiguration logic Performs monitoring Provides Power supply for transducers Command & Monitor philosophy used to detect failures by comparing computed outputs are within predefined thresholds.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Airbus Fly-By-Wire Design considerations computer architectureP I L O T I N P U TS I D E S T I C K
FLIGHT CONTROL COMPUTER COMMAND Software 1 d COM C O N T R O L L E R ACTUAL d 1
d COM
ELECTROVALVE HYDRAULIC ACTUATOR 1 2
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
S Y S T E M
A D I R S S
MONITOR Software 2 d MON
ACTUAL d 2 DEFLECTION d of CONTROL SURFACE
d
I F N C P C U T etc.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Airbus Fly-By-Wire Design implementation Mechanical back-up (A318, A319, A320, A321, A330-200, A330-300, A340-300)all safety objectives are fulfilled by redundancy, dissimilarity,system architecture In Addition A flight control mechanical back-up is provided:
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
For pitch control
For Yaw / roll control
Stabilise and control the aircraft during a temporary loss of all computers.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire control laws - Concept pilot stick input, to aircraft response, is called thecontrol law
The control law determines the handling characteristics ofthe aircraft.
The Control Law algorithm is optimised to obtain the bestaircraft performance throughout the flight envelope AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Fly-By-Wire control laws - ConceptNon-fly-by-wire aircraftCONTROL COLUMN
Mechanical linkage
Surface deection
Fly-by-wire aircraft AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
SIDESTICK
FLIGHT CONTROL COMPUTER Pilot order
+ -
Surface deection order
Surface deection Aircraft response
FeedbackAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire control laws - ConceptFlt Control computers Control lawSYSTEM STATUS SIDESTICK Pilot order Electrical signal
NORMALSurface deection
ALTERNATE
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
DIRECT
Control law selected dependent upon Flight Control System statusAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire control laws - ConceptNormal and alternate lawSIDESTICKFLIGHT CONTROL COMPUTER Pilot order
+ -
Surface deection order
Surface deection Aircraft response
Feedback
Pilots input is converted into an A/C objective. No direct relationship between stick and surface. The aircraft is servo looped
Direct law AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
SIDESTICK
FLIGHT CONTROL COMPUTER Surface deection
Surface deflection order kinematic
Aircraft response
Pilots input is directly converted into surface deflection orders.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Fly-By-Wire control laws - Concept
Control laws are modified to the flight phases and ground to air transition conditions.
Ground mode AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Transition
Flight mode
Transition
Flare mode
Transition
Ground mode
Transitions are smooth
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
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Monday, February 27, 12
Fly-By-Wire control laws Pitch control Forward or aft sidestick deflection results in a verticalload factor demand (G Load) / pitch rate.FLIGHT CONTROL COMPUTER G load demand
SIDESTICK
+ -
Elevator & THS deflection order
Surface deection Aircraft response
G Load / Pitch rate feedback
In short term, commanded flight path is maintainedElevator AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
and THS are automatically deflected to compensate for turbulences, thrust, configuration and speed changes. Aircraft is automatically and continuously trimmed (neutral static stability)
In long term, pilots action may be required to adjust flightpath as desired.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire control laws Pitch control
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Fly-By-Wire control laws Lateral control Lateral side stick deflection results in a roll rate demand.SIDESTICKFLIGHT CONTROL COMPUTER Roll rate demand e
+ -
Roll & Yaw deflection order
Surface deection Aircraft response
Roll Yaw rate / Bank Slide slip feedback
The roll rate is achieved by roll surfaces while rudder provides automaticturn coordination and yaw damping. AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
The aircraft is laterally stable: no aileron trim is required (neutral spiralstability) Roll and yaw surfaces are automatically deflected to cope with turbulences or aircraft asymmetry, using max deflection if required.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire control laws Lateral control
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Fly-By-Wire control lawsWithin the normal flight envelope regardless of altitude, speed, Cg or configuration,Aircraft Aircraft Loads
is stable: yet is highly maneuverable on demand response is precise and consistent about all axiss.
are controlled & monitored in both pitch and roll.
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Fly-By-Wire control lawsWithin the normal flight envelope regardless of altitude, speed, Cg or configuration,Aircraft Aircraft Loads
is stable: yet is highly maneuverable on demand response is precise and consistent about all axiss.
are controlled & monitored in both pitch and roll.
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Resulting handling characteristics provide a safe, accurate and comfortable flight within the normal flight envelopeAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire protection A full set of protection is provided in case the normalwindshear, very high turbulences, midair collision avoidance manoeuvres, or GPWS, TCAS activation,
flight envelope is violated due to some extreme situation such as
Protection Function:Gives AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
full authority to pilot and achieves the best aircraft performance response Reduces the risk of over controlling / overstressing the aircraft Compatible with Pilot instinctive response to flight conditionsAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire protectionPitch attitudePitch limits
Load factor
Bank angle
Ground mode AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Flight mode
Flare mode
Ground mode
High AOAAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
AIR FLOW
High speedOctober 2004 Page
Monday, February 27, 12
Fly-By-Wire protection Pitch attitude Design aim:To enhance the effectiveness of AOA and high speed protection in extreme conditions. Pitch authority is reduced at extreme attitudes.
Principle:
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Nose-up Flaps 0 to 3 30 Flaps full 25
Nose down 15Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire protection Load factor Design aim:To minimize the probability to damage the aircraft structure when high maneuverability is needed + 2.5 g to - 1g in a clean configuration + 2 g to 0 g with slats/flaps extendedConventional A/CNz AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
G load
Limitations:
FBW A/C (normal or alternate control law)Nz 2.5 g Straight pilot's input
Cautious pilot's input
2.5 g g load A/C response
g load A/C response t0 Time t0 Time A/C time constantOctober 2004 Page
A/C time constant + pilot's reaction timeAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Monday, February 27, 12
Fly-By-Wire protection Bank angle If side stick is released when the bank angleexceeds 33, the aircraft will return to and maintain 33 bank angle. bank angles up to 33.
Automatic pitch compensation provided for
AP disconnects and FD bars disappear when thebank is > 45, FD bars reappear when bank angle is < 40 (or 45 if AOA or high speed protection). AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
With full side stick bank angle is limited to 67 If high speed protection is operative, the positivespiral stability threshold starts from 0 and bank angle is limited to 45.October 2004 Page
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Monday, February 27, 12
Fly-By-Wire protection High speed Design aim:Protects the aircraft from exceeding VMO/MMO limit by introducing a positive load factor (nose-up demand) to the side stick
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
VMO/MMO limit
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
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Fly-By-Wire protection High Angle of Attack Design aim:To
introduce positive static stability at the low speed end of flight envelope To protect against stall, even in high dynamic manoeuvres or in gusts To provide the ability to reach and maintain a high CL, side stick full aft, without exceeding stall angle No interference with normal operating speeds and manoeuvres
Principle:When AOA greater
than AOA prot., a fwd/aft side stick input results in
an AOA demand AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Results:AOA
prot. is maintained if side stick is left at neutral position AOA max is maintained if side stick is deflected fully aft
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
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Fly-By-Wire protection High Angle of Attack
CL
Angle of Attack (AOA) Stall : Sudden loss of lift and or aircraft control AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Max: Angle of attack reached with full aft stick(max aircraft performance) Floor: Angle of attack, where TOGA thrust is automatically applied by the A/THR
Prot: Angle of attack from which stick input is converted into angle of attack demand (stick neutral Prot) VLS: Angle of attack reached at approach speed (VLS)Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Fly-By-Wire protection High Angle of Attack As speed decreases itreaches Vls, the lowest achievable speed with autothrust engaged
Between PROT & MAX, Floor will activate, autopilot disconnects and speed brakes automatically retract if extended
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
Monday, February 27, 12
Control law reconfiguration Normal LawPitch attitudePitch limits
Load factor
Bank angle Pitch normal lawPitch side stick = load factor demand
Ground mode AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Roll normal lawRoll side stick = roll rate demand
Flare mode
Ground mode
High AOA
AIR FLOW
High speed
With any single failure, all protections remain availableAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Control law reconfiguration (A318-A319-A320-A321)Normal lawDouble or triple ADR failure Double self detected IR failure Double hydraulic failure Double FAC failure Double SFCC slat channel failure Yaw damper function loss Double aileron Double ELAC failure All spoilers loss Triple SEC failure THS jammed ELAC2 + hyd B ELAC1 + hyd G ELAC1 + hyd Y
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Alternate LawsAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Control law reconfiguration Alternate Law(A318-A319-A320-A321) Pitch attitudePitch limits
Load factor
Bank angle Pitch normal lawPitch sidestick = load factor demand
Ground mode AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Roll normal law Roll Direct law
Flare mode
Ground mode
High AOA
AIR FLOW
Stall warning
overspeedHigh speed stabilityOctober 2004
Overspeed warningPage
Low speed stabilityAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
Monday, February 27, 12
Control law reconfiguration (A318-A319-A320-A321)Normal lawDouble or triple ADR failure Double self detected IR failure Double hydraulic failure Double FAC failure Double SFCC slat channel failure Yaw damper function loss Double aileron Double ELAC failure All spoilers loss Triple SEC failure THS jammed ELAC2 + hyd B ELAC1 + hyd G ELAC1 + hyd Y Triple IRS failure Double IRS failure (2nd not self detected) Double R/A failure when landing gear down
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Direct Laws
Landing gear down
Alternate LawsAirbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Control law reconfiguration Direct LawPitch attitudePitch limits
Load factor
Bank angle Pitch normal law Pitch direct law Roll normal law Roll direct law
Ground mode AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Flare mode
Ground mode
High AOA
AIR FLOW
High speed The direct law provides the Handling characteristics of a natural Aircraft.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Control law reconfiguration Direct LawIn direct law, the aircraft is a natural aircraft with improved handling characteristics compared to a non fly-by-wire aircraft:SIDESTICKFLIGHT CONTROL COMPUTER Surface deection
Surface deflection order kinematic (CG, configuration)
Aircraft response
In pitch: The
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
elevator deflection is proportional to the stick deflection maximum deflection is a function of configuration and CG. The aircraft response is homogeneous regardless of configuration and CG. The pitch trim is manually controlled using trim wheel.
In roll: The
aileron / spoiler deflections depend upon the stick deflection and on aircraft configuration. The aircraft response is homogeneous regardless of configuration. Simple yaw damping and limited turn co-ordination are provided as a function of yaw rate and stick deflection.Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2 October 2004 Page
Monday, February 27, 12
Control and indicating (A318-A319-A320-A321)
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
Page
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This document and all information contained herein is the sole property of AIRBUS S.A.S. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS S.A.S. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, AIRBUS S.A.S. will be pleased to explain the basis thereof.
AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Airbus Fly-By-Wire Overview - EYDCC - Ref. D27PR0302099 - Issue 2
October 2004
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