Civil Avionics Systems
Ian Moir Allan G Seabridge Display chapter contributed by Malcolm Jukes
Professional Engineering Publishing Limited, London and Bury St Edmunds, UK
This edition published 2003 by Professional Engineering Publishing, UK. Published in USA by American Institute of Aeronautics and Astronautics, Inc. This publication is copyright under the Berne Convention and the International Copyright Convention. All rights reserved. Apart from any fair dealing for the purpose of private study, research, criticism, or review, as permitted under the Copyright Designs and Patents Act 1988, no part may be reproduced, stored in a retrieval system, or transmitted in any form or by any means, electronic, electrical, chemical, mechanical, photocopying, recording or otherwise, without the prior permission of the copyright owners. Unlicensed multiple copying of this publication is illegal. Inquiries should be addressed to: The Publishing Editor, Professional Engineering Publishing Limited, Northgate Avenue, Bury St Edmunds, Suffolk, IP32 6BW, UK.
ISBN 1 86058 342 3
Copyright © 2003 Ian Moir and Allan Seabridge.
A CIP catalogue record for this book is available from the British Library.
The publishers are not responsible for any statement made in this publication. Data, discussion, and conclusions developed by the authors are for information only and are not intended for use without independent substantiating investigation on the part of the potential users. Opinions expressed are those of the authors and are not necessarily those of the Institution of Mechanical Engineers or its publishers.
Printed and bound in Great Britain by St Edmundsbury Press Limited, Suffolk, UK
Cover image © Airbus
About the Authors Ian Moir BSc, CEng, FRAeS, FIEE served twenty years in the Royal Air Force as an Engineering Cadet/Officer, retiring with the rank of Squadron Leader. He then went on to work for eighteen years at Smiths Industries, Cheltenham, UK. Here he had responsibilities for the introduction of avionics technology into aircraft utilities systems on both military and civil aircraft. He was Programme Manager for the integrated Utilities Management System on the UK Experimental Aircraft Programme (EAP); and technology demonstrator for the European Fighter Aircraft. Ian’s principal successes at Smiths Industries included the selection and development of new integrated systems for the McDonnell Douglas/Boeing AH-64C/D Longbow Apache attack helicopter and Boeing 777 (Queens Award for Technology – 1998), both of which are major production programmes. Ian has over 40 years’ experience in the aerospace industry. He is currently an International Aerospace consultant, operating in the areas of aircraft electrical and utilities systems and avionics. Allan Seabridge BA, MPhil is currently the Chief Flight Systems Engineer at BAE SYSTEMS, a position held since 1998. Before that he was the Avionics Integrated Product Team Leader on the Nimrod MRA4 programme for five years. He has worked in the aerospace industry for over 30 years in flight systems and avionic systems engineering, business development, and project management. He has been involved in a wide range of military fast jet, trainer, and ground or maritime surveillance aircraft projects. Allan has worked in many international collaborative programmes in Europe and the United States, and he has led a number of national and international engineering teams. This has led to an interest in all aspects of system engineering capability – the practice of engineering, the processes and tools employed, and the people and skills required. Malcolm Jukes BSc, FRAeS, FIEE has over 35 years’ experience in the aerospace industry, mostly working for the Smiths Group at Cheltenham, UK. Among his many responsibilities as Chief Engineer for Defence Systems Cheltenham, Malcolm managed the design and experimental flight trials of the first UK Electronic Flight Instrument System (EFIS) and subsequently the development and application of shadow-mask CRT technology for multi-function, head-down displays on the F/A-18, AV8B, Eurofighter Typhoon and EH101 aircraft. In this role, and and subsequently as Technology Director, for he was responsible for product technical strategy the acquisition of new technology Smiths UK aerospace products. One of his most significant activities was the application of AMLCD technology to civil and military aerospace applications. Malcolm is now an aerospace consultant operating in the areas of displays, display systems, and mission computing.
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Contents Acknowledgements ForewoTrb Bu dycker ForeworC bB dyosgrove
xiii xiv xv
Authors’ Preface Acronymasnd Abbreviations
xvi xvii
ChapteIr– n1troduction
1
Chapter A 2 – vionicT s echnology Thenatureofmicroelectronicdevices Processors Memory devices Digital data buses Databusexamples–integrationofaircraftsystems Regionalaircraft/businessjets Fibre-optic buses Avionicspackaging–LineReplaceableUnits Typical LRU architecture Environmental conditions Integrated Modular Avionics Software References
5 7
Chapter 3–SystemD s evelopment System design Keyagenciesanddocumentation Designguidelinesandcertificationtechniques EquivalenceofUSandEuropeanSpecifications Interrelation of processes Requirements capture
Requirements example Fault Tree Analysiscapture FailureModesandEffectsAnalysis(FMEA) Component reliability Dispatch reliability Markov Analysis Development processes
10 11 11 21 24 25 26 27 28 30 31 32 33 34 34 34 37 37 40
43 42 45 46 47 48 50
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The produce life cycle Development programme ‘V’ diagram ETOPSandLROPSrequirements References
50 57 58 59 62
Chapter 4 ElectricaSl ystems – Aircraftelectricalsystemcharacteristics Power generation DC power generation
AC power generation Power generation control Modernelectricalpowergenerationtypes Electrical power quality Primary power distribution Powerconversionandenergystorage Batteries Secondary power distribution Power switching Load protection Solid state power controllers Electrical loads Motors and actuation Lighting Heating Subsystemcontrollersandavionicssystems Ground power Emergency power generation Ram Turbine Air Back-up converters Permanent magnet generators Typical aircraft DC system Typicalciviltransportaircraftsystems Civilaircraftelectricalsystemexamples Boeing 767 Boeing 747-400 Airbus A330/340 Boeing 777 Airbus A380 More-Electric Aircraft (MEA) Electrical system displays Aircraft wiring References ChaptS ere–n5sors data Air Magnetic sensing MagneticHeadingReferenceSystem(MHRS) Inertial navigation
63
65 65 65 6668 72 76 77 78 80 81 81 81 82 82 82 84 84 85 85 86 86 87 88 88 90 90 91 92 94 95 97 97 97 98 99 101 101 110 112 115
Contents
Inertial sensing Inertial navigation Inertial platforms Strapdown systems Radar sensors Radar altimeter Doppler radar Weather radar References
115 118 119 121 122 122 125 126 128
C haFrequency pter6 –Cspectrum ommunicationsandNavigationAids Radio Communications systems High Frequency Very High Frequency Satellite communications AirTrafficControl(ATC)transponder TrafficCollisionandAvoidanceSystem Communicationscontrolsystem Navigation aids Automatic Direction Finding VeryHighFrequencyOmni-Range DistanceMeasuringEquipment TACAN VORTAC Satellitenavigation systems Instrument Landing System TransponderLandingSystem(TLS) MicrowaveLandingSystem(MLS) Hyberbolicnavigationsystems References
129 130 132 134 135 138 141 144 146 146 147 147 148 149 150 150 153 156 156 157 159
ChapteDr–is7plays Introduction Theelectromechanicalinstrumentedflightdeck Earlyflightdeckinstruments The1950s–piston-enginedaircraft The 1970s jet – aircraft TheAttitudeDirectionIndicator TheHorizontalSituationIndicator altimeter The TheAirspeed Indicator(ASI) Standby instruments
161
The ‘glass’ flight deck Advancedcivilflightdeckresearch BAC1-11technologydemonstrator Boeing 757 and 767 BritishAerospaceadvancedturbo-prop Airbus A320/A330
161 161 161 162 164 166 168 168 169 171 171 171 172 175 175 176
ix
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Boeing 747-400 Upgradeof‘Classic’ aircraftflightdecks Glass standby instruments Airworthiness regulations Regulatory requirements Certification guidelines Display format guidelines Display system architectures Display suite components Display systems
178 179 182 183 183 184 185 186 186 189
Electronicflightinstrumentsystems CombinedEFISandEICAS/ECAMsystems Modularavionicsdisplaysystems Display media Visual requirements Environmental requirements Electricalpowersupplytransientimmunity The Cathode Ray Tube TheActiveMatrixLiquidCrystalDisplay Displaysfortheflightdeckofthefuture Largeareahead-downdisplays Three-dimensional and four-dimensional display formats The Head-Up Display References
189 192 193 194 194 195 195 196
ChapteN r–8 avigation Basic navigation Radio navigation Oceanic crossings Inertial navigation AirDataandInertialReferenceSystems(ADIRS) Satellite navigation error GPS Differential GPS Integrated navigation Sensorusage–phasesofflight GPS overlay programme Categories of GPS receiver FlightManagementSystem(FMS) FMSControlandDisplayUnit(FMSCDU) FMS procedures FANS TerrainAwarenessandWarningSystem(TAWS) GPWS and EGPWS References
215 215 218 220 220 223 226 227 227 229 230 232 232 232 236 244 246 246 247 248
Chapter 9–FlightControS l ys te m s Inter-relationshipofflightcontrolfunctions Flightcontrol–framesofreference Flight control systems
199 205 205 207 209 213
251 251 253 254
Contents
Mechanical back-up Flight control actuation Flightcontrolandmonitoringrequirements Airbus FBW philosophy Boeing777flightcontrolsystem Top-levelBoeing777PFCSoverview AutopilotFlightDirectorSystems(AFDSs) Autopilot modes Integratedautopilotsystem–Boeing777AFDS Autoland Flight Management System Futuresystems–AirbusA380FBW Flight Data Recorders References Chapter 10–EngineandUtilitySystems Engine systems Enginecontrolonamoderncivilaircraft Air and environmentalsystems Controlled environment for crew, passengers, and equipment systems Fuel Characteristicsoffuelsystems Fuel system components Integratedcivilaircraftfuelsystems Hydraulic systems Hydraulic system services Emergencyhydraulicpowersources Civil transport comparison Landing gear systems Central maintenance systems AirbusA330/340CentralMaintenanceSystem Boeing 777 Central Maintenance Computing System In-Flight Entertainment In-FlightEntertainment(IFE) Rockwell Collins I2S References Chapter 11–SystemsIntegration Advantages Disadvantages Open architecture issues Component obsolescence Definition of IMA cabinets – first-, second-, and third-generation
implementations First-generation IMA Second-generation IMA Third-generation IMA IMA Examples References
255 255 259 260 264 271 273 277 279 280 283 286
282
287 289 289 290 293 293 300 301 301 302 309 309 311 311 315 317 318 321 322 322 324 327 329
331 331 332 333 334 334 335 335 336 347
xi
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Chapter 12–FutureAir NavigationSystem Communications Air–ground VHF data link Air–groundSATCOMcommunications link data HF 8.33kHzVHFvoicecommunications Navigation Classic method for defining navigation performance RNP RNAV RNAV standardswithinEurope
34 9
350 350 351 351
RVSM RVSM implementation DifferentialGPSenhancements Protected ILS Introduction of the Microwave Landing System (MLS) Polar routes Surveillance TCAS S Mode ATC 366 Automatic Dependent Surveillance – address mode (ADS-A) Automatic Dependent Surveillance – broadcast 367mode (ADS-B) Direct Routing Need for flight management systems (FMS) BoeingFANS1Implementation AirbusFANS-A Implementation High-precision approaches
352 352 352 356 358 361 361 363 365 365 365 366 366 367 367 367 368 368 369 370
References Chapter 13–MilitaryAircraftAdaptation Avionicandmissionsysteminterface Navigation and flight management Navigation aids Flight deck displays Communications Aircraft systems Applications Personnel,matériel,andvehicletransport Air-to-air refuelling Maritime patrol Airborne early warning Ground surveillance Electronic warfare Flying classroom Range target/safety References Index
373 37 5 376
379 380 381 382 383 383 383 384 385 388 388 389 390 390 390 391
Acknowledgements The authors have been practising aerospace engineers with a collective experience approaching 80 years, much of that time spent in the specification, design, and development of avionics and utilities systems for high-performance military aircraft and civil aircraft. It is a truism that the more experience and knowledge gained with modern avionics systems, the more it is realized how extensive the subject is and how very much more there is to learn. The writing of this book would not have been possible without the generous support, advice, and guidance of many colleagues, specialists, and companies on both sides of the Atlantic. Special mention must be made of Malcolm Jukes, formerly of Smiths Aerospace, who added his considerable and specialized experience to the preparation of the book; especially in the Displays chapter – Chapter 7. The comprehensive nature of the book would not have been possible without the dedication and persistence of those who reviewed the book and offered advice as to how it could be improved: Michael I Braasch of Ohio University, US Derek Bracknell of QinetiQ, UK Mike Hirst of Loughborough University, UK Dr Amy Prichard of Georgia Institute of Technology, US During the writing and review of the book generous help has also been given by a wide range of individuals and specialists who have provided specialized support in their fields of expertise to ensure that the details of all the systems described are accurate. Invaluable support and assistance have been given by the following companies and organizations: Airbus BAE SYSTEMS Boeing Bombardier Aerospace CMC Electronics Duxford Imperial War Museum Honeywell Korry Electronics Micro Circuit Electronics
Northrop Grumman Corporation Parker Aerospace Raytheon Rockwell Collins Society of Automobile Engineers (SAE) Smiths Aerospace QinetiQ VDO Luftfahrtgerate Werk
Foreword
by B Tucker
Over the past forty years, the development of aircraft for civil applications has been enhanced by the increasing introduction of electronic systems to enable greater operational freedom, safety, and efficiency to be achieved. These electronic systems, called avionics, have been at the heart of the creation of the sophisticated commercial airliners of today and they will play an important part in the succeeding generations of aircraft in the 21st century. Avionics systems have played a key role in the great advances in air safety, which have been a feature of the past few decades. They have played a major part in providing safe and affordable long-haul travel for business and leisure users. In addition, parallel developments for military aircraft have offered technologies for both civil and military applications, and techniques developed in one area have transferred to the other with rapidity and ease. Both civil and military avionics systems have utilized, to a very large extent, the revolution in computing that has so much changed the growth of technology since the 1950s. To keep up to date with these avionics systems can be a formidable task, made more complex by the architectural concepts within which avionics systems lie. Technological advances in processing, memory, displays, and data communication systems have made, and will continue to make, significant changes to individual systems and systems architectures in a constant striving for even better safety, maintainability, and operating costs. This book offers the reader an opportunity to understand the evolution of the systems being employed today, and it gives detailed explanations of the architecture within which they operate and the concept of operations of the avionics systems. As electronic systems began to emerge into the commercial aircraft, they essentially operated independently of each other and could be considered and certificated, from that viewpoint. This situation has changed very rapidly over the last two decades and today the interaction between systems is both complex and essential for safe aircraft operation. The reader will be able to understand these interactions from the text and this will enable a good basis for realizing the implications of even greater integration in new aircraft. The next generation of avionics systems will also achieve much greater integration with the whole Air Traffic Management infrastructure and this book will help in preparing the reader for these developing concepts. The field of avionics is extremely wide and it is commendable that this book manages to cover such a wide area, and yet give detailed information on many of today’s key systems. I hope that you will enjoy reading the book and that it will aid the reader’s understanding of the enormous progress that has been made over the past decades in the systems on aircraft and the opportunity that new avionics systems will bring to safety, operational efficiency, and the comfort and convenience of passengers.
Brian G S Tucker OBE, BSc(Hons), FRAeS, CEng,. Senior Vice President, Business Acquisition & Customer Relations, BAE SYSTEMS
Foreword
by B Cosgrove
There can be few of us who have not been touched in the last four decades by the modern miracle of air travel; the ability to step onto an aeroplane and alight in some exotic and distant location within a matter of hours. As well as serving the business traveller, the availability of cheap and safe air transport has brought worldwide mobility within the scope of most people who wish to travel. As the world becomes smaller, families can re-unite and young folk can travel the world and gain experiences that their parents – and certainly grand-parents – could hardly have dreamt of. The advances of air travel were caused by new developments in aerodynamics, airplane structures, propulsion systems, and the advances in aircraft avionics systems. Avionics systems embraced the application of electronics to control all the vital aircraft functions. These systems can involve the display of data to the flight crew, navigation of the aircraft, communications, flight control and fly-by-wire, and automatic control of the aircraft flight path. They also control many of the housekeeping functions on the aircraft: fuel, hydraulics, environmental, and other systems vital to the safe flight of the aircraft and the comfort of those on-board. To achieve a comprehensive understanding of this multitude of systems is a daunting task. In particular, aircraft could not operate in the crowded skies of today without the comprehensive and accurate knowledge of aircraft position, height, track, etc. that the avionics systems bring. The accurate navigation capability that modern systems bestow enable fuel economy to be maximized and adverse environmental effects and noise footprints to be minimized. Finally, the development of in-flight entertainment systems and rapidly improving air–ground broad-band connectivity enable the entertainment and business needs of the passengers to be satisfied. These systems also evolve swiftly as the enabling micro-electronic technology rapidly advances, and it is difficult to capture this development in a single reference. In Civil Avionics Systems Ian Moir and Allan Seabridge have succeeded in encapsulating all these topics in a single book, written in a clear, concise, and easily understood way. As well as documenting the newer developments, the authors have also presented a historical perspective to enable the reader to understand why systems have evolved in the way they have. This work will be of benefit to many throughout the Industry, whether they are students just embarking upon their career, or senior managers and engineers who wish to keep abreast of the latest technology improvements.
Benjamin A. Cosgrove, NAE, Fellow of the AIAA and RAeS, 1991 recipient of the Wright Brothers Trophy, Retired Senior Vice President of Engineering, Boeing Commercial Airplane Group
Authors’ Preface Civil Avionics Systems is a companion to our book Aircraft Systems. Together the books describe the complete set of systems that form an essential part of modern military and commercial aircraft. There is much common ground – many basic aircraft systems such as fuel, air, flight control, and hydraulics are common to both types, and modern military aircraft are incorporating commercially available avionic systems such as liquid crystal cockpit displays and flight management systems. Avionics is an acronym that broadly applies to AVIation (and space) electrONICS. Civil avionic systems are a key component of the modern airliner and business jet. They provide the essential aspects of navigation, human–machine interface, and external communications for operation in the busy commercial airways. The civil avionic industry, like the commercial aircraft industry it serves, is driven by regulatory, business, commercial, and technology pressures and it is a dynamic environment in which risk must be managed carefully and balanced against performance improvement. The result of many years of improvement by systems engineers is better performance, improved safety, and improved passenger facilities. Civil Avionics Systems provides an explanation of avionic systems used in modern aircraft, together with an understanding of the technology and the design process involved. The explanation is aimed at workers in the aerospace environment – researchers, engineers, designers, maintainers, and operators. It is, however, aimed at a wider audience than the engineering population; it will be of interest to people working in marketing, procurement, manufacturing, commercial, financial and legal departments. Furthermore, it is intended to complement undergraduate and post graduate courses in aerospace systems to provide a path to an exciting career in aerospace engineering. The book is intended to operate at a number of levels: ● ●
●
providing a top-level overview of avionic systems with some historical background; providing a more in-depth description of individual systems and integrated systems for practitioners; providing references and suggestions for further reading for those who wish to develop their knowledge further.
We have tried to deal with a complex subject in a straightforward, descriptive manner. We have included aspects of technology and development to put the systems into a rapidly changing context. To fully understand the individual systems and integrated architectures of systems to meet specific customer requirements is a long and complicated business. We hope that this book makes a contribution to that understanding.
Ian Moir and Allan Seabridge 2003
Acronyms and Abbreviations A429 ARINC 429 A600 ARINC 600 A629 ARINC 629 A Amperes AC Advisory Circular (FAA) AC Alternating Current ACARS Aircraft Communications And Reporting System ACE Actuator Control Electronics (Boeing 777 flight control system) ACFD Advanced Civil Flight Deck ACM Air Cycle Machine ACMP AC Motor Pump A/D Analogue to Digital ADC Air Data Computer ADD Airstream Direction Detector ADF Automatic Direction Finding
AIMS Airplane Information Management System (Boeing 777) ALT Barometric Altitude AM Amplitude Modulation AMJ Advisory Material Joint AMLCD Active Matrix Liquid Crystal Display AMSL Above Mean Sea Level ANP Actual Navigation Performance AoA Angle of Attack AOC Airline Operation Centre AOR–E Azores Ocean Region - East AOR–W Azores Ocean Region - West APB Auxiliary Power Breaker APEX Application Executive API Application Implementation APU Auxiliary Power Unit ARINC Air Radio INC
BNR Binary BR Bus Request (1553B) BPCU Bus Power Control Unit BRNAV Basic RNAV BSCU Brake System Control Unit (Boeing 777) BTB Bus Tie Breaker BTC Bus Tie Contactor BTMU Brake Temperature Monitoring Unit C Centre CA Course/Acquisition (GPS code) CAA Civil Aviation Authority CADC Central Air Data Computer CAS Calibrated Airspeed Cat I Category I approach Cat II Category II approach Cat III Category III approach CBIT Continuous Built-In Test
ADI Attitude Direction Indicator ADIRS Air Data and Inertial Reference System ADIRU Air Data and Inertial Reference Unit (Boeing 777) ADM Air Data Module ADP Air Driven Pump ADS-A Automatic Dependent Surveillance – Address Mode ADS-B Automatic Dependent Surveillance – Broadcast Mode Aero-C SATCOM operating configuration – PC capability Aero-H/H+ SATCOM operating configuration – high gain global capability Aero-I SATCOM operating configuration – medium gain over-land capability Aero-M SATCOM operating configuration – single channel AEW Airborne Early Warning AFCS Automatic Flight Control System AFDC Autopilot Flight Director Computer AFDS Autopilot Flight Director System AFDX Avionics Fast Switched Ethernet AGCU APU GCU AHARS Attitude and Heading Reference System
ARP Aerospace Recommended Practice AS Aerospace Standard (SAE) ASCB Avionics Standard CommunicationBus ASI AirSpeed Indicator ASIC Application Specific Integrated Circuit ASTOR Airborne STand Off Radar ATA Air Transport Association ATC Air Traffic Control ATI Air Transport Instrument ATM Air Transport Management ATN Aeronautical Telecommunications Network ATP Advanced Turbo-Prop ATR Air Transport Radio ATSU Air Traffic Services Unit AVM Airframe Vibration Monitor AWACS Airborne Warning And Control System BAC British Aircraft Corporation (forefather of BAe) BAe British Aerospace (UK) BAES BAE SYSTEMS BC Bus Controller BCAG Boeing Commercial Airplane Group BCD Binary Coded Decimal BCU Bus Control Unit (Boeing 747-400) BIT Built-In Test BITE Built-In Test Equipment
CBLTM Control-By-LightTM (Raytheon fibreoptic data bus) CCA Common Cause Analysis CCB Converter Control Breaker (Boeing 777) CCD Cursor Control Device CDI Course Deviation Indicator CDR Critical Design Review CD ROM Compact Disc Read Only Memory CDU Control and Display Unit CF Course to a fix CF Constant Frequency CFIT Controlled Flight Into Terrain CH Channel CIV Centre Interconnect Valve CMA Common Mode Analysi s CMCS Central Maintenance Computing System (Boeing 777) CMM Capability Maturity Model CMS Central Maintenance System (Airbus) CNS Communications, Navigation, Surveillance C of G, CG Centre of Gravity COTS Commercial Off-The Shelf CPDLC Controller to Pilot Data Link Communications CPM Central Processing Module
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CPU Central Processing Unit CRT Cathode Ray Tube CSD Constant Speed Drive CSDB Commercial Standard Data Bus CTC Cabin Temperature Controller Cu in Cubic Inches CW Continuous Wave DA Decision Altitude – referenced to sea level D/A Digital to Analogue DAPS Data Access Protocol System (ATC mode S) DATAC Digital Autonomous Terminal Access Communication DC Direct Current DCDU Datalink Display and Control Unit (FANS A) Def Stan Defence Standard DEOS Digital Engine Operating System DF Direct to a Fix DFDR Digital Flight Data Recorder DFDRS Digital Flight Data Recording System DFDAU Digital Flight Data Acquisition Unit DFGC Digital Flight Guidance Computers DG Directional Gyro DGPS Differential GPS DH Decision Height – referenced to terrain DLP Digital Light Projector DMC Display Management Computer DMD Digital Micromirror Device DME Distance Measuring Equipment
EGPWS Enhanced Ground Proximity Warning System EHA ElectroHydrostatic Actuator EHF Extremely High Frequency EHSI Electronic Horizontal Situation Indicator EICAS Engine Indication and Crew Alerting System (Boeing and others) ELAC Elevator/Aileron Computer (A320 flight control system) ELCU Electronic Load Control Unit elec electrical ELM Extended Length Messages (ATC mode S) ELMS Electrical Load Management System (Boeing 777) EMA Electro-Mechanical Actuator EMC ElectroMagnetic Compatibility EMI Electro-Magnetic Interference EMP Electrical Motor Pump EPC External Power Contactor EPIC Honeywell integrated avionics system EPR Engine Pressure Ratio EPROM Electrically Programmable Read Only Memory ESA European Space Agency ESM Electronic Support Measures ESS Environmental Stress Screening ETA Estimated Time of Arrival ETOPS Extended Range Twin Operations EU Electronic Unit EUROCAE European Organisation for Civil Aviation Equipment
FCSC Flight Control Secondary Computer (A330/340 flight control system) FD Flight Director FDAU Flight Data Acquisition Unit FDC Fuel Data Concentrator (Airbus A340500/600) FDDI Fibre Distributed Data Interface FDR Flight Data Recorder FDX Fast Switched Ethernet FHA Functional Hazard Analysis FIS Flight Information Services FL Flight Level – altitudes defined above transition level FLIR Forward Looking Infra-Red FMEA Failure Modes and Effects Analysis FMES Failure Modes and Effects Summary FMGEC Flight Management Guidance and Envelope Computer (Airbus A330/340 flight control system) FMQGS Fuel Measurement and Quantity Gauging System (Bombardier Global Express) FMS Flight Management System FMSP Flight Mode Selector Panel FMU Fuel Metering Unit FOG Fibre-Optic Gyroscope FQIS Fuel Quantity Indication System FQPU Fuel Quantity Processing Unit (Boeing 777) FSEU Flap/Slats Electronics Unit (Boeing 777) FSK Frequency Shift Keying FSU File Server Unit
DoD Department of Defense DTI Department of Trade and Industry (UK) DU Display Unit DVOR Doppler VOR EADI Electronic Attitude Direction Indicator EAP Experimental Aircraft Programme EAS Equivalent Airspeed EBHA Electrical Back-up Hydraulic Actuator (A380 flight control system) EC European Community ECAM Electronic Centralised Aircraft Monitor (Airbus) ECCM Electronic Counter Counter Measures ECM Electronic Counter Measures ECS Environmental Control System EDP Engine Driven Pump EEC Electronic Engine Controller E2PROM Electrically Erasable
EW Electronics Warfare ext external FA Fix to an Altitude FAA Federal Aviation Administration FAC Flight Augmentation Computer (A320 flight control system) FADEC Full-Authority Digital Engine Control FANS Future Air Navigation System FANS 1 Boeing implementation of FANS functions FANS A Airbus implementation of FANS functions (A330/340) FANS B Airbus implementation of FANS functions (A320) FAR Federal Aviation Regulation FBW Fly-by-Wire FCC Flight Control Computer FCDC Flight Control Data Concentrator (A330/340 flight control system)
FTA Fault Tree Analysis FTE Flight Technical Error Fwd Forward g Acceleration due to gravity GA General Aviation Gallileo Proposed European satellite navigation constellation GCB Generator Control Breaker GCR Generator Control Relay GCU Generator Control Unit GEC General Electric Company (UK) Gen Generator GEO Geo-stationary Earth Orbit GHz 1 x 109 cycles per second GLC Generator Line Contactor GLONASS GLObal NAvigation Satellite System – Russian equivalent to GPS GNSS Global Navigation Satellite System GNSS-1 EGNOS Concept GNSS-2 Gallileo System
EFAProgrammableRead-Only European Fighter AircraftMemory EFIS Electronic Flight Instrument System EGT Exhaust Gas Temperature EGNOS European Geo-stationary Navigation Overlay System
FCMC Fuel Control Monitoring Computer (Airbusand A340-500/600) FCMS Fuel Control and Monitoring System (Airbus A340-500/600) FCPC Flight Control Primary Computer (A330/340 flight control system)
GPCU Ground Power Control Unit GPS Global Positioning System GPWS Ground Proximity Warning System GS Glide slope H Earth’s Magnet Field HDD Head-Down Display
Ac ro ny ms an d Ab br ev ia ti on s
xix
Hex Heat Exchanger HF High Frequency HF Height to a fix HFDL High Frequency Data Link HIRF High Intensity Radio Frequency HMSU Hydraulic Systems Monitoring Unit (Airbus) HOL High Order Lang uage HP High Pressure HSI Horizontal Situation Indicators HUD Head-Up Display HX Holding to Fix HYDIM Hydraulic system control card (Boeing) Hz Frequency – cycles per second I2t I Squared versus Time – electrical trip characteristic IAP Integrated Actuator Package IAS Indicated Airspeed IBIT Initiated Built In Test IC Integrated Circuit ICO Instinctive Cut-Out ICAO International Civil Aviation Organisation IDG Integrated Drive Generator IF Initial Fix IFE In-Flight Entertainment IFF Identification Friend or Foe IFR Instrument Flight Rules IFSD In-Flight Shut-Down IGV Inlet Guide Vane I2S Integrated Information System (Rockwell Collins)
Distribution System kHz 1 x 103 cycles per second kVA Kilowatt Volts-Amperes kW Kilowatt L Left L Level (fluid) LAAS Local Area Augmentation System (GPS enhancement) LAN Local Area Network lb Pound(s) - mass LC Liquid Crystal LCoS Liquid Crystal on Silicon LED Light Emitting Diode LF Low Frequency LISA Limited Instruction Set Architecture LIV Left Interconnect Valve LNA Low Noise Amplifier (SATCOM) LNAV Lateral Navigation LORAN LOng RAnge Navigation (LORAN C is latest variant) LOX Liquid Oxygen LP Low Pressure LRM Line Replaceable Module LROPS Long Range Operations LRU Line Replaceable Unit LSB Lower Sideband LSI Large Scale Integration L Slat Left Slat (MD-80 AFDS) MA Markov Analysis Mach, M Mach Number MAD Magnetic Anomaly Detector MAT Maintenance Access Terminal (Boeing 777)
Standard MPA Maritime Patrol Aircraft MSAS Multifunction Satellite Augmentation System (Japan) MSL Mean Sea Level MSI Medium Scale Integration MTBF Mean Time Between Failure MTI Moving Target Indication NAS National Airspace System NAT North Atlantic NATO North Atlantic Treaty Organisation NAV Navigation (Mode) ND Navigation Display NDB Non-Directional Beacon NOTAM Notice to Airmen nm Nautical Miles NH or N2 Engine speed – high pressure shaft Ni-Cd Nickel-Cadmium NL or N1 Engine speed – low pressure shaft OAT Outside Air Temperature OBOGs On-Board Oxygen Generating System OEM Original Equipment Manufacturer O/H Overheat OMS On-board Maintenance System OP Overhead Panel P Pressure Pc Capsule Pressure PC Personal Computer PCU Power Control Unit (Boeing 777 flight control system) Pd Dynamic Air Pressure
ILS Instrument Landing System IMA Integrated Modular Avionics IN Inertial Navigator in Inch(es) INMARSAT International Maritime Satellite Organisation INS Inertial Navigation System Inv Inverter I/O Input/Output IOC Initial Operational Capability IOM Input/Output Module IOR Indian Ocean Region IP Intermediate Pressure (Rolls-Royce triple-shaft engines) IPT Integrated Product Team IR Infra-Red IRP Integrated Refuelling Panel IRS Inertial Reference System ISA Instruction Set architecture ISIS Integrated Standby Instrument System
MAU Modular Avionics Unit (Honeywell EPIC) mb milli-bar(s) Mb Mega Bit Mb/sec Mega Bits per second MCDU Multi-function Control and Display Unit MCM Multi-Chip Module MCU Modular Concept Unit MDA Minimum Decision Altitude MEA More-Electric Aircraft MF Medium Frequency MHRS Magnetic Heading Reference System MHz 1 x 106 cycles per second MIL-STD Military Standard MLS Microwave Landing System Mmo Maximum Operating Mach Number MMR Multi-Mode Receiver MNPS Minimum Navigation Performance
PDA Power Distribution Assembly PDR Preliminary Design Review PFC Primary Flight Computer PFCS Primary Flight Control System (Boeing 777) PFD Primary Flight Display PMA Permanent Magnet Alternator PMAT Portable Maintenance Access Terminal PMG Permanent Magnet Generator POR Pacific Ocean Region PPS Precise Positioning System (GPS) PRA Particular Risks Analysis Pri Primary PRNAV Precision Area Navigation PROM Programmable Read-Only Memory PRSOV Pressure Reducing Shut-off Valve Ps Static Air Pressure PSEU Proximity Switch Electronics Unit (Boeing 777)
ISS Integrated Sensor Suite IT Information Technology ITO Indium Tin Oxide JAA Joint Aviation Authorities JAR Joint Aviation Regulation JSF Joint Strike Fighter JTIDS Joint Tactical Information
Specification Mode A ATC Mode A (range and bearing) Mode C ATC Mode C (range, bearing and altitude) Mode S ATC Mode S (range, bearing, altitude and unique identifier) MOPS Minimum Operational Performance
PSR Surveillance PSSAPrimary Preliminary System Radar Safety Analysis PSU Power Supply Unit Pt Total Air Pressure PTU Power Transfer Unit QFE Altimeter Setting relating to a specific feature eg airport
xx
Civil Avionics Systems
QNH Altimeter Setting related to sea level R Right RA Resolution Advisory (TCAS II only) Rad Alt Radar Altimeter RAE Royal Aircraft Establishment (UK) RAF Royal Air Force RAIM Receiver Autonomous Integrity Monitor RAM Random Access Memory RAT Ram Air Turbine RCT Rear Cargo Tank (Airbus A340-500) Rcv Receive R&D Research and Development RDCP Refuel/Defuel Control Panel (Bombardier Global Express) Recirc Recirculation RF Radio Frequency RF Route to a fix RFI Request For Information RFP Request For Proposal RFU Radio Frequency Unit (SATCOM) RGB Red; Green; Blue RISA Reduced Instruction Set Architecture RLG Ring Laser Gyro RMI Radio Magnetic Indicator RNAV Area Navigation RNP Required Navigation Performance ROM Read-Only Memory RS Electronic Industries Association Recommended Standard R Slat Right Slat (MD-80 AFDS) RSS Root Sum Squared RT Remote Terminal
SEC Spoiler/Elevator Computers (A320 flight control system) SELCAL SELective CALling SFCC Slat/Flap Control Computer (A330/340 flight control system) SG Symbol Generator SG Synchronisation Gap (ARINC 629 data bus) SHF Super High Frequency SI Smiths Industries (UK), now Smiths Aerospace SIB System Isolation Breaker SID Standard Instrument Departure SIAP Standard Instrument Approach Procedure SIGINT SIGnals INTelligence SIM Serial Interface Module SIOM Standard Input/Output Module SIU Secure Interface Unit SLAR Sideways Looking Aperture Radar SLR Sideways Looking Radar SMP Systems Management Processor SOV Shut-Off Valve SPS Standard Positioning System (GPS) SRR System Requirements Review SS Sub-System (1553B) SSA System Safety Analysis SSB Single Sideband SSB Split System Breaker (Boeing 747-400) SSI Small Scale Integration SSPC Solid-State Power Controller SSR Secondary Surveillance Radar SSR Software Specification Review
TLS Transponder Landing System TPMU Tyre Pressure Monitoring Unit T/R Transmit/Receive TRU Transformer Rectifier Unit TSO Technical Service Order (FAA) TURB Turbulence Mode – Weather Radar TV Television UHF Ultra High Frequency UK United Kingdom UPS United Parcels Service ULD Underwater Locating Device US United States usa Useable Screen Area USB Upper Sideband UV Ultra-Violet VAC Volts AC VCS Voice Command System VDC Volts DC VDL VHF Data Link ‘V’ Diagram Validation and Verification Procedure VDR VHF Digital Radio VF Variable Frequency VFR Visual Flight Rules VG Vertical Gyro VHF Very High Frequency VHFDL Very High Frequency Data Link VHPIC Very High Performance Integrated Circuit VLF Very Low Frequency VLSI Very Large Scale Integration Vmo Maximum Operating Speed VMS Vehicle Management System
RTA Required Time of Arrival RTCA Radio Technical Committee Association RTZ Return to Zero RVR Runway Visual Range RVSM Reduced Vertical Separation Minima RW Runway SAARU Secondary Attitude Air Data Reference Unit (Boeing 777) SAE Society of Automobile Engineers SAFEbus® Proprietary Backplane Bus (Honeywell AIMS) SAR Synthetic Aperture Radar SAS Standard Altimeter Setting (29.92inHg/1013.2mb) SAT Static Air Temperature SATCOM SATellite COMmunications SB Sideband SCR Silicon Controlled Rectifier S/D Synchro to Digital
STAR Standard Terminal Approach Routes STC Supplementary Type Certificate STCM Stabiliser Trim Control Module (Boeing 777 flight control system) SV Solenoid Valve SW Switch T Temperature TA Traffic Advisory (TCAS I and II) TAB Tape Automated Bonding TACAN TACtical Air Navigation system TACCO TACtical COmmander TADS Triple Air Data System TAS True Airspeed TAT Total Air Temperature TAWS Terrain Avoidance Warning System TBD To Be Determined TCAS Traffic Collision and Avoidance System TDMA Time Division Multiple Access TF Track to a fix
VNAV Vertical Navigation VOD Video On-Demand VOR Very High Frequency Omni-Range VOR/TAC VOR/TACAN VS Vertical Speed VSCF Variable Speed Constant Frequency VSI Vertical Speed Indicator VSV Variable Stator Vane W Watt WAAS Wide Area Augmentation System (GPS enhancement) WAP Wireless Access Protocol wef With effect from WGS World Geodetic System WOW Weight-On-Wheels Xmt Transmit Xfr Transfer XPC External Power Contactor (Boeing 747-400) XVGA X Video Graphics Adaptor
SDR Review SDU System SatelliteDesign Data Unit (SATCOM) Sec Secondary
TFT Thin Film Transistor TG Terminal Gap THS Tailplane Horizontal Stabiliser
ZSA Zonal Safety Analysis
Data bus ARINC 429 ARINC 629 FDDI Video Bus ‘Firewire’
TYPICAL DRIVERS IT/Domestic markets Commercial/Military Interactions Availability/supportability Airline market forces
Semiconductors Processors Memory ASICs Chip set integration
MIL-STD1553B
Yield
Fibre optic
Commercial Aircraft Avionics Pilot Interface
Software
Display technology
Languages Standards Processes - CMM
Packaging ATR/ARINC 600 IMA
Human Factors Voice I/O Crew workload Safety
Computer 'Revolution' VLSI/MCMs Microelectronics/LSI
Digital Aircraft Systems
Transistors Airborne Radar Developments
Thermionic Valves
19 30
1 94 0
19 5 0
1 9 60
1 97 0
19 80
1 9 90
2 00 0
Analogue Electronic Engine Controls
Part-digital Electronic Engine Control
Engine Control
Full Authority Digital Engine Control
Analogue Primary/Mechanical Backup Digital Secondary Control Digital Primary/Mechanical Backup
Flight Digital Primary/ No Mechanical Backup
Control
1950
1960
1970
1980
1990
2000
' D ig i t aW l o r ld ' Physical parameters represented by digital words: 8 bit; 16 bit 32 bit etc Processors able to process and manipulate digital data extremely rapidly & accurately
'R e aW l o r ld '
D/A Conversion
D/A Chip
Analogue parameters have physical characteristics eg volts; degrees/hour; pitch rate; etc
Value
1
0
16 Bit Data Word
Processor Chip
Memory Chip
Time
8 Bit Flag /Address A/D Chip
A/D Conversion
Digital ASIC
I/O ASIC
Hybrid Chip
Analogue
Digital
1000 gate digital array
8 x Analogue ‘strips: 3 op amps/strip
Bonding Pads ~70
Voltage level shifting/test array
Semiconductor Wafer
Defective Die
Good Die
107 Circuit Level Integration 6
10
p i h C r e p s r o t is n s a r T
Very High Performance (VHPIC)
105
104
103
102
Very Large Scale (VLSI)
Large Scale (LSI)
Medium Scale (MSI)
Small Scale (SSI)
10
1 1 95 0
1 96 0
1 97 0
1 98 0
1 99 0
2000
Time
Sink Source Node 1
Node 1
Sink Node 2 Source Node 2 Sink Node 3 Source Node 2 Sink Node 4
Signal Leads So u LrRcUe
L SR i nUk
Tr a n s m i t te r
Re ce i ve r Shields A429 RTZ Modulation Logic 1
Logic 0
Logic 1 High
Null
To other Receivers (up to 20 maximum)
Low 1 Bit Period = 10microsecond (Clock Rate = 100kHz)
O
4
Label
8
Source Data Identifier
12
16
20
24
28
'Data' - encoded depending upon message type Binary Coded Decimal (BCD) Binary (BNR)
32
Parity Signal Status Matrix
Discretes Alphanumeric Formats etc
Data Rate is 12 to 14 kHz or 100 kHz (100kHz is more usual)
Bus A
Bus B
Bus Controller
Data Data Data Data
Remote Terminal
3U t0op S u b s ys t e m s
Remote Terminal
3U t0op S u b s ys t e m s
20 bits = 20 microseconds 1
2
3
4
5
6
7
8
0
1
1
0
0
9
10
11
12
13
14
15
16
17
18
19
20
Bit Times
Data Word SYNC
Data
Command Word RT Address (5)
T/R (1)
Sub-address Mode (5)
Data word count /mode code (5)
Status Word MessageService Terminal error Request Address (5) (1) (1)
BR recd (1)
Instrumention Reserved (1) (1)
SS Term Flag Flag (1) Dyn (1)
Busy (1)
Bus Control Parity (1) (1)
Remote Terminal A to Bus Controller Transfer
~ 70 microsecondss Bus Controller
Transmit Command
Next
Remote Terminal A
St a t u s W o r d
Da t a Wo r d
#
* Remote Terminal A to Remote Terminal B Transfer
~ 120 microsecondss Bus Controller
Receive Command
Transmit Command
Next
Remote
St a t u s W o r d
Da t a Wo r d
Terminal A Remote Terminal B
Status Word
#
#
*
1553B full Remote Terminal (RT) and Bus Controller Function Two transceiver die may be Mounted on top to drive the 1553 bus transformers Contains a lot of RAM for the storage of 1553 bus messages
MIL-STD-1553B or A629 Bus A
Bus B 32 Terminals max for Mil-STD-1553B
TERMINAL 1
TERMINAL 2
TERMINAL 3
TERMINAL 4
Data Bus
TERMINAL 5
128 Terminals max for ARINC 629
Bus Coupler
Stub
Terminal
Multiple-Source Multiple-Sink
Bus 4
Data Data
Bus 1
Terminal
Terminal Subsystems
Up to 128 Terminals
Terminal
Terminal Subsystems
Terminal 1 TI - Transmit Interval M
TI SG
TG
M
Terminal 2 TI
TI - Transmit Interval TG
M
SG
TG
M
TI
Terminal 3 TI
TI - Transmit Interval TG
TG
M
SG
TG
TG
Major Cycle
Driver 1 Sum
XMT XFR
A629 Terminal Controller
2
Mangt & Cont
Driver 2 Channel Arbitration
Receiver 1
2
RCV XFR
Sum
Stanchion Connector
Serial Interface Module (SIM)
Receiver 2
Coupler
A629 Manchester Biphase
Host LRU 0
1
1
A629 Data Bus
0
-6 seconds or Bit is O.5 x 10 2 Mbits/second
1
2
Sync
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
1 81
92
0
Parity Data (depends upon word type) A629 Word Formats: General Format System Status Word Function Status Word Parameter Validity Word Binary (BNR) Word Discrete Word
Avionics MIL-STD-1553B Data Bus
10 RT
Aircraft Systems
Power Plant Control
Power Plant
BC1 0 R T
BC
Systems
Systems
Management Processor A
Management Processor B
RT 1
RT 2
RT 3
RT 4
Systems Management Processor C
Systems Management Processor D
RT 5
RT 6
Reversionary Instruments
Maintenance RT Data 7 Panel
Aircraft Systems
Power Plant Control
Power Plant
Utilities MIL-STD-1553B Data Bus
Fuel
E l e ct r i ca l Distribution/ Bus C ontr ol Load Management
FQIS
EL M S
L an di nG gear G e ne ra t io n
BPCU
G CU
Brakes/ Antiskid
Ty re Pres sure
BSCU
TPMU
Brak e T emp
BTMU
L R
APU
AS/PCU AS/PCU
Pre ss uris at io n
CTC CTC
PPSEU S EU
Flaps /Slats
Prox SW
Card Card File Files
AV M
Hydraulics, ECS, O/H Det
Ca bi n Te mp
APU + Environmental
FFSEU S EU
Aircraft System A629 Buses
Misc
Vib Mon
Displays
ASCB-D Aircraft Digital Data Buses: Dual Buses 10Mhz bit rate
Up to 48 Terminals [Stations]
Cursor Control Device
Modular Avionics Unit (MAU)
Modular Avionics Unit (MAU)
Cursor Control Device
Terminal A
Terminal D
Terminal B
Fibre- Optic Ring Topology: Terminal C
- Each Link transmits Uni-directional Data - Ring Topology allows Data to be passed from Terminal to Terminal - Dual Ring Topologyallows Data top be passed following a Terminal Failure - Data transfer @ 1.25 MBits/sec
Height
7.64 in
Width
12.76 in
Depth Width:
Depends upon LRU Form Number W = (N x 1.3) - 0.32 in = 1 0.37 in for N of 8 [8 MCU]
Analogue Inputs
Analogue to Digital Conversion (A/D)
Analogue Outputs
Digital to Analogue Conversion (D/A)
Synchro
Discrete Inputs Discrete Outputs
Processor & Memory
ARINC 429 Data Bus Output
Synchro to Digital Conversion (S/D)
Processor Bus
ARINC 426 Data Bus Input
+ 5v
Discrete Inputs & Outputs
+ 15v
-15v
Power Supply Unit
Aircraft Power Supply: 115v AC or 28v DC
Internal EMI Interference Lightning
Electronic Modules
A1
A2
A3
A4
A5
A6
Radiated Susceptability
A7
A8
Power Supply Unit
Aircraft Wiring Connectors
Conducted Susceptability
Aircraft Wiring
EMI Filters
EMI 'Clean' Area
EMI 'Dirty' Area Lightning
External EMI Interference
A
B
Integrated Rack
Line Replaceable Unit (LRU)
C
A B C D
Power Supply Unit E D
G
E
F
H
I
J
ARINC 600 Discrete LRUs
FG H I J
Power Supply Unit
Line Replaceable Module (LRM)
Integrated Modular Avionics (IMA) Cabinet
Safety Assessment Process Guidelines & Methods (ARP 4761) Intended Aircraft Function
Function, Failure & Safety Information
System Design
System Development Processes (ARP 4754) Aircraft System Development Process
Functions & Requirements
Hardware Life-Cycle Process
Hardware Development Life-Cycle (DO-254)
Software Life-Cycle Process
Software Development Life-Cycle (DO-178B)
Implementation
An alysis
Design
Aircraft Level FHA
Aircraft Level Requirement
System-Level FHAs
Aircraft Functions
System Architecture Common Cause Analysis
PSSAs Software Requirements
SSAs
System Implementation
Certification
We need an FMS function to reduce workload and improve accuracy
We need the function of lateral guidance and navigation
We need the following modes of operation:
Top Level System Requirement
Subsystem Module 1
Subsystem Module 2
Subsystem Module 3
Subsystem Module 4
SubModule
SubModule
SubModule
SubModule
- VOR - Inertial - GPS ....etc
1a 1b 1c
2a 2b
3a 3b
4a 4b
Top Level System Requirements Established
Module Functional Inter-action Defined
Subsystem Module 1
SubModule
1a
Subsystem Module 2
Subsystem Module 3
SubModule
SubModule
2a 1b
Subsystem Module 4
SubModule
3a 3b
4a 4b 3c
Individual Functional Sub-Modules and Behaviour Well Documented & Understood
Fuel Jettison Valves (2) 'Open' Fuel Dump Valves (2) 'Open'
Fuel Jettison Select Min Fuel Quantity Set
Isolation Valves (2) Select
Power C
Isolation Valves (2) 'Open'
Power D Fuel Quantity
Fuel Quantity Function
Fuel Quantity
Fuel Management Function
Left Tank Probes (20) Centre Tank Probes (12) Right Tank Probes (20)
Fuel Dump Valves (2) 'Open' Fuel Dump Valves (2) Select Power A Power B
Fuel Transfer Valves (4) Select Fuel Transfer Valves (4) 'Open/Closed'
-9 Target Figure > 1 x 10
Probability of Total Power Loss
Analysis shows: Probabilityof Total Loss = 4.9 x 10-10 which = 0.49 x 10-9
4.9 x 10-10
&
which meets target
4.9 x 10-7
Probability of Loss of Both Main Buses
Probabilty of 1 x 10-3 Failure of RAT to Deploy
&
7.0 x 10-4
Probability of Loss of Main Bus 1
Probability of Loss of Main Bus 2
OR
OR
Probability of Loss of Generator 1
5.0 x 10-4
Probabilty of Loss of GCU 1
2.0 x 10-4
7.0 x 10-4
Probability of Loss of Generator 2
Probability of Loss of GCU 2
5.0 x 10-4
2.0 x 10-4
Generator
Generator Control Unit (GCU) Generator Line Contactor
Main AC Bus
Probability of Dispatch 1.00 0.99 0.98
0.97 0.96
B777 Dispatch Criteria: ' in the event of a failure within a channel, the system shall continue to operate for a further 10 days with at least a 99% likelihood of a second failure not occurring'
5 10 Days without Maintenance Action
15
FADEC Lane A Lane A Monitor Lane A Control
Engine Thrust Demand
Engine Fuel Lane B Monitor
Demand
Lane B Control
FADEC Lane B
CaMa.CbMb 6
CaMa.CbMb
CaMa.CbMb
CaMa.CbMb
2
7
12
CaMa.CbMb
CaMa.CbMb
CaMa.CbMb
3
8
13
CaMa.CbMb
CaMa.CbMb
4
9
CaMa.CbMb
CaMa.CbMb
5
10
CaMa.CbMb
CaMa.CbMb
1
16
CaMa.CbMb 14
CaMa.CbMb 15
CaMa.CbMb 11
N Fa oil u r e s
F a1ilu r e
2 Failures
Fa 3i lu r e s
F a4ilu r e s
Dispatchable Engine
Ca - Control Lane A
Cb - Control Lane B
Controllable Engine
Ma - Monitor Lane A
Mb - Monitor Lane B
Engine Shut-Down
Ca - Control Lane A
(failed)
Ma - Monitor Lane A (failed)
PRODUCT LIFECYCLE Concept
De finition
Design
Build
Test
Operate
Refurbish
Retire
Understand the customer’s emerging needs and arrive at a conceptual system solution. Typical considerations are: How many passengers/stores;What routes/missions; How many operating hours; turnaround time; despatch reliability; autonomous operation; Fleet size; export potential; Direct operating costs; initial purchase price; through life costs.
Concept
Definition
Design
Build
Test
Operate
Refurbish
Retire
Define a system solution that meets the customer’s requirements, and establish feasibility of design and manufacture. Typical considerations are: Safety; Function, operational needs, performance, physical and installation characteristics, interface requirements, qualification and certification requirements.
C oncept
Definition
Design
Build
Test
O per at e
Refurbish
Retire
Detailed design of airframe and systems leading to issue of drawings. Suppliers selected and designing equipment and components. Test, qualification & certification process defined and agreed. Modelling of design solutions to assist qualification.
Concept
Definition
D esi gn
Build
Test
Operate
Refurbish
Retire
Manufacture of sub-assemblies, final assembly of aircraft. Delivery of equipment to build line. Testing of installed systems
Concept
Definition
Design
Build
Test
Operate
Refurbish
Retire
Ground and flight test of the aircraft. Analysis of test data Collation of data to support release to service
Concept
Definition
Design
Build
Test
Operate
Refurbish
Retire
Ground and flight test of the aircraft. Analysis of test data Collation of data to support release to service
Concept
Definition
D esi gn
Build
Test
Operate
Refurbish
Retire
Examine cost of ownership, reliability, obsolescence. Consider Mid-life updates, life extension, re-sale op tions.
Concept
Definition
Design
Build
Test
Operate
Refurbish
Retire
System Design Review (SDR) System Requirements Review (SRR)
Preliminary Design Review (PDR)
Requirements Analysis
Critical Design Review (CDR)
Preliminary Detailed Hardware Hardware Design Design
Hardware Development
Hardware Build
Preliminary System Design
Integration & Test
Requirements Analysis
Preliminary Software Software Detailed Design Design
Software Preliminary Specification Design Review Review (SSR) (PDR)
Software Coding & Test
Critical Design Review (CDR)
Software Development
System Requirement
Development Activities
Develop Software Requirement
Verification Activities Software Requirement
Design Software
Software Requirement Review
Design Review
Software Design
Code Software
Code Review /Module Test Module Code
Integrate Modules
Integrate Hardware/ Software
Module Integration Test
Integrated Module code
Total System Code
System Validation Test
Hardware/ Software Integration Test
System in Service
Severe
Severe
Severe
Benign Demanding Demanding
Demanding
Severe Benign
Benign
Benign Demanding
Severe
Severe
Severe
Diversion Time 480 Minutes
LROPS Four Engined
180 Minutes
ETOPS Twin Engined
Benign
Demanding
Severe
Generator
Power Generation
Generator Control Unit (GCU)
Other Channel(s) GC B
BT B
ELCU or 'Smart Contactor'
High Power Loads
Primary Power Panel
Power Conversion
TRU
AC
Primary Power Distribution
DC
Secondary Power Panel
Secondary Power Distribution
Secondary Aircraft Loads
Shunt Field Winding
Terminal Voltage
G
Voltage Increase
G
Terminal Voltage Voltage Decrease
Control & Regulation Raw AC Pow er
Regulated 3 Phase Power Output
Regulated DC Excitation
Excitation Rotor +
Engine Gearbox
Rotating Diodes
Power Rotor
Excitation Stator
Power Stator
Permanent Magnet Generator [PMG] Regulated DC Excitation
Phase A Phase B
Voltage
A Phase Neutral Point
Phase Voltage = 115VAC
Phase C
Line Voltage = 200VAC
Time C Phase B Phase
Paralleling Contacts B uD sC 1 No
B uD sC 2 No
G2
G1
Equalising Coils
Trim Gen1
Error
Excitation
Detection A
CSD 1
Gen 1
B C
Trim CSD 1 Speed
Error Detection
Trim Gen2 Excitation
Error Detection A
CSD 2
Gen 2
Real Load (Speed)
B C
Trim CSD 2 Speed
Error Detection
Reactive Load (Voltage)
Constant Shaft Speed
Variable Engine Speed Approx 2 : 1 for Turbofan
Constant Speed Drive
Generator
Constant Frequency 3-Phase. 115VAC 400 Hz
Integrated Drive Generator (IDG)
Features: Constant frequency AC power is most commonly used on turbofan aircraft today System is expensive to purchase & maintain; primarily due to complexity of Constant Speed Drive (CSD) Single company monopoly on supply of CSD/IDG Alternate methods of power generation are under consideration
Variable Speed Engine Drive Approx 2 : 1 for Turbofan
Generator
Variable Frequency 3-Phase 115VAC 380 - 720 Hz Power
Features: Simplest form of generating power, cheapest and most reliable Variable frequency has impact upon other aircraft subsystems Motor controllers may be needed for certain aircraft loads Beginning to be adopted for new programmes: gains outweigh disadvantages
Variable Speed Constant Frequency (VSCF) Converter
Variable Speed Shaft Speed Approx 2 : 1 for Turbofan
Constant Frequency 3-Phase 115VAC 400Hz Power
Generator
Features: Conversion of VF electrical power to CF is accomplished by electronic controlled power switching DC Link & Cycloconverter options available Not all implementations have proved to be robust/reliable Cycloconverter shows most promise Still unproven in transport market
Power Contacts
Phase A
Generator or Power Source
High Power Electrical Load
Phase B
Phase C
Contactor Status Auxiliary Contacts
Contactor Control
Contactor Coil
Power Contacts
Phase A
Generator or Power Source
Current Transformers
High Power Electrical Load
Phase B
Phase C
Contactor Status Auxiliary Contacts
Contactor Control
Contactor Coil
Sensing & Control Electronics
Contactor Trip
Phase Current [A, B, C]
Phase A
Feed from Primary 115Vac Bus Bar
Phase B
Transformer Rectifier Unit (TRU)
To 28Vdc Bus Bar & DC Distribution
Phase C
Optional Temperature Status
Aircraft Belly
3
Airflow
Emergency AC Electrical Power
Ram Air Turbine (RAT) Emergency Hydraulic Power
L eE f tng in e
Left Backup Generator
Right Backup Generator
PM G s
Left IDG
Left VF Generator (~ 20kVA)
R ig hEtn gi n e
PMG s Right IDG
3
Flight Control DC System xx
3
Right VF Generator (~ 20kVA)
Backup VSCF Converter
3 Constant Frequency Backup Power
Right Engine
Left Engine APU
Right Main Generator - 1
Left Main Generator - 1 APU Generator - 1
Right Backup (VSCF) Generator - 1
Left Backup (VSCF) Generator - 1
Right Flight Control DC - 2
Left Flight Control DC - 2
Right Main Engine FADEC; Channels A & B - 2
Left Main Engine FADEC; Channels A & B - 2
Total PMGs used on B777: 13
1 G en
1 G en
N B1u osbar
Non-Essential Consumers
N B2u osbar
Inv 2
Inv 3
Non-Essential Consumers
Non-Essential AC
Battery Busbar
Ground Power
Inv 1
Centre Busbar
Essential Consumers
Essential AC Consumers
Gen 1
APU Gen Ground Power
Gen 2
RAT Gen
L eM f t aiA nB Cu s
Aircraft AC Power: 115 Vac 3-Phase 400Hz Typically ~ 90Kva
Ri g hMt aiA nB Cu s
Lo aAdC s
Emer AC Bus
1 T RU
Lo aAdC s
2 T RU Batt Charger
Emer TRU
L efM t ain DC Bu s
Ri g hM t ain DC Bu s
LD oC ad s
Battery
Aircraft DC Power: 28 Vdc
LD oC ad s Emer DC Bus
Notes: Most High power loads are 115 Vac Most Electronic/Avionic Loads are 28 Vdc
APU Gen/ AGCU 1 APB 1
APU Gen/ AGCU 2
BCU 1
BCU 2
APB 2
XPC 2
XPC 1
IDG 1/ GCU 1
IDG 2/ GCU 2
GCB 1
IDG 3/ GCU 3
IDG 4/ GCU 4
GCB GCB 2 3 AC B u1s
BTB 1
AB Cu2s
E L C Us
GCB 4 AC B u3s
E L CU s
BTB 3
BTB 2
AC B u4s
E L C Us
E L C Us
BTB 4
SSB T 1RU
DBCu1s
T 2 RU
DBCu2s
TRU 3
DC Bus 3
T 4 RU
DBCu4s
APU Gen/ AGCU 1
APB GLC
IDG 2/ GCU 2
IDG 1/ GCU 1 GLC 1 ACBu s1
BTC 1
GLC 3 AC Bus 3
GLC 2 ACB us2
BTC 2
IDG 4/ GCU 4
IDG 3/ GCU 3
SIB
EPC 2
BTC 3
GLC 4 AC Bus 4
BTC 4
EPC 2
GPCU EXTERNAL POWER A
EXTERNAL POWER B
IL DeGf t
LEFT GCU
AP U G e n e r a t o r
BACKUP CONVERTER
APU GCU
Left Primary Panel
LEFT TRU
2 # ly b m e s s A r e lit F
3 # y l b m e s s A r te il F
4 # y l b m e s s A r te il F
P S U #2 CP U #1 D u a l ARI N C 629 I /O #1
Standby Secondary Panel 1 # y l b m e s s A r e lti F
2 # y l b m e s s A r e lti F
3 # y l b m e s s A r e ilt
4 # y l b m e s s A r e itl
I /O #3 I /O #4
I /O #6 I /O #7 I /O #8 I /O #9 D u a l ARI N C 629 CP U #1 P S U #1
EU (P110)
BATTERY CHARGER
CENTRE 1 TRU
I /O #2
I /O #5
RAT GCU
Centre Primary Panel
Left Secondary Panel
1 # ly b m e s s A r e lit F
R a m Ai r T u r b i n e
F
F
PS U # 2 CPU # 1 DualARINC 629 I/O# 1 I/O# 2 I/O# 3 I/O# 4 I/O# 5 I/O# 6 I/O# 7 I/O# 8 I/O# 9 DualARINC 629 CPU # 1 PS U # 1
EU (P310)
RIiD gG ht
RIGHT GCU
BPCU Right Primary Panel
CENTRE 2 TRU Ground Servicing Panel
RIGHT TRU Right Secondary Panel 1 # ly b m e s s A r te il F
2 # ly b m e s s A r te il F
3 # ly b m e s s A r tle i F
4 # ly b m e s s A r tle i F
PS U # 2 CPU # 1 DualARINC 629 I/O# 1 I/O# 2 I/O# 3 I/O# 4 I/O# 5 I/O# 6 I/O# 7 I/O# 8 I/O# 9 DualARINC 629 CPU # 1 PS U # 1
EU (P210)
Pitot Static Probe Pitot Tube
Static Port
Static Vent
Airflow
Airflow Static Port
Aircraft Skin Aircraft Skin
Heater Pitot Pressure
Static Pressure Static Pressure
Total Temperature Probe Sensor Element Airflow
Aircraft Skin
[resistance proportional to temperature]
Heater
Total Temperature
Flight Levels SAS
Transition Altitude
Height QFE Altitude QNH Airfield Elevation Sea Level
Pitot Pressure
Total Temperature
Static Pressure
Air Data Computer (ADC) Air Data Compututations & Corrections
Altitude Airspeed (IAS) Aircraft Power Supply
Mach Vertical Speed Other Parameters
Pitot Pressure (Pt)
Mechanical Airspeed Indicator
Static Pressure (Ps)
Indicated Airspeed (IAS)
Pressure Error Correction
Airspeed Sensing Module
Computed Airspeed
Square Law
Square Law Compensation
Calibrated Airspeed (CAS)
Compressibility Compensation
Equivalent Airspeed (EAS)
Air Density Compensation
True Airspeed (TAS)
Mach Altitude
Total Air Temperature Static Pressure (Ps)
Airflow
Airsteam Direction Detector (ADD)
Aircraft Skin Heater Angle of Attack (AoA)
Pitot Line Standby ASI
Standby Altimeter
Static Line
Forward
Pitot 3
ADM
1Pitot
2Pitot ADM
S ta 1tic
ADM
Static 2
ADM
Static 3
Display & Navigation Systems
ADM
ADM
ADM
ADM
Sta 1tic Static 2 Static 3
Z
Hz
H
Magnetic angle of Inclination (Magnetic Dip)
Hy
Y
Hx
X
Magnetic angle of Declination (Magnetic Variation)
Radio Navaids
Magnetic Detector (Flux Valve)
Magnetic Heading
Aircraft Heading
Magnetic Heading & Reference System Inertial Heading
Directional Gyro (DG)
Aircraft Flight Director System Aircraft Heading
Heading Selector Panel
Radio Magnetic Indicator (RMI)
Horizontal Situation Indicator (HSI)
Z Y Direction of Spin
X
X Arrow A
Arrow B
Y Z
A
Inner Gimbal
B
Outer Gimbal
Centre Gimbal
Photodiode Detectors Prism
Mirror
Clockwise & Input Rate
Mirror
Counter Laser Clockwise Beams
Mirror Gas Discharge
Torque Motor
Permanent Magnet
Restoring Coil
Case
Excitation Coil
Input Axis
e r u t c ru t S tf ra c ri A
Pick-Off
Excitation Coil
Permanent Magnet
Pendulous Arm
Hinge
Three Rate Gyros & Accelerometers
Y Acceleration Y
Z Acceleration Z Orthogonal Axis Set stabilised in Space
X
O
X Acceleration
Features of an Inertial Platform: Platform is Gyro Stabilised in Space Sensitive Accelerometers detect acceleration i n the direction of the orthogonal axes: Ox, Oy, Oz Accelerations are integrated to give first velocity and then position in the Ox, Oy, Oz axes Platform readings can be transformed to relate to earth rather than spatial axes and coordinates
Resolver Torque Motor
Y X, Y , Z Accelerometers
Z
X
Torque Motor
Resolver
Inner Gimbal Outer Gimbal X, Y , Z Gyros
Resolver
Torque Motor
Stable Platform
North
9O North
Aligned IN platform is referenced to earth co-ordinates
Line of Latitude
Vertical East Alignment Position:
O Equator
Latitude: 30 degrees North Longitude: 45 degrees West (approx)
Line of Longitude
9O South
180 Inertial Sensors are referenced in Space
90E
90W 0
Radar Altitude Barometric Altitude
Terrain
Sea Level
Oscillator & Modulator
Frequency Counter
Indicator
Transmitter
Transmit Antenna
Receiver
Receive Antenna
Transmit Signal Frequency Mhz
Receive Signal
4350 F1 F2
4250
O
T2
T1 T
O.01
Time (sec)
Vtotal Vy Vz Vx
Beam 3 Beam 1
Beam 2
Antenna Tilt
Storm Cloud
Terrain Weather Radar Display
Transmit
Transmitter/ Receiver Receive
Video
Antenna Assembly
Control Panel Display
HF - VHF Spectrum
Key: Communications
Aircraft & wiring resonant frequencies Navigation Aid TACAN ILS Glideslope
VHF Comms
DME
Radar Altimeter Weather Radar
Marker Beacon HF Communications
LORAN-C
ILS Localiser HF Communications
1
10kHz
2
3
4
5
6 7 89 1
100kHz
2
3
4
5
6
7891
1M Hz
2
3
4
5
6 7 89 1
10M Hz
2
UHF TV
VHF TV
3
4
5
6 7891
100 M Hz
2
3
4
5
Ground Based Radars
6 7891
1 GH z
2
3
4
5
6 789
1 0 GH z
TCAS
ATC GPS
SATCOM (Top Mounted)
VOR
HF ADF
VHF L
Weather Radar
SATCOM (Side Mounted)
DME R Marker Beacon DME L Rad Altimeter
ILS Glideslope Capture & Localiser
VHF C
TCAS ATC ILS VHF R Glideslope Track
Voice Signal
Time
Modulation RF Carrier
AM Signal
Time
Transmitted Power Amplitude Modulation (AM)
Single Sideband (Lower SB)
Single Sideband (Upper SB)
Suppressed Power B S r e w o L
R E I R R A C
2099
B S r e p p U
B S r e w o L
21 01
2099
2100 F R E Q U E N C YK H Z
R E I R R A C
B S r e p p U
2101 2100
FREQUENCY KHZ
Suppressed Power B S r e w o L
R E I R R A C
209 9
B S r e p p U
21 01 2100
FR E Q U E N C YK H Z
Ionosphere
Aircraft or Ship
Ground Station Key: Sky Wave Ground Wave
8
2
5 3
10 11
13
12
9
7
1
6 4
Ground Transmitter/ Receiver
Aircraft Transmitter/ Receiver
R = Maximum Range
VHF Controller
VHF Antenna
128.15
VHF Transceiver
Digital Tuning Transmitter Keying Audio
ACARS Control Unit Data
Flight Management Computer
ACARS Management Unit
Printer
Inmarsat Satellite
Uplink L-Band Downlink L-Band
Downlink C-Band Uplink C-Band
Ground Earth Station
Aircraft
C-Band:
4 - 6 MHz
L-Band:
1530 - 1660 MHz
~ 85North Degrees
~ 85 Degrees South
54 W 15.5W AOR-W AOR-E
64E IOR
178E POR
A429 (4)
A429 (4)
Beam Steering Unit Port
Radio Frequency Unit A429 (2)
Satellite Data Unit
High Gain Antenna Starboard A429 (2)
Beam Steering Unit Starboard
High Power Amp High Gain Antenna RF Splitter
High Gain Antenna Port
High Power Relay
A429 (2)
< < < <
High Power Amp - Low Gain Antenna
< < < < < Low Gain Antenna
Airborne Transponder Radar Energy
Reply 1090 MHz Aircraft Return
Interrogator 1030 MHz
Secondary Surveillance Radar (SSR)
BeaconV ideo
Synchronisation
ATC Radar Scope
Primary Surveillance Radar (PSR)
R adarV ideo
0297
Controller Altimeter
Transponder
Interrogator 1030 MHz
Antenna
SSR Optional Second Antenna
Transponder 1090 MHz
Top Antennae
ATC Mode S ransponder 1
Audio System
ATC Mode S Transponder 2 TCAS Transmitter /Receiver 9986
TCAS/ Transponder Control
Top Directional Antennae
Annunciators
VSI/RA/TA Indicator
Optional TA Indicator
Bottom Antennae Bottom Antenna
Optional Bottom Directional Antenna
Lubber Line
Bearing Pointer
Compass Card
Heading Knob
Airborne DME Equipment Transmitter 125.5
Receiver Reply Pulses
Interrogation Pulses
Ground DME Station
Receiver
Transmitter
Space Segment L1 [1575.42MHz] & L2 [1227.6MHz] Navigation Signals L1 [1575.42MHz] & L2 [1227.6MHz] Navigation Signals
S Band Uplink & Telemetry Downlink
User Segment Control Segment
Monitor Stations Ground Antennae (Dishes)
Left Beam
Localiser
[90 Hz]
Glideslope ~ 3.3 Degrees
Right Beam
Runway
[150 Hz]
Upper Beam [90 Hz]
Right Beam ILS Characteristics: Localiser transmitting between 108112MHz
Glideslope Extended Runway Centre-Line
Glideslope transmitting between 329335MHz Audible Morse code tone for identification
Lower Beam
'Hard' Pairing of ILS Localiser, Glideslope and associated DME to ease flight crew workload
[150 Hz]
Left of Centreline
Above Glideslope
Below Glideslope
Right of Centreline
FLY DOWN
FLY RIGHT
ON CENTRELINE ON GLIDESLOPE
FLY UP
FLY LEFT
ILS Markers: All markers transmit on 75MHz
+/- 85 Degrees
Runway
Outer Marker
Outer marker:
400Hz - 2 tones/sec
Middle marker:
1300Hz - dash-dot /sec
Inner marker: +/- 40 Degrees
3000Hz - six dots/sec
Middle Marker Inner Marker
Runway ~1000 feet ~3000 feet ~ 4 to 7 nautical miles
20 degrees
20,000 Feet
15 degrees
20 nm 3 degrees
AZIMUTH - 40 degrees
ELEVATION
+ 40 degrees
7 nm
Back Azimuth
Approach Azimuth
20 nm
C
X
A
X
Blue Master
Blue Slave
X
B
LEGEND: Transmitting Control Monitor
LOCATIONS: M - Seneca W - Caribou X - Nantucket Y - Carolina Beach Z - Dana
I.L.S.
Automatic pilot cut-out switch
P. 12 compass
Air speed
I.L.S. Radio
Height
Altimeter
Artificial horizon
D.M.E.
Rate of climb Turn and bank
Elevator and aileron control
A.D.F. repeater
O.R.B. CL2 compass CL2 compass Control
Rudder trim control
Rudder control Pedal adjuster
Flap
Airspeed Indicator
Gyro Horizon
Climb / Dive Indicator
Airspeed Indicator
Altimeter
Direction Indicator
Attitude Director Indicator
Altimeter
Turn & Bank Indicator
“Basic 6” Configuration RadioMagnetic Indicator
Horizontal Situation Indicator
Vertical Speed Indicator
“Basic T” Configuration
Autopilot Annunc iators
Selected Speed
Selected Height
Airspeed Counter/Pointer Scale
Flight Director
Vertical Speed
Attit ude Ball
Baro Height Vertical Tape Scale
Heading Scale
Mach No
Baro Set
2
2
2
2
2
2
R
G
G
B
G
R
B
R
G
B
W
R
Quad double green
B
R
Triad
G
Quad double white
G
B
Stripe
IAS or Mach
Vy
Vx
Windspeed Vector (Windspeed & Direction)
Waypoint
Vz
Magnetic True Radar North North Baro Altitude Altitude
True North
Heading
Bearing (Magnetic)
Magnetic North
Bearing (Magnetic)
Heading
Bearing (True)
Waypoint Position: Latitude Longitude
Drift Angle
Aircraft Present Position: Latitude Longitude Heading/TAS Windspeed & Direction Drift Angle
Track
Groundspeed /Track
Magnetic Declination (or Variation) (West)
Bearing (True)
N Ex
Ey Ay Ez Ax
Az
Earth Datum Axis Set: Ex, Ey, Ez Aircraft Axis Set: Ax,Ay,Az
S
W a yp o i n1t
Waypoint 2
W a yp o i n3t
NDB 3 NDB 1
DME 4 VOR 3 /DME 3 VOR 1 /DME 1
VOR 2 /DME 2 DME 5
NDB 2
W a yp o i n1t
Waypoint 2
Latitude 1 Longitude 1
W a yp o i n3t
Latitude 2 Longitude 2
Latitude 3 Longitude 3
Weather Radar
E FI S/ FD
FMS
Autopilot
EF I S / F D
DISPLAYS
DISPLAYS
CDU
CDU
INS #1
Mode Selector
INS #2
Mode Selector
VOR 1
VOR 2
INS #3 DME 1
1
DME 2
ADC
GPS
SENSORS
GP 2S
AD C
SENSORS
Rate Gyro Package (6)
ARINC 629 Interface
Sensor Processing
1 2 3 4
Accelerometer Package (6)
L
C
R
A629 Data Buses
Skewed Sensor Set
Rate Gyro Package (4)
ARINC 629 Interface
Sensor Processing
1 2 Accelerometer Package (4)
L
C
R
A629 Data Buses
Flight Control A629 Data Buses L C R
Flush Static Ports
ADM - Left Static
ADM - Right Static
Secondary Attitude Air Data Reference Unit (SAARU)
Standby Attitude Display
ADM - Center Static AoA Right
AIMS Right
TAT
AoA Left
AIMS Left
Left Pitot Probe
ADM - Left Pitot
Right Pitot Probe
ADM - Right Pitot
Center Pitot Probe
ADM - Center Pitot
Air Data Inertial Reference Unit (ADIRU)
Flush Static Ports
GEO
GEO
GPS GPS GPS
Wide-area Reference Station (WRS) Wide-area Master Station (WMS)
GPS
GPS
GPS
LAAS Reference:
VHF
GPS Receiver
Processor
VHF Transmitter
Monitor Service
Inertial Reference System
M C D U1
M C D U2
EFIS Navigation Aids
Comms Management Unit
GNSS Sensors
Air Data System
FMS 1
FMS 2
Autopilot & Autothrottle
Clock & Fuel Sensors
Compass Rose Heading Lubber
GRH 0535.4Z 32.5 NM
GS 300
T RK
340 M AG
SEA CRS0 5 5 DM E 1 3 .5
G S2 5 0
090
HDG
M AG
33 0
DME Distance
12
6 0
1 5 0
6
3
FRED 40
1 8
0 0
VOR bearing
GRH 3 3
12
YKM 42
03
ELN
72
ADF Bearing
VO RL Y KM DM E 3 5 .0
Intended Flight Path
NAV Mode
C LB
CRZ
DES
VO R R EL N DM E 2 8 .5
FIRST OFFICER'S NAVIGATION DISPLAY
CAPTAIN'S NAVIGATION DISPLAY
ILS LOC
TO
A P PR
C LB
CRZ
DES
AP P R
ILS Frequency F AIL
VHF Frequency
O FS T
PER F
M SG
F AI L
1
2
3
4
5
6
8
9
M SG
0
-
CLEAR
DI S P
N EXT PH AS
PPO S
O FS T
PER F
M SG
1
2
3
4
5
6
8
9
M SG
0
-
CLEAR
EXEC AI RP O RT
FU EL
EXEC D IR HDG SEL
AI R P O RT
FU EL
7
7
+
+
EN G OU T
A
B
C
D
E
F
G
EN G OU T
A
B
C
D
E
F
G
SEC FPLN
H
I
J
K
L
M
N
SEC FPLN
H
I
J
K
L
M
N
O
P
Q
R
S
T
U
O
P
Q
R
S
T
U
V
W
X
Y
Z
/
V
W
X
Y
Z
/
D AT A
FI X
S TART
Time to Waypoint ANP/RNP
DI S P
N EXT PH AS
PPO S
D IR HDG SEL
ILS Frequency
1
D AT A
FI X
S TART
CDU
2
FMS COMPUTER 1
CD U
FMS COMPUTER 2
DSB 0735.4 Z 20.5 NM
GS 300
TRK
140
MAG
15
12 SAU
BERKS
18
OSTOR
MADLY
BRLU
TAILS
C LB
CRZ
DES
AP P R
Flight Phase Annunciators
Light Sensors
Line Keys F AI L
DISP
NEXT PHAS
PPOS
OFST
PERF
M SG
1
2
3
4
5
6
EXEC DIR
Annunciators
AIR -
FUEL
PORT
HDG SEL
DAT A
FI X
START
Function Keys
ENG OUT SEC FPLN
A
B
C
D
7
8
9
MSG
+
0
-
CLEAR
E
F
G
H
I
J
K
L
M
N
O
P
Q
R
S
T
U
V
W
X
Y
Z
/
Alpha Keys
Brightness Control
ETA Window Waypoint 15
ILS Approach Runway 27
Wind 290 6 Knots
ETA WAY 15
1530:30
EARLY 1529:45 LATE 1540:10 ILS RWY 27
ANP/ RNP Data
WIND 290/6
DME 45 VOR 117.5 ILS 127.5
ANP/RNP 0.15/0.30
Numeric Keys
ETA Window: Early/ Late
Nav Aid Data: VOR/DME & ILS LOC
FMS COMPUTER Nav Data Base: Sensor Fusion -
Nav Sensors:
Airways Airports
Kalman Filter
-
INS
-
GPS
-
VOR/DME
-
ILS
-
ADF
Runways Routes, SIDS, STARS etc
-
Procedures
Navigation Computations
-
Flight Plans
Display Data
-
Winds
Fuel State
Aircraft Performance Model
Communications Management
Air Data
POL 112.1 Ch 58 N 53 44 63 W 002 06 20
XUMAT WAL 21.3d N 53 27 95 W 002 28 38
P
OL
04
1
POLE HILL
0 0 4
1R 22
T0 MC
P
O
L
1Z S, L4 PO
056
3 4
5 R 1, Y
P O L 1 8 4 R
5 Manchester MCT 113.55 Ch 82Y
R 56
Course
Ra d Course
ia l
-1
35
COURSE TO RADIAL
PROCEDURE TURN VOR/DME Beacon Non-Directional Beacon (NDB)
Course
Ra di al -
070
15 0
DME ARC TURN
Course
HOLDING PATTERN
D
LAKEY TNT 85d DCS 32d N54 14 33 W002 58 87
A LE Y
D A LE Y
14 9
1A
SETEL DCS 53d NEW 67d N54 00 75 W002 26 15
30
1B
15 2
20 D A L
6
Warton
E
ARTHAR POL 7d N53 46 98 W002 17 12
Y 1 B ,
1 7
1 C
295
DALEY TNT 44d N53 40 13 W002 20 95
TN T
POLE HILL POL 112.1 Ch 58 N53 44 63 W002 06 20
GOLES OTR 35d N53 36 48 W001 05 00
DAL EY 1 D
DA 32 LE 6 Y 1E 15 2R
293
265 265 DALE Y 1E
STOCK WAL 48d OTR 62d POL 16d N53 32 06 W001 49 27
Manchester
UPTON POL 30d OTR 43d N53 35 22 W001 18 05
Woodford
ILS/DME Approach 06L
MCH/MCT
236
056 3 De
10
8.6
g
4
1 MCH 428 N53 21 20 W002 16 38
P O
L
1
1
2
.1 1
6 05
6
6
R
Woodford
ILS/DME I-MM 109.5 Ch 32
236
MCT 113.55 Ch 82Y N53 21 42 W002 15 73
M MCT CT 11 4R 13 5R
056 10nm
13 5
AMLET MCT 16d TNT 14d N53 16 12 W001 50 30
31 5 AMDAYNE TNT 17d MCT 11d N53 14 32 W002 01 75
Manoeuvre Envelope
High Red
+ 2000 Feet
High Yellow + 1000 Feet
Medium Yellow - 500 Feet
Medium Green
- 1000 Feet
Terrain
Light Green
- 2000 Feet
Clear Screen
MCDU
Pilot Controls
FCU
Displays Primary Flight Display
Nav Display
Actuators
FMS
AFDS
FBW
ATA 34
ATA 22
ATA 27
Sensors
Attitude Trajectory Flight Mission
X Axial Force
Y Z
Axial Velocity Axial Acceleration Roll Rate
Lateral Force Lateral Velocity Lateral Acceleration Pitch Rate
Normal Force Normal Velocity Normal Acceleration Yaw Rate
Autopilot
Flight Control Computers 1
PITCH ROLL YAW
PITCH ROLL YAW
Mechanical Backup
Pilots Controls
Pitc h
R ol l / Y a w
2 3
GROUND SPOILERS SPEED BRAKES RO LL
R O LL
Ai lLe r o n s
A iR ler o n s
Rudder Sections
THS Actuators Normal & Standby
L Elevators
R Elevators
PITCH
YAW
Hydraulic Power
Cable & Pulley
Channel A
Solenoid Valve SV
Mechanical Signalling
Hydraulic Actuator
Control Rods
Feedback
Hydraulic Power
Cable & Pulley
Solenoid Valve
Solenoid Valve SV
Mechanical Signalling
Control Rods
SV
Hydraulic Screwjack
Position
Electric Power
Cable & Pulley
Actuator Package
Mechanical Signalling
Hydraulic Actuator
Feedback
Control Rods
Channel B
Hydraulic Power
Channel A
FBW Command Solenoid Valve
Solenoid Valve SV
Electrical Signalling
Direct Electrical Link
SV
Hydraulic Actuator
Feedback
Electric Power
FBW Command EHA Package
Electrical Signalling
Direct Electrical Link
Hydraulic Actuator
Feedback
Electric Power
FBW Command EMA Package
Electrical Signalling
Direct Electrical Link
Electric Screwjack
Feedback
◆
◆ ◆
◆
◆
◆
◆ ◆
◆
◆
B o e in g 777
PFC L
Airbus A330/340
ACE L1 Spoilers ACE L2
Flaperons
3 x FLIGHT CONTROL PRIMARY COMPUTERS COMMAND
MONITOR
Ailerons ACE
PFC C
Elevator
Spoilers Ailerons Elevator Rudder Stabilizer
C Rudder ACE R
COMMAND
MONITOR
Spoilers Ailerons (standby) Elevator (standby) Rudder (trim/travel limit)
2 x FLIGHT CONTROL SECONDARY COMPUTERS
PFC R 3 x FLIGHT CONTROL COMPUTERS
Spoiler Elevator Computer (SEC) 1
Elevator Aileron Computer (ELAC) 1
2
Flight Augmentation Computer (FAC) 1
2
G N D- SP L L AF
G ND- SP L
S P D - BR K
S P D- BR K
L AF
ROLL
G
ROLL
Y
B
Y
G
G
Y
B
Y
A il e r o Ln B
ELAC SEC SEC
1
2
3
G Ai l e r o Rn
G
2 2
1
1
2
3 2
Normal Normal Standby
3 2
3
1
1
G
B
1
2
2
THS Actuator
E l eLv B
ELAC SEC
1 1
G
Y
G
Y
E le Rv G
2 2
Y
2
1 1
2
FAC 1
G
FAC 2
Y
B
2 2
1 1
M
ELAC ELAC SEC
Yaw M Damper Actuator
B
Trim
Mechanical Trim
Y
G
FMGEC FMCEG
Autopilot Pitch Commands
Electrical Motors
Hydraulic Motors
M
FCPC FCPC FCPC
Autotrim
Y
Elevators
M
B
M
THS Actuator
G Sidestick Commands
B
Normal
FCSC FCSC Sidestick Controller
Alternate
FMGEC FMGEC
Travel Limitation Unit
Autopilot Yaw Commands
Centred Spring
B
M Mech Stop
G
Yaw Damper Actuators
FCSC FCSC
Y
G Y
FCPC FCPC FCPC
Rudder M Rudder Trim Actuator
Artificial Feel
Rudder Trim
Rudder Pedal Command
FCDC
FCPC
1
1
FCSC
FCSC
1
2
2
1 2
2
3
GN D- S P L
GN D- S P L
S P D- B R K
S P D- B R K
R O LL
Y
G
A i l er onL Y
G
Y
B
B
B
G
G
Y
G
G
F CPC/ F C SC G
R OL L
Slats PCU
B
B
Y
G
F CPC/F CSC
Y A i l eronR
B
G
B
Y
G
Flaps PCU
FCPC/FCSC
FCPC/FCSC
Horizontal Stabilator
B
Key: Y
FCPS - Flight Control Primary Computer FCSC - Flight Control Secondary Computer FCDC - Flight Control Data Concentrator SFCC - Slat/Flap Control Computers
B
L Elevator B
G
R Elevator
G
Y
FCPC
G
FCSC
Y
B
FCPC/FCSC
FCPC/FCSC
Yaw M Damper Actuator
FCPC
M a330fc.vsd
19/10/97
Y
Actuator Control Electronics (4)
Typical Actuator Control Surface
An a l o g u e
An al o gu e
Position Transducers
Control Yoke & Rudder Pedals
Mechanical
Primary Flight Computer (3)
Backdrive Actuators
Flight Control ARINC 629 Buses (3)
AFD C(3 ) Analogue
A IM S
A D IR U
S A AR U
Flight Control A629 Data Buses L
C
Hydraulic System (Left)
R
Actuator Control Electronics (ACE)
28 VDC Power
Solenoid Valve Actuator Demand Actuator Feedback
Actuator Loop Control
Position Sensors
Digital 'World'
SV
SV
Left Inboard PCU
28VDC Power (2)
Example shown is for the Left Inboard Power Control Unit (PCU) and is part of the L1 ACE
Analogue 'World' acepcu.vsd
12/10/97
Flap/Slat Control Units
Autopilot Flight Director Computers
Pilots Controls Flight Control A629 Data Buses (3)
Speed Brake Lever
Auto Speed Brake Actuator
Position Transducers: Control Columns
6 6 4 4
Rudder Pedals
-
Pitch Roll Yaw Speed Brake
Actuator Control Electronics (ACE)
Autopilot Back -Drive Actuators: 2 - Pitch 4 - Speed Brake
Wheel Trim Commands
Stabilizer & Rudder Trim Commands
Trim Actuators:
Feel Units:
1 - Roll 1 - Yaw
2 - Pitch Variable 1 - Roll Fixed 1 - Yaw Fixed
2 - Yaw
Column Feel Actuators
Power Control Unit (PCU) (31)
PCU (2) Right Elevator
Elevator Feel Actuators (2)
PCU (2) Left Elevator
Mechanical Elevator Feel Units (2) Control Yoke & Rudder Pedals
Force Transducers (2)
ACE (4)
Position Transducers (6) Flight Control ARINC 629 Buses (3)
Backdrive Actuators 2) A F D C( 3 )
AIM S
AD I R U PFC(3)
Stabiliser Position Modules Alternate Pitch Trim Levers
Stabiliser Ballscrew Actuator
ACE (4) M/B Stabiliser Trim Control Modules (2)
Control Yoke Pitch Trim Switches (4)
M/B Stabiliser Cutout Switches Flight Control ARINC 629 Buses (3)
AIMS PFC(3) Pitch Trim Indicator (2)
PCU(2) (2) PCU PCU PCU(2) (2) Right Flaperon Right Flaperon
Spoilers 44 & & 11 Spoilers 11 Mechanical Mechanical
Aileron Trim Trim Aileron Actuator Actuator
PCU PCU(2) (2)
Feel & Centring Feel & Centring Mechanism Mechanism
Control Control Yoke & Yoke & Rudder Rudder Pedals Pedals
Position Position Transducers (6) Transducers (6) Force Force Transducers (2) Transducers (2)
PCU (2) PCU (2)
ACE (4) ACE (4)
PCU (2) PCU (2)
Flight Control Flight Control ARINC 629 ARINC Buses629 (3) Buses (3) AFDC (3) AFDC (3)
Right Aileron Right Aileron
Left Aileron Left Aileron
PCU (12) PCU (12)
Speed Brake Speed Brake Lever Lever Transducers (4) Transducers (4)
Backdrive Backdrive Actuators 2) Actuators 2)
Left LeftFlaperon Flaperon
All Spoilers All Spoilers except 4 & 11 except 4 & 11
PFC(3) PFC(3)
Rudder Trim Selector
Rudder Trim Actuator Feel & Centring Mechanism Rudder Pedals
PCU (3)
Rudder
ACE (4)
Pedal Position Transducers (4)
Mechanical
Flight Control ARINC 629 Buses (3)
Backdrive Actuators 2) AFDC (3)
AIMS
PFC(3)
Rudder Trim Indicator
PCU
Spoiler 11 Control Yoke & Rudder Pedals
Mechanical Cables
PCU
Spoiler 4
Horizontal Stabiliser Alternate Pitch Control Levers Mechanical Cables
Left Hydraulic System Right STCM M/B M/B Left STCM Centre Hydraulic System
Ballscrew Actuator
L C R
PFC - L
PFC - C
ACE - L1
ACE - L2
ACE - C
ROB Aileron LOB Flaperon
A629 Flight Control Data Buses
CDU - L
PFC - R
LOB Elevator
LOB Aileron RIB Flaperon
PCUs
Spoiler 2
Spoiler Spoiler Spoiler Spoiler
Spoiler 13
ADM Pitot L
ADM Static L
ADM Pitot C
ADM Static C
LOB Elevator L Elev Feel Act
CDU - R
ACE - R
LIB Aileron ROB Flaperon
RIB Aileron LIB Flaperon
Upper Rudder PCUs
CDU - C
P C Us
5 4 11 10
ROB Elevator R Elev Feel Act Spoiler Spoiler Spoiler Spoiler
Lower Rudder P C Us
1 7 8 14
RIB Elevator
Spoiler Spoiler Spoiler Spoiler
3 6 9 12
ADM Pitot R
ADM Static R
L ef tA I M S
R i gh tA IM S
A D IR S
SA A RU
AFDC - L
AFDC - C
AFDC - R
Left PFC Commands Shown on Left Bus
Center & Right PFCs similarly operate on Center & Right Buses respectively
L C R A629 Flight Control Data Buses
A629 Terminal Interface
Command Lane
A629 Terminal Interface
Standby Lane
Lane 1 Lane 2 Lane 3
A629 Terminal Interface
Flight Control DC Power System (Left PSA)
Monitor Lane
Primary Flight Computer (Left Shown)
Acceleration
Aerodynamics
Rate Position
Actuator Inner Loop Feedback
Processing Autopilot Inputs
Servomotors /Actuators
Control Surfaces
Manual Operation
Capt MCDU CADC 1
A429 Buses
Air Data 1
Vertical Gyro 1 &2
P, R & Y Demand
Digital Flight Guidance Computer 1 P, R & Y Feedback
Directional Gyro 1 & 2
VOR/ILS 1&2
Flight Guidance Control Panel
A+B A+B
Roll Aileron Control Run Right Elevator A+B Dual Servo A+B Motor Pitch Up x
P, R & Y Demand
Digital Flight Guidance Computer 2
Rad Alt 1&2 CADC 2
Air Data 2
F/O MCDU
Roll Left
X
Dual 3-Axis Accel Dual Lat Accel
Aileron Dual Servo Motor
P, R & Y Feedback
A+B A+B
Elevator Pitch Control Run Down Aileron Dual Servo Motor Yaw Left X
Yaw Rudder Control Run Right
A429 Buses
Digital FlightGuidance Computer 2
Dual Servo Drive
Digital Flight Guidance Computer 1
Synchro
Position A 28Vac Reference
Demand A
M
Rate A
G G
G T
G
G T
Rate B
G
Demand B
M
Position B 28Vac Reference Engage Logic Relays
T
T
Synchro
Clutch Engage
Engage Clutch Slip Clutch
Aircraft Control Run: Aileron, Rudder, Elevator
FMS
Black triangle denotes units associated with the Mach Trim function
A429 Bus Flight Guidance
Mach Trim Actuator Digital Flight Guidance Computer 1
Rad Alt 1 &2
Lane B
Radio Altitude
Lane A
CADC 1&2
A429 Bus Air Data
Demand A Pitch Control Laws
Left & Right Flap Postn VOR/ILS Receiver 1&2
Flap Position Left & Right
Feedback A
Demand B
Glideslope Deviation
Feedback B
Pitch Angle
X
Vertical Gyro 1 & 2 Dual 3Axis Accelerometer
Dual Elevator Servo Drive
Elevator Control Run
Normal & Longitudinal Accelerations A & B
Horizontal Stabilator Position Left Elevator Position Right Elevator position
Black triangle represents units associated with Yaw Damper function
Digital Flight Guidance Computer 1
Rad Alt 1 &2 Radio Altitude
Dual Lateral Accelerometer Rudder Position Sensor
Yaw Damper Actuator
Lane B Lane A
Lateral Acceleration A&B
Demand A Yaw Control Laws
Rudder Position
Feedback A
Demand B
Dual Rudder Servo Drive
Feedback B
VOR/ILS Receiver 1&2
VOR/Localiser Deviation Bank Angle X
Vertical Gyro 1 & 2 Dual 3Axis Accelerometer
Rudder Control Run
Lateral Acceleration A&B
Flap Handle Position Slat Position Horizontal Stab Position
Left & Right AoA Angle of Attack
Digital Flight Guidance Computer 1
Rad Alt 1 &2
Lane B Radio Altitude
CADC 1&2 L&R Flap Postn L&R EPR Tx
Lane A
A429 Bus Air Data
Flap Position Left & Right
Speed Control Laws
Autothrottle Actuator
Engine Pressure Ratio (Thrust)
Pitch Angle Bank Angle
Vertical Gyro 1 & 2 Dual 3Axis Accelerometer
Normal & Longitudinal Accelerations A & B
Elevator Position
L&R Elev Postn
Vertical Speed Window
Speed Window
Heading Window
FD
SPD SEL
OFF
MACH SEL
FMS EPR OVRD L IM
340 SPEED
NAV
MACH AUTO THROT
OFF
VOR/ LOC ILS
185 H
Altitude Window
V - 2000 INC
AUTO LAND
Mode Select Buttons
IAS MACH VNAV
DEC
15000
VERT ALT SPD HOLD
FD
OFF
AP 1
AP 2
T U RB
◆ ◆
◆◆
◆ ◆
◆◆
◆
◆
◆
◆
◆ ◆
◆ ◆ ◆ ◆ ◆
◆
◆◆ ◆
◆
◆ ◆◆
◆
◆ ◆ ◆
◆
◆
◆ ◆ ◆ ◆ ◆ ◆ ◆ ◆ ◆ ◆ ◆ ◆◆◆◆◆◆◆◆◆
◆ ◆
◆ ◆ ◆ ◆◆◆◆◆◆◆◆◆
◆ ◆
◆
◆
A629 Flight Control Data Buses
Mode Control Panel A4 2 9
ADIRS ADIRU
A4 2 9
SAARU
L, C, R Buses
AFDC - L
PFC - L PFC - C
AFDC - C
PFC - R
AFDC - R ACEs (4): L, C ,R Buses
EICAS Warnings, Cautions & Advisories
L2 R
AIMS - L AIMS - R
MFD Status Messages
L1 C
PCUs: FSEU
PFD Modes Selection, Target Values & Autoland Status
PSEU WOW Card File
A629 System Data Buses
Pitch - 4 Elevators Roll - 14 Spoilers; 4 Aileron; 4 Flaperon Yaw - 3 Rudder Total: 31
Category I
Decision Height (DH) Feet 200
Decision Height (DH) not < 200 Feet Visibility not < 2600 Feet
Category II Decision Height (DH) not < 100 Feet
or RVR not < 1800 Feet
RVR not < 1200 Feet
100 Category IIIA DH < 100 Feet RVR not < 700 Feet 'See to Land' 50 Category IIIB DH < 50 Feet RVR not < 150 Feet 'See to Taxi' Visibility/RVR Feet 26 00
180 0
1200
700
150
Inertial Reference System
M C D U1
M C D U2
EFIS Navigation Aids
Comms Management Unit
GNSS Sensors
Air Data System
Clock & Fuel Sensors
FMS 1
FMS 2
Autopilot & Autothrottle
H yd ra u l i cC h a n n e l1 R e s e rv o i rs
H yd r a u l i cC h an n e l2 Electrical Channel 1 2xV F Gs
1
EN G
Electrical Channel 2
ENG 2
4
Ex4DE P x1M : P
Hydraulic Actuators
Re se rvoirs
2xV F Gs
ENG E N G3
Ex4DE P x1M : P
EHAs + EBHAs
EHAs + EBHAs
Hydraulic Actuators
Key:
Left Engine
Hot Air Cool Air
FAN VALVE
Starter Air
LP FAN
Non-Return Valve Engine Start
STARTER STARTER VALVE
T
T
P
I/ PRESS H/ PRESS
LIV
CIV Right Engine
PRSOV HP SOV
Air Services
P
Air Services
APU SOV
Core Exhaust Ground Air Supply APU
X
Exhaust Air
Forward
Modulating Valve
Engine Bleed Air
P
Air Pack 2
Exhaust Air
Pressure Vessel
Aft
Outflow Valve
Outflow Valve
P
Air Pack 1 Engine Bleed Air
Key: Engine Bleed Air X
Modulating Valve
Conditioned Air
P
Pressure Sensor
SENSOR
TARGET
Proximity Switch Proximity Switch Electronics Unit 2 (PSEU 2) A629 Aircraft Data Buses
Proximity Switch Electronics Unit 1 (PSEU 1)
ATA Chapter 32 Landing Gear - Nose landing Gear - Right Main Landing Gear - Left Main Landing Gear
(10) (10) (10)
ATA Chapter 52 Doors: - Main Cabin Doors - Cargo Doors
(32) (18)
ATA Chapter 78 Thrust Reversers: - Left Engine - Right Engine
(7) (7)
PRIMARY FLIGHT DISPLAY
PRIMARY FLIGHT DISPLAY
D SB 0735.4 Z 20.5 N M
GS 300
T RK
140 MAG
T RK
340
MAG
33 3
SAU
0
0
GR H 0
20
B ER KS 18
2
3
7
ELM
YKM
0 6
4 2
O ST O R
0 9
12
M AD LY
GR H 0515.Z 32.5N M
GS350
15
12
B R LU
21
20 81
51
T AILS
MCDU
ATC Communication Functions
Navigation Functions
Index
10BaseT 343, 345 1553B 14, 17 25.1303 Flight and navigation instruments 183 25.1309 Equipment, systems, and installations 183 25.1323 Airspeed indicating systems 183 25.1333 Instrument systems 183 25.1334 Flight director systems 183 29.92 inHg/1013.2 mb 105 2ATI 171, 182 3ATI 165, 171, 182, 183 5ATI 165, 179, 203–205 8.33 kHz VHF voice 350, 352
Air conditioning packs 295, 297, 299 Air Cycle Machine (ACM) 295, 296 Air data 101 sensors 233 system 282 Air Data and Inertial Reference System (ADIRS) 27, 121, 223, 238, 280 Air Data and Inertial Reference Unit (ADIRU) 223–225, 265 Air Data Computers (ADC) 105–108, 168, 169, 222, 223, 238, 343 Air Data Modules (ADMs) 109, 110, 121, 223, 224 Air Traffic Control (ATC) 129, 141, 142, 143, 350, 356, 367 mode S 144–146, 343, 351, 366
multisensor 353 VOR/DME 353 APU 77, 80, 90, 92–95, 292, 295, 303, 304, 313, 319, 344 Controller 24 Area Navigation (RNAV) 232, 239, 240–241, 352, 358, 367, 373 ARINC 11, 135, 136, 378 11 26 404A 27 429 6, 11, 12, 94, 106, 109, 113, 140, 188, 192, 203, 225, 297, 318, 320, 321, 339, 341 568 203 600 27, 30, 31, 79 629 6, 12, 96, 193, 224, 297, 318,
A42927,12, 13,304, 14, 17, 21,335, 22, 25, 275, 305,19, 329, 336 A429 Bus 13 A629 11, 12, 17, 18, 19, 20, 21, 23, 24, 223, 259, 264–266, 271, 272, 279, 280, 305, 329, 336–338 AC 25.1309-1A 34 Accelerometers 115, 118 Active Matrix Liquid Crystal Display (AMLCD) 161, 164, 178, 179, 182, 183, 187, 188, 199–205, 207, 236, 339, 343, 344 Actual Navigation Performance (ANP) 237, 238, 352, 355–357 Actuator Control Electronics (ACE) 259, 265, 266, 267, 268–269 ADB-0100 76, 99 Airborne Communications, Addressing and Reporting System (ACARS) 136, 137, 269–270, 319, 325–326, 350 Advanced Civil Flight Deck (ACFD) 171, 172 Aeronautical Telecommunications Network (ATN) 370
Air Transport 62, 321 Association (ATA) 34, Air Transport Management (ATM) 349, 350 Airborne Early Warning (AEW) 376, 388 Aircraft: course 168 electrical power 43 electrical systems 43, 65 heading 168 Information Management System (AIMS) 193, 194, 224, 225, 265, 280, 297, 321, 322, 334, 336, 339–341, 344 systems 383 wiring 98 Air-Driven Pump (ADP) 313, 314 Air-to-air refuelling 376, 384 Altimeter 104, 163, 168 AMJ 25.1309 34, 183 APB 91, 93 Application Executive (APEX) 336, 345 Approach 232, 361
321,17 339, 341 Data Data Bus 32 bus structure 378 characteristics 629 32 specifications 429 32 Attitude 182, 252 Attitude Direction Indicator (ADI) 165, 166, 179, 203 Attitude Heading Reference System (AHRS) 113, 127, 223, 343 Automatic Dependent Surveillance (ADS) 367 address mode (ADS-A) 144, 366, 367 broadcast mode (ADS-B) 366, 367 Automatic Direction Finding (ADF) 129, 147, 163, 167, 218, 220, 238, 343 Autopilot 282 Flight Director Computer (AFDC) 267, 268, 279, 280 Flight Director Systems (AFDSs) 251, 252, 273, 279 modes 276, 279
392
Civil Avionics Systems
Autothrottle 276, 277, 282 Avionics: conditioning 298 Data Buses 32 Fast Switched Ethernet (AFDX) 336, 345, 346 Full Duplex Ethernet (AFDX) 12 Standard Communication Bus (ASCB) 12, 24, 335, 336, 343 ventilation computer 23
Circuit breakers 81, 98 Civil Aviation Authority (CAA) 39, 40 CNS 349, 367 CNS/ATM 350, 366 Command words 15, 16 Commercial Off-The-Shelf (COTS) 3, 10, 47, 205, 333, 334, 335, 343, 344, 345, 375 Ethernet 343 Common Cause Analysis (CCA) 37, 40
Distance Measuring Equipment (DME) 129, 131, 136, 147, 148, 149, 157, 164, 168, 218, 221, 222, 233, 237, 241, 343, 352, 354, 356, 367 scanning 149 DME (P-DME) 157 DME/ILS 246 Domestic en route 230, 353 Doppler 125–127, 215, 217, 220, 222 beams 125, 126 principle 125
Back-up converters 86, 87 101, 216 Barometric altitude (ALT) Basic Area Navigation (BRNAV) 356, 358 Basic navigation 215, 216 Basic six 162, 165 Basic T 165, 175, 185 BIT Equipment (BITE) 318, 340 Bleed air 294 control 23 Bottom-up approach 40, 41 Build phase 50, 54 Built-In-Test (BIT) 97, 191, 304, 317, 318 Bus Control Units (BCUs) 92–94 Bus Controller (BC) 15, 17, 19 Bus Power Control Unit (BPCU) 24, 77, 91, 92, 95 Bus Tie Breakers (BTBs) 91, 93 Bus Tie Contactor (BTC) 92, 94
Communication control system 350, 233 382 management unit 282 Navigation, Surveillance/Air Transport Management (CNS/ATM) 215 Concept phase 50, 51, 52 Control and Display Unit (CDU) 222, 233, 236, 252, 271, 282, 283, 318–320, 322, 355 Controlled Flight Into Terrain (CFIT) 161, 207, 247 Core Processing Modules (CPMs) 339, 340, 346, 347 CSD 63, 64, 73 Cursor Control Devices (CCDs) 343, 344
radar 122, 125, 148 126 VOR (DVOR) Dual Doppler 220, 221 Dual servomotor 274, 275 Dumb display architecture 187, 188 Dynamic pressure 102, 104
Cabin: domain 345 pressure control 23 pressurization 299 Temperature Control (CTC) 24, 297 Calibrated airspeed (CAS) 107, 170 Capability Maturity Model (CMM) 31 Card file 24, 297, 336, 341, 342 Cat I 228, 239, 281, 364 Cat II 229, 364 Cat II/III 239, 281 Cat III 229, 364 Catastrophic failure condition 38, 39, 58 Cathode Ray Tube (CRT) 161, 171, 172, 175, 176, 178, 187, 188,
Data: conversion gateway 339 links 384 words 15 DC: generator parallel operation 69 link 72, 74 motors 83 power generation 65 system generation control 68 Decision Altitude (DA) 105, 241 Decision Height (DH) 105, 281, 370, 372 Definition phase 50, 52, 53 Design phase 50, 53, 54 Differential current protection 71, 77 Differential GPS (DGPS) 152, 156, 227, 228, 352, 363, 364, 383 Direction 216
Earth: datum 217 magnetic field 110 EHSI 175, 179, 204 Electrical Back-up Hydraulic Actuators (EBHAs) 97, 283, 285 Electrical Load Management System (ELMS) 24, 87, 95, 96, 97, 297, 305, 306, 334, 336–339 Electrical Motor Pumps (EMPs) 285, 310, 311 Electrohydrostatic Actuators (EHAs) 97, 257, 258, 283, 285 Electromagnetic Actuator (EMA) 258, 259 Electromagnetic Interference (EMI) 25, 28, 29, 330, 332 Electronic ADI (EADI) 175, 176, 179, 204 Electronic Centralized Aircraft Monitor (ECAM) 97, 193, 290, 313, 318, 389 Electronic Countermeasures (ECM) 389 Electronic Engine Controllers (EECs) 23, 183, 189, 192, 193, 232, 233–234, 236–238, 282 Electronic Flight Instrument System/Flight Director (EFIS/FD) 189, 222
194–196, 198, 199, 202, 207, 210, 236 Central Air Data Computers (CADC) 273, 275 Central Maintenance Computing System (CMCS) 23, 318–320, 321 Centre of Gravity (CG) 302, 303, 307
Gyro (DG) 112 indicator 163 Dispatch 48 availability 47 Display Management Computer (DMC) 188, 192, 318 Display Unit (DU) 189, 190, 192, 193
Electronic Load Control Units (ELCUs) 77, 78, 81, 96 Electronic Support Measures (ESM) 386–389 Electronic Units (EUs) 96, 334 Electronics Warfare (EW) 130, 376, 389 En route procedures 243, 244
Index
393
Engine Indication and Crew Alerting System (EICAS) 93, 94, 97, 175, 280, 290, 297, 304, 313, 318, 344 Engine-Driven Pumps (EDPs) 285, 314, 310 Enhanced Ground Proximity Warning System (EGPWS) 122, 246–248, 381 Environmental Control System (ECS) 73, 76, 293, 295–298, 341 EPIC 24, 25, 30, 335, 336, 342–344
Fly-By-Wire (FBW) 76, 116, 251, 252, 255, 257, 258–261, 264, 283, 284 Flying classroom 376, 390 Forward Looking Infra-Red (FLIR) 212 Four-dimensional navigation 240, 242, 283 Free flight 367, 368 FTE 353, 360, 361 Fuel:
240, 241, 281, 282, 343, 350, 352, 358, 363–365, 367, 380, 381 GLONASS 150, 226, 364 Ground Proximity Warning Systems (GPWS) 211, 246–248, 381 Ground surveillance 376, 388 Groundspeed 216 Gyro artificial horizon 163
Estimated Time of Arrival (ETA) 221, 236, 242 Experimental Aircraft Programme (EAP) 21, 22 Extended Twin Operations (ETOPS) 59, 61, 86, 87, 292–293 External Power Contactor (EPC) 77, 85, 91, 94
control 23 Control Management Computers (FCMCs) 307 Data Concentrators (FDCs) 307 gauge 162 management 42, 43 Management and Quantity Gauging System (FMQGS) 303, 305 on-board 233 quantity function 43 Quantity Indication (FQI) 24, 307 quantity measurement 42 Quantity Processor Unit (FQPU) 305, 306 quantity system measurement 43 sensors 282 state 238 systems 300 Full Authority Digital Engine Control (FADEC) 7, 8, 23, 48, 88, 290, 292 Full performance based navigation 240, 242, 283 Functional Hazard Analysis (FHA) 36, 37, 38, 39, 40 Future Air Navigation Systems (FANs) 2, 132, 136, 139, 144, 148, 215, 229, 232, 240, 242, 246, 283, 349, 357, 360, 367–370 FANS 1 368, 369 FANS-A 369, 370
Heading 183,(HUDs) 216 Head-Up 168, Displays 2, 3, 209–212, 344 High Frequency (HF) 2, 129, 130, 131, 132, 134, 135, 325, 326, 351, 382–384 High-Frequency Data Link (HFDL) 134, 135, 325, 350, 367, 351 Horizontal Situation Indicator (HSI) 113, 165, 168, 173, 179, 203 Hydraulic control 23, 341
Failure Modes and Effects Analysis (FMEA) 36, 45, 46 Failures 38, 39, 40, 44, 45, 46, 48, 49, 50 FAR/JAR 25.1309 43 Fast Switched Ethernet (FDX) 12, 345 Fault Tree Analysis (FTA) 36, 39, 43, 44, 45 Federal Aviation Authority (FAA) 34, 59, 144, 150, 156, 165, 232, 247, 343, 367 AC 25-11 183, 185, 194, 213 Fibre Distributed Data Interface (FDDI) 26, 321 Flap Slats Electronics Unit (FSEU) 24, 280 Flight Control Data Concentrators (FCDCs) 23, 264 Flight Control Primary Computers (FCPC) 23, 260, 262 Flight Control Secondary Computers (FCSCs) 23, 260, 262, 264 Flight Management Guidance and Envelope Computer (FMGEC) 225, 262, 370 Flight Management System (FMS) 40, 122, 137, 156, 204, 222, 229, 232, 233, 236, 238–241, 242–244, 251, 252, 273, 275, 278, 282, 283, 318, 322, 355, 367–370, 373, 379 Control Display Unit 236, 238 MCDU 326 procedures 243 Flight Mode Selector Panel (FMSP) 252, 276, 278
Hazardous/Severe/Major failure condition 38, 39, 58
Galileo 153, 364 Generator Control Breaker (GCB) 71, 77, 93 Generator Control Unit (GCU) 23, 24, 44–46, 67, 77, 85, 91, 93–95
I/O modules (IOMs) 338, 339 Identification Friend or Foe (IFF) 383, 384, 388 Secondary Surveillance Radar (SSR) 129, 142 Inclination 110, 111 Indicated airspeed (IAS) 101, 106, 107, 216 and mach number 182 Inertial navigation 115, 118, 220 Inertial Navigation System (INS) 40, 119–121, 165, 217, 220–224, 225, 230, 238, 240, 248, 282, 352, 358 In-Flight Entertainment (IFE) 289, 322–324 In-Flight Shut Down (IFSD) 30, 293 Instrument Flight Rules (IFR) 150, 230, 240 Instrument Landing System (ILS) 129, 131, 153, 154, 157, 163, 164, 168, 211, 227, 229, 234, 238, 246, 252, 276, 281, 343, 352, 365, 367, 369, 381 approach 243, 245 DME 245
Glide slope 153, 155 Global Navigation Satellite System (GNSS) 112, 129, 150, 153, 215, 226, 227, 233, 364 Global Positioning System (GPS) 40, 121, 129, 149, 150–152, 156, 157, 204, 215, 222, 226, 227–233, 238,
glide slope 153, 164 LOC 237 localizer 153, 156 markers 155 VOR 149 Integrated Actuator Packages (IAPs) 256, 257, 259, 283
394
Civil Avionics Systems
Integrated Circuits (ICs) 3, 8, 9, 17, 47, 200 Integrated Drive Generator (IDG) 63, 72, 76, 87, 91, 92, 94, 95 Integrated Modular Avionics (IMA) 3, 29–30, 329, 331, 332, 334–336, 344, 345 Integrated Refuel Panel (IRP) 305, 306 Integrated Sensor Suite (ISS) 343 Integrity 33, 45, 47, 48
Mean Time Between Failure (MTBF) 44, 46, 191 Mechanical link 255, 261, 262, 267, 270 Microwave Landing System (MLS) 129, 156, 157, 229, 252, 281, 352, 365, 381, 383 MIL-HDBK-781 46 MIL-STD-1553 11, 14, 18, 378 MIL-STD-1553B 6, 12, 14, 15, 16, 17, 19, 20, 21, 26, 329
Power: contactor 77, 78 Control Unit (PCU) 266, 267, 268, 270 conversion 65, 78 and energy storage 78 Distribution Assemblies (PDAs) 344 generation 65 control 68 quality 76 Supply Unit (PSU) 27, 29, 329, 330,
Joint Airworthiness Authority (JAA) 34, 59 Joint Airworthiness Requirements (JARs) 183 Juneau, Alaska 356, 370–373
Minor condition 38, 39, Mode Sfailure 142–146, 350, 366, 36758 Modular Avionics Units (MAUs) 25, 343, 344 More-Electric Aircraft (MEA) 97, 258 Multifunction Control and Display Units (MCDUs) 232, 252, 273 Multimode Receiver (MMR) 227, 381
334, 335, switching 77, 341 81 Transfer Unit (PTU) 311, 313 Precision RNAV (PRNAV) 356, 358 Preliminary Systems Safety Analysis (PSSA) 36, 37, 39, 40 Primary Flight Computers (PFCs) 259, 264, 272 command lane 272 monitor lane 272 standby lane 272 Primary Flight Control System (PFCS) 254, 264, 265, 266, 271, 279, 280 Primary Flight Display (PFD) 153, 171–173, 189, 192, 205, 207, 208, 211, 252, 369 Primary power: distribution 77 and protection 65 Primary Surveillance Radar (PSR) 141, 142 Product life cycle 50, 51 Proximity Switch Electronics Unit (PSEU) 24, 280, 315
Kalman filter 238 sensor fusion 238 Lateral navigation (LNAV) 239–242, 278, 283, 361 Lighting 82, 84 Line Replaceable Modules (LRMs) 30, 96, 331, 338, 343 Line Replaceable Unit (LRU) 11, 19, 21, 26, 27, 28, 29, 30, 85, 95, 192 Link 16 382, 384 Liquid Crystal (LC) 199, 202 Local Area Augmentation System (LAAS) 153, 157, 227, 229, 281, 352, 363–365 Local Area Network (LAN) 26, 321 Localizer 153 needle 153 Long Range Operations (LROPS) 60, 61 LORAN C 1, 129, 158, 215, 218, 230, 240, 358 Lower SB (LSB) 132, 133
NATO STANAG 3838 12 Navigation 171, 217, 339, 350, 352 aids 282, 380 and flight management 379 database 239 Displays (ND) 171–173, 178, 189, 205, 207, 209, 233, 252, 369 instruments 189 sensors 238 System Data Base 249 Non-Directional Beacon (NDB) 147, 219, 230, 239 North Atlantic (NAT) 220 Notices to AirMen (NOTAMS) 11 Oceanic en route 229, 353 On-Board Oxygen Generation System (OBOGS) 21, 383 Operate phase 50, 55–56 Original Equipment Manufacturers (OEMs) 25, 332
Mach (M) 101, 105, 107, 216 Magnetic compass 162 Heading and Reference System (MHRS) 112–113 north 216 sensing 110
Parallel operation 68–70 Permanent Magnet Alternators (PMAs) 88, 291, 292 Permanent Magnetic Generator (PMG) 65, 86, 88 Personnel, matériel, and vehicle
RA 145, 146 Radar: altimeter 122 altitude 216 sensors 101, 122 Radio: altimeter 164 Frequency (RF) 129 frequency spectrum 129 Frequency Unit (RFU) 138, 140 Magnetic Indicator (RMI) 113, 147 navigation 215, 218
Maintenance Access Terminal (MAT) 321 Major failure condition 38, 39, 58 Manchester biphase 15, 20 Maritime Patrol 376, 385 Aircraft (MPA) 385–388 Markov Analysis (MA) 36, 48, 49, 50
transport 376, 383 PFD/ND 172, 176, 190 Pitch 167, 252 attitude 167 Portable Maintenance Access Terminal (PMAT) 11, 321 Position gyroscopes 115
Technical Committee Association (RTCA) 34 DO 178B 184, 213 DO-160 195 DO 160C 34, 37, 76, 99 DO 178B 31, 32, 34–37 DO 181 159
Index
395
DO 185 159 DO 186 159 DO 254 34, 35, 36, 37, 62, 184, 213 Ram Air Turbine (RAT) 44, 45, 77, 86, 87, 90, 95, 311–314, 338 Random Access Memory (RAM) 11 Range target: safety 390 security aircraft 376 RAs 145
ARP 1068 194, 213 ARP 1874 194, 213 Design objectives for CRT displays in transport aircraft 183 ARP 4256 195, 213 ARP 4754 34, 35, 37, 43, 62, 184 ARP 4761 34, 35, 36, 37, 43, 62 AS 8034 194, 213 Minimum performance standards for Electronic Displays 183 Solid-State Power Controllers (SSPC)
UK Def Stan 00-18: Parts 12 Parts 1 12 Ultra High-Frequency (UHF) 129, 138, 382 TV 130
Rate gyroscopes 115, 116 Receiver Autonomous Integrity Monitoring (RAIM) 152, 230–232 Reduced Vertical Separation Minima (RVSM) 105, 146, 352, 361, 363, 373 Implementation 363 Reliability 44, 46 Remote Terminals (RTs) 15, 17 Required Navigation Performance (RNP) 237, 352, 355–359, 372, 373 0.15 356, 370 0.2 370 0.3 356, 370 1 356, 358 2 356 4 356, 357 5 356, 358 10 356 12 356 RNAV 355, 360, 373 Required Time of Arrival (RTA) 350 RLGs 116, 121 Root Sum Squared (RSS) 353, 354 Royal Aircraft Establishment (RAE) 172 Runway Visual Range (RVR) 281
82, 98Trim Control Modules Stabilizer (STCMs) 268, 271 Standard Instrument Departure (SID) 230, 243 Standard Terminal Approach Routes (STARs) 236, 239, 243 Standard Terminal Arrival Routes (STAR) 230, 244, 245 Standby instruments 169, 171, 182 Static Air Temperature (SAT) 101, 103, 107 Static pressure 102, 104 Status words 15, 16 Surveillance 350, 366 System requirements 42, 43 System Requirements Review (SRR) 57, 58 System Safety Analysis (SSA) 36, 37, 39, 40
(VSCF) 95 62, 64, 72, 74–77, 87 converter cycloconverter 72 VDL 350–351, 366 Vehicle Management System (VMS) 22 Vertical navigation (VNAV) 240, 241, 242, 248–249, 278, 283, 353–354 Vertical speed (VS) 101, 163 Very High Frequency (VHF) 2, 129, 131, 132, 135, 136, 138, 147, 227, 229, 319, 325, 326, 343, 350, 367, 382 Data Links (VHFDLs) 136, 350 Digital Radios (VDRs) 370 Omnidirectional Radio Range (VOR) Distance Measuring Equipment (DME) 373 OmniRange (VOR) 40, 129, 131, 136, 147–150, 167, 220, 221, 222, 227, 230, 234, 237, 238, 239–240, 244, 276, 279, 343, 352, 358 DME 149, 218–220, 233, 240, 243, 244, 354, 358, 367 Error 354 ILS 273, 275 TACAN (VOR/TAC) 129, 148, 150, 219 OmniRanging/Distance Measuring Equipment (VOR/DME) 218 TV 130 voice 352 Voltage regulation 68, 70
SAFEbus® 340 Satellite Communications (SATCOM) 129, 131, 138–141, 325, 326, 350, 367, 384 Scanning DME 149 Secondary Attitude Air data Reference Unit (SAARU) 223, 224, 225,
TA 144 TACtical Air Navigation (TACAN) 129, 149, 150, 167, 221, 230, 234, 238, 381, 383, 384 DME 150 Tailplane Horizontal Stabilizer (THS) 254, 256 258, 261, 262, 264, 283 Terrain Avoidance Warning System (TAWS) 3, 246, 249, 381 Test Phase 50, 55 Time Division Multiple-Access (TDMA) 351 Top-down approach 40, 41 Total Air Temperature (TAT) 101, 103 Traffic Collision and Avoidance System (TCAS) 3, 129, 144, 146,
265, 280 Secondary Surveillance Radar (SSR) 141, 142, 144 Shadow-mask CRT 187, 196, 198 SIDS 236, 239, 244 Society of Automobile Engineers (SAE) 34
204, 212, 247, 366 TCAS I 144 TCAS II 144–146, 366 Change 7 146 Transformer Rectifier Unit (TRU) 65, 78–80, 90, 92, 93, 96 True airspeed (TAS) 101, 216
V Diagram 58, 59 Variable Frequency (VF) 70, 72, 73–75, 87, 97, 285 Variable Speed Constant Frequency
Weather radar 122, 126–128 Wide Area Augmentation System (WAAS) 153, 157, 228, 229, 281, 352, 363–365
Further Reading Aircraft Electrical Systems, E H J Pallett, Longmans Group Limited, 1987, ISBN 0-582-98819-50. Aircraft Instruments and Integrated Systems, E H J Pallett, Longmans Group Limited, 1992, ISBN 0-582-08627-2. Aircraft Systems, Ian Moir and Allan Seabridge, Second Edition, Professional Engineering Publishing Ltd (IMechE) in association with the AIAA, published May 2001, ISBN 1-86058-289-3 (UK)/1-56347-505-3 (US).
Avionics Navigation Systems, Second Edition, Myron Kayton and Walter R Fried, John Wiley & Sons, 1997, ISBN 0-471-54795-6. Digital Avionics Systems, Principles and Practice, Second Edition, Cary Spitzer, McGraw-Hill Inc, 1993, ISBN 0-07-060333-2. Flight Control Systems: Practical Issues in Design and Implementation, R Pratt, IEE Publishing, 2000, ISBN 0-85296-766-7. Introduction to Airborne Radar , Second Edition , George W Stimson, SciTech Publishing Inc, 1998, ISBN 1-891121-01-4. Mechanical Reliability , A D S Carter, Second Edition, ISBN 0-333-40586-2 Practical Reliability Engineering, Patrick D T O’Connor, Third Edition 1992, ISBN 0-471-92696-5. Principles of Avionics Data Buses , Avionics Communications Inc, 1995, ISBN 1-88554400-6. Reliability Toolkit: Commercial Practices Edition, Reliability Analysis Center, 1995 Edition. The Future Air Navigation System (FANS), Vincent P Galotti Jr, Ashgate Publishing Company Limited, 1998, ISBN 0-291-39833-2.
