Avionics Lecture - 2022 Computer Architecture PDF

A/C general physic COMPUTER ARCHITECTURE COMPUTER ARCHITECTURE 2022 January 2022 1 I) INTRODUCTION ◦ Notion of system, ATA breakdown ◦ Avionics: definition, meaning II) COMPONENTS OF...

A/C general physic COMPUTER ARCHITECTURE COMPUTER ARCHITECTURE 2022 January 2022 1 I) INTRODUCTION ◦ Notion of system, ATA breakdown ◦ Avionics: definition, meaning II) COMPONENTS OF AN AIRBORNE ELECTRONIC SYSTEM ◦ Sensors ◦ Actuators ◦ Computers III) DEVELOPMENT PROCESS ◦ Off-the-shelf equipment / specific equipment ◦ Actors and development phases for specific equipment IV) FLIGHT DECK V) CONCLUSIONS COMPUTER ARCHITECTURE 2022 2  Notion of system  Avionics within the airborne systems COMPUTER ARCHITECTURE 1/6/2025 3  A system is an organized assembly of ………........... which have relations with each other and with the external environment and fulfill together an ……………….. …………………..  A system may, in turn, be a component of another system ◦ Example: A transport aircraft is a system:  Which is a component of the transport system,  Which is, itself, made up of several airborne systems.  Airborne system consists in equipment used together for a common purpose COMPUTER ARCHITECTURE 1/6/2025 4 communication satellites SATCOM global positioning satellites (GPS) aircraft TCAS S mode ATSU (detection and coordination) VDL HFDL SATCOM ground station VHF HF ground station ground station ACARS network Airline Air Operations Traffic Control Control COMPUTER ARCHITECTURE 1/6/2025 5  AVIONICS = ELECTRONICS / AIRCRAFT ASSEMBLY OF THE AIRBORNE ELEMENTS (SENSORS, DATA TRANSMISSION, COMPUTERS, CONTROL AND COMMAND ELEMENTS) USED TO PERFORM ……………. USING …….………….. AND ……..………….TECHNIQUES. COMPUTER ARCHITECTURE 1/6/2025 6 COMPUTER ARCHITECTURE 2022 7  Controls Flight Controls computers Actuators SEC 1 - servocontrol (ELEC/hydrau) - yaw damper SEC 2 - trim actuator - Travel limit Unit - ELEC/Hydrau PRIM 1 Actuator PRIM 2 EWD Sensors : PRIM 3 - accelerometers - gyrometer SD - tachymeter,... Others systems : - FMGEC FCDC 1 - SFCC - ADIRU - RA FCDC 2 - LGCIU - ECU Audio and maintenance COMPUTER ARCHITECTURE 1/6/2025 8 AIRFRAME SYSTEMS 21 AIR COND. 22 AUTO FLIGHT 23 COMMUNICATIONS 24 ELECTRICAL POWER 25 EQUIPMENT 26 FIRE PROTECTION 27 FLIGHT CONTROLS 28 FUEL 29 HYDRAULIC POWER 30 ICE & RAIN 31 INSTRUMENTS 32 LANDING GEAR PROTECTION 34 NAVIGATION 35 OXYGEN 33 LIGHTS 37 38 WATER/WASTE 36 PNEUMATIC 46 INFORMATION 49 AIRB. AUX. POWER 45 MAINTENANCE SYSTEM 53 FUSELAGE 51 STRUCTURE 52 DOORS 56 WINDOWS PRACTICES 55 STABILIZERS 54 NACELLES/PYLONS 57 WINGS POWER PLANT 71 POWER PLANT 72 ENGINE 73 ENGINE FUEL & CTL 74 IGNITION 75 AIR 76 ENGINE CONTROLS 77 ENGINE INDICATING 78 EXHAUST 79 OIL 80 STARTING 81 TURBINE 82 WATER INJECTION COMPUTER ARCHITECTURE 1/6/2025 9  STRUCTURE/ EQUIPMENT ENGINES MANUFACTURING - Avionics - Section assemblies - Servocontrols - Hydraulic/air cond./ - Jacks fuel piping - Other procurements - Electrical harnesses - Etc. EXAMPLE A340: RECURRING COSTS A340 A330 Other equipment 50 % (servocontrol, jack, ENGINES 44 % 39 % packs, etc.) 17 % EQUIPMENT 15 % Avionics STRUCTURE/ 44 % 50 % (Control unit, CRT, MANUFACTURING 41 % computers, etc.) COMPUTER ARCHITECTURE 1/6/2025 10  A300 (19 + 1 OPTIONAL PMS) Example: AIRBUS AUTOPILOT (and FMS) (SINGLE 1 ATS) N1 LIMIT 1 AUTO THRT 2 TEST COMPUTER A310 / A300-600 4 (10) PITCH TRIM 2 4 TCC YAW DAMP & LIM 2 A320 FMC (4) LOGIC COMPUTER 2 A340 + 1 FD FAC/FLC 4 (2) SWITCHING LONGITUDINAL 2 2 FMGC COMPUTER LATERAL 2 2 2 2 FCC FAC FMGEC COMPUTER 1st DIGITAL 2nd DIGITAL 3rd DIGITAL ANALOG GENERATION GENERATION GENERATION (VOLUME: 134 LITRES) (VOLUME: 63 LITRES) (VOLUME: 31 LITRES) COMPUTER ARCHITECTURE 1/6/2025 11 Systems that must manage complex interactions and high coupling are more prone to accidents Complex interactions are those of unfamiliar, unplanned, or unexpected sequences, and either not visible or not immediately comprehensible Tightly coupled systems have more time dependent processes; they cannot wait or stand by until attended to 12 Airborne system software (kSLOC) (Source Line Of Code x1000) 13  AFDX (shared Big data Sustainability Autonomous systems ARINC 429 ressources) Quantum Data Software as System integration Digitalization computer broadcast a service 2000 2020 2040 Pressure to digitalize, to reduce emission at the same time as reducing journey times are already driving innovation through the value chain AFDX : Avionics Full Duplex Switched Ethernet COMPUTER ARCHITECTURE 2022 14  Sensors and actuators  Computers  Links COMPUTER ARCHITECTURE 1/6/2025 15  SENSORS Definition: Device which provides, from a ………………… quantity, another quantity (often in electrical form), - function of the first one, - directly usable. EXAMPLES: Two-state "discrete" sensors Pressure switch Doors, landing gear status "Analog" sensors Angle of Attack Pressure Temperature COMPUTER ARCHITECTURE 1/6/2025 16  ACTUATORS Definition: Device (mechanical, electrical, pneumatic, hydraulic) intended to actuate an equipment, a system, to modify its operation or state. EXAMPLES: Indicator light Loud speaker Display unit CRT (Cathode Ray Tube) LCD (Liquid Crystal Display) matrix screen Servocontrol hydraulic jacks( ailerons, spoilers) electric motors (trim) COMPUTER ARCHITECTURE 1/6/2025 17  COMPUTER Definition: "Black" box the purpose of which is to ……. …… …………………. ………... It usually consists in the following: An envelope → housing and backplane Power supply → power Input/output cards → interface with external environment A CPU (Central Processor Unit) card → brain Specific cards Examples: - FMGEC → Flight and navigation computer - FWC → warning computer COMPUTER ARCHITECTURE 1/6/2025 18 COMPUTER COMPUTER ARCHITECTURE 1/6/2025 19  COMPUTER Hardware Similar electronic components (CPU, memory, …) Electronic boards assembly (I/O, power supply, …) Build to perform specific functions COMPUTER ARCHITECTURE 1/6/2025 20  COMPUTER Software Software coding Software architecture (Instructions run by CPU, store in memory, …) Use if Inputs and Outputs COMPUTER ARCHITECTURE 1/6/2025 21  COMPUTER Hardware Hardware Stand alone machine Machine integrated in a global environment Light environmental standards Severe environmental standards Short-term life Medium / Long-term life Variable reliability Contractual safety / reliability State of the art technology Proved technology COMPUTER ARCHITECTURE 1/6/2025 22  COMPUTER Software Software Compatibility with many software Specific software OS (Windows, Linux, …) No OS Often customisable Few customisations possible Variable stability Very stable COMPUTER ARCHITECTURE 1/6/2025 23 Purpose: Ensure aircraft and occupants safety 4 levels of failure consequences: Minor Hazardous Major Catastrophic Each level is associated to safety constraints Ex: the failure rate of a Catastrophic scenario must be less than 10-9 / FH To achieve safety requirements: ………………………………………………..…………………………… ………………………………………………..…………………………… ………………………………………………..…………………………… COMPUTER ARCHITECTURE 1/6/2025 24 Purpose: Optimise the computer availability to allow the aircraft accomplishing a mission in a safe way and in due time Computer reliability determined by the reliability of its most fragile sub- assembly (generally the power supply or functional card) Contained failure: A failure that does not provoke a failure on another computer or information losses for other computers To ensure failure containment: ……………………………………………………………………. ……………………………………………………………………. Reliability measured through MTBF – Mean Time Between Failure MTBUR – Mean Time Between Unit Replacement COMPUTER ARCHITECTURE 1/6/2025 25 DO 254 Design Assurance Guidance for Airborne Electronic Hardware is a document providing guidance for the development of airborne electronic hardware. The DO-254 standard are formally recognized by the authorities (EASA, FAA, …) as a means of compliance for the design of complex electronic hardware in airborne systems. There are five levels of compliance depending on the computer criticality ◦ A - ………………… ◦ B - ………………… ◦ C - ………………… ◦ D - ………………… ◦ E - ………………… A DAL (………………………………………………..) is associated to each computer depending on its criticality (e.g. ELAC is DAL A) Equivalent document exist for software development (referenced D0 178 - Software Considerations in Airborne Systems and Equipment Certification) COMPUTER ARCHITECTURE 1/6/2025 26 DO 160 qualification tests Temperature and altitude Magnetic effect Temperature variation Power input Humidity Voltage spike Shocks Audio frequency conducted susceptibility Vibration Induced signal susceptibility Explosion proofness Radio frequency susceptibility Waterproofness Emission of radio frequency energy Fluids Susceptibility Lightning induced transient susceptibility Sand and dust Lightning direct effect Fungus Resistance Icing Salt spray Electrostatic discharge Fire, flammability COMPUTER ARCHITECTURE 1/6/2025 27  POWER SUPPLY Sensors, Analog other INPUTS Discrete computers Digital digital DATA MEMORY CPU Analog Actuators, Discrete OUTPUTS other Digital computers PROGRAM MEMORY COMPUTER ARCHITECTURE 1/6/2025 28 Basic elements in a computer A computer is made of The casing Connector pins (Link up the computer to its environment) “Back plane” or cabled structure (Distributes signals inside the computer) Power supply Functional cards (Containing the CPU, memories, …) COMPUTER ARCHITECTURE 1/6/2025 29  Basic elements in a computer LRU (Line Replaceable Unit) CONCEPT HARDWARE SOFTWARE Power supply unit ARINC 600 connector Execution Interface board (Acquisition, generation, etc.) Software Specific board (Audio, memory Application expansion, etc.) backplane Software OBRM Mechanical structure (On-board replaceable module) CPU board (Processor, storages, etc.) COMPUTER ARCHITECTURE 1/6/2025 30 Computer : location and protection Memory Modules containing Operational programs Circuit DMC 1, 2, 3 breakers FWC 1, 2 SDAC 1, 2 Electrical compartment Overhead Aft avionics panel compartment Forward avionics compartment COMPUTER ARCHITECTURE 1/6/2025 31 LRUs are identified by their Part Number (P/N). HARDWARE Software and hardware modifications are traced through a P/N change. SOFTWARE A/C configuration management applies to hardware as well as software ! Software changes can be implemented : in shop : by reloading each EPROM in shop (A300) by OBRM replacement (A320/330/340), tape(s) inserted through the slots in front of the computer by data loading on aircraft : via MDDU (A320/330/340), A615-3 standard via DLCS (A380), high speed A615-A standard via portable data loader, A615-A OBRM : On Board Replaceable Module MDDU : Multipurpose Disk Drive Unit DLCS : Data Loading and Configuration System COMPUTER ARCHITECTURE 1/6/2025 32 BITE = Built-In Test Equipment Purpose : to detect and report failures, and to ease maintenance BITE functions : Monitors the operations of the various computer ressources Locates faults and memorize them Transmit faults to built-in maintenance function Data memorized by the BITE function software can be used : In flight : transmission to the onboard maintenance computer On ground, onboard the A/C : dialogue with the computer through dedicated interface, for troubleshooting On ground, in shop : analysis of data stored in memory only, for shop repair COMPUTER ARCHITECTURE 1/6/2025 33  Size (MCU)  Weight (kg)  Electrical power consumption (W)  Interface capability : various types (inputs / outputs)  discretes  analog  digital  Computation power ◦ referred to the application processed, the following performances shall be defined  cycle time  response time  number of data to be processed  Reliability: ◦ MTBF : Mean Time Between Failures  example : CRT >16,000H; LCD > 45,000H ◦ MTBUR : Mean Time Between Unscheduled Removal  example : CRT >15,000H; LCD > 40,000H  Environmental qualification  Development assurance level (DAL) COMPUTER ARCHITECTURE 1/6/2025 34 INTEGRATED MODULAR AVIONICS More and more functions on A/C, systems more complex : despite decreasing weight and size for each LRU, the global size and weight on A/C is increasing : more wiring, more power, more volume, diverse components to be managed MODULARITY: same computer hardware for several applications (in one or several LRMs) INTEGRATION: allocate the available physical space for the global ressources (computation, memory, communication), and allocate these ressources to the various applications COMPUTER ARCHITECTURE 1/6/2025 35 N different computers (LRUs), each dedicated to a function N identical computers (LRMs), hosting different softwares COMPUTER ARCHITECTURE 1/6/2025 36  N different computers (LRUs), each dedicated to a function A large « cabinet », in which LRMs are hosted, with common power supply and high-speed communication between LRMs COMPUTER ARCHITECTURE 1/6/2025 37 LRU : 1 COMPUTER = 1 ………………….. DEVELOPMENT LRM : - DEVELOPMENT OF ………………….. MODULES - USABLE BY MOST OF THE SYSTEMS - GROUPED IN STANDARD RACKS Benefits: Reduction of avionics costs (acquisition, spares) Reduction of avionics bay volume/weight Bring actuator and sensor processing units closer together Possible standardization of equipment Reduced development efforts Flexibility for function upgrading Improve operating safety Easier on-line maintenance …but some drawbacks to be addressed (common failure mode, segregation…) ! COMPUTER ARCHITECTURE 1/6/2025 38 LRU : 1 COMPUTER = 1 SPECIFIC DEVELOPMENT LRM : - DEVELOPMENT OF STANDARD MODULES - USABLE BY MOST OF THE SYSTEMS - GROUPED IN STANDARD RACKS Benefits: Reduction of costs (development & recurring & maintenance costs) Reduction of avionics bay volume/weight Bring actuator and sensor processing units closer together Possible standardization of equipment Reduced development efforts Flexibility for function upgrading Improve operating safety Easier on-line maintenance Easier hard and soft updates …but some drawbacks to be addressed (common failure mode, segregation…) ! COMPUTER ARCHITECTURE 2022 39 1980 1990 2020 2030 Federated architecture IMA architecture DIMA architecture 1 function = 1 function = 1 function = Many functions = Dynamic distribution many LRUs 1 LRU 1 LRM 1 LRM of functions on LRM Modularity Integration Ex: A330, Future Ex: A310 Ex: A320 Ex: B777 aircraft A350, B787 DIMA : Distributed Integrated Modular Avionics RDC : Remote Data Concentrator COMPUTER ARCHITECTURE 2022 40  Off-the-shelf equipment / specific equipment  Actors and development phases for specific equipment. COMPUTER ARCHITECTURE 1/6/2025 41  The same equipment (featuring the same P/N) may be installed on several aircraft types from several manufacturers (ex.: on board VHF transceiver, VOR, DME,...).  The equipment meets a well-defined standard and does not depend on the aircraft characteristics. (radio communication / radio navigation equipment)  These equipment items can be selected and bought by the airline. (BFE - Buyer Furnished Equipment)  The aircraft manufacturer manages the interface only. COMPUTER ARCHITECTURE 1/6/2025 42  The equipment is developed for a given aircraft type (ex.: A340 FWC).  The equipment is generally of complex design; there is no specific standard ; the equipment is closely united to the other aircraft systems and/or dependent from the aircraft characteristics.  It is usually provided by a single equipment manufacturer (for a given aircraft).  The aircraft manufacturer controls and manages the specification, the tests, the certification and the changes. COMPUTER ARCHITECTURE 1/6/2025 43  The aircraft manufacturer drafts more and more detailed specifications (of specific systems). ◦ Because of the higher systems integration/interaction ◦ for better design control (safety analysis, cost and time control, etc.) ◦ for better knowledge of the system (easier incident analysis, modification impact measurement, etc...) ◦ for better change control and better reactivity  Wide use of the computer-aided means (CAS, control tools) to improve the specification quality  Validation of the specifications by means of simulation tools  Automatic encoding of the application software ◦ coding error removal ◦ test simplification COMPUTER ARCHITECTURE 1/6/2025 44 TIMELINE when STAGES what MAIN ACTORS who SPECIFICATION AIRCRAFT SPECIFICATION MODIF. REQUEST CUSTOMER SYSTEM SPECIFICATION MODIF. AIRCRAFT MANUFACTURER T0-48 EQUIPMENT SPECIFICATION ANALYSIS EQUIPMENT DESIGN NON CONFORMITY DESIGN T0-36 HARDWARE MANUF. EQUIPMENT MANUFACTURER SOFTWARE PRODUCTION T0-24 VERIFICATION EQUIPMENT TESTS INTEGRATION TESTS AIRCRAFT MANUFACTURER T0-12 FLIGHT TESTS CERTIFICATION T0 IN SERVICE COMPUTER ARCHITECTURE 1/6/2025 45  Validation Verification Aircraft Flight MANUFACTURER spec. tests AIRCRAFT System spec. Integration bench tests Equipment spec. Hardware HW spec. tests MANUFACTURER Software SW EQUIPMENT spec. tests Component spec. COMPUTER ARCHITECTURE 1/6/2025 46 COMPUTER ARCHITECTURE 2022 47 A319/A320/A321 A330/A340 COMPUTER ARCHITECTURE 2022 48  EFIS EFIS ECAM STAND BY INSTRUMENTS COMPUTER ARCHITECTURE 2022 49  EFIS EFIS STAND BY INSTRUMENTS ECAM COMPUTER ARCHITECTURE 2022 50  ELECTRONIC FLIGHT INSTRUMENT SYSTEM PFD1 ND1 ND2 PFD2 COMPUTER ARCHITECTURE 2022 51 EFIS CONTROLS COMPUTER ARCHITECTURE 2022 52 ELECTRONIC CENTRALIZED AIRCRAFT MONITORING Engine/Warning Display System Display COMPUTER ARCHITECTURE 2022 53  ECAM CONTROLS Lights System pushbuttons COMPUTER ARCHITECTURE 2022 54  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 55  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 56  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 57  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 58  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 59  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 60  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 61  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 62  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 63  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 64  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 65  ECAM Engine/Warning ECAM Display control Panel System Display COMPUTER ARCHITECTURE 2022 66 Master Warning & Master Caution COMPUTER ARCHITECTURE 2022 67 Basic Standby ISIS instruments Or (Integrated Standby Instrument System) COMPUTER ARCHITECTURE 2022 68  VIDEO A330 Landing from the cockpit COMPUTER ARCHITECTURE 2022 69 EIS and FWS COMPUTER ARCHITECTURE 2022 70  EIS (Electronic Instrument System) The FWS uses the EIS (ECAM part) to display the warning messages Display function for : - EFIS (Electronic Flight Instrument System) - ECAM (Electronic Centralized FWS Aircraft Monitoring) (Flight Warning Computer) Central Warning/Caution Processing and Management Navigation sensors ; A/C systems COMPUTER ARCHITECTURE 2022 71 COMPUTER ARCHITECTURE 2022 72 The Electronic Instrument System is composed of the following : ◦ Six identical (7.25 in x 7.25 in) cathode ray tubes Display Units (DU) or flat screen DU, including integrated graphics generator :  Two primary flight displays + two navigation displays (EFIS).  One engine warning display + one system display (ECAM). ◦ Three Display Management Computers (DMC) :  Generating images to be displayed on PFD, ND and ECAM DUs.  Digital data link to display units.  Each DMC has two independent channels EFIS/ECAM.  Each DMC is able to drive all 6 DUs with 4 independent format (PFD, ND, E/WD, SD) ◦ Two System Data Acquisition Concentrators (SDAC) :  Acquiring systems data for transmission of caution to FWCs and systems condition to DMCs.  Operations are not affected with a failure of one SDAC ◦ Two Flight Warning Computers (FWC) :  Generating alert messages, aural alerts and procedural messages for display on ECAM.  Operations are not affected with a failure of one FWC. COMPUTER ARCHITECTURE 2022 73 COMPUTER ARCHITECTURE 2022 74  The EIS systems has the following characteristics :  Fully redundant architecture :  partitioned DMCs to drive the DUs  Full reconfiguration capability  Independence between EFIS and ECAM switching COMPUTER ARCHITECTURE 2022 75 Landing on water shall always be done whith wheels up, otherwise… COMPUTER ARCHITECTURE 2022 76  Flight Mode Annunciator Attitude Guidance Altitude Airspeed Vertical Speed Heading/track All necessary information for short term flight COMPUTER ARCHITECTURE 2022 77  ROSE ILS ROSE VOR ROSE NAV ARC PLAN Weather radar image can be superimposed All data necessary for navigation and long term flight COMPUTER ARCHITECTURE 2022 78 COMPUTER ARCHITECTURE 2022 79  Wheel page Elec page Air bleed page Cabin pressure page APU page Engine page Hydraulics page Fuel page Door/oxygen page Air conditioning page Flight control page Cruise page COMPUTER ARCHITECTURE 2022 80  System computer ◦ There are two Flight Warning Computers (FWCs) which generate alert messages, aural alerts and procedural messages for display on the ECAM. ◦ The operations are not affected with either FWC failure. ◦ The FWS performs in real time the computation and management of central warning and cautions :  Warning/caution hierarchical classification (level 3 : red warning ; level 2 : amber caution ; level 1 : simple caution) and priority rules  Warning/caution inhibitions  Operational failure categorization : independent failure ; primary failure ; secondary failure. COMPUTER ARCHITECTURE 2022 81 ◦ The FWS directly activates the crew attention getters (aural and visual) and uses the EIS (ECAM : E/WD and SD) to display the warning/caution messages. ◦ The FWS also computes the MEMO information (presented on the E/WD) and performs an automatic radio height call-out function. COMPUTER ARCHITECTURE 2022 82  Engine/Warning Display Data permanently displayed Data related to flight phase or Engine primary depending of A/C system failure/status parameters Fuel Slat/flap position Memo or Warning/Caution messages System Display System synoptic or Status Permanent data COMPUTER ARCHITECTURE 2022 83  Wheel page Engine page Cruise page Doors/oxygen page APU page Door Wheel Engine Cruise Wheel Door APU Engine 2 nd engine shutdown 1 st engine to power 1 500 ft Electrical power engine start 800 ft 5 minutes after Touch-down Lift off 80 kt 80 kt st 1 1 2 3 4 5 6 7 8 9 10 COMPUTER ARCHITECTURE 2022 84  The ECAM function operates in four modes : ◦ NORMAL mode : automatic flight phase related mode  MEMO on E/WD most suitable system page on SD ◦ MANUAL mode : use of the ECAM control panel  any of the system pages may be called-up on SD by pressing the corresponding selector keys of the ECAM control panel ◦ ADVISORY mode : parameter trend monitoring  corresponding system page on SD with affected parameter pulsing ◦ FAILURE RELATED mode :  failure indication and abnormal/emergency procedures on E/WD affected system synoptic on SD Note : E/WD is the Engine and Warning Display (upper ECAM) and SD is the System Display (lower ECAM) COMPUTER ARCHITECTURE 2022 85  FAILURE 2 CORRECTIVE ACTION 1 FAILURE IDENTIFICATION CORRECTIVE ACTION ASSOCIATED SYSTEM PAGE FAILURE IDENTIFIED 3 ACTIONS CLEARED MEMO SAME SYSTEM PAGE AUTOMATIC SYSTEM CORRECTIVE PAGE 4 ACTION SHOWN 5 MEMO STATUS SYSTEM PAGE COMPUTER ARCHITECTURE 2022 86  In case of a failure occurs in one system (detected by the BITE of a computer), the ECAM will display : ◦ The description of failure and associated corrective procedure (on EWD) ◦ The associated system synoptic with visual cues (on SD)  The following pages describe a presentation sequence when an independent failure occurs, the example of a blue hydraulic reservoir OVHT fault is taken. COMPUTER ARCHITECTURE 2022 87 Engine/warning display System display ECAM configuration (cruise) before the warning occurs COMPUTER ARCHITECTURE 2022 88  Single chime Engine/warning display System display Failure identification Switch “OFF” Blue ENG PUMP 1 Corrective action for next page COMPUTER ARCHITECTURE 2022 89  Engine/warning display System display Press for next page Secondary failure COMPUTER ARCHITECTURE 2022 90 Engine/warning display System display Press for next page COMPUTER ARCHITECTURE 2022 91 Engine/warning display System display Next Allow return to flight phase related system page COMPUTER ARCHITECTURE 2022 92  Engine/warning display System display “STS” reminder indicates to the crew that the status page is no longer empty COMPUTER ARCHITECTURE 2022 93 COMPUTER ARCHITECTURE 2022 94  NEW NEEDS HMI - Human Machine Interface (e.g: Interactive display, 3D display). Intelligent systems (e.g. predictive maintenance) Improved communications (air to ground & between airplanes) Optimized navigation and aircraft utilization Improved passenger experience Sustainable aviation COMPUTER ARCHITECTURE 2022 95  POSSIBLE SOLUTIONS Data science DIMA architecture New communication standards and support (e.g: Bus, Networks, Optical) Use of standard hardware and/or software elements of non-aeronautical fields (e.g. tablets) Data-link, 3D screen, voice recognition,... COMPUTER ARCHITECTURE 2022 96