Functional Description Elite Evolution S612 EASA CS-FSTD (A) BITD Flight Simulators Limited Unit 3A Gilray Road Vinces road Industrial Estate Diss Norfolk. IP22 4EU www.flight-simulators.co.uk Tel: +44 1603 397334 Also At International Aviation Academy - Norwich
section page 2 of 39 Table of Contents 1 Functional Description Summery...6 1.1 General... 6 1.2 Scope... 6 1.3 General Configuration...6 1.3.1 Cockpit... 7 1.3.2 Instructor Station...7 1.3.3 Control System... 7 1.3.4 Computer System...7 1.4 Maintenance and Support...7 1.4.1 Documentation... 7 1.4.1.1 Documentation Guide...8 1.4.1.2 Operating Manuals...8 1.4.1.3 Maintenance Manuals and Associated Documents...8 1.4.1.4 Computer and Peripheral Manuals...8 1.4.1.5 Range of Spares...8 1.4.2 Spare Parts... 8 1.4.2.1 General...8 1.4.2.2 Elite evolution S612 Spare Parts...8 1.4.2.3 Computer Spare Parts...8 1.4.3 Tools and Test Equipment...8 1.4.4 Maintainability... 9 1.4.5 Standardization... 9 1.4.6 Warranty... 9 2 Description of flight deck...10 2.1 General... 10 2.1.1 Cockpit... 10 2.1.2 Aircraft Parts...10 2.1.3 Panel Layout...11 2.1.3.1 Overview...11 2.1.3.2 Pilot's Main Panel...12 2.1.3.3 Engine Instrument Panel...12 2.1.3.4 Avionics Panel / Nav Panel...14 2.1.3.5 Power Quadrant and Switches Panel...15 2.1.4 Primary Flight Controls...16 2.2 Instrument Panel Technical Realization...16 2.3 Simulated Instruments...17 3 Instructor Station... 18 3.1 Instructor Station Features...18 3.2 Pages Overview...19 3.2.1 Initial Position...19 3.2.2 Meteo Pages... 19 3.2.3 Control Page... 22 3.2.4 MAP Page...22 3.2.5 Navigation Modification Page...24
section page 3 of 39 3.2.6 Configuration Page...25 3.2.7 Malfunctions Page...25 3.2.7.1 Individual Instrument Failures...25 3.2.7.2 System Failures...25 3.2.7.3 Receiver Failures...25 3.2.7.4 Transponder...25 3.2.7.5 Gear / Flaps...25 3.2.7.6 Engines...26 3.2.8 Aircraft-State Snapshot...26 3.2.9 Communication System...26 3.2.10 Instructor Seat...26 4 Primary Flight Controls... 27 4.1 General Description...27 5 Computer System and Peripherals...28 5.1 Hardware... 28 5.2 Programming Language...28 5.3 Maintenance Capabilities...28 5.4 System Spare Capacity...28 5.5 Diagnostic... 28 6 Description of Simulation...29 6.1 Aerodynamic and Performance...29 6.1.1 Wind Effects... 29 6.1.2 Atmosphere...29 6.1.3 On Ground Handling...29 6.1.4 Take-Off and Climb-Out...29 6.1.5 Stalls... 29 6.1.6 Landing... 29 6.1.7 Instrument Responses...30 6.2 Radio Navigation Simulation...30 6.2.1 Radio Navigation Computation...30 6.2.2 Ground Facility Data...30 6.3 Aircraft Systems Simulation...30 6.3.1 Electrical System...30 6.3.2 Engine System...30 6.3.3 Fuel System...31 6.3.4 Pitot Static System...31 6.3.5 Landing Gear, Brakes and Nose Wheel Steering Systems...31 6.3.6 Flight Control System...31 6.4 Avionics / Radio System Simulation...31 6.4.1 General... 31 6.4.2 VHF Navigation / Communication System...31 6.4.3 Transponder System...32 6.4.4 ADF System...32 6.4.5 DME System... 32 6.4.6 GPS System...32 6.5 Flight Director / Autopilot System...32
section page 4 of 39 6.6 Sound System... 32 7 Visual System (optional)...33 7.1 Visual System Features...33 7.1.1 Field of View... 33 7.1.2 Airport Associated Lighting Facilities...33 7.1.3 Day to night transition...33 7.1.4 Clouds / Visibility...33 7.1.5 Runway Features...33 7.1.6 Real Airport Models...33 7.1.7 Satellite Image Technology...34 7.1.8 Digital Terrain Models...34 7.1.9 Programming Languages used in RealView / GenView...34 8 Project Scheduling... 35 8.1 Project Scheduling System...35 8.2 Milestone Schedule...35 8.3 Project Status Reviews...35 8.4 Project Reports...35 9 Installation... 36 9.1 Site Layout... 36 9.2 Power... 36 9.3 Environmental Considerations...36 10 Acceptance Procedure... 37 10.1 Acceptance Timing...37 10.2 Testing Procedure...37 11 On-Device Training...38 11.1 Factory Training... 38 12 Request for EASA CS-FSTD (A) qualification...39 12.1 EASA Certification...39
section page 5 of 39 Illustration Index Image 1: Elite Avionics Rack...14 Image 2: Meteo wind and turbulence Page...19 Image 3: Meteo clouds and visibility Page...20 Image 4: Metar Page...21 Image 5: Control Page...21 Image 6: Map Page...23 Image 7: Navigation Modification Page...24 Image 8: Configuration Page...25 Image 9: Malfunctions Page...26
section page 6 of 39 1 Functional Description Summery 1.1 General This document presents a detailed procurement specification for a BITD Elite evolution S612, single engine high performance Training Device, meeting the requirements specified in the EASA document EASA CS-FSTD (A). Definitions: a) Customer b) Manufacturer Elite Simulation Solutions AG, Dübendorf, Switzerland c) Basic Instrument Training Device (BITD) A ground based training device which represents the student pilot s station of a class of aeroplanes. It may use screen based instrument panels and spring loaded flight controls, providing a training platform for at least the procedural aspects of instrument flight. d) Flight deck Cockpit environment replicating the simulated Aircraft and in which the controls and switches will operate as in that Aircraft (table based solution). It is sufficiently enclosed to exclude pilot distraction and furnished with ergonomically positioned pilot seats. e) Cockpit Instrument Panel replicating a generic single engine high performance instrumentation. f) Functional - A three - dimensional reproduction or actual aircraft part connected to system logic or instructor controlled logics. g) Non-functional (dummy) - A three-dimensional reproduction or actual aircraft part not connected to system logics. h) System logics - Limited simulated Aircraft systems operation, in accordance to meet the training requirements. i) Available Data - Aircraft design data, Pilot s Operating Handbook, Aircraft Maintenance manuals, Observations on ground and in the air. j) Flight Test Data - Data will be / has been gathered by the Aircraft manufacturer. 1.2 Scope The Elite evolution S612 equipment shall simulate normal conditions for ground operations (limited), take-off, in-flight manoeuvres, radio navigation, instrument approach and landings. Actions by the crew on the simulated controls in the flight compartment shall interact with simulated system logics and dependencies in accordance with this specification and the available Aircraft data. The limits of flight and systems are specified herein. 1.3 General Configuration The Elite evolution S612 is consisting of the following major sub assemblies: a) A Cockpit layout representative of a generic dual piston engine land aircraft (MEL). b) An Instructor Station to give the instructor access to the simulation environment, as well as to a variety of training tools. A graphic display for various information, areaand approach tracking is also part of this facility.
section page 7 of 39 c) A spring loaded Control Loading System which produces Aircraft configuration dependent control feelings and control travels which respond in a similar manner under the same flight conditions as in a typical single engine aircraft. d) A simulation computer system consisting of a state of the art computer hardware, complying to the current industry standard and simulation software. 1.3.1 Cockpit Actual aircraft hardware components are not used. A functional device is fabricated by the manufacturer. Factors which have resulted in the use of replicas include: a) Cost b) Reliability - Aircraft use is more demanding than simulator use. c) Ease of maintenance - Maintenance access is necessarily different from the Aircraft. d) Availability - Many aircraft components have unacceptable long lead times leading to delays in Simulator delivery. 1.3.2 Instructor Station The instructor station will give the instructor access to the following functions: Environment conditions Aircraft status Freeze selection Repositions Pre-selection of environmental conditions Malfunction selection Selection of visual conditions (only if external Visual System installed) Navigation area selection Simulated ATC communication with the cockpit crew Selection of initial conditions 1.3.3 Control System The spring-based control system provides the pilot a repeatable controls force and natural controls response that broadly corresponds to the control forces and travels of the simulated class of aeroplane. 1.3.4 Computer System The computer system consists of the current industry standard PC. The current industry standard of software is used for the operating system, as well as for the simulation software. 1.4 Maintenance and Support 1.4.1 Documentation The Documentation for the Elite evolution S612 contains the following:
section page 8 of 39 1.4.1.1 Documentation Guide Complete contents of the documentation package. It lists all the volumes and describes the content of each volume. 1.4.1.2 Operating Manuals Maintenance Operations Manual, includes a general description of the Elite evolution S612 and the major assemblies. Instructor s Operations Manual, describe the Simulator complex and provides checklists and descriptions to enable the instructor to set-up and operate the Simulator under normal and emergency conditions. 1.4.1.3 Maintenance Manuals and Associated Documents This volume contains information primarily concerning the Elite evolution S612 hardware including technical descriptions and instructions for operating and maintaining of this hardware. The documents will comprise the following: Maintenance Manual Vendor Data Test Procedures 1.4.1.4 Computer and Peripheral Manuals The manufacturer s manuals for the computers and peripherals, giving programming, operating and maintenance information, will be provided under this volume. 1.4.1.5 Range of Spares This document comprises a list of all spares, tools and test equipment recommended by the manufacturer for maintenance of the Elite evolution S612. This document will be supplied during the early stages of the contract. 1.4.2 Spare Parts 1.4.2.1 General All spares will be ordered at Elite evolution S612 order date. Manufacturer supports the Elite evolution S612 complex for five (5) years. In case of obsolescence of parts, the manufacturer will inform the customer in advance for the possibility of last buy. Also the manufacturer tries to find a substitute. 1.4.2.2 Elite evolution S612 Spare Parts A detailed and firm spare part quotation will be given for the Elite evolution S612 excluding the computer complex. For every type of power supply one spare unit will be kept. A sufficient number of mechanic and electromechanical parts that are required to support the Elite evolution S612 operation will be kept. 1.4.2.3 Computer Spare Parts Are kept by the manufacturer in-house. The customer will have a detailed description of the used computer components to provide a fast exchange if needed. 1.4.3 Tools and Test Equipment Tools and test programs are used by the manufacturer via remote access to the operator. It will be necessary that the operator is connected to an ISDN or faster modem in order to grant the accessibility of the system software to the manufacturer.
section page 9 of 39 1.4.4 Maintainability The Elite evolution S612 is designed with maintainability in mind. Every effort has been made to ensure that there is minimal need to disassemble equipment or to remove parts. Routing of wire bundles do not interfere with any part or assembly. The design of the Elite evolution S612 is in such that if required - all components are readily accessible for replacement and repair. 1.4.5 Standardization Standard Industry parts and assemblies are used to a high extent wherever it is applicable or practical. A high grade of common parts are used too. 1.4.6 Warranty The manufacturer will guarantee for 24 months after delivery that the equipment and any initial spare parts sold to the Customer will be free from defects in materials, workmanship and design under normal use and service.
section page 10 of 39 2 Description of flight deck 2.1 General The flight deck is designed to withstand normal loads, shocks and other conditions incidental to normal operation, transportation and assembly. The structure is sufficiently rigid to assure that there is no discernible movement of the Elite evolution S612 due to personnel movement or control movement within the flight deck. The area included in the simulation are from the rudder pedals to aft of the crew member seats. An open Instructor station is attached to the flight deck. The flight deck is enclosed and the front windows are fabricated from clear material for an undisturbed view to the optional visual scene. 2.1.1 Cockpit The interior of the flight deck is designed according to the aircraft specified above. Non-aircraft hardware such as switches and knobs are located in the correct location and provide the same general action. They are in a similar appearance as in the aircraft. 2.1.2 Aircraft Parts The Elite evolution S612 does not include original aircraft parts.
section page 11 of 39 2.1.3 Panel Layout 2.1.3.1 Overview MASTER BAT ALT MAGNETO L R Speed Turn/ Bank RMI GEN RESET ENG START AVIONICS MASTER AUX FUEL PUMP Annunciator panel Horizon HSI YOKE PITOT HEAT PARKING BRAKE Altitude VSI NAV2 DASHB. LIGHT BCN NAV TAXI MP Alt / VS Preselector Compass COMM 1 NAV 1 COMM 2 NAV 2 RPM ADF Fuel flow CHT EGT Oil temp & press Alt load Bus volt Cowl Flaps Flaps indic. Pitch / Rudder trim indicator Fuel Qty DME Transponder Autopilot LDG RUDDER TRIM LDG GEAR FLAPS SWITCH GEAR LIGHTS POWER UNIT VISUAL CONTROL STICK COWL FLAP OFF Elite evolution S611 BITD LEFT FUEL SELECTOR BOTH POWER RIGHT HOBBS METER TRANSMIT
section page 12 of 39 2.1.3.2 Pilot's Main Panel Name Type Implementation Airspeed Indicator generic for single engine A/C Elite Software Turn / Bank Indicator generic Elite Software Dual Needle RMI KNI 582 Elite Software Annunciator Panel Autopilot & Mkr Beacon Elite Software Artificial Horizon generic Elite Software HSI generic Elite Software Altimeter KEA 130 A Elite Software Vertical Speed Indicator generic for single engine A/C Elite Software CDI Nav 2 KI 209A Elite Software 2.1.3.3 Engine Instrument Panel
section page 13 of 39 MP Alt / VS Preselector Compass RPM Fuel flow CHT EGT Oil temp & press Alt load Bus volt Pitch / Rudder trim indicator Cowl Flaps Flaps indic. Fuel Qty TAXI LDG LDG GEAR SWITCH GEAR LIGHTS FLAPS Name Type Implementation Manifold Pressure generic single engine A/C Elite Software RPM generic single engine A/C Elite Software Fuel Flow gauge generic single engine A/C Elite Software CHT / EGT temperature gauge generic single engine A/C Elite Software Oil temperature & Oil pressure generic single engine A/C Elite Software Altitude & Vertical Speed preselector generic single engine A/C Elite Software Alt load & Bus volt indicator generic single engine A/C Elite Software Pitch & Rudder trim indicator generic single engine A/C Elite Software Compass generic Elite Software Cowl flaps & Flaps position indicator generic single engine A/C Elite Software Fuel quantity gauge generic single engine A/C Elite Software
section page 14 of 39 2.1.3.4 Avionics Panel / Nav Panel Nav/Comm1 Nav/Comm2 ADF DME Transponder Autopilot Image 1: Elite Avionics Rack
section page 15 of 39 NAV / COMM 1 NAV / COMM 2 ADF DME Transponder Autopilot Name Control Function Push buttons, turn knobs, display elements Push buttons, turn knobs, display elements Push buttons, turn knobs, display elements Slide switches, turn knobs, display elements Push button, turn knobs, display elements Push buttons, rocker switch (mom. up / mom. down, neutral), display elements 2.1.3.5 Power Quadrant and Switches Panel Functionality based on KX 165-25 Functionality based on KX 165-25 Functionality based on KR87, with BFO and ANT mode Functionality based on KN 62A, with remote and standalone frequency Functionality based on KT 70 Transponder unit Functionality based on KFC 150, MODES: FD-ALT-HDG-NAV-APR-BC MASTER BAT ALT GEN RESET AVIONICS MASTER PITOT HEAT left side MAGNETO L R ENG START AUX FUEL PUMP YOKE PARKING BRAKE DASHB. LIGHT BCN NAV TAXI LDG LDG GEAR SWITCH GEAR LIGHTS FLAPS POWER UNIT right side RUDDER TRIM COWL FLAP LEFT BOTH OFF RIGHT FUEL SELECTOR HOBBS METER POW ER TRANSMIT POWER UNIT
section page 16 of 39 Name Control Function Master Bat On / off switch Controls battery setting Master Alt On / off switch Controls alternator Gen reset On / off / momentary reset Controls gen reset Avionics Master On / off switch Controls avionics setting Pitot Heat On / off switch Controls pitot heat system Parking Brake Push button Brake on / off with the use of the pedal Dashboard light On / off switch Controls dashboard light setting Beacon light On / off switch Controls beacon light setting Nav light On / off switch Controls Nav light setting Taxi light On / off switch Controls taxi light setting Landing light On / off switch Controls Nav light setting Landing Gear Control Up / down switch Controls position of landing gear Gear lights Display elements Red / green / off landing gear status indication Flap Lever Momentary up / down switch Controls flaps settings Rudder Trim Forward / backward rotation Manual trim change the trim wheel does not rotate when using the electrical pitch trim on the yoke?? Cowl Flap Momentary open / OFF / momentary close Controls cowl flaps Fuel Selector Turn knob Off / L / Both / R Controls fuel supply Hobbs Meter Display elements???? Hours & Minutes Power light On / off switch Controls power light setting Transmit light On / off switch Controls transmit light setting 2.1.4 Primary Flight Controls The standard Elite evolution S612 yoke is based on a Beech Baron 58 design and features an electric pitch trim switch and flight director engage / disengage button. 2.2 Instrument Panel Technical Realization The technical solution will be realised using 2 TFT monitors (pilot primary and secondary instruments). The appearance to the flight crew is like in the aircraft. All instruments are displayed close to actual size. All buttons, controls and switches are located according to above (chapter 2.1.3) layout.
section page 17 of 39 2.3 Simulated Instruments All simulated instruments are basically operational as in the aircraft. Instrument face markings, including graduations, pointers, flags, etc. are reproduced as authentically as possible according to the actual aircraft instruments. Instrument functionality that requires hardware components that are not simulated is not implemented. All switches and knobs are operational and have a comparable feel as its original counterparts. Instrument response rates are equal to those found in the aircraft.
section page 18 of 39 3 Instructor Station 3.1 Instructor Station Features The main components of the instructor station are: 19 TFT Display Keyboard / mouse Printer The instructor s area is located for optimum crew station view and instructor station's interface within applicable physical constraints. The following controls are available via the instructor station: Emergency Stop Sounds Communication Master Reset System Reset Std. Atmosphere Reset External Power Engine Quick Start Visual Display (ON / OFF) Freeze (Total, Position) Reposition The instructor has access to the following pages, where he can edit the relevant parameters via keyboard or mouse input. Initial position Meteo pages Control page Visual control Map page (displays airports and facilities for quick selection) Navigation modification page Configuration page Malfunctions page
section page 19 of 39 3.2 Pages Overview 3.2.1 Initial Position At start-up the simulator is set to a predefined initial position. The instructor has the possibility to load self-created state files containing Aircraft loading, Cockpit Instrument settings, Weather conditions, Malfunctions and Aircraft position. 3.2.2 Meteo Pages The Meteorological conditions are controlled on 2 pages: The Meteo Wind and Turbulence page contains information concerning the atmospheric conditions in the simulated environment. Parameters such as temperature, pressure, wind speed and direction, air turbulence etc. are variable and the instructor has the possibility to modify these by inserting the desired values via the keyboard and / or mouse. The values can be specified for 3 layers in the atmosphere. ISA standard day parameters are default values. All conditions can be saved and stored within a time frame where changes occur. Variable limits are as follows: Temperature range -40C to +40C deviation from ISA temperature Sea level pressure 27.76 to 31.27 in./hg (also displays in HPA) Wind direction 0 to 359 Wind speed 0 to 60 knots Wind turbulence level 0 to 12 Image 2: Meteo wind and turbulence Page The Meteo Clouds and Visibility page allows modification of the visibility and cloud types on three separate layers and enables the instructor to create realistic weather situations. State files recording weather settings can be created at any time and reloaded when required.
section page 20 of 39 Image 3: Meteo clouds and visibility Page Actual Metar data can be downloaded from the internet and imported into the simulation for realistic representation of the weather settings. The positions of sun and moon are calculated from the current time and date of the simulation.
section page 21 of 39 Image 4: Metar Page Image 5: Control Page
section page 22 of 39 3.2.3 Control Page The control page allows date and time manipulation for realistic day to night transition and light environment. Visual detail settings can be changed from sparse to detailed - the optional RealView / GenView Visual features high resolution runways and taxiways and a complete approach light system including PAPI/VASI, EFAS and REIL systems. Aircraft load and usable fuel can be changed here as well. 3.2.4 MAP Page The instructor is able to select the runway or to reposition the aircraft to any desired map position. The map page contains all facilities and airports, based e. g. on Jeppesen Navigational Databases. On the map page the following information is visualized: Aircraft position (LAT/LONG) Aircraft heading Aircraft altitude Indicated airspeed Aircraft track Transponder code The navigational aids are displayed as symbols and their identifier are also visible on Screen. To prevent the map from becoming too cluttered, a feature to switch off selected types of navigation stations from the display is available to the instructor. The US victorairways can also be shown on the map. Included on the area map page the following instructor controllable functions are available: After the aircraft flies past the area map boundary, it will hold the previous selected map scale TRACK ERASE This clears the current track and will begin a new one SYMBOL DISPLAYS This feature will enable the instructor to blank out types of NAV AIDS (ILS, VOR, NDB, etc.) from the map INSTRUMENT DISPLAYS The instructor has a choice of miniaturized instruments to be displayed on the map screen to allow observation of the instrument readout during the training session or for debriefing purposes (replay function including the display of the instruments status) PROFILE VIEW When selected, the area map will additionally display aircraft speed, Flaps position, Gear position, Altitude and deviation to Glide Slope. The profile view is scalable The Profile view displays the ILS capture area and shows both vertical and horizontal track relative to the glide slope and localizer position. It shows the aircraft position in relationship to the selected ILS, clearly depicting glide slope deviation. Additionally, all associated marker beacons are displayed on both approach plans. The Flight Path Replay function allows powerful and sophisticated analysing of Pilot action during simulator flight for debriefing purposes. Information available in profile and extended (aircraft speed, gear and flap settings) view can be displayed on the map page. When approaching an ILS facility the deviation between the ideal and the actually flown path can be analysed at any zoom level half and one degree deflection is visualised on the profile
section page 23 of 39 section of the map page. In case of using the Simulator in combination with the optional external Visual System, the cross section of the underlying terrain is displayed at any position. The maximum recording time is 60 minutes. Print map, zoom functions, database load and state file save functions are standard map page features. Image 6: Map Page
section page 24 of 39 3.2.5 Navigation Modification Page The Navigation Modification Page enables the instructor to modify any facility and airport. Additional navigational aids can be defined by the instructor. This page can be password protected. Image 7: Navigation Modification Page
section page 25 of 39 3.2.6 Configuration Page The Configuration Page contains one time settings such as volume control, calibration of the three control axis, damping values for the control axis, UTC time settings. Aircraft specific data is displayed for reference (critical speeds etc.). Image 8: Configuration Page 3.2.7 Malfunctions Page Failures can occur immediately or within a specifiable time window. Random failures can be activated. The malfunction page displays all armed and failed instruments. The instructor is able to clear any malfunction individually and also clear all malfunctions with one input. 3.2.7.1 Individual Instrument Failures Attitude indicator HSI Altitude Vertical Speed Indicator Airspeed indicator Turn/bank coordinator 3.2.7.2 System Failures Vacuum pump Pitot freeze Electrical system Static system Pitot & drain freeze 3.2.7.3 Receiver Failures Nav1 receiver CDI / LOC / GS Nav2 receiver CDI / LOC / GS ADF receiver 3.2.7.4 Transponder Transponder 3.2.7.5 Gear / Flaps Gear ADF antenna Flaps
section page 26 of 39 3.2.7.6 Engines Engines power loss Oil temperature Oil pressure Cylinder temp. Image 9: Malfunctions Page 3.2.8 Aircraft-State Snapshot This will create a file with all aircraft related parameters such as aircraft position, attitude, instrument settings, failure settings, meteorological situation. This information can be reloaded for repeating lessons or recalled for debriefing purposes. 3.2.9 Communication System To enable communications between instructor and trainees. Hot mike communication within the cockpit crew is audible to the instructor. 3.2.10 Instructor Seat The instructor seat is placed in a position to allow close observation of the cockpit crew as well as aircraft state.
section page 27 of 39 4 Primary Flight Controls 4.1 General Description The spring loaded control system corresponds broadly to the control feeling for the aileron, elevator and rudder controls
section page 28 of 39 5 Computer System and Peripherals 5.1 Hardware The components of the Computer Hardware complies with the current industry standards. For later upgrades and / or modifications a certain amount of Spare Slots are available. Via a Keyboard and Monitor the system operator has access to the computer for operation and maintenance purpose. A printer is installed as hard copy device to print out instructor station pages. 5.2 Programming Language Standard high level programming languages C and C++ are used for implementation of the flight simulation software. 5.3 Maintenance Capabilities Tools for maintenance are available at the manufacturer s site and will allow, with remote access to the operator, immediate access. 5.4 System Spare Capacity The computer system has adequate spare capacity in both memory and processing time. The amount of spare memory will be at least 30%, the spare processing time for the Cockpit Instruments are at least 40%, for the Real View Visual at least 20%. 5.5 Diagnostic Incorporated in the design is a diagnostic system (software) to enable verification of the I/O device integrity as well as to identify and isolate faulty I/O channels.
section page 29 of 39 6 Description of Simulation 6.1 Aerodynamic and Performance The aerodynamic flight simulation will widely reproduce the flight characteristics of a single engine high performance aircraft. The simulation of the flight performance is based on an accurate mathematic model. Full consideration is given to all variable surfaces and their effects. Simulation does include: Variation of aircraft longitudinal, lateral and directional stability with altitude, airspeed and gross weight Stall characteristics Ground handling characteristics 6.1.1 Wind Effects The effect of wind from any direction, at speeds from zero to sixty knots is realistically simulated and controlled by the instructor. The wind does show the correct effect on the ground track display during in-flight operation of the Elite evolution S612. 6.1.2 Atmosphere Variation of temperature, pressure and density with altitude does follow the ISA standard model. 6.1.3 On Ground Handling Simulation does include turning effects due to rudders, brakes and nose wheel steering, representative flare and touch down effects. 6.1.4 Take-Off and Climb-Out With parking brake set and applied power, proper aircraft pitch effects are simulated. During take-off, heading control is accomplished via the use of nose wheel steering and/or rudder. 6.1.5 Stalls There is full representation of the approach to Stall and the recovery from it. Stall is simulated by cockpit instruments and associated flight characteristics. The influence of aircraft attitude, gross weight, configuration and altitude is also simulated. 6.1.6 Landing The following is simulated during the landing phase: Rate of descent versus speed, power setting and wind conditions Control approach response Stall speeds in the approach and landing configuration Ground roll and deceleration Ground effects (including wind effects) and air to ground transients are simulated to the best available data, representative of the in-ground effect characteristics of the actual flight.
section page 30 of 39 6.1.7 Instrument Responses Instrument responses to actual aircraft responses do reflect: Aircraft slip and rate of turn Rate of turn, as a function of bank angle and airspeed Attitude, altitude, rate of climb and trim changes with gear position and flap setting changes Pitch attitude, as a function of gross weight and airspeed 6.2 Radio Navigation Simulation 6.2.1 Radio Navigation Computation In order to execute the radio navigation simulation function, real world Navigation Databases are used. Periodical updates are available if necessary. Modification of existing and creation of new facilities is possible. 6.2.2 Ground Facility Data Worldwide based on Navigation Databases 6.3 Aircraft Systems Simulation 6.3.1 Electrical System Changing the status of electricity consumers in the cockpit (e. g. switching on / off avionics panel) are reflected in the consumption of electricity. Should the aircraft s electrical systems run on battery only without being constantly fed by the alternator, battery load will decrease. When running on standby generator only Nav1 and Comm1 will work. 6.3.2 Engine System The engine and the associated controls and indicators are simulated as described in the Aircraft data. The basis for the engine and aircraft model is a Beech Bonanza A36. Simulation of the power plants include engine start on the ground and in the air, normal- and emergency handling, acceleration, deceleration and shut down. Variations of the effects of altitude, airspeed and ambient temperature are included in the performance computations. Characteristics for the applicable engine and their effect on the flight path are reproduced in response to engine control selections. The engine monitoring system has the capability of depicting a realistic representation of engine operations. Propeller control and operation are realistically simulated. This includes full range of pitch control, feathering and propeller governing.
section page 31 of 39 6.3.3 Fuel System The aircraft fuel system is simulated in accordance with aircraft data. The effects of fuel depletion is simulated. Fuel quantity indicators are simulated from aircraft data. 6.3.4 Pitot Static System The aircraft pitot static system is simulated in accordance with aircraft data. 6.3.5 Landing Gear, Brakes and Nose Wheel Steering Systems The normal landing gear system controls, indicators and warning sounds are simulated according to the aircraft data. The simulated aircraft brake system has a realistic force feel and also represents asymmetrical brake functionality. Parking brake control is simulated. Nose wheel steering is simulated. Steering forces are felt by the pilot through the rudder pedals when using a spring loaded Control Loading unit. 6.3.6 Flight Control System The flight controls are installed for a one pilot (single yoke) operation in the cockpit and functions according to the available aircraft data. Realistic force feel and dynamic response is available through available aircraft data. The simulation of trim for elevator and rudder is provided. Trim position indicators are present for elevator and rudder and reflect system operation. The aircraft flaps operation is simulated and affects the aircraft s performance. Cockpit control and indication are functional. 6.4 Avionics / Radio System Simulation 6.4.1 General All avionics operate as they would in the actual Aircraft, except as explained in this section. Avionics operation is limited by the capabilities of the Elite evolution S612 navigation system. The avionics of the Elite evolution S612 include the following: NAV/COM Receivers (Bendix/King KX 165-25) ADF (Bendix/King KR 87) DME (Bendix/King KN 62A) Transponder (Bendix/King KT 70) Autopilot KFC 150 6.4.2 VHF Navigation / Communication System The KX 165-25 operates as in the actual Aircraft with the exception that the COMM part does only display the Frequency and has no effect on communication between Instructor and pilot. The Navigation part is simulated according to the approved Aircraft data. An ATIS System is installed.
section page 32 of 39 6.4.3 Transponder System The KT 70 Transponder is a unit with dials and functional lighting. The reply light illuminates when the IDENT button is pressed, after release of this button it extinguishes after approximately 10 seconds. 6.4.4 ADF System The ADF system is simulated according to the original KR 87 device. 6.4.5 DME System The DME system is simulated according to the original KN 62A device. 6.4.6 GPS System An optional GPS is available for the Elite evolution S612. 6.5 Flight Director / Autopilot System The Elite evolution S612 has a fully functional automatic flight control system, including autopilot and flight director, simulating the Bendix/King KFC 150. 6.6 Sound System The following sounds are simulated if audible in the cockpit of the Elite evolution S612: Engine, propeller Landing gear retraction and extension Flaps retraction and extension Touchdown bumps System sounds like Stall warning, indents etc. are present
section page 33 of 39 7 Visual System (optional) 7.1 Visual System Features The main components are: Image Generator (Software License and Computer) Projector and projection screen Visual Databases according to customer requirements The following cues are available: 7.1.1 Field of View Horizontal: up to 60 degrees per channel (recommended 45 degrees) Vertical: up to 40 degrees (recommended 30 degrees) 7.1.2 Airport Associated Lighting Facilities Approach lighting system Runway lighting system Taxiway lighting system VASI / PAPI lights Runway End Identification Lights (REIL) Strobe lights 7.1.3 Day to night transition The Visual features a realistic time and light condition simulation. Sun / Moon rise and set and changing ambient light are correctly represented based on an accurate astronomic model. 7.1.4 Clouds / Visibility Variable cloud layers and RVR settings possible, controllable via modifications on Meteo page. 7.1.5 Runway Features Runways are always dry with textures. 7.1.6 Real Airport Models Real Airport Models can be programmed through the manufacturer upon request.
section page 34 of 39 7.1.7 Satellite Image Technology Based on real digital satellite images the area around selected airports is visualized with geospecific textures. The images are physical measurements of the real environment covering large areas and reflect the land cover of a region. By using data of different sensors with different geometric properties (i. e. Landsat Thematic Mapper data with 25 m, SPOT 3 / 4 data with 10m or even Aerial Photographs with down to 60 cm geometric resolution) user s needs can be taken into account. The Customer can specify regions of interest for which detailed visual scenery information is required. 7.1.8 Digital Terrain Models Elevation data of global coverage is used for the terrain representation. If high accuracy is required the manufacturer will acquire elevation data with higher resolution respectively will locally densify the global model. The processed satellite images and elevation models are input to the Visualisation Engine. 7.1.9 Programming Languages used in RealView / GenView The Real View Visual is based on OpenGL. OpenGL ensures excellent image quality and the currently available video cards offer hardware accelerated fast rendering. The Visual is based on an object oriented framework of classes written in C++.
section page 35 of 39 8 Project Scheduling 8.1 Project Scheduling System A project scheduling system with the following features is maintained at the manufacturers site: Milestone Schedule Reviews Project Reports 8.2 Milestone Schedule A detailed Milestone Schedule will be discussed and implemented depending on customers demands and preferences. 8.3 Project Status Reviews These reviews are held on a regularly basis to ensure that the project is proceeding according to the approved specification. 8.4 Project Reports Inputs from Milestone Schedule Meetings and Design Reviews Meetings are used to generate Project Reports. A copy of these reports are sent to the customer.
section page 36 of 39 9 Installation 9.1 Site Layout The operator shall consider the following: access doors with at least 80 cm width and 2m height equipment requires an area of 3m x 4m x 2.3m (w x l x h) for 1-channel visual equipment requires an area of 4m x 4m x 2.4m (w x l x h) for 3-channel visual ISDN or cable modem Internet connection for remote access 9.2 Power The Customer shall provide 380 VAC / 50 HZ three phase power through an Europlug CEE type (32 A) 3 LNPE and related surge protection. The total electric power consumption for a S612 with one visual channel is max 3.0 kw (incl. 3-channel visual system) 9.3 Environmental Considerations Temperature: +10 C - +25 C (Monitor, Projector) Humidity: 20 % - 80 %, non-condensing Heat dissipation: STD without pilots/instructor 14000 Btu/hr The light environment of the STD room must be controllable is recommended to paint the entire simulator room (incl. ceiling) matt black if an external visual system is installed
section page 37 of 39 10 Acceptance Procedure 10.1 Acceptance Timing An on site acceptance is carried out by the Customer in accordance to a Qualification Test Guide and mission flights, which shall insure that the Elite evolution S612 meets the specified requirements. 10.2 Testing Procedure Elite evolution S612 evaluation during acceptance shall be accomplished only when the Elite evolution S612 is loaded with all deliverable object modules. A record of the load status must be kept at all times. All hard- or software changes incorporated at the time of acceptance will be properly documented.
section page 38 of 39 11 On-Device Training 11.1 Factory Training A training course for customer technical personnel in Elite evolution BITD S612 maintenance and operation as well as all software provided will be held on request by Flight Simulators UK. The training course covers the complete Elite evolution BITD S612 including the computer and peripherals. The training course is held our workshops land includes on the job training. A detailed training syllabus is provided and advance copies of the training notes are made available one month prior to start of training.
section page 39 of 39 12 Request for EASA CS-FSTD (A) qualification 12.1 EASA Certification The ELITE Evolution S612 BITD has received certification by a joint STD Evaluation Team. The STD fulfills the requirements of EASA CS-FSTD (A) and represents the class of aeroplanes as Twin Engine Piston and Single Engine Piston. Flight Simulators Limited Unit 3A Gilray Road Vinces road Industrial Estate Diss Norfolk. IP22 4EU www.flight-simulators.co.uk Tel: +44 1603 397334 Also At International Aviation Academy - Norwich