Functional Description. Elite Evolution S812 FNPT II EASA / FAA / CASA compliant

Transcription

1 Functional Description Elite Evolution S812 FNPT II EASA / FAA / CASA compliant Flight Simulators Limited Unit 3A Gilray Road Vinces road Industrial Estate Diss Norfolk. IP22 4EU Tel: Also At International Aviation Academy - Norwich

2 page 2 of 98 Table of Contents 1 Functional Description Summery General Scope General Configuration Cockpit Instructor Station Dynamic Control Loading External Visual System Computer System Maintenance and Support Documentation Documentation Guide Operating Manuals Maintenance Manuals and Associated Documents Computer and Peripheral Manuals Spare Parts General Elite Evolution S812 FNPT II Spare Parts Computer Spare Parts Tools and Test Equipment Maintainability Standardization Warranty Description of flight deck General Cockpit Aircraft Parts Common Elements Primary Flight Controls / Yoke Avionics Rack with Audiopanel Special Avionics Racks with GPS Common Elements CB10 Unit Emergency Gear Lever Center Console with Pitch trim wheel and emergency stop Specific Elements Twin Engine Aircraft Piper Seneca III Beech Baron B Beech Duchess Single Engine Aircraft Piper Arrow IV Cessna 172RG Beech Bonanza A Simulated Instruments Instructor Station... 44

3 page 3 of Instructor Station Features Pages Overview Initial Position Meteo Pages Control Page MAP Page Navigation Modification Page Configuration Page Malfunctions Page Individual Instrument Failures System Failures Receiver Failures Transponder Gear / Flaps Engines Aircraft-State Snapshot Communication System Instructor Seat Dynamic Control Loading (DCL) General Description Safety System Computer System and Peripherals Hardware Programming Language Maintenance Capabilities System Spare Capacity Diagnostic Description of Simulation Aerodynamic and Performance Wind Effects Atmosphere Ground Handling Take-Off and Climb-Out Stalls One Engine Inoperative Performance Landing Instrument Responses Radio Navigation Simulation Radio Navigation Computation Aircraft Systems Simulation Electrical System Engine System Fuel System Pitot Static System Landing Gear, Brakes and Nose Wheel Steering Systems Flight Control System...59

4 page 4 of Avionics / Radio System Simulation General Audio System VHF Navigation / Communication System Transponder System ADF System DME System GPS System Flight Director / Autopilot System Sound System Visual System One Channel Visual System Hardware Setup Three Channel Visual System Hardware Setup Visual Cues Field of View Airport Associated Lighting Facilities Day to night transition Clouds / Visibility Runway Features Real Airport Models Data and Technology Digital Terrain Models Standard Database GenView Optional Database RealView Programming languages used in RealView / GenView Optional 3D Airport insets Project Scheduling Project Scheduling System Milestone Schedule Project Status Reviews Project Reports Installation Site Layout Power Environmental Considerations Acceptance Procedure Acceptance Timing On-site Acceptance Testing Procedure Training Factory Training Acceptance by authorities Formal acceptance of Civil Aviation Authorities worldwide Screen shots & Pictures...74

5 page 5 of Seneca III Seneca III Single Pilot Seneca III Dual Baron Duchess Duchess with GPS Arrow IV Arrow IV with simulated GPS C172RG C172RG DG C172RG HSI with GPS Bonanza A Bonanza A36 DG Bonanza A36 HSI...94 Illustration Index Image 1: Yoke...11 Image 2: Elite Avionics Rack...12 Image 3: Pilot subpanel A / Nav/Audiopanel (Module 1)...13 Image 4: Garmin GNS Image 5: Apollo GPS...15 Image 6: Trimble GPS...15 Image 7: CB10 Unit...16 Image 8: Emergency Gear Lever...16 Image 9: Centre Console with Pitch trim wheel unit and emergency stop...17 Image 10: Emergency Stop...17 Image 11: Pilot subpanel A (Module 1)...18 Image 12: Pilot subpanel B (Module 2)...19 Image 13: Pilot subpanel A (Module 3)...19 Image 14: CB10 Unit Seneca III...20 Image 15: Alternate Air and Cowl flaps panel (Module 5)...21 Image 16: Rudder trim / Fuel selector panel (Module 7)...22 Image 17: Pilot subpanel A (Module 1)...23 Image 18: Pilot subpanel B (Module 2)...23 Image 19: Pilot Subpanel A (Module 3)...24 Image 20: CB10 Unit Baron Image 21: Rudder trim / Fuel selector panel (Module 7)...26 Image 22: Pilot subpanel A (Module 1)...27 Image 23: Pilot subpanel B (Module 2)...27 Image 24: Pilot Subpanel A (Module 3)...28 Image 25: Cowl flaps panel (Module 5)...29 Image 26: Aileron tab / Rudder tab panel (Module 7)...30 Image 27: Pilot subpanel A (Module 1)...31 Image 28: Pilot subpanel B (Module 2)...31 Image 29: Pilot subpanel A (Module 3)...32 Image 30: CB10 Unit Arrow IV...33 Image 31: Rudder trim / Fuel selector panel (Module 7)...34 Image 32: Pilot subpanel A (Module 1)...35

6 page 6 of 98 Image 33: Pilot subpanel B (Module 2)...35 Image 34: Pilot subpanel A (Module 3)...36 Image 35: Nose / Cowl flaps panel (Module 5)...38 Image 36: Fuel selector panel (Module 7)...39 Image 37: Pilot subpanel A (Module 1)...40 Image 38: Pilot subpanel B (Module 2)...40 Image 39: Pilot subpanel A (Module 3)...41 Image 40: CB10 Unit Bonanza A Image 41: Rudder trim / Fuel selector panel (Module 7)...43 Image 42: Meteo wind and turbulence Page...45 Image 43: Meteo clouds and visibility Page...48 Image 44: Metar Page...49 Image 45: Control Page...49 Image 46: Map Page...51 Image 47: Navigation modification Page...52 Image 48: Configuration Page...53 Image 49: Malfunctions Page...54 Image 50: Typical layout for single channel visual projection...62 Image 51: Typical layout for three channel visual projection...63 Image 52: Screen shot GenView (Central Switzerland)...66 Image 53: Screen shot RealView (Central Switzerland)...67 Image 54: Screen shot 3D Airport sample (Milano Malpensa Airport, Italy)...68 Image 55: Screen shot custom built 3D airport (Milano-Linate)...68 Image 56: Screen shot Pilot Seneca III Single Pilot...74 Image 57: Screen shot Engine instruments Seneca III Single Pilot...75 Image 58: Screen shot Pilot Seneca III Dual...76 Image 59: Screen shot Engine instruments Seneca III Dual...77 Image 60: Screen shot Pilot Baron Image 61: Screen shot Engine instruments Baron Image 62: Screen shot Pilot Duchess...80 Image 63: Screen shot Engine instruments Duchess...81 Image 64: Screen shot Pilot Duchess with GPS...82 Image 65: Screen shot Engine instruments Duchess with GPS...83 Image 66: Screen shot Pilot Arrow IV...84 Image 67: Screen shot Engine instruments Arrow IV...85 Image 68: Screen shot Pilot Arrow IV with simulated GPS...86 Image 69: Screen shot Engine instruments Arrow IV with simulated GPS...87 Image 70: Screen shot Pilot C172RG DG...88 Image 71: Screen shot Engine instruments C172RG DG...89 Image 72: Screen shot Pilot C172RG HSI with GPS...90 Image 73: Screen shot Engine instruments C172RG HSI with GPS...91 Image 74: Screen shot Pilot Bonanza A36 DG...92 Image 75: Screen shot Engine instruments Bonanza A36 DG...93 Image 76: Screen shot Pilot Bonanza A36 HSI...94 Image 77: Screen shot Engine instruments Bonanza A36 HSI...95 Image 78: Outside cockpit view with three channel external visual...96 Image 79: Panel view with multi-channel external visual (Seneca III)...97 Image 80: sample S812 FNPT II Cessna 172RG...98

7 page 7 of 98 1 Functional Description Summery 1.1 General This document presents a detailed procurement specification for an Elite Evolution S812 FNPT II, Flight and Navigation Procedures Training Device, meeting the requirements specified under EASA CS-FSTD (A). Definitions: a) Customer Name and Address b) Manufacturer Elite Simulation Solutions AG, Dübendorf, Switzerland c) Flight deck Cockpit environment replicating the simulated Aircraft and in which the STD-controls and switches will operate as in that Aircraft. It is sufficiently enclosed to exclude pilot and Instructor distraction and furnished with ergonomically positioned seats. d) Cockpit Instrument Panel replicating a generic twin engine Aircraft instrumentation. e) Functional - A three - dimensional reproduction or actual Aircraft part connected to system logic or Instructor controlled logics. f) Non-functional (dummy) - A three-dimensional reproduction or actual Aircraft part not connected to system logics. g) System logics - Limited simulated Aircraft systems operation, in accordance to meet the training requirements. h) Available Data - Aircraft design data, Pilot s Operating Handbook, Aircraft Maintenance manuals, Observations on ground and in the air. i) Flight Test Data - Data gathered by the Aircraft manufacturer and test flights carried out by the FNPT manufacturer. 1.2 Scope The Elite Evolution S812 FNPT II shall simulate normal conditions for ground operations (limited), take-off, in-flight manoeuvres including engine failure procedures, radio navigation, instrument approaches and landings. Actions by the pilot 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 S812 FNPT II consists of the following major sub assemblies: a) A Cockpit layout representative of a generic twin engine Aircraft b) An enclosed 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, area- and approach tracking is also part of this facility. c) A 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 Aircraft. d) A simulation computer system consisting of a state of the art Computer Hardware, complying to the current industry standard and simulation software.

8 page 8 of 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 restrictive (e. g. airworthiness) 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 FNPT delivery Instructor Station The Instructor Station, consisting of two 19 TFT Flat screens 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 Navigation area selection Simulated ATC communication with the Cockpit crew Selection of initial conditions FNPT & automatic QTG control page Visual setup page Dynamic Control Loading The independent, electromechanical dynamic control loading system provides the pilot with a precise, repeatable control force and natural control response. A safety system is implemented, to protect both the user and the hardware from equipment failures and human error External Visual System The standard one channel projection system provides a generic representation of the terrain and conforms to the EASA CS-FSTD (A) requirements for FNPT II. For more details refer to chapter 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. Elite uses standard Microsoft Windows based Operating Systems.

9 page 9 of Maintenance and Support Documentation The Documentation for the Elite Evolution S812 FNPT contains the following: Documentation Guide Complete contents of the documentation package. It lists all the volumes and describes the content of each volume Operating Manuals Maintenance Operations Manual, includes a general description of the Elite Evolution S812 FNPT II and the major assemblies. Instructor s Operations Manual, describe the Simulator complex and provides check-lists and descriptions to enable the Instructor to set-up and operate the Simulator under normal and emergency conditions Maintenance Manuals and Associated Documents This volume contains information primarily concerning the Elite Evolution S812 FNPT II 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 Computer and Peripheral Manuals The manufacturer s manuals for the computers and peripherals, giving operating and maintenance information, will be provided under this volume.

10 page 10 of Spare Parts General All spares will be ordered at Elite Evolution S812 FNPT II order date. manufacturer supports the Elite Evolution S812 FNPT II 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 Elite Evolution S812 FNPT II Spare Parts A detailed and firm spare part quotation will be given for the Elite Evolution S812 FNPT II 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 S812 FNPT II operation will be kept 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 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 training device is connected to the Internet (at least 128 kbit/sec required) in order to grant the accessibility of the system software to the manufacturer. The access to the system will only take place in close cooperation with the operator Maintainability The Elite Evolution S812 FNPT II 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 S812 FNPT II is in such that if required - all components are readily accessible for replacement and repair 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 Warranty The manufacturer will guarantee for twenty-four months after the installation 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. In case of replacing defective material, it is at the manufacturers discretion if an on site replacement through an Elite technician is needed or if an exchange of the defective material can be done by the customer. Shipping charges from the manufacturer to the customer are paid by the manufacturer during the warranty period. VAT and import taxes have to be carried by the customer. Shipping charges from the customer to the manufacturer are paid by the customer. In case of an on site replacement by the manufacturer, travel cost and accommodation to and from the customer will be carried by the customer.

11 page 11 of 98 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 S812 FNPT II due to personnel movement or control movement within the Flight Deck. The Flight Deck, including the Instructor Station, is enclosed. The front windows are fabricated from clear material for an undisturbed view to the visual scene Cockpit The interior of the Flight Deck is ergonomically designed to comfortably accommodate the trainee and the Instructor. 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. The technical solution is realised using two 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 layout Aircraft Parts Despite of the circuit breakers, the standard Elite Evolution S812 FNPT II does not include any original Aircraft parts (except where noted) Common Elements Primary Flight Controls / Yoke The standard Elite Evolution S812 FNPT II Yoke is based on a generic design and features an electric pitch trim switch and flight director engage / disengage button. The Yoke does not cover an A/P disconnect push button. The pitch trim wheel does not move when using the trim on the Yoke. A stop watch and chart holder is placed in the centre of the yoke. Image 1: Yoke

12 page 12 of Avionics Rack with Audiopanel NAV / COMM 1 NAV / COMM 2 ADF DME Image 2: Elite Avionics Rack 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 Functionality based on KX Functionality based on KX Functionality based on KR87, with BFO and ANT mode Functionality based on KN 62A, with remote and standalone frequency Transponder Push button, turn knobs, Functionality based on KT 70, OFF-

13 page 13 of 98 Autopilot Name Control Function display elements Push buttons, rocker switch (mom. up / down, neutral), display elements ON-ALT-TEST-IDENT Functionality based on KFC 150, MODES: FD-ALT-HDG-NAV-APR-BC Image 3: Pilot subpanel A / Nav/Audiopanel (Module 1) Name Control Function MKR test button Display elements Activates the marker lights for test purpose MKR Up / down switch Sets sensitivity for marker to high, low or test SPKR / Phone Up / down switch Redirects the COM-Sound output to headphones or speakers TX Display element Indication for push to talk button left trumb horn RX 1 / 2 Display elements Indication for received sound RMI PIL 1 /2 Up / down switch Selector switch for RMI RMI F / 0 1 / 2 Up / down switch Autopilot search switch AP1 / AP2 Up / down switch No Function / only MCC-Function COM1 Push button Turns communicator 1 COM2 Push button Turns communicator 2 NAV1 Push button Turns navigator 1 ident sound NAV2 Push button Turns navigator 2 ident sound MKR Push button Turns MKR ident sound DME Push button Turns DME ident sound ADF Push button Turns ADF ident sound AUX Push button Turns AUX MIC COM1 / COM2 Up / down switch Dummy switch

14 page 14 of Special Avionics Racks with GPS For RNAV the following GPS selection is available: GARMIN GNS 530 GPS Name Control Function Push buttons, turn knobs, display elements Original Garmin GNS 530 device GARMIN GNS 430 GPS Image 4: Garmin GNS 430 Name Control Function Push buttons, turn knobs, display elements Original Garmin GNS 430 device

15 page 15 of 98 Image 5: Apollo GPS Apollo GPS Name Control Function Push buttons, turn knob, display elements Functionality based on GX-50 to 65 Trimble GPS Image 6: Trimble GPS Name Control Function Push buttons, turn knob, display elements Functionality based on GX-50 to 65

16 page 16 of Common Elements CB10 Unit Image 7: CB10 Unit Emergency Gear Lever Image 8: Emergency Gear Lever

17 page 17 of Center Console with Pitch trim wheel and emergency stop Image 9: Centre Console with Pitch trim wheel unit and emergency stop Name Control Function Pitch trim wheel Up / down Only manual trim change the trim wheel does not rotate when using the electrical pitch trim on the yoke Pitch trim indication Deviation indication gauge LED for indication Image 10: Emergency Stop

18 page 18 of Specific Elements Twin Engine Aircraft Piper Seneca III Image 11: Pilot subpanel A (Module 1) Name Control Function Master switch On / off switch Master switch for cockpit L / R Alt On / off switch Left and right alternator switches Left / right magneto On / off switch Left and right magneto switches for left engine Start L / R Rocker switch Starts left or right engine L / R primer Push buttons Injects fuel left / right engine Left / right magneto On / off switch Left and right magneto switches for right engine Recog light On / off switch Controls recog light Park Brake Push button Activates / deactivates the park brake Landing light On / off switch Control landing light systems Nav lights On / off switch Controls nav lights AntCol light On / off switch Control anti-collision light switch Pitot heat On / off switch Controls pitot heat system Aux fuel switches On / off switch Controls auxiliary fuel pumps

19 page 19 of 98 Image 12: Pilot subpanel B (Module 2) Name Control Function Prop sync Up / down switch Controls prop synchrophaser Radio master On / off switch Controls power supply to radio system Ldg gear lever Up / down switch Controls position of landing gear Gear down indication lights Display elements Red / green / off landing gear status indication Flap lever Up / down switch Controls flap position Image 13: Pilot subpanel A (Module 3) Name Control Function - / + Deviation indication gauge Indicates offset between magnetic compass and unslaved HSI CCW / CW Momentary left / right switch Controls deviation between magnetic compass and HSI Free / Slave Up / down switch Controls slave / free mode for HSI Surface De-Ice On / off switch Controls surface de-ice Wing Ice Light On / off switch Controls wing ice light Wing tail De-Icers Indication LED Indicates de-icing of wing tails

20 page 20 of 98 Name Control Function Prop De-Ice On / off switch Controls prop de-ice system Amperes Ampere indication gauge Indicates ampere load for prop de-ice system Windshld Heat On / off switch Controls Windshield heating Image 14: CB10 Unit Seneca III Name Control Function COM / NAV 1 CB CB for COM / NAV 1 L ALT CB CB for left alternator COM / NAV 2 CB CB for COM / NAV 2

21 page 21 of 98 Name Control Function R ALT CB CB for right alternator DME CB CB for DME Gear CB CB for gear Autopilot CB CB for autopilot Flaps CB CB for flaps motor Fuel QTY CB CB for fuel qty Pitch TR CB CB for Pitch TR Image 15: Alternate Air and Cowl flaps panel (Module 5) Name Control Function Alt air left and right Open / closed levers Controls alt air Cowl flaps left and right Open / closed levers Controls for cowl flaps

22 page 22 of 98 Image 16: Rudder trim / Fuel selector panel (Module 7) Name Control Function Rudder trim knob Turn knob L / R Adjusts rudder trim position Left fuel engine On / off / x-feed lever Controls left fuel source Right fuel engine On / off / x-feed lever Controls right fuel source

23 page 23 of Beech Baron B58 Image 17: Pilot subpanel A (Module 1) Name Control Function Magnetos / Starter left engine Turn knob Off / R / L / Both / Start Magnetos / Starter right engine Turn knob Off / R / L / Both / Start Selector between magnetos and starter momentary position Selector between magnetos and starter momentary position Master BAT On / Off switch Controls master battery setting Master L ALT On / Off switch Controls left alternator Maser R ALT On / Off switch Controls right alternator Avionics master On / Off switch Controls avionics master Prop Sync On / Off switch Controls prop sync Park Brake Push button Activates / deactivates the park brake Pitot Heat On / Off switch Controls Pitot heat setting Prop De-Ice On / Off switch Controls prop de-ice setting Annun test Push button Pull for annunciator test Image 18: Pilot subpanel B (Module 2)

24 page 24 of 98 Name Control Function BCN On / Off switch Controls beacon light setting NAV On / Off switch Controls nav lights setting TAXI On / Off switch Controls taxi lights setting LDG On / Off switch Controls landing lights setting Cowl flap L On / Off switch Controls left cowl flaps setting Cowl flap R On / Off switch Controls right cowl flaps setting Fuel boost pump L On / Off switch Controls left fuel boost pump setting Fuel boost pump R On / Off switch Controls right fuel boost pump setting LDG Gear Up / down switch Controls landing gear position Gear down indication lights Display elements Red / green / off landing gear status indication Flaps Up / down switch Controls flaps position Image 19: Pilot Subpanel A (Module 3) Name Control Function - / + Deviation indication gauge Indicates offset between magnetic compass and unslaved HSI CCW / CW Momentary left / right switch Controls deviation between magnetic compass and HSI Free / Slave Up / down switch Controls slave / free mode for HSI Amperes Ampere indication gauge Indicates ampere load for prop de-ice system

25 page 25 of 98 Image 20: CB10 Unit Baron 58 Name Control Function COM / NAV 1 CB CB for COM / NAV 1 L ALT CB CB for left alternator COM / NAV 2 CB CB for COM / NAV 2 R ALT CB CB for right alternator DME CB CB for DME Gear CB CB for gear Autopilot CB CB for autopilot Flaps CB CB for flaps motor

26 page 26 of 98 Name Control Function Fuel QTY CB CB for fuel qty Pitch TR CB CB for Pitch TR Image 21: Rudder trim / Fuel selector panel (Module 7) Name Control Function Rudder trim knob Turn knob L / R Adjusts rudder trim position Left fuel engine On / off / x-feed lever Controls left fuel source Right fuel engine On / off / x-feed lever Controls right fuel source

27 page 27 of Beech Duchess 76 Image 22: Pilot subpanel A (Module 1) Name Control Function LALT On / off switch Controls left alternator BATT On / off switch Controls battery setting RALT On / off switch Controls right alternator Magnetos / Starter left engine Turn knob Off / R / L / Both / Start Magnetos / Starter right engine Turn knob Off / R / L / Both / Start Selector between magnetos and starter momentary position Selector between magnetos and starter momentary position LAND On / off switch Controls landing lights setting TAXI On / off switch Controls taxi lights setting NAV On / off switch Controls nav lights setting STROBE On / off switch Controls strobe lights setting Cabin Air Blower On / off switch Controls cabin air blower setting Pitot Heat On / off switch Controls Pitot heat system Elec Trimm On / off switch Controls electronic trim system Heater On / off switch Controls heater system Image 23: Pilot subpanel B (Module 2)

28 page 28 of 98 Name Control Function Aux fuel pump L On / off switch Controls left fuel pump setting Aux fuel pump R On / off switch Controls right fuel pump setting Ldg gear lever Up / down switch Controls position of landing gear Image 24: Pilot Subpanel A (Module 3) Name Control Function Park Brake Push button Activates / deactivates the park brake Flaps Up / down switch Controls flaps position Avionic Bus 1 Up / down switch Controls avionics bus 1 Avionic Bus 2 Up / down switch Controls avionics bus 2 CB10 Unit Duchess picture follows Name Control Function A1 CB CB for left engine gauges A2 CB CB for right engine gauges B1 CB CB for stall & gear warn horn B2 CB CB for flap motor C1 CB CB for flaps and gear ind C2 CB CB for LDG gear motor D1 CB CB for left avionics master D2 CB CB for right avionics master E1 CB CB for left alternator E2 CB CB for right alternator

29 page 29 of 98 Image 25: Cowl flaps panel (Module 5) Name Control Function Carb Heat On / off switch Controls carb heat Cowl Flap Open /closed switch Controls cowl flaps

30 page 30 of 98 Image 26: Aileron tab / Rudder tab panel (Module 7) Name Control Function Aileron tab Turn knob L / R Adjusts aileron tab position Rudder tab Turn knob L / R Adjusts rudder tab position

31 page 31 of Single Engine Aircraft Piper Arrow IV Image 27: Pilot subpanel A (Module 1) Name Control Function Magnetos / Starter left engine Turn knob Off / R / L / Both / Start Selector between magnetos and starter momentary position Master switch On / off switch Master switch for cockpit Alternator On / off switch Controls the alternator Fuel pump On / off switch Controls the fuel pump Radio master On / off switch Controls the radio master bus Park brake Push button Activates / deactivates the park brake Image 28: Pilot subpanel B (Module 2) Name Control Function NAV On / off switch Controls nav lights setting LAND On / off switch Controls landing lights setting Anti Coll Light On / off switch Controls anti coll light Pitot Heat On / off switch Controls pitot heat system LDG Gear Up / down switch Controls landing gear position

32 page 32 of 98 Name Control Function Gear down indication lights Display elements Red / green / off landing gear status indication Flaps Up / down switch Controls flaps position Image 29: Pilot subpanel A (Module 3) Name Control Function - / + Deviation indication gauge indicates offset between magnetic compass and unslaved HSI CCW / CW Momentary left / right switch Controls deviation between magnetic compass and HSI Free / Slave Up / down switch Controls slave / free mode for HSI

33 page 33 of 98 Image 30: CB10 Unit Arrow IV Name Control Function Pitch Trim CB CB for Pitch Trim COM / NAV 1 CB CB for COM / NAV 1 Fuel Pump CB CB for fuel pump COM / NAV 2 CB CB for COM / NAV 2 Gear CB CB for gear ADF CB CB for ADF Turn & Bank CB CB for turn and bank DME CB CB for DME Autopilot CB CB for autopilot

34 page 34 of 98 Name Control Function Transponder CB CB for transponder Image 31: Rudder trim / Fuel selector panel (Module 7) Name Control Function Rudder trim Turn knob L / R Adjusts rudder trim position ALT Air switch Up / down switch Controls supply of alternate air Fuel selector Turn knob Off / L / R Controls fuel supply

35 page 35 of Cessna 172RG Image 32: Pilot subpanel A (Module 1) Name Control Function Aux fuel pump On / Off switch Controls aux fuel pump setting ALT On / Off switch Controls alternator BAT On / Off switch Controls battery setting Primer Push button Injects fuel Magnetos / Starter left engine Turn knob Off / R / L / Both / Start Selector between magnetos and starter momentary position Park Brake Push button Activates / deactivates the park brake Image 33: Pilot subpanel B (Module 2) Name Control Function TAXI On / Off switch Controls taxi lights setting Land On / off switch Controls landing lights setting Gear Up / down switch Controls position of gear Carb heat Pull button Controls carb heat system Pitot Heat On / Off switch Controls pitot heat system Nav On / Off switch Controls nav lights setting BCN On / Off switch Controls beacon lights setting

36 page 36 of 98 Name Control Function Avionics On / Off switch Controls avionics setting Image 34: Pilot subpanel A (Module 3) Name Control Function Flaps Up / down switch Controls flaps position

37 page 37 of 98 Name Control Function COM / NAV 1 CB CB for COM / NAV 1 MDI CB CB for MDI COM / NAV 2 CB CB for COM / NAV 2 TBI CB CB for TBI DME CB CB for DME Gear CB CB for Gear Autopilot CB CB for Autopilot Flaps CB CB for Flaps Fuel QTY CB CB for fuel qty Pitch TR CB CB for pitch tr

38 page 38 of 98 Image 35: Nose / Cowl flaps panel (Module 5) Name Control Function Nose Turn knob L / R Controls nose position Cowl Flaps Up / down switch Controls cowl flaps

39 page 39 of 98 Image 36: Fuel selector panel (Module 7) Name Control Function Fuel Turn knob Off / L / Both / R Controls fuel supply

40 page 40 of Beech Bonanza A36 Image 37: Pilot subpanel A (Module 1) Name Control Function Magnetos / Starter left engine Turn knob Off / R / L / Both / Start Selector between magnetos and starter momentary position Master BAT On / off switch Controls battery setting Master ALT On / off switch Controls alternator Gen Reset On / off switch Controls gen reset Avionics Master On / off switch Controls avionics setting Pitot Heat On / off switch Controls pitot heat system Park Brake Push button Activates / deactivates the park brake Annun Test Push button Pull for annunciator test Aux Fuel Pump Hi / lo / off switch Controls auxiliary fuel pumps Image 38: Pilot subpanel B (Module 2) Name Control Function STRB On / off switch Controls strb lights setting BCN On / off switch Controls beacon lights setting NAV On / off switch Controls nav lights setting TAXI On / off switch Controls taxi lights setting

41 page 41 of 98 Name Control Function LDG On / off switch Controls landing lights setting LDG Gear Up / down switch Controls landing gear position Gear down indication lights Display elements Red / green / off landing gear status indication Flap Up / down switch Controls flap position Image 39: Pilot subpanel A (Module 3) Name Control Function - / + Deviation indication gauge indicates offset between magnetic compass and unslaved HSI CCW / CW Momentary left / right switch Controls deviation between magnetic compass and HSI Free / Slave Up / down switch Controls slave / free mode for HSI

42 page 42 of 98 Image 40: CB10 Unit Bonanza A36 Name Control Function COM / NAV 1 CB CB for COM / NAV 1 Alternator CB CB for alternator COM / NAV 2 CB CB for COM / NAV 2 Gear motor CB CB for gear motor DME CB CB for DME Gear lights CB CB for gear lights Autopilot CB CB for autopilot Flaps CB CB for flaps motor Fuel QTY CB CB for fuel qty Pitch TR CB CB for Pitch TR

43 page 43 of 98 Image 41: Rudder trim / Fuel selector panel (Module 7) 2.2 Simulated Instruments All simulated instruments are basically operational as in the Aircraft. Instrument face markings, including graduations, pointers and flags are reproduced as authentically as possible according to the actual Aircraft instruments. In some cases the manufacturer of original hardware equipment might provide a choice of different colours. As an example, the flight director can be either green or magenta. In such cases, Elite has chosen one of the listed colours.

44 page 44 of 98 3 Instructor Station 3.1 Instructor Station Features The main components of the Instructor Station are: Two 19 TFT Flat screens Keyboard / Mouse Printer The Instructor s area is located for optimum crew station view and Instructor s Station interface within applicable physical constrains. The following controls are available via the Instructor Station: Emergency Stop Sounds Communication Standard Atmosphere Reset External Power switches for Cockpit, Control Loading and Visual Freeze (total, position and fuel freeze) 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 Malfunction Page 3.2 Pages Overview 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 Meteo Pages The Meteorological conditions are controlled on 2 pages:

45 page 45 of 98 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 to in./hg (also displays in HPA) Wind Direction 0 to 359 Wind Speed 0 to 60 knots Wind turbulence level 0 to 12 Image 42: 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.

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48 page 48 of 98 Image 43: 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.

49 page 49 of 98 Image 44: Metar Page Image 45: Control Page

50 page 50 of 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. Aircraft load and usable fuel can be changed here as well 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 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 Victor- Airways 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 of the map page. In case of using the Simulator in combination with the optional

51 page 51 of 98 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 46: Map Page

52 page 52 of 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. Image 47: Navigation modification Page

53 page 53 of 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 48: Configuration Page 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 Individual Instrument Failures Attitude Indicator HSI Altitude Vertical Speed Indicator Airspeed Indicator Turn/bank coordinator System Failures Vacuum pump Pitot freeze Electrical system Receiver Failures Nav1 receiver GS Nav2 receiver GS ADF receiver Static system Pitot & drain freeze CDI/LOC CDI/LOC ADF antenna

54 page 54 of Transponder Transponder Gear / Flaps Gear Engines Engines power loss Oil temperature Flaps Oil pressure Cylinder temp. Image 49: Malfunctions Page 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 Communication System To enable communications between Instructor and trainees. Hot mike communication within the Cockpit crew is audible to the Instructor Instructor Seat The Instructor seat is placed in a position to allow close observation of the Cockpit crew as well as Aircraft state.

55 section page 55 of 98 4 Dynamic Control Loading (DCL) 4.1 General Description The electromechanical DCL gives the pilot a realistic control feeling for the aileron & elevator controls. The control loading system is controlled via the host computer, so that the pressure on the yoke controls will be automatically adjusted in accordance to: Flight control position Flight control trim setting Bank angle Aircraft in flight or on the ground Autopilot inputs Airspeed Due to the revolutionary modular build concept of Elite's dynamic control loading system, the customer has the ability to upgrade from a single pilot device to a dual pilot device at a later stage. The upgrade can be done on-site at customers premises. 4.2 Safety System A safety system is incorporated to protect both the user and the Elite Evolution S812 FNPT II from the hazards of in proper operation, equipment failure or power failure. However, the customer shall under no circumstances manipulate control load settings as this might result in a complete damage of the control loading unit.

56 section page 56 of 98 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 optional RealView and standard GenView 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.

57 section page 57 of 98 6 Description of Simulation 6.1 Aerodynamic and Performance The aerodynamic flight simulation will widely reproduce the flight characteristics of a twin engine Aircraft. The simulation of the flight performance is based on an accurate mathematics 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 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 S812 FNPT II Atmosphere Variation of temperature, pressure and density with altitude does follow the ISA standard model Ground Handling Simulation does include turning effects due to rudders, brakes and nose wheel steering 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 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 One Engine Inoperative Performance Representation of 1-Engine in op. characteristics and performance are implemented 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

58 section page 58 of 98 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 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 speed gear position and flap setting changes Pitch attitude, as a function of gross weight and airspeed 6.2 Radio Navigation Simulation 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 are done using the modification page. Elite is updating on a regular basis the Navigation Database. However, the manufacturer cannot assure, that on the date of delivery, the Navigation Database is current. In case of an obsolete Navigation Database, the operator is asked to modify the facilities using Elite s modification page. Alternatively, Elite can upload current Navigation data via remote access to the customers FNPT II device. 6.3 Aircraft Systems Simulation 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 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 Piper Seneca III. 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.

59 section page 59 of Fuel System The Aircraft fuel system is simulated in accordance with Aircraft data. The effects of fuel use is simulated. Fuel quantity indicators are simulated from Aircraft data Pitot Static System The Aircraft pitot static system is simulated in accordance with Aircraft data 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 is functional. Parking brake control is simulated. Nose wheel steering is simulated Flight Control System The flight controls are installed for a single Pilot operation in the Cockpit and correspond according to the available Aircraft data. Realistic force feel & dynamic response on the yoke is achieved from Aircraft data. The simulation of trim for elevator, rudder and aileron is provided. Trim position indicators Software and Hardware are present for elevator and rudder and reflect system operation. The Aircraft flaps operation is simulated and affects the Aircraft s performance. 6.4 Avionics / Radio System Simulation 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 S812 navigation system. The avionics of the Elite evolution S812 FNPT II include the following: Audio Control Console / Intercom NAV/COM Receivers (Bendix/King KX ) ADF (Bendix/King KR 87) DME (Bendix/King KN 62A) Transponder (Bendix/King KT 70) Autopilot KFC 150 Apollo GPS GX50, GX55, GX60 and GX65 or Trimble 2000 Approach Plus or optionally Garmin GNS430 original manufacturer hardware or optionally Garmin GNS530 original manufacturer hardware

60 section page 60 of Audio System The audio control system simulates NAV, COMM, ADF, Marker audio and Intercom. All above mentioned Instruments (6.4.1) which produce sounds such as Ident or marker sounds are audible through the loudspeakers and through the headphones VHF Navigation / Communication System The KX 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 Transponder System The Transponder is simulated according to the original KT 70 device ADF System The ADF system is simulated according to the original KR 87 device DME System The DME system is simulated according to the original KN 62A device GPS System An Apollo GPS GX50, GX55, GX60 and GX65 or a Trimble 2000 Approach Plus is implemented in the Elite Evolution S812 FNPT II. Optionally a Garmin GNS430 or GNS530 using original Garmin Hardware is available. The type of GPS hast to be selected by the customer at order date. 6.5 Flight Director / Autopilot System The Elite Evolution S812 FNPT II has a fully functional automatic flight control system, including autopilot and flight director, simulating the Bendix/King KFC Sound System The following sounds are simulated if audible in the Cockpit of the Elite Evolution S812 FNPT II: Engine, propeller Landing gear retraction and extension Flaps retraction and extension Touchdown bumps System sounds like Stall warning, idents etc. are present ATIS Above mentioned sounds are audible through the loudspeakers or through the headphones.

61 section page 61 of 98 7 Visual System 7.1 One Channel Visual System The main components are: Image Generator (Software License and Computer) projector and projection screen Visual Databases according to customer requirements Hardware Setup The standard Hardware set up for a single channel Visual system consists of a projector with a front projection screen.

62 section page 62 of 98 Image 50: Typical layout for single channel visual projection 7.2 Three Channel Visual System The main components are: Image Generators (Software License and Computer) projectors and projection screens Visual Databases according to customer requirements Hardware Setup The standard Hardware set up for a three channel Visual system consists of 3 projectors with front projection screens. The following space is required for a standard installation (top view):

63 section page 63 of 98 Image 51: Typical layout for three channel visual projection

64 section page 64 of Visual Cues Field of View Horizontal: 45 degrees per channel Vertical: 35 degrees per channel Airport Associated Lighting Facilities Approach lighting system Runway lighting system Taxiway lighting system VASI / PAPI lights Runway End Identification Lights (REIL) Strobe lights 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 Clouds / Visibility Variable cloud layers and RVR settings possible, controllable via modifications on Meteo page Runway Features Runways are always dry with textures Real Airport Models Real 3D Airport Models can be programmed through the manufacturer upon request.

65 section page 65 of Data and Technology Digital Terrain Models Elevation data of global coverage, based on a 1 km resolution grid, is used for the terrain representation. Based on this data, elevations may differ from actual values due to interpolation effects. Airport elevation for the 5 airports selected as main training fields will be within +/- 50 ft of ARP elevation. If higher accuracy is required, the manufacturer will acquire elevation data with higher resolution and will locally densify the global model. As like with RealView the customer shall specify his training requirements. Please contact us to discuss further details Standard Database GenView GenView displays the landscape based on generic textures. Geographic features such as lakes, rivers, urban areas, railroads or streets are represented using vector data. The runway environment consists of approach lights, center line lights, edge lights, PAPI / VASI according to Nav Data specifications. Due to the high amount of above mentioned facilities in each database, the position of the taxiways as well as the lighting of the taxiways (green for center line, blue for edge lights) are drawn generically.

66 section page 66 of 98 Image 52: Screen shot GenView (Central Switzerland)

67 section page 67 of Optional Database RealView The RealView External Visual System is based on the ViRGIS project (Virtual Reality Geographic Information System) by the Federal Institute of Technology Zurich. The aim of ViRGIS is the real-time visualisation of large geographic datasets. Accordingly, RealView External Visual System creates a realistic model of the geographic scenery by utilising digital elevation models and satellite images as geospecific textures. By using data of different sensors with different geometric properties (i. e. Landsat Thematic Mapper data with 25 m, SPOT 3 / 4 data with 10 m or even Aerial Photographs with down to 1 m geometric resolution) user s needs can be taken into account. A complex level of detail concept is required to cope with the large amounts of data required for this approach. Both the terrain model and the satellite textures are adapted to achieve the best image quality without compromising excellent system performance. Image 53: Screen shot RealView (Central Switzerland) RealView is available as an option to all FNPT Training Devices and require specifications from the customer such as coverage or level of detail. Please contact an Elite Sales representative to discuss your needs 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++.

68 March 2014 Elite evolution S812 FNPT II Flight Simulators Limited - UK section page 68 of 98 version Optional 3D Airport insets The customer has the option to add 3D Airport environments to RealView sceneries. Typically a custom built 3D Airport environment add-on would cover the following: 7 x 7 km square coverage based on 60cm ultra-high resolution aerial photography accurate depiction of all buildings within the airport perimeter Taxiway lighting VASI / PAPI lights Runway End Identification Lights (REIL) Strobe lights Taxiway markings Image 54: Screen shot 3D Airport sample (Milano Malpensa Airport, Italy) Image 55: Screen shot custom built 3D airport (Milano-Linate)

69 section page 69 of 98 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.

70 section page 70 of 98 9 Installation 9.1 Site Layout The operator shall consider the following: access doors with at least 85 cm width and 2m height sufficiently wide access corridors. Preferably you can provide a plan copy of the room and the access to the room to evaluate whether the material can be carried into room. the Elite Evolution S812 FNPT II Mock up with instructor station enclosure size is 2.50 m x 4.25 m x 2.40 m (w x l x h) and includes a mounting unit for the visual projection system and a visual projection canvas. DSL or better internet connection for remote access Minimum required room space is 3.5 m x 5.0 m x 2.5 m (w x l x h) please note that a multi-channel Visual set up requires more space. 9.2 Power The Elite Evolution S812 FNPT II complex will operate on 110 / 230 V / 50 Hz electric power. All interfacing equipment (transformers, inverters, etc.) will be provided by the manufacturer. 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 an S812 FNPT II with one visual channel is about 8 to maximally 10 kw and consists of the following main components: Control Loading Unit ~4 kw Visual System ~1 kw (one channel) Simulator ~2.5 kw 9.3 Environmental Considerations Operating Temperature: +10 C C (Monitor, Projector) Humidity: 20 % - 80 %, non-condensing Heat dissipation: STD without pilots/instructor Btu/hr The light environment of the FNPT II room must be controllable

71 section page 71 of Acceptance Procedure 10.1 Acceptance Timing A factory acceptance must be carried out with the customer in accordance with the Qualification Test Guide and mission flights, which ensure that the Elite Evolution S812 FNPT II meets the specified requirements On-site Acceptance An on-site final acceptance will be carried out by Elite and the customer to verify the agreed specifications and to assure the full functionality carried out during the factory acceptance Testing Procedure The Elite Evolution S812 FNPT II evaluation during acceptance shall be accomplished only when the Elite Evolution S812 FNPT II is equipped 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.

72 section page 72 of Training 11.1 Factory Training A training course for the customers designated technical personnel on the Elite Evolution S812 FNPT II maintenance and operation as well as all software provided will be held by the manufacturer. The training course covers the complete Elite Evolution S812 FNPT II including the computer and peripherals. The training course is held at the manufacturers location and includes on the job training. The course duration is estimated to be one day (1 working day). Ideally, the training course is held shortly before the Elite Evolution S812 FNPT II shipping date, e. g. in connection with the factory acceptance. An additional training course for Flight Instructors is also held at the manufacturers location, following the factory acceptance. This training course covers all aspects on the daily use of the S812 FNPT II including the use of the automatic QTG software to enable the customer to do his own QTG tests if required.

73 section page 73 of Acceptance by authorities 12.1 Formal acceptance of Civil Aviation Authorities worldwide Switzerland Great Britain Germany Netherlands Serbia Poland Spain France Belgium Norway Sweden Italy Ireland USA Canada South Africa Austria Croatia Hungary Slovakia Bulgaria Greece Turkey Denmark India New Zealand Australia Brazil Mexico Israel Slovenia U.A.E.

74 section page 74 of Screen shots & Pictures 13.1 Seneca III Seneca III Single Pilot Image 56: Screen shot Pilot Seneca III Single Pilot

75 section page 75 of 98 Image 57: Screen shot Engine instruments Seneca III Single Pilot

76 section page 76 of Seneca III Dual Image 58: Screen shot Pilot Seneca III Dual

77 section page 77 of 98 Image 59: Screen shot Engine instruments Seneca III Dual

78 section page 78 of Baron 58 Image 60: Screen shot Pilot Baron 58

79 section page 79 of 98 Image 61: Screen shot Engine instruments Baron 58

80 section page 80 of Duchess Image 62: Screen shot Pilot Duchess

81 section page 81 of 98 Image 63: Screen shot Engine instruments Duchess

82 section page 82 of Duchess with GPS Image 64: Screen shot Pilot Duchess with GPS

83 section page 83 of 98 Image 65: Screen shot Engine instruments Duchess with GPS

84 section page 84 of Arrow IV Image 66: Screen shot Pilot Arrow IV

85 section page 85 of 98 Image 67: Screen shot Engine instruments Arrow IV

86 section page 86 of Arrow IV with simulated GPS Image 68: Screen shot Pilot Arrow IV with simulated GPS

87 section page 87 of 98 Image 69: Screen shot Engine instruments Arrow IV with simulated GPS

88 section page 88 of C172RG C172RG DG Image 70: Screen shot Pilot C172RG DG

89 section page 89 of 98 Image 71: Screen shot Engine instruments C172RG DG

90 section page 90 of C172RG HSI with GPS Image 72: Screen shot Pilot C172RG HSI with GPS

91 section page 91 of 98 Image 73: Screen shot Engine instruments C172RG HSI with GPS

92 section page 92 of Bonanza A Bonanza A36 DG Image 74: Screen shot Pilot Bonanza A36 DG

93 section page 93 of 98 Image 75: Screen shot Engine instruments Bonanza A36 DG

94 section page 94 of Bonanza A36 HSI Image 76: Screen shot Pilot Bonanza A36 HSI

95 section page 95 of 98 Image 77: Screen shot Engine instruments Bonanza A36 HSI

96 section page 96 of 98 Image 78: Outside cockpit view with three channel external visual

97 section page 97 of 98 Image 79: Panel view with multi-channel external visual (Seneca III)

98 section page 98 of 98 Image 80: sample S812 FNPT II Cessna 172RG Flight Simulators Limited Unit 3A Gilray Road Vinces Road Industrial Estate Diss Norfolk. IP22 4EU United Kingdom Tel: Also located at: International Aviation Academy - Norwich