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Elite Simulation S623T Operator's Manual

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OPERATORS MANUAL
ELITE MODEL S623T HELICOPTER
1997 - 2013, Elite Simulation Solutions AG, all rights reserved

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  • Page 1 OPERATORS MANUAL ELITE MODEL S623T HELICOPTER 1997 - 2013, Elite Simulation Solutions AG, all rights reserved...

  • Page 2: Table Of Contents

    Table of Contents SECTION 1 TECHNICAL DESCRIPTION SUMMARY..................5 1.1 General..............................5 1.2 Scope...............................5 1.3 General Confi guration..........................6 1.3.1 Cockpit..............................6 1.3.2 Instructor Station..........................7 1.3.3 Computer System..........................7 1.4 Maintenance and Support........................8 1.4.1 Documentation..........................8 1.4.1.1 Operating Manuals............................8 1.4.1.2 Maintenance Manuals and Associated Documents..................8 1.4.1.3 Computer and Peripheral Manuals......................8 1.4.1.4 Range of Spares............................8 1.4.2 Spare Parts............................8 1.4.3 Computer Spare Parts........................8...
  • Page 3 2.1.3 Instrument Panel T echnical Realization..................10 2.1.4 Simulated Instruments........................10 2.2 Standard Cockpit Panel Layout......................11 2.2.1 Overview Instrumentslayout......................11 2.2.2 Pilot’s Main Panel...........................12 2.2.3 Co-Pilot’s Main Panel........................13 2.2.4 Engine Instrument Panel.........................14 2.3 Avionics Panel / Nav Panel (various layouts available)..............15 2.4 Overhead Panel.............................16 2.4.1 Implementation..........................17 2.4.2 General............................17 2.4.3 Aft Control Panel..........................17...
  • Page 4 3.1 Instructor Operating Station (IOS) Features..................33 3.2 Software Pages Overview........................34 3.2.1 Initial Position..........................34 3.2.2 Meteo Pages...........................34 3.2.3 Control Page...........................36 3.2.4 MAP Page............................37 3.2.5 Navigation Modifi cation Page......................39 3.2.6 Confi guration Page.........................40 3.2.7 Malfunctions Page..........................41 3.2.7.1 Instrument and System failures.........................42 3.2.8 Helicopter-State Snapshot......................43 3.2.9 Communication System........................43 3.2.10 Instructor Seat..........................43 SECTION 4 COMPUTER SYSTEM AND PERIPHALS..................44...
  • Page 5 5.1.4 Landing............................45 5.1.5 Instrument Responses........................46 5.2 Radio Navigation Simulation.......................46 5.2.1 Radio Navigation Computation.......................46 5.2.2 Visual Database..........................46 5.3 Aircraft Systems Simulation........................48 5.3.1 Electrical System..........................48 5.3.2 Engine System..........................48 5.3.3 Fuel System............................48 5.3.4 Steering............................48 5.3.5 Flight Control System........................48 5.4 Avionics and Radio System Simulation....................49 5.4.1 General............................49 5.4.2 Audio System..........................49 5.4.3 VHF Navigation / Communication System..................49...
  • Page 6 6.1.2 Airport Associated Lighting Facilities....................58 6.1.3 Day to Night Transition........................58 6.1.4 Clouds / Visibility..........................58 6.1.5 Runway Features..........................58 6.1.6 Real Airport Models.........................58 6.1.7 3D Objects (available optionally)....................59 6.1.8 Digital T errain Models........................62 6.1.9 Programming Languages used in RealView™ / GenView™............62 SECTION 7 INSTALLATION..........................63 7.1 Site Layout............................63 7.2 Power..............................63 7.3 Temperature Sensors...........................63...

  • Page 7: Section 1 Technical Description Summary

    General This document presents a detailed procurement specifi cation for an Advanced Aviation Training Device Evolution S623T , helicopter twin engine turbine, meeting all standards and performance criteria for qualifi cation as outlined under FAA AC 61-136 (Advanced ATD) regulations.

  • Page 8: Scope

    Scope The Evolution S623T helicopter equipment shall simulate take-off, hovering, in-fl ight maneu- vers, radio navigation, instrument approaches and landings on Helicopter pads, rooftops, oil rigs, ships and other specifi c areas. Actions by the crew on the simulated controls in the fl ight compartment shall interact with the simulated system logics and dependencies in accordance with this specifi...

  • Page 9: Instructor Station

    1.3.2 Instructor Station The instructor station provides access to the following functions: Helicopter Status Freeze selection Repositioning 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 1.3.3 Computer System The computer system consists of the current industry standard PC for both Software and...

  • Page 10: Maintenance And Support

    The manufacturer will try to fi nd a suitable substitute. A detailed and fi rm spare part quotation can be given for the Evolution S623T helicopter ex- cluding the computer system.

  • Page 12: Tools And Test Equipment

    Routing of wire bundles do not interfere with any part or assembly. The design of the Evolution S623T heli- copter is in such that, if required, all components are readily accessible for replacement and repair.

  • Page 13: Section 2 Flight Deck

    The fl ight deck is designed to withstand normal loads, shocks and other conditions incidental to normal operation, transportation and assembly. The structure is suffi ciently rigid to assure that there is no discernible movement of the Evolution S623T helicopter due to personnel movement or control movement within the fl ight deck.

  • Page 14: Standard Cockpit Panel Layout

    Standard Cockpit Panel Layout 2.2.1 Overview Instruments Layout Copilot (EFIS version) Engine Pilot (EFIS version) 2.2.2 Pilot’s Main Panel...
  • Page 15 Airspeed Indicator Generic for twin engine turbine helicopter Altitude Indicator Generic for twin engine turbine helicopter Dual Needle RMI KNI 582 HSI or EFIS Generic or EFIS EFS 40 GSP Annunciator Panel Generic Rotor RPM and NF1/2 Generic for twin engine turbine helicopter Vertical Speed Indicator Generic for twin engine turbine helicopter (Instantaneous type for IFR helicop- ters in Australia)

  • Page 16: Co-Pilot's Main Panel

    2.2.3 Co-Pilot’s Main Panel Airspeed Indicator Generic for twin engine turbine helicopter Altitude Indicator Generic for twin engine turbine helicopter Dual Needle RMI KNI 582 HSI or EFIS Generic or EFIS EFS 40 Rotor RPM Generic for twin engine turbine helicopter Generic for twin engine turbine helicopter (Instantaneous type for IFR helicopters in Australia) Vertical Speed Indicator...

  • Page 17: Engine Instrument Panel

    2.2.4 Engine Instrument Panel Left engine fuel gauge Generic for twin engine turbine Right engine fuel gauge Generic for twin engine turbine Left engine fuel pressure gauge Generic for twin engine turbine Right engine fuel pressure gauge Generic for twin engine turbine Left engine oil pressure gauge Generic for twin engine turbine Right engine oil pressure gauge...
  • Page 18 Avionics Panel / Nav Panel (various layouts & options available) Trimble GPS 2000 Approach + Garmin GNS 430* (when installed NAV1 COMM1 is omitted) autopilot KFC 150 Audio Panel NAV1 / COMM1 KX 165-25 NAV2 / COMM2 KX 165-25 EFIS EFS 40/50 EFIS EFS 40/50 DME KN 62A Transponder KT 70...

  • Page 20: Overhead Panel

    Overhead Panel...

  • Page 21: Implementation

    2.4.1 Implementation The overhead panels are divided in Aft Control Panel, Fwd Control Panel and Control Quad- rant. This section describes the hardware implementation of the several overhead panel ele- ments. 2.4.2 General All buttons are background lit. Light intensity can be controlled with OP_ACDC_3, which is imple- mented on the “AC-DC Gauge Selector Panel”...

  • Page 22: Aft Control Panel, Left Side, Panel 1

    2.4.3.1 Aft Control Panel, left side, Panel 1 The following switches are implemented: Switch ID Type Label OP_AFTL_2 Pushbutton PITCH TRIM ACTUATOR OP_AFTL_3 Pushbutton TRIM RELEASE OP_AFTL_5 Pushbutton ROLL TRIM ACTUATOR OP_AFTL_6 Pushbutton CRANK LH ENG OP_AFTL_7 Pushbutton FIRE EXT No1 OP_AFTL_10 Pushbutton FIRE EXT No2...
  • Page 23 Layout Aft Left Side – Switch panel 1...

  • Page 24: Aft Control Panel, Right Side, Panel 4

    2.4.3.2 Aft Control Panel, right side, Panel 4 The following switches are implemented: Switch ID Type Label Backgrou Remarks nd Color OP_AFTR_3 Pushbut- FUEL INTERC black Double light intensity if valve is opened OP_AFTR_6 Pushbut- CRANK RH ENG black OP_AFTR_7 Pushbut- FIRE EXT No1 OP_AFTR_10...
  • Page 25 Layout, Aft Right Side – Switch panel 4...

  • Page 26: Fwd Control Panel

    2.4.4 Fwd Control Panel 2.4.4.1 Fwd Control Panel, left side, Panel 2 Fwd Control Panel, left side, original layout Switch ID Type Label Background Color OP_FWDL_3 Pushbutton INVERT LH black OP_FWDL_4 Pushbutton GEN LH black OP_FWDL_5 Pushbutton LH B.P . black OP_FWDL_6 Pushbutton...
  • Page 27 Layout, FWD Left Side – Switch panel 2 The following buttons are not implemented and are covered with blanks: 1,2 In addition the following gauge has been implemented: Gauge ID Type OP_FWDL_G1 Pointer gauge AC Voltmeter...

  • Page 28: Fwd Control Panel, Right Side, Panel 3

    2.4.4.2 Fwd Control Panel, right side, Panel 3 Fwd Control Panel, right side, original layout The following switches are implemented, options are marked: Switch ID Type Label Background Remarks Color OP_FWDR_1 Pushbutton RH EXT PWR black BATT OP_FWDR_2 Pushbutton RH B.P . black OP_FWDR_3 Pushbutton...
  • Page 29 Layout, FWD Right Side – Switch panel 3 The following buttons are not implemented and might be covered with blinds: 5,6 In addition the following gauges have to be implemented: Fwd Control, right side gauges, OP_FWDR_G1 and OP_FWDR_G2 Gauge ID Type OP_FWDR_G1 Pointer gauge...
  • Page 30 TRIM RELEASE PITCH TRIM TRIM RELEASE ACTUATOR FIRE EXT PITCH No 1 TRIM FIRE EXT ROLL CRANK ACTUATOR No 1 TRIM ACTUATOR ENGINE FIRE EXT FIRE EXT STROBE No 2 No 1 FIRE EXT No 2 CONSOLE COPILOT WIPER COPILOT FIRE EXT WIPER No 2...

  • Page 31: Ac-Dc Gauge Selector Panel

    2.4.5 AC-DC Gauge Selector Panel Switch ID Type Label Remarks OP_ACDC_1 5 Position turn U 26V~LH U 115V~LH knob <no label> U 26V~RH U 115V~RH OP_ACDC_2 5 Position turn knob V ESS RH V SHED I.GENE LH RH OP_ACDC_3 Turn knob LIGHTING SWITCHES PANELS Layout, AC-DC Gauge Selector Panel...

  • Page 32: Overhead Panel General Overview

    2.4.6 Overhead Panel General Overview...

  • Page 33: Engine Control Quadrant

    Engine Control Quadrant LH engine fuel shut-off lever (red) generic LH engine fuel fl ow control lever (yellow) generic Rotor brake control lever (red) generic RH engine fuel fl ow control lever (yellow) generic RH engine fuel shut-off lever (red) generic Start pushbutton generic...

  • Page 34: Primary Flight Controls

    Primary Flight Controls The standard Evolution S623T helicopter Cyclic is based on a generic design and features dual Dynamic Control Load (DCL) on cyclic, collective and pedals set-up. 2.6.1 Pedals Pedals aft / forward motion Generic / Dynamic Control Loading enabled...

  • Page 35: Collective Pilot

    2.6.2 Collective Pilot Collective Generic governed throttle Squirrel / Ecureuil type Landing light Generic dummy switch unless visuals high-end Engine trim Generic T ail rotor Servo Cut Generic 2.6.3 Collective Co-Pilot Collective Generic governed throttle Squirrel / Ecureuil type Landing light Generic dummy switch unless visuals high-end Engine trim Generic...

  • Page 36: Cyclic

    2.6.4 Cyclic CYCLIC Generic Dynamic Control Load enabled Elite Hardware Autopilot disengage Generic Elite Hardware Electrical trim Generic Elite Hardware Generic Elite Hardware...

  • Page 37: Section 3 Instructior Station

    SECTION 3 INSTRUCTIOR STATION Instructor Operating Station (IOS) Features The main components of the IOS are: Two 19” TFT Display Keyboard & Mouse Color Printer The instructor’s area is located for optimum crew station view and instructor’s station interface within applicable physical constraints. The following controls are available via the instructor sta- tion: Initial Helicopter Position Meteo Pages...

  • Page 38: Software Pages Overview

    Software Pages Overview 3.2.1 Initial Position At start-up the simulator is set to a predefi ned initial position. The instructor has the possibility to load self-created state fi les containing helicopter loading, cockpit instrument settings, weather conditions, malfunctions and helicopter position. 3.2.2 Meteo Pages The Meteorological conditions are controlled on two pages:...
  • Page 39 The “Meteo Clouds and Visibility” page allows modifi cation of the visibility and cloud type on three separate layers and enables the instructor to create realistic weather situations. State fi les record- ing weather settings can be created at any time and reloaded when required. Actual Metar data can be downloaded from the Internet and imported into the simulation for realistic representation of the weather settings.

  • Page 40: Control Page

    3.2.3 Control Page The control page allows date and time manipulation for realistic day to night transition and light en- vironment. High resolution helipads, runways and taxiways and a complete approach light system including PAPI/VASI, EFAS and REIL – systems are implemented. Helicopter load and usable fuel can also be altered here.

  • Page 41: Map Page

    3.2.4 MAP Page The instructor is able to select the Heli pad / Runway or reposition the helicopter to any de- sired map position. The following information can be depicted: Helicopter position (LAT/LONG) Helicopter heading Helicopter altitude Indicated airspeed Helicopter track Transponder code The Navigational Aids are displayed as symbols including identifi...
  • Page 42 The fl ight path can be stored and replayed - maximum recording time is 60 minutes. Print map, zoom functions, database load and state fi le save functions are standard map page features. Map page...

  • Page 43: Navigation Modifi Cation Page

    3.2.5 Navigation Modifi cation Page The Navigation Modifi cation Page enables the Instructor to modify any facility or even create new one’s. Map modifi cation page...

  • Page 44: Confi Guration Page

    3.2.6 Confi guration Page The Confi guration Page contains one-time settings such as sound volume control, calibration of the control axes, or specifi able cockpit instrumentation layout. Confi guration page...

  • Page 45: Malfunctions Page

    .2.7 Malfunctions Page Malfunctions page Failures can be defi ned to occur immediately or within a specifi able time window. The mal- function page displays all armed and failed instruments or systems.

  • Page 46: Instrument And System Failures

    3.2.7.1 Instrument and System failures Primary Instruments (selectable for Pilot or Copilot) Attitude Indicator Altimeter Turn/bank coordinator Airspeed Indicator Vertical Speed Indicator System Failures Static system Pitot & Drain freeze Pitot freeze dynamic Receiver Failures NAV1 receiver CDI/LOC Glide slope NAV2 receiver CDI/LOC Glide slope...

  • Page 47: Helicopter-State Snapshot

    3.2.8 Helicopter-State Snapshot This will create a fi le with all helicopter related parameters such as helicopter position, attitude, instrument settings, failure settings and meteorological situation. This information can be reload- ed for subsequent lessons or recalled for debriefi ng purposes. 3.2.9 Communication System T o enable intercom and simulated radio communication between the instructor and the train-...

  • Page 48: Section 4 Computer System And Periphals

    SECTION 4 COMPUTER SYSTEM AND PERIPHALS Hardware The components of the Computer Hardware comply with the current industry standards. Suffi cient hard disc space, memory and processing speed is available for later upgrades and modifi cations. Programming Language Standard high-level programming languages C and C++ are used for implementation of the fl ight simulation software.

  • Page 49: Section 5 Simulation

    The effect of wind from any direction, at speeds from zero to sixty knots is realistically simulated and controlled by the instructor. The wind shows the correct effect on the ground track display during in-fl ight operation of the Evolution S623T helicopter. 5.1.2 Atmosphere Variation of temperature, pressure and density with altitude does follow the ISA standard model.

  • Page 51: Instrument Responses

    5.1.5 Instrument Responses Instrument responses to actual helicopter responses do refl ect: Helicopter slip and rate of turn Rate of turn, as a function of bank angle and airspeed Attitude, altitude and rate of climb Pitch attitude, as a function of airspeed and CG Radio Navigation Simulation 5.2.1 Radio Navigation Computation...
  • Page 52 RealView visual database example Custom generated visual database example...

  • Page 53: Aircraft Systems Simulation

    Aircraft Systems Simulation 5.3.1 Electrical System Changing the status of electrical consumers in the cockpit (e. g. switching on / off Avionics panel) is refl ected in the consumption of electricity. Should the helicopter’s electrical systems run on battery only without being constantly fed by the generator, battery load will decrease. 5.3.2 Engine System The engine and the associated controls and indicators are simulated as described in the he-...

  • Page 54: Avionics And Radio System Simulation

    General All avionics operate as they would in the actual helicopter, except as explained in this section. Avionics operation is limited by the capabilities of the Evolution S623T helicopter navigation system. The avionics of the Evolution S623T helicopter include the following:...

  • Page 55: Adf System

    Garmin GNS430 or GNS530 are available as options. Flight Director / Autopilot System The Evolution S623T helicopter has a fully functional two-axis automatic fl ight control system, including autopilot and fl ight director, simulating the Bendix/King KFC 150. An autopilot dis- connect button is installed in both cyclic controls.

  • Page 56: Section 6 Visual System

    SECTION 6 VISUAL SYSTEM Visual System Features 6.1.1.1 Standard 3 to 5 channel Multiscreen Visual Systems Field of View (approx): between 120° x 30° and 120° x 50° FOV depending on confi guration / meets FAA AATD, CASA FSD2 Cat B requirements Image Generators: Three to fi...

  • Page 58: Standard 3-Channel Multiprojector Visual System

    6.1.1.2 Standard 3-channel Multiprojector Visual System Field of View (approx): 120° x 35° / meets FAA AATD, CASA FSD2 Cat B requirements Image Generators: Three image generators based on the latest technology and performance criteria Screens: Three COTS high-resolution projectors Res- olution on 1024 x 768 pixels Brightness 2200 ANSI lumens Contrast ratio 500 : 1...
  • Page 59 Required room dimensions 4 x 4 meters...

  • Page 61: Cave Visual System

    6.1.1.3 CAVE Visual System Field of View (approx): 270° x 65° / meets JAA JAR-AATD H / FAA AATD, CASA FSD2 Cat B requirements Image Generators: Three image generators based on the latest technology and performance criteria Screens: Three high-resolution projectors optimised for Visualisation & Simulation Resolution 1400 x 1050 pixels Bright- ness 3300 ANSI lumens Contrast ra- tio 2500 : 1...
  • Page 62 CAVE External Visual System Required room dimensions 7.5 x 7.5 meters (25 ft x 25 ft)

  • Page 63: Airport Associated Lighting Facilities

    6.1.2 Airport Associated Lighting Facilities Approach lighting system Heli pad / Runway lighting System T axiway Lighting System VASI and PAPI Lights Runway End Identifi cation Lights (REILS) 6.1.3 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 astronomical model.

  • Page 64: Objects (Available Optionally)

    6.1.7 3D Objects (available optionally) Examples of some of the 3D objects available at cost.

  • Page 65: Digital Terrain Models

    6.1.8 Digital Terrain Models Elevation data of global coverage and specifi c high resolution areas are used. 6.1.9 Programming Languages used in RealView™ / GenView™ The Real / GenView™ Visual is based on OpenGL. OpenGL ensures excellent image quality with the currently available video cards offering hardware accelerated fast rendering.

  • Page 66: Section 7 Installation

    Power Supply) Power The Evolution S623T AATD complex will operate on 3-phase 380/400 V / 50 Hz (CEE 32 wall socket) electric power. All interfacing equipment will be provided by the manufacturer. The total electric power consumption for the S623T helicopter with three visual channels is about 3.8 kW and consists of the following separable circuits:...

  • Page 67: Section 8 Acceptance Procedures

    ACCEPTANCE PROCEDURES Acceptance Timing Following a factory acceptance an on site acceptance is carried out by the Customer in accor- dance with a fi nal acceptance, which shall ensure that the Evolution S623T AATD meets the specifi ed requirements. Testing Procedure Evolution S623T helicopter evaluation during acceptance shall be accomplished only when the device is loaded with all deliverable object modules.

  • Page 68: Section 10 Options

    SECTION 10 OPTIONS 10.1 Optional instrumentation layout 10.1.1 Conventional instrumentation for Pilot and Copilot...

  • Page 69: Garmin Gns 430 / 530 (Real Time Components)

    10.1.2 Garmin GNS 430 / 530 (real time components) The GNS 430W, designed as the fi rst in a line of new aviation products, is an equally versatile panel-mounted companion to the GNS 530. It is a WAAS-upgradeable IFR GPS, COM, VOR, LOC, and glide-slope with colour moving map in one multi purpose unit.
  • Page 70 Setup with 4 LED 55 inch TV Visual system...
  • Page 71 Sample layout with Garmin GNS 530W and EFS 40 and Gear Lever...
  • Page 73 Software screen shot Pilot Instruments (EFIS Version)
  • Page 74 Software screen shot Co-Pilot Instruments (EFIS Version)
  • Page 75 Software screen shot Pilot Instruments (conventional Version)
  • Page 76 Software screen shot engine instruments (EFIS & convention Version...
  • Page 77 Software screen shot Co-Pilot Instruments (non_EFIS Version)
  • Page 78 SECTION 11 SINGLE PILOT IFR SYSTEM, SFIM 85T31 A.F.C.S. Quick Reference Guide 11.1 GENERAL The SFIM Automatic Flight Control System signifi cantly reduces pilot workload allowing single pilot IFR operations on Twinstar helicopters. It combines one basic three-axis Autopilot, one Flight Director Coupler (FDC) and one Pitch and Roll Monitor.
  • Page 79 11.3 FLIGHT DIRECTOR COUPLER (FDC) The FDC provides fl ight path guidance: when coupled, the system will automatically sat- isfy pitch and roll commands necessary to capture and track the desired fl ight path. Selecting a fl ight director mode causes the fl ight director bars to come into view on the ADI.
  • Page 80 MONIT ITEM DESCRIPTION - FUNCTION Pitch channel engage buttion Roll channel engage button Yaw channel engage button Altitude hold push button Capture and hold of the vertical speed set on the pilot’s VSI Airspeed hold Capture and hold of an ILS glideslope beam Failure monitoring unit and AP disengage push button Coordinated turn mode push button Selected heading hold push button...
  • Page 81 11.4 PITCH AND ROLL MONITOR The PITCH AND ROLL MONITOR monitors the operation of pitch and roll channels at various levels: • ATTITUDE SENSORS • CONTROL LAWS • SERIES ACTUATORS NOTE: The trim computer monitors the proper operation of the automatic trims 11.5 SYSTEM COMPONENTS 11.5.1 AP/FDC MODE CONTROLLER...
  • Page 82 11.5.3 FDC COMPUTER The Flight Director Computer receives information from various sensors and navigation sources: • Vertical gyro • • • Radio-altimeter • VOR / ILS receiver The FDC provides inputs to the autopilot and the command bars of the ADI in accordance with the pilot’s selection on the AP/FDC mode controller.
  • Page 83 11.6 PANEL MOUNTED COMPONENTS 11.6.1 Gyro-Horizon (ADI) NOTE: ADI and HSI models may vary. This is for descriptive purposes only. The gyro-horizon displays airc raft pitch and roll attitudes and inclues pitch and roll command bars, inclinometer, glide-slope pointer and various warning fl ags. The pitch and roll command bars displayed computed steering commands to approach and maintain a desired fl...
  • Page 84 Gyro-Horizon (ADI) Horizontal Situation Indicator (HSI)
  • Page 85 11.6.3 Vertical Speed Indicator (VSI) The VSI displays the instantaneous vertical speed of the helicopter an dby means of a knob con- trolled bug allows the pilot to select the desisre vertical speed for the V/S mode. 11.6.4 Actuator Position Indicators (API) The API give an indication of series actuator extension or retraction about their mid point.
  • Page 86 When illuminated, the green annunciators indicate that the relevant mode(s) is (are) active (one longi- tudinal mode can coexist with one lateral mode, e.g. ALT and HDG). The display is the repetitve of that one shown by the AP/CPL mode controller on which an active mode is signalled by “ON”...
  • Page 87 • A “trim demand”. This alarm is triggered whenever a P or R series actuator is out of the center by more than 2/3 of the actuator’s stroke. This might happen in case of an inoperative auto-trim. In this event, the pilot switches off the relevant trim and recenters the corresponding API whenever the trim demand light comes on.
  • Page 88 • The rotating selector enables the pilot to pre-fl igh test: - The annunciators - The excessive devition warning lights - The automatic trims - The pitch and roll monitor • A small red light signals a test is in progress. 11.6.6 ACTUATOR POSITION INDICATORS The API gives an indication of series actuator extension or retraction about its mid-point.
  • Page 89 TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS TRIM DEMAND LIGHT if the pilot see this....he declutches the stick and moves it to the right. if the pilot see this....he declutches the stick and moves it backwards.
  • Page 90 11.6.7 CYCLIC STICK GRIP CONTROLS Stick top fourway beep-trim switch (“coolie hat”) Activation of this switch commands a change in reference attitude at a rate of approx. 2 deg per second and 4/s in roll (automatic trim function) or, when the AP is disengaged, a shift in the stick anchoring by causing the trim motor to rotate (manual trim).
  • Page 91 SECTION 12 BASIC AUTOPILOT MODES 12.1 Pitch and Roll Attitude Retention The long term attitude hold modes of pitch and roll can be engaged independently but are typically engaged at the same time by depressing the P and R push buttons on the mode controller. When they are engaged, a green “ON”...
  • Page 92 The processed heading error signal activates the series actuator. Since there is no automatic trim in the yaw control linkage, the pilot has to refer from time to time to the yaw API. Fly-through characteristics: • In hover: To change the heading reference datum the pilot acts on the antitorqe pedals. The pedal motion detector by detecting the pilot input on the pedals, switches the yaw channel into syncronization.
  • Page 93 SECTION 13 RECOMMENDED OPERATING LIMITATIONS • On the ground, the AP must be disengaged except for prefl ight checks. • Recommended airspeed for IFR operation: 55 kts • If the height to clear obstacles is less than 400 feet the pilot must fl y hands-on. •...
  • Page 94 SECTION 14 VERTICAL MODES The FDC coupler generates pitch commands to the autopilot computer. If F/D mode is punched on the FDC controller, these pitch commands are displayed by the ADI horizontal (pitch) command bar thereby allowing the pilot to monitor the correct operation of the FDC . 14.1 ALT - Baro-Altitude Hold Normal prior conditions are: •...
  • Page 95 The altitude hold mode is engaged by pressing the ALT button on the mode controller. All other FDC pitch axis modes previously selected (A/S, G/S, V/S, or G/A) are over ridden. The altitude hold mode controls the helicopter to the altitude observed at mode selection. The FDC computer uses altitude error to generate pitch inputs to the autopilot computer.
  • Page 96 14.2 A/S - Airspeed Hold Normal prior conditions are: • AP pitch channel “ON” • CPL “ON” • F/D “ON” if desired MONIT “A/S” green caption illuminates TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS Flashes whenever altitude deviation from reference altitude datum exceeds +/- 120 ft.
  • Page 97 The airspeed hold mode is engaged by pressing the A/S button on the mode controller. All other FDC pitch axis modes previously selected (ALT, G/S, V/S or GA) are over ridden. The airspeed observed at mode engagement will be maintained automatically. The FDC computer uses airspeed error to generate pitch inputs to the autopilot computer.
  • Page 98 14.3 V/S - Vertical Speed Hold Normal prior conditions are: • AP pitch channel “ON” • CPL “ON” • F/D “ON” if desired MONIT “V/S” green caption illuminates TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS...
  • Page 99 The vertical speed mode is engaged by pressing the V/S button on the mode controller. All other FDC pitch axis modes previously selected (ALT, G/S, A/S or GA) are over ridden. The V/S set by the cursor posiion onthe pilot’s vertical speed indicator is acquired and maintained automatically, providing the pilot has applied suffi...
  • Page 100 14.4 G/S - Glide Slope - Capture and tracking of an ILS Glide Slpe Beam Normal prior conditions are: • AP pitch channel “ON” • CPL “ON” • F/D “ON” if desired • Radio-altimeter signal valid, DH set on indicator •...
  • Page 101 “V/S” green caption illuminates TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS Since the glide-slope can be captured with any vertical mode previously selected, the aircraft is typically fl yikng ALT mode ON. It is recommended to capture glide-slope from below the beam. It is the pilot’s responsibility to follow a fl...
  • Page 102 When the deviation from glide-slope beam falls below a predetermined value (1/3 dot on glide de- viation scales) the FDC feeds inputs to the AP pitch channel so as to asymptotically approach the glide-slope beam. The pilot reduces power manually to avoid VNE over shooting. G/S green caption illuminates.
  • Page 103 TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS Excessive deviation from the glide-slope beam is displayed by the fl ashing of the G/S excessive beam annunciator. This warning is generated when deviation from glide-slope beam is slightly above 1 dot. 14.4.4 Auto-Level When approaching the runway, the FDC automatically levels off and automatically maintains a radio-height of 80 feet providing radio-altimeter signal is valid.
  • Page 104 NOTE: 1) Beep-trim and stick release are disabled as soon as G/S mode is effective 2) The pilot is not supposed to operate these commands unless safety demands 3) If during glide-slope approach the radio-altimeter signal turns invalid (actual failure or instrument test carried out by the pilot), the G/S mode is automatically disengaged.
  • Page 105 All other coupled modes are reset except HDG, the G/A annunciator illuminates, the aircraft rolls wings level and the yaw channel maintains the heading observed at mode engagement or fl ies to the heading selected on the HSI if HDG mode is active. Once the G/A mode has been selected and all lateral modes reset (except HDG), any lateral mode can be subsequently reselected.
  • Page 106 SECTION 15 LATERAL MODES The FDC coupler generates roll commands to the autopilot computer. If F/D mode is punched on on the mode controller, those roll commands are displayed by the ADI vertical (roll) command bar thereby allowing the pilot to monitor the correct operation of the FDC. The engagement of any of the lateral modes freezes the roll reference at zero.
  • Page 107 TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS Pressing the HDG button on the mode controller engages the Heading Select Modce. The FDC then feeds inputs to the AP roll channel so as to command a turn to the heading selected by the lo- cation of the bug on the HSI.
  • Page 108 15.2 VOR - Automatic Capture and Tracking of a Radial Displayed on the HSI Normal prior conitions are: • AP Roll channel engaged • CPL “ON” • F/D “ON” if desired • Navigation receiver tuned to the desired VOR station •...
  • Page 109 Since any vertical mode (except G/A) can be selected and coupled without affecting VOR opera- tion, ALT mode is also punched “ON”. TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS VOR Amber Light ON 15.2.2 VOR Radial CAPture When intercept angle or route error > 45 degrees: When deviation from the selected radial falls below a predetermined value (about 2/3 of a dot on the HSI deviation scale) the coupler progressively banks the helicopter so as to cut the selected ra- dial at 45 degrees.
  • Page 110 MONIT VOR green caption illuminates TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS VOR amber caption goes out...
  • Page 111 15.2.3 VOR Radial Tracking The helicopter is slaved to the VOR radial as soon as its fl ight path meets the radial. It will smoothly roll out and track the radial with crosswind corrections. TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS “CPL”...
  • Page 112 15.2.4 At VOR Beacon Passage MONIT VOR green caption fl ashes TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS OSS amber caption illuminates...
  • Page 113 15.2.4.1 Without Selection of a Different Outbound Radial The AFCS 85T31 includes a VOR overstation sensor (OSS) which inhibits response to the beam signal when in the cone of confusion above the VOR station. When the beam rate becomes excessive, only course data are fl own for a time interval (approxi- mately 45 seconds).
  • Page 114 15.2.5 V/L - VOR / LOC: Capture and Tracking of ILS Front Course Localizer Beam Normal prior conitions are: • AP Roll channel “ON” • CPL “ON” • F/D “ON” if desired • Navigation receiver tuned on ILS frequency • HSI course pointer set to the published inbound runway heading •...
  • Page 115 ““ALT” & “HDG” green captions illuminate TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS “V/L” & “G/S” amber captions illuminate The aircraft is fl ying o the selected intercept heading set on the HSI. HDG is “ON”. (Intercept heading can also be fl own in the basic AP present heading hold mode). Intercept angles are to be chosen with regard to the distance from the runway threshold.
  • Page 116 15.2.5.2 LOC Beam CAPture When deviation from the localizer beam drops below a predetermined value corresponding to about 2 dots on the HSI deviation scale, the couple progressively banks the helicopter so as to cut the locaizer beam at an intercept angle (or route error) of 25 degrees. Turn is auto- matically coordinated provide T/C and Y channel are punch on.
  • Page 117 15.2.5.3 Localizer Beam Tracking The system tracks the center of the localizer beam with automatic crosswing correction. Piloting inputs are displayed by the vertical (roll) command bar. In the event any info required for V/L mode operation becomes invalid, the mode is automatidclly decoupled, the roll command bar bias out of view, the CPL light fl...
  • Page 118 15.2.6 B/C - Back Course: Capture and Tracking of ILS Back Beam Normal prior conitions are: • AP Roll channel “ON” • CPL “ON” • F/D “ON” if desired • Navigation receiver tuned on ILS frequency • Localizer signal valid •...
  • Page 119 Operation of this mode is similar to the V/L mode, ie. the desired intercept heading is set on the HSI and ALT may be selected to maintain approach altitude. MONIT TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS When the helicopter approaches the localizer back beam, automatic capture and tracking occurs. FDC generated roll piloting inputs are fed to the autopilot computer and displayed by the roll com- mand bar.
  • Page 120 Excessive deviation from the localizer back beam is displayed by the fl ashing of the LOC excessive deviation annunciator. Amber light fl ashes TRIM GYRO TEST DEVIATIONS TEST MONIT TRIM VOR OSS NOTE: 1) Beep-trim and stick release are disabled as soon as B/C mode is effective. 2) The pilot is not supposed to operate these commands unless safety demands.
  • Page 121 15.2.7 V/L - VOR / LOCALIZER Approach Mode Normal prior conitions are: • AP Roll channel “ON” • CPL “ON” • F/D “ON” if desired • Navigation receiver tuned to the desired VOR station • HSI course pointer set on the desired course •...
  • Page 122 FREQ This mode has been specially optimized for VOR radial intercept at a short distance from the VOR station, for VOR approach and climbout procedures at low speed, for the VOR station pasage at low altitude without signifi cant course modifi cation at the station and for very accurate radial hold. Seen from the cockpit, operation of this mode is identical to the VOR mode.
  • Page 124 Supplement to the ELITE Evolution Series Manual Helicopter IOS Malfunction Generator...
  • Page 125 Table of Contents 1 General Introduction.......................4 1.1 Failure Control........................4 1.1.1 First Group........................5 1.a Failure time window....................5 1.b Immediate failure using the time window..............6 1.c Specifi c time failure....................6 1.1.2 Second Group......................7 2.a Engine failures......................7 1.2 Random Failures.......................7 1.3 General Controls.......................9 1.3.1 Failure states......................9 1.3.2 Reset to ARM......................10 1.3.3 Ref.

  • Page 126: General Introduction

    General Introduction The MALFUNCTIONS Page is used to create failure scenarios. The ability to set up and prac- tice realistic failures is one of the most powerful features in any simulation. Many of these fail- ures would be impractical, impossible, or unsafe to recreate in an actual aircraft. Yet, exposure to these same situations in a simulated environment can add invaluable experience.

  • Page 127: First Group

    1.1.1 First Group The fi rst group’s failures can be controlled as follows: 1. Freeze – the instrument maintains indications present at time of failure. No warning fl ags appear as the instrument is completely blocked. 2. Gradual – the instrument gradually changes indication, warning fl ags appear as appropriate To “Freeze”...

  • Page 128: Specifi C Time Failure

    Specifi c time failure To invoke a failure at a specifi c (future) time, enter the SAME values (minutes) in BOTH “Between” windows. If we had been fl ying for fi fteen minutes and wanted the Pitot Tube to freeze over with an accumulation of ice three minutes from now, we would simply enter 18 and 18 respectively in the “Between”...

  • Page 129: Random Failures

    Random Failures The Random Failures panel allows you to experience what it is like to expect the unexpected. To set up a random failure enter the failure time window interval(s). As previously described, you can use these intervals to invoke failures immediately, at specifi ed times, or within a de- fi...

  • Page 130: General Controls

    General Controls At the lower-left of the MALFUNCTIONS Page you will fi nd a box containing several buttons that are applicable to the entire MALFUNCTIONS Page as opposed to the control of individual failures de- scribed previously. 1.3.1 Failure states Similar to saving and loading METEO States, the SAVE and LOAD buttons next to “Failure State”...

  • Page 131: Aircraft Type Specifi C Failures - Helicopter

    Aircraft Type specifi c failures – Helicopter This section describes the different failures available on the different aircraft types. The individual columns depict the following: • Failure Name • affi liation to either Group 1 or Group 2 or direct control •...

  • Page 132: Instruments

    2.2.1 Instruments Failure Name Affi liation Effect Recovery Pilot - AI Group 1 Fails the operation of the Attitude Indicator, Pilot side IOS only Pilot - HSI Group 1 Fails the operation of the HSI, Pilot side IOS only Pilot - VSI Group 1 Fails the operation of the Vertical Speed Indicator, Pilot side IOS only...

  • Page 133: Electrical

    2.2.2 Electrical Failure Name Affi liation Effect Recovery Generator, LH Group 2 Fails the LH generator system IOS only Generator, RH Group 2 Fails the RH generator system IOS only Generator, LH w. Rst Group 2 Fails the LH generator system IOS or Pilot action Generator, RH w.

  • Page 134: Receivers

    2.2.3 Receivers Failure Name Affi liation Effect Recovery NAV 1 – REC Group 2 Fails the NAV 1 receiver. The receiver unit on the avionics panel turns off. IOS only In case of using a Garmin GNS430 device, the receiver still indicates the frequency, but the connection between the receiver and the instrument is interrupted.

  • Page 135: Engines

    2.2.4 Engines Failure Name Affi liation Effect Recovery Left Engine Group 2 Fails the operation of the left engine completely IOS only Left Auxiliaries Group 2 Triggers a decrease in oil pressure indication below IOS only Oil Press lower limit, left engine Left Auxiliaries Group 2 Triggers an increase in oil temperature indication...
  • Page 136 Failure Name Affi liation Effect Recovery Governor HiSide Rwy L Group 2 Triggers a runaway increase of left governor, causing IOS or engine Tq and Ng indication to increase above limits shut down Governor HiSide static L Group 2 Triggers a high indication of left governor IOS only Governor None respond.

  • Page 137: Units

    2.2.5 Units Failure Name Affi liation Effect Recovery Hyd LH Group 2 Fails the LH hydraulic system IOS only Hyd RH Group 2 Fails the RH hydraulic system IOS only Limit Group 2 Limit caption illuminates IOS only Servo LH Group 2 LH servo fails IOS only...
  • Page 138 Failure Name Affi liation Effect Recovery Filter LH Group 2 LH fi lter caption illuminates IOS only Filter RH Group 2 RH fi lter caption illuminates IOS only Door Group 2 Door caption illuminates IOS only Fire LH x 1 Group 2 Engine Fire LH caption illuminates IOS or activation of 1 LH fi...

  • Page 139: Random Failures

    2.2.6 Random failures Failure Name Affi liation Effect Recovery Instruments Random F. Randomly fails the selected number of intruments in the IOS only specifi ed time window Systems Random F. Randomly fails the selected number of systems in the IOS only specifi...

  • Page 140: System Failures

    2.2.7 System Failures Failure Name Affi liation Effect Recovery Right Seat - Static Group 1 Freezes the static port IOS and alternate static port Right Seat - Pitot Group 1 Freezes the pitot tube IOS and pitot heat Inlet Freeze Right Seat - Pitot Group 1 Freezes the pitot tube and drain.

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