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SECTION 4

COMPUTER SYSTEM AND PERIPHALS

4.1 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.

4.2 Programming

Language

Standard high-level programming languages C and C++ are used for implementation of the fl ight

simulation software.

4.3 Maintenance

Capabilities

Tools for software maintenance are available at the manufacturer’s site and will allow, with remote

access to the operator’s computer for immediate corrective access.

4.4 System

Spare

Capacity

The computer system has adequate spare capacity in both memory and processing time as fol-

lows:

The amount of spare memory and disk space will be at least 30% in excess.

The spare processing time for the cockpit Instruments are at least 40% in excess.

For all different visual setup, at least 60 frames per second.

4.5 Diagnostic

Incorporated in the design is a diagnostic system (software) to enable verifi cation of the I/O

device integrity as well as to identify and isolate faulty I/O channels.

Содержание S623T

Страница 2: ...t 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...

Страница 3: ...plementation 17 2 4 2 General 17 2 4 3 Aft Control Panel 17 2 4 3 1Aft Control Panel left side Panel 1 18 2 4 3 2Aft Control Panel right side Panel 4 20 2 4 4 Fwd Control Panel 22 2 4 4 1 Fwd Control...

Страница 4: ...tions 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 4 1 Hardwa...

Страница 5: ...stem 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 5 4 4 Transponder System 49 5 4 5 ADF System 49 5 4 6 DME System...

Страница 6: ...ng Languages used in RealView GenView 62 SECTION 7 INSTALLATION 63 7 1 Site Layout 63 7 2 Power 63 7 3 Temperature Sensors 63 SECTION 8 ACCEPTANCE PROCEDURES 64 8 1 Acceptance Timing 64 8 2 Testing Pr...

Страница 7: ...pilot distraction and furnished with ergonomically positioned pilot seats d Cockpit Instrument Panel replicating generic twin engine turbine with high perfor mance instrumentation various options avai...

Страница 8: ...the instructor access to the simulation environ ment as well as to a variety of training tools Two TFT display for various information such as area and approach tracking c A simulation computer syste...

Страница 9: ...ion 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 C...

Страница 10: ...oper ating and maintenance information will be provided under this volume 1 4 1 4 Range of Spares This document comprises a list of all spares tools and test equipment recommended by the man ufacture...

Страница 11: ......

Страница 12: ...ed to disassemble equipment or to remove parts 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 componen...

Страница 13: ...ame general action They are in a similar appearance to those found in the actual helicop ter 2 1 2 Aircraft Parts The Evolution S623T helicopter does not include original helicopter parts 2 1 3 Instru...

Страница 14: ...2 2 Standard Cockpit Panel Layout 2 2 1 Overview Instruments Layout Copilot EFIS version Engine Pilot EFIS version 2 2 2 Pilot s Main Panel...

Страница 15: ...eric 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 OAT Generic...

Страница 16: ...eric 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 Vertical Speed Indicator Generic for twin engine...

Страница 17: ...ngine turbine Right engine oil pressure gauge Generic for twin engine turbine Left engine oil temp gauge Generic for twin engine turbine Right engine oil temp gauge Generic for twin engine turbine Lef...

Страница 18: ...ons 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...

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Страница 20: ...2 4 Overhead Panel...

Страница 21: ...t Light intensity can be controlled with OP_ACDC_3 which is imple mented on the AC DC Gauge Selector Panel see chapter 2 4 5 Exceptions are OP_FWDR_7 BATT Panel 3 and OP_AFTR_3 FUEL INTERC Panel 4 The...

Страница 22: ...ushbutton TRIM RELEASE OP_AFTL_5 Pushbutton ROLL TRIM ACTUATOR OP_AFTL_6 Pushbutton CRANK LH ENG OP_AFTL_7 Pushbutton FIRE EXT No1 LH OP_AFTL_10 Pushbutton FIRE EXT No2 LH OP_AFTL_12 Pushbutton INST P...

Страница 23: ...Layout Aft Left Side Switch panel 1...

Страница 24: ...ANK RH ENG black OP_AFTR_7 Pushbut ton FIRE EXT No1 RH red OP_AFTR_10 Pushbut ton FIRE EXT No2 RH red OP_AFTR_11 Pushbut ton STROBE LT black OP_AFTR_12 Pushbut ton LTS TRANSF LH RH black OP_AFTR_14 Pu...

Страница 25: ...Layout Aft Right Side Switch panel 4...

Страница 26: ...r 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 LH EXT PWR BATT black OP_FWDL_7 Pushbutton HORN black OP_FWDL_8 Momentar...

Страница 27: ...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 Vo...

Страница 28: ...Pushbutton RH EXT PWR BATT black OP_FWDR_2 Pushbutton RH B P black OP_FWDR_3 Pushbutton GEN RH black OP_FWDR_4 Pushbutton INVERT RH black OP_FWDR_6 Momentary TEST AU TOR black OP_FWDR_7 Pushbutton BAT...

Страница 29: ...ns 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 Poi...

Страница 30: ...TRIM ACTUATOR RAD ALT COPILOT WIPER FIRE EXT No 2 LH FIRE EXT No 1 LH TRIM RELEASE PITCH TRIM ACTUATOR FIRE EXT No 1 RH FIRE EXT No 2 RH STROBE LT CONSOLE LT OP_FW DL _G1 OP_FW DL _G1 OP_FW DL _G1 HOR...

Страница 31: ...D Type Label Remarks OP_ACDC_1 5 Position turn knob U 26V LH U 115V LH no label U 26V RH U 115V RH OP_ACDC_2 5 Position turn knob LH V ESS RH V SHED I GENE LH RH OP_ACDC_3 Turn knob LIGHTING SWITCHES...

Страница 32: ...2 4 6 Overhead Panel General Overview...

Страница 33: ...el shut off lever red generic 2 LH engine fuel flow control lever yellow generic 3 Rotor brake control lever red generic 4 RH engine fuel flow control lever yellow generic 5 RH engine fuel shut off le...

Страница 34: ...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...

Страница 35: ...ght 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 G...

Страница 36: ...2 6 4 Cyclic CYCLIC Generic Dynamic Control Load enabled Elite Hardware Autopilot disengage Generic Elite Hardware Electrical trim Generic Elite Hardware PTT Generic Elite Hardware...

Страница 37: ...ated 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 Positio...

Страница 38: ...ions 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 t...

Страница 39: ...ic weather situations State files 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 simulati...

Страница 40: ...ation 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 impl...

Страница 41: ...strument readout during the training session or for debriefing purposes replay function including the display of the instruments status TURN ON EXTENDED PROFILE VIEW When selected the area map will ad...

Страница 42: ...The flight path can be stored and replayed maximum recording time is 60 minutes Print map zoom functions database load and state file save functions are standard map page features Map page...

Страница 43: ...3 2 5 Navigation Modification Page The Navigation Modification Page enables the Instructor to modify any facility or even create new one s Map modification page...

Страница 44: ...3 2 6 Configuration Page The Configuration Page contains one time settings such as sound volume control calibration of the control axes or specifiable cockpit instrumentation layout Configuration page...

Страница 45: ...2 7 Malfunctions Page Malfunctions page Failures can be defined to occur immediately or within a specifiable time window The mal function page displays all armed and failed instruments or systems...

Страница 46: ...rain freeze Pitot freeze dynamic Receiver Failures NAV1 receiver CDI LOC Glide slope NAV2 receiver CDI LOC Glide slope ADF receiver ADF antenna DME GPS RAIM loss Electrical Failures Generator Battery...

Страница 47: ...can be reload ed for subsequent lessons or recalled for debriefing purposes 3 2 9 Communication System T o enable intercom and simulated radio communication between the instructor and the train ees Ho...

Страница 48: ...available at the manufacturer s site and will allow with remote access to the operator s computer for immediate corrective access 4 4 System Spare Capacity The computer system has adequate spare capac...

Страница 49: ...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 flight operation of the Evolution S623T he...

Страница 50: ......

Страница 51: ...function real world Navigation databases are supplied Periodical updates are available if required Modification of existing and creation of new facilities is possible by the user 5 2 2 Visual Database...

Страница 52: ...RealView visual database example Custom generated visual database example...

Страница 53: ...uded in the performance computations Characteristics for the applicable turbines and their effect on the flight path are reproduced in re sponse to engine control selections The turbines monitoring sy...

Страница 54: ...f used NAV1 COMM1 is on the GPS EFIS EFS 40 50 option 5 4 2 Audio System The audio control system simulates NAV COMM ADF Marker audio and Intercom 5 4 3 VHF Navigation Communication System The KX 165...

Страница 55: ...tor Autopilot System The Evolution S623T helicopter has a fully functional two axis automatic flight control system including autopilot and flight director simulating the Bendix King KFC 150 An autopi...

Страница 56: ...Cat B requirements Image Generators Three to five image generators based on the latest technology and performance criteria Screens Three HDTV 55 LCD screens optionally available 4th and 5th screen mo...

Страница 57: ......

Страница 58: ...SD2 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 Br...

Страница 59: ...Required room dimensions 4 x 4 meters...

Страница 60: ......

Страница 61: ...s 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...

Страница 62: ...CAVE External Visual System Required room dimensions 7 5 x 7 5 meters 25 ft x 25 ft...

Страница 63: ...sition 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 6 1 4 Clou...

Страница 64: ...6 1 7 3D Objects available optionally Examples of some of the 3D objects available at cost...

Страница 65: ...s 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 hard...

Страница 66: ...m x 7 5 m x 2 4 m w x l x h or 25 ft x 25 ft x 8 ft These dimensions are required for the AATD and the instructor station ISDN connection for remote access broadband recommended Consideration should b...

Страница 67: ...tance shall be accomplished only when the device is loaded with all deliverable object modules A record of the load status must be kept at all times All hardware or software changes incorporated at th...

Страница 68: ...SECTION 10 OPTIONS 10 1 Optional instrumentation layout 10 1 1 Conventional instrumentation for Pilot and Copilot...

Страница 69: ...30 It is a WAAS upgradeable IFR GPS COM VOR LOC and glide slope with colour moving map in one multi purpose unit A huge database that can be updated with a front loading data card contains all airport...

Страница 70: ...Setup with 4 LED 55 inch TV Visual system...

Страница 71: ...Sample layout with Garmin GNS 530W and EFS 40 and Gear Lever...

Страница 72: ......

Страница 73: ...Software screen shot Pilot Instruments EFIS Version...

Страница 74: ...Software screen shot Co Pilot Instruments EFIS Version...

Страница 75: ...Software screen shot Pilot Instruments conventional Version...

Страница 76: ...Software screen shot engine instruments EFIS convention Version...

Страница 77: ...Software screen shot Co Pilot Instruments non_EFIS Version...

Страница 78: ...opilot that is normally engaged prior to take off and disengaged after landing The SFIM 85T31 autopilot is a three axis attitude referenced autopilot of the series parallel type SERIES because one ele...

Страница 79: ...nds displayed by the command bars the pilot gradually flies the helicopter back to the desired flight path in accordance with the piloting Jaws set in the flight director computer F 0 crossbars never...

Страница 80: ...rtical speed set on the pilot s VSI 6 Airspeed hold 7 Capture and hold of an ILS glideslope beam 8 Failure monitoring unit and AP disengage push button 9 Coordinated turn mode push button 10 Selected...

Страница 81: ...he AP computer receives Attitude signals from a vertical gyro Heading information from a gyro compass Heading select error information fron an HSI Baro altitude and airspeed information from a baro an...

Страница 82: ...s actuator The pitch and roll monitor is automatically switched into operation by simply punching on either one of the pitch or roll channels or both It is disengaged by pressing the dedicated push bu...

Страница 83: ...isplays to provide a map like display of the aircraft position The indi cator displays aircraft displacement relative to VOR radials localizer and glideslope beams The heading select knob located in t...

Страница 84: ...Gyro Horizon ADI Horizontal Situation Indicator HSI...

Страница 85: ...Actuator Position Indicators API The API give an indication of series actuator extension or retraction about their mid point They are located on the top RH corner of the instrument panel 11 6 5 Annun...

Страница 86: ...captions When illuminated the amber CPL warning annunciator indicates that The coupler has been disengaged either manually by the pilot or automatically The last active mode on the longitudinal or lat...

Страница 87: ...rapid motion of the course pointer on the HSI When flasing the non marked amber captions next to VL and G S indicate the occurrence of excessive deviation from the ILS localizer and glide slope beams...

Страница 88: ...omatic trims which keep the series actuators around their center position saturation may be observed in the yaw channle follow to significant power changes for example In this event the pilot has to t...

Страница 89: ...N BC BC VS AS AP LOC VOR VOR ALT HDG VOR OSS A N V L G S CPL TRIM GYRO G A G S TRIM DEMAND LIGHT if the pilot see this he declutches the stick and moves it to the right if the pilot see this he declu...

Страница 90: ...trim function or when the AP is disengaged a shift in the stick anchoring by causing the trim motor to rotate manual trim Trim or stick release button Activation of this button declutches the artifici...

Страница 91: ...ft the Pitch or Roll reference data the pilot acts on the stick top fourway button A command in pitch changes the pitch reference at a rate of approximately 2 degrees per second A command in roll chan...

Страница 92: ...red as soon as bank angle exceeds 5 degrees After turn completion the new heading reference is frozen from the mo ment the heading rate falls below approximately 1 5 degrees per second It is therefore...

Страница 93: ...ited MODES RECOMMENDED LIMITATIONS ALT Airspeed 60 kts Vertical speed at mode engagement withing 1200 ft min A S Airspeed 50 kts V S Airspeed 65 kts Selected Vertical Speed within 1200 ft min HDG Airs...

Страница 94: ...FD MONIT T C HDG VOR NAV B C V L CPL ON ON ON ON FD 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 pit...

Страница 95: ...bias out of view Since the desired performance is achieved by feeding signals to the lon gitudinal control sufficient collective pitch is to be manually applied so as to ensure the minimum recommend a...

Страница 96: ...LT V S A S G S CPL FD MONIT T C HDG VOR NAV B C V L CPL ON ON ON ON ON FD LTS TEST O DEVIATIONS MONIT TRIM TEST A N BC BC VS AS AP LOC VOR VOR ALT HDG VOR OSS A N V L G S CPL TRIM GYRO G A G S A S gre...

Страница 97: ...de provid ed by the gyro horizon Should G H pitch data disappear the horizontal pitch command bar will bias out of view To change the airspeed reference datum the mode is to be disengaged on the mode...

Страница 98: ...LT VOR HDG VOR OSS A N V L G S CPL TRIM GYRO G A G S P R Y ALT V S A S G S CPL FD MONIT T C HDG VOR NAV B C V L CPL ON ON ON ON ON FD 14 3 V S Vertical Speed Hold Normal prior conditions are AP pitch...

Страница 99: ...S signal processed from the derived altitude signal and selected V S signal Piloting inputs are also displayed by the pitch command bar on the ADI providing GH pitch data are valid Loss of validity o...

Страница 100: ...eceiver tuned on ILS frequency Glideslope signal valid HSI course pointer set to the published inboud runway heading Operation of this mode generally combined with tge V L mode can be broken down into...

Страница 101: ...ode previously selected the aircraft is typically flyikng ALT mode ON It is recommended to capture glide slope from below the beam It is the pilot s responsibility to follow a flight path which makes...

Страница 102: ...avoid VNE over shooting G S green caption illuminates G S amber caption goes out 14 4 3 Glide slope Beam Tracking The system tracks the center of the glide slope beam Piloting inputs are displayed by...

Страница 103: ...iator 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...

Страница 104: ...B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B B...

Страница 105: ...cted Pitch attitude is controlled so as to acquire and maintain 75 Kts FDC generated piloti inputs are displayed by the horizontal pitch command bar on the ADI Sufficient power must be manually applie...

Страница 106: ...operation of the FDC The engagement of any of the lateral modes freezes the roll reference at zero 15 1 HDG Heading Select Capture and Tracking of a Heading Selected on the HSI Normal prior conditions...

Страница 107: ...ed it over rides the VOR V L B C and NAV modes Any vertical mode can be selected and coupled without affecting HDG select operation While the mode is engaged the pilot acts against the roll feel sprin...

Страница 108: ...Operation of this mode can be broken down into 4 phases Closing up Beam capture Beam tracking VOR station passage with or without radial change 15 2 1 ARMed Phase Closing Up The aircraft is flying on...

Страница 109: ...lected ra dial at 45 degrees Turns are automatically coordinated providing T C and Y channel are punched on When intercept angle or route error 45 degrees Heading is kept unchanged until the VOR devia...

Страница 110: ...FD MONIT T C HDG VOR NAV B C V L LTS TEST O DEVIATIONS MONIT TRIM TEST A N BC BC VS AS AP LOC VOR VOR ALT HDG VOR OSS A N V L G S CPL TRIM GYRO G A G S CAP ON ON ON ON ON VOR green caption illuminate...

Страница 111: ...the HSI while tracking the VOR radial the VOR mode is automatically decoupled the roll FD command bar bias out of view the CPL light flases for 10 sec onds and the AP keeps the helicopter at zero rol...

Страница 112: ...S A S G S CPL FD MONIT T C HDG VOR NAV B C V L CAP ON ON ON ON ON LTS TEST O DEVIATIONS MONIT TRIM TEST A N BC BC VS AS AP LOC VOR VOR ALT HDG VOR OSS A N V L G S CPL TRIM GYRO G A G S VOR green capti...

Страница 113: ...n when the TO FROM indi cator changes direction In this case the helicopter will follow as though it were heading so providing a preliminary rough interception of the new radial After a time interval...

Страница 114: ...S frequency HSI course pointer set to the published inbound runway heading Localizer signal valid Operation of this mode generally combined with the G S mode can be broken down into 3 phases Closing u...

Страница 115: ...lluminate The aircraft is flying o the selected intercept heading set on the HSI HDG is ON Intercept heading can also be flown in the basic AP present heading hold mode Intercept angles are to be chos...

Страница 116: ...eceived deviation signal falls below a predetermined value corresponding to about 1 3 of a dot on the HSI deviation scale Then the FDC feeds inputs to the AP roll channel so as to asymptotically appro...

Страница 117: ...ld If the invalid contition clears itself the pilot reengages the V L mode to resume automatic coupling G S interception is described in the Vertical Modes section LTS TEST O DEVIATIONS MONIT TRIM TES...

Страница 118: ...d Navigation receiver tuned on ILS frequency Localizer signal valid HSI course pointer set on the published inbound course CPL ON ON ON ON ON P R Y ALT V S A S G S CPL FD MONIT T C HDG VOR NAV B C V L...

Страница 119: ...NS MONIT TRIM TEST A N BC BC VS AS AP LOC VOR VOR ALT HDG VOR OSS A N V L G S CPL TRIM GYRO G A G S When the helicopter approaches the localizer back beam automatic capture and tracking occurs FDC gen...

Страница 120: ...RO G A G S Excessive deviation from the localizer back beam is displayed by the flashing of the LOC excessive deviation annunciator Amber light flashes NOTE 1 Beep trim and stick release are disabled...

Страница 121: ...R NAV B C V L ON CAP F D 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 p...

Страница 122: ...course modification at the station and for very accurate radial hold Seen from the cockpit operation of this mode is identical to the VOR mode However if the interception point of the radial is detect...

Страница 123: ......

Страница 124: ...Supplement to the ELITE Evolution Series Manual Helicopter IOS Malfunction Generator...

Страница 125: ...2 4 Engines 16 2 2 5 Units 18 2 2 6 Random failures 20 2 2 7 System Failures 21 Illustration Index Illustration 1 First Group failure 5 Illustration 2 Second Group failure 7 Illustration 3 General Co...

Страница 126: ...rm the failure s by pressing the associated ARM button s Note that the ARM button will change to FAIL when that particular item has actually failed Click on the FAIL button once to RESET the item to A...

Страница 127: ...ween column and press the ARM button in the Gradual column next to AI If this were done at the start of our flight the Ref Failure Time would already be set to zero But if we had been flying for some...

Страница 128: ...tems will NOT change to FAIL If for example we FAILed the Static System the ARM button under Static would change to FAIL at the time of the fail ure and the VSI ALT and ASI labels respectively would c...

Страница 129: ...in the number of failures you would like to occur If for example we entered in a failure time window of between 3 and 12 minutes then entered 2 in the Instruments window ELITE would randomly fail two...

Страница 130: ...n the LOAD button to open the Open Malfunction files dialog box Select a failure state from those listed previously saved and click Open 1 3 2 Reset to ARM The Reset to ARM and Clear all failures butt...

Страница 131: ...ifferent failures available on the different aircraft types The individual columns depict the following Failure Name affiliation to either Group 1 or Group 2 or direct control effect of the failure re...

Страница 132: ...itude Indicator Pilot side IOS only Pilot ASI Group 1 Fails the operation of the Airspeed Indicator Pilot side IOS only Copilot AI Group 1 Fails the operation of the Attitude Indicator Copilot side IO...

Страница 133: ...Group 2 Fails the RH generator system IOS or Pilot action Bat Temp Group 2 Triggers the Bat Temp caption IOS only Bat Fuse Group 2 Triggers the Bat Fuse caption IOS only Inv LH Group 2 Fails the LH In...

Страница 134: ...avionics panel turns off 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 The appropriate fl...

Страница 135: ...l Press Group 2 Triggers a decrease in oil pressure indication below lower limit right engine IOS only Right Auxiliaries Oil Temp Group 2 Triggers an increase in oil temperature indication above the u...

Страница 136: ...s left engine to go to ground idle settings IOS only Governor HiSide Rwy R Group 2 Triggers a runaway increase of right governor causing Tq and Ng indication to increase above limits IOS or engine shu...

Страница 137: ...vo FWD Group 2 FWD servo fails IOS only Servo RH Group 2 RH servo fails IOS only Servo Tail Group 2 Tail servo fails IOS only Servo Line Group 2 Servo line fails IOS only MGBP Group 2 Main Gear Box Pr...

Страница 138: ...tion illuminates IOS or activation of 2 LH fire extinguishers Fire LH ul Group 2 Engine Fire LH caption illuminates IOS only Fire RH x 1 Group 2 Engine Fire RH caption illuminates IOS or activation of...

Страница 139: ...fails the selected number of systems in the specified time window IOS only Receivers Random F Randomly fails the selected number of receivers in the specified time window If an original Garmin GNS430...

Страница 140: ...Freeze Group 1 Freezes the pitot tube and drain The respective instrument indication will get stuck at the present position IOS and pitot heat Left Seat Static Group 1 Freezes the static port IOS onl...

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