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Eclipse RatioMatic 500, System Manual

The Eclipse RatioMatic 500 System Manual is a comprehensive guide that enables users to maximize the potential of this innovative product. Available for free download on our website, this detailed manual provides easy-to-follow instructions and essential tips, ensuring a seamless experience with the Eclipse RatioMatic 500.

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Section 6.  Ice Protection 

 

Eclipse 5OO  Systems Manual 

 Copyright

 

© — Eclipse Aviation Corporation  

100

 

 Version 2.0   April 2007  

6.5.2  Defog  

In the event of a failure of the windshield heat system, a defog system is available.  It 
is controlled from the ENVIR synoptic. 

6.5.3  Pneumatic De-ice  

The airplane is equipped with pneumatically operated neoprene de-ice boots 
mounted on the leading edges of the wings and horizontal stabilizer.  There is one 
boot on each wing, separated into an inboard and outboard section; And also one 
boot on each horizontal stabilizer. 

 

 

Figure 66.

 

Leading Edge De-Ice Boot Location 

De-ice boot inflation is activated by selecting ENG/WING on center switch panel.  At 
least one engine must be running for the system to operate since engine bleed air 
inflates the boots. 

An ENG/WING ICE PROT ON status message indicates both engine anti-ice and 
wing de-ice are activated.  Normal operation of the boot de-ice system is indicated on 
the ICE protection synoptic by green leading edges on the wings and horizontal 
stabilizer on the airplane graphic display.  When the de-ice system is off, the leading 
edges are black with a white outline. 

The ACS controls the inflation/deflation cycle and monitors system pressure.  
Pneumatic air is first routed to the inboard wing and horizontal stabilizer boots, then 
to the outboard wing boots.  Each cycle takes approximately one minute.  When the 
system is switched off, the current cycle is completed and the system turns off.   

Bleed air from the engines is fed to a common de-ice manifold through pressure 
regulating shut-off valves on each engine.  A dual distribution valve in the de-ice 
manifold directs pressurized bleed air into the boots, resulting in boot inflation that 
breaks any ice accretion.  After the boots are inflated, the dual distribution valve then 
directs the pressurized air through an ejector nozzle within the manifold that creates 
suction to deflate the boots and maintain the aerodynamic profile of the leading 
edges. 

Summary of Contents for RatioMatic 500

Page 1: ...d Microphones 9 1 7 EMERGENCY EQUIPMENT 10 1 7 1 Fire Extinguisher 10 1 7 2 Emergency Exits 11 1 7 3 Oxygen 12 1 8 AIRCRAFT OVERVIEW REVIEW QUESTIONS 13 2 Avio Avionics Suite 15 2 1 GENERAL 15 2 2 AIRCRAFT COMPUTER SYSTEMS 17 2 2 1 Command and Control of systems 17 2 2 2 Performs Pilot Commands 17 2 2 3 Systems Monitoring and reporting 18 2 3 PILOT DISPLAYS 19 2 3 1 Primary Flight Displays PFD 19 ...

Page 2: ...ALERTING SYSTEM MESSAGES 50 3 9 FLIGHT CONTROLS REVIEW QUESTIONS 51 4 Landing Gear and Brakes 53 4 1 GENERAL 53 4 2 AIRCRAFT COMPUTER SYSTEMS ACS INTERFACES 54 4 3 LIMITATIONS AND SPECIFICATIONS 55 4 3 1 Airspeed Mach and Altitude Limitations 55 4 3 2 Tire Speed Limitation 55 4 3 3 Tire Pressure 55 4 3 4 Hard Landing Indicators 55 4 4 CONTROLS AND INDICATORS 56 4 4 1 Gear Handle 56 4 4 2 Emergency...

Page 3: ... 5 Cockpit Oxygen Gauge 76 5 5 6 Armrest Oxygen Panel 77 5 5 7 Blowout Disc 78 5 5 8 Oxygen Regulator 78 5 5 9 Pilot Oxygen 79 5 5 10 Cabin Passenger Oxygen 80 5 5 11 Pilot Oxygen Masks 81 5 5 12 Passenger Oxygen Masks 83 5 5 13 Emergency Operation 84 5 6 NORMAL OPERATIONS 86 5 6 1 Oxygen System Preflight 86 5 6 2 Oxygen Duration 86 5 6 3 Oxygen System Post Flight 87 5 7 ABNORMAL PROCEDURES 88 5 7...

Page 4: ... SYSTEM MESSAGES 111 6 9 ICE PROTECTION REVIEW QUESTIONS 112 7 Fuel 114 7 1 GENERAL 114 7 2 AIRCRAFT COMPUTER SYSTEM ACS INTERFACES 115 7 3 LIMITATIONS AND SPECIFICATIONS 117 7 3 1 Approved Fuel Grades 117 7 3 2 Fuel Capacities 117 7 3 3 Fuel Additives 117 7 3 4 Fuel Temperature 117 7 4 CONTROLS AND INDICATORS 118 7 4 1 MFD Fuel Display 118 7 4 2 Fuel Synoptic 120 7 5 SYSTEM DESCRIPTION 122 7 5 1 ...

Page 5: ...11 Start Cycle 148 8 3 12 Battery Start 148 8 4 CONTROLS AND INDICATORS 149 8 4 1 Engine Start Switch Panel 149 8 4 2 Throttle Quadrant 150 8 4 3 Engine Controls 150 8 4 4 Continuous Ignition 150 8 4 5 Engine Instrument Display on MFD 151 8 4 6 Engine ENG Synoptic 151 8 4 7 N1 RPM 154 8 4 8 Indicated Turbine Temperature ITT 155 8 4 9 N2 RPM 156 8 4 10 Fuel Flow 157 8 4 11 Oil Pressure 157 8 4 12 O...

Page 6: ...FT 189 9 4 4 Pressurization Synoptic 191 9 5 SYSTEM DESCRIPTION 193 9 5 1 Bleed Air Supply System BASS 193 9 5 2 Cabin Air Distribution 197 9 5 3 Air Conditioning 204 9 5 4 Pressurization 207 9 6 NORMAL OPERATIONS 211 9 7 ABNORMAL PROCEDURES 212 9 8 COLD WEATHER OPERATIONS TEMPERATURE SENSOR INDICATIONS 212 9 8 1 Single Engine Operations 212 9 9 CREW ALERTING SYSTEM MESSAGES 213 9 10 CLIMATE CONTR...

Page 7: ... Lower Cabin Wash Lighting Optional 252 11 5 7 Cabin Reading Lights 253 11 5 8 Baggage Compartment Lights 254 11 6 NORMAL OPERATIONS 255 11 6 1 Cabin Override Switch 255 11 7 ABNORMAL PROCEDURES 256 11 8 CREW ALERTING SYSTEM MESSAGES 257 11 9 INTERIOR LIGHTING REVIEW QUESTIONS 258 12 Exterior Lighting 260 12 1 GENERAL 260 12 2 AIRCRAFT COMPUTER SYSTEM ACS INTERFACES 262 12 3 LIMITATIONS AND SPECIF...

Page 8: ...mal Mode 293 14 3 3 Tile 1 Flight Mode Annunciation FMA 294 14 3 4 Tile 2 Attitude Direction Indicator Primary Flight Information 295 14 3 5 Tile 3 Primary Secondary NAV Source Selection Data block and Left Line Select Keys 313 14 3 6 Tile 4 Horizontal Situation Indicator HSI and Overlays 316 14 3 7 Tile 5 Communication Navigation Surveillance Display Data Block and Right Line Select Keys 323 14 4...

Page 9: ...5 9 4 Function Group 394 15 9 5 Alpha Group 395 15 9 6 Numerical Group 395 15 9 7 COM NAV Group 395 15 9 8 Cursor Control Device Joystick 397 15 10 NORMAL OPERATIONS 398 15 11 ABNORMAL PROCEDURES 399 15 11 1 MFD Failure 399 15 12 CREW ALERTING SYSTEM MESSAGES 400 15 13 TAKEOFF CONFIGURATION WARNINGS 400 15 14 MFD REVIEW QUESTIONS 402 16 Autoflight 405 16 1 GENERAL 405 16 2 AIRCRAFT COMPUTER SYSTEM...

Page 10: ...07 16 6 2 Before Takeoff 426 16 7 ABNORMAL PROCEDURES 432 16 7 1 Uncommanded Autopilot Mode Change 432 16 7 2 Pitch Mistrim 432 16 7 3 Stall Protection or Stick Pusher Failure 432 16 7 4 Autopilot and Yaw Damper Failure 432 16 8 CREW ALERTING SYSTEM MESSAGES 433 16 9 AUTOFLIGHT REVIEW QUESTIONS 435 Index 1 ...

Page 11: ...re 20 Line Select Key 28 Figure 21 Rocker Key 28 Figure 22 Primary Function Keys 29 Figure 23 Concentric Knobs 30 Figure 24 Single Rotary Knob 31 3 Flight Controls 35 Figure 25 Flight Controls Schematic 35 Figure 26 ACS Flap Interface 36 Figure 27 ACS Trim Interface 37 Figure 28 Sidestick 39 Figure 29 Throttle Quadrant 40 Figure 30 FLCS Synoptic Flight Controls 41 Figure 31 Flap Position Normal 43...

Page 12: ...n 100 Figure 67 Engine Inlet Anti Ice 101 Figure 68 Wing Inspection Light Location 102 Figure 69 Windshield Overheat 104 Figure 70 Windshield Heat Failure 105 Figure 71 Wing De Ice Failure 106 Figure 72 Engine Anti Ice Failure 107 Figure 73 Pitot AOA Probe Failure 108 Figure 74 Windshield Heat Sensor Fault 109 7 Fuel 114 Figure 75 Fuel ACS Interface 116 Figure 76 MFD Fuel Display 118 Figure 77 Sum...

Page 13: ...e Indicator Engine Pylon 173 9 Climate Control 182 Figure 118 Climate Control System Overview 183 Figure 119 Climate Control System ACS Interface 185 Figure 120 Cabin Air Sub Panel 187 Figure 121 MFD Pressurization Display 188 Figure 122 Environmental Synoptic 189 Figure 123 Pressurization Synoptic 191 Figure 124 Pylon Bleed Air Schematic 193 Figure 125 Cabin Air Distribution Components 197 Figure...

Page 14: ...ting Left Side View 261 Figure 161 Exterior Lighting ACS Interfaces 263 Figure 162 Center SWITCH Panel Standard 265 13 Air Data 274 Figure 163 Pitot AOA Pitot Static and Static Ports 274 Figure 164 Air Data ACS Interface 276 Figure 165 Pitot AOA Probe Left Side 280 Figure 166 Pitot AOA Inlet Locations 280 Figure 167 Dual Static Port Left Side 281 Figure 168 Pitot Static Probe 281 Figure 169 Pitot ...

Page 15: ...0 Heading Window 320 Figure 211 Heading Bug 321 Figure 212 Projected Track Indicator 321 Figure 213 Course Selection 322 Figure 214 Tile 5 Communication Navigation Surveillance 323 Figure 215 Tile 5 Data Block 323 Figure 216 COM Radio Tuning 328 Figure 217 Primary NAV Source Selection VLOC 330 Figure 218 Primary NAV Source Selection FMS 331 Figure 219 Secondary NAV Source Selection VLOC 331 Figure...

Page 16: ...ge 377 Figure 264 Co Pilot Audio Synoptic Page 377 Figure 265 Keyboard Audio Control 379 Figure 266 OPS Synoptic Page 381 Figure 267 OPS Weights Synoptic Page 382 Figure 268 OPS VSPEED Synoptic Page 384 Figure 269 OPS VSPEED Manual VR Entry 385 Figure 270 OPS Systems Test 387 Figure 271 SENSOR Synoptic Page 389 Figure 272 SETUP Synoptic Page 390 Figure 273 Keyboard 391 Figure 274 Keyboard Composit...

Page 17: ...Pressure 145 Table 13 Normalized Indicated Oil Pressure 145 Table 14 Fuel Temperature 146 Table 15 Oil Pressure Amber and Red Indications 158 Table 16 Oil Temperature CAS Delay Time 160 Table 17 Engine Chip Color Indications 160 Table 18 Impending Bypass Color Indications 161 Table 19 Start Motoring Modes 174 Table 20 Engine CAS Messages 178 9 Climate Control 182 Table 21 Air Source Switch Selecti...

Page 18: ...ti Function Display MFD 348 Table 37 Synoptic Pages and Features 375 Table 38 MFD CAS Messages 400 Table 39 Takeoff Configuration Warnings 400 16 Autoflight 405 Table 40 Lateral Flight Mode Annunciations 413 Table 41 Vertical Flight Mode Annunciations 413 Table 42 Approach Flight Mode Annunciations 413 Table 43 Autothrottle Speed Flight Mode Annunciations 414 Table 44 Overspeed Protection Based on...

Page 19: ...Table of Contents Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 xix THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 20: ......

Page 21: ...light controls that do not require hydraulics except for the master brake cylinders In general the management of the Eclipse 500 is divided into four functional areas 1 Avio Integration ACS and PFD 2 Thrust Control Throttles and Engine Control Systems 3 Emergency Controls Left Switch Panel Hard Switches 4 Flight Controls Mechanical Flight Control System The avionics system on the Eclipse 500 provi...

Page 22: ...Section 1 Aircraft Overview Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 2 Version 2 0 April 2007 Figure 1 Eclipse 500 ...

Page 23: ...Section 1 Aircraft Overview Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 3 1 2 Aircraft Dimensions Figure 2 Aircraft Dimensions Figure 3 Cabin Dimensions ...

Page 24: ...onal space Removal of seats is accomplished by pulling four release wires at the base of each seat Doing so releases the seat base from the tracks it can then be slid forward and removed For ease of entry and stowing baggage passenger seats have a lever on the aisle facing side that allows the seats to fold forward To return the seats to the upright position push the seatback up and aft until it l...

Page 25: ...Section 1 Aircraft Overview Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 5 Figure 6 Four Seat Configuration ...

Page 26: ...tion 90 NBAA IFR Range 4 Occupants at high speed 200 lb Pilot 3 170 lb Passengers 1 155 nm VSO Stall Speed landing configuration 70 Time to Climb 35 000 ft 19 min Vo Operating maneuvering speed 180 Max Climb rate Both Engines Takeoff Power 3 314 fpm VMO Max Operating Limit Speed 275 Single engine climb rate 888 fpm MMO Max Operating Mach Number 0 64 M VFE Flaps TO 200 VFE Flaps LDG 120 VLE 275 VLO...

Page 27: ...Max Ramp Weight 5 800 lbs Height 50 in Max Landing Weight 5 415 lbs Width 56 in Max Takeoff Weight 5 760 lbs Aisle Width 9 in Max Zero fuel Weight 4 860 lbs Luggage Area 16 ft3 260 lbs Useful Load 2 266 lbs Operating Pressure 8 000 ft cabin 41 000 ft 8 33 psi Total Fuel Capacity 1 540 lbs Pressurized Volume 240 ft3 Total Useable Fuel 1 516 lbs Wing Power Plant Wing Span 37 4 ft Two Pratt Whitney 6...

Page 28: ...verage turbojet engine The control of thrust in the Eclipse 500 does not require Avio in order to continue to operate The engine thrust control has three basic elements 1 Throttles 2 Full Authority Digital Engine Control FADEC units 3 Fuel Metering Units FMUs The use of dual FADEC channels increases redundancy and heath monitoring capability Thrust is manually set using two throttles or automatica...

Page 29: ...rols the audio sent to the Copilot s speaker in the same manner as the Pilots controls Speaker functionality is outlined in Section 15 9 Keyboard 1 6 2 Handheld Microphones There are two hand held microphones Pilot s and Copilot s Each handheld microphone has a built in Push To Talk switch There is a separate handheld microphone jack on each of the flight crew s armrests so that the handheld micro...

Page 30: ... rated halon fire extinguisher is located below the throttle quadrant The safety pin should be checked prior to flight and may be retained with a plastic band to prevent inadvertent fire extinguisher activation The halon extinguishing agent may make breathing difficult and use of the fire extinguisher should be accompanied with the use of an oxygen mask and smoke goggles if available Figure 7 Fire...

Page 31: ...mergency exit located on the right side of the aircraft to be used in the event that the primary left side exit is rendered unavailable This door weighs approximately 12 lbs To open the door Remove the cover Pull the red handle to release the door Pull the door in to rotate approximately 90 Place door through exit hatch and discard on aircraft wing Figure 8 Emergency Exit ...

Page 32: ...of cabin pressurization or presence of smoke or fumes in the cockpit The Eclipse 500 is equipped with either a 22 cubic foot oxygen bottle or an optional 40 cubic foot oxygen bottle The 40 cubic foot bottle option also includes a right pilot seat quick donning mask There are four constant flow oxygen masks for the rear passenger seats as well as a constant flow oxygen mask for the right front pass...

Page 33: ...anium d Aluminum 3 Describe how to remove seats from the Eclipse 500 4 The useful load of the Eclipse 500 is a 2 250 lbs b 2 500 lbs c 2 266 lbs d None of the above 5 Maximum Zero Fuel Weight is a 5 000 lbs b 4 000 lbs c 4 860 lbs d None of the above 6 The maximum operating altitude for the Eclipse 500 is a FL 250 b FL 500 c FL 250 d FL 410 7 The design life of the Eclipse 500 is 20 000 hours or a...

Page 34: ...5OO Systems Manual Copyright Eclipse Aviation Corporation 14 Version 2 0 April 2007 c d 10 In the optional configuration what is the maximum seating capacity of the Eclipse 500 including both front pilot seats a Five b Six c Seven d Four ...

Page 35: ...Generation Distribution While there are five functional areas the two Primary Flight Displays PFDs and two Aircraft Computer Systems ACS are considered the pillars of the avionics system Through a series of 30 data busses that interconnect all components of the avionics many of the operations of the aircraft are routed through a combination of these four components Data busses are electrical paths...

Page 36: ...ed Aircraft Systems Center Pedestal Engine Start Switches Left Sidestick Right Sidestick ACS PFD Communications Bus Left Byteflight Bus Right Byteflight Bus ACS Aircraft Systems Buses ACS PFD Communications Bus ACS Aircraft Systems Buses THE FIVE MAJOR FUNCTIONAL AREAS OF AVIO Aircraft Computer Systems Pilot Displays Pilot Controls Primary Sensors Aircraft Subsystems Left ACS Aircraft Systems Righ...

Page 37: ...e control system FADEC Fully Automated Digital Engine Control The engine demands that fuel control decision to the engine must be made many times per second each time taking into account a range of aircraft parameters such as outside air temperature air speed and altitude In cases like this the pilot is informed of overall performance Indicated Turbine Temperature ITT N1 and N2 turbine speeds and ...

Page 38: ...surization and climate control system monitoring temperature sensors valves Trim monitoring trim motor the current state and position of primary and secondary flight controls flaps trims control surfaces Landing gear monitoring gear position actuator operation Ice Protection monitoring operation of anti ice and deice system components Door indication monitoring state of main cabin door Brake syste...

Page 39: ...tion and route it to the MFD for display In addition the PFDs provide the following display and control functionality The PFDs are outlined in detail in the PFD chapter of this manual 1 Airspeed Mach Display 2 Altitude and Vertical Speed Display 3 Autopilot Yaw Damper Mode Display 4 Baro Correction Display 5 Autopilot Targets Display a Airspeed b Attitude Flight Director Command Bars c Altitude d ...

Page 40: ...t needs to be aware of or that he she has control over Less significant information such as vent lines and other data not required to diagnose system state or performance is excluded to prevent clutter System synoptic layouts are designed around operational control of the system and while similar are not representative of actual system layout The MFD provides the following display and control func...

Page 41: ...nterface to aircraft systems and as a means of routing commands from other pilot control interfaces to the ACS Direct pilot controls include Landing Light Taxi Recognition Lights Landing Gear Strobe Beacon Lights Ice Protection Engine Anti Ice Wing Deice Ice Inspection Light Cabin Lights Dome Light Footwell Lights Optional Cockpit Dimming Night Day Switch Command Routing Autopilot Control Panel En...

Page 42: ... START Initiates Start Sequence position for normal operations CONT IGN Manually activates igniters Figure 13 Engine Start Switch Panel c Autopilot Control Panel Autopilot Control Panel inputs are routed through the center switch panel to the PFD and on to the ACS The Autopilot Control Panel allows control of the following functions Autoflight mode and pre select bug control Barometer Setting BARO...

Page 43: ... to talk switch that is directly wired its respective PFD switch inputs from each sidestick are routed through the center switch panel to the PFD and on to the ACS The left and right sidesticks allow for the following functionality All Interrupt Switch Autopilot Disconnect Transponder IDENT Microphone push to talk Pitch and Roll Trim Landing Gear Warning Mute Figure 15 Sidestick ...

Page 44: ...nd do NOT require ACS control to function The item that requires ACS functionality to operate is the CABIN AIR SOURCE switch that controls the position of the flow control valves Left switch panel functionality includes Communications selections headset mask Left or Right PFD Mechanical Circuit Breakers Left PFD Left ACS ELT Switch and Annunciation Five Electrical Contactor Switches Generators x2 ...

Page 45: ...lipse Aviation Corporation Version 2 0 April 2007 25 f Right Switch Panel Optional The right switch panel contains the same communications selections available on the left switch panel Communications selections headset mask Left or Right PFD Figure 17 Right Switch Panel ...

Page 46: ...nputs are routed directly to the PFDs All control functions with the exception of some PFD composite mode functionality can be accessed elsewhere on the flight deck The keyboard supports the following Audio Selection and Control Communication Radio Selection and Control Flight Management System FMS Functions Future Functionality Alphanumeric Entry of waypoints and Radio Frequencies Synoptic Page S...

Page 47: ... position sensors for each throttle is sent directly to the FADEC Units Rudder trim flap selector autothrottle disconnect and TOGA switch position information is sent through the center switch panel to the PFDs then on to the ACS Figure 19 Throttle Quadrant i Line Select Keys Line select keys on the PFD and MFD allow control of various aircraft inputs including frequency entry and system control E...

Page 48: ...several pages at the bottom of the lower right and lower left tiles of the PFD and MFD These keys can be pressed once to move the selected page left or right Holding down the key allows slow steady scrolling through the available pages Scrolling is not a looping function and once the end of a particular set of pages is reached the pilot must scroll back to return to the first page in the sequence ...

Page 49: ...ure the lower two tiles of the MFD as follows MAP Lower left set to MAP lower right is set to page previously on lower left FMS Lower left tile set to FMS lower right tile set to MAP CKLST Lower left tile set to Checklists lower right tile set to the associated system synoptic page SYS Lower left set to last used systems synoptic page or if last page not known to the first page in the tabbed list ...

Page 50: ... down menu rotating the outer knob moves the curser from field to field Rotating the inner knob will scroll through drop down menu choices when shown and selections are made by pressing the inner knob Rotating the outer knob with the drop down menu choices displayed will cancel the drop down menu Sequential Choice Selection When a display allows sequential choices in a field such as environmental ...

Page 51: ... provided to the ACS by two Integrated Sensor Suites ISS An ISS is comprised of three independent units working together 1 Three Air Data Computers ADC 2 Two Attitude Heading and Reference Systems AHRS a Two Magnetometers MAGs 3 Two Global Positioning Systems GPS Information from all three of these systems is sent to the ACS for comparison and failure monitoring to FADECs for engine control and to...

Page 52: ...pages Exceptions to this are Oxygen controlled on the left switch panel Landing Gear controlled through the center switch panel and Autoflight controlled through the autopilot control panel While most aircraft systems functions are shared between the ACS units there are some that are routed through a specific on side ACS Flap and landing gear actuators are controlled by the onside ACS i e left ACS...

Page 53: ...List and briefly describe the three functions of the Aircraft Computer Systems ACS a b c 3 The ACS controls what function of the two aircraft engines 4 What information is NOT displayed on the upper portion of the MFD a Landing Gear Position b Oil Temperature c Oil Pressure d Fuel Level 5 How do signals from the center switch panel get to the Aircraft Computer System a Through the autopilot contro...

Page 54: ...me control of the cockpit speakers b They allow the pilot to move from page to page on both the PFD and MFD c Rocker keys allow the pilot to dim the PFD and MFD display d None of the above 9 What is the purpose of the primary function keys located below the MFD a They allow the pilot to quickly access frequently used MFD functions b They are used as a backup to the rocker keys c Both A B d None of...

Page 55: ...flight controls is electrically powered Elevator and aileron trim is controlled by a four position switch on the top of each sidestick Rudder trim is controlled by a rotary switch mounted on the aft portion of the center pedestal Trim position for all three axes is displayed on the MFD If a normal trim control fails all three trim systems can be controlled using the flight controls synoptic page o...

Page 56: ... selected by the pilot using the flap selector switch on the throttle quadrant The ACS also monitors each actuator for actual position versus the pilot selected position as well as monitoring the status of each actuator for failure The left flap actuators receive their commands and report their status to the right ACS while the right flap actuators receive their commands and report their status to...

Page 57: ...are made through the rudder trim switch on the throttle quadrant The ACS commands the actuators based on these pilot inputs The left ACS is responsible for commanding and monitoring the left pitch trim and roll trim motors while the right ACS is responsible for commanding and monitoring the right pitch trim and yaw trim motors In addition to commanding the trim motors the ACS also receives positio...

Page 58: ...s Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 38 Version 2 0 April 2007 3 3 Limitations and Specifications 3 3 1 Wing Flaps Maximum altitude for flap extension 20 000 ft MSL VFE T O 200 KEAS LDG 120 KEAS ...

Page 59: ... director yaw damper over underspeed protection and interrupts the stick pusher and all trim while the ALL INTERRUPT switch is pressed Holding this switch down for two seconds will prompt the Flight Controls FLCS synoptic to appear on the MFD MIC Keys the headset or oxygen mask microphone GEAR MUTE Silences the landing gear warning horn for conditions when the warning horn is mutable IDENT Activat...

Page 60: ...Section 3 Flight Controls Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 40 Version 2 0 April 2007 3 4 2 Throttle Quadrant Figure 29 Throttle Quadrant ...

Page 61: ...WD or Right Wing Down RWD Rudder Left or Right Each trim position display has a green band which is the trim position range for takeoff Should trim indications become unavailable a TRIM POSITION FAULT advisory message appears and the trim pointer is removed Four line select keys provide additional control of the flight control system TRIM All trim switches aileron elevator and rudder can be disabl...

Page 62: ... to ALTERNATE ALL INTRP The ALL INTERRUPT line select key disables all interrupt switch on both sidesticks in the event that the switch fails in the all interrupt position The ALL INTRP line select key has two selections NORMAL DISABLE STALL PROT The stall protection line select key allows enabling and disabling of the stall protection system and has two selections ON OFF Pressing the stall protec...

Page 63: ...Flap Position Normal When the flap selector is moved a white box is displayed around the selected position The flap position tick mark turns magenta until the flap position agrees with the flap selector position at which point the tick turns white and the white box disappears Figure 32 In Transit to T O Position Figure 33 Flap Position Display T O Position ...

Page 64: ... Eclipse Aviation Corporation 44 Version 2 0 April 2007 If a flap failure occurs due to an actuator failure or asymmetry sensed by any flap actuator all flap movement stops the pointer remains displayed in the last position and a FLAP FAIL caution message appears ...

Page 65: ...pulleys to the control surfaces 3 5 2 Rudder Rudder deflection is accomplished through the left and right rudder pedals Pedal travel is four inches fore and aft of neutral Control inputs pass from the rudder pedals to the rudder control surface through a series of cables pushrods and other associated components Figure 34 Rudder Pedals Rudder pedals are individually adjustable fore and aft 1 75 inc...

Page 66: ...g horn for conditions when the warning horn may be muted IDENT Activates the transponder IDENT feature TRIM Activates Aileron and Elevator trim 3 5 5 Trim The aileron elevator and rudder trim are electrically operated Aileron and elevator trim are controlled by switches on each sidestick while rudder trim is controlled by a rotary switch on the throttle quadrant Inputs from the trim control switch...

Page 67: ...ized Electronics in each flap actuator monitor its position relative to the other actuators If any actuator senses or causes a flap position mismatch greater than two degrees all flap motion ceases and a FLAP FAIL caution message appears If flap asymmetry is sensed on the ground the ACS automatically attempts to synchronize the flaps If flap synchronize is unsuccessful a FLAP FAIL caution message ...

Page 68: ...tch to avoid introducing unwanted roll Moving the sidestick toward the left commands a left bank while moving the sidestick toward the right commands a right bank On the ground the sidestick is full forward as the static position of the elevators is full down As airspeed increases during the takeoff roll the elevators and sidestick assume a neutral pitch position before rotation TRIM Aileron and p...

Page 69: ...that the left and right elevator tabs differ in position a ELEVATOR TRIM TAB SPLIT advisory message appears Re synchronizing the tabs is accomplished by making small trim inputs 3 7 3 Alternate Trim In the event of a failure of a normal sidestick or rudder switch trim control a L R SIDESTICK TRIM FAULT or RUDDER TRIM FAULT advisory message appears and alternate trim must be selected This is accomp...

Page 70: ...ion FLAP POSITION HOLD FAIL Backdrive clutch failed actuator motor will actively try to keep flaps in position Caution RUDDER TRIM FAIL Rudder trim actuator not responding normally to input or has failed Caution L R ALL INTERRUPT FAULT Left or right all interrupt switch has failed ground only Advisory ELEVATOR TRIM TAB SPLIT Left and right elevator trim tabs differ in position Advisory RUDDER TRIM...

Page 71: ... interfaces a b 3 The trim system on the Eclipse 500 is best described as a Electrically powered and operated b Manually powered via a mechanically operated trim wheel c Pitch trim is electronically powered aileron and rudder trim are both powered manually via a mechanically operated trim wheel d None of the above 4 The flaps on the Eclipse 500 are best described as a Hydraulically powered fowler ...

Page 72: ...h respective trim axis c The trim can ONLY be adjusted on the sidestick d None of the above 10 The FLAP FAIL caution message is displayed when a A flap position mismatch of more than two degrees has occurred b If flaps cannot be extended electrically c If the pilot selects the LDG flap position during the before takeoff checklist d None of the above 11 What MFD synoptic page will be displayed when...

Page 73: ...able rudder pedals Extension and retraction is accomplished by three electrically powered actuators Mechanical brakes on the gear actuator motors hold the gear in the retracted position These mechanical brakes also hold the gear in the extended position with the aid of over center braces These actuator brakes are capable of supporting the gear throughout the flight envelope Normal extension takes ...

Page 74: ... for status display on the MFD Emergency extension of the landing gear is a direct mechanical release and does not require ACS control to accomplish There is a emergency landing gear handle proximity switch that is monitored by the ACS that reports if the emergency gear handle remains extended following an emergency gear extension Center Switch Panel Right PFD Left ISS Left ACS L KBD Autopilot Con...

Page 75: ...rspeed Mach and Altitude Limitations Maximum Gear Speed VLO 200 KEAS VLE 275 KEAS 4 3 2 Tire Speed Limitation Maximum Speed 139 Knots Ground Speed 4 3 3 Tire Pressure Main Gear 103 2 PSI Nose Gear 70 2 PSI 4 3 4 Hard Landing Indicators A maintenance inspection of the landing gear is required before takeoff if any hard landing indicator shows evidence of a hard landing ...

Page 76: ...OO Systems Manual Copyright Eclipse Aviation Corporation 56 Version 2 0 April 2007 4 4 Controls and Indicators 4 4 1 Gear Handle Figure 38 Gear Handle Location 4 4 2 Emergency Gear Release Handle Figure 39 Emergency Gear Release Handle Location ...

Page 77: ...ation Corporation Version 2 0 April 2007 57 4 4 3 Landing Gear Position Annunciation A position annunciation for each gear is displayed on the upper portion of the MFD Figure 40 Landing Gear Position Annunciation A green circle with white border indicates the gear is Down and Locked ...

Page 78: ...hite squares will disappear NOTE During composite mode operation on the PFD when gear is displayed on the upper right hand portion of the PFD gear Up and Stowed position annunciation does not disappear after ten seconds If any indicator is not Up and Stowed or Down and Locked the entire display stays in view and the failed gear is indicated with amber hatched squares If any gear is in transit for ...

Page 79: ...Section 4 Landing Gear and Brakes Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 59 ...

Page 80: ...ted the wheel and tire assemblies are not enclosed and protrude from the wheel well approximately 1 2 inch Fairings on the outer hubs make the wheels aerodynamically clean The main gear is held in the retracted position by mechanical brakes on the actuator motors and in the extended position by the actuator brakes and over center folding braces Each main gear assembly has three proximity sensors D...

Page 81: ...Gear 4 5 3 Landing Gear Actuators The main gear and nose gear have electromechanical actuators that retract to extend the gear and extend to retract the gear This design provides minimum exposure of the extended portion of the actuator to the elements for increased reliability Each actuator assembly consists of a ball screw actuator an electric motor and a mechanical actuator brake 4 5 4 Landing G...

Page 82: ...nceable for conditions 1 and 2 The warning can be silenced for condition 3 with the GEAR MUTE button on either sidestick 4 5 6 Nose Wheel Steering Nose wheel steering operates through mechanical linkage With weight on the nose gear a steering lever at the top of the nose gear engages a mating lever attached to the rudder pedals When the gear is retracted and weight is off the nose wheel the steeri...

Page 83: ...pulling the parking brake handle on the center pedestal This moves a mechanical lever on the parking brake cylinder which traps pressure between the parking brake cylinder and the wheel brakes When the parking brake is set the valve handle position is sensed by a proximity switch that triggers a PARKING BRAKE status message The parking brake is released by pushing in the parking brake handle If th...

Page 84: ...ipse Aviation Corporation 64 Version 2 0 April 2007 Figure 44 Nose Gear Hard Landing Indicator Figure 45 Main Gear Hard Landing Indicator NOTE If a hard landing is indicated by either the split ring or tab a maintenance inspection of the landing gear is required before flight ...

Page 85: ...s into the wheel well the two nose gear doors close along with an aft strut mounted door When each gear moves to the gear up proximity sensor the gear position annunciation changes from amber hatched In Transit to white bordered Up and Stowed If all gear indicate Up and Stowed for ten seconds the white borders and the word Gear disappear 4 6 2 Gear Extension When the gear handle is placed in the D...

Page 86: ...le The Emergency Gear Extension procedure is 1 Put the gear handle in the DOWN position 2 Reduce airspeed to between 195 and 200 knots 3 Open the emergency release handle door and pull the emergency release handle up and aft This causes two things to happen A proximity switch sends a signal to the ACS to remove electrical power from the three gear actuator motors At full throw the emergency gear h...

Page 87: ...rting System Messages Table 4 Landing Gear CAS Messages Message Condition Category EMER GEAR HANDLE Emergency gear handle is not stowed Caution LANDING GEAR FAIL Landing gear system failure Caution BRAKE FLUID LOW Low brake fluid Advisory WOW SENSOR FAULT Weight on wheels sensors disagree Advisory PARKING BRAKE Parking brake is set Status ...

Page 88: ...oors locking closed d Aerodynamic forces generated within the landing gear wells 4 Nose wheel steering is accomplished by a A nose wheel steering motor which is controlled by the ACS when the pilot engages the nose wheel steering switch b Mechanical linkages between the nose wheel and the rudder pedals c Mechanical linkages between a tiller and the nose wheel d Differential braking with a free cas...

Page 89: ...heck the tire pressure before the next flight 11 What holds the landing gear in the down extended position a The landing gear actuator brakes b Over center folding braces c Continuous mechanical pressure from the landing gear actuator motors d Both A and B are correct 12 What will happen if the landing gear is in transit for longer than 15 seconds a A LANDING GEAR FAIL caution message is displayed...

Page 90: ...opyright Eclipse Aviation Corporation 70 Version 2 0 April 2007 15 What indicates that the brake pads are worn 16 What does the PARKING BRAKE status message indicate 17 What might I expect to see on the MFD landing gear indicator in high G maneuvers Ex steep turns ...

Page 91: ...nd connected to an outlet in the left armrest The right pilot seat is fitted with a constant flow mask contained behind a door on the lower right side of the instrument panel In addition the right pilot seat is optionally fitted with a quick donning diluter demand mask located on the top right portion of the right pilot seat Two constant flow mask containers are located in the ceiling of the cabin...

Page 92: ...gen to the passenger masks When oxygen pressure decreases below 46 4 PSI the switch triggers an OXYGEN PRESSURE warning message This message will disappear once the oxygen pressure increases to 60 PSI Center Switch Panel Right PFD Left ISS Left ACS L KBD Autopilot Control Panel Left PFD Optional R KBD MFD Right ISS Engine Start Switches ACS PFD Communications Bus Left Byteflight Bus Right Byteflig...

Page 93: ...tle Pressure 200 psi NOTE The minimum pressure for oxygen regulator operation is 200 psi Refer to the Aircraft Flight Manual oxygen duration chart for the oxygen requirement for a particular flight 5 3 2 Oxygen Type The oxygen system must be serviced with aviation grade oxygen to avoid freezing and or malfunction of the oxygen system 5 3 3 Oxygen System Activation AUTO Oxygen System Activation 14 ...

Page 94: ...rols Figure 47 Oxygen Panel Location OXYGEN CONTROL KNOB ON Oxygen system is on pressure regulated oxygen is available OFF Oxygen system is off PASSENGER MASK SELECTOR OFF Oxygen system is off AUTO Passenger masks automatically deploy at 14 000 foot cabin altitude DROP Passenger masks deploy immediately OXYGEN BOTTLE PRESSURE GAUGE Oxygen bottle pressure ...

Page 95: ...ight pilot seat Four passenger masks 5 5 2 Optional Configuration 40 cubic foot oxygen bottle and regulator assembly Quick don diluter demand oxygen mask on the left pilot seat Quick don diluter demand oxygen mask on the right pilot seat Five constant flow oxygen masks One passenger mask at the right pilot seat Four passenger masks 5 5 3 Oxygen Bottle The airplane is equipped with either a 22 cubi...

Page 96: ...indicated by a red band Instrument Caution Range Yellow Normal Range Green Max Limit Red Oxygen Pressure psi 0 300 psi 1 550 1 850 psi 1 850 psi Full Scale 5 5 5 Cockpit Oxygen Gauge Oxygen bottle pressure can also be read on a gauge on the left switch panel The caution range and maximum limit pressures are indicated differently than the exterior service panel gauge A low oxygen pressure of 0 200 ...

Page 97: ...e Aviation Corporation Version 2 0 April 2007 77 Figure 50 Cockpit Oxygen Pressure Gauge 5 5 6 Armrest Oxygen Panel The pilot quick don mask oxygen hose and oxygen mask microphone are connected via the left and right armrest panels Figure 51 Armrest Oxygen Panel ...

Page 98: ... an overpressure has occurred or that the oxygen system has been improperly serviced A ruptured disc requires maintenance action before flight Figure 52 Blowout Disc Location CAUTION Always provide 24 inches of free space perpendicular to disk during aircraft preflight 5 5 8 Oxygen Regulator An oxygen regulator is connected to the oxygen cylinder to reduce oxygen pressure to the pilot and passenge...

Page 99: ...the oxygen control knob is in the ON position low pressure oxygen from the regulator flows to the pilot oxygen mask s To use the system the pilot need only don the oxygen mask and breathe Oxygen pressure is confirmed by a green flag on the crew mask hose Figure 53 Oxygen Control Knob Activation Figure 54 Crew Mask Hose Flow Indicator ...

Page 100: ...ne of two ways Electrically by a solenoid triggered by the 14 000 foot cabin altitude switch Mechanically by selecting DROP with the PASSENGER MASK selector NOTE The pilot can deploy the mask at any time without electrical power using this mode When cabin altitude decreases to 10 000 feet the altitude switch resets the solenoid valve and oxygen flow ceases to the passenger masks However if the mas...

Page 101: ...e mask With no oxygen supply a red indicator will be displayed When stowed the mask should be set in 100 with the harness packed in accordance with the packing instructions located within the mask stowage cup Figure 56 Pilot Quick Don Mask Location Donning the mask is accomplished by removing the mask from the seat mounted compartment and squeezing a red lever on the side of the regulator This inf...

Page 102: ...ion NORMAL Regulator supplies a mixture of oxygen and ambient cabin air Oxygen flow is on demand 100 Regulator supplies 100 oxygen with no ambient cabin air Oxygen flow is on demand NOTE It is recommended that the mask be stored set on this mode EMERGENCY 100 oxygen is delivered under pressure This mode is automatically active at 34 000 feet cabin altitude regardless of the setting on the mask Mas...

Page 103: ...he system either because low cabin pressure cabin altitude 14 000 feet and above triggers the cabin oxygen valve solenoid or because the pilot selects DROP on the PASSENGER MASK selector A pin release mechanism is attached to the mask by a lanyard When the mask is pulled the lanyard pin is released and oxygen flows to the mask A green flow indicator appears in a clear section of the hose to indica...

Page 104: ...n altitude exceeds 12 750 feet MSL an aural alert Mask On Descend will sound every 30 seconds until the cabin altitude descends below 12 500 feet or if the cabin altitude is descending at 1 800 fpm or greater If cabin altitude exceeds 14 000 feet MSL with the oxygen control knob in the ON position and the passenger oxygen selector in AUTO the cabin pressure altitude switch will open the passenger ...

Page 105: ... passenger oxygen by moving the PASSENGER MASK selector to the DROP position This bypasses the solenoid valve and mechanically opens the oxygen valve The PASSENGER MASK selector does not require electrical power to operate To assure oxygen flow to masks check the green flow indicator located in the mask lines and verify the pin is pulled to initiate the flow of oxygen to the masks ...

Page 106: ... one pilot wear an oxygen mask and use oxygen above FL350 Operations under 14 CFR Part 91 require a 10 minute supply of oxygen for all passengers in the event of a cabin depressurization The 22 cubic foot bottle meets this requirement Operations under 14 CFR Part 135 require a two hour supply of oxygen for each crew member and a 10 minute supply for all passengers The 40 cubic foot bottle meets th...

Page 107: ...cy Descent Requirement 10 min LITERS 30 Minute Rule for Passenger Oxygen Reserve Above 15K ft LITERS Single Pilot Cruise Consumption Above 25K ft Mask in NORM LITERS Maximum Oxygen Consumption Time Above 25K ft for Pilot Mask in NORM MINUTES 0 1 1005 2 32 32 84 0 00 969 84 444 88 1 1 1005 2 32 32 84 139 88 829 965 380 72 2 1 1005 2 32 32 84 279 75 690 09 316 56 3 1 1005 2 32 32 84 419 63 550 215 2...

Page 108: ...Abnormal Procedures 5 7 1 Low Oxygen Pressure The OXYGEN PRESSURE warning message appears with low pressure downstream of the oxygen regulator Thus when the oxygen system is off oxygen control knob in the OFF position with at least one engine operating or in flight the OXYGEN PRESSURE warning message is displayed ...

Page 109: ...O Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 89 5 8 Crew Alerting System Messages Table 8 Oxygen CAS Messages Message Condition Category OXYGEN PRESSURE Oxygen line pressure below 46 psi Warning ...

Page 110: ...altitude of 14 000 ft 500 500 feet 2 Label the RED GREEN and AMBER range maximum and minimum values using the diagram below 3 The purpose of the blowout disk is a To adjust cabin pressure b Indicates that an over pressurization has occurred and indicated that the bottle requires service c To prevent ice from forming in the oxygen bottle when the pressurized oxygen is released d To keep the oxygen ...

Page 111: ...owed oxygen bottle pressure is a 1800 PSI b 250 PSI c 400 PSI d 200 PSI 9 At which cabin altitude will the passenger oxygen system automatically activate a 12 750 ft b 14 000 ft c 15 000 ft d 12 500 ft 10 If selected which oxygen regulator mode will ALWAYS deliver 100 oxygen under pressure a Normal b 100 c Emergency d Oxygen is never delivered under pressure with the quick don mask 11 On the three...

Page 112: ...Section 5 Oxygen Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 92 Version 2 0 April 2007 a b ...

Page 113: ...2007 93 6 Ice Protection 6 1 General The ice protection system is comprised of the following Pneumatic de ice boots on the leading edges of the wing and horizontal stabilizer Left and right heated windshields Heated pitot Angle Of Attack AOA probes Heated pitot static probe Heated static ports Engine anti ice ...

Page 114: ...ngine The pilot selections using the ENG WING switch on the center switch panel are sent through the PFD to the ACS which in turn controls inflation and deflation of the boots and routing of air to the engine inlets by turning on and off applicable Electronic Circuit Breakers ECBs The ECBs for the ice protection system are located within the Aft Power Distribution Center in Electronic Circuit Brea...

Page 115: ...ations Bus Left Byteflight Bus Right Byteflight Bus ACS PFD Communications Bus ECBU 4 Left ACS Communications Bus Sensor Information to ACS Right ACS Right ACS Communications Bus Left PRSOV 1 Outboard Deice 1 Right PRSOV 2 Sensors 6 Total Sensors Left Engine Press and Temp Right Engine Press and Temp Wing Boots Press x 2 Sensor Information to ACS Inboard Deice 1 Left PRSOV 2 Outboard Deice 2 Right...

Page 116: ...erations When operating the engines at idle speed on the ground in freezing fog and visible moisture the engine speed must be increased once every five minutes to 65 N1 to avoid ice accumulation on the spinner 6 3 2 Pneumatic De ice The use of wing deice boots is prohibited The following wing deice Electronic Circuit Breakers ECBs must be collared INBOARD WING DEICE L INBOARD WING DEICE R OUTBOARD...

Page 117: ...d Indicators 6 4 1 Center Switch Panel Ice Protection Figure 63 Center Switch Panel Ice Protection ENG WING Switch ENG WING Engine anti ice and boot de ice systems on ENG Engine anti ice system only on OFF Engine anti ice and boot de ice systems off INSP LIGHT Switch INSP LIGHT Wing inspection light on OFF Wing inspection light off ...

Page 118: ...shield overheat or failure White temperature Normal temperature range Red temperature Overheat with red OVHT PITOT STAT LINE SELECT KEY ON Pitot static heat on AUTO Automatic PROBE DISPLAY Green Probe Static heat on Amber Probe Static heat failed DE ICE BOOT DISPLAY Green De ice system on White De ice system off Amber De ice system failed Engine Display Green Engine anti ice on White Engine anti i...

Page 119: ...tream Figure 65 Windshield Heater Mat The ACS maintains the windshield temperature between 127 F and 140 F 53 C and 60 C by cycling windshield heat on and off The left and right windshield heat is powered by separate Electronic Circuit Breakers ECBs so that an electrical problem will not impact both windshields Windshield heat is controlled by two line select keys labeled L WSHLD AND R WSHLD on th...

Page 120: ... operation of the boot de ice system is indicated on the ICE protection synoptic by green leading edges on the wings and horizontal stabilizer on the airplane graphic display When the de ice system is off the leading edges are black with a white outline The ACS controls the inflation deflation cycle and monitors system pressure Pneumatic air is first routed to the inboard wing and horizontal stabi...

Page 121: ...ard Figure 67 Engine Inlet Anti Ice Engine anti ice is activated by selecting engine anti ice only ENG or both engine anti ice and wing de ice ENG WING on the center switch panel An ENG A ICE ON status message indicates only engine anti ice is activated An ENG WING ICE PROT ON status message indicates both engine anti ice and wing de ice are activated Normal operation of the engine anti ice system...

Page 122: ...lect key labeled PITOT STAT on the ICE protection synoptic The default state for PITOT STAT heat is the AUTO position Probe and port heat begins automatically cycling on when at least one engine is running On the ground probe heat can be manually activated without engines running using the PITOT STAT line select key Normal operation of the probe and static port heat is indicated on the ICE protect...

Page 123: ...und operations 6 6 2 Flight Operations In flight the pilot can activate windshield heat using the ICE protection synoptic In the event of a windshield heat failure the DEFOG feature should be used In actual and or anticipated icing conditions windshield heat and engine anti ice should be activated Constant use of engine cowl heat will prevent ice from being ingested into the engines Air data probe...

Page 124: ...verheat The appearance of a L R WSHLD OVHT warning message should be considered a false indication as windshield heat is inoperative Overheat is also indicated on the ICE protection synoptic The outline of the windshield turns amber a red OVHT message appears inside the windshield outline and the temperature display changes to red Figure 69 Windshield Overheat ...

Page 125: ...ersion 2 0 April 2007 105 6 7 2 Windshield Heat Failure If either windshield fails for a reason other than an overheat L R WSHLD HEAT FAIL caution message appears Failure is also indicated on the ICE protection synoptic by the windshield outline turning amber Figure 70 Windshield Heat Failure ...

Page 126: ...oots causes a WING DEICE FAIL caution message to appear Malfunctions include inadequate pressure for inflation boot not deflating inadequate vacuum to retain the boots against the wing when the system is off and failure of de ice manifold heat The failure is also indicated on the ICE protection synoptic by the affected wing or horizontal boot section turning amber Figure 71 Wing De Ice Failure ...

Page 127: ...uring flight causes a L R ENG A ICE FAIL caution message to appear along with the associated caution alert tone The failure is also indicated on the ICE protection synoptic by the engines cowls on the airplane graphic turning amber Figure 72 Engine Anti Ice Failure NOTE This CAS message also appears if the system is switched on and the inlet temperature sensor remains cold indicating no airflow ...

Page 128: ...FAIL L R STATIC HEAT FAIL or STBY PITOT HEAT FAIL caution message to appear along with the associated caution alert tone The failure is also indicated on the ICE protection synoptic by the probe or port turning amber Since static ports have two heating elements it is possible that only one may fail Should this occur a L R STATIC HEAT FAIL advisory message appears to alert the loss of redundancy Fi...

Page 129: ...ion 2 0 April 2007 109 6 7 6 Windshield Heat Sensor Fault A malfunction of the imbedded temperature sensors causes a L R WSHLD HEAT FAULT advisory message to appear The associated temperature display on the ICE protection synoptic appears as three red dashes Figure 74 Windshield Heat Sensor Fault ...

Page 130: ...advisory message appears and flight into icing conditions is prohibited Should this fault occur in flight wing de ice is unavailable and a WING DEICE FAIL caution appears 6 7 9 Engine Anti Ice Sensor Fault Should an engine anti ice sensor malfunction be detected on the ground an ENG ANTI ICE MON FAULT advisory message appears and flight into icing conditions is prohibited Should this fault occur i...

Page 131: ...re inoperative Caution L R WSHLD HEAT FAIL Windshield heat is inoperative Caution WING DEICE FAIL Wing deice malfunction detected Caution L R ENG A ICE VLV FAULT Engine anti ice valve is stuck open Advisory ENG ANTI ICE MON FAULT Engine anti ice sensors failed Ground Only Advisory L R STATIC HEAT FAIL Static port A or B heater is inoperative Ground Only Advisory L R WSHLD HEAT FAULT L R windshield...

Page 132: ...Only when ice is visibly present on the airframe c Only below temperatures of 40 C d None of the above 4 When should engine anti ice be used a Anytime icing conditions exist or are anticipated b Only after significant airframe ice accretion has occurred c Anti ice should only be used in the air to prevent cowl overheating d Both A and B are correct 5 On the Ice Protection Synoptic what does an amb...

Page 133: ...oard bleed air port on each engine c Conditioned bleed air from the deice manifold d Engine bleed air from the outboard bleed air port on each engine 10 What is the air source for the pneumatic boots a A compressor in the nose section inflates the boots as needed b Engine bleed air is used for boot inflation c The boots are mechanical in nature and are inflated via servo motors d None of the above...

Page 134: ... 7 1 General The fuel system is a supply pressurized wet wing design Normally each engine receives fuel from the corresponding wing tank but fuel from either wing can supply both engines through a crossfeed valve Fuel Management and balancing is automatically controlled by the ACS but can be overridden by the pilot ...

Page 135: ...electric fuel pumps and fuel system valves automatically as necessary for normal operation Sensors and components on the right side of the fuel system reports directly to the Right ACS while sensors and components on the left side reports directly to the Left ACS The pilot has direct fuel system control inputs through the FUEL synoptic on the MFD and can view system status as reported by the ACS f...

Page 136: ...Right ACS Right Side Sensors Sump Fuel Temperature Fuel Level Sensors 6 Fuel Density Sensor Low Fuel Sensor Fuel Pressure Fuel Shutoff Valve Open Closed Right ACS Communications Bus Left Electric Fuel Pump Left Fuel Shutoff Valve CLOSE Left Fuel Shutoff Valve OPEN Right Electric Fuel Pump Right Fuel Shutoff Valve CLOSE Right Fuel Shutoff Valve OPEN Left Side Sensors Sump Fuel Temperature Fuel Leve...

Page 137: ...US Gal per side NOTE 1 Usable Fuel can be safely used during all Normal Category maneuvers NOTE 2 Fuel weights are calculated at 15 C 1 US Gal 6 77 lbs NOTE 3 Un coordinated maneuvers including sideslips skids are limited to 45 seconds in duration 7 3 3 Fuel Additives Anti Icing additives meeting the following specifications are required for all operations Example Prist MIL I 27686 MIL I 85470 Phi...

Page 138: ...capacity is displayed as a horizontal green scale with caution amber indicating 280 pounds of total fuel remaining and warning red indicating 210 pounds of total fuel remaining areas on the left side Fuel quantity is indicated by a white pointer above the scale Total fuel quantity remaining in pounds is displayed above the scale The total quantity display turns amber when fuel remaining is less th...

Page 139: ...in amber if least one sump tank quantity decreases to the caution level of 140 pounds or less and red when the corresponding sump quantity decreases to less than 105 pounds Figure 77 Sump Tank Quantity Display Sump tank fuel quantities of 140 lbs and 105 lbs that turn the sump quantity display amber and red equate to the fuel quantities that trigger the FUEL QTY LOW caution and L R FUEL QTY LOW wa...

Page 140: ...nd right fuel supply lines Fuel flow for each engine Estimated fuel used and estimated fuel remaining Status of the fuel filter MEASURED FUEL QUANTITY Total fuel quantity from the gauging system is displayed at the top of the fuel synoptic along with tank quantities in both wing tanks and both sump tanks The total fuel quantity digits turn amber when total fuel quantity is below 280 lbs and red wh...

Page 141: ...stimated fuel remaining are displayed at the bottom of the fuel synoptic A snapshot of the total fuel is taken at engine start and then fuel used and fuel remaining are calculated using fuel flow Estimated fuel quantity is independent of the gauging system and serves as a backup in the event of a gauging system failure A significant difference in the estimated and gauged fuel quantity might also b...

Page 142: ...st pumps are venturi type that have no moving parts and do not require electrical power to operate Pressurized return fuel from the engines flows through the ejector boost pump venturi pulling fuel from the sump tank Return fuel is also called motive fuel since it causes the pumping action 7 5 4 Ejector Transfer Pumps An ejector transfer pump is located in each sump tank to aid gravity flow by pum...

Page 143: ...table between AUTO and ON When an electric fuel pump is operating a L R FUEL PUMP ON status message appears The pump on status message will not appear during automatic fuel balancing If low pressure is detected from an electric fuel pump a L R FUEL PUMP FAIL caution message appears and fuel crossfeed from the affected side is no longer available 7 5 6 Engine Fuel Pumps Two engine driven fuel pumps...

Page 144: ...is displayed on the fuel synoptic Should the crossfeed valve fail or not reach its commanded position a XFEED VLV FAIL advisory message appears and fuel crossfeed may not be available FUEL SHUTOFF VALVES An electric fuel shutoff valve for each engine is located in the wing root downstream of the ejector boost pumps and electric fuel pumps The valves open and close automatically during normal engin...

Page 145: ...thin each sump tank measures sump tank fuel temperature If the fuel temperature in a sump tank reaches 150 F a HOT FUEL caution message appears The sump temperature information turns amber If the fuel temperature in a sump tank reaches 170 F a HOT FUEL warning message appears The sump temperature information turns red Figure 80 Fuel Synoptic Fuel Hot Caution and Warning ...

Page 146: ...om the wing tanks into the sump tanks Since the return fuel has been heated by the fuel oil heat exchanger in the engine the return fuel serves to keep the fuel tank temperature above the fuel freeze point 7 5 12 Fuel Quantity Gauging System The fuel gauging system consists of seven capacitance gauging probes per wing Quantity and density information is sent to the ACS where the fuel quantity in p...

Page 147: ... the fuel gauging system If either sump tank fuel quantity decreases to 105 pounds useable fuel the optical sensor in that tank triggers a L R FUEL QTY LOW warning message In this case the respective sump tank quantity on the fuel synoptic turns red The low level sensors are independent of the fuel gauging system and monitored by the opposite ACS for further independence Figure 82 Fuel Synoptic Lo...

Page 148: ...e aircraft wing vents into the aft vent bay on each wing to allow equalization of tank pressure during climb Two vent lines that connect to the vent bay vent out of the aircraft on the underside of each wing allowing the vent bay proper ventilation and facilitating the equalization of pressure within the wings A third vent line is connected to a float valve that allows overflow fuel that may have ...

Page 149: ...Section 7 Fuel Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 129 Figure 83 Fuel Synoptic Low Fuel Pressure Pressure Sensor Fault ...

Page 150: ...umps fuel from the heavy wing will flow to both engines When the quantity difference is within 10 pounds the crossfeed valve closes and the electric fuel pump is switched off The rate at which an imbalance is corrected depends on engine fuel burn Normally a lateral imbalance will be corrected within 10 minutes In the event of an engine failure the automatic balance system keeps the fuel load balan...

Page 151: ... no automatic shutoff If the tank is over filled fuel will overflow onto the top of the wing Figure 84 Over wing Fuel Port Right Wing The sump tanks fill first due to the positive wing dihedral However if fueling is stopped before the sump tanks are full gravity feed may not fill the tanks In this situation the transfer ejector pumps will fill the sump tanks once the engines are started A L R FUEL...

Page 152: ...message appears Should automatic balancing continue for 15 minutes without the imbalance being corrected an AUTO BALANCE FAIL caution appears This message may be an indication of a fuel leak and EST FUEL REMAINING should be compared to total fuel quantity from the gauging systems to confirm if a leak is present If automatic balancing is inoperative the pilot can manually control fuel crossfeed usi...

Page 153: ... F Caution L R FUEL UNUSABLE Failure of internal wing fuel transfer and or trapped fuel outboard Caution FUEL BALANCE MON FAULT Later fuel balance detection is inoperative Automatic fuel balance disabled Advisory L R FUEL BYPASS FAULT Fuel filter bypass switch has malfunctioned Ground Only Advisory L R FUEL FILTER Impending fuel filter bypass detected engine running Ground Only Advisory FUEL GAUGI...

Page 154: ...m and where does the motive flow fuel originate 5 List 4 conditions that will cause the Electric Fuel Pump to AUTOMATICALLY activate a 1 ___________________________________________________ b 2 ___________________________________________________ c 3 ___________________________________________________ d 4 ___________________________________________________ 6 Fuel shutoff valves SOVs are used to cut ...

Page 155: ...ANCE FAIL caution message appears d Both B C 10 What failure s will render the automatic fuel balancing capability inoperative a Electric fuel pump failure b Ejector boost pump failure c Capacitance probe failure one or more d Both A C e All of the above 11 What is the total fuel quantity and useable fuel quantity for the Eclipse 500 12 List and describe the function of the 10 fuel pumps on the Ec...

Page 156: ...e fuel pump c They are mechanical pumps using internal gears to pump the fuel to the engine d None of the above 15 How is the fuel kept from freezing on the Eclipse 500 a Engine oil fuel heat exchangers are used to keep fuel temperatures above freezing limits b Anti icing additives must be used at all times c Both A and B 16 A FUEL QTY LOW caution message will be displayed when fuel quantity drops...

Page 157: ...nd counter rotate to reduce the effects of torque An accessory gearbox connected to the N2 rotor drives the Starter Generator fuel pumps and oil pumps The PW 610F A engines do not use thrust reversers The engines are controlled by two dual channel Full Authority Digital Engine Control FADEC units through the dual Aircraft Computer Systems ACS All engine parameters are displayed on the MFD Primary ...

Page 158: ...ction and Suppression 8 2 1 Thrust Control The primary thrust control interface for the pilot is through the two throttles located on the throttle quadrant Inputs from each throttle go directly to both FADEC units The FADEC combines these inputs with air data information received from the Integrated Sensor Suites and sets thrust by regulating fuel output from the Fuel Metering Unit FMU The FADECs ...

Page 159: ...Bus Right Byteflight Bus ACS PFD Communications Bus Right ACS Left FADEC 1A Center Pedestal Left Sidestick Right Sidestick Left FADEC 1B Right FADEC 2B Right FADEC 2A Right Throttle Left ENG Left Throttle Fuel Metering Unit Fuel Metering Unit Primary Engine Sensors N1 N2 ITT Primary Engine Sensors N1 N2 ITT Left ACS Communications Bus Right ACS Communications Bus Inter FADEC Communication Bus Prim...

Page 160: ...ACS to the FADECs and to other aircraft systems involved in or reconfigured during the engine start process Electrical Fuel Climate Control and Ice Protection During on ground engine starts the ACS also provides an automatic start abort feature If an engine start is aborted the ACS reconfigures the aircraft systems back to a power off configuration and prompts a ENG START ABORT caution message app...

Page 161: ...Section 8 Engines Fire Protection Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 141 Figure 88 Engine Starting ACS Interface ...

Page 162: ...ystem status through the PFDs to the MFD for display Sensors from the left engine send their information to the left ACS while sensors for the right engine send their information to the right ACS The engine sensors that send information to the ACS are Chip Detector Fuel Filter Impending Bypass Switch Oil Filter Impending Bypass Switch Oil Temperature Oil Pressure Fire Detection Figure 89 Secondary...

Page 163: ... of the left or right FIRE ARMED button Fire suppression is provided by a single fire suppression canister in each engine pylon This canister is controllable by and reports its status to the ACS Pressing the FIRE ARMED button once sends a signal to the ACS to remove fuel and electrical power from the engine arms the fire canister and illuminates the green ARMED portion of the FIRE ARMED button A s...

Page 164: ...OUND IDLE Continuous 46 7 min FLIGHT IDLE Continuous 52 1 min b TAKEOFF 5 minutes a 795 100 102 APR 10 minutes a 795 100 102 MAXIMUM CONTINUOUS Continuous 795 100 102 TRANSIENT 20 sec 810 102 103 a The total time during which take off thrust may be used is limited to 5 minutes The 5 minute limit commences when the throttle is first advanced to the take off position b Flight idle speeds are a funct...

Page 165: ... is first advanced to the take off position b Oil pressure See Oil Pressure Minimum and Maximum chart c During engine start or motoring cycles oil pressure of 0 0 0 PSIG is only allowable below 15 N2 Positive oil pressure is required above 15 N2 8 3 3 Oil Pressure Minimum and Maximum Table 13 Normalized Indicated Oil Pressure Green Band Yellow Band Red Band N2 ALL High Low High Low 15 100 2 0 8 0 ...

Page 166: ... 40 a 121 GROUND IDLE Continuous 40 a 121 FLIGHT IDLE Continuous 18 a 121 TAKEOFF 5 minutes a 18 121 APR 10 minutes 18 121 MAXIMUM CONTINUOUS Continuous 18 a 121 a Minimum fuel temperature limit is not applicable to ground operation 8 3 7 Fuel Temperature Limits for Engine Start Maximum engine fuel temperature for engine start 121 C 8 3 8 Engine Start Maximum Crosswind Limit 30 knots Maximum Tailw...

Page 167: ...e 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 147 8 3 10 In Flight Restart 25 000 Feet and Below Airspeed 139 234 KEAS 15 000 Feet and Below Airspeed 237 KEAS Figure 91 Starter Assisted Air Start Envelope ...

Page 168: ...less than 100 C before initiating in flight engine restart 8 3 11 Start Cycle Engine starters are limited to the following operating cool down intervals both for engine start and motoring Operating Cool Down Cycle 1 30 sec 1 min Cycle 2 30 sec 1 min Cycle 3 30 sec 30 min NOTE The cycles may be repeated as required 8 3 12 Battery Start Minimum Temperature Battery only engine start 5 C 41 F Minimum ...

Page 169: ...rporation Version 2 0 April 2007 149 8 4 Controls and Indicators 8 4 1 Engine Start Switch Panel Figure 93 Engine Start Switch Panel OFF Initiates engine shutdown sequence ON START Initiates engine start sequence Normal position when engine is operating CONT IGN Provides continuous ignition ...

Page 170: ...he ceiling directly above the throttle quadrant Other engine functions are controlled from line select keys on the ENG synoptic page Engine Start Switch Panel Start ON START Stop OFF Continuous ignition CONT IGN NOTE The switch must be pushed in to move between OFF and ON START 8 4 4 Continuous Ignition Continuous ignition is turned on by moving the rotary switch on the engine start switch panel t...

Page 171: ...07 151 8 4 5 Engine Instrument Display on MFD Figure 95 MFD Primary Engine Parameter Display Primary engine parameters are continuously displayed on the upper portion of the MFD Primary engine parameters include N1 speed and ITT tapes as well as digital readouts of N2 Fuel Flow and Oil Pressure 8 4 6 Engine ENG Synoptic ...

Page 172: ... Left dry motoring OFF Left dry motoring off R DRY MTR ON Right dry motoring OFF Right dry motoring off NOTE The L and R DRY MTR line select key selections disappear when the aircraft is in flight weight off wheels APR AUTO Automatic Power Reserve is automatically controlled OFF Automatic Power Reserve deactivated ECB LINK Selects engine circuit breakers on Electronic Circuit Breaker ECB synoptic ...

Page 173: ...r RPM tape and digital value Oil pressure tape and digital value Oil temperature tape and digital value Fuel flow tape and digital value Fuel Metering Unit FMU temperature digital value Oil filter bypass OK IMP BYP Chip detector OK DETECT The current level is indicated by a digital readout or by a moving tape gauge and a digital readout Each tape gauge display has an adjacent tape showing operatin...

Page 174: ...100 to 101 A red band begins at the maximum continuous limit of 101 The digital value and moving tape are white for N1 values in the green band in amber for N1 values in the amber band and in red for N1 values above the RPM limit If the RPM exceeds the limit for 20 seconds a L R ENG EXCEEDANCE warning message appears A blue bug and blue digital readout between the left and right N1 tapes display t...

Page 175: ... continuously displayed on the MFD with a moving tape and digital readout The ITT tape range is 0 850 C An adjacent tape displays ITT limits A green band on the limit tape extends from 300 C to the maximum continuous ITT limit The FADEC determines the maximum ITT limit and a red band is displayed beginning at that value The digital ITT value and moving tape are displayed in white for values under ...

Page 176: ...readout on the engine synoptic page The scale of the tape is 0 to 105 An adjacent tape displays N2 limits A green band on the limit tape extends from 45 to 100 An amber band extends from 100 to 102 A red band begins at the maximum continuous limit of 102 The digital value and moving tape are white for N2 values in the green band in amber for N2 values in the amber band and in red for N2 values abo...

Page 177: ... is continuously displayed on the MFD with a digital readout in pounds per hour PPH and with a white moving tape and digital readout on the engine synoptic page The scale of the tape is 0 800 PPH An adjacent tape displays fuel flow range with a green band extending from 60 PPH to the top of the tape There are no amber or red bands 8 4 11 Oil Pressure Figure 102 Oil Pressure Displays Digital and Ta...

Page 178: ...e are white If the oil pressure is in the caution amber band range either high or low the tape and digital value are amber The amber bands and the lower red band incorporate a time delay for transient conditions If the oil pressure is in the high caution range of 8 1 9 0 for greater than 5 minutes the digital value and tape turn amber and a L R OIL PRESSURE HIGH warning message appears This messag...

Page 179: ...r tape are white If the oil pressure is in the caution amber band range either high or low the tape and digital value are amber The amber bands incorporate a time delay for transient conditions If the oil temperature enters the high caution range of 135 C 140 C or the low caution range of less than 20 C the digital value and tape turn amber and a L R ENG OIL TEMP LOW or L R ENG OIL TEMP HIGH cauti...

Page 180: ...mber for 90 seconds then red Less than 20 C None immediately amber Below 40 C None immediately red 8 4 13 Engine Chip Indication Figure 105 Engine Chip Display If the ACS detects metal contamination in the oil it is displayed on the CHIP display at the bottom of the engine synoptic page The display has three states Table 17 Engine Chip Color Indications Situation Display Normal OK white Chip Detec...

Page 181: ... Oil Filter Display If the ACS detects an impending oil filter bypass a L R ENG OIL FILTER advisory message appears and an indication is displayed on the OIL FILTER display at the bottom of the engine synoptic page The display has three states Table 18 Impending Bypass Color Indications Situation Display Normal OK white Bypass Switch Failed White Oil Filter Impending Bypassed IMP BYP White ...

Page 182: ...s Manual Copyright Eclipse Aviation Corporation 162 Version 2 0 April 2007 8 4 15 Engine Fuel Temperature Figure 107 Engine Fuel Temperature Display Engine fuel temperature in the FMU is displayed on the engine synoptic with a white digital readout in C ...

Page 183: ... FADEC has full authority over the operation of the engine The FADEC sets thrust by controlling fuel flow based on throttle position Throttle position measured by potentiometers correlates to the desired engine power There are three primary operating ranges for the throttles Idle Maximum Continuous Thrust MCT and Takeoff Figure 108 Throttle Position vs Engine Power Thrust level Throttle Position D...

Page 184: ...gine however for reliability reasons the FADEC units are located in the compartment inside the pressure vessel Each engine has two FADEC cards either of which can control the engine Each set of two FADEC cards is co located with an ACS in one of the aircraft s two Avio Processing Centers APC The FADEC cards are physically separated The left Avio Processing Center houses one FADEC card from each of...

Page 185: ...engine when the other engine experiences a loss of power when both throttles are at the takeoff power setting APR ARMING APR arms automatically when both throttles are advanced to takeoff power with both engines running Arming of APR is indicated by white APR ARMED text that appears above the N1 tape on the MFD Operation with APR ARMED at takeoff thrust is allowed for five minutes Should this five...

Page 186: ...re 110 APR Line Select Key Disarming the system is a two step operation requiring pilot confirmation This prompts an APR DISARMED status message to appear while on the ground Rearming APR does not require confirmation and is a one step operation Disarm AUTO CONFIRM OFF AUTO CANCEL AUTO Re arm OFF AUTO Figure 111 APR Disarm Sequence ...

Page 187: ... continuous thrust MCT setting TEST APR ACTIVATION With APR armed reduce one engines throttle below the mid range while leaving the other engine at takeoff DEACTIVATION Once APR is activated either automatically or via a test activation it will remain active until the engines are shutdown or the pilot uses the Manual Disarm Deactivation procedure 8 5 5 Starter Generators A starter generator is mec...

Page 188: ...oil system is completely contained within the engine Oil is drawn from the oil tank by an engine driven oil pump The pump incorporates a pressure relief valve to avoid damage during engine starts in cold temperatures From the oil pump the oil passes though a full flow filter that incorporates a bypass valve and a differential pressure switch to indicate impending oil filter bypass Should the press...

Page 189: ...Section 8 Engines Fire Protection Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 169 Figure 112 Engine Oil Schematic ...

Page 190: ...e fire detection system monitors the aircraft engines for signs of overheating and fire Engine fire protection consists of firewalls ventilation of all zones within the engines drainage in those areas subject to leakage of flammable fluids fire detection fire suppression The fire detection system gives multiple indications of an engine overheat or fire condition to the air crew These include L R E...

Page 191: ...oop It also monitors the fire detection system and gives an indication of the failure of system integrity to the air crew Should a fire loop experience a fault a L R FIRE DETECTOR FAULT advisory message appears When the sensor cable is exposed to a temperature of 400 F 204 C the instrument panel red fire indicator will illuminate an audible alarm will sound and a L R ENG FIRE warning message appea...

Page 192: ...ine by a tube and nozzle located inside the nacelle and aimed to provide maximum dispersion The fire extinguisher is a single shot system dispersed by an electrical charge that activates an explosive squib in the fire extinguisher canister releasing the agent under pressure Rigid tubes convey the suppression agent to the nacelles where it is injected via nozzles located on the firewalls The agent ...

Page 193: ...he bleed air valve PRSOV 3 Turns off the igniters 4 Closes Flow Control Valve 5 Closes Fan Air Control Valve 6 Arms the fire canister 7 Green ARMED text on the FIRE ARMED button is illuminated when the fire extinguisher is armed for discharge NOTE In the event that the engine was shut down inadvertently using the FIRE ARMED button the engine may be restarted by turning the engine start switch to t...

Page 194: ...g Motoring On Ground Assisted In Flight Assisted Wet Dry AUTOMATIC START ABORT The FADEC provides automatic start abort functionality for failed ground starts based on 1 ITT Exceedance 2 No light off 3 Hung start 4 N2 Below Fuel on Threshold 5 Loss of required inputs outputs for FADEC during engine start ON GROUND START SEQUENCE 1 Engine Start Switch ON START 2 Electrical system is configured for ...

Page 195: ...contactor switch and verify that it is in AUTO once completed engine restart may be attempted Should engine parameters exceed limits during engine start on the ground the FADEC automatically aborts the start and an ENG START ABORT caution message appears If this message appears determine the cause of the abort and if a mechanical failure is suspected do not attempt to restart the engine IMPORTANT ...

Page 196: ...ambient conditions The engines are rated to produce 900 pounds of thrust at sea level at or below International Standard Atmosphere ISA temperature 10 C 8 6 5 Continuous Ignition To avoid engine flameout in turbulence heavy rain or icing conditions continuous ignition is selected by placing the engine start switch to the CONT IGN position 8 6 6 Flight and Ground Idle RPM Engine idle speed is highe...

Page 197: ...toff Valve by pressing the FIRE ARMED button once 8 7 4 Engine Failure In the event that an engine failure a L R ENG FAIL warning message appears 8 7 5 Engine Control Failures FADEC Channel Failures SINGLE CHANNEL A failure of one of the FADEC channels causes a loss of redundancy in the engine control system and prompts a L R ENG CONTROL advisory message to appear on ground This message indicates ...

Page 198: ...tion L R ENG OIL TEMP HIGH Oil temperature is between 135 C and 140 C Caution L R ENG OIL TEMP LOW Oil temperature below 20 C ground only Caution L R ENG CHIP DETECTED Metal particles detected in engine oil ground only Advisory L R ENG CHIP FAULT Engine oil chip detector has failed and may not be ale to detect metal in the engine oil ground only Advisory L R ENG CONTROL A loss of redundancy in the...

Page 199: ...n the side of each engine nacelle b By viewing the oil level in the sight gauge c Oil level is displayed on the Engine ENG synoptic page d None of the above 4 The minimum battery voltage for a battery only engine start is a 48V b 28V c 20V d 23V 5 FADEC stands for which of the following a Full Authority Digital Engine Controller b Fixed Axis Digital Engine Coupler c Fuel Air Data Engine Controller...

Page 200: ...running it without adding fuel c Provide engine cooling following long periods of operation d None of the above 13 How can the engines be turned off a By pressing the FIRE ARMED button once b By selecting CONT IGN for both engines using the engine rotary switch c By selecting OFF for both engines on the engine rotary switch d Both A C 14 Fire suppression for each engine is provided by a A fire ext...

Page 201: ...Section 8 Engines Fire Protection Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 181 ...

Page 202: ...itch panel The Cabin Air Distribution Sub System distributes conditioned bleed air and air conditioned air throughout the pressurized cabin through two evaporator units according to the temperature and operational mode demands of two control zones within the cabin Cockpit and cabin air flow rate is automatically controlled by the ACS or manually controlled though the environmental ENVIR synoptic T...

Page 203: ...Section 9 Climate Control Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 183 Figure 118 Climate Control System Overview ...

Page 204: ...m the PFD inputs are sent to the ACS which then configures the climate control system components by turning on and off applicable Electronic Circuit Breakers ECBs The ECBs for the climate control system are located within the Aft Power Distribution Center in Electronic Circuit Breaker Units ECBUs four and five Cabin pressure regulation is accomplished through the primary outflow valve and controll...

Page 205: ...ow Control Valve 2 Left Side Sensors Cabin Zone Temperature Sensor Aft Evaporator Temperatures Bleed Air Over Temp Sensor Pylon Over Temp Sensor Sensor Information to ACS Cabin Air Source Selector Aft Evap Fan LOW Aft Evap Fan MED Aft Evap Fan HIGH Isolation Valve ECBU 5 Right Flow Control Valve 1 Right Flow Control Valve 2 Fwd Evap Fan LOW Fwd Evap Fan MED Fwd Evap Fan HIGH Isolation Valve Left F...

Page 206: ...aximum Regulated Negative Cabin Pressure Differential ΔP 0 5 PSI Positive Pressure Relief Primary Outflow Valve 8 6 PSI Positive Pressure Relief Secondary Outflow Valve 8 7 PSI Maximum Bleed Air Muffler Duct Temperature 185 F 85 C Maximum Evaporator Temperature 176 F 80 C Maximum Pylon Temperature 350 F 177 C Landing with cabin pressurized is not approved When operating in the Manual mode negative...

Page 207: ...Section 9 Climate Control Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 187 9 4 Controls and Indicators 9 4 1 Cabin Air Controls Figure 120 Cabin Air Sub Panel ...

Page 208: ... cockpit L Bleed air provided from left engine only Right flow control valve closed Left flow control valve set to high flow R Bleed air provided from right engine only Left flow control valve closed Right flow control valve set to high flow Based on AIR DISTR selection NOTE Should AIR SOURCE switch fail an AIR SOURCE SW FAULT advisory message appears CABIN DUMP SWITCH Table 22 Cabin Dump Switch S...

Page 209: ...wing conditions must be met A rate of descent of 1 800 feet per minute or greater A descent below 12 500 ft cabin altitude NOTE A CABIN ALTITUDE warning message may indicate cabin depressurization RATE FPM Cabin altitude rate of change rounded to the nearest 100 FPM Feet Per Minute is presented Should the cabin altitude rate be too high the numeric digits turn amber The crew can select the cabin r...

Page 210: ...blue box steps through the four parameters Rotate the inner MFD knob to the desired setting Table 23 Environmental Synoptic Selections Function Settings 84 F 78 F Current cockpit and cabin temperature in degrees F SET Desired cockpit and cabin temperature in 2 degree increments from 64 F to 84 F plus MAX HEAT and MAX COOL Default setting at power up is 72 F FAN Cockpit and cabin evaporator fan OFF...

Page 211: ...TE functions are controlled by the concentric MFD knobs While in MANUAL mode of operation rotate the outer portion of the concentric MFD knob to select the function to be controlled The blue box steps through the three boxes Rotate the inner portion of the MFD knob to desired setting Table 24 Pressurization Synoptic Indications Pylon Temperature Temperature in pylon Flow Control Valve Setting HIGH...

Page 212: ...FT Set cabin altitude in MANUAL pressurization mode Range is 1 000 feet to 11 500 feet SEL CABIN RATE FT Set cabin rate in MANUAL pressurization mode Range is 0 to 2 500 fpm AUTO Pressurization controlled automatically MANUAL Pressurization controlled manually using CABIN ALT FT and CABIN RATE FT windows MODE CABIN ALT HOLD Pressurization maintained at present cabin pressure altitude AUTO Air dist...

Page 213: ...eed air heat exchanger located in each pylon regulates bleed air temperature based on the demand for cockpit and cabin heating or cooling There are two sources of airflow through the bleed air heat exchanger used for cooling the high pressure bleed air from the engine ram air and fan air During ground operations there is not enough ram air pressure for cooling so low pressure fan bleed air is used...

Page 214: ...re exceeds 85 C 185 F the temperature display remains white a L R BLEED AIR TEMP HIGH advisory message appears and the associated flow control valve closes Should the bleed air temperature exceed 100 C 212 F the temperature display turns red an L R BLEED AIR OVERHEAT warning message appears and if not already closed the associated flow control valve automatically closes TEMPERATURE SENSOR FAILURE ...

Page 215: ...00 feet Cabin rate of climb exceeds 2 500 fpm L or R selected on the AIR SOURCE switch Bleed air is available from only one engine Cabin temperature control falls approximately 7 F below the selected temperature DUMP is selected ON The shutoff function is automatically controlled by the ACS with manual shutoff override from the cockpit AIR SOURCE switch Table 27 Flow Control Valve Automatic Shutof...

Page 216: ...ow control valve closed Right flow control valve is in automatic control mode OFF Both flow control valves closed Using AIR SOURCE switch When the AIR SOURCE switch is set to an on position NORM L or R the flow control valves will not open if any of the following conditions exist Bleed air temperature is too high Engine is starting When the AIR SOURCE selector is placed in the OFF L or R position ...

Page 217: ...Section 9 Climate Control Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 197 9 5 2 Cabin Air Distribution Figure 125 Cabin Air Distribution Components ...

Page 218: ...r and exits through the primary and secondary outflow valves FORWARD EVAPORATOR The forward evaporator located behind the throttle quadrant supplies conditioned bleed air and air conditioned cooled air to the switch panel gaspers foot warmer outlets cockpit mid waist outlets side window and windshield defog outlets using a 3 speed 28 volt DC fan Conditioned bleed air normally supplied by the right...

Page 219: ...ly Diverter Valve Defog IP Vent Diverter Value Three Speed Blower Bleed Air Supply Bypass To Under Floor Evaporator Coil Floor Vent X2 Side Window Defog X2 Window Defog X2 Mid Waist Vent X2 Instrument Panel Vent X2 Defog Floor Diverter Valve Bleed Air Supply Diverter Valve Defog IP Vent Diverter Value Three Speed Blower Bleed Air Supply Bypass To Under Floor Figure 127 Forward Evaporator Schematic...

Page 220: ... through Spar Three Speed Blower Overhead Outlet Gaspers Bleed Air Supply Bleed Air Supply Diverter Valve Bypass To Under Floor Floor Vent Floor Vent Figure 128 Aft Evaporator Schematic TEMPERATURE REGULATING DIVERTER DOORS The forward and aft evaporators incorporate a temperature regulating diverter door Conditioned bleed air introduced to the cabin air distribution system is regulated to meet th...

Page 221: ...ll be routed to the cabin aft evaporator through the cabin shutoff valve and prevented from flowing to the cockpit by the isolation valve Figure 129 Cabin Isolation and Shutoff Valves Isolation Valve Isolates the left bleed air source from the right bleed air source Cabin Shutoff Valve Regulates bleed air going to the cabin The isolation and cabin shutoff valves are automatically controlled by the...

Page 222: ...lable Left bleed air available Right bleed air available Figure 130 Automatic Isolation Cabin Shutoff Valve Operation Cabin Cockpit Cockpit Only Figure 131 Manual Isolation Valve Cabin Shutoff Valve Operation AIR DISTR Line Select Key NOTE In the third Line Select key position AUTO air distribution is controlled by the ACS or the Air Source Switch ...

Page 223: ... Eclipse Aviation Corporation Version 2 0 April 2007 203 Figure 132 Manual Isolation Valve Cabin Shutoff Valve Operation AIR SOURCE Switch NOTE When the AIR SOURCE switch is in any position other than AUTO the AIR DISTR Line Select key reverts to the AUTO position ...

Page 224: ... are located on the right hand side of the aircraft nose An inward opening condenser inlet door allows intake of ambient air used for cooling during ground operations After the ambient air is routed through the condenser it is exhausted through an outward opening outlet door Figure 133 Condenser Inlet and Exhaust Doors Each evaporator incorporates a three speed LOW MED HIGH 28 volt DC fan that is ...

Page 225: ...Section 9 Climate Control Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 205 Figure 134 Air Conditioning System Schematic ...

Page 226: ...ting MAX COOL for the cabin and or cockpit routes bleed air to the evaporators at the minimum temperature available from the heat exchanger and provides maximum cooling from the air conditioning Cold air is supplied to that zone until the minimum allowed temperature 50 F is reached Once the zone temperature reaches 50 F the evaporator fan automatically steps to MED or LOW speed to maintain that te...

Page 227: ...nt rate as determined by the position of the flow control valves Aircraft pressurization is controlled by regulating the rate at which air escapes from the cabin via outflow valves The pressurization system consists of the following components Pressurization control Primary outflow valve Secondary outflow valve Cabin dump switch Cabin pressure sensor integral to primary outflow valve OUTFLOW VALVE...

Page 228: ...a schedule to meet the following parameters Airplane Altitude Cabin Altitude 41 000 feet 8 000 feet 20 000 feet 2 500 feet 1 500 feet Sea Level In the MANUAL mode cabin altitude and cabin rate of climb are selected on the pressurization synoptic The pressurization system regulates to the selected cabin altitude and cabin rate of climb The CABIN ALT HOLD mode maintains the present cabin pressure al...

Page 229: ...e the cabin pressure to ambient pressure in the event of over pressurization smoke in the cabin or in the event of ground pressurization With the DUMP switch ON both outflow valves open fully and all bleed air is routed to the cockpit at high flow A red CABIN DUMP text also appears on the left side of the pressurization synoptic Figure 136 Cabin Dump Switch ...

Page 230: ...The cabin dump switch dumps the cabin to 13 500 ft 1500 feet SMOKE CLEARING In the event of smoke in the cabin the smoke and fumes evacuation checklist requires the cabin DUMP switch to be activated This opens both outflow valves routes all air forward to facilitate forward to aft airflow and sets the forward evaporator speed to high to vent the smoke overboard ...

Page 231: ...Section 9 Climate Control Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 211 9 6 Normal Operations No content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 232: ...hould be considered false due to the extreme cold The temperature regulation control will also default to a special mode of operation for cold temperatures Once the engines are started and warm bleed air warms the system the ACS will stop displaying senor failures and temperature regulation will resume to normal 9 8 1 Single Engine Operations In the event of an engine shutdown or failure bleed air...

Page 233: ...BIN ALT HOLD MODE Primary pressurization failed Backup controller attempting to hold cabin altitude constant Advisory AIR CONDITIONING FAIL Air conditioning has failed Advisory L R BLEED AIR TEMP HIGH Bleed air supply temperature is too high Normal bleed air temperature control has failed L or R bleed air temperature is being limited by the flow control valves Advisory CLIMATE CTRL FAIL Indicates ...

Page 234: ...in altitude greater than 10 000 ft b Cabin over pressurization c Failure of the bleed air supply system d None of the above is correct 3 What are the three levels of cabin altitude alerting a b c 4 What does sounding the Mask On Descend aural alert indicate 5 What are three items occur when the DUMP switch is activated a b c 6 Why may a pilot elect to use the cabin dump switch a To clear smoke fro...

Page 235: ...bin b To the cockpit c It depends on what engine has failed d None of the above are correct 10 How does the climate control system heat the cockpit and cabin a Four electric heating elements are strategically placed throughout the cabin for uniform heating and air circulation b Conditioned engine bleed air is allowed to enter the cabin for heating and pressurization needs c Fresh air inlet on the ...

Page 236: ...nstalled in the aircraft a 1 b 2 c 3 d 5 e None of the above is correct 15 What is the purpose of the outflow valves a The outflow valves are an integral part of the air conditioning system in that they control the amount of refrigerant in the system b The outflow valves shut off the bleed air supply system allowing the cabin to depressurize c The outflow valves prevent engine power loss on takeof...

Page 237: ... in mechanical circuit breakers significantly reduces cockpit switch panel clutter In addition the use of the more reliable ACS controlled ECBs reduces pilot workload There are also two 22 amp hour 24 VDC sealed maintenance free lead acid batteries located in the nose compartment of the aircraft A start battery and systems battery provide aircraft power when generators are not running and float on...

Page 238: ...S monitors the status of electrical system components including contactor position bus voltages generator output battery state and rate of charge or discharge as well as ECB status The ACS provides control commands and receives status information for the following electrical system components 1 Battery Bus Contactor 2 Start Battery Contactor Lighting Controller 3 Start Battery Heater 4 Systems Bat...

Page 239: ...ight ACS Right ACS Communications Bus Left Generator Control Unit Center Pedestal Left Sidestick Right Sidestick Right Generator Control Unit Start Battery Heater ECBU 1 ECBU 2 External Power Contactor Systems Battery Contactor Systems Battery Heater Aft Power Distribution Center ECBU 4 Start Battery Contactor Lighting Controller ECBU 5 Right Forward CB Left Aft Bus Right Aft Bus Left Forward CB F...

Page 240: ...voltage each generator 28 5 VDC Maximum continuous output current each generator 200 amps External Power Maximum voltage 29 VDC Minimum voltage 45 seconds 24 VDC Minimum voltage any duration 10 VDC The External Power Contactor automatically opens if the polarity is wrong or if the voltage is out of limits Greater than 29 volts at any time Aircraft current draw greater than 400A External Power curr...

Page 241: ...enerator contactor ACS controlled OFF Right generator contactor open SYS BATT ON Systems battery contactor closed OFF Systems battery contactor open START BATT ON Start battery contactor closed OFF Start battery contactor open BUS TIE AUTO Bus tie contactor under ACS control OPEN Bus tie contactor open EXT POWER Green LED indicates external power is connected and voltage is the correct polarity an...

Page 242: ...arge Current flow Voltage on certain buses Generator current output GENERATOR OUTLINE Green Generator operating White Generator off Amber Generator failed inoperative BATTERY OUTLINE Green Battery Charging Amber Battery Discharging White Battery Contactor Open no power to or from Bus bar segments are green if voltage is greater than 20 volts Bus bar segments are white if voltage is 20 volts or les...

Page 243: ... April 2007 223 Figure 141 Battery State Display 10 4 3 Electronic Circuit Breaker ECB Synoptic Figure 142 Electronic Circuit Breaker Synoptic The upper display allows the pilot to select the ECBs by state out tripped pulled or collared The lower display allows the pilot to select the ECBs by system ...

Page 244: ...ion of the air conditioning system The air conditioning compressor is load shed during single generator operation 10 5 2 Generator Control Units GCUs The left and right Generator Control Units are located in the aft compartment outside the pressure vessel and control the starter generators during engine start The GCUs automatically switch from the start mode to generator mode at a specific engine ...

Page 245: ...sponsible for monitoring temperatures in the heater pads and forwarding it to the Right ACS Both ACSs turn on power to the battery heater when the Outside Air Temperature falls below 10 degrees C and the aircraft is powered by generator or GPU power The ACSs turn the heaters off when the temperature as sensed by the temperature sensor rises to 80 degrees C and on when it falls to 70 degrees C Fail...

Page 246: ... engine start EXTERNAL POWER LIGHT The green external power light on the electrical panel is on if the following conditions are met External power is plugged in Power is the correct polarity and the voltage is between 24 and 29 volts NOTE Illumination of the green external power light does not indicate that external power is being used both battery switches must be in the ON position ...

Page 247: ...normal operation the ACS divides the buses into a left right configuration with the left forward and left aft buses receiving power from the left generator and the right forward and right aft buses receiving power from the right generator The left and right aft bus voltages are indicated on the lower portion of the electrical synoptic adjacent to the left and right aft bus segments In the event th...

Page 248: ...nue to operate on battery power When this occurs the ACS automatically will shed electrical equipment to provide at least 30 minutes of electrical power to those loads that are essential to continued safe flight and landing This state is called Battery Only Load Shed When Battery Only Load Shed occurs the ACS automatically sheds or Locks non essential ECB s SMART LOAD SHED Smart Load Shed function...

Page 249: ...pears If the start battery contactor trips due to an over current condition the start battery is isolated from the electrical system and a START BATT CONTACT TRIP advisory appears NOTE Engine start is not possible with the start battery isolated START BATTERY CONTACTOR AND LIGHTING CONTROLLER The start battery contactor and lighting controller is a self contained unit that houses the following ele...

Page 250: ...ed to the various electrical components through ECBs rather than mechanical circuit breakers Each ECB detects over current conditions to trip the ECB to protect the aircraft wiring 127 ECBs are contained in five Electronic Circuit Breaker Units ECBUs each associated with one electrical bus ECBU 1 Left Forward Bus ECBU 2 Right Forward Bus ECBU 3 Battery Bus ECBU 4 Left Aft Bus ECBU 5 Right Aft Bus ...

Page 251: ... with an ECB is lost or if it is unable to be switched off an ECB CTRL FAULT advisory message appears POWER DISTRIBUTION CENTERS There are two Power Distribution Centers on the aircraft They are considered Line Replaceable Units LRUs for the electrical system The Forward Power Distribution Center is located aft of the forward pressure bulkhead and contains the power distribution components for the...

Page 252: ...Section 10 Electrical Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 232 Version 2 0 April 2007 ECBU 5 ...

Page 253: ...power all buses If the SYS BATT switch is then placed to ON the systems battery is paralleled with the start battery Ground operation on battery power should be of limited duration to prevent battery depletion When the start or system battery is discharging a START or SYS BATT DISCHARGE caution message appears EXTERNAL POWER All buses may be powered by external power Both battery switches must be ...

Page 254: ...hrough the engine s accessory gearbox to start the engine After the first engine is started and generator power is available the electrical system reconfigures to a left right configuration Both left and right forward circuit breaker contactors close the right battery bus contactor opens disconnecting the systems battery from the right forward bus and the bus tie contactor remains closed to power ...

Page 255: ...he left and right electrical systems are split bus tie contactor is open The left system is powered by the left generator and is connected to and charges the systems battery The right system is powered by the right generator and is connected to and charges the start battery AIR GROUND LOGIC The ACS uses the current status of the aircraft on ground or in flight as determined through the Weight On W...

Page 256: ... loads that are not required for continued safe flight and landing The systems battery and start battery have sufficient capacity to power the remaining emergency loads for at least 30 minutes For engine start when both generators inoperative the start battery powers the starter generator for the engine being started The systems battery powers those loads on the forward busses required for continu...

Page 257: ... tie contactor BTC This will remove power from all equipment associated with the Battery Bus Left Forward Bus and Left Aft Bus including any redundant ECB s RIGHT BUS ISOLATION The right bus isolation procedure requires the pilot to remove power from all right side equipment and calls for the pilot to turn off the right generator GEN start battery START BATT and open the bus tie contactor BTC This...

Page 258: ...erator switch off Caution BUS TIE FAIL The bus tie contactor is stuck closed Caution LOAD SHED SYS FAULT Air conditioning load shed capability is lost ground only Caution START BATT DISCHARGE Start Battery is discharging Caution SYS BATT CONTACT TRIP Battery Bus Contactor has tripped due to over current System Battery is off and isolated from Battery Bus Caution SYS BATT DISCHARGE System Battery i...

Page 259: ... motors to start the jet engines b Power generators to power the aircraft s electrical system c Small electric motors that turn larger generators to produce electrical power d Both A and B are correct 3 The Voltage output of a starter generator is a 12 5 VDC b 24 VDC c 28 5 VDC d 30 VDC 4 The regulated Voltage output of to the aircraft electrical system is a 12 5 VDC b 24 VDC c 28 5 VDC d 30 VDC 5...

Page 260: ...of external power IE green light on a 1 ________________________________________ b 2 ________________________________________ c 3 ________________________________________ d 4 ________________________________________ 8 What items are powered by the HOT BATTERY BUS 9 When the External Power Light Green is illuminated what is happening a External power is plugged in b External power is of the correct...

Page 261: ... load shedding should automatically remove power to what system s during single generator operation 14 What type of batteries are installed on the Eclipse 500 a NiMh Nickel Metal Hydride b Maintenance free lead acid c NiCad d Sealed gel batteries 15 Which battery is connected to the Hot Battery Bus a Start Battery b Systems Battery c Aft Battery d No battery is attached to the Hot Battery Bus Exte...

Page 262: ... 18 If both starter generators fail in flight what is the minimum battery time available a 60 min b 30 min c 45 min d 35 min 19 Which two electrical system components are independent of the Aircraft Computer Systems a b 20 List the five conditions that will cause external power to automatically disconnect a b c d e ...

Page 263: ... Well Lighting Optional Map Lights Cabin Upper Cabin Wash Lighting Lower Cabin Wash Lighting Optional Cabin Reading Lights Baggage Compartment Light Most of the interior lights are controlled by a lighting controller within the electrical system With both battery switches OFF the hot battery bus provides power to the cabin overhead and baggage compartment lights With battery power only these light...

Page 264: ...ntroller is located in the Start Battery Contactor Lighting Controller unit and is considered part of the electrical system and has no direct link to the ACS This controller provides the following functions 1 Switching 2 Current limiting 3 Lighting Timer Pilot inputs for interior lighting are through several switches throughout the cockpit as well as an interface on the center switch panel ...

Page 265: ...ection 11 Interior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 245 11 3 Limitations and Specifications No content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 266: ...evel according to time of operation such as DAY or NIGHT A control knob on the MASTER DIM panel may be rotated to gradually increase or decrease interior light intensity Figure 145 Center Switch Panel Standard Figure 146 Center Switch Panel FOOT WELL Light Option Table 32 Interior Light Center Switch Panel Controls Sub Panel Switch Nomenclature Control CABIN OVRD Override Upper Cabin Wash Lighting...

Page 267: ...t have specific Electronic Circuit Breakers associated with them the lighting controller will act in this capacity deactivating any light that experiences an overcurrent situation 11 5 2 Cockpit Dome Lighting The cockpit dome lighting consists of a string of LED s on the front end of the overhead console Two light switches control the cockpit dome lighting One switch is located on the Armrest Ligh...

Page 268: ...on 248 Version 2 0 April 2007 11 5 3 Cockpit Foot Well Lighting Optional The foot well lighting system consists of a series of LED lights located underneath the instrument panel The FOOTWELL switch located on the center switch panel activates this lighting Figure 149 Cockpit Foot Well Lighting ...

Page 269: ...t of two groups of focused LED located under the glare shield for map reading in the cockpit with one group on either side of the cockpit A switch on the autopilot control panel is used to activate each light The co pilot light is operated by an identical knob on the right side of the autopilot control panel Figure 150 Map Lighting Figure 151 Map Light Control ...

Page 270: ... lighting consists of LED s running the perimeter of the overhead console in the cabin The cabin lighting control panel located on the overhead console allows control of this lighting Pushing the upper cabin wash lighting switch once turns lights on dim pushing it a second time turns them on bright and a third time turns them back off Figure 152 Overhead Cabin Wash Lighting ...

Page 271: ...Section 11 Interior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 251 Figure 153 Overhead Cabin Wash Lighting Control ...

Page 272: ...co pilot s seat to the beginning of the cargo compartment on the right side of the aircraft and from the edge of the door to the beginning of the cargo compartment on the left side of the aircraft These lights are controlled by a switch on the overhead console lighting control panel Pushing the lower cabin wash lighting switch once turns lights on dim pushing it a second time turns them on bright ...

Page 273: ...2007 253 Figure 155 Lower Cabin Wash Lighting Control 11 5 7 Cabin Reading Lights The cabin reading lights provide the individual light for each passenger seat The bezel on each light allows it to swivel and it has its own control located near each LED light on the overhead console Figure 156 Cabin Reading Lights ...

Page 274: ...sion 2 0 April 2007 11 5 8 Baggage Compartment Lights The LED baggage lights provide lighting to the baggage area in the aft cabin The control switch for this light is located on the overhead console lighting control panel Figure 157 Baggage Compartment Light Figure 158 Baggage Compartment Light Control ...

Page 275: ... Cabin Override Switch A CABIN OVRD switch on the center switch panel allows pilot override of passenger control of all cabin lighting Selecting the OVRD position extinguishes all cabin lighting If it is returned to the off position only reading lights will come back on all other cabin will have to be turned back on using cabin lighting control panel ...

Page 276: ...Section 11 Interior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 256 Version 2 0 April 2007 11 7 Abnormal Procedures No content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 277: ...Section 11 Interior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 257 11 8 Crew Alerting System Messages No content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 278: ...re being used on battery power only c For cosmetic purposes only d None of the above 4 The interior lighting system is divided into which two categories a Forward Aft b Upper Lower c Right Left d Cockpit Cabin 5 Where is the switch for the foot well lighting located a Under the left pilot s armrest b On the center switch panel c There is no switch these lights are always on but and can only be dim...

Page 279: ...here is the switch for the passenger reading lights located a On the center switch panel b Under each passenger s arm rest c On the overhead panel next to each passenger reading light d None of the above 10 What is the function of the CABIN OVRD switch a Activation and deactivation of the upper cabin wash lighting b Overrides the cabin switch for the reading lights prevents passenger activation an...

Page 280: ... taxi recognition lights if installed Position Lighting Red and green position lights located on the left and right wingtips and a white aft facing tail light located on the trailing edge of the horizontal stabilizer fairing Anti Collision Lighting Strobes on each wingtip and in the tail cone Several of the aircraft lights utilize Light Emitting Diodes LEDs Each of these lights contains several st...

Page 281: ...Section 12 Exterior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 261 Figure 160 Exterior Lighting Left Side View ...

Page 282: ...ng ECBs reside on Electronic Circuit Breaker Units one four and five All exterior lighting is controlled by the pilot through hard switches on the center switch panel Commands from the center switch panel are routed through the PFD to the ACS which in turn command the ECBs The following lights are part of the exterior lighting system 1 Left and Right Landing Lights 2 Left and Right Taxi Recognitio...

Page 283: ...tions Bus Left Byteflight Bus Right Byteflight Bus ACS PFD Communications Bus ECBU 4 Left ACS Communications Bus Right ACS Right ACS Communications Bus Left Anti Collision Light Tail Anti Collision Light Right Anti Collision Light LAND Switch Left Taxi Recog Light Left Landing Light Beacon Light Position Lights Right Landing Light Right Taxi Recog Light ECBU 1 Wing Inspection Light TAXI RECOG Swit...

Page 284: ...Section 12 Exterior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 264 Version 2 0 April 2007 12 3 Limitations and Specifications No content INTENTIONALLY LEFT BLANK ...

Page 285: ...T LIGHT sub panels Figure 162 Center SWITCH Panel Standard 12 4 1 Center SWITCH Panel Standard Table 33 Exterior Lighting Switch Functions Sub Panel Switch Nomenclature Control LAND Left and Right Landing Lights EXT LIGHT TAXI RECOG Left and Right Taxi Lights Steady on ground and alternating flashing in air STROBE BEACON Left Right Wing and Tail Strobes Flashing Beacon EXT LIGHT BEACON Flashing Be...

Page 286: ...rward dry bay of the wing tip tanks A white aft facing position light is located on the horizontal stabilizer fairing Each light consists of a string of four red green or white LEDs Position lights are automatic and are illuminated anytime the avionics system is powered up A failure of any of the position lights causes a POSITION LIGHT FAIL advisory message to appear ANTI COLLISION LIGHTS Two whit...

Page 287: ...OBE BEACON position all strobes and the beacon will be in operation 12 5 5 Taxi Recognition Lights There are two 35W taxi lights located in each of the wing tips to provide for additional lighting when taxiing and during night operations The operation of the Taxi Recognition lights is dependant on the status of the Weight On Wheels WOW sensor During ground operation the Taxi Recognition lights wil...

Page 288: ...Section 12 Exterior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 268 Version 2 0 April 2007 12 6 Normal Operations No content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 289: ...on Corporation Version 2 0 April 2007 269 12 7 Abnormal Procedures 12 7 1 Battery Only Load Shed In the event the electrical system is powered by battery power only the ACS load sheds the following lights Beacon Anti Collision Left and Right Taxi Right Landing All Optional Lighting ...

Page 290: ...Messages Message Condition Category LANDING LIGHT FAIL Landing light failure detected Advisory POSITION LIGHT FAIL Position light failure detected Advisory STROBE FAIL Strobe light failure detected Advisory TAXI LIGHT FAIL Taxi light failure detected Advisory INSPECTION LIGHT FAIL Wing ice inspection light failure detected Advisory BEACON LIGHT FAIL Beacon light failure detected Advisory ...

Page 291: ...wer is applied to the aircraft wing roots d None of the above 4 What type of lighting is used for anti collision purposes a The Eclipse 500 does not use anti collision lights b Strobe lights located on each wingtip and the tail c Red and green lights located on the wingtips d White lights located in the wingtips 5 Where are the landing lights located on the Eclipse 500 a In the wing roots b On the...

Page 292: ...f light is used for the wing inspection lighting system a A halogen bulb b A tightly packed group of LEDs c A HID High Intensity Discharge lamp d None of the above 12 How can the aircraft s beacon be operated independently a By moving the STROBE BEACON switch to the BEACON position b By pulling the ECBs for the strobes c If the strobes are operating the beacon will also be operating and each light...

Page 293: ...Section 12 Exterior Lighting Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 273 ...

Page 294: ...de of the forward fuselage below the windshield and cross connected upper right cross connected to the lower left static port to compensate for the effects of aircraft yaw or sideslip There is a third pitot static probe that provides air data information to the MFD ADI and can be used by the pilot for comparison in the event of air data disagreement The air temperature system consists of two OAT p...

Page 295: ...he air data computers process this information and send it to the AHRS for distribution to the aircraft systems GPS information is collected by two GPS units and sent to the AHRS for distribution to the aircraft systems Two Attitude Heading and Reference Systems serve as the primary attitude and heading sources for the left and right PFD s as well as the MFD Attitude Indicator ADI The AHRS units u...

Page 296: ...Section 13 Air Data Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 276 Version 2 0 April 2007 Figure 164 Air Data ACS Interface ...

Page 297: ...Section 13 Air Data Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 277 ...

Page 298: ...13 3 Limitations and Specifications 13 3 1 Attitude and Heading Reference System AHRS Operation at latitudes requiring direction indication referenced to true North are prohibited 13 3 2 Air Data Computer 3 ADC 3 Following the loss of both ADCs 1 and 2 the use of ADC 3 is limited to airspeeds of 160 KEAS and below ...

Page 299: ...Section 13 Air Data Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 279 ...

Page 300: ...ressure bulkhead The Air Data Computers interpret the data provided along with error corrections to present airspeed for display on the PFDs as well as total pressure for use by the FADEC and ACS Angle of attack is sensed by differential pressure transducers contained in the base of each pitot AOA probe and transmitted to the Air Data Computer where the data is processed and provided to the PFD AC...

Page 301: ...for display This information is also used by the FADECs and processed by the ACS The static ports are heated by dual internal heating elements that provide anti ice protection Figure 167 Dual Static Port Left Side 13 4 3 Pitot Static An independent pitot static probe provides information directly to the ACS for display on the MFD ADI Information provided by this probe may also be used by the pilot...

Page 302: ...TOT STAT line select key on the ICE protection synoptic page and is in AUTO for normal operations 13 4 5 Outside Air Temperature OAT Each OAT probe contains two independent sensors that provide information to the Air Data Computers and both ACSs Both computer systems process the data provided and present OAT for display on the PFDs and Total Air Temperature TAT for use by the FADECs The OAT sensor...

Page 303: ...Reference System AHRS where it is combined with other navigation data and sent to the ACS 13 4 7 Integrated Sensor Suite ISS There are two Suites on the aircraft The ISS can be considered a grouping of three separate system components that work together to provide air data information to the ACS An ISS is composed of the ADC AHRS and GPS unit Data from the ADC and GPS is sent to the AHRS where it ...

Page 304: ...BARO SET line select key is also available for a secondary means of altimeter entry primary source is the BARO SET knob on the Autopilot Control Panel LINE SELECT KEYS AHRS SRC AUTO AHRS automatically selected by ACS 1 Left and Right PFD using Left 1 AHRS 2 Left and Right PFD using Right 2 AHRS ADC SRC AUTO ADC automatically selected by ACS 1 Left and Right PFD using Left 1 ADC 2 Left and Right PF...

Page 305: ...ts to determine airspeed Mach and total pressure The ADC uses air temperature from the OATs to determine airspeed Mach and air temperature and present the data on the PFD This information is also used by the ACS for comparison and failure monitoring and by the FADEC for engine control Angle Of Attack data is derived from the pitot AOA probes and transmitted to the ADC where differential air pressu...

Page 306: ...dications 13 7 2 Sensor Failure The air data system is a redundant design preventing complete loss of air data in the event of a component failure Should any component ADC AHRS or GPS fail one of the following messages will appear AHRS 1 FAIL CAUTION AHRS 2 FAIL CAUTION ADC 1 FAIL ADVISORY ADC 2 FAIL ADVISORY ADC 3 FAIL ADVISORY GPS 1 FAIL ADVISORY GPS 2 FAIL ADVISORY With ADC and AHRS SRC on the ...

Page 307: ...Left and right attitude disagree Caution HEADING DISAGREE Left and right heading disagree Caution ADC 1 FAIL ADC 1 Failure or AHRS 1 to ADC 1 communication is lost System will automatically revert to operating ADC in AUTO mode Advisory ADC 2 FAIL ADC 2 Failure or AHRS 2 to ADC 2 communication is lost System will automatically revert to operating ADC in AUTO mode Advisory ADC 3 FAIL Airspeed and al...

Page 308: ...aft nose b From the pitot static probe only c From the static ports d No angle of attack information is used by the ADC 5 What is the purpose of thepitot static probe a It is the only heated probe and thus provides pertinent data when ice is encountered b Provides information to the ACS for use on the MFD ADI c Can be used in the event of a system abnormality or disagreement between primary probes...

Page 309: ...andby instruments on the MFD c They can change the air data source on the SENSOR synoptic page d All of the above 11 With the air data sources set in the AUTO position what will happen in the event of a failure a The pilot will be prompted by a CAS message that indicates the failed component b The ACS will automatically select the operative source of air data c None of the above d A B are correct ...

Page 310: ...traditional electronic flight instrument representation including Flight Mode Annunciations FMAs an Attitude Direction Indicator ADI Airspeed Indicator Altimeter Vertical Speed Indicator and Horizontal Situation Indicator including a moving map The PFD also provides a Composite Mode in which the PFD provides a reversionary capability showing additional aircraft systems information which can be use...

Page 311: ...Section 14 Primary Flight Display PFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 291 14 2 Limitations and Specifications No content INTENTIONALLY LEFT BLANK ...

Page 312: ...lipse Aviation Corporation 292 Version 2 0 April 2007 14 3 System Description 14 3 1 Initialization Figure 173 PFD Initialization On initial power up of the PFD an initialization page displaying the version of Avio is presented This information should be verified prior to flight ...

Page 313: ...ADI Slip Skid Indicator Flight Director Altimeter Approach Minimums Display Vertical Speed Indicator Marker Beacon Receiver TILE 3 CONFIGURABLE Primary Navigation NAV selection Secondary Navigation NAV selection Range and view selection TILE 4 True Airspeed Outside Air Temperature OAT Time Horizontal Situation Indicator HSI Rate of Turn Indicator Wind Indicator Projected Track Indicator TILE 5 CON...

Page 314: ...om the Autoflight system Figure 175 Flight Mode Annunciation Window The lateral and vertical navigation mode sections of the FMA field are further subdivided into subfields for the Active engaged and Armed modes The Autoflight displays only one active and one armed mode at a time for lateral and vertical control If the system is reporting both an active and armed mode as valid for display the acti...

Page 315: ...ile 2 the PFD continuously displays primary flight instruments of attitude airspeed altitude and vertical speed Tile 2 also displays flight director cues autopilot targets air data instrument trends slip skid precision approach path deviations mach radar altitude and barometric BARO correction Air data instruments and other alphanumeric fields are overlaid on top of the attitude indicator Autoflig...

Page 316: ...xt AP appears in the upper left corner of tile 2 adjacent to the airspeed tape When the yaw damper is engaged green YD text is also displayed below the autopilot indication adjacent to the airspeed tape Figure 178 Autopilot Yaw Damper Display PFD When the autopilot is disconnected whether by the pilot autopilot failure or automatic disconnect an amber AP DISC text appears on the PFD and an aural a...

Page 317: ...ach number display Figure 180 Airspeed Indicator PFD Airspeed Tape The airspeed indicator tape is displayed on the left portion of tile 2 The airspeed scale is displayed in Knots Equivalent Airspeed KEAS labeled every 20 knots with a 60 knot rage continuously visible There are larger unlabeled tick marks every 10 knots The current airspeed is a rolling digit presentation in the center of the scale...

Page 318: ...Mach number is 450 or above and remains displayed until the Mach decreases to 400 If Mach number is not displayed the graphical display disappears Figure 181 Mach Indication Trend Vector A blue airspeed trend vector is displayed slightly to the right of the current airspeed such that it is not hidden behind the current airspeed window This airspeed trend vector points at the airspeed scale at the ...

Page 319: ...the bug becomes hollow Figure 182 Airspeed Bug V Speeds Several V speeds are displayed on the airspeed tape Rotation Speed ROT Rotation speed is bugged with ROT text next to a single black tick mark on the airspeed tape when the appropriate speed is set in the OPS page on the MFD ROT XX KTS is also displayed below in an outline window where the Mach display appears Takeoff Flap Extension Speed T O...

Page 320: ...e above VMO or MMO as long as there is no speed exceedance If VMO is exceeded the airspeed tape is solid red and the airspeed display is red If MMO is exceeded the airspeed tape is solid red and the Mach display is red Figure 183 Airspeed and Mach Exceedance Stall The airspeed tape is displayed as a red dashed line below the stall speed for the current configuration as long as the airspeed is abov...

Page 321: ... Direction Indicator ADI is located in the center portion of tile 2 It uses a traditional blue sky brown ground with a horizon line extending the width of Tile 2 The ADI also contains a pitch ladder roll angle pointer scale and an amber wedge style attitude reference symbol Flanking the attitude reference symbol are two amber horizon reference pointers referred to as outriggers Figure 185 Horizon ...

Page 322: ...t 10 20 30 40 50 and 70 with unlabeled lines every 5 The right and left side of the larger increments have tick marks pointing either up or down towards the horizon At 90 of pitch there is a small circular ring Roll Figure 187 Roll Indications The ADI is accurate for 180 of roll The roll scale is displayed with black triangles at black triangles at 0 45 left and 45 right large tick marks at 30 and...

Page 323: ...f the roll pointer triangle Flight Director FD Figure 189 Flight Director When active the Flight Director FD is displayed in the center of the ADI on top of the pitch wedge The FD provides simultaneous roll and pitch guidance The FD moves vertically in line with the airplane reference symbol for pitch guidance and rotates about its center for roll guidance Pitch guidance is provided for 15 and rol...

Page 324: ...displays a horizontal deviation indicator when VLOC1 or VLOC2 is tuned to and receiving a localizer frequency The HDI scale provides tick marks for zero deviation half and full scale left right The navigation source is displayed to the right of the HDI and will indicate ILS LOC BCRS back course or FMS A white HDI pointer indicates course deviation if the pointer exceeds full scale deviation it tur...

Page 325: ...ost or invalid the HDI pointer is removed the associated text turns red and a red X covers the HDI Figure 193 Horizontal Deviation Indicator Signal Loss Vertical Deviation Indicator VDI Figure 194 Vertical Deviation Indicator VDI The PFD displays a vertical deviation glide slope indicator when VLOC1 or VLOC2 is tuned to and receiving a localizer frequency ...

Page 326: ...te either ILS or FMS A white VDI pointer indicates course deviation if the pointer exceeds full scale deviation it turns amber Figure 195 Vertical Deviation Indicator Full Scale If the PFD detects vertical deviation data as invalid or failed due to lost communications without a change in VLOC frequency or a change in Primary Navigation source the VDI pointer is removed the associated text turns re...

Page 327: ...vigation source and or if an ILS or localizer approach is loaded in the FMS When activated the marker beacon receiver sensitivity is automatically set to LO the marker beacon audio is automatically turned on and the following signals are detected and displayed Outer Marker Blue display labeled OM Figure 197 Outer Marker Display on PFD Middle Marker Amber display labeled MM Figure 198 Middle Marker...

Page 328: ...rsion 2 0 April 2007 Figure 199 Inner Marker Display on PFD If an ILS or localizer is not selected or an ILS or localizer approach is not loaded in the FMS the marker beacon receiver sensitivity is automatically set to HI and the following signal is detected and displayed Airway Marker White display labeled AM ...

Page 329: ...ve motion of the altitude window with respect to the altimeter scale is up for increasing altitudes The altitude window contains the numeric value of the baro corrected altitude in 20 foot increments The movement of the altitude scale lower limit is at 1 000 MSL and the upper limit is at 50 000 MSL Trend Vector The altimeter also displays a trend vector when altitude is changing at rates above 300...

Page 330: ... altitude data reported from the Air Data Computer When pressure altitude is determined to be invalid the PFD removes the altitude window with value the altitude trend vector the altitude scale the altitude bug numeric value and displays a red X covering the area where the altitude scale was Baro Set Altimeter Setting The upper portion of a data block located below the altitude tape displays barom...

Page 331: ... marks are located at 500 fpm ex 2500 fpm High Vertical Speeds The digital value of vertical speed is displayed when the vertical speed exceeds 3000 fpm and is rounded to the nearest 100 fpm for values greater than or equal to 3000 fpm When the autopilot is in altitude change ALT CHG mode a green diamond indicates the vertical speed target used when this mode is engaged Vertical Speed Bug A magent...

Page 332: ...yright Eclipse Aviation Corporation 312 Version 2 0 April 2007 Radar Altimeter An optional radar altimeter provides information on the aircraft s absolute aircraft altitude The absolute altitude value is displayed below the vertical speed tape Figure 203 Radar Altimeter ...

Page 333: ...y PFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 313 14 3 5 Tile 3 Primary Secondary NAV Source Selection Data block and Left Line Select Keys Figure 204 PFD Tile 3 Line Select Key Options ...

Page 334: ... to local or UTC Zulu time on the SETUP synoptic page Outside Air Temperature OAT The OAT is displayed as an integer of up to three digits with no leading zeros The units for temperature are in degrees C or degrees F based upon pilot preference selection on the SETUP synoptic page True Airspeed TAS The true airspeed is displayed as a whole number of up to three digits Ground Speed GS The ground sp...

Page 335: ...he left concentric knob Line Select Key 1 NAV Primary NAV source select VLOC 1 VLOC 2 FMS OFF Line Select Key 2 BRG Secondary NAV source select VLOC 1 VLOC 2 FMS OFF Line Select Key 3 NO FUNCTION Line Select Key 4 NO FUNCTION Line Select Key 5 View Range Pressing View Range allows use of left concentric knob to select range and view Concentric Knob LEFT Inner Knob When VIEW RANGE is selected press...

Page 336: ... 14 3 6 Tile 4 Horizontal Situation Indicator HSI and Overlays Figure 206 PFD Tile 4 HSI The HSI is located in PFD Tile 4 and it displays a standard HSI format with aircraft heading selected heading selected course bearing to waypoint or station course deviation flight plan to from distance to waypoint and wind magnitude direction ...

Page 337: ...ts having no leading zeros ex 03 for 30 degrees through the use of the VIEW RANGE line select key and left concentric knob Figure 207 View Range Selection View With the full compass view 360 with N S E W cardinal headings displayed the aircraft symbol is located at the center of the full compass rose scale Major graduation marks are located every 10 degrees beginning at North It displays numeric l...

Page 338: ...gree Compass View The forward looking arc compass rose scale depicts 120 degrees and maintains the same graduation scale as the full view The wing fuselage intersection of the aircraft symbol is at the radial center of the forward looking arc compass rose scale and points towards the top of the screen Figure 209 120 Degree Arc View HSI Map Range NM ...

Page 339: ...on for both the inner and outer ring is controlled by pressing the VIEW RANGE line select key and rotating the inner portion of the left concentric knob Rotating the knob left decreases range while rotating the knob right increases range The current range selection in NM is displayed on the upper right portion of the rings Range is selectable to the following distances Distance nm Inner Ring 1 2 5...

Page 340: ...nchs to current aircraft heading Heading bug position is controlled by the HDG SEL knob on the Autopilot Control Panel and associated pre select information is displayed in the heading pre select window located in the upper right portion of the HSI display One knob click is equal to 1 degree however scrolling the HDG SEL knob quickly will cause an accelerate function to rapidly rotate the heading ...

Page 341: ...s of a CDI needle a TO FROM indicator and a deviation scale and corresponds with the NAV line select key on the PFD The CDI arrowhead points to the current selected course on the HSI compass rose to the current selected course of the primary navigation source Course Selection Course is selected with the left concentric knob and is displayed as course CRS in the NAV line select key window Rotating ...

Page 342: ...eft or right Localizer When a localizer is the primary navigation source the CDI indicates localizer deviation in degrees with a full scale range of 2 5 degrees left or right FMS When the FMS is the primary navigation reference full scale deflection is dependent upon the current navigation mode Navigation Mode Full Scale Deflection Enroute 5 0 nm Terminal 1 0 nm Approach 0 3 nm The TO FROM indicat...

Page 343: ...Copyright Eclipse Aviation Corporation Version 2 0 April 2007 323 14 3 7 Tile 5 Communication Navigation Surveillance Display Data Block and Right Line Select Keys Figure 214 Tile 5 Communication Navigation Surveillance TILE 5 DATA BLOCK Figure 215 Tile 5 Data Block ...

Page 344: ...rogated by ground based radar Line Select Keys and Concentric Knob RIGHT Five line select keys provide selection of communication and navigation and transponder sources frequency and transponder code entry as well as a monitoring feature Pilot control of these inputs is provided through three PFD pages COM NAV XPDR that are selectable through a rocker key below line select key five The COM page is...

Page 345: ...imums in FT MSL Set using right concentric knob Line Select Key 2 R2 MONITOR Active A Standby S Navigation frequency monitor selection NAV 1 A NAV 1 S NAV 2 A NAV 2 S Line Select Key 3 R3 NAV 1 Active A Standby S Navigation 1 Radio Selection Active Frequency Standby Frequency Line Select Key 4 R4 NAV 2 Active A Standby S Navigation 2 Radio Selection Active Frequency Standby Frequency Line Select K...

Page 346: ...onder will transition to altitude reporting with weight off wheels following takeoff and automatically transition back to GND following touchdown Line Select Key 4 R4 VFR VFR Transponder Code Selection Pressing this line select key automatically changes transponder CODE to 1200 Line Select Key 5 R5 NO FUNCTION Concentric Knob RIGHT Inner Knob CODE entry When the CODE line select field is highlight...

Page 347: ... for each individual audio source is located on the MFD AUDIO synoptic page All CNSand Audio control and display capabilities are available on the PFD and MFD Some alternative input methods are available via the keyboard Three radio pages are available selected with the right rocker key below right line select key 5 The rocker key is used to select the desired tab at the bottom right of the PFD CO...

Page 348: ... set to the 25 level Figure 216 COM Radio Tuning COM Radio Tuning 1 Select COM page using the rocker key 2 Only a standby S frequency can be tuned 3 Press right line select key 3 to tune the standby frequency for COM 1 or right line select key 4 to tune the standby frequency for COM 2 4 Tune the standby frequency by using the right concentric knob Rotating the outer portion of the concentric knob ...

Page 349: ...PFD with the appropriate COM window selected Com Radio Monitor In addition to the transmit radio one additional COM radio can be monitored with right line select key 2 Pressing the MONITOR line select key allows monitoring of COM 1 Standby S COM 1 Active A COM 2 Standby S COM 2 Active A OFF NOTE The ACTIVE COM radio cannot be monitored The monitor feature is independent of the other PFD this allow...

Page 350: ... and type of navaid VOR ILS are displayed below the NAV source The ACS automatically identifies the frequency by listening to the Morse code identifier comparing it to the navaid database When the frequency is positively identified the navaid identifier replaces the numeric frequency Selected course CRS xxx is displayed on the bottom line of the window Also displayed within the primary NAV line se...

Page 351: ...appears to the right of the BRG text The appropriate frequency and type of navaid VOR ILS are displayed below the NAV source The ACS automatically identifies the frequency by listening to the Morse code identifier comparing it to the navaid database When the frequency is positively identified the navaid identifier replaces the numeric frequency Selected current bearing BRG is displayed on the bott...

Page 352: ... frequency can be tuned 3 Press right line select key 3 to tune the standby frequency for NAV 1 or right line select key 4 to tune the standby frequency for NAV 2 4 Tune the standby frequency by using the right concentric knob Rotating the outer portion of the concentric knob bi directionally scrolls through the range 108 to 117 MHz in 1 MHz increments Rotating the inner portion of the concentric ...

Page 353: ...MS line select window as the MIN window below the altimeter on the PFD and as an amber horizontal line on both altimeters An entry on one PFD automatically enters it on the other PFD Entering Minimums 1 Select NAV page using the rocker key 2 Press right line select key 1 to activate a cursor in the MINIMUMS line select window 3 Rotating the outer portion of the concentric knob moves the cursor bet...

Page 354: ...ponder Code Entry 1 Select XPDR page using the rocker key 2 Press right line select key 2 to activate a cursor in the CODE window 3 Rotating the outer portion of the concentric knob moves the cursor between digits while rotating the inner portion of the concentric knob changes individual digits Transponder codes can also be set using the keyboard 1 Press the XPDR 1 or XPDR 2 key verify associated ...

Page 355: ...SBY GND keys to set transponder as necessary VFR Pressing the right line select key 4 automatically sets the VFR transponder code 1200 in the selected transponder IDENT Feature AVAILABLE ON KEYBOARD and SIDESTICK A transponder IDENT feature is available through a dedicated key on the keyboard There is also a pinky controlled switch on each sidestick dedicated to IDENT NOTE If the selected transpon...

Page 356: ...adio communication will still be available the pilot must select the opposite PFD using the COM SOURCE switch on the left switch panel 14 5 2 PFD Composite Mode Composite Mode allows the pilot to use pages that are normally available only on the MFD in the event of an MFD failure When selected for composite mode the PFD remains similar in appearance to the normal mode of operation however there ar...

Page 357: ...t rocker key on the PFD Keyboard Selection 1 Press the left or right PFD key 2 Press the PFD COMPOSITE key Figure 225 Keyboard Composite Group MFD Failure In the event of an MFD failure two page tabs labeled NORMAL and COMPOSITE automatically appear at the left bottom corner of the left PFD Figure 226 Composite Mode PFD Selection Select the COMPOSITE page with the rocker key NOTE Once COMPOSITE is...

Page 358: ... functions as selected with the COM NAV and XPDR keys at the bottom of the PFD Tile 6 Engine Instruments Engine information is permanently displayed on the left side of the PFD to the left of the airspeed indicator The following engine information is displayed N1 Tapes ITT Tapes Fuel Quantity Digital Display Tile 7 Aircraft Systems Pertinent aircraft system information is permanently displayed on ...

Page 359: ...O Acknowledgement of CAS messages is accomplished using the right line select key number five Primary Function Selection Selecting the primary function options is available using left line select keys 1 through 5 or by using the keyboard Composite Mode Page Selection from PFD Select the Composite Mode 1 Press left line select keys 1 through 5 for the desired Composite Mode page a L1 CKLST b L2 FMS...

Page 360: ...Section 14 Primary Flight Display PFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 340 Version 2 0 April 2007 Figure 228 Keyboard Primary Function Group ...

Page 361: ...PAGES Systems Page SYS The aircraft system synoptic and the operational pages can be selected with the left rocker key 1 Engine ENG 2 Fuel FUEL 3 Electrical ELECT 4 Electronic Circuit Breaker ECB 5 Environmental ENVIR 6 Pressurization PRESS 7 Ice Protection ICE 8 Operation OPS 9 Sensor SENSOR 10 Setup SETUP Figure 229 Composite Mode Systems PRESS ...

Page 362: ...mposite Mode for the duration of the flight Composite Mode Lockout To avoid conflicting commands only one user interface is active at one time If the left PFD is in composite mode with the MFD working system functions normally controlled through the MFD are locked out If only the right PFD is in composite mode with the MFD working functions are locked out on the MFD If both PFDs are in composite m...

Page 363: ...Section 14 Primary Flight Display PFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 343 Figure 231 PFD Composite Mode Warning CAS ...

Page 364: ...opyright Eclipse Aviation Corporation 344 Version 2 0 April 2007 14 6 Crew Alerting System Messages Table 36 PFD CAS Messages Message Condition Category AVIONICS COOLING FAN Left or Right PFD fans have failed Advisory XPDR 1 FAIL Transponder 1 or 2 has failed Advisory ...

Page 365: ... Indicated airspeed b True airspeed c Calibrated airspeed d Equivalent airspeed 5 When is Mach number displayed and when does it disappear 6 What does the airspeed trend vector display a Where airspeed will be in the next 10 seconds b Where airspeed will be in the next 6 seconds c The direction of change only d None of the above 7 What does the YSE bug that appears on the airspeed tape indicate a ...

Page 366: ... ADI when a localizer frequency is the primary navigation source a A small HSI b A small glide slope indicator will be displayed to the right of the ADI and a HDI will be displayed centered below the ADI c Both A B d None of the above 12 When does the altitude trend vector appear 13 When ALT CHG mode is active and the autopilot is engaged how will the altitude bug appear a Solid magenta b Solid gr...

Page 367: ...on Full or 120 arc d B C are correct 18 How is Rate of turn is indicated a With a white rate of turn indicator below the HSI b With a blue curved bar which appears above the compass rose c With a vertical hourglass shape that appears next to the HSI d None of the above 19 What are the two ways to enter the composite mode on the PFD a b 20 What information is lost from the PFD when composite mode i...

Page 368: ... MFD permanently displays important aircraft systems information including the MFD ADI engine instruments as well as the status of the landing gear flight control pressurization and fuel systems information Also included on the upper portion of the MFD is the Crew Alerting System CAS message window The lower portion of the MFD allows pilot control of the Flight Management System moving map electro...

Page 369: ...on 15 Multi Function Display MFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 349 15 2 Limitations and Specifications No content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 370: ...n 2 0 April 2007 15 3 System Description 15 3 1 Initialization Figure 233 MFD Initialization On initial power up of the MFD an initialization page displaying the version of Avio is presented Also presented are the version and effective dates of the Navigation Data This information should be verified prior to flight ...

Page 371: ...tiles are configurable Figure 234 MFD Tile Layout Tile 1 MFD Attitude Direction Indicator ADI Tile 2 Engine Instruments N1 Tape ITT Tape N2 Digital Display Fuel Flow Digital Display Oil Pressure Digital Display Tile 3 Landing Gear Status Flap Position Cabin Pressurization Current cabin altitude Current cabin altitude rate of climb Cabin differential pressure dP Fuel Quantity Indicator Trim Positio...

Page 372: ...he following information Air Data Source Selection ADC and AHRS Airspeed tape and digital airspeed readout KEAS Mach digital display Attitude Indicator Slip Skid Indicator Altimeter tape and digital altitude readout MSL Barometric altimeter setting 120 compass rose magnetic heading The following information is NOT displayed on the MFD ADI Flight Mode Annunciations FMAs Airspeed upper or lower redl...

Page 373: ...ce are displayed in the top left corner of the MFD ADI ADC 3 and AHRS 2 are the default air data and attitude information sources on initial start up The primary sources of air data and attitude information for the MFD ADI are selectable using the SENSOR synoptic page 15 4 2 Attitude Heading Reference System AHRS Sources AHRS 1 AHRS 2 AHRS 3 If Installed 15 4 3 Air Data Computer Sources ADC 1 ADC ...

Page 374: ...ine Instruments Tile 2 displays N1 and ITT tapes as well as N2 Fuel Flow and Oil Pressure in digital format 15 5 1 N1 RPM Figure 237 N1 RPM N1 is continuously displayed on the MFD with a moving tape and digital readout in percent of maximum RPM The scale of the tape is 0 to 105 An adjacent tape displays N1 limits A green band on the limit tape extends from approximately 21 to ...

Page 375: ...nds an ENG EXCEEDANCE warning message appears A blue bug and blue digital readout between the left and right N1 tapes display the N1 target calculated by the ACS for the mode of flight With the throttles advanced to the takeoff setting the state of the Automatic Power Reserve APR is displayed above the N1 tapes as either APR ARMED white or APR ON green Figure 238 APR Indications When the throttles...

Page 376: ...An ENG EXCEEDANCE warning message appears If ITT exceeds the limit but not above 810 C for 20 seconds If the ITT reaches 810 C 15 5 3 N2 RPM Figure 240 N2 RPM Display N2 is continuously displayed on the MFD with a digital readout in percent of maximum RPM and with a moving tape and digital readout on the ENG synoptic page The scale of the tape is 0 to 105 An adjacent tape displays N2 limits A gree...

Page 377: ...low is continuously displayed on the MFD with a digital readout in pounds per hour PPH and with a white moving tape and digital readout on the ENG synoptic page The scale of the tape is 0 800 PPH An adjacent tape displays fuel flow range with a green band extending from 60 PPH to the top of the tape There are no amber or red bands 15 5 5 Oil Pressure Figure 242 Oil Pressure Display ...

Page 378: ...f the engine RPM When oil pressure is in the normal green band range the moving tape and digital value are white If the oil pressure is in the caution amber bands range either high or low the tape and digital value are amber If the oil pressure is above 9 or below 1 the tape and digital value are red and a L R OIL PRESSURE HIGH or L R OIL PRESSURE LOW caution appears The amber bands and the lower ...

Page 379: ... Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 359 15 6 Tile 3 Aircraft Systems Tile 3 displays systems status information for the landing gear flaps cabin pressurization fuel and trim Figure 243 Aircraft Systems Display ...

Page 380: ...ar position displays the status of the gear by both the color and shape of the indicator A green circle with white border indicates the gear is Down and Locked Figure 244 Landing Gear Down Locked Indication An amber hatched square indicates the gear is in transit Figure 245 Landing Gear In Transit Indication A hollow white square indicates the gear is Up and Stowed ...

Page 381: ...operation on the PFD when gear is displayed on the upper right hand portion of the PFD gear Up and Stowed position annunciation does not disappear after ten seconds If any indicator is not up and stowed or down and locked the entire display stays in view and the failed gear is indicated with amber hatched squares If any gear is in transit for more than 15 seconds a LANDING GEAR FAIL caution messag...

Page 382: ...lap lever is moved a white box is displayed around the selected position The flap tick mark turns magenta until the flap position agrees with the flap lever position at which point the tick turns white and the white box disappears Figure 249 In Transit to T O Position When the flap position matches the flap lever position the display is white Figure 250 Flap Position Display T O Position Flap asym...

Page 383: ...sounds To silence the aural warning of the following conditions must be met A rate of descent of 1800 fpm or greater A descent below 12 500 ft NOTE A CABIN ALTITUDE warning message indicates a cabin altitude of 10 000 ft and which may indicate a rapid cabin depressurization RATE FPM Cabin altitude rate of change rounded to the nearest 100 fpm is presented Should the cabin altitude rate be too high...

Page 384: ... Total fuel quantity remaining in pounds is displayed above the scale The total quantity display turns amber when fuel remaining is less than 280 pounds and red when fuel remaining is less than 210 pounds An individual sump quantity display appears below the total fuel quantity scale with the quantity digits in amber if least one sump tank quantity decreases to the caution level of 140 pounds or l...

Page 385: ...el quantity information Trim is indicated by a white pointer and a green band indicates the allowable trim range for takeoff If throttles are advanced to takeoff power with the trim pointer is outside of the green band on any of the three indicators a CONFIG PITCH TRIM CONFIG AILERON TRIM or CONFIG RUDDER TRIM warning message appears If this occurs re trim until the indicator is within the green b...

Page 386: ...tones that are transmitted to the crew headphones and speakers A single concentric knob located on the upper right side of the MFD is used to select and acknowledge CAS messages Figure 255 CAS Message Display 15 7 1 CAS Message Classifications Hierarchy CLASSIFICATION There are four classifications of CAS messages warning caution advisory and status Warning Messages A red warning message alerts co...

Page 387: ...s keep the pilot informed without burdening him her with nuisance or unnecessary information HIERARCHY Warning messages have priority over cautions and cautions have priority over advisories On the CAS message window warnings are always displayed above cautions and cautions are always displayed above advisories Status messages are located at the bottom of the CAS message window below a white divid...

Page 388: ...ompanying aural alert and flashing master warning caution button lights for warning and caution conditions Figure 257 CAS Message Annunciation Figure 258 Warning Caution Button Advisory messages are not accompanied by aural alerts or master warning caution button lights A selection box is automatically presented around the message NOTE Status level messages cannot be highlighted using the selectio...

Page 389: ...age shall disappear Checklist and synoptic remain on the MFD tiles until the pilot selects a different view 5 Upon checklist completion if available and if the event has not been corrected the CAS message shall move to the recall bin Recall The recall function provides the ability to recall previous warning caution and advisory CAS messages where the condition still exists those that have not been...

Page 390: ...r warning alert tone VISUAL Warning light on autopilot control panel illuminates and CAS message appears on MFD The warning light stays on until the condition goes away or the master warning button is pressed by the pilot The CAS message remains until the condition goes away or the checklist has been completed and the corrective action accomplished Cabin Altitude CONDITION Cabin altitude exceeds 1...

Page 391: ...Master warning light illuminates Red FIRE portion of the FIRE ARMED button illuminated L ENG FIRE or R ENG FIRE Warning message The master warning light is extinguished when the pilot presses the master warning button A single press of the FIRE ARMED button ceases fuel flow and automatically closes several engine related control valves and illuminates the green ARMED portion of the FIRE ARMED butt...

Page 392: ...um altitude AUDIO Voice Message Approaching Minimums VISUAL NONE Minimums CONDITION Descending through preset minimum altitude AUDIO Voice message Minimums VISUAL NONE Master Caution CONDITION Alert associated with amber caution level CAS messages AUDIO Master caution alert tone VISUAL Caution Light on autopilot control panel illuminates and CAS message appears on MFD The caution light stays on un...

Page 393: ...elected altitude blue text disappears Deviation Alert greater than 200 feet from selected altitude Amber ALTITUDE DEVIATION text appears below the altitude set in the pre select window Landing Gear Warning CONDITION Landing gear is up when aircraft is in landing configuration below 12 500 feet Flaps extended beyond T O setting Airspeed less than 120 knots and either or both throttles below mid ran...

Page 394: ...sage is not annunciated to the flight crew prior to departure proceeding with the takeoff is not approved The T O CONFIG OK Status Message is automatically removed when the throttles are advanced for takeoff T O Config Warning Messages If the throttle is advanced for takeoff when the airplane is not correctly configured the takeoff warning horn sounds and a red warning message is displayed showing...

Page 395: ...set to MAP lower right is set to page previously on lower left FMS Lower left tile set to FMS lower right tile set to MAP CKLST Lower left tile set to Checklists lower right tile set to the associated system synoptic page SYS Lower left set to last used systems synoptic page or if last page not known to the first page in the tabbed list ENG Available Synoptics and features are listed below A more ...

Page 396: ...ry of cabin altitude rate landing altitude Ice Protection ICE Status of engine anti ice system Status of wing stabilizer deice boot function Status of pitot static AOA heater Status and temperature of windshield heater Flight Controls FLCS Status of trim Manual trim Disabling of ALL INTERRUPT sidestick switch Operations OPS Weight and balance entry Rotation and reference speed entry Systems tests ...

Page 397: ...noptics There are several additional synoptic pages AUDIO OPS SENSOR SETUP available for pilot use AUDIO SYNOPTIC Figure 263 Pilot Audio Synoptic Page Figure 264 Co Pilot Audio Synoptic Page The AUDIO synoptic page is selected with a single or double press of the AUDIO primary function key on the MFD A single press of the primary function key displays ...

Page 398: ... while a double press displays the pilots audio page on tile 6 lower left and the co pilots audio page on tile 7 lower right tile This synoptic allows selection of Pilot and Co Pilot audio setup intercom and cockpit radio split Line select keys on the audio synoptic SELECT PILOT COPlLOT INTERCOM PILOT ISOL CREW ISOL TX SELECT NORMAL SPLIT ECB LINK Links to Avionics ECB synoptic page ...

Page 399: ... audio selection There are also several hollow outlined boxes on the left side of each audio selection With an audio setting selected pressing the inner portion of the right knob fills this box allowing the audio for this selection to be heard over an activated speaker The Transmit Radio shall be identified by a TX RX next to it in the Audio Page source list The Monitor Radio shall be identified b...

Page 400: ...above the PA key is illuminated The MFD Audio Page does not have to be displayed Pilot Isolate PILOT ISOL Pressing the PILOT ISOL key toggles the intercom mode between its current mode and pilot isolate mode If the intercom was already in pilot isolate mode pressing this key has no effect When the pilot isolate is active the light above the PILOT ISOL key is illuminated OPS The Operations OPS syno...

Page 401: ...nger two PAX 2 passenger three PAX 3 passenger four PAX 4 and baggage BAGGAGE are automatically summed and indicated on the PAYLOAD line NOTE If a value of 260 lbs is entered into the BAGGAGE field the value turns red indicating that compartment capacity is over design limits Aircraft empty weight is automatically displayed and is non selectable Available fuel load as calculated by the ACS is auto...

Page 402: ...cursor over a value in a weight field resets the value to the default setting Pressing the RESET line select key with the FUEL line selected will remove the amber MAN text and reset the fuel value to the weight calculated by the ACS RETURN TO OPS Pressing the RETURN TO OPS line select key displays the AIRCRAFT OPERATIONS portion of the OPS page Figure 267 OPS Weights Synoptic Page ...

Page 403: ...nd flap settings appears in the window This speed is also automatically bugged on the airspeed tape on the PFDs Rotating inner portion of the concentric knob clockwise or counterclockwise manually increases the rotation speed value in one knot increments and automatically changes the bugged airspeed to the selected value When a rotation speed is manually selected amber MAN text appears in the VR l...

Page 404: ...clipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 384 Version 2 0 April 2007 RETURN TO OPS Pressing the RETURN TO OPS line select key displays the AIRCRAFT OPERATIONS portion of the OPS page Figure 268 OPS VSPEED Synoptic Page ...

Page 405: ...Section 15 Multi Function Display MFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 385 Figure 269 OPS VSPEED Manual VR Entry ...

Page 406: ...his will activate the selected system test displays a Test in progress message below the TESTS window as well as brings up a STOP TEST line select key option Pressing the STOP TEST line select key will abort the test COCKPIT LAMPS TEST Activating this test will automatically command the autopilot control panel center switch panel and keyboard lights to illuminate This test is available in flight a...

Page 407: ...FD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 387 Figure 270 OPS Systems Test RETURN TO OPS Pressing the RETURN TO OPS line select key displays the AIRCRAFT OPERATIONS portion of the OPS page ...

Page 408: ...ilure of either primary AHRS source 1 or 2 occur the off side PFD will automatically use the remaining operating AHRS 1 Selection of 1 for the AHRS SRC manually sets both the left and right PFD to uses AHRS 1 2 Selection of 2 for the AHRS SRC manually sets both the left and right PFD to uses AHRS 2 PFD ADC SRC The Air Data Computer Source ADC SRC line select key allows selection of the ADC source ...

Page 409: ...Section 15 Multi Function Display MFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 389 Figure 271 SENSOR Synoptic Page ...

Page 410: ...mming setting as well as the ability to see the software versions for the left and right PFDs as well as the MFD SHOW VERSIONS Pressing the SHOW VERSIONS line select key will display the current software versions for the left PFD as well as provide a SYSTEM line select key option Pressing the SYSTEM line select key will change the synoptic page display between left PFD right PFD and MFD Figure 272...

Page 411: ...d the switch panel below the PFD and is accessed by pushing a door cover that will fold under the keyboard when it is deployed The keyboards do not replace any functionality on the PFD and MFD and are designed to provide a secondary and in some cases easier means of selection and programming on the displays by providing one button push functions that might require several steps on the PFD or MFD T...

Page 412: ...ITE one time changes the left PFD into Composite Mode Pressing PFD COMPOSITE again toggles the left PFD back to Normal Mode If the R PFD key is active pressing PFD COMPOSITE one time changes the right PFD into Composite Mode Pressing PFD COMPOSITE again toggles the right PFD back to Normal Mode Only one of the L PFD or R PFD keys can be active at any time 15 9 3 Transponder Group Figure 275 Keyboa...

Page 413: ...A code displayed in the CODE line select window on the PFD To change a code press the XPDR SQWK and enter four digits using the keyboard then press ENTER This will set the code in the CODE line select window SBY Sets the selected transponder to Standby Mode ALT Sets the selected transponder to reply to ATC interrogations with both Mode A and Mode C replies using whatever Mode A code is currently s...

Page 414: ...To data entry block ready to receive a waypoint identifier and MFD tile 7 set to Moving Map AFM Pressing the AFM key brings up the AFM portion of the OPS page on tile 6 of the MFD and shifts previously shown information on tile 6 to tile 7 PREV Previous Pressing PREV selects the previous to the left tabbed page on tile 6 of the MFD NEXT Pressing NEXT selects the next to the right tabbed page on ti...

Page 415: ...e 6 and 7 only when alphabetic character input is appropriate The four alphanumeric keys associated with the cardinal headings N S E and W are highlighted with a white square 15 9 6 Numerical Group Figure 278 Keyboard Numerical Group The numerical group consists of the keyboard s numerical character keys plus the and ENTER keys located in the middle area of the keyboard Key presses in this group m...

Page 416: ...by frequency The user may enter a new frequency at the cursor position SWAP Pressing this key exchanges the active frequency and standby frequency for the communication radio whose line select key window contains the highlighted cursor MIN SET Allows the pilot to edit the minimum altitude displayed in the MIN pre select window below the altimeter To change altitude press the MIN SET and enter four...

Page 417: ...tercom Pilot Isolate Mode on and off The light on the keyboard above the PILOT ISOL key illuminates when the pilot isolate mode is on Both the Left and Right Keyboards can control this function MB Pressing this key toggles the Marker Beacon received audio on and off for the associated crew member The Left Keyboard controls Pilot MB audio and the Right Keyboard if installed controls Copilot MB audi...

Page 418: ...Section 15 Multi Function Display MFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 398 Version 2 0 April 2007 15 10 Normal Operations No Content THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 419: ... Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 399 15 11 Abnormal Procedures 15 11 1 MFD Failure In the event that a MFD fails all flight information will be available through the primary standby indications on the PFDs ...

Page 420: ...L One or more data busses have been lost Advisory L KEYBOARD FAIL L or R Keyboard has failed Advisory 15 13 Takeoff Configuration Warnings Table 39 Takeoff Configuration Warnings Message Condition Categories CONFIG AILERON TRIM Aileron trim is not within takeoff limits and TLA past 40 Warning CONFIG ELEV TRIM Elevator trim is not within takeoff limits and TLA past 40 Warning CONFIG FLAP Flaps exte...

Page 421: ...Section 15 Multi Function Display MFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 401 ...

Page 422: ... Multi Function Display MFD Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 402 Version 2 0 April 2007 15 14 MFD Review Questions 1 List the information contained within each of the tiles below ...

Page 423: ... are advanced to takeoff power what is displayed above the N1 Tape a TAKEOFF POWER in green text b T O in white text c APR ARMED in white text with both engines operating d APR ON in green text when a single engine is operating e Both C D are correct 5 List the visual indications of a flap failure on the MFD 6 How is cabin altitude displayed a With an analog cabin altimeter mounted below the MFD b...

Page 424: ...p to bottom of CAS message hierarchy as well as their associated colors 9 How can a pilot silence an aural alert accompanied with a CAS message 10 The pilot sets the desired cockpit and cabin temperatures on the _________ synoptic page 11 What is the purpose of maintenance mode Can the pilot access this mode and if so how 12 Describe the functionality of the AUDIO primary function key 13 Holding t...

Page 425: ...keyboard is the ONLY way to tune NAV 1 NAV 2 b The keyboard is the ONLY way to set the transponder c The keyboard is the ONLY way to switch the PFD to composite mode d The keyboard does NOT replace any functionality It is designed as a secondary interface with the PFD and MFD 19 In the event of a MFD failure what shall the pilot do a Land immediately and except a sudden loss of electrical power b ...

Page 426: ...s are also sent to the PFD s for display of the autopilot targets and flight mode annunciation Each autopilot servo contains a motor control as well as an autopilot computer that receives and process autopilot commands from the pilot The autoflight system also sends automatic trim commands for pitch trim through the PFDs to the left and right ACS Additional inputs from the all interrupt autopilot ...

Page 427: ... Left PFD Optional R KBD MFD Right ISS Engine Start Switches ACS PFD Communications Bus Left Byteflight Bus Right Byteflight Bus ACS PFD Communications Bus Right ACS Stick Force Yaw Servo Pitch Servo Roll Servo Right Byteflight Bus Left Byteflight Bus Inter Servo Communications Center Pedestal Left Sidestick Right Sidestick Stick Force TOGA A T Disconnect Figure 281 Autoflight ACS Interface ...

Page 428: ...d and altitude restrictions apply Do not intentionally overpower the autopilot Autopilot and Yaw Damper must be selected OFF for takeoff and landing Autopilot minimum use height Climb Enroute or Descent 1 000 feet AGL Approach Precision 400 feet AGL Visual and non precision 400 feet AGL Autopilot must be operational for RVSM operations Stall Protection System and Stick Pusher must be successfully ...

Page 429: ...damper if not already engaged by autopilot engagement When engaged green YD text appears on the upper left portion of the PFD as well as illumination of a green light on the yaw damper button NOTE The yaw damper is automatically engaged with autopilot engagement Figure 283 Autopilot and Yaw Damper Engaged Indications PFD AP OFF ON AUTOPILOT OFF ON The AP OFF ON button engages and disengages the au...

Page 430: ...t window appears directly above the airspeed tape that displays the digital value in addition to the magenta bug Rotating the SPD SEL knob clockwise or counterclockwise respectively increases and decreases the value of the airspeed bug Pressing the SPD SEL knob synchronizes the airspeed bug and pre select value to the current airspeed NAV NAVIGATION The NAV button allows lateral autopilot navigati...

Page 431: ...t When ALT CHG is selected green ALT CHG text appears in the flight mode annunciation window on the PFD THUMB WHEEL UP DOWN The thumb wheel provides selection of both vertical speed and pitch targets for climbs and descents When the autopilot is operating in PITCH only mode rotating the thumb wheel up or down adjusts the flight director command bars When the autopilot is operating in ALT CHG desce...

Page 432: ...n Figure 285 Flight Mode Annunciation Window MODES OF OPERATION Within the three categories of autopilot mode annunciation there are a number of flight mode annunciations that are divided into lateral vertical approach and speed modes With the exception of the takeoff T O mode a flight director only mode all the autopilot modes are the same as flight director modes When a previously armed mode bec...

Page 433: ... Hold HDG Navigation FMS FMS Armed FMS FMS Capture Track FMS Navigation VOR VOR Armed VOR VOR Capture Track VOR Navigation LOC LOC Armed LOC LOC Capture Track LOC Go Around G A HDG HOLD Takeoff FD Only TO ROLL Table 41 Vertical Flight Mode Annunciations Category Sub Mode ACTIVE Text ARMED Text Pitch Hold PITCH Altitude Altitude Capture ALT CAP ALT Altitude Track ALT ALT Altitude Change ALT CHG Cli...

Page 434: ...ertical Text ARMED Vertical Lateral Text Capture Track LOC APPR VOR Armed VOR APPR Capture Track VOR APPR ILS LOC GS Armed LOC APPR GS LOC GS Capture Track LOC APPR GS FMS Armed FMS APPR Capture Track FMS APPR Table 43 Autothrottle Speed Flight Mode Annunciations Category Sub Mode ACTIVE Text Speed Hold SPD HOLD Thrust Reference Max Continuous Thrust MCT MCT Underspeed Protection SPD PROT Autothro...

Page 435: ...ntrols the ailerons elevators and rudder to meet the targets set by the flight director depicted on the PFD Green AP text appears in the upper left hand portion of the ADI to indicate that the autopilot is engaged The yaw damper can be independently engaged in the roll ailerons and pitch elevator axis Should the autopilot be engaged without any previous flight director modes selected the autopilot...

Page 436: ...irector The single cue flight director is presented on each PFD over imposed onto the ADI The autopilot function is inclusive of the flight director function as it is not possible to have autopilot engaged without the flight director on Should the autopilot be engaged while flight director modes are active the autopilot will engage with those modes active ENGAGEMENT The engagement envelope of the ...

Page 437: ...movements leading to Dutch Roll The servo has as much authority as the rudder can travel ENGAGEMENT The yaw damper engagement envelope is the same as the autopilot The yaw damper is engaged manually by pressing the YAW DAMP button on the autopilot control panel but will always automatically engage when the autopilot is selected and the yaw damper wasn t already engaged Once engaged green YD text a...

Page 438: ...ion The autoflight system continuously monitors airspeed trends and uses the autothrottles to prevent an aircraft overspeed or stall as the aircraft nears overspeed VMO MMO or underspeed stall In addition to speed protection the autoflight systems also uses the autothrottles to aid the stall protection system in preventing a deep stall OVERSPEED PROTECTION If the aircraft will exceed maximum speed...

Page 439: ... and limit airspeed Autothrottle Automatically engages to control and limit airspeed Autopilot Controls roll attitude to its state prior to the Underspeed protection engagement limited to 15 Holds the altitude prior to the Underspeed engagement Autopilot Will NOT automatically engage pilot must manually control airspeed using pitch elevator Figure 288 Over and Underspeed Protection Flight Mode Ann...

Page 440: ...flight mode annunciation window In addition the autopilot will set a fixed pitch target based on the number of operating engines and display GA PITCH as the active pitch mode in the flight mode annunciation window As with takeoff mode go around mode will not capture a pre selected altitude To capture a pre selected altitude ALT CHG must first be pressed Figure 289 TOGA Flight Mode Annunciations RO...

Page 441: ...rse is set by using the lower left concentric knob on the PFD When arming the navigation mode using a VOR frequency VOR text appears as the armed mode in the flight mode annunciation window When the autopilot captures the VOR course VOR appears pulses for three seconds and then becomes steady as the active mode If the autoflight system detects that the aircraft is flying over the station the fligh...

Page 442: ...he autopilot flight director is using the altitude bug as a target The target bug will not synchronize itself to the altitude being tracked and will remain a hollowed outline associated with the altitude the pilot had previously selected To select a new altitude with the altitude bug the pilot must use the ALT SEL knob on the autopilot control panel ALT CHG Alt change mode behaves differently base...

Page 443: ...C APPR appears as the active mode in the flight mode annunciation window The APPR LOC will enable the GS capture if signal is present for use on ILS approaches The flight director will use vertical deviation indication to compute guidance in order to center it If the ACS detects a back course signal it will automatically reverse the polarity of the CDI In addition to the appearance of the LOC APPR...

Page 444: ...t APPR annunciation will replace TERM on the PFD near the HSI and is not related to the Autoflight Annunciation SPEED MODES Speed Hold Speed hold is the default speed mode when the autothrottle system is activated using the ATS OFF ON button on the autopilot control panel When activated SPD HOLD appears in the speed portion of the flight mode annunciation window This mode tracks the target airspee...

Page 445: ...an be overpowered without causing AP to disconnect While overpowering in PITCH forward aft direction the following will occur a The pitch trim tab will be commanded to move b The Trim In Motion aural alert will sound after trim servo moving for 2 seconds c The PITCH MISTRIM CAS will appear after about 4 seconds indicating pitch clutch slippage 7 Verify that the rudder pedals can be overpowered wit...

Page 446: ...F ON button on the Autopilot Control Panel AP OFF ON button on the Autopilot Control Panel AP mode buttons on the Autopilot Control Panel 16 6 2 Before Takeoff After positioning the aircraft on the runway centerline the pilot will configure the aircraft for takeoff by pressing the TOGA button In the takeoff mode the flight director will not be coupled to the autopilot until the autopilot is turned...

Page 447: ...vigation source to be captured otherwise the heading should be adjusted so an appropriate intercept can be made VOR Navigation Selected on PFD and ARMED HDG Æ VOR ALT CHG Æ ALT VOR Navigation Selected on PFD and Active VOR ALT CHG Æ ALT Aircraft Asked to Hold Current Altitude During Climb While climbing in ALT CHG Mode the pilot may press the ALT button to cancel active climb and hold the current ...

Page 448: ...l panel to set the desired altitude using the altitude bug This newly selected altitude will appear on the PFD and pressing ALT CHG to capture the new altitude After reaching and capturing the pre selected altitude the pilot need not take further action unless a further climb or descent is required VOR ALT CHG Æ ALT Descent To descend the pilot must select the desired altitude with the ALT SEL kno...

Page 449: ...to capture and hold the aircraft s current altitude Level off Altitude Capture In Progress VOR ALT CAP Æ ALT Level Off Altitude Captured VOR ALT Descent Continued From Level off To continue the descent from an intermediate level off the pilot need only press the ALT CHG button This will resume the descent to the previously selected altitude If this altitude needs to be changed the ALT SEL knob can...

Page 450: ... as the armed lateral mode and GS appears as the armed vertical mode When the localizer and glideslope courses are captured they become the active modes for the autopilot ILS Intercept from HDG Mode SPD HDG Æ LOC APPR ALT Æ GS ILS Approach After Course Capture In order for the glideslope to be captured the autopilot must first be able to capture and track the localizer When the localizer course ha...

Page 451: ...nd the throttles should be advanced to maintain airspeed The aircraft will fly with roll hold and pitch hold during TOGA operations Following the go around ALT CHG mode can be selected and it may necessary to change the pre selected altitude for the missed approach procedure Missed Approach With VOR Mode Armed HDG HOLD Æ VOR GA PITCH Missed Approach After VOR Mode and ALT CHG Have Activated VOR AL...

Page 452: ...ON FAIL caution message appears A similar message appears in the event of only a stick pusher failure in this case it is a STICK PUSHER FAIL caution message If either message appears in flight it requires the pilot to increase the final approach speed possibly increase landing distance based on the flap setting and limit bank angles to less than 30 to protect against potential stalls in the landin...

Page 453: ...essage Condition Categories AUTOPILOT FAIL Autopilot system component has failed Caution AP FD MODE CHANGE Uncommanded mode transition Caution PITCH MISTRIM Autopilot is maintaining constant forces on elevator Caution STALL PROTECTION FAIL Stall warning and stick pusher have failed Caution STICK PUSHER FAIL Stick pusher has failed Caution YAW DAMPER FAIL Yaw damper has failed Caution ...

Page 454: ...Section 16 Autoflight Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 434 Version 2 0 April 2007 ...

Page 455: ...ted a b 5 When climbing in ALT CHG mode how will the speed bug appear a Hollow b Solid c Hollow and will change color to magenta d Solid and will change color to green 6 What will happen when the HDG SEL knob is pressed on the autopilot control panel a The heading bug will become solid b The heading bug will sync with the aircraft s current heading c Nothing the HDG SEL knob cannot be pressed d No...

Page 456: ... pilot can never override the stick pusher b By pressing and holding the ALL INTERRUPT button on the side stick c By overpowering the stick pusher causing the servo clutches to slip d Both B C 10 Describe how the autopilot test is activated 11 What does the appearance of a AP FD MODE CHANGE caution message indicate 12 What are the two primary modes of operation for the Eclipse 500 autopilot system...

Page 457: ...Section 16 Autoflight Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation Version 2 0 April 2007 437 ...

Page 458: ...Section 16 Autoflight Eclipse 5OO Systems Manual Copyright Eclipse Aviation Corporation 438 Version 2 0 April 2007 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 459: ...Copyright Eclipse Aviation Corporation Version 2 0 April 2007 Index 1 Index S sample entry 1 ...

Page 460: ...Eclipse 5OO Systems Manual Index Copyright Eclipse Aviation Corporation Index 2 Version 2 0 April 2007 ...

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