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Eclipse 500 System Manual

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Table of Contents

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Eclipse 5OO Systems Manual
Contents
1. Aircraft Overview .......................................................................................................................1
1.1 GENERAL ...........................................................................................................................1
1.2 AIRCRAFT DIMENSIONS ...................................................................................................3
1.3 SEATING ARRANGEMENTS..............................................................................................4
1.4 PERFORMANCE AND CAPABILITIES ...............................................................................6
1.4.1 Performance ..............................................................................................................6
1.4.2 Aircraft Parameters and Capabilities ..........................................................................7
1.5 ECLIPSE 500 AIRCRAFT SYSTEMS .................................................................................8
1.5.1 Avio Avionics Suite ....................................................................................................8
1.5.2 Thrust Control............................................................................................................8
1.5.1 Essential Systems .....................................................................................................8
1.5.2 Mechanical Flight Controls ........................................................................................8
1.6 AUDIO ..................................................................................................................................9
1.6.1 Cabin Speakers .........................................................................................................9
1.6.2 Handheld 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
2.3.2 Multi-Function Display (MFD) ..................................................................................19
2.4 PILOT CONTROLS ...........................................................................................................21
2.5 PRIMARY SENSORS........................................................................................................31
2.6 AIRCRAFT SUBSYSTEMS ...............................................................................................31
2.7 AVIONICS OVERVIEW REVIEW QUESTIONS ................................................................33
3. Flight Controls .........................................................................................................................35
3.1 GENERAL .........................................................................................................................35
3.2 AIRCRAFT COMPUTER SYSTEM (ACS) INTERFACES .................................................36
Version 2.0 April 2007
Copyright © — Eclipse Aviation Corporation
i

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Summary of Contents for Eclipse 500

  • Page 1 1.3 SEATING ARRANGEMENTS....................4 1.4 PERFORMANCE AND CAPABILITIES ................6 1.4.1 Performance ......................6 1.4.2 Aircraft Parameters and Capabilities ................7 1.5 ECLIPSE 500 AIRCRAFT SYSTEMS .................8 1.5.1 Avio Avionics Suite ....................8 1.5.2 Thrust Control......................8 1.5.1 Essential Systems .....................8 1.5.2 Mechanical Flight Controls ..................8 1.6 AUDIO ..........................9...

  • Page 2: Table Of Contents

    4.5.5 Landing Gear Warning Horn..................62 4.5.6 Nose Wheel Steering....................62 4.5.7 Brakes ........................62 4.5.8 Parking Brake ......................63 4.5.9 Hard Landing Indicators ..................63 4.6 NORMAL OPERATIONS....................65 4.6.1 Gear Retraction .......................65 4.6.2 Gear Extension......................65 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 3 6.3.3 Windshield Heat ......................96 6.4 CONTROLS AND INDICATORS ..................97 6.4.1 Center Switch Panel-Ice Protection .................97 6.4.2 Ice Protection Synoptic....................98 6.5 SYSTEM DESCRIPTION ....................99 6.5.1 Windshield Heat ......................99 6.5.2 Defog........................100 6.5.3 Pneumatic De-ice ....................100 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 4 7.5.13 Vent System ......................128 7.5.14 Fuel Pressure Measurement ................128 7.5.15 Fuel Balancing.....................130 7.6 NORMAL OPERATIONS....................131 7.6.1 Fueling........................131 7.7 ABNORMAL PROCEDURES ..................132 7.7.1 Automatic Fuel Balance Failure................132 7.8 CREW ALERTING SYSTEM MESSAGES ..............133 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 5 8.5.6 Engine Fuel System ....................167 8.5.7 Bleed Air........................168 8.5.8 Oil System ......................168 8.5.9 Fire Protection .......................170 8.6 NORMAL OPERATIONS....................174 8.6.1 Engine Start......................174 8.6.2 Engine Shutdown ....................175 8.6.3 Engine Dry Motoring....................175 8.6.4 Takeoff ........................176 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 6 10.5.1 Starter/Generator Units ..................224 10.5.2 Generator Control Units (GCUs) .................224 10.5.3 Batteries ......................224 10.5.4 225 External Power ........................225 10.5.5 Electrical Buses ....................227 10.5.6 Circuit Protection ....................228 10.6 NORMAL OPERATIONS....................233 10.6.1 Ground Operation....................233 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 7 12.8 CREW ALERTING SYSTEM MESSAGES ..............270 12.9 EXTERIOR LIGHTING REVIEW QUESTIONS .............271 13. Air Data ..........................274 13.1 GENERAL ........................274 13.2 AIRCRAFT COMPUTER SYSTEM (ACS) INTERFACES ..........275 13.3 LIMITATIONS AND SPECIFICATIONS................278 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 8 15.4.1 Air Data Source Selection (ADC & AHRS) ............353 15.4.2 Attitude Heading Reference System (AHRS) Sources ........353 15.4.3 Air Data Computer Sources.................353 15.5 TILE 2 – ENGINE INSTRUMENTS ................354 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007 viii...
  • Page 9 16.5.4 Pitch Auto Trim ....................417 16.5.5 Yaw Damper......................417 16.5.6 Autothrottle ......................417 16.5.7 Flight Envelope Protection...................418 16.5.8 Stick Pusher ......................419 16.5.9 Modes of Operation .....................419 16.6 NORMAL OPERATIONS....................425 16.6.1 Before Taxi ......................425 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 10 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 11 Figure 40.Landing Gear Position Annunciation ............57 Figure 41.Main Landing Gear ..................60 Figure 42.Nose Landing Gear..................61 Figure 43. Brake Wear Indicators ................63 Figure 44.Nose Gear Hard Landing Indicator.............64 Figure 45.Main Gear Hard Landing Indicator .............64 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 12 Figure 89.Secondary Engine Parameter-ACS Interface...........142 Figure 90.Fire Detection and Suppression-ACS Interface ........143 Figure 91.Starter Assisted Air Start Envelope ............147 Figure 92.Engine Temperature Operating Envelope ..........148 Figure 93.Engine Start Switch Panel ................149 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 13 Figure 136.Cabin Dump Switch ................209 Figure 137.Cabin Dump- PRESS Synoptic ..............210 10. Electrical..........................217 Figure 138.Electrical Power Distribution-ACS Interfaces .........219 Figure 139.Electrical Switches..................221 Figure 140.Electrical Synoptic ..................222 Figure 141.Battery State Display ................223 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007 xiii...
  • Page 14 Figure 181.Mach Indication..................298 Figure 182.Airspeed Bug ..................299 Figure 183.Airspeed and Mach Exceedance............300 Figure 184.Attitude Direction Indicator..............301 Figure 185.Horizon Reference Pointers..............301 Figure 186.Pitch Chevrons ..................302 Figure 187.Roll Indications ..................302 Figure 188.Slip/Skid Indicator ...................303 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 15 Figure 233.MFD Initialization ..................350 Figure 234.MFD Tile Layout..................351 Figure 235.MFD ADI ....................352 Figure 236.Engine Instruments.................354 Figure 237.N1 RPM ....................354 Figure 238.APR Indications ..................355 Figure 239. ITT Display.....................355 Figure 240.N2 RPM Display ..................356 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 16 Figure 287.Flight Director- Autopilot Engaged............417 Figure 288.Over and Underspeed Protection Flight Mode Annunciation ....419 Figure 289.TOGA Flight Mode Annunciations............420 Figure 290.PITCH and ROLL Hold Flight Mode Annunciations........421 Figure 291.Altitude Change Flight Mode Annunciations...........423 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 17 Table 29.Climate Control System CAS Messages............213 10. Electrical..........................217 Table 30.Electronic Circuit Breaker States..............224 Table 31.Electrical CAS Messages ................238 11. Interior Lighting ........................243 Table 32.Interior Light Center Switch Panel Controls ..........246 12. Exterior Lighting........................260 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007 xvii...
  • Page 18 Table 42.Approach Flight Mode Annunciations............413 Table 43.Autothrottle/Speed Flight Mode Annunciations ..........414 Table 44.Overspeed Protection Based on Autopilot Engagement......418 Table 45.Underspeed Protection Based on Autopilot Engagement......419 Table 46.Autoflight CAS Messages................433 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007 xviii...
  • Page 19 Table of Contents Eclipse 5OO Systems Manual THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 21: Aircraft Overview

    1. Aircraft Overview 1.1 General The Eclipse 500 is a twin-turbofan aircraft powered by two Pratt & Whitney Canada PW610F-A engines. It is a five- to six-place, low-wing, T-tail aircraft using conventional aircraft semi-monocoque structural elements joined together using both friction stir welding and mechanical fasteners.

  • Page 22: Figure 1.Eclipse 500

    Section 1. Aircraft Overview Eclipse 5OO Systems Manual Figure 1. Eclipse 500 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 23: Figure 2.Aircraft Dimensions

    Section 1. Aircraft Overview Eclipse 5OO Systems Manual 1.2 Aircraft Dimensions Figure 2. Aircraft Dimensions Figure 3. Cabin Dimensions Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 24: Figure 4.Standard Five Seat Configuration

    To return the seats to the upright position, push the seatback up and aft until it locks in position. Figure 4. Standard Five Seat Configuration Figure 5. Six Seat Configuration Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 25: Figure 6.Four Seat Configuration

    Section 1. Aircraft Overview Eclipse 5OO Systems Manual … Figure 6. Four Seat Configuration Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 26: Table 1.Performance Data

    (Flaps TO) (Flaps LDG) Limit Load Factors Operational Limitations Flaps UP +3.62/-1.45 g’s Max operating altitude 41,000 ft Max Cabin Pressure Differential 8.7 PSI Single engine service ceiling 25,000 ft Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 27: Table 2. Aircraft Parameters And Capabilities

    Two Pratt & Whitney 610F 900 lbs Wing Span 37.4 ft turbofan engines Thrust Wing Sweep leading edge Design Life 20,000 Wing Area 144.4 ft Hours hours 20,000 Aspect Ratio 8.88 Cycles cycles Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 28 PW610F-A high-bypass turbofan engines. These engines produce high fuel efficiency and lower noise output in comparison to an average 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.
  • Page 29 PFD. When a member of the flight crew pushes the handheld Push-To-Talk button, the microphone audio is transmitted over COM1 or COM2, depending on the flight crew/member’s radio selection. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 30: Figure 7.Fire Extinguisher

    (if available). Figure 7. Fire Extinguisher Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 31: Figure 8.Emergency Exit

    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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 32: Figure 9.Passenger Oxygen

    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.

  • Page 33: Aircraft Overview

    8. The single engine service ceiling is: a. 25,000 feet b. 35,000 feet c. 41,000 feet d. None of the above 9. What are the four major functional areas that comprise the Eclipse 500? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 34 Section 1. Aircraft Overview Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation...

  • Page 35: Figure 10.Cockpit Layout

    It is along these data busses that commands are sent to the aircraft and systems status information is then returned to the pilot. Figure 10. Cockpit Layout Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 36: Figure 11.Avionics Architecture

    Systems Systems ACS-Aircraft Systems Buses ACS-Aircraft Systems Buses THE FIVE MAJOR FUNCTIONAL AREAS OF AVIO Aircraft Computer Systems Pilot Displays Pilot Controls Primary Sensors Aircraft Subsystems Figure 11. Avionics Architecture Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 37 Eclipse 500. Unlike aircraft cockpits of the past, the Eclipse 500 is devoid of many of the various switches, levers and other manual controls for aircraft systems. In its place, the pilot’s interface takes place primarily through the use of line select key controls on various aircraft systems synoptic pages normally located on the MFD.
  • Page 38 Due to the built in redundancy of aircraft systems, many of these failures do not result in a complete loss in system functionality, but only a loss in a redundant component. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 39 2.3 Pilot Displays The Electronic Flight Instrument System (EFIS) is the primary component of the integrated avionics suite contained on the Eclipse Model 500. The primary components of the EFIS are two 10.4 inch active matrix liquid crystal Primary Flight Displays (PFD) and one 15.3 inch active matrix liquid crystal Multi Function Display...
  • Page 40 1. Aircraft Systems Synoptics a. Engine b. Fuel c. Electrical d. Electronic Circuit Breakers e. Environmental Pressurization g. Ice Protection h. Flight Controls Aircraft Operations Sensor Status k. Setup 2. Audio Pages Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 41: Figure 12.Center Switch Panel

    Command Routing • Autopilot Control Panel • Engine Start Switch Panel • Left and Right Sidesticks • Center Pedestal (Rudder Trim Switch and Flap Selector Inputs) Figure 12. Center Switch Panel Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 42: Figure 13.Engine Start Switch Panel

    • Barometer Setting (BARO Set) • Map Lights (Left and Right) • Caution/Warning Flights (Left and Right) • Fire Warning and Suppression (Left and Right) Figure 14. Autopilot Control Panel Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 43: Figure 15.Sidestick

    • All Interrupt Switch • Autopilot Disconnect • Transponder IDENT • Microphone push-to-talk • Pitch and Roll Trim • Landing Gear Warning Mute Figure 15. Sidestick Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 44: Figure 16.Left (Essential) Switch Panel

    • Five Electrical Contactor Switches (Generators x2, Batteries x2, Bus Tie) • Oxygen Control and Pressure Display • Cabin Air Control (Air Source and Cabin Dump) Figure 16. Left (Essential) Switch Panel Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 45: Figure 17.Right Switch Panel

    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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 46: Figure 18.Keyboard

    • Communication Radio Selection and Control • Flight Management System (FMS) Functions- (Future Functionality) • Alphanumeric Entry of waypoints and Radio Frequencies • Synoptic Page Selection on the MFD Figure 18. Keyboard Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 47: Figure 19.Throttle Quadrant

    MFD function is enabled. Line select keys are often associated with the PFD or MFD pages within which they are used to activate or deactivate specific systems components (Ex. Fuel Pumps). Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 48: Figure 20.Line Select Key

    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. Figure 21. Rocker Key Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 49: Figure 22.Primary Function Keys

    Lower left set to PILOT AUDIO page, lower right set to page previously shown on lower left. Double Press ⎯ Lower left set to PILOT AUDIO page, lower right set to COPILOT AUDIO page Figure 22. Primary Function Keys Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 50: Figure 23.Concentric Knobs

    While editing text, rotating the outer knob counterclockwise with the cursor on the first character will deactivate text editing. Figure 23. Concentric Knobs Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 51: Figure 24.Single Rotary Knob

    Information from all three of these systems is sent to the ACS for comparison and failure monitoring, to FADECs for engine control and to the PFD and MFD for display. 2.6 Aircraft Subsystems The Eclipse 500 aircraft Subsystems include: Engines & Fire Protection Fuel...
  • Page 52 Trim also functions in this manner; the left ACS controls the left pitch trim actuator as well as the roll trim actuator, while the right ACS controls the right pitch trim actuator, as well as the yaw trim. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 53 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 control panel b. Directly Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 54 A knob that can be turned both ways b. A knob with an inner and outer portion c. A knob used on the PFD and MFD to make graduated selections d. All of the above Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 55: Figure 25.Flight Controls Schematic

    The wing flaps are electrically powered fowler flaps, controlled by a three-position flap selector lever located on the throttle quadrant. Flap position is displayed on the upper portion of the MFD. Figure 25. Flight Controls Schematic Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 56: Flaps

    3.2 Aircraft Computer System (ACS) Interfaces 3.2.1 Flaps There are four electromechanical flap actuators on the Eclipse 500, two per flap. The ACS is responsible for commanding the flaps to the position 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.

  • Page 57: Trim

    Eclipse 5OO Systems Manual 3.2.2 Trim The Eclipse 500 has four trim motors; two are used for pitch trim, one for roll (aileron) trim and one for yaw (rudder trim). Pilot control for pitch and roll trim is through the trim switch on each sidestick, while rudder trim inputs are made through the rudder trim switch on the throttle quadrant.

  • Page 58: Wing Flaps

    Section 3. Flight Controls Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 59: Controls And Indicators

    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 ............... Activates transponder IDENT function. TRIM SWITCH ............Activates Aileron and Elevator trim. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 60: Throttle Quadrant

    Section 3. Flight Controls Eclipse 5OO Systems Manual 3.4.2 Throttle Quadrant Figure 29. Throttle Quadrant Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 61: Flight Controls Synoptic

    In the event of an emergency or if the pilot chooses to use the MFD as the primary means of trim control, selecting ALTERNATE will allow the pilot to use the Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 62 If CONFIRM is pressed, stall protection is turned OFF and a STALL PROTECTION OFF status message appears. ECB LINK The ECB LINK line select key selects the Flight Control Electronic Circuit Breaker synoptic. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 63: Flap Position Display

    Figure 32. n Transit to T/O Position Figure 33. Flap Position Display (T/O Position) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 64 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 65: System Description

    Rudder pedals are individually adjustable fore and aft (1.75 inch travel) by depressing a lever located above each pedal and pulling or pushing the pedals to adjust. Figure 35. Rudder Pedal Adjustment Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 66: Elevator

    A failure of trim in any axis will cause a PITCH TRIM FAIL, AILERON TRIM FAIL, or RUDDER TRIM FAIL caution message to appear. Trim for Aileron and Rudder will be Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 67: Flaps

    The rudder is held in position by mechanical resistance in the nose wheel steering system. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 68: Normal Operations

    TRIM Aileron and pitch trim are accomplished by moving the four-way trim switch on either sidestick. Rudder trim is activated by moving the rotary rudder trim switch on the pedestal. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 69: Abnormal Procedures

    Trim is accomplished using the inner knob. Each “click” of the knob provides a 0.25 second trim command. The inner knob must be continuously rotated to keep the trim moving. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 70: Crew Alerting System Messages

    (ground only) Trim position indicators failed. TRIM POSITION FAULT Advisory Trim pointer is removed ALL INTERRUPT ACTIVE ALL INTERRUPT switch active Status STALL PROTECTION OFF Stall protection selected OFF Status Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 71: Flight Controls Review Questions

    2. What are two components of the Flight Control System that have Aircraft Computer System interfaces? 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.

  • Page 72: Flight Controls

    11. What MFD synoptic page will be displayed when the ALL Interrupt button on the sidestick control is pressed for two seconds? a. Ice protection. b. Fuel c. Pressurization d. Flight Controls Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 73: Landing Gear And Brakes

    These actuator brakes are capable of supporting the gear throughout the flight envelope. Normal extension takes approximately ten seconds and retraction takes approximately seven seconds. Figure 36. Landing Gear Schematic Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 74: Aircraft Computer Systems (Acs) Interfaces

    Right ACS Communications Bus Left Main Nose Landing Position Right Main Position Position Landing Gear Gear Actuator Indications Gear Actuator Indications Indications Actuator Position Information to ACS Figure 37. Landing Gear-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 75: Limitations And Specifications

    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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 76: Controls And Indicators

    Section 4. Landing Gear and Brakes Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 77: 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 78 If any gear is in transit for more than 15 seconds, a LANDING GEAR FAIL caution message appears and the in-transit symbol remains displayed. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 79 Section 4. Landing Gear and Brakes Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 80: System Description

    Each main gear assembly has three proximity sensors—Down and Locked, Up and Stowed, and Weight On Wheels (WOW). The WOW sensor prevents gear retraction when there is weight on the landing gear. Figure 41. Main Landing Gear Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 81: Nose Gear

    In the event of electrical failure, the actuator brakes lock in place and prevent any movement of the actuators. Manual gear extension is accomplished with an Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 82: Landing Gear Warning Horn

    When this occurs, the pilot can expect to see a gear unsafe indication for the gear or gears that are being re-stowed. 4.5.5 Landing Gear Warning Horn The landing gear warning horn sounds under 12,500 feet MSL, if any gear is not Down and Locked under three conditions: 1. Flaps extended beyond T/O setting 2.

  • Page 83: Parking Brake

    For the nose gear, a hard landing will bend a tab near the top of the nose gear strut on the aft side. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 84: 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 85: Normal Operations

    When each gear moves to the gear-down proximity sensor, the gear position annunciation changes from amber/hatched (In Transit) to green (Down and Locked). Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 86 WOW SENSOR FAULT advisory message appears. CAUTION: This will cause the aircraft to depressurize when the speed goes below 60 KEAS and the autopilot, including yaw damper and stick pusher, to be lost. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 87: Table 4.Landing Gear Cas Messages

    Landing gear system LANDING GEAR FAIL Caution failure BRAKE FLUID LOW Low brake fluid Advisory Weight on wheels sensors WOW SENSOR FAULT Advisory disagree PARKING BRAKE Parking brake is set Status Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 88 Left ACS b. Right ACS c. Landing gear actuators have independent controllers d. Both ACS have control 2. The Eclipse 500 landing gear system is powered by: a. A hydraulic pump. b. An electrically powered worm gear drive. c. Compressed nitrogen.
  • Page 89 13. Which is the only condition where the landing gear warning horn may be silenced? a. Airspeed less than 140 knots below 12,500 feet MSL and either or both throttles at idle. b. Airspeed less than 120 knots and either or both throttles at idle.
  • Page 90 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 91 The passenger masks automatically deploy in the event of depressurization, or the masks can be manually deployed by the pilot. Passengers must pull down on the mask to activate the flow of oxygen. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 92 R KBD Left Left Right Right Engine Start Switches Center Switch Panel Left Center Right Sidestick Pedestal Sidestick Left Right ACS Communications Buses Oxygen Pressure Switch Figure 46. Oxygen-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 93 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 ........14,000 +000/-500 feet cabin altitude Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 94 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 95 The airplane is equipped with either a 22 cubic foot or 40 cubic foot oxygen bottle, located in the left side of the nose compartment. Figure 48. Oxygen Bottle Location (40 Cubic Foot) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 96 >1850 psi is indicated in amber. Normal operating range, 200-1850 psi is green. Instrument Caution Range (Red) Normal Range (Green) Max. Limit (Yellow) Oxygen Pressure (psi) 0-200 psi 200-1,850 psi 1,850 psi – Full Scale Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 97 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 98 An oxygen regulator is connected to the oxygen cylinder to reduce oxygen pressure to the pilot and passenger masks. The regulator is activated by the oxygen control knob on the left switch panel. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 99 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 100 However if the masks are manually deployed using the DROP selection on the passenger mask selector, oxygen flow will continue below 10,000 feet. Figure 55. Passenger Mask Selector Activation Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 101 Once the harness and mask are in place, releasing the red lever deflates the pneumatic harness for a snug fit. Comfort adjustors located on the harness hose attach points allow for repositioning on the mask on the pilot’s face. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 102 This mode is automatically active at 34,000 feet cabin altitude regardless of the setting mask. Mask pressure proportional to the cabin altitude up to 45,000 feet. Figure 58. Quick Don Mask Regulator Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 103 Figure 59. Passenger Mask Location and Deployment (Right Switch Panel) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 104 If the cabin 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.
  • Page 105 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 106: Table 5.Table Oxygen Duration 22 Cu Ft Cylinder - Part 91

    (Mask in "NORM") (LITERS) (LITERS) (MINUTES) 2.32 32.84 544.84 249.93 2.32 78.84 498.84 228.83 2.32 124.84 452.84 207.72 2.32 170.84 406.84 186.62 2.32 216.84 360.84 165.52 2.32 262.84 314.84 144.42 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 107: Table 6.Oxygen Duration 40 Cu Ft Cylinder - Part 91

    Refer to the onboard oxygen duration chart for oxygen requirements for a particular flight 5.6.3 Oxygen System Post-Flight When the engines are shut down, push in the oxygen control knob to shut off the oxygen system and prevent inadvertent oxygen depletion. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 108 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 109: Table 8.Oxygen Cas Messages

    Section 5. Oxygen Eclipse 5OO Systems Manual 5.8 Crew Alerting System Messages Table 8. Oxygen CAS Messages Message Condition Category Oxygen line pressure OXYGEN PRESSURE below 46 psi. Warning Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 110 The masks will automatically deploy with a cabin pressure altitude of 14,000 ft +0/-500 feet c. The masks will automatically deploy with a cabin pressure altitude of 12,500 ft. +500/-500 d. The masks will automatically deploy with a cabin pressure altitude of 14,000 ft +500/-500 feet 2.
  • Page 111 AUTO c. DROP 12. At what cabin pressure altitude does the ‘Mask On, Descend!” aural alert activate? 13. What are two ways to deactivate/silence the ‘Mask On, Descend!” aural alert? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 112 Section 5. Oxygen Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 113 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 114 Inlet Temperature b. Regulated Pressure Switch 2. Right Engine a. Inlet Temperature b. Regulated Pressure Switch 3. Deice Boots a. Outer Wing Boot Pressure Switch b. Inner Wing/Stabilizer Boot Pressure Switch Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 115: Figure 14.Autopilot Control Panel

    Sensors (6 Total) Sensors -Left Engine (Press and Temp) -Right Engine (Press and Temp) Sensor Information to ACS’ Sensor Information to ACS’ -Wing Boots (Press x 2) Figure 62. Ice Protection-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 116 OUTBOARD WING DEICE L and OUTBOARD WING DEICE R. 6.3.3 Windshield Heat The use of windshield heat is prohibited. The following windshield heat ECB must be collared: L/R WINDSHIELD HEAT. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 117 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 118 Green...................Engine anti-ice on White....................Engine anti-ice off Amber ..................Engine anti-ice failed OAT ..................Outside Air Temperature TAT ....................Total Air Temperature NOTE: Amber and red display colors are consistent with CAS message colors. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 119 A white windshield outline indicates that the windshield heat is off. A green windshield outline indicates that windshield heat is on and functioning normally. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 120 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 121: Engine Anti-Ice

    Normal operation of the engine anti-ice system is indicated on the ICE protection synoptic by green engine inlets on the airplane graphic display. When the system is off, the engines are displayed in black with a white outline. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 122: Pitot/Aoa Probes, Pitot-Static Probe And Static Ports

    The wing inspection light is controlled by a two position INSP LIGHT switch on the center switch panel. Figure 68. Wing Inspection Light Location Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 123: Normal Operations

    To monitor accumulation of ice at night, activate the ice inspection light switch to illuminate the leading edge of the left wing. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 124: Abnormal Procedures

    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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 125: 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 126: Pneumatic De-Ice System Failure

    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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 127: Engine Anti-Ice System Failure

    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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 128: Probe And/Or Port Heat Failure

    Should this occur a L (R) STATIC HEAT FAIL advisory message appears to alert the loss of redundancy. Figure 73. Pitot/AOA Probe Failure Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 129: 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 130: Pressure Regulating Shut-Off Valve Fault

    6.7.10 Static Heater Monitor Fault Should the ACS be unable to monitor the function of the static heaters, a STATIC HTR MON FLT advisory message appears. The heaters will still operate. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 131: Crew Alerting System Messages

    Advisory Ground Only) ENG A/ICE ON Engine anti-ice only on Status ENG/WING ICE PROT ON Engine anti-ice and wing de-ice on Status WINDSHIELD HEAT MANUAL Windshield heat manually activated Status Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 132: Ice Protection Review Questions

    The windshield heating element has malfunctioned and can no longer provide windshield heat. d. None of the above. 7. How is automatic probe and port heat is activated? 8. How is probe and port heat manually activated? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 133 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 134: Fuel

    Fuel Management and balancing is automatically controlled by the ACS, but can be overridden by the pilot. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 135: Aircraft Computer System (Acs) Interfaces

    Electronic Circuit Breakers (ECBs). The ECBs for the fuel system are located within the Aft Power Distribution Center in Electronic Circuit Breaker Units (ECBUs) four and five. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 136 Right Electric Fuel Pump Left Electric Fuel Pump Right Fuel Shutoff Valve- Left Fuel Shutoff Valve- OPEN OPEN Right Fuel Shutoff Valve- Left Fuel Shutoff Valve- CLOSE CLOSE Figure 75. Fuel-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 137: Limitations And Specifications

    Phillips PFA-55MB 7.3.4 Fuel Temperature Maximum fuel sump temperature, continuous.......... 66°C (150°F) Maximum fuel sump temperature, transient (30 minute maximum) ..77°C (170°F) Maximum fuel sump temperature, takeoff..........51°C (124°F) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 138: Controls And Indicators

    The total quantity display turns amber when fuel remaining is less than 280 pounds, and red when fuel remaining is less than 210 pounds. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 139 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 warning messages. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 140: Fuel Synoptic

    Line select keys on the fuel synoptic provide manual control of the two electric fuel pumps and the crossfeed valve. L PUMP ......................AUTO / ON Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 141 A significant difference in the estimated and gauged fuel quantity might also be an indication of a fuel leak. Figure 79. Estimated Fuel Used & Estimated Fuel Remaining Display Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 142: System Description

    If there is a failure of internal wing transfer or fuel becomes trapped outboard a L (R) FUEL UNUSABLE caution message appears and the total amount of unusable fuel for flight should be increased to 50 lbs. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 143: Electric Fuel Pumps

    Should this bypass switch fail a L (R) FUEL BYPASS FAULT advisory appears on the ground only. Flight with a failed bypass switch is prohibited. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 144: Fuel Valves

    7.5.9 Fuel Heat A fuel/oil heat exchanger in each engine keeps fuel within normal operating temperature limits. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 145: Fuel Temperature Sensor

    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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 146: Return Fuel

    Fahrenheit degrees. The gauging system adjusts fuel quantity based on aircraft pitch and indicates zero with zero usable fuel (the gauging accurate within +/- 2% with zero pitch). Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 147 Should a capacitance probe fail a FUEL GAUGING FAULT advisory message appears and white FUEL GAUGING FAULT text appearing above the affected white wing outline on the fuel synoptic. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 148: Vent System

    Should fuel pressure information become unavailable a L (R) FUEL PRESS FAULT advisory appears on the ground only and white triple dashes will be displayed. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 149 Section 7. Fuel Eclipse 5OO Systems Manual Figure 83. Fuel Synoptic- Low Fuel Pressure & Pressure Sensor Fault Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 150: Fuel Balancing

    XFEED line select key on the fuel synoptic. Activating manual fuel XFEED causes a FUEL MAN XFEED L R or FUEL MAN XFEED L R status message to appear. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 151: Normal Operations

    A L (R) FUEL QTY LOW warning message may be displayed briefly until the sump tanks are full. The fuel gauging system is accurate during this time. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 152: Abnormal Procedures

    Selecting L←R or L→R opens the crossfeed valve, turns on the appropriate electric fuel pump, and prompts a FUEL MAN XFEED L←R or FUEL MAN XFEED L→R status message to appear. Figure 85. Fuel Synoptic- Manual Fuel Crossfeed Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 153: Crew Alerting System Messages

    Manual fuel crossfeed selected Status FUEL MAN XFEED L Manual fuel crossfeed selected Status Respective electric fuel pump on for other than L (R) FUEL PUMP ON fuel crossfeed Status Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 154 JET A/A1 b. JP-8 c. Any kind of Avgas d. Both A & B 2. What is the maximum allowable fuel imbalance on the Eclipse 500? a. 12 US Gallons b. 50 lbs c. 50 US Gallons d. 65 lbs 3.
  • Page 155 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 Eclipse. 13. How is fuel balanced on the Eclipse 500? a.
  • Page 156 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.
  • Page 157 The engine start sequence is automatic when an engine start switch is placed to the ON/START position. Figure 86. PW 610F-A Engine Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 158 (FMU). The FADECs monitor the primary engine sensors (N1, N2 and ITT) and report this information to the ACS which is then routed through the PFD to the MFD for display. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 159 (1B) (2A) Inter-FADEC Communication Bus Fuel Metering Unit Fuel Metering Unit Primary Engine Primary Engine Primary Engine Primary Engine Sensors Sensors Sensors Sensors Left Left Figure 87. Thrust Control-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 160 Once and engine start is complete, the FADECs run the engine independently and report primary engine parameters (N1, N2 and ITT) to the ACS for display to the pilot. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 161 Section 8. Engines & Fire Protection Eclipse 5OO Systems Manual Figure 88. Engine Starting-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 162 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 Engine Parameter-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 163 Once discharged the fire canister reports its status to the ACS which in extinguishes the green ARMED indication from the FIRE/ARMED button Figure 90. Fire Detection and Suppression-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 164: Table 11.Engine Operating Limitations

    (b) Flight idle speeds are a function of ambient pressure and temperature. The engine control will keep the engine within its mechanical limits. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 165: Table 12.Oil Pressure

    CAS message appears. NOTE 2: If the 90-second caution time period is exceeded, the oil temperature display changes from amber to red and an exceedance CAS message appears. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 166: Table 14.Fuel Temperature

    Engine starting at temperatures between -20°C (-4°F) and 5°C (41°F) must be accomplished with an external Ground Power Unit (GPU) connected and supplying electrical power. Engine starts are not permitted at a temperature less than -20°C/-4°F. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 167 Section 8. Engines & Fire Protection Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 168 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 start battery voltage Battery only engine start................23 VDC Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 169 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 170 Continuous ignition is turned on by moving the rotary switch on the engine start switch panel to the CONT IGN position. It is recommended that continuous ignition is activated while operating in heavy rain, severe turbulence, or volcanic dust Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 171 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 172 The L and R DRY MTR line select key selections disappear when the aircraft is in flight (weight off wheels). AUTO........Automatic Power Reserve is automatically controlled OFF............. Automatic Power Reserve deactivated ECB LINK Selects engine circuit breakers on Electronic Circuit Breaker (ECB) synoptic Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 173 All primary engine instruments are fully redundant. The circuits that control and monitor primary engine parameters are duplicated to reduce the possibility of a hardware failure causing the pilot to receive misleading or no information about engine status. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 174 With the throttles advanced to the takeoff setting the state of the APR is displayed above the N tapes as either APR ARMED (white) or APR ON (green). Figure 98. APR Indications Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 175 An L (R) ENG EXCEEDANCE warning message appears: If ITT exceeds the limit (but not above 810°C) for 20 seconds If the ITT reaches 810°C Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 176 N values above the RPM limit. If the RPM exceeds the limit for 20 seconds, a L (R) ENG EXCEEDANCE warning message appears Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 177 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 Tape Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 178: Table 15.Oil Pressure Amber And Red Indications

    This message also appears if the oil pressure enters the low warning range for more than 15 seconds. Table 15. Oil Pressure Amber and Red Indications Oil Pressure Time Delay for Amber Display 9.1 – 10 None 8.1 – 9 5 minutes Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 179 Should the engine oil temperature sensor fail, a L (R) OIL TEMP FAULT advisory message appears and oil temperature indications for that engine will be unavailable and a red X appears in place of the oil temperature tape. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 180: Table 16.Oil Temperature Cas Delay Time

    The display has three states: Table 17. Engine Chip Color Indications Situation Display Normal OK (white) Chip Detector Failed --- (White) Contamination Detected DETECT (White) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 181: Table 18.Impending Bypass Color Indications

    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) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 182 Eclipse 5OO Systems Manual 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 183 Idle, Maximum Continuous Thrust (MCT) and Takeoff. Figure 108. Throttle Position vs. Engine Power Thrust level Throttle Position (Degrees) Idle 0 – 4 Maximum Continuous 59 – 65 Takeoff / APR 67 – 70 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 184 The right Avio Processing Center also houses one FADEC card from each of the left and right engines. FADEC POWER SOURCES Each FADEC unit has three power sources: Left generator Right generator System battery Figure 109. FADEC Power Sources Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 185 APR is also disarmed manually using the ‘Manual APR Disarming/Deactivating’ procedure. MANUAL APR DISARMING/DEACTIVATING The APR system can be disarmed on ground or in flight with a line select key on the ENG synoptic page. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 186 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 187 Fuel returns to the FMU and passes through a high pressure pump and fuel metering valve controlled by the FADEC. The fuel metering valve then distributes fuel to the fuel nozzles. Excess fuel is routed back Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 188 Metal contamination triggers a L (R) ENG CHIP DETECTED advisory message to appear. If this detector fails, a L (R) ENG CHIP FAULT advisory appears and chip detection is unavailable. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 189 Section 8. Engines & Fire Protection Eclipse 5OO Systems Manual Figure 112. Engine Oil Schematic Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 190 L (R) ENG FIRE warning messages dual guarded indicator/control buttons that turn on when a fire (red) condition occurs “Left Engine or Right Engine Fire” audible alarm Figure 114. FIRE/ARMED Button Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 191 If the red fire indicator remains illuminated, a fire condition exists and the fire extinguishing system should be activated Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 192 The fill level should be in the green band indicated on the canisters which can be seen through clear windows in the top of each pylon. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 193 Once the extinguishing agent is discharged the green ARMED text extinguishes and a L (R) EXTNGR DSCHG advisory message appears indicating that the fire extinguisher capability has been depleted. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 194: Table 19.Start/Motoring Modes

    3. N2- 3 to 10% a. Starter ON b. Fuel Shutoff valve- OPEN c. Electric Fuel Pump- ON d. Igniters ON e. ITT Redline- INCREASES TO 850°C 4. N2- 15% a. Oil Pressure rise Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 195 This fuel can be pumped out (without adding more fuel and without ignition) by dry motoring the engine using the line select keys labeled L DRY MTR and R DRY MTR Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 196 47% N2), as determined by the WOW sensor. This feature is incorporated to provide a higher margin in-flight and avoid the possibility of engine flameout due to anomalies in engine inlet airflow. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 197 FIRE/ARMED button. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 198: Table 20.Engine Cas Messages

    Once discharged, the fire extinguisher capability Advisory has been depleted L (R) FIRE DETECTOR Fire detection circuit is shorted or open. Fire Advisory FAULT detection is unavailable. APR DISARMED APR disarmed (ground only) Status Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 199 8. APR will increase thrust up to how much on the operating engine in the event of an engine failure? a. 25% of takeoff thrust (N1) b. 110% of takeoff thrust (N1) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 200 -20° C or -4° F 16. List the three sources of power for the FADEC units: 17. What is engine bleed air from the inboard P3 bleed port on the engine used for? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 201 Section 8. Engines & Fire Protection Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 202 The Cabin Pressurization Control Sub-System works in conjunction with the ACS to automatically regulate the cabin pressure. The system can also be controlled manually by the pilot through the pressurization (PRESS) synoptic. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 203 Section 9. Climate Control Eclipse 5OO Systems Manual Figure 118. Climate Control System Overview Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 204 Bleed Air Over Temperature Sensor d. Pylon Over Temperature Sensor 2. Right Engine a. Cockpit Zone Temperature Sensor b. Forward Evaporator Temperatures c. Bleed Air Over Temperature Sensor d. Pylon Over Temperature Sensor Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 205 Fwd Evap Fan- Aft Evap Fan- HIGH HIGH Left Flow Control Air Conditioning Aft Evaporator Isolation Fwd Evaporator Right Flow Control Valve Condenser Fan Valve Valve Figure 119. Climate Control System-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 206 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 entries of Selected Cabin Altitude are not approved. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 207 Section 9. Climate Control Eclipse 5OO Systems Manual 9.4 Controls and Indicators 9.4.1 Cabin Air Controls Figure 120. Cabin Air Sub Panel Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 208: Table 21.Air Source Switch Selections

    Table 22. Cabin Dump Switch Selections Normal operation Both outflow valves fully open Both flow control valves switch to high flow All bleed air routed to cockpit 9.4.2 Pressurization Display Figure 121. MFD Pressurization Display Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 209 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 rate of climb or descent between 0 and 2,500 feet per minute.

  • Page 210: Table 23.Environmental Synoptic Selections

    OFF / ON. Default setting at power-up is OFF AIR COND OFF / AUTO. Default setting at power-up is OFF Outside Air Temperature in degrees °C ECB LINK Selects Climate Control ECB synoptic page Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 211: Table 24.Pressurization Synoptic Indications

    Temperature in pylon Flow Control Valve Setting HIGH or LOW flow Bleed air temperature downstream of Duct Temperature heat exchanger Position of isolation and cabin air shutoff Isolation/Cabin Shutoff Valves valve Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 212 0 and 11,500 feet. Set cabin altitude in MANUAL pressurization mode. SEL CABIN ALT FT Range is -1,000 feet to 11,500 feet. Set cabin rate in MANUAL pressurization mode. SEL CABIN RATE FT Range is 0 to 2,500 fpm.
  • Page 213 The variable ram exhaust outlet modulates the amount of ram air over the heat exchanger to condition the bleed air as required by the climate control system. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 214 Pylon If the pylon temperature sensor fails, a L (R) PYLON TEMP FAULT advisory message appears and the temperature display on the pressurization synoptic page reverts to red dashes. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 215: Table 26.Flow Control Valve Functions - High/Low

    Low Flow Ground Idle No Power Cabin altitude exceeds 10,000 feet Cabin rate of climb exceeds 2,500 fpm L or R selected on the AIR SOURCE switch High Flow Bleed air is available from only one engine Cabin temperature control falls approximately 7 °F below the...

  • Page 216: Table 28.Flow Control Valve Manual Shutoff Operation

    SOURCE SELECTOR status message appears, indicating that one or both of the bleed air sources is off. If a flow control valve fails, a L (R) BLEED VALVE FAIL advisory message appears. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 217 Section 9. Climate Control Eclipse 5OO Systems Manual 9.5.2 Cabin Air Distribution Figure 125. Cabin Air Distribution Components Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 218 Air conditioned air is provided separately within the forward evaporator unit by air flowing through the evaporator coil, that is then routed Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 219 Conditioned bleed air that was not diverted underfloor is then routed directly to the floor vents in the cabin temperature zone. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 220 The cabin sensor is on the center of the aft cabin ceiling. In the event a cabin or cockpit temperature sensor fail, white dashes replace the zone temperature on the ENVIR synoptic page. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 221 AIR DISTR line-select key on the MFD. In the event that the pilot selects the AIR SOURCE switch to OFF, L or R an AIR SOURCE SELECTOR status message appears. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 222 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 223 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 224 29,000 ft, the air conditioning automatically shuts down and automatically restarts when the airplane descends through 28,000 ft. In the event that a component of the air conditioning system fails, an AIR CONDITIONING FAIL advisory message appears. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 225 Section 9. Climate Control Eclipse 5OO Systems Manual Figure 134. Air Conditioning System Schematic Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 226 The default setting at power-up is OFF. Optimal DEFOG performance is obtained when the cockpit temperature is set to MAX HEAT, the forward evaporator FAN is set to HIGH and the dehumidification (DEHUMID) feature is ON. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 227 The outflow valves do not require electrical power to operate. Figure 135. Secondary and Primary Outflow Valves Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 228 Should the cabin remain pressurized on the ground a CABIN PRESS ON GROUND caution message appears and the cabin must be depressurized through the activation of the cabin DUMP switch. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 229 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 230 Eclipse 5OO Systems Manual Figure 137. Cabin Dump- PRESS Synoptic NOTE: 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 .
  • Page 231 Section 9. Climate Control Eclipse 5OO Systems Manual 9.6 Normal Operations No content. THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 232 In the event of an engine shutdown or failure, bleed air from the operating engine is routed to the cockpit. This automatic function can be overridden by the pilot with the AIR DISTR line select key on the pressurization synoptic. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 233: Table 29.Climate Control System Cas Messages

    Advisory The air source selector is in another position AIR SOURCE SELECTOR Status than NORM. Cabin altitude hold mode active as selected by CABIN ALT HOLD MODE Status the pilot. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 234 To clear smoke from a smoke-filled cabin. b. To depressurize aircraft that is pressurized on the ground. c. In the event of an over pressurization. d. All of the above are correct. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 235 None of the above is correct. 11. Air conditioning in the Eclipse 500 is achieved by: a. Running compressor bleed air through air conditioning “packs,” which are next two each engine pylon.
  • Page 236 The outflow valves determine cabin pressure by regulating how much pressurized air can escape from the cabin. 16. Which electronic circuit breaker units provide power to climate control system components? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 237 Eclipse 5OO Systems Manual 10. Electrical 10.1 General The Eclipse 500 electrical power distribution system is a split bus, DC system, powered by two 200 amp, 30 VDC regulated starter/generators driven by the engine’s accessory gearbox. Circuit protection is provided by 127 Electronic Circuit Breakers (ECBs) in conjunction with two mechanical circuit breakers on the left switch panel.
  • Page 238 Electronic Circuit Breaker Unit #4 b. Electronic Circuit Breaker Unit #5 c. Bus Tie Contactor (BTC) d. Left Forward Circuit Breaker/Contactor e. Right Forward Circuit Breaker/Contactor Left Aft Bus g. Right Aft Bus Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 239 Bus Tie ECBU #4 ECBU #5 Left Aft Bus Right Aft Bus Contactor Left Generator Control Right Generator Control External Power Contactor Unit Unit Figure 138. Electrical Power Distribution-ACS Interfaces Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 240 Aircraft current draw greater than 400A External Power current draw from aircraft greater than 5 A Less than 24 volts for longer than 45 seconds, or Less than 10 volts at any time. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 241 EXT POWER.............Green LED indicates external power is connected and voltage is the correct polarity and within limits. LEFT PFD ............Mechanical circuit breaker for left PFD LEFT ACS ............Mechanical circuit breaker for left ACS Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 242 Bus bar segments are green if voltage is greater than 20 volts. Bus bar segments are white if voltage is 20 volts or less. Vertical ribbon to right of batteries indicates state of battery charge in volts. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 243 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 244: Table 30.Electronic Circuit Breaker States

    30 minutes power to essential systems. During normal operation the batteries “float” on the buses to minimize voltage transients that may be caused by electrical loads being switched on or off. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 245 Greater than 29 volts at any time Aircraft current draw greater than 400A External Power current draw from aircraft greater than 5 A Less than 24 volts for longer than 45 seconds Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 246 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 247 Single generator Battery External power All aircraft buses are powered in the above situations and when operating on a single generator or external power, both batteries are being charged. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 248 Left and Right Air Data Computers (ADC) Left and Right Angle of Attack Processors Left and Right GPS (2) Left and Right Pitot/AOA Heat Left and Right Integrated Sensor Suite (ISS) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 249 A lighting controller function internal to this unit allows for control and regulation of internal lighting along with the internal timer to deactivate those lights after five minutes. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 250 AUTO/ON Normal state AUTO/OFF ECB turned off by the ACS TRIPPED ECB off due to circuit fault PULLED ECB opened by the pilot COLLARED ECB locked out by a maintenance technician Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 251 ⎯ • Left Forward Circuit Breaker • Left Aft Bus • ECBU #4 • Bus Tie Contactor (BTC) Right Side ⎯ • Right Forward Circuit Breaker • Right Aft Bus Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 252 Section 10. Electrical Eclipse 5OO Systems Manual • ECBU #5 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 253 The green EXT POWER light on the left switch panel indicates that good external power (correct polarity and voltage) is available for use. The states of the external power contactor or battery switches have no effect on the external power light. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 254 If desired, the second engine can be started with external power paralleled with the start battery. To do this, the pilot turns off the GEN switch for the operating engine to allow the external power contactor to close. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 255 The ACS uses the current status of the aircraft (on-ground or in-flight, as determined through the Weight-On-Wheels sensor) to determine the appropriate control functions for normal operation and failure conditions. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 256 10.7.4 Electrical Smoke Clearing In the event of electrical smoke in the cabin, the pilot initiates the Smoke Clearing Procedure to isolate the source of the smoke. The Smoke Clearing procedure turns Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 257 All ECBs maintain their state before the smoke clearing procedure because the state of each ECB is stored in its internal memory. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 258: Table 31.Electrical Cas Messages

    Start battery contactor has tripped due to over START BATT CONTACT TRIP current. Start Battery is isolated from electrical Advisory power system BATT HEATER FAIL Battery heater blanket has failed (ground only) Advisory Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 259 30 VDC 5. A SINGLE Starter Generator can provide power for the entire airplane with the exception of what system? a. Passenger lighting. b. Fire suppression. c. Air conditioning. d. Pressurization. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 260 External power is plugged in. b. External power is of the correct voltage. c. The batteries are being charged if the battery switches are ON. d. All of the above are correct. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 261 13. ACS 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.
  • Page 262 45 min d. 35 min 19. Which two electrical system components are independent of the Aircraft Computer Systems? 20. List the five conditions that will cause external power to automatically disconnect: Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 263 With battery power only, these lights are on timers to prevent battery depletion. Dome light ....................... 5 minutes Baggage compartment light ................5 minutes Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 264 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 265 Section 11. Interior Lighting Eclipse 5OO Systems Manual 11.3 Limitations and Specifications No content. THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...

  • Page 266: Table 32.Interior Light Center Switch Panel Controls

    CABIN OVRD Override Upper Cabin Wash Lighting DOME Cockpit Dome Lighting FOOTWELL Foot Well Lighting MASTER DIM Interior lights dimming, low to high NIGHT/DAY Interior Lights NIGHT (Low), DAY (Bright) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 267 The other switch is located on the center switch panel. Figure 147. Cockpit Dome Lighting Armrest Switch Figure 148. Cockpit Dome Lighting Center Switch Panel Switch Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 268 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 269 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 270 Figure 152. Overhead Cabin Wash Lighting Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 271 Section 11. Interior Lighting Eclipse 5OO Systems Manual Figure 153. Overhead Cabin Wash Lighting Control Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 272 Figure 154. Lower Cabin Wash Lighting Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 273 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 274 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 275 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 276 Section 11. Interior Lighting Eclipse 5OO Systems Manual 11.7 Abnormal Procedures No content. THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 277 Section 11. Interior Lighting Eclipse 5OO Systems Manual 11.8 Crew Alerting System Messages No content. THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 278 Section 11. Interior Lighting Eclipse 5OO Systems Manual 11.9 Interior Lighting Review Questions 1. LED lights are used on the Eclipse 500 to: a. Provide extended lighting system component life & redundancy by using multiple strings of LEDs b. Reduce drag c.
  • Page 279 Deactivates the lower cabin wash lighting d. Overrides the cabin switch for the upper cabin wash lighting-prevents passenger activation and turns lights off if on e. None of the above Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 280 Several of the aircraft lights utilize Light Emitting Diodes (LEDs). Each of these lights contains several strings of individual LEDs. This ensures that should one light or string of lights fail, the rest remain illuminated. Figure 159. Exterior Lighting – Top View Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 281 Section 12. Exterior Lighting Eclipse 5OO Systems Manual Figure 160. Exterior Lighting- Left Side View Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 282 1. Left and Right Landing Lights 2. Left and Right Taxi/Recognition Lights (Optional) 3. Left, Right, Aft Anti-Collision (Strobe) Lights 4. Beacon Light 5. Left, Right, Aft Position Lights 6. Wing (Ice) Inspection Light Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 283 Wing Inspection Light Beacon Light Right Anti-Collision Light Position Lights Tail Anti-Collision Light Left Taxi/Recog Light Right Taxi/Recog Light Left Landing Light Right Landing Light Figure 161. Exterior Lighting-ACS Interfaces Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 284 Section 12. Exterior Lighting Eclipse 5OO Systems Manual 12.3 Limitations and Specifications No content. INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 285 TAXI / RECOG alternating flashing in air) STROBE/BEACON Left, Right Wing and Tail Strobes & Flashing Beacon EXT LIGHT BEACON Flashing Beacon only ICE PROT INSP LIGHT Ice Inspection Light Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 286 The wing inspection light is controlled with a two-position INSP LIGHT switch located on the center switch panel. A failure of the wing inspection light causes an INSPECTION LIGHT FAIL advisory message to appear. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 287 Taxi lights are activated by a two position TAXI/RECOG switch located on the center switch panel. A failure of one of the Taxi/Recognition lights causes a TAXI LIGHT FAIL advisory message to appear. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 288 Section 12. Exterior Lighting Eclipse 5OO Systems Manual 12.6 Normal Operations No content. THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 289 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 290 Strobe light failure detected Advisory TAXI LIGHT FAIL Taxi light failure detected Advisory INSPECTION LIGHT Advisory FAIL Wing ice inspection light failure detected BEACON LIGHT FAIL Beacon light failure detected Advisory Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 291 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 wing tips c.
  • Page 292 Beacon, anti-collision, left & right taxi, right landing, all optional lighting b. Ice inspection light & right landing light c. Only decorative interior lighting will be load shed d. None of the above Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 293 Section 12. Exterior Lighting Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 294 Information from these probes is transmitted to an Air Data Computer where it is processed and made available to other systems as needed. Figure 163. Pitot/AOA, Pitot/Static, and Static Ports Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 295 There are two pieces of information that are returned to the Integrated Sensor Suites for correction purposes, these are: 1. RAIM (Radio Autonomous Integrity Monitoring) information to the GPS units 2. BARO (Altimeter Setting) correction to the Air Data Computers Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 296 Section 13. Air Data Eclipse 5OO Systems Manual Figure 164. Air Data-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 297 Section 13. Air Data Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 298 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.. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 299 Section 13. Air Data Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 300 Air Data Computer, where the data is processed and provided to the PFD, ACS, and FADECS. Figure 165. Pitot/AOA Probe- Left Side Figure 166. Pitot/AOA Inlet Locations Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 301 MFD ADI. Information provided by this probe may also be used by the pilot in the event of a system abnormality or a disagreement between the primary probes. Figure 168. Pitot Static Probe Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 302 Mach number. The OAT probes are located on the vertical stabilizer fairing and are outside of ice accretion areas and do not require heating for anti-icing protection. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 303 ACS. Information from the ISS is sent directly to the PFD for display, to the ACS for comparison and failure monitoring, and to the FADEC for engine control. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 304 2.............Left and Right PFD using Right (#2) ADC. BARO-SET Altimeter setting between 22.50 through 34.50 inches Hg entered using concentric knob on MFD. Pressing inner knob sets standard 29.92 in Hg Figure 171. SENSOR Synoptic Page Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 305 PFDs and MFDs. OAT information is also used by the ACS to provide the FADEC with Total Air Temperature (TAT) for engine control. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 306 NOT be able to be reengaged. There is no pilot control over GPS selection. In the event of a GPS failure, the ACS will automatically revert to the operating GPS. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 307 GPS Advisory GPS 2 Failure- System will automatically GPS 2 FAIL revert to operating GPS Advisory Left and right total air temperature disagree TAT DISAGREE in flight Advisory Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 308 One is located on the nose and the other is located on the tail c. Along the top of the aft fuselage at the base of the vertical stabilizer fairing. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 309 Left & Right Pitot/AOA heat, and Left & Right Static port heat b. Left side Pitot/AOA heat only c. Right side heat Pitot/AOA heat only d. None of the above Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 310 Mode in which, the PFD provides a reversionary capability showing additional aircraft systems information which can be used in the event of a Multi Function Display (MFD) failure. Figure 172. Primary Flight Display (PFD) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 311 Section 14. Primary Flight Display (PFD) Eclipse 5OO Systems Manual 14.2 Limitations and Specifications No content. INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 312 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 313 TILE 5 (CONFIGURABLE) Active communication (COM) Frequency Communication frequency being monitored (MON) Heading pre-select display Communication (COM) radio tuning and selection Navigation (NAV) radio tuning and selection Transponder (XPDR) tuning and selection Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 314 If the system is reporting both an active and armed mode as valid for display the active mode appears to the left in green and the armed mode appears to the right in white. Figure 176. Flight Mode Annunciation Example Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 315 A specific annunciation of autothrottle engagement state is not required since if engaged, by pilot action or automatically, text appears in the autothrottle portion of the Flight Mode Annunciation window. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 316 AP DISC text appears on the PFD and an aural alert tone will sound to notify the flight crew of autopilot disengagement. This occurs during any phase of flight. Figure 179. Autopilot Disconnect Annunciation Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 317 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 displayed as a black filled airspeed window with white digits. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 318 This airspeed trend vector points at the airspeed scale at the predicted airspeed 6 seconds in the future based upon the airspeed change in the last 2 seconds. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 319 The final approach reference speed is bugged with REF 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 320 If the airspeed reaches the stall speed for the current configuration, the airspeed tape is solid red and the airspeed display is red. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 321 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 Reference Pointers Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 322 (fixed at the top of the ADI). NOTE: The roll scale remains fixed at the top of the ADI while the roll pointer and the airplane symbol roll in parallel with the airplane. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 323 FD is engaged and the autopilot off. When the autopilot is activated the FD command bars turn magenta. Invalid flight director data will cause the flight director to be removed. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 324 ILS, LOC, BCRS (back course) or FMS. A white HDI pointer indicates course deviation; if the pointer exceeds full scale deviation, it turns amber. Figure 192. Horizontal Deviation Indicator- Full Scale Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 325 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 326 VLOC frequency or a change in Primary Navigation source, the VDI pointer is removed, the associated text turns red and a red X that covers the VDI. Figure 196. Vertical Deviation Indicator- Signal Loss Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 327 Outer Marker ............Blue display labeled “OM.” Figure 197. Outer Marker Display on PFD Middle Marker ............Amber display labeled “MM.” Figure 198. Middle Marker Display on PFD Inner Marker............White display labeled “IM.” Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 328 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.” Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 329 A magenta target altitude bug is displayed to the left side of the tape. When the flight director/autopilot is engaged the target indicates what altitude has been selected for capture. When the ALT-SEL knob on the autopilot control panel is Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 330 PFD is displayed in the data block and an amber tick mark will appear on the altitude tape. Within 100 feet for the set minimums an aural alert, “APPROACHING MINIMUMS” is sounded. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 331 +/- 1000, 2000 and 3000 fpm and small unlabeled tick marks every 100 feet up to +/- 1000 fpm. After +/- 1000 fpm intermediate tick marks are located at 500 fpm (ex. 2500 fpm) High Vertical Speeds...
  • Page 332 Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 333 Section 14. Primary Flight Display (PFD) Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 334 The ground speed between 0 and 999 kts is displayed as a whole number of up to three digits and includes a label "GS" to the left of the ground speed value and a label "KTS" to the right. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 335 HSI view from full to 120° arc. Outer Knob........When VIEW/RANGE is selected, rotating the outer knob changes the NM value of the inner and outer range rings on the HSI. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 336 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 337 10 degrees, beginning at North. It displays numeric labels for non-cardinal headings every 30 degrees starting from North and displays N, E, S, or W for the appropriate cardinal headings. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 338 Figure 209. 120 Degree Arc View HSI Map Range (NM) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 339 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 Outer Ring Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 340 The heading bug is solid only if being used by the flight director/autopilot to capture a preset heading. The heading bug remains solid while in heading mode. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 341 TO indication. Pressing the knob without a navigation frequency tuned and identified, synchs the course selection arrow with current aircraft heading. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 342 PFD. When selected to an FMS or VLOC frequency, the RMI arrowhead points to the current selected course of the primary navigation source. The bearing pointer is not displayed if the VLOC source is tuned to an ILS or LOC station. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 343 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 344 Communication 1 Radio Selection.........Active Frequency Standby Frequency Line Select Key 4 (R4), COM 2 (Active- A, Standby- S) Communication 2 Radio Selection.........Active Frequency Standby Frequency Line Select Key 5 (R5) NO FUNCTION Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 345 Outer Knob....................MHz With a NAV frequency highlighted, rotating the outer knob changes the MHz portion (three digits left of the decimal point) of the communication frequency Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 346 Outer Knob..................CODE entry When the CODE line select field is highlighted, rotating the outer knob moves the cursor between digits within the transponder code. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 347 PFD. Two frequencies—Active (A) and Standby (S)—are displayed for each NAV radio. The navigation course on the HSI is selected with the left concentric knob on the bottom of the PFD. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 348 118 to 136 MHz in 1 MHz increments. Rotating the inner portion of the concentric knob bi-directionally scrolls through the range 0 to 975 KHz in 25 KHz increments. 5. Pressing the inner portion of the knob swaps the active and standby frequencies. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 349 PFD. Rotating the knob left or right decreases or increases pilot audio volume. Pressing the knob activates squelch control and rotating the knob left or right decreases or increases pilot squelch. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 350 FMS appears to the right of the NAV text. The FMS course (DTK) and distance to the next waypoint is displayed on the bottom line of the window. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 351 FMS appears to the right of the BRG text. The FMS bearing to the next waypoint is displayed on the bottom line of the window. . Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 352 108 to 117 MHz in 1 MHz increments. Rotating the inner portion of the concentric knob bi-directionally scrolls through the range 0 to 950 KHz in 50 KHz increments. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 353 2. NAV page is automatically selected, a cursor is placed in MINIMUMS window 3. Enter the minimum altitude using the number keys on the keyboard 4. Press ENTER to set the minimums Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 354 2. Press XPDR SQWK key. 3. Enter the transponder code using the number keys on the keyboard Mode Selection 1. Press right line select key 3 to change mode between SBY, GND Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 355 There is also a pinky controlled switch on each sidestick dedicated to IDENT. NOTE: If the selected transponder is not in ON or ALT, there is no affect Figure 223. Keyboard Transponder Group Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 356 These tiles contain necessary aircraft and engine systems information. Figure 224. PFD Composite Mode Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 357 Once COMPOSITE is selected, the page tabs change from NORMAL and COMPOSITE to MAIN and HSI. When this occurs, the keyboard is the only means of exiting the composite mode. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 358 There are two composite mode page options that become available along the lower left portion of the PFD. These pages are MAIN and HSI and are selectable using the left rocker key on the PFD. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 359 Select the Composite Mode: 1. Press L PFD or R PFD 2. Press PFD COMPOSITE 3. Press the key for the desired option. a. MAP b. FMS c. CKLST d. SYS e. AUDIO Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 360 Section 14. Primary Flight Display (PFD) Eclipse 5OO Systems Manual Figure 228. Keyboard Primary Function Group Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 361 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 362 R5 line select key, any time a new caution or warning level message appears. Figure 230. PFD Composite Mode - Caution CAS Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 363 Section 14. Primary Flight Display (PFD) Eclipse 5OO Systems Manual Figure 231. PFD Composite Mode- Warning CAS Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 364 14.6 Crew Alerting System Messages Table 36. PFD CAS Messages Message Condition Category AVIONICS COOLING FAN Left or Right PFD fans Advisory have failed XPDR 1 FAIL Transponder 1 or 2 has Advisory failed Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 365 Chevrons are located beyond the pitch ladder c. The ADI will not pitch beyond 70° d. None of the above 9. How are slips and skids indicated on the PFD? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 366 A black square d. None of the above 16. Describe how the pilot can change the view from the 120 arc view to the 360 degree compass view on the PFD: Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 367 19. What are the two ways to enter the composite mode on the PFD? 20. What information is lost from the PFD when composite mode is entered? 21. What is the default page on the PFD during composite mode? Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 368 The lower portion of the MFD allows pilot control of the Flight Management System, moving map, electronic checklists and all system synoptic pages. Figure 232. Multi-Function Display (MFD) Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 369 Section 15. Multi Function Display (MFD) Eclipse 5OO Systems Manual 15.2 Limitations and Specifications No content. THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 370 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 371 Flap Position Cabin Pressurization ⎯ Current cabin altitude ⎯ Current cabin altitude rate of climb ⎯ Cabin differential pressure (dP) Fuel Quantity Indicator Trim Position ⎯ Pitch ⎯ Roll ⎯ Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 372 Airspeed and Altitude Trend Vectors All Autopilot pre-select windows and bugs Flight director command bars. Localizer or Glide slope deviation indicators (HDI) and (VDI) Vertical speed V-speed bugs Radar Altimeter AOA indication Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 373 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 2 ADC 3 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 374 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 375 ACS, blue MCT text appears at the lower portion of the tape that is associated with the blue N1 bug. 15.5.2 Indicated Turbine Temperature (ITT) Figure 239. ITT Display Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 376 N2 values in the amber band, and in red for N2 values above the RPM limit. If the RPM exceeds the limit for 20 seconds, an ENG EXCEEDANCE warning message appears. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 377 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 378 If the exceedance continues, the oil pressure value and tape turn red. Oil Pressure Time Delay for Amber Display 9.1-10 None 8.1-9 5 minutes 1-1.9 90 seconds 0-0.9 10 seconds Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 379 Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 380 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 381 If any gear is in transit for more than 15 seconds, a LANDING GEAR FAIL caution message appears and the in-transit symbol remains displayed. Figure 247. Landing Gear Fail in Transit Indication Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 382 Figure 250. Flap Position Display (T/O Position) Flap asymmetry sensed by any flap actuator stops all flap movement, an CAS caution message FLAP FAIL also appears and the flap pointer remains in the last known position. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 383 Cabin altitude rate of change rounded to the nearest 100 fpm is presented. Should the cabin altitude rate be too high, the numeric digits turn amber. The crew can select the cabin rate of climb or descent between 0 and 2,500 feet per minute.
  • Page 384 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 warning messages. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 385 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 band and the message will disappear. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 386 Advisory Messages. A white advisory message alerts conditions that require flight crew awareness and may require subsequent flight crew response. Examples include a system malfunction or failure leading to a loss of redundancy or degradation of a system. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 387 CAS message window below a white dividing line. Within each group of messages, i.e. warnings, cautions, etc., a new message will displayed above existing messages. Figure 256. CAS Message Hierarchy Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 388 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 selection box Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 389 When “RECALL” is selected via the control knob and acknowledged, recall messages appear above the “RECALL” label. Messages in the recall bin are grouped chronologically within their categorizations. Figure 259. CAS Message Recall Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 390 DISC” appears on the PFD below the ⎯ FMA line. A second press of the autopilot disconnect pushbutton on the sidestick causes the aural tone and “AP DISC” message to disappear simultaneously. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 391 ARMED portion of the FIRE/ARMED button. • A second press of the FIRE/ARMED button discharges extinguishing agent and prompts a L (R) EXTNGR DSCHG advisory message to appear. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 392 Radar Altitude Callout CONDITION — Callouts of radar altitudes of 500, 100, 50, 20 and 10 feet. ⎯ AUDIO — Voice messages: ⎯...
  • Page 393 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 range •...
  • Page 394 CONFIG FLAP..........Flaps extended beyond takeoff range CONFIG ENG TEMP....Ambient temperature not entered on OPS synoptic NOTE: CONFIG FLAP warning will not appear for attempting takeoff with the flaps in the UP position Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 395 Ignition test control APR disable control Measured fuel quantity in each tank Low sump fuel state Fuel (FUEL) State of fuel pumps and valves Engine fuel flow Fuel temperature at sump tanks Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 396 AUDIO — Lower left set to AUDIO page, lower right set to page previously shown on lower left. OR if pressed twice, PILOT audio page appears on the lower left tile and COPILOT audio page appears on the lower right tile. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 397 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 398 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 ⎯ Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 399 If SPLIT is selected, the pilot and copilot can select different radios as their own transmit radio. Keyboard Control Figure 265. Keyboard Audio Control Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 400 Also displayed are aircraft totals for: Flight Hours ⎯ Left Engine Hours ⎯ Right Engine Hours ⎯ Left Engine Starts ⎯ Right Engine Starts ⎯ Cycles ⎯ Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 401 If the GROSS weight exceeds the maximum ramp weight the numeric value turns red. Should the calculated fuel load be unavailable the GROSS weight is displayed in amber, as the maximum takeoff weight. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 402 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 403 Pressing the REMOVE TARGET line select key removes the VREF bug on the PFDs and replaces the VREF value with three white dashes in the line select key window. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 404 Eclipse 5OO Systems Manual ⎯ 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 405 Section 15. Multi Function Display (MFD) Eclipse 5OO Systems Manual Figure 269. OPS VSPEED Manual VR Entry Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 406 “STALL, STALL” aural warning and activation of the stick pusher. Once the stick pusher has been engaged, indicating normal operation, the test is discontinued by pressing the STOP TEST line select key. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 407 Eclipse 5OO Systems Manual 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. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 408 Selection of the AHRS and ADC Source for the MFD ADI is not available. On start-up, the AHRS source defaults to AHRS 2, and if installed AHRS 3, while the ADC defaults to ADC 3. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 409 Section 15. Multi Function Display (MFD) Eclipse 5OO Systems Manual Figure 271. SENSOR Synoptic Page Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 410 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. SETUP Synoptic Page Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 411 PFD or MFD. The keyboard is divided into several key groups: Composite, Transponder, Primary Function, Alpha, Numerical, and COM/NAV. Figure 273. Keyboard Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 412 XPDR1 and XPDR2. When either XPDR1 or XPDR2 key is pressed, a green light above the XPDR1 or XPDR2 key illuminates and the selected transponder becomes active. This also automatically selects the XPDR page on the PFD. One Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 413 Sets the selected transponder to reply to ATC interrogations with the Mode A replies using whatever Mode A code is currently set. Sets the Mode A code of both transponders to 1200, Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 414 6 to tile 7. PERF Pressing the W/B key brings up the performance portion of the OPS page and shifts previously shown information on tile 6 to tile 7. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 415 PFD Tile 5 for communication and navigation frequency/code entries and MFD tiles 6 and 7 when numerical character input is appropriate. 15.9.7 COM/NAV Group Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 416 Pressing this key toggles the selected crew member’s overhead speaker on and off. The left keyboard controls the left Overhead Cockpit Speaker and the right keyboard controls the right Overhead Cockpit Speaker. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 417 MB key illuminates when the MB audio is on. 15.9.8 Cursor Control Device/Joystick Figure 280. Cursor Control Device/Joystick The cursor control device/joystick is used for input on the MAP display. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 418 Section 15. Multi Function Display (MFD) Eclipse 5OO Systems Manual 15.10 Normal Operations No Content THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 419 Eclipse 5OO Systems Manual 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 420 OAT not entered on OPS page and TLA past 40° Warning CONFIG PARKING BRAKE Parking brake handle is set and TLA past 40° Warning CONFIG RUDDER TRIM Rudder trim is not within takeoff limits and TLA Warning past 40° Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 421 Section 15. Multi Function Display (MFD) Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 422 Section 15. Multi Function Display (MFD) Eclipse 5OO Systems Manual 15.14 MFD Review Questions 1. List the information contained within each of the tiles below Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 423 It is displayed continuously as a digital readout on the top portion of the MFD c. Cabin altitude is only displayed when the pressurization synoptic page is selected d. None of the above Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 424 Eclipse 5OO Systems Manual 7. When will the total fuel quantity value turn amber on the fuel display? a. When total fuel remaining is less than 500 pounds b. When total fuel remaining is less than 100 pounds c. When total fuel remaining is less than 310 pounds d.
  • Page 425 Autoflight system mode annunciation is displayed on the PFD. The Autopilot, Yaw Damper and Autothrottle buttons on the autopilot control panel are also lighted to indicate a selected status. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 426 The ACS provides air data and attitude information as well as providing control of the stall warning function and provides the autoflight system with a command to activate the stick pusher as part of the stall protection system. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 427 R KBD Left Left Right Right Engine Start Switches Center Switch Panel Left Center Right Sidestick Pedestal Sidestick Stick Stick TOGA Force Force Disconnect Left Right Figure 281. Autoflight-ACS Interface Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 428 Stall Protection System and Stick Pusher must be successfully tested prior to flight. The use of the autothrottle system is prohibited. The following Autothrottle ECB must be collared: AUTOTHROTTLE SERVOS. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 429 PFD just above the green YD text on the upper left portion of the PFD. The green light on the AP OFF/ON button will also illuminate with Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 430 ARM the appropriate approach mode and show following white text on the flight mode annunciation window: 1. Lateral Modes a. LOC BC APPR b. LOC APPR c. VOR APPR d. FMS APPR NOTE: LOC APPR appears for both localizer and ILS approaches Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 431 The Flight Mode Annunciator (FMA) consists of several display fields at the top of the PFD. These modes appear in green when active and in white when armed. A white arrow appears in the lateral and vertical portions of the flight mode annunciation Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 432 When a previously armed mode becomes the active/engaged mode; the green text of the new active mode pulses for three seconds before becoming solid. The mode transitions which use pulsing are: Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 433 Table 42. Approach Flight Mode Annunciations ACTIVE ARMED Approach ACTIVE Lateral ARMED Lateral Sub-Mode Vertical Vertical Category Text Text Text Lateral Text LOC BC LOC BC APPR LOC BC APPR LOC ONLY Armed LOC APPR Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 434 FMS APPR Table 43. Autothrottle/Speed Flight Mode Annunciations Category Sub-Mode ACTIVE Text Speed Hold SPD HOLD Thrust Reference/Max Continuous Thrust (MCT) Autothrottle Underspeed Protection SPD PROT Overspeed Protection SPD PROT Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 435 • Pitch attitude within -15° and +25° • Pitch rate within ± 3.5° per second • Roll angle within 30° Left or Right Wing Down • Roll rate within ± 2° per second Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 436 In addition, the flight director will disappear automatically on the ground with airspeeds less than 45 knots. Manual removal of the flight director is accomplished by pressing the ALL INTERRUPT button on either sidestick. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 437 When coupled with the rest of the autopilot modes, the autoflight system is able to track airspeed, or if necessary automatically activate as part of the over and underspeed protection. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 438 -Automatically engages to control and limit airspeed airspeed Autopilot- -Autopilot- -Used to reduce and control airspeed using Will NOT automatically engage, pilot must pitch (elevator) manually control airspeed using pitch Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 439 Takeoff mode is a flight director only mode that is activated when the aircraft is on the ground in a takeoff configuration with the TOGA switch pressed. Both flight director Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 440 30° bank angle. In the event of an engine failure, the wings level logic will default to a 2° angle of bank into the operative engine to compensate for yaw due to asymmetric thrust. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 441 (ALT, ALT CHG, GS) becomes unavailable without a subsequent flight director mode present. To utilize pitch hold, press the A/P OFF/ON button to turn on the autopilot, if Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 442 The vertical speed target is automatically set on the VSI based on a computed 3° glide-path. The vertical speed bug will be solid, indicating that the flight director is tracking the vertical speed bug as a target. ALT CHG appears as the active Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 443 (this is commonly referred to at the cone of confusion). When using the VOR approach mode the lateral tracking tolerance is lowered for better accuracy during the approach. FMS APPR Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 444 When ALT CHG is activated, the thrust automatically increase to MCT, MCT appears as the active speed mode and the autopilot will track the airspeed using elevator authority. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 445 13. Press YD OFF/ON button and VERIFY that a. YD OFF/ON button light is off b. Symbol “YD” disappears from the top of the ADI c. Rudder pedals can be moved in either direction with normal resistance Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 446 ALT CHG is activated. After the pilot verifies speed bug position, the ALT CHG mode should be activated. ALT will appear as the armed pitch mode, with ALT CHG appears as the active pitch mode. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 447 ALT Button Pressed and Altitude Capture In-Progress ALT CAP ALT Button Pressed and Altitude Has Been Captured Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 448 VSI. This vertical speed will provide a 3° glide-path during the descent. To adjust the airspeed during the descent the pilot will have to adjust the power setting. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 449 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 be used to select the new altitude target. Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 450 Approach mode must be selected for the autoflight system to utilize the glideslope. Approach mode is also necessary to navigate with the precision required for an instrument approach procedure. Missed Approach Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 451 Missed Approach With VOR Mode Armed HDG HOLD GA-PITCH Missed Approach After VOR Mode and ALT CHG Have Activated ALT CHG Missed Approach With Heading Hold Only HDG-HOLD GA-PITCH Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 452 If a reset is unsuccessful the aircraft must descend below 20,000 ft and maintain airspeed below 250 knots per aircraft limitations. NOTE: See Airplane Flight Manual, Section 2- Limitations Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 453 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 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 454 Section 16. Autoflight Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 455 Nothing, the HDG-SEL knob cannot be pressed d. None of the above 7. Where is the autopilot computer located on the Eclipse 500? a. In the back of the plane against the pressure bulkhead b. There is no autopilot computer; all of the servos have central processing modules that work together.
  • Page 456 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? a. Yaw and roll b.
  • Page 457 Section 16. Autoflight Eclipse 5OO Systems Manual Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 458 Section 16. Autoflight Eclipse 5OO Systems Manual THIS PAGE INTENTIONALLY LEFT BLANK Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007...
  • Page 459 Index sample entry – 1 Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007 Index-1...
  • Page 460 Eclipse 5OO Systems Manual Index Copyright © — Eclipse Aviation Corporation Version 2.0 April 2007 Index-2...

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