Eclipse 550® Systems Manual

4.9 Oxygen Review Questions ................................................................................ 4-26 5 Ice Protection System ................................................................................ 5-1 5.1 General ................................................................................................................ 5-1 5.2 Aircraft Computer System (ACS) Interfaces .................................................... 5-2 5.3 Limitations and Specifications.......................................................................... 5-4 5.4 Controls and Indicators ..................................................................................... 5-6 5.5 System Description ............................................................................................ 5-8 5.6 Normal Operations ............................................................................................. 5-13 5.7 Abnormal Procedures ........................................................................................ 5-18 5.8 Crew Alerting System Messages ...................................................................... 5-24 5.9 Ice Protection Review Questions ...................................................................... 5-25 6 Fuel..................................................................................................................... 6-1 6.1 General ................................................................................................................ 6-1 6.2 Aircraft Computer System (ACS) Interfaces .................................................... 6-1 6.3 Limitations and Specifications.......................................................................... 6-3 6.4 Controls and Indicators ..................................................................................... 6-5 6.5 System Description ............................................................................................ 6-8 6.6 Normal Operations ............................................................................................. 6-18 6.7 Abnormal Procedures ........................................................................................ 6-19 6.8 Crew Alerting System Messages ...................................................................... 6-20 6.9 Fuel Review Question ........................................................................................ 6-21 7 Engines and Fire Protection ................................................................... 7-1 7.1 General ................................................................................................................ 7-1 7.2 Aircraft Computer Systems (ACS) Interfaces .................................................. 7-4 7.3 Limitations and Specifications.......................................................................... 7-11 7.4 Controls and Indicators ..................................................................................... 7-16 7.5 System Description ............................................................................................ 7-30 7.6 Normal Operations ............................................................................................. 7-44 7.7 Abnormal Procedures ........................................................................................ 7-47 Manual Contents Eclipse 550® Systems Manual Revision 00, May 2015 iii P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 00\06- Copyright © — Eclipse Aerospace Inc. 7.8 Crew Alerting System Messages ...................................................................... 7-49 7.9 Engine and Fire Protection Review Questions ................................................ 7-50 8 Climate Control ............................................................................................. 8-1 8.1 General ................................................................................................................ 8-1 8.2 Aircraft Computer System (ACS) Interfaces .................................................... 8-3 8.3 Limitations and Specifications.......................................................................... 8-4 8.4 Controls and Indicators ..................................................................................... 8-5 8.5 System Description ............................................................................................ 8-10 8.6 Abnormal Procedures ........................................................................................ 8-28 8.7 Crew Alerting System Messages ...................................................................... 8-29 8.8 Climate Control Review Questions ................................................................... 8-30 9 Electrical Distribution................................................................................. 9-1 9.1 General ................................................................................................................ 9-1 9.2 Aircraft Computer System (ACS) Interfaces .................................................... 9-2 9.3 Limitations and Specifications......................................................................... 9-4 9.4 Controls and Indicators ..................................................................................... 9-5 9.5 System Description ............................................................................................ 9-9 9.6 Normal Operation ............................................................................................... 9-17 9.7 Abnormal Procedures ........................................................................................ 9-20 9.8 Electronic Circuit Breakers Bus Allocation ..................................................... 9-22 9.9 Crew Alerting System Messages ...................................................................... 9-26 9.10 Electrical Review Questions.............................................................................. 9-27 10 Interior Lighting ............................................................................................ 10-1 10.1 General ................................................................................................................ 10-1 10.2 Aircraft Computer System (ACS) Interfaces .................................................... 10-1 10.3 Controls and Indicators ..................................................................................... 10-2 10.4 System Description ............................................................................................ 10-3 10.5 Normal Operations ............................................................................................. 10-10 10.6 Interior Lighting Review Questions .................................................................. 10-11 11 Exterior Lighting........................................................................................... 11-1 11.1 General ................................................................................................................ 11-1 11.2 Aircraft Computer System (ACS) Interfaces .................................................... 11-3 11.3 Controls and Indicators ..................................................................................... 11-5 11.4 System Description ............................................................................................ 11-6 11.5 Abnormal Procedures ........................................................................................ 11-7 11.6 Crew Alerting System Messages ...................................................................... 11-7 11.7 Exterior Lighting Review Questions ................................................................. 11-8 Manual Contents Eclipse 550® Systems Manual iv Revision 00, May 2015 P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 00\06- Copyright © — Eclipse Aerospace Inc. 12 Air Data ............................................................................................................. 12-1 12.1 General ................................................................................................................ 12-1 12.2 Aircraft Computer System (ACS) Interfaces .................................................... 12-2 12.3 Limitations and Specifications.......................................................................... 12-2 12.4 Controls and Indicators ..................................................................................... 12-4 12.5 System Description ............................................................................................ 12-6 12.6 Normal Operations ............................................................................................. 12-10 12.7 Abnormal Procedures ........................................................................................ 12-11 12 12.8 Standby Display Unit .......................................................................................... 12-12 12.9 Crew Alerting System Messages ...................................................................... 12-19 12.10 Air Data Review Questions ................................................................................ 12-20 13 Primary Flight Display (PFD) .................................................................. 13-1 13.1 General ................................................................................................................ 13-1 13.2 Limitations and Specifications.......................................................................... 13-2 13.3 System Description ............................................................................................ 13-4 13.4 Normal Operations ............................................................................................. 13-43 13.5 Abnormal Procedures ........................................................................................ 13-52 13.6 Distance Measuring Equipment (DME)............................................................. 13-59 13.7 Automatic Direction Finder (ADF)..................................................................... 13-60 13.8 Traffic Advisory System (TAS) .......................................................................... 13-61 13.9 Weather Radar System (WXR)........................................................................... 13-65 13.10 Stormscope ......................................................................................................... 13-69 13.11 Crew Alerting Messages – CNS......................................................................... 13-71 13.12 PFD Review Questions ...................................................................................... 13-72 14 Multi-Function Display (MFD) ................................................................. 14-1 14.1 General ................................................................................................................ 14-1 14.2 Limitations and Specifications.......................................................................... 14-2 14.3 System Description ............................................................................................ 14-2 14.4 Tile 5 – Crew Alerting System (CAS) ................................................................ 14-4 14.5 Tiles 7 & 8 – Configurable Displays .................................................................. 14-13 14.6 Checklists............................................................................................................ 14-40 14.7 Keyboard ............................................................................................................. 14-44 14.8 FMS Function Group .......................................................................................... 14-51 14.9 MAP Function Group........................................................................................14-111 14.10 Abnormal Procedures ......................................................................................14-145 14.11 Crew Alerting System Messages ....................................................................14-145 14.12 Takeoff Configuration Warnings .....................................................................14-145 14.13 Terrain Awareness and Warning System (TAWS)..........................................14-146 14.14 MFD Review Questions ....................................................................................14-152 Manual Contents Eclipse 550® Systems Manual Revision 00, May 2015 v P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 00\06- Copyright © — Eclipse Aerospace Inc. 15 Autoflight ......................................................................................................... 15-1 15.1 General ................................................................................................................ 15-1 15.2 Aircraft Computer System (ACS) Interfaces .................................................... 15-1 15.3 Limitations and Specifications.......................................................................... 15-3 15.4 Controls and Indicators ..................................................................................... 15-4 15.5 System Description ............................................................................................ 15-10 15.6 Normal Operations ............................................................................................. 15-21 15.7 Abnormal Procedures ........................................................................................ 15-29 15.8 Crew Alerting System Messages ...................................................................... 15-30 15.9 Autoflight Review Questions............................................................................. 15-31 16 Abbreviations and Acronyms ................................................................. 16-1 16.1 Eclipse 550 Abbreviations and Acronyms ....................................................... 16-1 Manual Contents Eclipse 550® Systems Manual vi Revision 00, May 2015 P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 00\06- Copyright © — Eclipse Aerospace Inc. [Intentionally Blank Page] Copyright © — Eclipse Aerospace Inc. -i P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Contents Eclipse 550® Systems Manual 1 Revision 00, May 2015 1 Avio Avionics Suite 1 1.1 General.............................................................................................................. 1-1 1.2 Aircraft Computer Systems...................................................................... 1-3 1.2.1 Automatic Command and Control of Systems ................................... 1-3 1.2.2 Performs Pilot Commands.................................................................... 1-4 1.2.3 Systems Monitoring and Fault Reporting ........................................... 1-4 1.3 Pilot Displays ................................................................................................. 1-5 1.3.1 Primary Flight Displays (PFD) .............................................................. 1-6 1.3.2 Multi Function Display (MFD) ............................................................... 1-7 1.4 Pilot Controls ................................................................................................. 1-9 1.4.1 Center Switch Panel (CSP) ................................................................... 1-9 1.4.2 Engine Start Switch Panel..................................................................... 1-10 1.4.3 Autopilot Control Panel......................................................................... 1-10 1.4.4 Sidestick (Left and Right) ..................................................................... 1-11 1.4.5 Instrument Panel - Left (IPL)................................................................. 1-12 1.4.6 Instrument Panel - Right (IPR).............................................................. 1-13 1.4.7 Armrest Panel ........................................................................................ 1-14 1.4.8 Keyboards .............................................................................................. 1-15 1.4.9 Throttle Quadrant Switches (Flaps and Rudder Trim) ....................... 1-16 1.4.10 Line Select Keys .................................................................................... 1-17 1.4.11 Tab Select Knobs................................................................................... 1-18 1.4.12 Primary Function Keys.......................................................................... 1-19 1.4.13 Concentric Knobs.................................................................................. 1-20 1.4.14 Single Rotary Knob ............................................................................... 1-21 1.5 Primary Sensors ........................................................................................... 1-21 1.6 Aircraft Subsystems.................................................................................... 1-22 1.7 Avionics Overview Review Questions ................................................. 1-23 Chapter 1. Avio Avionics Suite Contents Eclipse 550® Systems Manual – 06-124561 1-ii Revision 00, May 2015 P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Copyright © — Eclipse Aerospace Inc. Figures Figure 1-1. Cockpit Layout ............................................................................................... 1-1 Figure 1-2. Avionics Architecture...................................................................................... 1-2 Figure 1-3. Center Switch Panel....................................................................................... 1-7 Figure 1-4. Engine Start Switch Panel.............................................................................. 1-8 Figure 1-5. Autopilot Control Panel .................................................................................. 1-8 Figure 1-6. Sidestick......................................................................................................... 1-9 Figure 1-7. Left (Essential) Switch Panel ......................................................................... 1-10 Figure 1-8. Instrument Panel - Right ................................................................................ 1-11 Figure 1-9. Pilot's Side Armrest Panel.............................................................................. 1-13 Figure 1-10. Keyboard........................................................................................................ 1-14 Figure 1-11. Throttle Quadrant ........................................................................................... 1-15 Figure 1-12. Line Select Keys ............................................................................................ 1-16 Figure 1-13. Tab Select Knob............................................................................................. 1-17 Figure 1-14. Primary Function Keys ................................................................................... 1-18 Figure 1-15. Concentric Knobs........................................................................................... 1-19 Figure 1-16. Single Rotary Knob ........................................................................................ 1-20 Copyright © – Eclipse Aerospace Inc. -1 P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Eclipse 550® Systems Manual Revision 00, May 2015 1 1Avio Avionics Suite 1.1 General The Avio Avionics Suite is a highly integrated avionics system that serves as the basic systems architecture for and interfaces with most aircraft functions. See Figure 1-1. Avio is further divided into five functional areas: 1. Aircraft Computer Systems (ACSs) 2. Pilot displays 3. Pilot controls/interfaces 4. Primary sensors 5. Aircraft subsystems (e.g., electrical power generation/distribution) See Figure 1-2. While there are five functional areas, the two Primary Flight Displays (PFDs) and two Aircraft Computer Systems (ACSs) are the core of the avionics system. Through a series of data busses that interconnect all components of the avionics, many of the operations of the aircraft are routed through a combination of these four components. Data busses are electrical paths used to transfer data and instructions back and forth between components. Commands are sent along these data buses to the aircraft, and systems status information is then returned to the pilot. Figure 1-1. Cockpit Layout Chapter 1. Avio Avionics Suite 1.1 General Eclipse 550® Systems Manual – 06-124561 1-2 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Figure 1-2. Avionics Architecture Chapter 1. Avio Avionics Suite 1.2 Aircraft Computer Systems Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-3 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.2 Aircraft Computer Systems The Aircraft Computer System (ACS) consists of two identical ACS computers. Each ACS unit is co-located with one of the aircraft’s two Full Authority Digital Engine Control (FADEC) units in a Line Replaceable Unit (LRU) known as an Avio Processing Center (APC). The left Avio Processing Center is located along the left aft fuselage wall, while the right Avio Processing Center is located underneath the baggage compartment floor. While these units are physically the same, each individual (left or right) ACS will perform slightly different operations. The ACS has three primary functions:  Automatic command and control of systems  Performs pilot commands  Systems monitoring and fault reporting 1.2.1 Automatic Command and Control of Systems The command and control of systems capability of the ACS is the pilot’s primary means of systems control on the Eclipse 550. Unlike aircraft cockpits of the past, the Eclipse 550 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. The Eclipse 550 utilizes multiple types of automation. One type of automation involves split-second decisions that are faster than the pilot can make. This type of automation is exemplified by the FADEC. Fuel control decisions for the engine must be made many times per second, each time taking into account a range of aircraft parameters such as outside air temperature, air speed and altitude. In cases like this, the pilot is informed of overall performance (Indicated Turbine Temperature (ITT), N1 and N2 turbine speeds and oil pressure) to verify that the engine is performing within its design limits. Another type of automation reduces pilot workload. In many cases, functions that are routine or unnecessarily burdensome tasks have been automated. An example of this is the command of the electric fuel pumps. For most normal operations, the electric fuel pumps are in the automatic (AUTO) mode of operation. This means the ACS will activate the fuel pumps automatically for engine start, fuel crossfeed, and low fuel quantity or pressure. Notification of the pilot that this is occurring takes place through a STATUS level CAS (Crew Alerting System) message; this assures that the pilot is always kept aware of the current state of systems components. Another example of the ACS providing workload reducing automation is automatic electrical load shedding. When the ACS detects a loss of electrical power, i.e., the loss of one or both generators, it automatically load sheds the necessary electrical equipment to maintain sufficient power and systems functionality for the pilot to safely manage the aircraft. Chapter 1. Avio Avionics Suite 1.2 Aircraft Computer Systems Eclipse 550® Systems Manual – 06-124561 1-4 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.2.2 Performs Pilot Commands While several systems have automatic controls, the pilot has the capability to override or manually control systems components through hard switches in the cockpit and Line Select Keys (LSKs) on aircraft systems control pages, also known as “synoptic” pages. Commands from these hard switches and synoptic page LSKs are sent to the ACS, which activates the individual components. Examples of control and command of systems include:  Engine system control – ignition control, engine dry motoring  Fire suppression  Fuel system control – electric fuel pumps, fuel crossfeed  Flight controls – flap and trim control  Electrical – control of Electronic Circuit Breakers (ECBs)  Environmental – fan activation and speed, temperature control  Pressurization – aircraft pressurization settings  Ice protection – anti-ice and de-ice controls  Primary landing gear control  Exterior lighting – command of ECBs to activate and deactivate lighting 1.2.3 Systems Monitoring and Fault Reporting The system’s monitoring and reporting capability of the ACS allows reporting of various systems status to the pilot through the Primary Flight and Multi Function Displays (PFD and MFD). Examples of system monitoring and fault sensing include:  Electrical system monitoring (voltage amperage, contactor status, ECB status)  Fuel system monitoring (fuel gauging probes, fuel pumps, valves)  Secondary engine parameter monitoring (fuel flow, oil temperature, oil pressure)  Engine fire detection (fire detection thermistor loop)  Pressurization and climate control system monitoring (temperature sensors, valves)  Electro-Mechanical Actuator/Servo position monitoring (pitch, roll, and yaw trim servos, Vapor Cycle System (VCS) doors, Variable Outlet Ram-air Exhaust (VORE) doors)  Landing gear monitoring (proximity weight on wheel (WOW) and gear position)  Ice protection monitoring (temperature and pressure sensors in the de-ice/anti-ice system)  Door indication monitoring (proximity sensor on the locking bayonet of the main cabin door)  Brake system monitoring (optical brake fluid level sensor)  Oxygen system monitioring (oxygen pressure) Control monitoring is often attached to various Crew Alerting System (CAS) messages. For example, a PARKING BRAKE status message indicates that the PARKING BRAKE handle is extended. Chapter 1. Avio Avionics Suite 1.3 Pilot Displays Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-5 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev As a compliment to monitoring of systems, the ACS also provides fault sensing capability for the various systems components and their associated sensors. Failure monitoring is provided for various systems, including the failure of flap actuators, control valves such as the fuel shutoff valve, sensors such as the climate control temperature sensors. Should a component or sensor fail, a CAS message is displayed to the pilot to indicate that a failure has occurred. 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. 1.3 Pilot Displays The Electronic Flight Instrument System (EFIS) is the primary component of the integrated avionics suite contained on the Eclipse 550. The primary components of the EFIS are two 10.4 inch active matrix liquid crystal Primary Flight Displays (PFDs) and one 15.3 inch active matrix liquid crystal Multi Function Display (MFD). Figure 1-3. Cockpit Layout Chapter 1. Avio Avionics Suite 1.3 Pilot Displays Eclipse 550® Systems Manual – 06-124561 1-6 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.3.1 Primary Flight Displays (PFD) The PFDs have an important role in the AVIO avionics system. The PFDs function as information distribution centers. The PFDs route pilot commands to the ACS, which then sends the command to the appropriate aircraft subsystem. The aircraft subsystems send information to the ACS which then sends the information to the PFDs for display and further distribution to the MFD. Additionally, the PFDs provide the following display and control functionality (the PFDs are outlined in detail in Chapter 13, “Primary Flight Display (PFD)”: 1. Airspeed/mach 2. Altitude and vertical speed 3. Autopilot/yaw damper mode 4. Baro Setting 5. Autopilot/Flight Director targets a. Airspeed b. Attitude-flight director command bars c. Altitude d. Vertical speed e. Heading 6. Localizer and glideslope deviation 7. Attitude Direction Indicator (ADI) a. Pitch attitude b. Roll attitude c. Slip/skid indication 8. Magnetic heading 9. VOR, ILS, and FMS information. 10. Communications and navigation radio tuning 11. Transponder control 12. Composite mode (used during MFD failure) a. FMS (all except VNAV available) b. SYS (all except OPS: WEIGHT & PERF) c. AUDIO NOTE: MAP, CHKLST are unavailable on the PFD Chapter 1. Avio Avionics Suite 1.3 Pilot Displays Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-7 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.3.2 Multi Function Display (MFD) The MFD is the primary interface for the pilot to the aircraft systems and their status. This display is the center of the displays and a focal point for the pilot. All information to and pilot commands from the MFD is routed through both of the PFDs to the ACSs. The MFD is divided into upper and lower portions. The upper-right portion of the MFD is continuously displayed; the lower- and upper-left portions are configurable. Several systems synoptic pages presented on the MFD provide primary control of most system functionality. Each system synoptic page contains a schematic of the selected system which displays the status of primary system components. A synoptic page contains only information that the pilot needs to be aware of or that he/she has control over. Less significant information such as vent lines and other data not required to diagnose system state or performance is excluded to prevent clutter. System synoptic layouts are designed around operational control of the system and, although similar, do not represent actual system layout. The MFD provides the following display and control functionality and is outlined in detail in Chapter 14, “Multi-Function Display (MFD).” UPPER PORTION 1 1. Mini Tile a. MAP b. PROGRESS c. ACTIVE 2. Aircraft systems information a. Engine b. Landing Gear c. Flight Controls 1. Flaps 2. Trim d. Cabin pressurization e. Fuel 3. Crew Alerting System (CAS) LOWER PORTION 1 1. MAP a. Nav Display (ND) b. MAP 1. MAP INFO PAGE 2. MAP SETTINGS (a) XM SETTINGS (1) XM AGES Chapter 1. Avio Avionics Suite 1.3 Pilot Displays Eclipse 550® Systems Manual – 06-124561 1-8 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev c. CHART 1. AIRPORT MENU (a) AIRPORT INFO (b) XM DATA (1) METAR (2) TAF (3) CITY FORECAST (c) CHART MENU (1) Chart View — Tall chart 2. FMS a. Active flightplan (ACTV) b. Progress (PROG) c. Route (ROUTE) d. Nearest (NREST) e. User waypoints (USER) f. Vertical navigation (VNAV) 3. Normal Checklist (CKLST) 4. Aircraft systems synoptics (SYS) a. Engine (ENG) b. Fuel (FUEL) c. Electrical (ELECT) d. Electronic Circuit Breakers (ECB) e. Environmental (ENVIR) f. Flight Controls (FLCS) g. Pressurization (PRESS) h. Ice Protection (ICE) i. Aircraft Operations (OPS) 1. Weight and Balance (WEIGHT) 2. V-speeds and Engine Temperatures entry (VSPEED ENG TEMP) 3. Performance (PERF) 4. System Test (a) EFIS SERVICE MODE (b) MAINTENANCE MODE j. Setup (SETUP) 1. SENSORS (a) GPS (1) SATELLITE STATUS 2. SETTINGS (a) INSTALLED EQUIPMENT 3. Audio Mixer(AUDIO) Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-9 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4 Pilot Controls In addition to the PFD and MFD, there are several switch/control panels that allow direct pilot inputs to the aircraft. 1.4.1 Center Switch Panel (CSP) See Figure 1-4. The center switch panel serves as both a pilot control interface to aircraft systems and as a means of routing commands from other pilot control interfaces to the ACSs. The CSP is dual-channeled for redundancy. Pilot commands travel via the Left and/or Right Byteflight busses to the PFDs for distribution. Direct pilot controls include:  Landing light  Taxi/recognition lights  Normal landing gear handle  Strobe/beacon lights  Ice protection (engine anti-ice and wing de-ice)  Ice inspection light  Cabin lights  Dome light  Footwell lights (optional)  Cockpit dimming  Night/day switch Command Routing:  Engine start switch panel  Left and right sidesticks  Center pedestal (rudder trim switch and flap selector inputs) Figure 1-4. Center Switch Panel Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 1-10 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.2 Engine Start Switch Panel See Figure 1-5. Commands from the engine start switch panel are routed through the center switch panel to the PFD, then on to the ACS. The engine start switch panel has three positions:  OFF – Commands engine to off  ON/START – Initiates start sequence, position for normal operations  CONT IGN – Manually activates igniters Figure 1-5. Engine Start Switch Panel 1.4.3 Autopilot Control Panel See Figure 1-6. Autopilot control panel inputs are routed through the center switch panel to the PFD and on to the ACS. The autopilot control panel allows control of the following functions:  Autoflight mode and pre-select bug control  Barometer setting (BARO)  Map lights (left and right)  Caution/warning lights (left and right)  Fire warning and suppression (left and right) Figure 1-6. Autopilot Control Panel ,123 YD OFF/ON A/P OFF/ON ATS OFF/ON DOWN ALT-SEL UP HDG-SEL SPD-SEL BARO SET PUSH STD PUSH TO SYNC PUSH TO SYNC PUSH TO SYNC APPR ALT GHG ALT HDG NAV VNAV Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-11 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.4 Sidestick (Left and Right) Switch inputs from each sidestick are routed through the center switch panel to the PFD and on to the ACS. See Figure 1-7. In addition to flight control of the aircraft, the left and right sidesticks allow for the following functionality:  ALL INTERRUPT switch  Autopilot disconnect  Transponder IDENT  Microphone push to talk  Pitch and roll trim  Landing gear warning mute Figure 1-7. Sidestick Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 1-12 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.5 Instrument Panel - Left (IPL) See Figure 1-8. The IPL is also called the essential switch panel since many of the switches and controls on this panel: — have direct connections to the associated component and — do not require ACS control to function. The item that requires ACS functionality to operate is the CABIN AIR SOURCE switch that controls the position of the flow control valves. Left switch panel functionality includes:  Communications microphone selections (MIC MASK/HEADSET)  Mechanical circuit breakers (LEFT PFD & CNS (Communication, Navigation, Surveillance) 1, LEFT ACS)  Emergency Locator Transmitter (ELT) switch and annunciation  Five electrical contactor switches (Right Generator, Left Generator, System Battery, Bus Tie Contactor, Start Battery)  Oxygen PULL-ON Knob, PASSENGER MASK mode selector, and oxygen pressure display.  Cabin air control (AIR SOURCE and cabin DUMP) Figure 1-8. Instrument Panel - Left Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-13 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.6 Instrument Panel - Right (IPR) See Figure 1-9. The IPR contains the fifth continuous flow passenger oxygen mask. Aircraft with the optional second quick-don oxygen mask will have a Communications Microphone Selection switch for the copilot quick-don oxygen mask. Figure 1-9. Instrument Panel - Right Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 1-14 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.7 Armrest Panel See Figure 1-10. The armrest panels, while not considered a switch panel, are an important pilot interface. A panel beneath both the left and right side pilot armrests provides the following:  Oxygen line connection (quick don mask)  Oxygen mask microphone jack (quick don mask)  Pilot headset jacks (headphone and microphone)  Handheld microphone jack  USB Port  Mechanical Circuit Breakers  Left Armrest — COM1/NAV1 — ACP1 — PFD1 — XPDR1/KYBD1  Right Armrest — XPDR2/KYBD2 — PFD2 — ACP2 — COM2/NAV2 The USB port located under the left (pilot’s) armrest allows for uploading of important software and database updates (e.g., Jeppesen E-Chart and Navigation Databases). The USB port located under the right (co-pilot’s) armrest is used for maintenance purposes only. Figure 1-10. Pilot's Side Armrest Panel IMPORTANT: The pilot should not attempt to use the right (co-pilot's) USB port for other than maintenance purposes. Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-15 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.8 Keyboards See Figure 1-11. The keyboards are an alternate means for inputting data and controlling functions. Keyboard inputs are routed directly to the PFDs. All control functions, with the exception of some PFD composite mode functionality, can be accessed elsewhere on the flight deck. The keyboard supports the following:  MFD Primary function selection  Audio selection and control  Communication radio selection and control  Flight Management System (FMS) functions  Alphanumeric entry of waypoints and radio frequencies  Tab control for the MFD (PREV/NEXT)  Cursor Control Device (CCD)  Data Entry Path (LPFD/RPFD or MFD)  PFD Composite control  OPS: PERF page selection  Transponder (XPDR) selection and control Figure 1-11. Keyboard ON STBY IDNT XPDR 1 R PFD L PFD VFR ALT XPDR SQWK XPDR 2 PFD COMPOSITE ENTER 3 6 9 . 2 5 8 0 1 4 7 +/- / A H O V B I P W C J Q X D K R Y F M T SP G CLR E L S Z N U MAP FMS AUDIO SYS CHKLST W/B PERF PREV NEXT D V COM 2 COM 1 VOL PUSH SQ LO HI MB SWAP PILOT ISOL COM SEL PA SPKR MIN SET MONITOR Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 1-16 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.9 Throttle Quadrant Switches (Flaps and Rudder Trim) See Figure 1-12. The throttle quandrant contains the following switches:  Left and Right Engine Control Thrust Lever Angle (TLA) Rheostats - Throttles  Take-Off / Go-Around (TOGA)  Autothrottle Disconnect (A/T DISC)  Flap Position Selector  Rudder Trim Switch The throttles have no direct connection to the ACS. Information sensed by two position sensors for each throttle is sent directly to the FADEC units. Rudder trim, flap selector, A/T DISC and TOGA switch position information is sent through the center switch panel to the PFDs, then on to the ACS. Figure 1-12. Throttle Quadrant Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-17 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.10 Line Select Keys See Figure 1-13. Line select keys on the PFD and MFD allow control of various aircraft inputs, including frequency entry and system control. Each display has ten Line Select Keys (LSKs), five on each side. The Top Left LSK is referred to as Left LSK 1. Bottom Right LSK is referred to as Right LSK 5. Depending on what PFD or MFD functions are enabled, the screen label next to the LSK will annunciate what pressing the LSK will command. Line select keys are often associated with the PFD or MFD pages within which they are used to activate or deactivate specific systems components, such as the fuel pumps. Figure 1-13. Line Select Keys Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 1-18 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.11 Tab Select Knobs See Figure 1-14. The left and right Tab Select Knobs allow the pilot to select the desired tab at the bottom of the lower right and lower left tiles of the PFD and MFD. These knobs can be rotated to scroll through the available tabs. Scrolling is not a looping function; 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 1-14. Tab Select Knob Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-19 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.12 Primary Function Keys See Figure 1-15. There are five primary function keys located at the bottom of the MFD. These keys control what appears on the lower two tiles of the MFD. The pilot has five options: Map (MAP), Flight Management System (FMS), Checklist (CKLST), Systems (SYS), and Audio (AUDIO). Pressing each of these keys will configure the lower two tiles of the MFD as follows:  MAP Lower left tile set to the last used MAP tab; lower right tile set to page previously on the lower left.  FMS Lower left tile set to the FMS ACTV tab; lower right tile set to page previously on the lower left.  CKLST Lower left tile set to the electronic checklist page; lower right tile set to page previously on the lower left.  SYS Lower left set to last used systems synoptic tab or, if last page unknown, to the first tab in the list (ENG); right tile set to page previously on the lower left.  AUDIO Lower left set to the AUDIO page; lower right set to page previously shown on lower left. Figure 1-15. Primary Function Keys Chapter 1. Avio Avionics Suite 1.4 Pilot Controls Eclipse 550® Systems Manual – 06-124561 1-20 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.13 Concentric Knobs See Figure 1-16. Two concentric knobs are located on the bottom portion of the PFD and MFD. Each knob corresponds specifically to the information presented on the adjacent side of the display (left knob corresponds to the left portion of the PFD or lower left tile of the MFD; right knob corresponds to the right portion of the PFD or lower right tile of MFD). The Dual Concentric Knob (DCK) consists of an outer knob, an inner knob, and a center push button. Generally the outer knob is used to move a selector or to set the larger value (such as the MHz portion of a COM frequency). The inner knob is used to change the selected value or set the smaller value (such as the KHz portion of a COM frequency). The push button is used to activate a function in the selected LSK window (such as toggling standby and active COM frequency). If a LSK window in the column above the Dual Concentric Knob (DCK) is in focus (as indicated by a green outline) the knob will change the value in that window. Drop Down Menu Selection Some display pages contain additional drop down menus for control. Rotating the outer knob moves the cursor from field to field. Rotating the inner knob scrolls through drop down menu choices, and selections are made by pressing the inner knob. Sequential Choice Selection When a display allows sequential choices in a field, such as environmental fan speed settings, rotating the associated outer knob moves the cursor from field to field. Rotating the inner knob cycles through the choices for that field and pushing the inner knob will have no effect. Text Editing Rotating the outer knob allows movement of the cursor location within the text field. Once the cursor is placed over the desired text, rotating the inner knob will change the text. When editing is complete, pressing the inner knob sets the text. Figure 1-16. Concentric Knobs Chapter 1. Avio Avionics Suite 1.5 Primary Sensors Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-21 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.4.14 Single Rotary Knob See Figure 1-17. Single rotary knobs on the PFD provide control of master volume and squelch. The single rotary knob on the MFD provides the selection and acknowledgment of CAS messages on the MFD. Figure 1-17. Single Rotary Knob 1.5 Primary Sensors Air data, attitude, and navigation information are provided to the ACS by two Integrated Sensor Suites (ISS). Each ISS is comprised of the following three independent units working together: 1. Air Data Computer (ADC)  Pitot  Angle of Attack (AOA)  Static  Outside Air Temperature (OAT) 2. Attitude Heading and Reference Systems (AHRS)  Magnetometers Information from both Integrated Sensor Suites is sent to the ACS for comparison and failure monitoring, to FADECs for engine control, and to the PFD and MFD for display. Chapter 1. Avio Avionics Suite 1.6 Aircraft Subsystems Eclipse 550® Systems Manual – 06-124561 1-22 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.6 Aircraft Subsystems The Eclipse 550 aircraft subsystems include:  Engines and Fire Protection  Fuel  Electrical — Electronic Circuit Breakers (ECBs)  Climate control — Environmental — Pressurization  Ice protection  Landing gear — Anti-Skid Brakes  Flight controls  Oxygen  Autoflight — Autopilot — Autothrottle While most aircraft system functions are shared between the ACS units, there are some that are routed through a specific on-side ACS. For instance, engine starting is controlled by the on-side ACS (i.e., the left ACS controls the left engine starting). Trim also functions in this manner. The left ACS operates the roll trim and the left pitch trim, while the right ACS operates the yaw trim and the right pitch trim. The Flap System uses a slightly different arrangement: the left ACS controls the flaps via the left inboard actuator, and the right ACS controls the flaps via the right inboard actuator. All aircraft subsystems have ACS interfaces that are outlined in the various systems chapters. Chapter 1. Avio Avionics Suite 1.7 Avionics Overview Review Questions Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 1-23 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 1.7 Avionics Overview Review Questions 1. What are the five functional areas of Avio? a. b. c. d. e. 2. List and briefly describe the three functions of the Aircraft Computer Systems (ACSs). a. b. c. 3. The ACS controls what function of the two aircraft engines? 4. What information is NOT displayed on the upper portion of the MFD? a. Landing Gear Position b. Oil Temperature c. Oil Pressure d. Fuel Level 5. How do signals from the center switch panel get to the ACS? a. Through the autopilot control panel b. Directly c. Through the MFD d. Through the PFDs Chapter 1. Avio Avionics Suite 1.7 Avionics Overview Review Questions Eclipse 550® Systems Manual – 06-124561 1-24 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 6. List the eight instrument/switch panel inputs the pilot has: a. b. c. d. e. f. g. h. 7. Where are line-select keys found? a. On both PFDs b. On the MFD c. Both A and B d. None of the above 8. What action is accomplished by tab select knobs? a. They allow for volume control of the cockpit speakers. b. They allow the pilot to move from page to page on both the PFD and MFD. c. They allow the pilot to dim the PFD and MFD display. d. None of the above 9. What is the purpose of the primary function keys located below the MFD? a. They allow the pilot to quickly access frequently used MFD functions b. They are used as a backup to the tab select knobs c. Both A and B d. None of the above 10. What is a concentric knob? a. 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 Aerospace Inc. -i P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Contents Eclipse 550® Systems Manual 1 Revision 00, May 2015 2 Flight Controls 2 2.1 General.............................................................................................................. 2-1 2.2 Aircraft Computer System (ACS) Interfaces...................................... 2-3 2.2.1 Flaps ....................................................................................................... 2-3 2.2.2 Trim ......................................................................................................... 2-3 2.3 Limitations and Specifications................................................................ 2-5 2.3.1 Wing Flaps.............................................................................................. 2-5 2.4 Controls and Indicators ............................................................................. 2-6 2.4.1 Sidestick ................................................................................................. 2-6 2.4.2 Throttle Quadrant .................................................................................. 2-7 2.4.3 Flight Controls Synoptic ...................................................................... 2-8 2.4.3.1 TRIM ...................................................................................................... 2-9 2.4.3.2 ALL INTRP ............................................................................................. 2-9 2.4.3.3 ECB LINK ............................................................................................... 2-9 2.4.4 Flap Position Display ............................................................................ 2-10 2.5 System Description ..................................................................................... 2-11 2.5.1 Ailerons .................................................................................................. 2-11 2.5.2 Rudder .................................................................................................... 2-11 2.5.3 Elevator................................................................................................... 2-12 2.5.4 Sidestick ................................................................................................. 2-12 2.5.5 Trim ......................................................................................................... 2-12 2.5.6 Speed Controlled Pitch Trim................................................................. 2-12 2.5.7 Pitch Auto Trim ..................................................................................... 2-12 2.5.8 Flaps ....................................................................................................... 2-13 2.5.9 Gust Lock ............................................................................................... 2-13 2.6 Normal Operations....................................................................................... 2-14 2.6.1 Sidestick ................................................................................................. 2-14 2.6.1.1 Control Movement ................................................................................... 2-14 2.6.1.2 TRIM ...................................................................................................... 2-14 2.7 Abnormal Procedures................................................................................. 2-15 2.7.1 Elevator Trim Tab Split .......................................................................... 2-15 2.7.2 Alternate Trim......................................................................................... 2-15 2.8 Crew Alerting System Messages ........................................................... 2-16 2.9 Flight Controls Review Questions......................................................... 2-17 Chapter 2. Flight Controls Contents Eclipse 550® Systems Manual – 06-124561 2-ii Revision 00, May 2015 P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Copyright © — Eclipse Aerospace Inc. Figures Figure 2-1. Flight Controls Schematic .............................................................................. 2-2 Figure 2-2. ACS – Flap Interface...................................................................................... 2-4 Figure 2-3. ACS – Trim Interface...................................................................................... 2-5 Figure 2-4. Sidestick......................................................................................................... 2-6 Figure 2-5. Throttle Quadrant ........................................................................................... 2-7 Figure 2-6. FLCS Synoptic Flight Controls ....................................................................... 2-8 Figure 2-7. FLCS Synoptic Flight Controls ....................................................................... 2-9 Figure 2-8. In Transit to T/O Position ............................................................................... 2-10 Figure 2-9. Flap Position Display (T/O Position) .............................................................. 2-10 Figure 2-10. Rudder Pedal Adjustment .............................................................................. 2-11 Figure 2-11. Gust Lock ....................................................................................................... 2-14 Tables Table 2-1. Flight Control CAS Messages ........................................................................ 2-16 Copyright © – Eclipse Aerospace Inc. -1 P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Eclipse 550® Systems Manual Revision 00, May 2015 2 2Flight Controls 2.1 General See Figure 2-1. The flight control system consists of primary flight controls (ailerons, rudder, and elevator) and secondary flight controls (wing flaps and trim). The primary flight controls are operated with a sidestick and rudder pedals at each pilot station. The primary flight control system is a mechanical system which uses bellcranks, pushrods, cables and pulleys to actuate the control surfaces. Rudder pedals are individually adjustable. Trim for the three primary flight controls is electro-mechanically actuated. Elevator and aileron trim is controlled by a four-position switch on the top of each sidestick. Rudder trim is controlled by a rotary switch mounted on the aft portion of the center pedestal. Trim position for all three axes is displayed on the upper portion of the MFD, and in detail on the Flight Controls (FLCS) Synoptic. If a normal trim control fails, all three trim systems can be controlled using the flight controls synoptic page on the MFD. All trim motors can be inhibited in the event of a trim runaway by use of the ALL INTERUPT button on the sidesticks. To protect against high wind conditions, a gust lock is placed over the left sidestick and locked into the pilot seat rail to secure the ailerons and elevator in place. Rudder movement is inhibited by mechanical resistance from the nose wheel steering system. The wing flaps are electro-mechanically actuated 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. Chapter 2. Flight Controls 2.1 General Eclipse 550® Systems Manual – 06-124561 2-2 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Figure 2-1. Flight Controls Schematic Chapter 2. Flight Controls 2.2 Aircraft Computer System (ACS) Interfaces Eclipse 550® Systems Manual – 06-124561 Revision 00, May 2015 2-3 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev 2.2 Aircraft Computer System (ACS) Interfaces 2.2.1 Flaps See Figure 2-2. There are four electromechanical flap actuators on the Eclipse 550, 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 monitors the actuators, and potentiometers to determine flap position. The left flap actuators receive their commands and report their status to the right ACS, and the right flap actuators receive their commands and report their status to the left ACS. All actuators communicate with each other to assure flap position agreement 2.2.2 Trim See Figure 2-3. The Eclipse 550 has four trim motors; two are used to move the elevator trim tabs (pitch), one to change the centering spring position (roll), and one to move the rudder trim tab (yaw). Pilot control for pitch and roll trim is through the trim switch on each sidestick, and rudder trim inputs are made through the rudder trim switch on the throttle quadrant. The ACS commands the actuators based on these pilot inputs. The left ACS is responsible for commanding and monitoring the left pitch trim and roll trim motors, while the right ACS is responsible for commanding and monitoring the right pitch trim and yaw trim motors. In addition to commanding the trim motors, the ACS also receives position information from each actuator and monitors for unexpected movement, actuator position errors, and pitch trim disagreement. Chapter 2. Flight Controls 2.2 Aircraft Computer System (ACS) Interfaces Eclipse 550® Systems Manual – 06-124561 2-4 Revision 00, May 2015 Copyright © – Eclipse Aerospace Inc. P:\Customer and Product Support\Technical Media\Master Systems Manual 550 (06-124561)\06-124561 - Rev Figure 2-2. ACS – Flap Interface