Garmin G5000 Airplane Flight Manual Supplement
  1. Manuals
  2. Brands
  3. Garmin Manuals
  4. Car Navigation system
  5. G5000
  6. Airplane flight manual supplement

Garmin G5000 Airplane Flight Manual Supplement

Hide thumbs
Table of Contents

Advertisement

Quick Links

Download this manual

Advertisement

Table of Contents
loading

Related Manuals for Garmin G5000

Summary of Contents for Garmin G5000

  • Page 2 GARMIN. GARMIN hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and...
  • Page 3 GARMIN International, Inc FAA Approved Airplane Flight Manual Supplement for G5000 Integrated Flight Deck Textron Aviation Citation Model 560XL Log Of Revisions PAGE DATE OF FAA APPROVED DESCRIPTION NO(S) APPROVAL Original Issue 06/07/2019 Robert G. Murray Changes for CPDLC including removal of...
  • Page 4 Revision 8 – Change Summary  Section Page Description of Change Section I -- General 1-11 Addition of manually scalable CDI support for A-RNP approaches. Appendix A – Systems A-20 Addition of CAS secondary aural cue description. Description Textron Aviation Citation 560XL 190-02313-03 Rev.
  • Page 5 Table of Contents Section I – General ............................ 1-1   Section II – Limitations ..........................2-1   Section III – Operating Procedures ......................3-1   Section IV – Performance .......................... 4-1   Section VI – Weight and Balance ......................6-1  ...
  • Page 6 This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8...
  • Page 7 The information in this supplement is FAA-approved material and must be attached to the FAA Approved Airplane Flight Manual (AFM) when the airplane has been modified by installation of the GARMIN G5000 Integrated Flight Deck including Digital Automatic Flight Guidance System in accordance with GARMIN International, Inc.
  • Page 8 Section I - General G5000 GNSS (GPS/SBAS) Navigation System Equipment Approvals The Garmin G5000 Integrated Avionics GNSS navigation system installed in this aircraft is a GPS system with a Satellite Based Augmentation System (SBAS) comprised of two TSO-C145c Class 3 approved Garmin GIA 64Es, two TSO-C146c Class 3 approved Garmin GTC 575 Touchscreen Control Units, Garmin GA36 and GA37 antennas, and GPS software version 7.0 or later approved version.
  • Page 9 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ B-RNAV / This does not FAA AC RNAV 5 constitute an 90-96A (Europe) operational approval. CHG 1, EASA AMC 20-4A RNP 4...
  • Page 10 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ (continued) following the aircraft and training guidance in AC 90-100A are authorized to fly RNAV 2 procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require...
  • Page 11 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ RNAV 1 The GNSS RNAV FAA AC Includes RNAV terminal system is installed 20-138D departure and arrival and meets the CHG 2, procedures.
  • Page 12 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ P-RNAV This does not FAA AC ICAO flight plan code for (Europe) constitute an 90-96A P-RNAV no longer exists. operational approval.
  • Page 13 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ RNP-2 GNSS FDE FAA AC The GPS equipment as (Oceanic / availability must be 20-138D installed complies with the Remote) verified prior to flight.
  • Page 14 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ RNP APCH When flying an RNP FAA AC Includes non-precision LNAV minima procedure with a 20-138D approaches based on radius-to-fix (RF) leg, CHG 2,...
  • Page 15 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ RNP APCH When flying an RNP FAA AC Includes area navigation LNAV/VNAV procedure with a 20-138D approaches titled minima radius-to-fix (RF) leg,...
  • Page 16 Model 560XL Section I - General Operational ICAO Flight Navigation Reference Requirements/ Plan Code Notes Specification Documents Authorization Item 10a Item 18 Code PBN/ (continued) authorized to fly RNP APCH LP minima procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval.
  • Page 17 FDE/RAIM availability worldwide can be determined via the following: • An FDE prediction tool that satisfies the guidance of FAA AC 20-138D and AC 90-105A (or later revision), such as the Garmin WFDE prediction program, part number 006-A0154-01 or later approved version with GPS SW >= 3.0 selected Also, within the United States: 190-02313-03 Rev.
  • Page 18 WFDE Prediction Program, refer to GARMIN WAAS FDE Prediction Program, part number 190-00643-01, ‘WFDE Prediction Program Instructions’. Garmin International holds an FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153A for database integrity, quality, and database management practices for the Navigation database. Flight crews and operators can view the LOA status at FlyGarmin.com then select “Aviation Database...
  • Page 19 Model 560XL Section I - General Deck AFMS, see the Textron AFMS “Airplanes Certified For Steep Approaches” and the basic airplane flight manual. 190-02313-03 Rev. 8 Textron Aviation Citation 560XL 1-13...
  • Page 20 Model 560XL Section I - General ATC Data Link System (CPDLC) and ACARS (Optional) The FAA has approved the optional aircraft data link system meeting the criteria in AC 20-140C for the following datalink capabilities: Optionally Installed Capability FANS 1/A + FAA Data Comm Link 2000+ ACARS...
  • Page 21 Model 560XL Section I - General When filing ICAO flight plans, use the table below to determine what equipment codes should be filed in reference to the installed data link system. Optionally Installed Capability  Flight Plan Filing FANS 1/A + (Includes ACARS) Field 10a: E3J4J7Z Field 10b: D1 Field 18:...
  • Page 22 Model 560XL Section I - General The following data link options are available in various combinations: FANS 1/A +, FAA Data Comm, Link 2000+, and ACARS. To determine what data link options have been installed on the aircraft: 1. On the GTC homepage, press the “ATC Datalink” button. If an “ADS-C” tab is visible on this page, FANS 1/A + is installed.
  • Page 23 Global Positioning System BANK Low-bank mode of the AFCS GPWS Ground Proximity Warning System BARO Barometric Setting Garmin Reference System (AHRS) Back Course Glide Slope BRNAV Basic Area Navigation Garmin Touchscreen Controller Course Deviation Indicator AFCS heading mode or the HDG button...
  • Page 24 Model 560XL Section I - General Navigation, or AFCS navigation mode, TEMP Temperature or NAV button on the GMC 7200 AFCS Takeoff Mode Controller TOLD Takeoff and Landing Data NEXRAD Next Generation Radar (XM Weather Product) Technical Standard Order Nautical Mile Underspeed Protection Non-precision Approaches VAPP...

  • Page 25: Table Of Contents

      G5000 Integrated Flight Deck ........................2-12   GRS 79 AHRS Areas of Operation Limitations (If Installed) ..............2-13   G5000 GNSS (GPS/SBAS) Navigation System Limitations ..............2-14   Autopilot Operation Limits ........................2-15   Synthetic Vision Limits ..........................2-15  ...
  • Page 26 Model 560XL Section II – Limitations This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 FAA Approved...

  • Page 27: Cockpit Reference Guide

    Section II – Limitations Cockpit Reference Guide The G5000 Cockpit Reference Guide for Textron Aviation Citation 560XL must be immediately available to the flight crew during all phases of flight. Use the G5000 Cockpit Reference Guide for Textron Aviation Citation 560XL, GARMIN part number 190-02538-02, revision A or later approved revision, when System Software Version 3343.02 is installed.
  • Page 28 Model 560XL Section II – Limitations Inter-Turbine Temperature Indicators (ITT): Model Excel (Aircraft Serial Numbers 560 – 5001 through 560 – 5500) ITT Scale Markings, Engine Start: Green Band: 0 – 670°C Amber Line: 670°C Amber Band: 670°C – 720°C Red Line: 720°C Red Band: 720°C and higher ITT Pointer and Numeric Markings –...
  • Page 29 Model 560XL Section II – Limitations Model XLS (Aircraft Serial Numbers 560 – 5501 through 560 – 6000) ITT Scale Markings, Engine Start: Green Band: 0 – 670°C Amber Line: 670°C Amber Band: 670°C – 740°C Red Line: 740°C Red Band: 740°C and higher ITT Pointer and Numeric Markings –...
  • Page 30 Model 560XL Section II – Limitations Turbine (N ) RPM Indicators Model Excel (Aircraft Serial Numbers 560 – 5001 through 560 – 5500) Numeric Display Coloring Numeric N Display Color ≤ 101.8% Green text, black background > 101.8% and ≤ 103% Black text, amber background within transient time limits * >...
  • Page 31 Model 560XL Section II – Limitations Oil Pressure Indicators Model Excel (Aircraft Serial Numbers 560 – 5001 through 560 – 5500) Numeric Oil Oil Pressure (PSI) Pressure Display Color White text on red > 0 and < 20 background Green text on black ≤...
  • Page 32 Model 560XL Section II – Limitations Model XLS (Aircraft Serial Numbers 560 – 5501 through 560 – 6000) Oil Pressure Numeric Oil Pressure (PSI) Display Color White text on red > 0 and < 20 background Green text on black ≤...
  • Page 33 Model 560XL Section II – Limitations Oil Temperature Display Markings Model Excel (Aircraft Serial Numbers 560 – 5001 through 560 – 5500) Aircraft Configurations AM, AX, and AY Oil Temp Numeric Oil Temp (°C) Display Color < -40 White text on red background ≥...
  • Page 34 Model 560XL Section II – Limitations Model XLS (Aircraft Serial Numbers 560 – 5501 through 560 – 6000) Oil Temp. Numeric Oil Temp. (°C) Display Color < -40 White text on red background ≥ -40, < 10 Black text on amber background ≥...

  • Page 35: Airspeed Indicator Markings

    Model 560XL Section II – Limitations Airspeed Indicator Markings There are no changes to airspeed limitations. Refer to the Airplane Flight Manual for airspeed limitations. Airspeed Indicator Markings – PFDs Maximum Red Line Below 8,000 feet ..................260 KIAS Between 8,000 to 26,515 feet ..............305 KIAS Above 26,515 feet ..................

  • Page 36: G5000 Integrated Flight Deck

    BATT and AVIONIC POWER switches turned on for at least 30 minutes prior to takeoff. (Refer to Operating Information, Cold Weather Procedures, in this AFMS). Ground operation of the G5000 system with the RADOME FAN CAS message displayed is limited to 30 minutes maximum.

  • Page 37: Grs 79 Ahrs Areas Of Operation Limitations (If Installed)

    GRS 79 AHRS Areas of Operation Limitations (If Installed) For aircraft equipped with the GRS 79 AHRS, flight operations with the G5000 Integrated Flight Deck are prohibited in the following regions, due to the unsuitability of the magnetic fields near the Earth’s poles.

  • Page 38: G5000 Gnss (Gps/Sbas) Navigation System Limitations

    (or later revision) to demonstrate that there are no outages on the specified route that would prevent the G5000 from providing primary means of Class II navigation in oceanic and remote areas of operation that requires RNP-2 oceanic/remote, RNP-4, or RNP-10 capability.

  • Page 39: Autopilot Operation Limits

    It is prohibited to flight plan to an alternate airport based on minima for which SBAS is required (RNAV(GPS) LP/LPV). Use of the Garmin G5000 GPS/SBAS receivers to provide navigation guidance during the final approach segment of an ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for “or GPS”...

  • Page 40: Taws, Gpws, And Terrain System Limits

    Data Link Weather (XM AND CONNEXT Weather) Limits Datalink weather information displayed by the G5000 system is limited to supplemental use only. XM or Garmin Connext (Iridium Satellite Data Link) weather data is not a source of official weather information.

  • Page 41: Takeoff And Landing Data (Optional)

    Section II – Limitations Takeoff and Landing Data (Optional) The flight crew must confirm the active TOLD database part number on each flight when takeoff or landing performance data is obtained from the G5000 system: Aircraft TOLD Database Part Number...
  • Page 42 Model 560XL Section II – Limitations This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 2-18 FAA Approved...
  • Page 43 Model 560XL Section III – Operating Procedures Section III – Operating Procedures Table of Contents Operating Procedures – General ....................... 3-3   AFM CROSS REFERENCE ........................3-4   RED MESSAGE PROCEDURES ......................3-5   AMBER MESSAGE PROCEDURES ..................... 3-6   WHITE MESSAGE PROCEDURES .......................
  • Page 44 Model 560XL Section III – Operating Procedures This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 FAA Approved...

  • Page 45: Operating Procedures - General

    Many of the original AFM procedures are unchanged, however several existing AFM procedures were modified or removed as part of the G5000 installation. The AFM cross reference sections in this manual will serve as a guide to locating the correct version of procedures for use with the G5000 installation. Warning and Test System The original annunciator panel has been replaced by an integrated CAS in the G5000.

  • Page 46: Afm Cross Reference

    Aircraft Flight Manual. No procedures that were newly added for the G5000 installation are listed in this cross reference, since they are only included in the G5000 AFMS.

  • Page 47: Red Message Procedures

    RED MESSAGE PROCEDURES Airspeed, Altitude and/or Vertical Speed Indicators, Red “X” on PFD (Air Data Computer Failure – Dual or Single) ..........G5000 AFMS Failed Airspeed, Altitude, and/or Vertical Speed Red “X” on PFD/MFD (Symbol Generator Failure-Single) ........... NOT APPLICABLE Red “X”...

  • Page 48: Amber Message Procedures

    ANTISKD INOP (LO BRK PRESS Cleared) ................. UNCHANGED AOA ............................G5000 AFMS AOA Fail AOA HTR FAIL ........................UNCHANGED AP FAIL or AP OFF ....................... G5000 AFMS AP Fail or AP - YD Fail APU FAIL ..........................UNCHANGED APU RELAY ENGAGED ....................... UNCHANGED ARM ............................
  • Page 49 Section III – Operating Procedures AFM Cross Reference GEN OFF L and R ............MODIFIED WITH ADDITIONAL INFORMATION Refer to this procedure in the G5000 AFMS for operative EMER bus equipment GEN OFF L or R ........................UNCHANGED GND PROX ..........................G5000 AFMS TAWS or GPWS Caution GS ..........................

  • Page 50: White Message Procedures

    TL DEICE PRESS L or R ...................... UNCHANGED EMERGENCY/ABNORMAL PROCEDURES ENGINE Engine Failure or Other Emergency During Takeoff ............UNCHANGED Engine Failure During Final Approach ................... G5000 AFMS Dual Engine Failure ......................UNCHANGED Engine Failure/Precautionary Shutdown ................UNCHANGED In-Flight Restart – One Engine ..................... UNCHANGED Engine Display Failure (Blank Display Channel) ............
  • Page 51 CABIN/COCKPIT/BAGGAGE COMPARTMENT FIRE OR SMOKE Environmental System Smoke or Odor ................UNCHANGED Electrical Fire or Smoke ..........MODIFIED WITH ADDITIONAL INFORMATION Refer to this procedure in the G5000 AFMS for operative EMER bus equipment Smoke Removal ........................UNCHANGED ELECTRICAL Battery Charging ........................UNCHANGED PRESSURIZATION/ENVIRONMENTAL Overpressurization (>9.5 PSID) ....................
  • Page 52 TAWS Warning, TAWS or GPWS Caution TCAS II Traffic Advisory......................UNCHANGED TCAS II Resolution Advisory ....................UNCHANGED Total Loss of COMM and/or NAV Radio Tuning ..............G5000 AFMS Dual GTC (Touch Screen Controller) Failure Airspeed, Altitude and/or Vertical Speed Indicators, Red “X” on PFD (Air Data Computer Failure –...

  • Page 53: Normal Procedures

    Before Taxi..........................UNCHANGED (EFIS Test Switch no longer installed) Taxi ............................UNCHANGED Before Takeoff ..............MODIFIED WITH ADDITIONAL INFORMATION Refer to G5000 AFMS for Transponder and TCAS mode verification Before Starting Engines ......................UNCHANGED Takeoff Static Takeoff ......................... UNCHANGED Rolling Takeoff ....................... UNCHANGED After Takeoff/Climb .......................

  • Page 54: Operating Information

    Anti-Ice Additives ........................UNCHANGED Supplemental Oxygen System ....................UNCHANGED Terrain Awareness Warning System ................NOT APPLICABLE Traffic Collision Avoidance System (TCAS II) ................G5000 AFMS Flight Into Icing ......................... UNCHANGED Anti-Ice and Deice Systems ..................... UNCHANGED Cold Weather Operations ......................UNCHANGED Rain Removal ...........................
  • Page 55 Model 560XL Section III – Operating Procedures Emergency Procedures Emergency Procedures Table of Contents Overspeed Recovery ..........................3-15   Engine failure during final approach ......................3-16   Electrical Fire or Smoke ........................... 3-17   GEN Off L and R Caution Lights On and Master Warning (Loss of Both Generators) ......3-18  ...

  • Page 56: Emergency Procedures

    Model 560XL Section III – Operating Procedures Emergency Procedures This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 3-14 FAA Approved...

  • Page 57: Emergency Procedures

    Model 560XL Section III – Operating Procedures Emergency Procedures OVERSPEED RECOVERY  MAXSPD Annunciator is displayed 1. Throttles – REDUCE AS REQUIRED. 2. Speed Brakes – AS REQUIRED.  WHEN OVERSPEED CONDITION IS CORRECTED: 3. Autopilot – RESELECT VERTICAL MODE (IF REQUIRED) NOTE The autopilot overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum redline airspeed (see Section II of this manual for PFD...

  • Page 58: Engine Failure During Final Approach

    Model 560XL Section III – Operating Procedures Emergency Procedures ENGINE FAILURE DURING FINAL APPROACH  Model Excel (Aircraft Serial Numbers 560 – 5001 through 560 – 5500)  IF FLAPS ARE 15° OR LESS (CONTINUE AND LAND AT 15° FLAPS) 1.

  • Page 59: Electrical Fire Or Smoke

    ELECTRICAL FIRE OR SMOKE  This procedure is unchanged with the installation of the G5000 system, except the operative equipment list with the battery switch in EMER and the generators OFF is updated below. With the battery switch in EMER and the generators OFF, a properly charged battery will supply...

  • Page 60: Gen Off L And R Caution Lights On And Master Warning (Loss Of Both Generators)

     WARNING (LOSS OF BOTH GENERATORS) This procedure is unchanged with the installation of the G5000 system, except the operative equipment list with the battery switch in EMER and the generators OFF is updated below. With the battery switch in EMER and the generators OFF, a properly charged battery will supply...

  • Page 61: Emergency Descent Mode (Autopilot)

    Section III – Operating Procedures Emergency Procedures EMERGENCY DESCENT MODE (AUTOPILOT)  The operation of the G5000 Emergency Descent Mode is described below. WARNING THE AUTOPILOT EMERGENCY DESCENT MODE (EDM) CANNOT ACHIEVE MAXIMUM DESCENT RATE. IT IS RECOMMENDED THAT THE AUTOPILOT BE DISENGAGED AND THE AIRPLANE HAND FLOWN IF MAXIMUM DESCENT RATE IS REQUIRED.

  • Page 62: Autopilot Or Yaw Damper Malfunction / Pitch Trim Runaway Or Failure

    Model 560XL Section III – Operating Procedures Emergency Procedures AUTOPILOT OR YAW DAMPER MALFUNCTION / PITCH TRIM  RUNAWAY OR FAILURE This procedure supersedes the previous AFM procedure AUTOPILOT MALFUNCTION and ELECTRIC ELEVATOR RUNAWAY TRIM. If the airplane attitude deviates unexpectedly from the planned flight path: 1.

  • Page 63: Autopilot Abnormal Disconnect

    Model 560XL Section III – Operating Procedures Emergency Procedures AUTOPILOT ABNORMAL DISCONNECT  Flashing on PFD, Continuous Aural Disconnect Alert 1. AP YD DISC/TRIM INT button – PRESS and RELEASE (To Cancel Aural Disconnect Alert) 2. Aircraft Attitude – MAINTAIN AIRCRAFT CONTROL NOTE The autopilot disconnect may be accompanied by a white CAS message “AP FAIL”...

  • Page 64: Elevator Mistrim

    Model 560XL Section III – Operating Procedures Emergency Procedures ELEVATOR MISTRIM   ELE  ELE Annunciator displayed Indicates a mistrim of the elevator while the autopilot is engaged. Servo is providing force in the indicated direction. The autopilot will normally trim the airplane as required. If the autopilot is disconnected while this message is displayed, high elevator control forces are possible.

  • Page 65: Autopilot Underspeed Protection Activation And Recovery

    Model 560XL Section III – Operating Procedures Emergency Procedures AUTOPILOT UNDERSPEED PROTECTION ACTIVATION AND  RECOVERY (Optional USP Equipped Aircraft Only) UNDERSPEED PROT ACTIVE CAS message displayed. MINSPD annunciator above the airspeed tape display May also be accompanied by an amber and aural “AIRSPEED”...

  • Page 66: Twy Takeoff Surfacewatch Warning

    Model 560XL Section III – Operating Procedures Emergency Procedures TWY TAKEOFF SURFACEWATCH WARNING  (Optional SurfaceWatch equipped aircraft only.) TWY TAKEOFF Annunciator is displayed and aural “TAXIWAY” Message Takeoff – ABORT. a. Brakes – APPLY. b. Throttles – IDLE. c. SPEED BRAKE Switch – EXTEND. d.

  • Page 67: Rwy Too Short Surfacewatch Warning (During Takeoff)

    SPEED BRAKE Switch – EXTEND. d. Thrust Reversers – DEPLOY (As Required). 2. Aircraft Position and Runway Assignment – CONFIRM. 3. Ensure correct origin, runway, and required takeoff distance have been entered into the G5000 system:  From the GTC Home screen: PERF – Takeoff Data...
  • Page 68 Model 560XL Section III – Operating Procedures Emergency Procedures 5. Do not retract flaps or landing gear until safe climb-out is assured.  AFTER POSITIVE RATE OF CLIMB IS ESTABLISHED WITH AN AIRSPEED OF AT LEAST 6. FLAPS – T.O. & APPR (15°). 7.
  • Page 69 Model 560XL Section III – Operating Procedures Abnormal Procedures Abnormal Procedures Table of Contents Aileron Mistrim ............................3-31   Elevator Mistrim ............................3-32   Rudder Mistrim ............................3-33   AP PITCH TRIM FAIL ..........................3-34   AP FAIL or AP – YD Fail .......................... 3-34  ...
  • Page 70 Model 560XL Section III – Operating Procedures Abnormal Procedures GPS Approach – Downgrade ........................3-45   GPS Approach – Loss of Navigation ....................... 3-45   Audio (GMA) Failure ..........................3-46   Loss of COM Radio Tuning Functions ..................... 3-46   Failed Airspeed, Altitude, and/or Vertical Speed ..................
  • Page 71 Model 560XL Section III – Operating Procedures Abnormal Procedures TAWS N/A or TAWS FAIL ........................3-58   GPWS FAIL .............................. 3-58   Amber SYNC Indication ........................... 3-58   Amber START Indication ......................... 3-58   FUEL IMBALANCE ..........................3-59   P/S HEATER L or R (Pitot-Static Heater Failure) ..................3-59  ...
  • Page 72 Model 560XL Section III – Operating Procedures Abnormal Procedures This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 3-30 FAA Approved...

  • Page 73: Aileron Mistrim

    Model 560XL Section III – Operating Procedures Abnormal Procedures AILERON MISTRIM  AIL or AIL Annunciator displayed Indicates a mistrim of the roll axis while the autopilot is engaged. The servo is providing force in the indicated direction. If the autopilot is disconnected while this message is displayed, high roll forces are possible.

  • Page 74: Elevator Mistrim

    Model 560XL Section III – Operating Procedures Abnormal Procedures ELEVATOR MISTRIM  ELE or ELE Annunciator displayed Indicates a mistrim of the elevator while the autopilot is engaged. The servo is providing force in the indicated direction. The autopilot will normally trim the airplane as required. However, during rapid acceleration, deceleration, configuration changes, or near either end of the elevator trim limits, momentary illumination of this message may occur.

  • Page 75: Rudder Mistrim

    Model 560XL Section III – Operating Procedures Abnormal Procedures RUDDER MISTRIM  RUD or RUD Annunciator displayed Indicates a mistrim of the rudder while the yaw damper is engaged. The servo is providing force in the indicated direction. The system cannot trim the airplane in yaw. This message may be displayed during conditions of high asymmetric thrust.

  • Page 76: Ap Pitch Trim Fail

    Model 560XL Section III – Operating Procedures Abnormal Procedures AP PITCH TRIM FAIL  AP PITCH TRIM FAIL CAS message displayed NOTE Display of this CAS message alerts the crew that the automatic pitch trim function of the autopilot has failed. Upon disconnect, be prepared to accept the out-of-trim forces. Elevator (ELE) mistrim annunciations may also be displayed on the PFDs.

  • Page 77: Flashing Amber Afcs Mode Annunciation

    Model 560XL Section III – Operating Procedures Abnormal Procedures FLASHING AMBER AFCS MODE ANNUNCIATION  Abnormal mode transitions (those not initiated by the pilot or by normal sequencing of the AFCS) will be annunciated by flashing the disengaged mode in amber on the PFD. Upon loss of a selected mode, the system will revert to the default mode for the affected axis, either ROL or PIT.

  • Page 78: Inaccurate Flight Director Display

    Model 560XL Section III – Operating Procedures Abnormal Procedures INACCURATE FLIGHT DIRECTOR DISPLAY  Indicated by one or both Flight Directors commanding attitude contrary to the intended flight path. 1. AP YD DISC/TRIM INT button – PRESS and RELEASE if AP is engaged. 2.

  • Page 79: Alt Miscompare

     ALT Annunciator displayed This message is displayed on both PFDs when the G5000 detects a difference of 200 feet or greater between the pressure altitude output of air data computer 1 and air data computer 2. The G5000 comparison is of uncorrected pressure altitude, i.e. the barometric setting of the pilot and co-pilot altimeters will not affect the comparison.

  • Page 80: Pitch Miscompare

    PITCH MISCOMPARE  PIT Annunciator displayed This message is displayed on both PFDs when the G5000 detects a difference of greater than 5° between the pilot’s and copilot’s pitch attitude. 1. Autopilot will be inoperative. 2. Refer to Standby Flight Display to determine which PFD is providing the most accurate data.

  • Page 81: Heading Miscompare

     HDG Annunciator displayed This message is displayed on both PFDs when the G5000 detects a difference of greater than 6° between the pilot’s and copilot’s heading. 1. Refer to the standby flight Display to determine which AHRS is providing the most accurate heading information.

  • Page 82: Vdi Miscompare

     VDI Annunciator displayed during Baro VNAV Approach The G5000 system is capable of providing an automatically generated and temperature compensated glidepath on certain RNAV approaches when SBAS is not available. This automatically generated glidepath depends on temperature input from the air data computers to function properly If a difference in temperature compensated altitudes from the two air data computers differs by more than 50 feet, the VDI Miscompare annunciator will be displayed on both PFDs.

  • Page 83: Loss Of Atc Altitude Reporting

    Model 560XL Section III – Operating Procedures Abnormal Procedures LOSS OF ATC ALTITUDE REPORTING  1. Verify selected transponder is in AUTO, TA ONLY, or ALT mode. NOTE When transponder is in ALT mode, TCAS will be in standby. No traffic will be displayed, and no TAs or RAs will be issued.

  • Page 84: Mfd Failure

    Model 560XL Section III – Operating Procedures Abnormal Procedures MFD FAILURE  MFD failure is indicated by a complete loss of image on the center display. If only individual elements of the display are failed, refer to appropriate procedures for the individual failures. To select reversionary display of composite primary flight instruments and engine instruments on PFD 1 and/or PFD 2: 1.

  • Page 85: Dual Gtc (Touch Screen Controller) Failure

    Model 560XL Section III – Operating Procedures Abnormal Procedures DUAL GTC (TOUCH SCREEN CONTROLLER) FAILURE  1. TOUCH CTRL 1 (PRIM) Circuit Breaker (LH Panel – AVIONICS) – IN. 2. TOUCH CTRL 1 (SEC) Circuit Breaker (RH Panel – AVIONICS) – IN. 3.

  • Page 86: Dual Gps/Sbas Failure

    Model 560XL Section III – Operating Procedures Abnormal Procedures DUAL GPS/SBAS FAILURE  or GPS LOI Displayed on HSI NO FMS POSITION MAY BE DISPLAYED ON NAVIGATION MAP  IF ALTERNATE NAVIGATION SOURCES (ILS, LOC, VOR, DME, ADF) ARE AVAILABLE: 1.
  • Page 87 During a GPS LPV, LNAV/VNAV, or LNAV+V approach, if the horizontal or vertical alarm limits are exceeded, the G5000 System will downgrade the approach. This will be annunciated in the System Messages window and by an annunciation change on the HSI from LPV, L/VNAV, or LNAV+V to LNAV.
  • Page 88 Model 560XL Section III – Operating Procedures Abnormal Procedures AUDIO (GMA) FAILURE  Audio panel failure may be indicated by a GMA 1/2 FAIL System Message or the inability to communicate using the affected audio processor. This failure may also be accompanied by the loss of some aural warnings such as Altitude Alert, Autopilot Disconnect, TAWS, and Traffic alerts.

  • Page 89: Failed Airspeed, Altitude, And/Or Vertical Speed

    Model 560XL Section III – Operating Procedures Abnormal Procedures FAILED AIRSPEED, ALTITUDE, AND/OR VERTICAL SPEED  RED "X" on PFD airspeed, altitude, and/or amber “X” on vertical speed indicator This indicates a loss of valid air data computer information from the respective air data computer. If airspeed or altitude is failed, the digital values will be removed, and a red “X”...

  • Page 90: Failed Attitude And/Or Heading

    Model 560XL Section III – Operating Procedures Abnormal Procedures FAILED ATTITUDE AND/OR HEADING  Red "X" over PFD attitude and/or heading display This indicates a loss of pitch, roll, and/or heading information from AHRS. In-flight, failure of one AHRS will cause the system to automatically display the output from the other operative AHRS.
  • Page 91 Model 560XL Section III – Operating Procedures Abnormal Procedures NOTE The following caution/warnings remain active with the engine display parameter failure:  LO FUEL LEVEL L & R  FUEL GAUGE L & R – Disabled when FUEL QTY circuit breaker is open, failed fuel quantity sensor(s) or signal conditioner.

  • Page 92: Eng Display Fault

    Model 560XL Section III – Operating Procedures Abnormal Procedures ENG DISPLAY FAULT  ENG DISPLAY FAULT CAS message displayed This indicates that there may be an error in the display of N , ITT, and/or fuel quantity. 1. PFD 1 SWITCH (DISPLAY FORMAT PANEL) – SELECT REV to display engine gauges for comparison.

  • Page 93: Mfd Fault

    Model 560XL Section III – Operating Procedures Abnormal Procedures MFD FAULT  MFD FAULT CAS message displayed This indicates that there may be an error in the MFD graphics processing of pitch attitude, roll attitude, and/or altitude on the MFD. The MFD must be in reversionary display mode for this message to display.

  • Page 94: Loss Of Vor / Ils / Loc / Gs Deviation Indicators

    Model 560XL Section III – Operating Procedures Abnormal Procedures LOSS OF VOR / ILS / LOC / GS DEVIATION INDICATORS  This indicates a loss of data from the selected NAV source. This may be indicated by an amber X on the HSI navigation presentation, or it may be indicated by no CDI deviation bar (no lateral course deviation indication) or no glideslope deviation indicator.

  • Page 95: Both On Att/Hdg1, Both On Att/Hdg2

    Model 560XL Section III – Operating Procedures Abnormal Procedures BOTH ON ATT/HDG1, BOTH ON ATT/HDG2  BOTH ON ATT/HDG1 BOTH ON ATT/HDG2 Annunciator displayed This message is displayed on both PFDs and indicates that both pilot and copilot PFDs are displaying data from the same Attitude Heading Reference System.

  • Page 96: Transponder Fail 1-2

    Model 560XL Section III – Operating Procedures Abnormal Procedures TRANSPONDER FAIL 1-2  FTRANSPONDER FAIL 1-2F CAS message displayed This CAS message indicates that a failure of both transponders has been detected. This message will only display when airborne. 1. XPDR 1 and XPDR 2 Circuit Breakers (RH Panel) – IN. 2.

  • Page 97: Ads-B Out Transmission Fail

     The G5000 system transmits ADS-B OUT messages using the selected ATC transponder. If the G5000 system is unable to transmit ADS-B OUT messages, one or both of the following messages will post as a system message on both GTCs: “XPDR1 ADS-B FAIL.

  • Page 98: Check Runway Surfacewatch Alert (During Takeoff)

    IF AIRCRAFT POSITION AND RUNWAY ASSIGNMENT ARE NOT CORRECT OR CANNOT BE DETERMINED: 2. Takeoff – ABORT. 3. Enter correct origin, runway, and required takeoff distance into the G5000 system: a. From the GTC Home screen: Perf – Takeoff Data. Procedure completed CHECK RUNWAY SURFACEWATCH ALERT (DURING LANDING) ...

  • Page 99: Surfacewatch Inhibited

    SURFACEWATCH INHIBITED SurfaceWatch will remain inhibited until manually un-inhibited by the crew, or a power-cycle of the system. After a shutdown of the G5000 system, SurfaceWatch will return to its normal state of operation and will not be inhibited. SURFACEWATCH FAIL ...
  • Page 100 Model 560XL Section III – Operating Procedures Abnormal Procedures TAWS N/A OR TAWS FAIL  TAWS N/A or TAWS FAIL Annunciator displayed 1. If one of these annunciators are displayed on the PFD and MFD, the system will no longer provide Forward Looking Terrain Avoidance functions (FLTA), Premature Descent Alerting (PDA), or display relative terrain elevations.
  • Page 101 Model 560XL Section III – Operating Procedures Abnormal Procedures FUEL IMBALANCE  FUEL IMBALANCE CAS message displayed A 400 LB or greater fuel imbalance exists between the left and right fuel tank. 1. FUEL CROSSFEED – CONSIDER use to correct fuel imbalance. Procedure completed P/S HEATER L OR R (PITOT-STATIC HEATER FAILURE) ...
  • Page 102 Model 560XL Section III – Operating Procedures Abnormal Procedures This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 3-60 FAA Approved...
  • Page 103 Model 560XL Section III – Operating Procedures Normal Procedures Normal Procedures Table of Contents Cockpit Inspection or Preliminary Cockpit Inspection ................3-63   Cockpit Preparation ..........................3-63   Before Taxi ............................... 3-63   Before Takeoff ............................3-64   After Landing ............................3-64  ...
  • Page 104 Model 560XL Section III – Operating Procedures Normal Procedures SELCAL ..............................3-80   SPEAKER OFF ............................3-80     Textron Aviation Citation 560XL 190-02313-03 Rev. 8 3-62 FAA Approved...

  • Page 105: Cockpit Inspection Or Preliminary Cockpit Inspection

    TAKEOFF. BEFORE TAXI This procedure is unchanged with the installation of the G5000 system, except for an addition of a fuel on board update for aircraft equipped with the optional TOLD (takeoff and landing data) system. For each takeoff, prior to calculating TOLD takeoff data: 1.

  • Page 106: Before Takeoff

    Normal Procedures BEFORE TAKEOFF This procedure is unchanged with the installation of the G5000 system, except for the update to the Transponder/TCAS modes listed below, and an additional confirmation of Takeoff Speeds. 1. Transponder/TCAS – No action required when operating in AUTO mode.

  • Page 107: Altitude Hold (Alt) Mode, Manual Capture

    VNAV function is available for climbs, enroute, and terminal descents. Vertical navigation is not available between the final approach fix (FAF) and the missed approach point (MAP). See the G5000 Citation 560XL Pilot’s Guide, 190-02537-02, for detailed information about the VNAV function.
  • Page 108 Model 560XL Section III – Operating Procedures Normal Procedures director will capture the VNAV reference altitude. ALTS will be the armed mode during the climb if the altitude preselect is set at or below the VNAV reference altitude, indicating that the autopilot / flight director will capture the altitude preselect altitude reference. VNAV Profile Descent 1.

  • Page 109: Lateral Modes

    Model 560XL Section III – Operating Procedures Normal Procedures LATERAL MODES Heading Mode (HDG) 1. HDG Knob – PUSH to sync heading bug to current heading. 2. HDG BUTTON – PUSH, green ‘HDG’ annunciated. 3. HDG Knob – ROTATE to set heading bug to desired heading. Navigation (VOR) 1.

  • Page 110: Approaches

    Normal Procedures APPROACHES The G5000 is capable of performing many tasks for the pilot to reduce pilot workload during the approach and landing phases of flight. The G5000 system references the Flight Plan programmed into the G5000 FMS to predict the pilot’s intended actions. Time permitting, the pilot should keep the Flight Plan updated with the destination airport and the instrument approach to be flown.

  • Page 111: Ils Approach, Glide Slope Inoperative

    GA (Go Around) button (on either thrust lever) – PRESS, execute missed approach procedure. ILS Approach, Glide Slope Inoperative 1. Load the approach into the Active Flight Plan – VERIFY G5000 tunes the proper ILS frequency 2. Approach Minimums – SET on GTC PROC page. ...

  • Page 112: Rnav (Gps) (Lpv Or Lnav/Vnav) Approach

    VNAV operation with automatic temperature compensation on the final approach segment. The approach baro VNAV glidepath may be intercepted and flown in the same manner as an SBAS generated glidepath. Refer to the G5000 Pilot’s Guide, 190-02537-02, for additional information on manually applying temperature compensation to other segments of an approach and approach minima.

  • Page 113: Rnav (Gps) (Lnav, Lp, Lnav + V) Approach

    Model 560XL Section III – Operating Procedures Normal Procedures  If Flying Full Approach Including Transition: 3. When cleared to an initial approach fix: a. ACTIVATE THE APPROACH from the PROC page, ACTIVATE a DIRECT TO the IAF b. HSI CDI – PRESS Active NAV softkey to select FMS navigation source. c.
  • Page 114 Model 560XL Section III – Operating Procedures Normal Procedures  If Flying Full Approach Including Transition: 3. When cleared to an initial approach fix: a. ACTIVATE THE APPROACH from the PROC page. ACTIVATE a DIRECT TO the IAF. b. HSI CDI – PRESS Active Nav softkey to select FMS navigation source. c.

  • Page 115: Vor Approach

    GA (Go Around) button (on either thrust lever) – PRESS, execute missed approach procedure. VOR Approach 1. Load the approach into the Active Flight Plan – VERIFY G5000 tunes the proper VOR frequency 2. Approach Minimums – SET on GTC PROC page. ...

  • Page 116: Back Course (Bc) Approach

    GA (Go Around) button (on either thrust lever) – PRESS, execute missed approach procedure. BACK COURSE (BC) Approach 1. Load the approach into the Active Flight Plan – VERIFY G5000 tunes the proper LOC frequency. 2. Approach Minimums – SET on GTC PROC page. ...
  • Page 117 Model 560XL Section III – Operating Procedures Normal Procedures  If Flying Full Approach Including Transition: 3. When cleared to an initial approach fix: a. ACTIVATE THE APPROACH from the PROC page. ACTIVATE a DIRECT TO the IAF. b. HSI CDI – PRESS Active NAV softkey to select FMS navigation source. c.

  • Page 118: Go-Around (Ga), Not Autopilot Coupled - Aircraft Not Equipped With Usp

    NOTE The pilot is responsible for initial missed approach guidance in accordance with published procedure. The G5000 may not provide correct guidance until the aircraft is established on a defined leg of the procedure. 5. Altitude Preselect – VERIFY set to appropriate altitude.

  • Page 119: Autopilot Coupled Go-Around (Ga) - Aircraft Equipped With Usp

    NOTE The pilot is responsible for initial missed approach guidance in accordance with published procedure. The G5000 may not provide correct guidance until the aircraft is established on a defined leg of the procedure. During a single-engine autopilot coupled go-around, the autopilot will attempt to hold wings level in the “GA”...

  • Page 120: Taws Functions

    Model 560XL Section III – Operating Procedures Normal Procedures 2. If flying the entire instrument approach procedure, activate a DIRECT TO the desired initial waypoint or ACTIVATE the approach procedure. Follow the appropriate procedure for the instrument approach being flown. ...

  • Page 121: Flap Override

    Model 560XL Section III – Operating Procedures Normal Procedures Flap Override FLAP OVR When intentionally landing with flaps in other than the LAND position, the FLAP OVERRIDE function should be selected to inhibit GPWS alerting. 1. On the GTC, select the TAWS Settings page. 2.
  • Page 122 Model 560XL Section III – Operating Procedures Normal Procedures 2. Steep Approach – TOUCH. 3. VERIFY the STEEP APR annunciations are removed from both PFDs. Procedure completed SELCAL SELCAL VHF 1 (2) (3) CAS message displayed This CAS message indicates the SELCAL system has received a VHF radio transmission from the indicated VHF COM radio (1, 2, or 3) with the airplane specific tone sequence.
  • Page 123 Model 560XL Section III – Operating Procedures Operating Information Operating Information Table of Contents Operating Information ..........................3-83   Electrical System ..........................3-83   Traffic Collision Avoidance System (TCAS II) ..................3-84   Takeoff and Landing Data – TOLD (Optional) ..................3-87  ...
  • Page 124 Model 560XL Section III – Operating Procedures Operating Information This page intentionally left blank. Textron Aviation Citation 560XL 190-02313-03 Rev. 8 3-82 FAA Approved...

  • Page 125: Operating Information

    If the battery switch is selected to EMER and no generators are online, power is not available to the Warning and Test system which operates all G5000 CAS messages replacing the previous annunciator panel lights. While operating in EMER, power is not available to the electric windshield, aural warnings, Master Warning, Master Caution and Fire annunciators.

  • Page 126: Traffic Collision Avoidance System (Tcas Ii)

    Traffic Collision and Avoidance System is an independent airborne system. It is designed to act as a back-up to the Air Traffic Control system and the “see and avoid” concept. See the G5000 Pilot’s Guide 190-02537-02 for additional information regarding the control and display of the TCAS system on the G5000.
  • Page 127 AIRPLANES WITHOUT OPERATING TRANSPONDERS. TCAS generates a traffic map display of nearby airplanes that may be displayed on the MFD and PFDs. See the G5000 Pilot’s Guide 190-02537-02 for additional information regarding the control of TCAS displays on the G5000 system.
  • Page 128 Model 560XL Section III – Operating Procedures Operating Information If high speed buffet is encountered when initially responding to an RA, relax pitch force as necessary to reduce buffet, but still continue to maneuver to the TCAS pitch command. If stall warning occurs during an RA maneuver, immediately abandon the RA and execute stall recovery procedures.

  • Page 129: Takeoff And Landing Data - Told (Optional)

    Speed Bugs page. The TOLD database part number is displayed on the PERF page on either GTC. Refer to Garmin G5000 Integrated Avionics System Pilot’s Guide for more information. 190-02313-03 Rev. 8 Textron Aviation Citation 560XL...

  • Page 130: Stabilized Approach (Optional)

    Model 560XL Section III – Operating Procedures Operating Information Stabilized Approach (Optional) The Stabilized Approach feature provides aural annunciations to notify the crew of unstable conditions during an instrument or visual approach to a designated landing runway. The feature monitors flap and gear position, lateral and vertical deviation on an instrument approach, airspeed relative to the posted approach speed, and sink rate.
  • Page 131 Stabilized approach alerts may be inhibited by pressing the Stabilized APPR Inhibit button on the Utilities – Setup – Avionics Settings page under the Alerts tab. Refer to Garmin G5000 Integrated Avionics System Pilot’s Guide for more information. 190-02313-03 Rev. 8...

  • Page 132: Cold Weather Operations

    Model 560XL Section III – Operating Procedures Operating Information Cold Weather Operations If the aircraft is exposed to ground ambient temperatures below -40° C (-40° F) with the BATT and AVIONIC POWER switches off, the cockpit and nose avionics bay must be warmed to -40° C (-40° F) or above with BATT and AVIONIC POWER switches turned on for at least 30 minutes prior to takeoff.
  • Page 133 Model 560XL Section IV – Performance Section IV – Performance No Change. Refer to basic Aircraft Flight Manual or appropriate supplement. 190-02313-03 Rev. 8 Textron Aviation Citation 560XL FAA Approved...
  • Page 134 Model 560XL Section IV – Performance Intentionally Left Blank Textron Aviation Citation 560XL 190-02313-03 Rev. 8 FAA Approved...
  • Page 135 Model 560XL Section VI – Weight and Balance Section VI – Weight and Balance No change to loading information. Refer to current weight and balance report for changes to empty weight, moment, and center of gravity. 190-02313-03 Rev. 8 Textron Aviation Citation 560XL...
  • Page 136 Model 560XL Section VI – Weight and Balance Intentionally Left Blank Textron Aviation Citation 560XL 190-02313-03 Rev. 8...
  • Page 137 General ............................... A-3   G5000 Integrated Avionics ......................... A-3   System Overview ............................ A-3   G5000 GTC System Messages ......................A-4   Instrument Panel ............................ A-4   Warning And Test System ........................A-4   Figure A-1, Instrument Panel ......................... A-5  ...
  • Page 138 Model 560XL Appendix – Systems Description Figure A-4, Left Circuit Breaker Panel ....................A-18   Figure A-5, Right Circuit Breaker Panel ....................A-19   Lighting Systems ............................A-19   Cockpit ..............................A-19   Dimming Panel .............................A-19   Display Format Selections ........................A-20   PFDs ..............................A-20  ...

  • Page 139: General

    COM and NAV radios, XM music, and the pilot’s intercom, is normally controllable through both GTCs. The G5000 incorporates a fully digital integrated autopilot and flight director. Pilot interface to the AFCS is through the GMC 7200 Autopilot Mode controller mounted in the center of the cockpit just below the airplane’s glareshield.

  • Page 140: G5000 Gtc System Messages

    Instrument Panel The G5000 Instrument Panel consists of two 14 inch LCD Primary Flight Displays, one 14 inch LCD Multi-Function Display, autopilot / flight director mode control panel, two 5.7” touch screen controllers, two GCU 275 PFD controllers, and a standby attitude and air data instrument.
  • Page 141 Model 560XL Appendix – Systems Description Figure A-1, Instrument Panel 190-02313-03 Rev. 8 Textron Aviation Citation 560XL...
  • Page 142 Model 560XL Appendix – Systems Description Figure A-2, Pilot’s Control Wheel Copilot’s wheel is similar but reversed. Textron Aviation Citation 560XL 190-02313-03 Rev. 8...
  • Page 143 Model 560XL Appendix – Systems Description Figure A-3, Center Pedestal Panels Typical arrangement 190-02313-03 Rev. 8 Textron Aviation Citation 560XL...

  • Page 144: Automatic Flight Control System

    Automatic Flight Control System AFCS: Autopilot and Flight Director The Automatic Flight Control System (AFCS) is fully integrated within the G5000 System avionics architecture. The G5000 includes a three-axis autopilot and flight director system which provides the pilot with the following features: Autopilot (AP) —...
  • Page 145 Model 560XL Appendix – Systems Description CAUTION Setting the battery switch to EMER with dual generator failure or both generators set to OFF will cause the autopilot to abnormally disconnect and the yaw damper to disconnect. An abnormal autopilot disconnect is normally annunciated visually by a red flashing ‘AP’ in the PFD FD mode window and a continuous “AUTOPILOT”...
  • Page 146 Model 560XL Appendix – Systems Description The following tables list the available AFCS vertical and lateral modes with their corresponding controls and annunciations. The mode reference is displayed next to the active mode annunciation for Altitude Hold, Vertical Speed, and Flight Level Change modes. The NOSE UP/DN Wheel can be used to change the vertical mode reference while operating under Pitch Hold, Vertical Speed, or Flight Level Change Mode.
  • Page 147 Model 560XL Appendix – Systems Description Table A-2, AFCS Lateral Modes Maximum Roll Lateral Mode Control Annunciation Command Limit 27° Left Bank Roll Mode (default) 27° Right Bank 15° Left Bank Low Bank BANK Key 15° Right Bank 27° Left Bank Heading Select HDG Key 27°...

  • Page 148: Underspeed Protection (Optional

    Model 560XL Appendix – Systems Description Underspeed Protection (Optional) Underspeed Protection (USP) is an optional feature that provides a level of protection against the aircraft stalling while the autopilot is engaged. If the autopilot is not engaged, Underspeed Protection will not activate.

  • Page 149: Afcs System Status Annunciations

    Manual Electric Elevator Trim Manual electric elevator trim is an integrated function included with the G5000 system. The electric elevator trim can be operated manually by the pilot using the pitch trim switches on either control wheel, or automatically by the autopilot.

  • Page 150: G5000 Flight Instruments

    % (turbine speed), oil pressure and temperature, fuel flow, and fuel quantity and temperature. The engine transducers send their signals to the Garmin GEAs (Engine and Airframe LRU) which process the signals and allow the engine parameters to be displayed on the MFD. Two GEAs are installed to provide independent display of parameters for each engine.

  • Page 151: Ground Communications

    GSD 2 ATC Data Link System (CPDLC) and ACARS (Optional) The G5000 installation may include an optional GDR 66 digital radio and an optional GSR 56 Iridium satellite radio (powered by the IRIDIUM ATS circuit breaker). With the proper software enablements, they may be used for FANS 1/A +, FAA Data Comm, Link 2000+, and ACARS functions.

  • Page 152: Synthetic Vision

    The Synthetic Vision Technology (SVT) sub system is dependent upon terrain data provided by the underlying G5000 system. If, for some reason, the terrain data is not available from the G5000, all of the components of the SVT will be unavailable. The flight path marker, flight path angle reference, horizon heading, and airport signs are all sub-components of the Synthetic Terrain display.

  • Page 153: Traffic

    UNTIL PAST THE TERRAIN OR OBSTACLE. Traffic If traffic that is within the SVT field of view is detected by the G5000 system, a symbol will be displayed on the PFD indicating the direction and relative altitude of the traffic. The traffic symbol size will increase as the traffic gets closer to give the pilot a sense of relative distance to the threat aircraft.

  • Page 154: Electrical System

    GPS position data has been lost. The autopilot and/or flight director may be coupled in FMS mode while the system is in Dead Reckoning mode up to 20 minutes. Refer to the G5000 Pilot’s Guide for further information. Revert to an alternate means of navigation appropriate to the route and phase of flight.

  • Page 155: Lighting Systems

    A Display Format and Dimming panel (DFD) is located on the center pedestal which contains five dimming controls for the G5000 displays. See Figure A-3 of this AFMS. These controls are labeled PFD 1, MFD, PFD 2, GTC 1, and GTC 2. These dimming controls will be activated and will control the display brightness when the PANEL LIGHT switch on the pilot’s instrument panel is set to ON.

  • Page 156: Display Format Selections

    These messages are not applicable to the G5000 system. The G5000 CAS messages are typically displayed on the MFD, but can be displayed on one or both PFDs if their switches on the Display Format and Dimming Panel are set to REV (reversionary).
  • Page 157 Model 560XL Appendix – Systems Description Table A-4, Listing of CAS Messages CAS Message Color Procedure UNDERSPEED PROT ACTIVE Emergency ADC 1 (2) FAULT Amber Abnormal AOA FAIL Amber Abnormal AP PITCH TRIM FAIL Amber Abnormal AVIONICS FAULT Amber Abnormal ENG DISPLAY FAULT Amber Abnormal...

  • Page 158: Rotary Test Switch

    Model 560XL Appendix – Systems Description Rotary Test Switch Several test indications have changed with the installation of the G5000 system. The updated rotary test indications are listed in Table A-5 below. Table A-5, Rotary Test Indications Rotary Test Switch Position Indication No change with installation of G5000 system.

Table of Contents